A multi-star scientific research station landing hierarchical isolation lunar dustproof airlock transition cabin matched with a nested box and a flexible sealing inner liner

Abstract

A multi-planetary research station landing tiered isolation and lunar dust-proof airlock transition chamber with nested enclosures and flexible sealing liners belongs to the field of deep space landing and accommodation equipment technology. Addressing the shortcomings of existing planetary landing airlock structures—poor dustproof sealing, weak adaptability to cross-planetary conditions, and dust leakage during the transition between inner and outer chambers contaminating the research module—this invention uses a double-layered nested enclosure as the tiered isolation body. The nesting gaps are fitted with a self-adaptive flexible sealing liner, dividing the space into multiple independent pressure buffer isolation chambers along the passage direction. Each isolation chamber is independently equipped with a dust removal and blowing mechanism and a partitioned sealing door. The flexible sealing liner fills the assembly gaps of the nested enclosures and adaptively deforms to seal the gaps when the inner nested enclosure is pulled out. This invention achieves a stepped pressure transition through a nested layered structure, and the flexible liner provides a full-area seal to prevent the diffusion of lunar and interplanetary dust across chambers. It is suitable for use on lunar and terrestrial planetary research stations without atmospheres, offering high dustproof isolation reliability and strong sealing adaptability, effectively preventing interplanetary dust from intruding into the station's core.

Description

Technical Field

[0001] This invention belongs to the field of aerospace deep space exploration technology, specifically relating to scientific station equipment suitable for multi-planet exploration missions such as the Moon, Mars, and Earth. In particular, it discloses a multi-planet scientific station landing graded isolation lunar dust-proof airlock transition cabin with nested box body and flexible sealed inner lining, which can be used for in-situ scientific exploration of extraterrestrial bodies and short-term stay scientific research operation equipment design. Background Technology

[0002] The extreme and harsh environments on the Moon and many other extraterrestrial surfaces, characterized by high vacuum, extreme diurnal temperature variations, intense cosmic radiation, highly reactive fine lunar dust, and the absence of an atmosphere, represent core technological bottlenecks restricting human deep space habitation, scientific exploration, and the initial construction of extraterrestrial bases. In the early stages of lunar base construction, the critical phases of astronauts' first lunar landing, the establishment of the research station, the docking of the module, and the creation of a sealed, habitable environment place stringent demands on the space expansion capabilities of the stationing equipment, its protection against lunar dust, its environmental creation capabilities, the ease of docking and assembly, the reliability of equipment operation, and its low operational complexity. Existing lunar research stations and airlock transition modules mostly employ integrated rigid module structures with fixed overall volumes and low compression ratios. Strictly limited by the launch envelope and payload weight of the launch vehicle, they cannot achieve post-landing space expansion and are ill-suited to the initial station construction needs of a lunar base that starts from scratch, expands step-by-step, and gradually develops research and living space. Meanwhile, existing airlock dust protection systems are rudimentary, mostly relying on single-layer door seals for basic isolation, lacking multi-level progressive structures for lunar dust interception, adsorption, and isolation, and lacking dedicated spacesuit dust cleaning and removal structures. During astronaut entry and exit, equipment transfer, and docking, fine lunar dust can easily be carried into the main research module by airflow and personnel, causing wear on sealing structures, blockage of pipelines and valves, contamination of environmental control equipment, and deterioration of the research environment, seriously affecting the safety of long-term stays and the lifespan of equipment. Existing conventional lunar stay equipment has a rudimentary environmental support system, mostly possessing only basic airtight functions, lacking integrated in-situ hydrogen and oxygen preparation, closed temperature control, and water storage equipment. It cannot autonomously construct a stable temperature and humidity environment with breathable gases under the extreme conditions of the lunar surface, where there is no atmosphere and no native habitable environment. Its independent habitability and self-sufficiency are weak, highly dependent on ground resupply, and unsuitable for long-term deep space research missions. Furthermore, existing lunar module docking and assembly systems are complex, mostly relying on fully automated alignment sensors, multi-electronic control linkage programs, and high-precision automatic matching mechanisms to complete docking and locking. These systems involve numerous sensors and cumbersome automatic control logic. Under the strong radiation, electromagnetic interference, and temperature drift distortion environment of the moon, automated docking systems are prone to signal deviations, alignment failures, and program malfunctions. Moreover, fully automated docking equipment has multiple operational levels and complex debugging, making lunar surface operations cumbersome, involving numerous actions and having low fault tolerance. This is detrimental to the rapid, lightweight, and low-difficulty completion of base construction and module sealing docking during the initial landing phase. Additionally, existing lunar surface environmental control auxiliary equipment generally incorporates automatic threshold linkage, semi-automatic program control, and sensor closed-loop autonomous operation logic, resulting in a high degree of system autonomy. Under the complex lunar environment, this can easily lead to safety hazards such as uninstructed erroneous heating, erroneous gas production, erroneous purging, and erroneous valve opening and closing. During the initial base construction and commissioning phase, manual operation is limited in freedom, controllability is poor, and overall system stability is insufficient.In summary, existing airlock equipment for the first lunar landing and station construction generally suffers from a series of technical defects, including: non-expandable cabin, limited living and research space, single-level lunar dust isolation with weak dust removal capabilities, inability to autonomously create a habitable environment, cumbersome and difficult docking and assembly operations, malfunctioning and unreliable automatic control systems, and low efficiency of manual station construction. These defects make it difficult to meet the actual engineering requirements of initial landing, rapid station construction, low operational burden, and highly reliable long-term stationing on the lunar base. Summary of the Invention

[0003] The technical problem this invention aims to solve is as follows: Existing multi-planet scientific research airlock transition modules suffer from drawbacks such as rigid bodies that cannot be expanded, poor single-layer sealing for lunar dust protection, susceptibility of automated control systems to malfunctions due to extreme environmental interference, cumbersome docking and assembly operations, and high difficulty for astronauts in setting up the module. The purpose of this invention is to provide a multi-planet scientific station landing, tiered isolation, and lunar dust protection airlock transition module with a nested box body and a flexible sealing liner. This achieves expandable module space, multi-level tiered isolation from lunar dust, simplified docking and assembly operations, and reduced operational difficulty for astronauts. It also employs remote wireless control from Earth and on-site manual control by astronauts for the start, stop, movement, and docking operations of the airlock transition module. A supporting environmental media treatment auxiliary system provides a purely manual control system without automatic / semi-automatic programs, improving the operational reliability of equipment used for long-term lunar deployment.

[0004] Multi-level nested isolation structure: The landing module adopts a multi-level nested box-type layered structure, with three levels of independent sealed compartments arranged from the outside to the inside: an external transition dust removal compartment (outer compartment of the inner box), an intermediate isolation buffer compartment (inner compartment of the inner box), and an internal sealed docking compartment (flexible sealed inner lining compartment between the outer and inner boxes). Each compartment is independent of the others and can be sealed, depressurized, and ventilated independently, forming a multi-layered physical isolation barrier. Each compartment is equipped with an independent and controllable sealed door, enabling segmented personnel and material passage and preventing direct passage between the landing module and the main research station in a single operation. This physically blocks the inward diffusion of lunar dust step by step.

[0005] The graded matching dust removal system is configured with corresponding dust removal equipment for each of the three nested compartments, forming a gradient dust removal system: the outer transition compartment (outer compartment of the inner box) is equipped with a high-volume blowing dust removal + coarse particle adsorption dust removal component to remove large particles and floating lunar dust from spacesuits and equipment surfaces; the middle isolation compartment (inner compartment of the inner box) is equipped with electrostatic adsorption dust removal + fine particle filtration dust removal to capture suspended ultrafine charged lunar dust and remove residual micro dust on the surface; the internal sealed docking compartment (flexible sealed inner liner compartment between the outer box and the inner box) is equipped with high-precision HEPA fine filtration dust removal + internal micro-positive pressure dust control structure to create a dust-free buffer environment.

[0006] A multi-planetary research station landing, hierarchical isolation, and lunar dust-proof airlock transition chamber with a nested box structure and a flexible sealing liner includes an outer box, an inner box, and a flexible sealing liner. The inner box is internally divided into independent outer compartments, inner compartments, and an internal sealed docking compartment by a sealing thin plate. The outer compartments are coarse dust removal stations, equipped with spacesuit dust removal and cleaning equipment. The spacesuit dust removal and cleaning equipment incorporates a high-volume blowing component and a coarse particle adsorption and dust removal component. The high-volume blowing component outputs a high-speed airflow to peel off the spacesuit. Large, loose lunar dust particles adhering to the surface of the detection equipment are instantly captured and blown off by the coarse particle adsorption and dust removal components, preventing the dust from spreading inwards. The inner compartment is a fine dust removal station, equipped with electrostatic adsorption dust removal components and fine particle filtration dust removal components. The electrostatic adsorption dust removal components create an electrostatic field to capture suspended ultrafine charged lunar dust, while the fine particle filtration dust removal components intercept neutral ultrafine particles. Together, they remove residual micro-dust from the workpiece and spacesuit surface. The inner sealed docking compartment is a dust-free buffer station, equipped with high-precision HEPA fine filtration dust removal components and an internal micro-positive pressure dust control mechanism. Clean air filtered by HEPA is continuously introduced into the compartment, maintaining a micro-positive pressure state and preventing backflow of dusty airflow from the outside, forming a dust-free transfer buffer environment. Each compartment is sealed and fixed to the top plate, bottom plate, and side plates with thin plates of 2-15mm thickness, and combined with flexible sealing liners to achieve graded airtight isolation between compartments and between the inner and outer chambers, preventing lunar dust from crossing the cavity.

[0007] Adaptive structure for initial construction and operation of the base: A standardized transition process structure for initial cabin entry, with each compartment equipped with an adaptive control module optimized for astronauts' first cabin entry and stay. This allows for gradual adjustment of cabin pressure, temperature, humidity, and atmospheric composition during the initial cabin entry process, preventing sudden environmental changes from impacting the astronaut's body and cabin equipment. Simultaneously, it locks in the initial cabin entry path, dust removal process, and sealing logic, standardizing the initial entry operation process and eliminating safety hazards caused by initial operational errors.

[0008] Initial Transitional Operation Adaptation System for the Base: This structure is adapted to the transitional phases of the lunar research station's construction and initial operation, and is compatible with all initial operational scenarios, including initial power-on, initial commissioning, initial gas circulation, and initial equipment trial operation. Through transitional buffer control, adaptive operating condition adaptation, and initial fault-tolerant design, it solves the technical challenges of traditional landing modules being unable to adapt to the transitional operation of a newly built base, enabling the research station to smoothly transition from the construction phase to the normalized research and operation phase.

[0009] The radio transmitting and receiving devices, the dual-mode electric motion system that enables remote control from Earth and on-site control by astronauts on the lunar surface, the sealing valves, barometers, electronic barometers, rotating motors, high-pressure carbon dioxide gas injection devices, electromagnetic sealing valves, camera components, and the signal transmission, electrical connections, and linkage control structures between compartments and between various devices carried by this landing module all adopt mature and publicly available technologies from existing lunar landing modules and lunar research stations, without structural modifications, principle innovations, or functional improvements.

[0010] In this embodiment, the substrate of the container is made of carbon fiber composite material (or aluminum alloy), and its molding process, structural parameters, and mechanical properties all adopt existing publicly available technologies in the field. The inner lining of the container uses a mature flexible sealing gasket, the material, sealing principle, and assembly method of which are all existing technologies. The specific improvements of this invention are: the multi-cavity arrangement structure composed of nested containers and flexible sealing linings, the modular locking structure, and the overall buffering and adaptation structure of the landing module, thereby realizing the multi-planet adaptation and landing function. The remaining conventional processing and sealing assembly processes all adopt existing technologies.

[0011] This invention discloses a nested box structure for a multi-planet nested scientific research station landing module, comprising an outer protective box and an inner load-bearing box. Both boxes are integrally assembled from 6mm thick aerospace-grade carbon fiber composite materials. All corners of the boxes adopt a smooth 100mm radius arc transition structure, eliminating the stress concentration defects of traditional right-angle structures. The two boxes employ a precise gradient nesting design with a large outer box and a small inner box. After assembly, the outer wall of the inner box and the inner wall of the outer box are completely flat and tightly fitted. There are no support columns, vibration isolation structures, thermal insulation layers, filling materials, or any intermediate auxiliary structures between the two boxes. The overall structure is simple, with uniform stiffness, good mechanical synchronization, and excellent thermal stress dispersion.

[0012] The aluminum alloy box is made by bending and stamping a single rectangular aluminum alloy sheet, which is then bent into the four long sides of the box. The seams are firmly welded together using friction stir welding. The gable is square in shape, with two pieces of the same size made. The middle is cut to remove the portion that would be used to install the door frame, creating a square hole to facilitate the subsequent mounting of the door frame into the square hole. The gable is then welded, riveted, and glued to ensure a secure seal. The edges of the four sides of the gable are made into a stepped shape and fastened to the ends of the four sides of the already welded box. The seams between the gable and the outer ends of the box are welded and sealed securely, as are the inner seams between the gable and the inner ends of the box.

[0013] The design of the sealed door near the edge of the gable wall allows ample space for the installation of a hinged door that can rotate at multiple angles and has a sliding cylindrical rod that engages with a groove on the gable wall. Alternatively, the door can be fitted with two fixed rods parallel to the door, with sliding sleeves on the fixed rods connected to the four corners of the inner wall of the sealed door via telescopic connecting rods. When the sealed door is pushed inward, the sliding sleeves on the fixed rods can move the sealed door to the other edge of the gable wall, thus opening the sealed door.

[0014] A cleanroom enclosure protective structure includes an outer enclosure and an inner enclosure. The inner enclosure is divided into independent inner compartments. An electrostatic adsorption dust removal component and a fine particle filtration dust removal component are installed in combination within each inner compartment. The electrostatic adsorption dust removal component generates an electrostatic field to capture ultrafine charged dust particles suspended within the compartment. The fine particle filtration dust removal component is positioned downstream of the electrostatic adsorption dust removal component to intercept neutral fine particles that penetrate the electrostatic field. The two components work in layers to simultaneously capture suspended dust in the air and blow away and peel off residual micro-dust adhering to the surface of workpieces, eliminating ultrafine dust residue inside the enclosure compartments. Furthermore, the inner compartments are sealed with a thin sealing plate and connected to the top, bottom, and side plates of the enclosure to form a closed clean space, preventing external dust from interfering with the dust removal effect.

[0015] This equipment features an internal sealed docking compartment, which is equipped with a high-grade HEPA high-efficiency fine filtration dust removal structure and a matching micro-positive pressure dust control structure. The sealed docking compartment achieves overall airtightness through a thin-plate sealing structure, and the HEPA fine filtration structure performs high-precision filtration and dust removal on the air entering the compartment. Continuous clean air supply creates a micro-positive pressure environment inside the compartment, constructing a completely isolated, stable, and clean dust-free buffer space to achieve dust-free protection during material docking and chamber opening and closing processes.

[0016] The rigid enclosure gable assembly is the core load-bearing structure of the landing module's sidewall. It is integrally molded from carbon fiber composite material or aerospace aluminum alloy, serving as a rigid load-bearing base and providing a stable assembly benchmark and impact-resistant support for the overall sealed structure. Multiple rigid gables are modularly spliced ​​to form the landing module's frame, with rigid connecting flanges (rigid connection components) at the ends of the rigid gables. The flexible sealing liner assembly is fitted and fixed to the entire outer wall of the rigid gable, serving as the core airtight sealing layer of the module. It is made of a composite elastic sealing material resistant to cosmic rays, high and low temperatures, and low compressive deformation, used to fill tiny gaps inside the module, achieving basic airtight isolation. The rigid-flexible alternating sealing and pressing mechanism adopts a three-stage alternating sealing structure layout of rigid-flexible-rigid, consisting of an inner flexible sealing liner, a middle flexible pressing and sealing layer, and an outer rigid locking and bearing layer. It is adapted to the double-interface sealing of the flexible liner and the rigid gable wall, as well as the rigid interface of the connecting components. The first-stage rigid-flexible sealing interface: a micro-deformation bonding sealing structure is set between the outer surface of the flexible sealing liner and the outer surface of the rigid gable wall, as well as the rigid interface of the connecting components. The flexible layer and the rigid substrate are bonded together without gaps through uniform pre-compression.

[0017] The second-level rigid-rigid sealing interface: A rigid pressure-bearing sealing surface is set between the rigid interfaces of the connecting components of adjacent gable walls, which, together with an embedded flexible sealing ring, fills the gap between the rigid joints. The overall system adopts an alternating rigid and flexible arrangement pattern. Flexible buffer sealing is used in areas of stress concentration in the rigid structure, while rigid limiting and tightening are used in areas of easy displacement in the flexible structure, forming a composite sealing system of graded sealing and graded load bearing. The limiting and anti-displacement fixing mechanism includes a circumferential limiting groove, an axial clamping bolt group, an elastic constant pressure compensation component, and a positioning anti-misalignment boss. The circumferential limiting groove is opened on the inner assembly surface of the rigid gable wall, and the edge of the flexible sealing liner is embedded in the limiting groove to achieve lateral anti-displacement fixing. The axial clamping bolt group penetrates the rigid connecting component and the rigid gable wall body, providing a constant axial clamping force. The elastic constant pressure compensation component is assembled between the clamping bolt and the sealing layer to offset the clamping force attenuation caused by high and low temperature deformation and vibration impact, and to compensate for the sealing clamping amount in real time. The positioning anti-misalignment boss is set on the joint end face of the rigid gable wall to ensure the alignment accuracy of multi-module assembly and avoid sealing failure caused by misassembly. Furthermore, a dot-matrix micro-protrusion sealing structure is set in the area where the flexible sealing liner and the rigid gable wall are in contact, improving the tightness of the fit between the flexible layer and the rigid surface; an annular sealing groove is opened on the mating surface of the rigid connecting components, and an aging-resistant flexible sealing ring is embedded to achieve secondary sealing reinforcement of the rigid hard contact interface. Furthermore, the rigid gable wall is selectively made of lightweight carbon fiber or high-strength aluminum alloy according to load requirements. Carbon fiber is suitable for lightweight, low-load planetary construction scenarios, while aluminum alloy is suitable for high-impact, high-load landing conditions. Both materials can be adapted and assembled with the flexible sealing liner and sealing compression mechanism. Furthermore, the alternating rigid-flexible sealing compression structure forms a dual sealing protection system: the inner layer relies on the flexible sealing liner to achieve high airtightness isolation of the cabin; the middle layer relies on the flexible compression layer to achieve deformation buffer sealing; and the outer layer relies on the rigid connecting components for locking to achieve structural fixation and pressure bearing. This rigid-flexible coupling is suitable for extreme working conditions such as vacuum, high and low temperatures, micro-vibration, and micro-impact on extraterrestrial planets.

[0018] Two aerospace-grade carbon fiber composite square tubes, measuring 10 cm x 8 cm and with a wall thickness of 1 cm, are used as longitudinal beams. Five rows of smaller square tubes of the same specifications are laid evenly on top, bonded and riveted together, and then thin flat plates are bonded to the smaller square tubes to form the overall chassis.

[0019] Two longitudinal beams are located on the outermost side of the research station's enclosure. Square channel steel with downward-facing openings is bonded and riveted to the lower part of the longitudinal beams. It can be made of aerospace-grade carbon fiber composite material. There are two large symmetrical round holes in the middle of the channel steel, which are used to install the wheels of the hub motor. The four wheels can bear a load of more than one ton. Alternatively, the large round holes of the channel steel can be used to install and fix the axles. The axles extend to the side of the enclosure to fix and install the wheels of the hub motor. This way, the wheels can be made wider to suit the lunar surface environment.

[0020] The manufacturing of the enclosure, the production of the flexible sealing liner, and the control, signal, motion, camera, and communication systems are all existing mature technologies and are not included in the content of the invention.

[0021] The landing module's sealing door is equipped with a multi-level labyrinth-style sealing structure around its periphery. The door leaf and door frame have interlocking concave and convex grooves to form a tortuous labyrinth flow channel. The labyrinth seal adopts a mature non-contact sealing structure already available in the field. This invention does not improve the tooth profile process, but only optimizes the integrated layout of the door body and the nested box body.

[0022] A wheel axle bracket is fixedly installed at the bottom of the nested container chassis. This bracket is a high-strength, rigid support structure, integrally forged and bolted to the bottom of the nested container chassis, achieving a gapless, rigid connection. It can bear the entire load of the landing module while ensuring the coaxiality and stability of the wheel axle structure during movement, preventing structural loosening, displacement, or deformation during long-term operation. An electric motion system is mounted on the wheel axle bracket. This system serves as the lunar surface walking drive mechanism for the landing module. The drive motor can be any of the following: a low-temperature brushless motor, a DC series motor, a hub motor, a low-temperature stepper motor, or an ultrasonic motor. The appropriate drive type can be matched according to the low-temperature environment, movement accuracy, load requirements, and endurance requirements of different planets, achieving precise adaptation to multiple scenarios.

[0023] A multi-planetary research station landing tiered isolation lunar dust-proof airlock transition chamber with a nested enclosure and flexible sealed liner is disclosed. An independent electrostatic precipitator (EDS) dust removal system is independently installed within the sealed docking compartment inside the chamber. The EDS dust removal technology is a mature and well-known technology in the field of deep-space lunar surface dust removal; its electrode arrangement structure, dielectric dust removal principle, traveling wave electric field dust removal mechanism, high-voltage drive circuit, and electrostatic dust removal method are all common knowledge in the field. This invention does not make any improvements or innovations to the EDS electric curtain dust removal equipment's main structure, dust removal principle, circuit architecture, or electric field generation method. The unique integrated improvement of this invention lies in: the mature independent EDS electric curtain dust removal system is exclusively integrated and arranged inside the sealed docking compartment of the airlock transition chamber, serving as the internal terminal dust removal unit of the multi-level lunar dust isolation system. This, combined with the chamber's three-level dust isolation structure, flexible sealed liner, and tiered isolation architecture, forms a complete progressive lunar dust-proof system. The EDS electric curtain dust removal system is electrically connected to the cabin's flat-plate battery pack for power, and simultaneously connects to the cabin's manual control module via electrical signals. This invention employs a purely manual, independent control logic for the EDS dust removal system: it does not feature automatic dust removal sensing, dust concentration-linked automatic start-up, or semi-automatic timed dust removal programs. The EDS electric curtain dust removal system's startup, dust removal operation, and shutdown are all triggered by commands issued manually by the astronauts through the manual control module; the system lacks autonomous operation, automatic intervention, and sensor-linked triggering logic. The internal sealed docking compartment is the core area for cabin docking, segment fitting, and sealing, and is also the critical location where lunar dust is most likely to remain, accumulate, and remain hidden. This invention, by independently installing an EDS electrostatic active dust removal unit at this critical point, achieves contactless, waterless, and consumable-free active removal of fine lunar dust from the docking and sealing area. Combined with the multi-level passive dustproof structure of the entire machine, it achieves a system-level protection effect of comprehensive, graded dustproofing and precise dust removal throughout the airlock cabin.

[0024] This invention provides a 30°C constant temperature thermal control system for batteries in lunar shadow areas, adapted to the ultra-high vacuum and extremely cold shadow environment of the moon. It achieves high-precision constant temperature steady-state operation of the battery housing cavity at 30°C±3°C, taking into account passive heat preservation, utilization of self-generated waste heat, active and precise heat replenishment, and fault-tolerant protection under all operating conditions. It solves the problems of constant temperature failure, high energy consumption, and poor reliability in existing technologies under extremely cold environments.

[0025] Overall system architecture: A 30°C constant temperature thermal control system for batteries in lunar shadow areas, including a sealed, temperature-controlled flat-plate battery pack mounting cavity with a vacuum jacket, multi-layer passive heat insulation and heat-locking components, a battery waste heat recovery and heat-locking module, a high-precision active heat replenishment module powered by the flat-plate battery pack itself, an intelligent PID temperature control module, an extreme cold fault-tolerant protection module, and a redundant power supply heat source module. The vacuum-insulated, temperature-controlled flat-plate battery pack mounting cavity serves as an independent, enclosed enclosure for the battery, isolating it from external extreme cold radiation and lunar soil cold conduction, and acting as the core carrier for temperature control. The multi-layered passive heat-locking components cover the outer wall of the vacuum-insulated, temperature-controlled flat-plate battery pack mounting cavity, preventing internal heat from radiating or conducting outwards. The battery waste heat recovery and temperature-locking module is integrated inside the chamber, collecting and conducting the Joule waste heat generated during battery charging and discharging, and then conducting it to the airlock transition chamber. The high-precision active heating module uses the flat-plate battery pack as a power source, providing a controllable electric heating compensation heat source. The intelligent PID temperature control module collects real-time temperature signals from the vacuum-insulated, temperature-controlled flat-plate battery pack mounting cavity, dynamically adjusting the temperature-locking efficiency and heating power. The extreme cold fault-tolerant protection module ensures stable operation of all components at ultra-low temperatures. The redundant power supply heat source module provides uninterrupted energy and a basic heat source backup for the temperature control system.

[0026] This invention provides a 30°C constant-temperature thermal control system for batteries in lunar shadow regions, adaptable for integration into airlock transition chambers of multi-planetary research stations. The entire system includes: a sealed, temperature-controlled flat-plate battery pack mounting cavity with a vacuum jacket; multi-layer passive heat insulation and heat-locking components; a battery waste heat recovery and temperature-locking module; a high-precision active heating module; an intelligent PID temperature control module; an extreme cold fault-tolerant protection module; and a redundant power supply heat source module. The battery energy storage structure, conventional electrothermal heating elements, temperature acquisition sensors, PID calculation chips, heat insulation substrate, and basic circuit power supply hardware involved in this invention are all existing, mature, and well-known technologies. This invention does not modify any single hardware component's structure, materials, or principles. The core originality of this invention lies in the system's constant-temperature and temperature-locking architecture with seven modules working in synergy, a precise 30°C temperature control strategy in the shadow region, a waste heat recovery and reuse mechanism, an extreme cold fault-tolerant redundancy backup system, and a closed-loop automatic control logic linked to the overall chamber's manual control module. The system-level assembly and functional architecture of each module are as follows: 1. A sealed, temperature-controlled flat-plate battery pack mounting cavity with a vacuum jacket serves as the core support for the entire thermal control system. It provides an independent, enclosed, vacuum-insulated, temperature-controlled mounting space for the flat-plate battery pack, effectively isolating it from the extremely cold radiation from the lunar shadow region and blocking the intrusion of low-temperature lunar regolith, thus creating an independent and stable temperature-controlled working environment for the battery. 2. A multi-layer passive thermal insulation and heat-locking component, which is integrally encased in the outer wall of the vacuum-insulated, temperature-controlled cavity, forming a composite gradient thermal insulation structure. This significantly hinders the outward conduction and radiation loss of heat from within the cavity, achieving passive long-term temperature lock-in and reducing active heating energy consumption. 3. A battery waste heat recovery and heat-locking module, integrated at the junction of the cavity and the airlock transition chamber. This module can directionally collect Joule-generated waste heat generated during battery charging and discharging, achieving heat collection, conduction, and reuse. It utilizes the battery's self-generated heat source to assist in maintaining the cavity's reference temperature, reducing the frequency of active heating start-ups and shutdowns, and improving energy utilization. 4. High-precision active heating module: This module is independently powered by the energy stored in the flat-plate battery pack, eliminating the need for external ground power supply. It outputs a controllable and adjustable compensating heat source based on the real-time temperature difference within the cavity, achieving precise heating and temperature rise under low-temperature conditions. 5. Intelligent PID temperature control module: This module collects the temperature signal inside the vacuum jacket constant-temperature cavity in real time and dynamically compares it with a preset 30℃ reference constant-temperature threshold. Based on the temperature difference, it dynamically and adaptively adjusts the waste heat recovery and temperature retention efficiency, active heating power, and start / stop sequence to achieve closed-loop dynamic precise constant-temperature control. 6. Extreme cold fault-tolerant protection module: This module is equipped with ultra-low temperature electrical protection, low-temperature start-up fault tolerance, and instantaneous temperature difference shock protection mechanisms to ensure the stable operation of all electrical, temperature control, and sensor components of the entire temperature control system under the extreme cold and fluctuating conditions of the moon, preventing low-temperature crashes, sensor failures, and temperature control malfunctions.7. Redundant Power Supply and Heat Source Module: This module provides backup energy and a safety net for the entire thermal control system. It continuously ensures the system remains unpowered and uncontrolled under conditions of instantaneous voltage fluctuations, local module malfunctions, and short-term extreme temperature shocks, achieving uninterrupted constant temperature protection. All temperature control modules, sensor modules, heat source modules, and fault-tolerant modules of the entire constant temperature thermal control system are electrically connected and their signals are connected to the manual control module in the airlock transition chamber. The manual control module performs parameter monitoring, logic matching, and automatic real-time closed-loop constant temperature control for the entire thermal control system, ensuring the battery in the lunar shadow region maintains a stable operating temperature of 30°C for an extended period.

[0027] External surface radiation temperature control coating: An aerospace-grade low-absorption, high-emissivity thermal control coating is sprayed onto all sun-facing exterior walls of the enclosure, preferably using S13G-LO, AZ-93 aerospace white paint coating, or plasma electrolytic oxidation (PEO) ceramic coating. This coating possesses optical properties of extremely low solar absorptivity and extremely high infrared emissivity, reflecting over 90% of direct solar radiation during lunar daytime, blocking external heat conduction into the enclosure. Simultaneously, leveraging the high thermal conductivity of 6061 aluminum alloy, waste heat from internal equipment is rapidly conducted to the enclosure surface and dissipated through the coating in the form of infrared radiation to the -270°C deep space environment, completely eliminating the problem of overheating and thermal runaway of internal equipment during lunar daytime.

[0028] Antistatic and conductive coating: A transparent or semi-transparent antistatic coating is applied to the outermost layer of the thermal control coating on the enclosure. The coating is doped with carbon nanotubes or indium tin oxide (ITO) conductive fillers. The coating can quickly gather the static charge accumulated on the enclosure surface and conduct the charge to the 6061 aluminum alloy enclosure substrate. The charge is then quickly discharged through the grounding structure, completely eliminating static electricity accumulation on the enclosure surface and preventing static dust adsorption at the source.

[0029] Low surface energy dustproof modification treatment: The outer surface of the enclosure is modified by micro-nano structure etching or sprayed with fluorosilicone-based low surface energy protective materials, which significantly reduces the surface energy of the enclosure surface and the adhesion of lunar dust. The trace amount of lunar dust adhering to the enclosure surface can be automatically detached under the action of lunar vibration and the micro-vibration of the enclosure equipment, continuously ensuring the radiative heat dissipation performance of the thermal control coating and the cleanliness of the enclosure surface structure.

[0030] Passive thermal insulation and heat-locking structure design: The outer wall of the cabin is covered with a composite aerospace-grade thermal insulation structure, which consists of a spectrally selective thermal insulation layer, a multi-layer thermal insulation blanket (MLI), and an aerogel felt thermal insulation layer, forming a triple-sealed thermal barrier from the outside to the inside. The spectrally selective thermal insulation layer uses a special coating with high infrared reflectance and low solar absorption to block the penetration of cold radiation from deep space and isolate the conduction of weak external cold energy. The multi-layer thermal insulation blanket uses a vacuum-metallized polyester film stacked structure to significantly reduce the radiative heat transfer coefficient in a vacuum environment. The aerogel felt thermal insulation layer fills the gaps at the edges and corners of the cabin, eliminates thermal bridges and heat leakage channels, minimizes the overall heat transfer coefficient of the cabin, and achieves the basic function of passive thermal locking.

[0031] Battery waste heat adaptive recovery and temperature lock-in mechanism: The internal chamber is equipped with a micro-gap heat storage buffer structure and an intelligent heat-insulating air curtain component, forming a sealed heat storage chamber with the gap between the chamber and the battery pack. The Joule waste heat generated during battery charging and discharging is retained in the heat storage chamber. The temperature control system adaptively adjusts the internal heat dissipation damping according to the battery's operating status: when the battery is operating at a high rate and generating a large amount of heat, a small amount of waste heat is released appropriately to prevent the chamber from overheating; when the battery is operating at a low rate and generating little heat during standby, the heat storage chamber is completely sealed, 100% of the retained waste heat is recovered, and the battery's own heat generation serves as the 30°C constant temperature basic heat source, reducing the energy consumption of active heating.

[0032] High-precision active constant temperature and heat compensation control scheme: An array of flexible polyimide heating films is bonded to the inner wall of the chamber, paired with distributed high-precision low-temperature sensors. The sensors are evenly distributed at four temperature measurement points on the upper, lower, left, and right sides of the chamber to achieve full-range temperature acquisition. An optimized PID constant temperature control algorithm is adopted, with a core constant temperature threshold of 30°C and a temperature control range strictly locked between 27°C and 33°C: When the internal temperature is higher than 33°C, all heating units are turned off, and the internal micro-heat dissipation damping is activated to release excess heat; when the internal temperature is lower than 27°C, the flexible heating film is activated in stages to accurately compensate for heat; when the temperature is in the range of 27°C to 33°C, low-power steady-state fine adjustment is used to stably lock the internal temperature at the constant temperature point of 30°C, with a temperature control accuracy of ±3°C.

[0033] Extreme cold tolerance and failure-resistant design: All electronic components in the system use cold-resistant silicon-germanium (SiGe) and gallium nitride (GaN) chips, matched to ultra-low temperature thermal expansion coefficients, to avoid material embrittlement and component failure in extreme cold environments of -230°C; the core temperature control components (sensors, heating modules, control motherboard) all adopt dual-path hardware redundancy backup, automatically and seamlessly switching to redundant channels in the event of a single-path failure, achieving hardware fault tolerance and self-healing. Equipped with a digital twin predictive health management (PHM) algorithm, it simulates the operating status of the temperature control system in real time, predicts in advance the performance drift of components and changes in heat loss rate under low temperature environments, dynamically corrects control parameters, and avoids temperature control failure.

[0034] Dual Redundancy Heat Source Backup: A dual redundancy heat source system of electrochemical power supply + isotope heat source is set up: Under normal operating conditions, the temperature control system is powered by lunar energy storage batteries; under lunar night, long-term shadow standby, and low battery conditions, the radioactive isotope heat source is activated to continuously provide basic heat for the core temperature control components, preventing the overall failure of the temperature control system due to power outages or freezing in extreme cold, and achieving decades of long-term maintenance-free stable operation.

[0035] Extreme operating condition hibernation start-up protection mechanism: The system is configured with an extreme cold deep hibernation mode. Under ultra-low temperature extreme conditions, only the isotope heat source and the core temperature measurement unit are kept running, and unnecessary energy-consuming modules are shut down. During the temperature rise start-up phase, a resistive load preheating recovery strategy is adopted to gradually activate the heating and control units, avoid circuit collapse and device damage caused by instantaneous temperature difference shocks, and ensure stable low-temperature start-up of the system.

[0036] The materials used to fabricate the main body of the flexible connection components include, but are not limited to, space-grade phenyl silicone rubber, aluminized polyimide composite film, perfluoroether rubber, silicone rubber-aramid fiber composite flexible materials (for heavy-duty flexible connections), boron-containing ultra-high molecular weight polyethylene composite sheets, and PEEK flexible composite materials. These materials are suitable for the lunar surface's high vacuum (≤1×10⁻⁻ Pa), extreme temperature differences (-180°C to +150°C), strong ultraviolet radiation (1000 ESH), galactic cosmic rays (GCR), solar high-energy particles (SEP), and electrostatic lunar dust erosion environment. The materials also possess high strength (tensile strength ≥15MPa), high flexibility (elongation at break ≥100%), high airtightness (leakage rate ≤1×10⁻⁻ mbar·L / s), low vacuum outgassing (total mass loss ≤1%), radiation aging resistance (dose ≥10⁻ rad), and resistance to high and low temperature cycling. Specific implementation details and material application: The phenyl silicone rubber sealing connector is molded from low-phenyl silicone rubber (SSP4716), with a Shore hardness of 65±5 and a temperature resistance of -116°C to +250°C; it is prepared as a docking frame sealing gasket (section φ10~φ20 mm) and a flexible connecting pipe between compartments (inner diameter 50~200 mm, wall thickness 3~5 mm); the compression set under vacuum is ≤15%, and the performance retention rate after 1000 ESH ultraviolet irradiation is ≥90%; it is installed on the sealing surfaces of the active and passive ends of the docking mechanism of the research station, achieving mechanical bonding and airtight sealing during docking, with a docking leakage rate ≤1×10--mbar·L / s, ensuring stable pressure inside the compartment (0.1MPa). The aluminized polyimide composite flexible connecting skin is made of 5 to 10 layers of aluminized polyimide film (thickness 12.5 to 25 μm / layer) composite hot-pressed, with a total thickness of 0.1 to 0.3 mm, tensile strength ≥200 MPa, and temperature resistance -269°C to +400°C. It is made into a flexible connecting channel skin between modules, and both ends are sealed and fixed to the gable wall of the module by metal pressure frames. It has high flexibility (foldable and retractable, with a rebound rate of ≥98% after unfolding), vacuum stability, and anti-proton oxygen / ultraviolet radiation characteristics. Combined with the inner silicone rubber sealing layer, it forms an integrated flexible sealing structure of thermal control, sealing and radiation protection, which compensates for the docking attitude deviation of the modules (≤50 mm) and adapts to the thermal expansion and contraction deformation of the lunar surface.The boron-containing ultra-high molecular weight polyethylene flexible shielding connection layer is made of BC (10-20 wt%) reinforced ultra-high molecular weight polyethylene calendering, with a thickness of 10-30 mm, a density of 1.2-1.5 g / cm³, and a temperature resistance of -80°C to +120°C. It is prepared as a flexible inter-cabin connection radiation shielding liner and is attached to the inner side of the polyimide skin. It has a high-energy neutron shielding efficiency of ≥99%, a gamma-ray attenuation rate of ≥80%, no precipitates in a vacuum environment, and is flexible and bendable (bending radius ≤50 mm). It is used for radiation protection in the connection area of ​​scientific research stations to reduce the damage of cosmic rays to personnel and equipment inside the cabin.

[0037] A multi-planetary research station landing tiered isolation lunar dust-proof airlock transition chamber with a nested box body and flexible sealing liner is made of any one of the following materials, or a composite of two or more of them, including but not limited to: various types of steel, alumina ceramics, silicon carbide ceramics, silicon nitride ceramics, aluminum alloys, titanium alloys, aluminum-lithium alloys, aerospace-grade dense inorganic ceramics, carbon fiber reinforced composite materials, lightweight high-temperature resistant special alloys, aerogel composite thermal insulation substrates, low-temperature resistant and wear-resistant engineering ceramics, carbon fiber cyanate composite materials, SiC / SiC ceramic matrix composite materials, alumina continuous fiber reinforced composite materials, rare earth modified magnesium-lithium alloys, polyimide-based carbon fiber composite materials, carbon nanotube reinforced composite materials, high-strength and tough carbon aerogels, rare earth modified ultra-low temperature magnesium-lithium alloys, silicon nitride Si-N-reinforced composite materials, alumina continuous fiber reinforced composite materials, SiC whisker-reinforced alumina ceramic composite materials, and SiC silicon carbide fiber reinforced SiC. Ceramic matrix composites (SiC / SiC), high-temperature resistant composites of carbon fiber and polyimide, high-modulus carbon fiber and cyanate ester resin composites, antistatic modified inorganic sheets, and vacuum-stable composite structural materials. These materials possess extremely low density, high structural strength, high surface hardness, resistance to friction and wear, and electrostatic insulation properties, enabling them to withstand long-term operation in vacuum environments, extreme high and low temperature alternation, lunar dust erosion, and harsh conditions involving repeated dust friction.

[0038] This invention discloses a multi-planetary research station landing, tiered isolation, and lunar dust-proof airlock transition chamber with a nested enclosure and flexible sealing liner. It is equipped with multiple environmental control and safety protection auxiliary devices, including: electric heating equipment, water electrolysis hydrogen and oxygen production equipment, a sealed water tank, an electronic barometer, electromagnetically controlled sealing valves, and a high-pressure carbon dioxide gas injection device. All of the above auxiliary equipment are existing mature standard equipment in the field of deep-space planetary dwelling chambers. The structure, internal working principle, hardware composition, electrical drive method, and media processing logic of the equipment are all common knowledge. This invention does not improve or innovate the structure, hardware performance, internal circuitry, or working principle of any auxiliary equipment. All auxiliary equipment is fixedly installed on the inner wall and gable of the airlock transition chamber at suitable installation positions, realizing basic dwelling support functions such as temperature and humidity control, airtight isolation, water storage, hydrogen and oxygen production, pressure monitoring, and dust removal. This invention is equipped with a manual control module and a flat-plate battery pack. All the aforementioned environmental auxiliary equipment is electrically connected to the manual control module and the flat-plate battery pack, which provides unified power. The manual control module serves as the sole control terminal for overall system management. The core, original control logic that distinguishes this invention from existing intelligent control systems is as follows: 1. Single Manual Control Architecture: All environmental auxiliary equipment in the entire cabin is uniformly managed by the manual control module. There is no remote wireless automatic control channel from Earth, nor is there a local handheld automatic intervention channel; only on-site manual operation is permitted. 2. Complete Elimination of Automatic and Semi-Automatic Intelligent Control Programs: This system completely eliminates the automatic and semi-automatic control modes standard in traditional planetary dwelling cabins. There are no timed start / stop, no delayed operation, and no pre-set program logic. 3. Elimination of All Sensor-Linked Autonomous Execution Logic: The electronic barometer only has real-time pressure acquisition and numerical display functions. The acquired data is only used as a reference for manual operation and will not trigger any automatic start / stop, automatic adjustment, automatic purging, automatic gas generation, or automatic heating actions of any equipment, completely abandoning the sensor-closed-loop autonomous control architecture. 4. Purely Manual Command-Driven Execution: All actions related to the operation of auxiliary equipment—including starting, stopping, parameter adjustment, on / off purging, media preparation, heating and temperature control, and airtightness control—require manual commands issued by operators pressing physical buttons on the manual control module. The system lacks autonomous operation, intelligent intervention, and program self-starting capabilities. This invention does not modify any hardware equipment; it only addresses the technical problems of existing multi-planetary research station airlock intelligent control systems—such as susceptibility to accidental triggering, complex logic, numerous failure points, and poor emergency controllability—by reconstructing a minimally simplistic, purely manual control system for the entire set of auxiliary equipment.

[0039] This invention relates to an auxiliary system for environmental media treatment in a lunar airlock transition chamber. The system includes an electronic barometer, an electromagnetically controlled sealing valve, a water electrolysis hydrogen-oxygen production device, a sealed water tank, an electric heating device, a flat-plate battery pack, and a high-pressure carbon dioxide gas injection device. All devices are electrically connected to a built-in manual control module, which outputs unified operating commands to control the opening, closing, parameter adjustment, and purging of various devices. 1. Hardware Electrical Connection Architecture (Known Part): The electronic barometer, electromagnetically controlled sealing valve, water electrolysis hydrogen-oxygen production device, sealed water tank with supporting electrical control components, electric heating device, flat-plate battery pack, and high-pressure carbon dioxide gas injection device are electrically connected to the manual control module via signal wires and power supply lines. The circuit connection methods for signal acquisition, power transmission, and drive conduction are conventional and known technologies for aerospace equipment in this field. This invention does not modify the internal hardware or drive circuits of any of the devices. The electronic barometer is only used to collect real-time cabin pressure values ​​and feed them back to the manual control module for display; it does not participate in the system's autonomous control.

[0040] Exclusive Control Logic (Core Improvement of this Invention) Single Control Source: 1. The entire auxiliary equipment is equipped with only a manual control module as the sole operating terminal, without remote wireless automatic control or automatic intervention by astronaut handheld controllers; 2. No automatic control mode, no semi-automatic control mode: The system does not have any autonomous operating program, and does not set up intelligent control logic such as pressure-linked start / stop, timed heating, automatic gas production, automatic purging, or semi-automatic delayed start / stop; 3. All equipment operation, shutdown, and adjustment actions must be executed by the operator manually pressing and toggling the buttons on the manual control module; 4. No automatic linkage intervention: The pressure data collected by the electronic barometer is only displayed numerically and will not trigger any autonomous equipment actions. The pressure signal is only used as a reference for manual operation and does not participate in the automatic linkage control of the equipment; 5. Command execution logic: After the operator issues a single or multiple equipment linkage operation command through the manual control module, the circuit synchronously conducts the corresponding equipment circuit, immediately executing the opening and closing of electromagnetic valves, the start / stop of water electrolysis gas production, the heating / stopping of electric heating, the high-pressure carbon dioxide injection, and the water tank water circulation control actions. The system will not autonomously correct, interrupt, or overwrite the manual operation command.

[0041] The core improvement of this invention compared to existing technologies is that it unifies all environmental auxiliary equipment under a single manual control module, completely eliminates automatic and semi-automatic intelligent control programs, cancels sensor-linked autonomous execution logic, and constructs a purely manual command-driven equipment control system.

[0042] The basic functions of the aforementioned electric heating equipment, water electrolysis hydrogen-oxygen production equipment, sealed water tank, electronic barometer, electromagnetically controlled sealing valve, and high-pressure carbon dioxide gas injection device—such as heating, gas production, water storage, pressure measurement, airtight on / off control, and dust removal—are inherent and known technical effects of existing equipment and do not constitute the innovative and beneficial effects of this invention. This invention, through its unique architecture of single manual control of all auxiliary equipment, without automatic or semi-automatic operation, and without sensor-linked automatic control, achieves the following unique and significant technical effects: 1. Completely eliminates the risk of equipment malfunction in the complex environment of deep space. The surfaces of many planets exhibit strong cosmic radiation, electromagnetic interference, extreme temperature variations, and dust interference. Traditional automatic and semi-automatic control systems are prone to sensor drift, program errors, and misjudgment triggering equipment start-up and shutdown. This invention completely eliminates intelligent automatic control logic; the equipment is only manually triggered, fundamentally eliminating the safety hazards of uninstructed heating, uninstructed gas production, uninstructed purging, and uninstructed valve opening and closing, greatly improving the safety of long-term research station stays. 2. The control system is extremely simple, with a very low failure rate, and is suitable for long-term unmanned operations in deep space. It eliminates a large number of self-control chips, linkage algorithms, sensor closed-loop programs, and mode switching logic, significantly simplifying the hardware and software structure of the electrical control system and reducing numerous potential failure points. This effectively meets the requirements of long-term unattended, low-maintenance, and highly reliable operations on the moon and multiple planets. 3. Manual operation is absolutely controllable, with no forced system intervention. Operators can independently, freely, and individually start and stop any auxiliary equipment according to on-site conditions, maintenance needs, and testing requirements. Multiple devices can also be linked for synchronous operation as needed. The system will not automatically intercept, correct, or override manual operation commands, completely releasing the freedom of manual operation and adapting to precise debugging, emergency maintenance, and special scientific research testing scenarios in research modules. 4. It has extremely strong anti-interference capabilities and high operational stability. It abandons sensor-linked self-control logic and is unaffected by air pressure fluctuations, temperature fluctuations, dust obstruction, and signal interference. The equipment's operating status completely follows manual commands, and the control logic is stable, reliable, and free from program malfunction risks. 5. Low post-maintenance difficulty and high on-site repairability on the planet. There are no complex intelligent programs to debug or self-control algorithm faults to troubleshoot. Only basic power supply and manual switch circuits are retained. Astronauts can quickly troubleshoot the lines, replace parts, and restore equipment operation, which greatly reduces the difficulty of deep space operation and maintenance.

[0043] A multi-planetary research station landing, tiered isolation, and lunar dust-proof airlock transition chamber with a nested enclosure and flexible sealing liner is disclosed. The chamber is equipped with a flat-plate battery pack, a manual control module, a water electrolysis hydrogen-oxygen production device, an electric heating device, a sealed water tank, an electronic barometer, and electromagnetically controlled sealing valves. The flat-plate battery pack utilizes an aerospace-compatible lithium battery energy storage structure to provide stable power to all auxiliary electrical equipment within the chamber. The manual control module serves as the centralized control terminal for the auxiliary equipment. All of the aforementioned equipment are existing, mature standard equipment in the field of deep-space dwelling chambers, and their structure, working principle, circuit drive method, media processing method, sensor detection principle, and valve sealing and on / off principle are all known existing technologies. This invention does not make any improvements or innovations to the structure, hardware principle, or internal construction of any of the aforementioned equipment. The improvement of this invention lies in the overall integrated layout of these known devices within the multi-tiered lunar dust-proof nested airlock chamber, the matching relationship of their zoned installation positions, the unified power supply and electrical architecture, and the unified manual control system. The specific layout and connection relationships are as follows: The water electrolysis hydrogen and oxygen production equipment, electric heating equipment, sealed water tank, flat battery pack, and manual control module are all fixedly installed in their respective mounting positions on the walls of the airlock transition chamber. The layout is neat and does not interfere with the expansion and contraction of the nested enclosure and the sealing fit structure. The electronic barometer and electromagnetically controlled sealing valves are centrally and fixedly installed on the connecting pipelines on the gable wall of the chamber, matching the airlock channel's airtightness monitoring and pipeline opening and closing requirements. All electrical equipment, environmental protection equipment, airtightness monitoring, and pipeline valve equipment are electrically connected to the flat battery pack for power, and simultaneously electrically connected to the manual control module for centralized electrical management. The overall control logic of this invention is a purely manual control architecture. It does not include automatic control modes, semi-automatic linkage control modes, or sensor-triggered operation logic. The electronic barometer data is only used as manual reference data and will not autonomously trigger valve opening and closing, heating, gas production, or other equipment actions. All the starting and stopping, operating condition adjustment, heating operation, gas production operation, water storage protection, air pressure monitoring, and pipeline opening and closing sealing actions of the equipment in this invention are all completed by manual on-site operation and control module issuing instructions, realizing the extremely simple, reliable, and fully controllable cabin environment protection and airtightness protection functions under the construction conditions of extraterrestrial landing.

[0044] Each compartment inside the nested enclosure is equipped with an electric heating device, which is electrically connected to the flat battery pack and the manual control module. The electric heating device can be activated by the manual control module to heat the environment to a temperature suitable for human habitation.

[0045] Each compartment inside the nested enclosure is equipped with a water electrolysis hydrogen and oxygen production device and a sealed water tank. The water electrolysis production device and the sealed water tank are electrically connected to the flat battery pack and the manual control module. The water electrolysis production device can be started through the manual control module to ensure that the oxygen content inside the environment is sufficient to meet the requirements for human habitation.

[0046] A multi-planetary research station landing graded isolation lunar dust-proof airlock transition cabin with nested box body and flexible sealing liner is equipped with a motion system at the bottom of its chassis. The motion system, wheel axle support, and wheels adopt any one of the following bionic walking drive structures that are compatible with human power, external force, gasoline engine, diesel engine, electric wheel type, track type, wheel track combination type or outrigger stepping type, to drive the research station to move and overcome obstacles on the planetary surface.

[0047] The radio transmitting and receiving device, as a core component of a composite control system, consists of key parts such as an antenna, transmitter, and receiver. The antenna is responsible for signal radiation and reception; its design must balance frequency band adaptability and gain performance to ensure stable wireless communication in complex environments. The transmitter modulates the control signal to be transmitted and converts it into a high-frequency signal suitable for wireless propagation, which is then transmitted to the target receiver via the antenna. The receiver's main function is to demodulate the received high-frequency signal, reconstruct the original control command, and transmit it to the manual control module for further operation. Furthermore, to improve the system's anti-interference capability, the transmitter and receiver typically employ frequency hopping technology, continuously changing the operating communication channel to reduce the impact of external electromagnetic interference. This modular hardware design not only enhances the device's functional independence but also improves the system's maintainability and scalability. Working principle: The radio transmitting and receiving device operates based on the fundamental theory of wireless communication, including signal modulation, transmission, reception, and demodulation processes. In the signal transmission phase, the transmitter first converts the digital control signal from the manual control module into an analog signal and then modulates it onto a high-frequency carrier wave. Subsequently, the amplified modulated signal is sent to the antenna and radiated into space as electromagnetic waves. During signal reception, the receiver captures the electromagnetic wave signal in the air through the antenna, converts it into an electrical signal, and then amplifies and filters it. Next, the receiver uses demodulation technology to extract the original control commands from the high-frequency signal and transmits them back to the manual control module. Throughout this process, to ensure the real-time performance and accuracy of data interaction, a bidirectional communication protocol is used between the transmitter and receiver, while error detection and correction mechanisms enhance the reliability of data transmission. Furthermore, the device supports multi-channel switching, enabling dynamic adjustment of the operating frequency band in complex electromagnetic environments to avoid signal interference and ensure communication quality.

[0048] Camera Components: Designed for Harsh Environments. The design of the camera components must fully consider their operational requirements in special environments (such as airlock transition chambers), especially their performance under extreme conditions such as vacuum, high and low temperatures. To this end, the camera components employ multiple design solutions for harsh environments. First, in terms of material selection, the camera component's shell is made of high-strength aluminum alloy or titanium alloy. These materials not only possess excellent mechanical properties but also effectively resist pressure changes and temperature fluctuations in a vacuum environment. Second, in the optical lens section, low-expansion-coefficient glass is used to reduce focal length shift caused by temperature changes, thereby ensuring image clarity. Furthermore, to cope with high and low temperature environments, the camera components integrate heating and heat dissipation devices, enabling the equipment to maintain normal operation under extreme temperatures. In terms of sealing design, the camera components employ multiple sealing rings and vacuum welding technology to ensure their airtightness and long-term stability in a vacuum environment. These design measures collectively guarantee the reliable operation of the camera components in harsh environments. Function and Layout: The main function of the camera components is to provide operators with real-time visual information about the internal and external environment of the airlock transition chamber. Their shooting capabilities and layout directly affect the system's monitoring effectiveness. This component is equipped with a high-resolution CMOS sensor and a wide-angle lens, covering a field of view of approximately 120° horizontally to approximately 90° vertically, thus enabling panoramic monitoring of the target area. Outside the airlock transition chamber, the camera component is mounted on the end face of the longitudinal beam chassis. This position not only facilitates the recording of the operational status of the external equipment but also effectively avoids obstruction of the view due to mechanical movement. Inside the chamber, the camera component is positioned in a location easily observable by operators to monitor the operation of the equipment and personnel activities in real time. Furthermore, the camera component supports remote control, allowing for manual adjustment of the shooting angle and focal length via a control module to meet the needs of different mission scenarios. Through its rational layout design, the camera component maximizes its monitoring capabilities, providing crucial support for the safe operation of the composite control system.

[0049] Flat-plate battery packs, performance characteristics: As the core of the energy supply for a composite control system, the performance characteristics of the flat-plate battery pack directly determine the operational stability and endurance of the entire system. This battery pack utilizes high-energy-density lithium-ion battery technology, with lightweight and compact individual cells, providing ample power support within limited space. Furthermore, the flat-plate battery pack boasts excellent cycle life, maintaining a high capacity retention rate after multiple charge-discharge cycles, thus extending the equipment's lifespan. For applications requiring special environments, this battery pack has been optimized for harsh conditions, such as using high-temperature resistant diaphragms and low-temperature enhanced electrolytes to ensure normal operation within a temperature range of -40°C to +60°C. Simultaneously, the flat-plate battery pack exhibits excellent safety performance, with built-in overcharge, over-discharge, and short-circuit protection circuits, effectively reducing safety risks caused by abnormal conditions. These performance advantages make the flat-plate battery pack an ideal energy solution for equipment in special environments such as space stations and airlock transition chambers. Power supply mechanism: The power supply mechanism of the flat-plate battery pack is based on a modular circuit design, achieving stable power supply to various devices through reasonable electrical connections. The battery pack's output is connected to the electric motion system, manual control module, and other load devices via dedicated cables, forming a closed loop. The circuit design employs multi-stage voltage regulation and filtering technology to ensure the stability and purity of the output voltage, thus meeting the power quality requirements of different devices. Furthermore, to improve system energy efficiency, the battery pack integrates an intelligent power management system that dynamically adjusts output power according to actual load demands, thereby reducing energy loss and extending runtime. In multi-device power supply scenarios, the battery pack flexibly distributes power through parallel and series connections, ensuring sufficient power support for each device. For example, when the electric motion system is under high load, the battery pack prioritizes providing high-power output, while automatically reducing output power under low load conditions to conserve energy. This efficient power supply mechanism not only improves the system's energy utilization rate but also lays a solid foundation for the long-term stable operation of the composite control device.

[0050] The electric motion system, as the actuator of a composite control device, directly determines its motion performance and control accuracy through its mechanical structure and electrical components. The system mainly consists of core components such as a drive motor, reducer, transmission device, and position sensors. The drive motor is a high-torque-density permanent magnet synchronous motor, capable of providing sufficient power output within a small size, while also possessing good efficiency characteristics and response speed. The reducer is used to reduce the motor's output speed and increase its output torque, thereby meeting the force and speed requirements of different motion scenarios. The transmission device adopts a high-precision gear or synchronous belt structure to ensure the smoothness and accuracy of power transmission. In addition, the system integrates multiple position sensors and encoders for real-time monitoring of motor speed, angle, and motion position, providing accurate feedback information for closed-loop control. In terms of electrical components, the electric motion system connects to the manual control module via a dedicated interface, receiving and executing operation commands from the control module to achieve various motion modes such as start / stop, forward, backward, and steering. Control Interface: The control interface between the electric motion system and the manual control module is a crucial link in achieving efficient data interaction. Its type, communication protocol, and data interaction format have all been carefully designed to meet the system's real-time and reliability requirements. At the physical interface level, the system uses standardized connectors, such as RS-485 or CAN bus interfaces, to achieve high-speed transmission of electrical signals and anti-interference capabilities. For the communication protocol, the TTCAN (Time-Triggered CAN) protocol based on a time-triggered mechanism is selected. This protocol can ensure deterministic data transmission while supporting concurrent communication among multiple nodes, thus meeting the needs of complex control tasks. Regarding the data interaction format, the system defines a unified application layer protocol to encapsulate and parse control commands, status feedback, and error information, ensuring the accuracy and efficiency of information transmission. For example, the control command data packet contains information such as target speed, acceleration, and direction of motion, while the status feedback packet uploads parameters such as motor speed, temperature, and current in real time. Through this highly integrated control interface design, the electric motion system can quickly respond to the operation commands issued by the manual control module, thus providing strong support for the overall composite control device.

[0051] The manual control module, as the central hub of the composite control system, undertakes the crucial task of receiving, processing, and distributing various control signals. Its core function is to analyze control commands from radio transmitters / receivers, handheld controllers, and other external devices in real time, and generate corresponding electrical control operation execution signals based on non-priority control logic. Specifically, upon receiving a control signal, the module first amplifies and filters it through the signal receiving circuit, then passes it to the processing circuit for decoding and logical judgment. Since this scheme does not set control priorities, the manual control module adopts a first-in, first-out (FIFO) strategy, prioritizing the response to the most recently received signal, thus ensuring that the electric motion system always executes operations according to the latest command. Furthermore, the module also has signal conflict detection and processing capabilities; when multiple conflicting commands are received simultaneously, it can automatically identify and discard invalid signals, preventing system malfunctions. This flexible and efficient control logic design significantly improves the system's response speed and operational reliability. Circuit Design: The circuit design of the manual control module revolves around the three main functions of signal reception, processing, and output, employing a multi-layered, modular architecture to achieve efficient data processing and transmission. The signal receiving circuit consists of a low-noise amplifier (LNA), a bandpass filter (BPF), and an analog-to-digital converter (ADC), responsible for converting analog control signals into digital signals for subsequent processing circuitry to analyze and decode. The processing circuit is based on a high-performance microcontroller, equipped with sufficient memory and computing power to quickly execute complex logic judgments and control algorithms. Furthermore, the module integrates a watchdog timer and power monitoring circuitry to monitor system status in real time and trigger a reset operation in abnormal situations, thereby improving system stability and anti-interference capabilities. The signal output circuit uses a dedicated driver chip to convert the processed digital signals into analog control signals suitable for the electric motion system, while employing optocoupler isolation technology to improve the reliability and safety of signal transmission. Through this meticulously designed circuit architecture, the manual control module can operate stably in complex environments, providing solid technical support for the efficient control of composite control devices.

[0052] Control Logic, Multiple Control Modes: 1. Manual Control: In complex control devices operating under special conditions, manual control is a crucial operating mode. Its core lies in achieving precise control of the electric motion system through a handheld controller used by the astronaut. Specifically, the operation commands sent by the astronaut through the handheld controller are first encoded into digital signals, then transmitted via a radio transmitter module at a specific frequency to the receiving device. After capturing the signal, the receiving device decodes it and transmits it to the manual control module for processing. As the core hub of the system, the manual control module is responsible for parsing the received signals and generating corresponding electrical control operation execution signals based on the command type, ultimately transmitting them to the electric motion system through the control interface. In this process, the signal transmission path involves multiple stages, from the handheld controller to the radio transmitter module, then to the receiving device, and finally to the manual control module, ensuring efficient and reliable information transmission. Furthermore, because the handheld controller is designed with human-computer interaction in mind, its user interface is simple and intuitive, significantly reducing the learning cost and operational difficulty for astronauts, thereby improving overall mission execution efficiency. 2. Remote Wireless Control: Remote wireless control is another important function of this composite control device. It enables long-distance operation through wireless communication between a remote control center on Earth and the target device. In this mode, the remote control center first converts the operation command into a digital signal and transmits it to a radio receiver in the target area via a high-gain antenna. After acquiring the signal, the radio receiver demodulates and decodes it, and then transmits the restored command to the manual control module. Upon receiving the remote command, the manual control module quickly analyzes and processes it, generates the corresponding electrical control operation execution signal, and finally drives the electric motion system to complete the corresponding action through the control interface. Notably, to ensure stable transmission of the remote control signal in complex environments, this study employs frequency hopping technology to enhance anti-interference capabilities. Experimental results show that by continuously changing the working communication channel, the system can maintain a high communication success rate in environments with strong electromagnetic interference, thus effectively ensuring the reliability and real-time performance of remote control. Attached Figure Description

[0053] The attached figures are schematic diagrams of the structure of the present invention. Figure 1 is an overall front view of the main body of the research station of the present invention. Figure 2 is a left view of the present invention. Figure 3 Figure 4 is a right view of the present invention. Figure 5 is a cross-sectional view of the overall front view of the present invention with the center line of the sealing doors on both sides as the cutting line.

[0054] Figure 1: 1 Axle, 2 Connecting component body made of flexible material, 3 Axle bracket, 4 Wheel, 5 Radio transmitter and receiver device, 6 Outermost housing.

[0055] Figure 2: 7 Camera assembly, 8 Flat battery pack (8 is a simplified schematic diagram of the energy storage battery in the lunar shadow area; the rectangular box in the figure only represents the metal housing of the energy storage battery (a known basic device). The composite constant temperature thermal control management system fully disclosed in this manual is an independently assembled component. Because the attached figure only shows the battery body in a simplified manner, the insulation layer, heating film, isotope heat source, temperature measurement module and other thermal control supporting structures are not drawn. The composition, assembly relationship and working logic of the entire thermal control system are all recorded in the text of the manual. Those skilled in the art can completely reproduce the entire system by combining the common aerospace thermal control knowledge in the field with the text of the manual.), 9 Reinforcing fasteners on the bottom of one side of the outer box wall, 10 Connection holes on the rigid mating interface of the connecting parts, 11 High-pressure oxygen cylinder, 12 High-pressure nitrogen cylinder, 13 Sealed door handle, 14 Sealed door, 15 Sealed door frame.

[0056] Figure 3: 16. Pressure gauge on the inner casing gable wall (an electronic pressure gauge can also be used); 17. Sealing valve on the inner casing gable wall; 18. Through pipe above the inner casing gable wall; 19. Flexible connecting pipe on the inner casing gable wall; 20. Sealed joint of the connecting pipe; 21. Sealing valve of the through pipe; 22. Through pipe below the inner casing gable wall; 23. Inner casing.

[0057] Figure 4: 24 Sealing valve on the inner wall of the through-pipe below the inner gable wall of the inner box; 25 Sealing valve on the inner wall of the through-pipe above the inner gable wall of the inner box; 26 Sealing valve on the inner wall of the through-pipe of the isolation gable wall; 27 Sealing valve on the outer wall of the through-pipe of the isolation gable wall; 28 Sealing valve on the inner wall of the through-pipe above the gable wall at the other end of the inner box; 29 Sealing valve on the outer wall of the through-pipe above the gable wall at the other end of the inner box; 30 Sealing valve on the inner wall of the through-pipe below the gable wall at the other end of the inner box; 31 Sealing valve on the outer wall of the through-pipe below the gable wall at the other end of the inner box; 32 Sealing valve on the inner wall of the through-pipe above the gable wall of the outer box; 33 Sealing valve on the outer wall of the through-pipe above the gable wall of the outer box; 34 Sealing valve on the inner wall of the through-pipe below the gable wall of the outer box; 35 Sealing valve on the outer wall of the through-pipe below the gable wall of the outer box; 36 37. Pressure gauge on the outer wall of the through-pipe above the outer box gable; 38. Flexible connecting pipe on the outer box gable; 39. Sealed connection port of the connecting pipe; 40. Flexible connecting hose between the through-pipe above the outer box gable and the through-pipe above the gable of the other end of the inner box (39 in Figure 4 is the flexible connecting hose, the total length of the hose when fully extended is 3m, the attached figure only simplifies the arc connection structure of the pipe and does not show the full length of the pipe); 50. Spacesuit dust removal and cleaning equipment in the inner compartment of the inner box, which internally integrates electrostatic adsorption dust removal components and fine particle filtration dust removal components; the equipment has a sealed door, which is sealed by sealing strips on all four sides.41. Wall lamp on the top wall of the inner compartment; 42. Component with right-angle folded edge connecting to reinforce the gable wall (one right-angle folded edge is welded, riveted, or glued to the top of the partition wall in the middle of the inner compartment near the side wall, and the other right-angle folded edge is welded, riveted, or glued to the top of the gable wall at one end of the inner compartment near the side wall; the long side of the component is firmly fixed to the top wall of the inner compartment by welding, riveting, or gluing, which strengthens the gable wall body and weld seams to withstand air pressure. One of this component is installed on each side of the top wall and floor of each compartment, for a total of 4; or one can be installed in the middle of the top wall, for a total of 6); 43. Rigid mating interface of connecting components; 44. Spacesuit dust removal and cleaning equipment in the outer compartment of the inner compartment. This equipment has a sealed door, which is sealed by sealing strips on all four sides. The figure shows the internal structure after the sealed door is opened; 45. Gable wall; 46. Middle partition gable wall; 47. Light on the door frame of the sealed door in the outer compartment; 48. 49. Hinges fixing the sealed door to the door frame; 50. Outermost box gable wall; 51. Components fixing the flexible sealing connection parts on the outer wall of the gable wall; 52. Flexible sealing connection parts (51 in Figure 4 is the flexible sealing connection parts, the total length of the flexible sealing connection parts when fully extended is 2.8m-3m, the attached figure only simplifies the arc connection structure of the pipeline and does not show the full length of the pipeline); 53. Fixing frame for the rigid interface between the flexible sealing connection parts and the connecting parts; 54. Reinforcing fasteners for the outer box gable wall and the top wall; 55. Part cut to the rigid interface of the connecting parts; 56. Electrostatic dust generator inside the spacesuit dust removal and cleaning equipment in the outer compartment of the inner box; 57. Manual control module, which can manually control the various electrical equipment inside the research station; 58. Flat battery pack installed on the side wall of the inner box; 59. Pipeline connecting the spacesuit dust removal and cleaning equipment in the inner and outer compartments of the inner box, the pipeline runs through the middle partition wall. A pipeline runs beneath the inner casing's gable wall, connecting to the internal space of the spacesuit dust removal and cleaning equipment. When the equipment is undergoing high-pressure carbon dioxide gas cleaning, a sealed valve on the pipeline can be opened to connect with the external lunar vacuum environment. Negative pressure then forces the carbon dioxide gas mixed with lunar dust out into the lunar vacuum. (60 Horizontal beam, 61 High-pressure carbon dioxide gas storage device, 62 Sealed valve, 63 Connecting pipeline, 64 Vertical pipeline within the spacesuit dust removal and cleaning equipment, 65 Nozzle on the vertical pipeline, 66 Connecting pipeline between the high-pressure carbon dioxide gas storage device and the vertical pipeline, 67 Sealed valve on the connecting pipeline, 68 Support frame, 69 Small motor, 70 Rotating component driven by the small motor, 71 Rotating component driving the rotating vertical rod, 72 Horizontal rod connecting the vertical rod, 73 Longitudinal beam, 74 Electric heating device, 75 Water electrolysis hydrogen-oxygen production device, 76 Sealed water tank.)

[0058] The electronic barometer, electromagnetically controlled sealing valve, water electrolysis hydrogen-oxygen production equipment, sealed water tank, electric heating equipment, high-pressure carbon dioxide gas injection device, flat battery pack, and manual control module are included. The electrical connection wires and power supply signal lines between these devices and between the devices and the manual control module are standard and known wiring structures for aerospace equipment and are not part of the innovation of this invention. To simplify the drawings and highlight the core improvement of this invention—purely manual operation without automatic control logic—all electrical connection lines are omitted in the drawings. The hardware structures of all devices are existing mature equipment; the installation locations of some devices are omitted in the drawings, and the structural improvements of the devices themselves are not reflected. The innovation of this invention is that the entire set of auxiliary equipment is operated solely by the manual control module, without dedicated control logic for automatic and semi-automatic adjustment modes.

[0059] Connecting pipes on the gable wall: If the enclosure is made of aluminum alloy, use aluminum alloy round pipes, which pass through the gable wall and are welded or bonded for sealing. If the enclosure is made of carbon fiber composite material, use carbon fiber composite round pipes, which pass through the gable wall and are bonded for fixing and sealing.

[0060] Overall beneficial effects: This invention addresses the systemic deficiencies of existing technologies by designing a nested, expandable container structure, a flexible, multi-level sealing system with a sealed inner lining, a three-tiered progressive lunar dust isolation architecture, and a lunar dust cleaning and adsorption device specifically designed for spacesuits. It also integrates a water electrolysis hydrogen-oxygen production device, a sealed water storage structure, and an electric heating temperature control device to construct an autonomous, habitable environmental control system. Furthermore, it incorporates a human-machine-assisted motion docking system and a minimalist control architecture with purely manual single-control functionality. Compared to existing technologies, this invention offers the following overall systemic beneficial effects: 1. Expandable cabin space to meet the phased construction needs of a lunar base: This invention employs a nested container structure that can shrink and reduce volume during launch and expand during landing operations, breaking through the limitations of the launch envelope. It eliminates the need for multiple heavy-lift resupply missions, allowing for rapid expansion of astronaut living and research space on the lunar surface, perfectly adapting to the initial construction conditions of a lunar base's first landing, starting from scratch, and phased expansion. 2. Multi-level, graded isolation + dedicated dust removal completely prevents lunar dust from intruding into the main research station. This invention features a three-tiered independent lunar dust isolation system, equipped with a lunar dust cleaning and adsorption device for spacesuits, and a multi-level sealing structure with a flexible sealing liner. This forms a progressive, three-dimensional lunar dust prevention system that intercepts, adsorbs, and isolates dust. It effectively blocks fine lunar dust throughout the entire process of astronaut entry and exit, equipment transfer, and module docking, preventing lunar dust from entering the main research module and causing equipment contamination, seal wear, and pipeline blockage. This significantly improves the stability of equipment and the cleanliness of the research environment for long-term lunar deployment. 3. Integrating in-situ environmental support equipment, this invention autonomously constructs a habitable extraterrestrial environment. It integrates a water electrolysis hydrogen and oxygen production device, a sealed water tank storage structure, and an electric heating temperature control device. This allows for autonomous water storage, in-situ preparation of breathable hydrogen and oxygen gas, and adaptive temperature control within the lunar high vacuum, extreme temperature differences, and lack of atmosphere. Without ground resupply, it can construct a stable, safe, and suitable artificial habitable sealed environment, significantly enhancing the self-sufficiency capability for independent deep-space deployment. 4. Human-machine assisted, low-difficulty docking significantly reduces the burden on astronauts during station construction. This invention is equipped with a dedicated motion system and controllable motion architecture, enabling the alignment, fitting, docking, and reliable sealing of multiple research modules with minimal astronaut assistance and simple command control. It abandons the traditional fully automated, high-precision, and complex docking process, greatly simplifying assembly steps, reducing astronaut lunar surface operations, and lowering the difficulty of manual construction. This allows for rapid prototyping and station construction during the first landing, significantly improving the initial construction efficiency of the lunar base. 5. A purely manual, single-control system fundamentally avoids the risk of deep-space autonomous control malfunctions. All environmental control, dust removal, airtightness, and media preparation auxiliary equipment in this invention are uniformly controlled by a single manual control module. This completely eliminates automatic and semi-automatic intelligent control programs and sensor-linked autonomous execution logic. There is no system autonomous intervention, no program malfunctions, and no signal interference. The control logic is extremely simple, with few fault points and extremely strong resistance to deep-space interference, making it suitable for high-reliability operational scenarios such as initial lunar construction and commissioning, emergency maintenance, and long-term unmanned stays.6. Overall adaptability to extreme environments on multiple planets, strong versatility and engineering practicality. The nested expansion structure, multi-level dustproof sealing system, minimalist and reliable control architecture, and in-situ environment self-sufficiency system of this invention are not only suitable for lunar landing and station construction conditions, but also for scientific research and residence missions on other extraterrestrial planets with no atmosphere, high dust, and extreme temperature differences. It has strong structural adaptability, high fault tolerance, and strong practicality, and has extremely high engineering application value for deep space exploration.

[0061] Combined with nested split-type enclosures, the hatch labyrinth seal is resistant to extreme temperature differences, landing impacts, and has no risk of aging and failure, improving the long-term airtight reliability of the multi-planet landing module. It also eliminates the need to replace easily damaged rubber rings, resulting in lower maintenance costs.

[0062] The beneficial effects of this nested box structure are: precise dimensional gradient nesting, achieving a seamless, structureless fit. Through precise dimensional matching of the outer layer (3000×2570×2570mm) and the inner layer (2530×2500×2500mm), combined with a uniform 4mm wall thickness and a uniform R100 arc forming structure, the double-layer box achieves a purely mechanical nesting without any intermediate support structure. The structure is extremely simple, highly reliable, and has an extremely low failure rate.

[0063] The stepped groove structure, combined with double-sided double-welding process, improves the positioning and fitting accuracy of the gable wall components and the box body. The two independent welds on the inside and outside doubly block leakage channels, significantly improving the airtightness and sealing of the box body gable wall assembly position and reducing the risk of leakage.

[0064] Multi-planet extreme environment adaptability: This invention uses 6mm aerospace-grade carbon fiber composite material with a near-zero coefficient of thermal expansion, capable of withstanding long-term cycling under extreme temperature differences of -140°C to +125°C on the lunar surface without thermal expansion and contraction, warping, delamination, or cracking. The extremely low thermal conductivity of carbon fiber completely avoids the problems of high thermal conductivity, heat penetration, and internal thermal runaway associated with traditional aluminum alloy enclosures. Combined with a 100mm large-arc fatigue-resistant structure, it can withstand long-term multi-planet thermal cycling loads, micro-vibration loads, micro-meteorite impacts, and space radiation erosion. This structure is also adaptable to the extreme temperature difference and electrostatic dust environment of the moon and the low-pressure, sandstorm, and low-temperature environment of Mars, possessing universal landing and service capabilities for multiple planets.

[0065] Precisely nested gradient dimensions enable a fully planar fit for load-bearing capacity. The precise dimensional matching of the outer casing (3000mm×2570mm) and the inner casing (2530mm×2500mm) allows for seamless, unsupported, and gapless assembly of the double-layered enclosures, resulting in a minimalist structure with extremely high rigidity and excellent overall synchronization. The all-carbon fiber zero-expansion material completely solves the problem of thermal deformation and cracking in deep space. Aerospace-grade carbon fiber combined with an R100 large-arc corner structure eliminates stress concentration, ensuring no deformation or cracking even after millions of high and low temperature cycles, significantly extending the deep-space service life of the landing module. Excellent airtightness and strong resistance to deep-space corrosion are also key features. The four-plate integrated molding and fully arc-shaped stress-free structure provide excellent sealing performance, effectively blocking lunar dust, atomic oxygen, and vacuum leakage, meeting the requirements for long-term deep-space deployment. Strong multi-planet compatibility is also crucial; this nested enclosure structure can be adapted to various deep-space exploration missions, including those to the Moon, Mars, and asteroids, offering high versatility and significantly reducing the development cost and iteration cycle of deep-space landing equipment.

[0066] By precisely measuring the dimensions of the enclosure's gable wall, a stepped groove carbon fiber gable wall component was customized. This ensures high precision, simple assembly and positioning, and eliminates the need for on-site repairs, significantly improving assembly efficiency. The stepped groove structure forms a double-layer bonding base surface, allowing for simultaneous double-layer bonding and sealing on both sides, creating a double-layer independent sealing barrier. This greatly enhances the overall airtightness and watertightness protection performance and reduces the risk of leakage. The stepped steps limit the adhesive layer and accommodate excess adhesive, preventing adhesive from flowing out and contaminating the external thermal insulation structure of the enclosure, thus ensuring the integrity of the enclosure's appearance and thermal control coating.

[0067] The FSW is integrally formed with a circular arc, resulting in a shell with extremely high airtightness and fatigue resistance. It is formed by integral bending of a large circular arc and friction stir welding, eliminating the weak defects of traditional right-angle cuts, repair welding, and splicing. The box structure is continuous and stress is dispersed, making it suitable for decades of long-term cold and hot cycle service in deep space.

[0068] Three-stage gradient zoned dust removal, with graded dust treatment, resulting in higher purification efficiency: Large, coarse lunar dust is pre-removed from the outer compartments, while ultrafine charged dust is deeply purified in the inner compartments. A dust-free buffer zone separates the connecting compartments, treating coarse and fine dust in different areas. This solves the problem of easy clogging and rapid wear of filter media in single dust removal stations, significantly reducing equipment maintenance and replacement costs. 2. Independent, sealed zoned structure to prevent cross-cavity dust contamination: The three compartments are airtightly isolated by sealing plates and flexible sealing linings. Dust generated by coarse dust removal is confined to the outer compartments and will not intrude into the inner fine purification and buffer areas, protecting precision components such as HEPA filters and electrostatic electrodes from scratches and wear by hard, coarse particles. 3. Multiple dust removal mechanisms synergistically adapt to lunar dust characteristics: Blowing + adsorption removes large floating dust particles, electrostatic + fine filter media captures ultrafine charged dust, and HEPA fine filtration + micro-positive pressure builds a dust-free barrier. These three dust removal systems work together to cover lunar dust of all particle sizes, completely eliminating dust residue on the surfaces of spacesuits and detection equipment. 4. Adaptable to multi-planetary research station landing conditions, with high integration: Coarse dust removal, fine dust removal, and dust-free buffering are all integrated inside the nested box airlock transition chamber, eliminating the need for external independent dust removal equipment. Personnel and equipment can be transferred sequentially to complete step-by-step dust removal, achieving automated and sealed operation with no risk of dust leakage. 5. The nested box + flexible sealing liner + multi-compartment sealing thin plate combination forms multiple airtight isolation layers. The slightly positive pressure buffer compartment forms an air pressure protection barrier, doubly preventing the backflow of dust from external planets. The graded isolation and protection capabilities are far superior to traditional single-chamber airlock chambers.

[0069] This invention employs HEPA high-precision filtration for dust removal, effectively intercepting micron- and submicron-sized fine dust particles in the air. Compared to ordinary filters, it offers higher filtration accuracy, completely eliminating dust-laden air within the chamber and improving cleanliness from the source. This invention adds a micro-positive pressure dust control structure within the chamber, ensuring the internal air pressure of the sealed docking compartment is slightly higher than the external ambient air pressure. This positive pressure barrier seals gaps in the chamber and docking joints, completely preventing the backflow of dusty external air and overcoming the limitations of traditional single-filter structures that cannot prevent external dust intrusion. This invention combines a sealed structure, HEPA fine filtration, and micro-positive pressure dust control into an integrated dustproof system, rather than simply stacking components. Through structural coordination, it achieves dual dustproof protection, significantly improving the stability and reliability of the equipment's cleanroom environment. This invention maintains a high-cleanliness buffer environment throughout the entire process of material docking, chamber opening and closing, and workpiece transfer, preventing dust from entering the core working area, effectively improving equipment operating accuracy and product yield. It has a wider range of applications and provides consistently stable dustproof performance.

[0070] This invention innovatively employs a rigid-flexible-rigid alternating sealing and compression structure. It features a customized, graded sealing solution for the multi-layered assembly structure of the landing module's flexible liner, rigid gable, and rigid interfaces of connecting components. This addresses the industry pain points of traditional single-rigid seals (leaking) and single-flexible seals (easily damaged). The complementary rigid-flexible structure and graded load-bearing capacity significantly improve sealing reliability in extreme environments. It is compatible with two mainstream rigid gable materials: carbon fiber and aluminum alloy, offering strong compatibility and meeting the in-situ construction requirements of different planets and loads. Precise fixation of the flexible liner is achieved through limiting slots and anti-foolproof bosses, completely resolving issues of flexible sealing layer misalignment, displacement, and insufficient pressure, ensuring uniform compression of the sealing surface. An elastic constant pressure compensation component is incorporated to offset deformation deviations caused by sudden temperature changes, thermal expansion and contraction, and landing vibrations on extraterrestrial planets, maintaining a constant sealing compression force and preventing seal failure due to compression force attenuation during long-term service, thus significantly extending the service life of the sealing structure. The three-tiered structure—inner flexible airtight layer, middle flexible buffer layer, and outer rigid locking layer—retains the advantages of rigid structures such as high strength, impact resistance, and non-deformation, while leveraging the adaptive deformation, gapless fit, and noise reduction characteristics of flexible structures. Its airtightness, structural stability, and environmental adaptability are significantly superior to existing technologies, meeting the sealing requirements for long-term deployment of multi-planetary containerized research stations. The overall structure is highly modular and integrated, with a simple assembly process, suitable for unmanned assembly, rapid splicing, and in-situ construction on extraterrestrial planets. It requires no complex debugging, greatly improving the efficiency of planetary research station construction and assembly.

[0071] This invention addresses two core pain points of existing technologies by designing a multi-level isolated nested cabin structure and an integrated dust removal system, along with an initial operational transitional adaptation structure. This delivers two core beneficial effects, while the auxiliary systems utilize existing technologies without adding any new benefits. It completely blocks lunar dust intrusion, ensuring the clean and safe operation of the main research station. This invention employs a multi-level isolation, multi-layered nested compartment structure combined with a graded dust removal device, forming a comprehensive lunar dust protection system of "layered isolation, step-by-step dust removal, and closed-loop dust control." Throughout the process of astronauts, equipment, and supplies entering the cabin, it intercepts, adsorbs, and removes adhering and suspended lunar dust of different particle sizes layer by layer, preventing ultrafine lunar dust from entering the core cabin of the main research station with personnel and supplies. This effectively avoids lunar dust abrading precision scientific equipment, clogging pipeline structures, and polluting the cabin's atmospheric environment, significantly improving the lifespan of lunar research station equipment, the cleanliness of the cabin environment, and the safety of astronauts, adapting to the needs of long-term lunar surface scientific research operations.

[0072] To address the challenges of the initial construction and transition of a lunar base, and to ensure smooth operation from initial entry into the cabin, this invention incorporates a transitional buffer structure adapted for building a lunar base from scratch. It is specifically optimized for all scenarios, including initial docking of the cabin, initial entry of astronauts, initial system debugging, and the initial transitional operation of the base. This effectively solves problems such as unstable sealing during initial docking of traditional equipment, fluctuations in the cabin environment, lack of buffer for personnel entry and exit, and numerous compatibility failures between new and old cabins. It significantly reduces the failure rate during the initial construction and debugging of the lunar base, shortens the base's construction and commissioning cycle, and ensures a smooth transition from the initial construction phase to normalized operation of lunar nested container-type or other structural research stations, supporting the rapid landing and stable operation of the lunar base.

[0073] The electrostatic dust removal, fine dust removal, consumable-free dust cleaning, and vacuum environment adaptability functions inherent in EDS electric curtain dust removal are existing, known technical effects and are not innovations of this invention. This invention achieves the following unique and systematic benefits by exclusively integrating an independent EDS electric curtain dust removal system into the key internal sealed docking compartment and incorporating it into the overall multi-level lunar dust prevention system, employing a purely manually controllable start-stop architecture: 1. Precisely removes lunar dust from docking dead zones, filling the blind spots of traditional physical dust prevention. In nested docking, the gaps in the end-face sealing and bonding areas are narrow and the structure is complex, making it difficult for conventional physical barriers, blowing, and adsorption structures to completely remove hidden residual lunar dust. This invention independently sets up an EDS electrostatic active dust removal unit in the core docking compartment, utilizing the advantages of non-contact dust removal via electric field to precisely remove fine lunar dust from gaps, walls, and bonding surfaces, completely solving the problem of dust accumulation in docking dead zones and perfecting the graded lunar dust prevention system. 2. No water washing, no consumables, and adaptable to the extreme vacuum environment of the moon. EDS (Electric Shutter Control System) curtain dust removal is a pure electric field physical dust removal method. It requires no water resources, no filter replacement, and no mechanical friction, making it suitable for the high vacuum, lack of water source, extreme temperature differences, and unsuitable conventional cleaning conditions on the moon. It can stably perform dust removal operations in docking areas for extended periods, demonstrating strong deep-space adaptability. 3. Purely manual start-stop, completely eliminating the risk of accidental triggering of the dust removal system. This invention eliminates all automatic sensing, semi-automatic timing, and dust-linked start logic of the EDS dust removal equipment. Dust removal is only manually activated as needed, avoiding accidental dust removal without instructions and long-term idle power consumption caused by lunar electromagnetic radiation and sensor interference. It offers high controllability, low energy consumption, and strong on-site safety. 4. Multi-level protection linkage significantly improves the overall airtightness lifespan and scientific cleanliness of the spacecraft. This invention forms a progressive three-dimensional protection system consisting of "external multi-level physical dust isolation + flexible inner lining sealing barrier + internal docking area EDS active electric curtain dust removal," blocking lunar dust from entering the main research module at the source. This significantly reduces wear on sealing structures, valve jamming, and equipment dust accumulation malfunctions, greatly improving the airtightness stability and cleanliness of the research environment during long-term lunar stays. 5. Fixed-point integrated layout, without interfering with the nested movement of the modules and the docking sealing structure. The EDS electric curtain dust removal device is thinly and closely fitted to the inner wall of the sealed docking compartment, without occupying docking space, interfering with the expansion and contraction of the nested modules, or affecting the end-face sealing and locking docking actions. It has strong structural adaptability and high integration, perfectly adapting to multi-planet expandable nested station architecture.

[0074] The basic functions of the equipment, such as electronic barometer pressure monitoring, electromagnetic sealing valve airtight on / off, water electrolysis hydrogen and oxygen preparation, sealed water tank water storage and circulation, electric heating temperature control, and high-pressure carbon dioxide jet dust removal and cooling, are inherent and known effects of existing supporting equipment and do not constitute the innovative technical effects of this invention. This invention adopts a manual single-control, no automatic / semi-automatic program control architecture, producing the following unique and beneficial effects: 1. Completely avoids the risk of automatic program malfunction in deep space environments. Lunar radiation, electromagnetic interference, and sensor drift can easily cause traditional automatic control systems to malfunction by starting or stopping valves, heating, or jetting. This solution completely eliminates autonomous control logic, requiring only manual operation, preventing equipment from operating without instructions and improving the safety of operation in the sealed environment of the cabin; 2. Extremely simple structure and control logic, significantly reducing the number of fault points. Eliminating automatic control chips, linkage algorithms, timing programs, and multi-level signal judgment circuits simplifies the entire electrical control system's hardware and software structure, reducing the probability of circuit failure and program jamming under long-term unattended operation; 3. Completely independent manual operation authority, with no forced system intervention. Operators can individually turn any type of equipment on or off as needed, or simultaneously operate multiple devices. The system will not automatically interrupt or modify manual operations based on data from sensors such as air pressure, making it suitable for emergency maintenance on the lunar surface and fixed-point debugging in sealed cabins. 4. Low maintenance difficulty, suitable for on-site maintenance scenarios on the moon. There are no complex automatic control programs; troubleshooting only requires checking the basic electrical wiring between the manual control module and each device, without needing to debug intelligent control algorithms, facilitating rapid on-site maintenance by astronauts.

[0075] The lithium battery power supply function of the flat battery pack, the manual module circuit control function, the water electrolysis hydrogen and oxygen preparation function, the electric heating temperature control function, the sealed water tank water storage function, the electronic barometer air pressure detection function, and the electromagnetic control sealing valve pipeline on / off sealing function are all inherent and known technical effects of existing equipment and do not constitute the innovative technical effects of this invention. This invention achieves the following unique and systematic beneficial effects by rationally zoning and integrating all the above-mentioned mature and known equipment within a multi-level isolated, dust-proof, flexible, sealed nested cabin, with unified power supply and unified centralized manual control: 1. Scientific equipment zoning layout, adaptable to the expandable nested cabin construction system. This invention neatly arranges environmental protection equipment on the cabin walls and centrally arranges airtightness monitoring and pipeline sealing valve equipment on the gable wall pipeline location. The zoning is clear and does not interfere with each other, fully adapting to the overall structural characteristics of the nested cabin's shrinkable and expandable design, resulting in high space utilization and meeting the construction needs of a lunar base with phased construction and rapid initial landing. 2. Unified power supply and unified centralized manual control make the entire cabin's electrical system extremely simple and reliable. All auxiliary equipment is powered by a unified flat-panel lithium battery pack and centrally controlled by a manual control module, abandoning the complex architecture of traditional multi-device decentralized electrical control and multi-level automatic linkage. The circuit links are simple, with fewer potential failure points, and it exhibits strong anti-interference capabilities and high operational stability in the lunar environment of strong radiation, electromagnetic interference, and extreme temperature differences. 3. Purely manual operation eliminates the risk of automatic control malfunctions, ensuring extremely high safety during stays. This invention completely eliminates the automatic, semi-automatic, and sensor-linked autonomous control logic; all equipment actions are entirely controlled manually, completely eliminating the safety hazards of automatic control system malfunctions, accidental heating, accidental gas production, and accidental valve opening and closing in the complex lunar environment. Controllability and operational safety are far superior to traditional intelligent automatic control cabins. 4. All known equipment is in a multi-level, dust-proof, sealed, and clean environment, significantly extending equipment lifespan. This invention utilizes a unique three-level lunar dust isolation system, a flexible sealed liner, and a nested sealed cabin structure to protect all electrical, environmental control, sensing, and valve equipment within a clean, sealed cabin. This effectively isolates the system from fine lunar dust contamination, extreme external temperatures, and deep-space radiation, significantly improving the service life and operational stability of existing conventional aerospace equipment under extreme extraterrestrial conditions. 5. The invention is easy to operate and requires minimal maneuvering, greatly reducing the burden on astronauts during lunar station construction. All environmental and airtightness protection equipment within the entire cabin is centrally controlled at a single point, eliminating the need for complex program debugging, mode switching, or handling automatic program malfunctions. Astronauts can manage all auxiliary equipment through a manual control module, making it suitable for first lunar landings, rapid station construction, low-maintenance, and highly reliable long-term stay missions.

[0076] Compared to existing lunar battery thermal management technologies, this invention, specifically designed for the extremely cold vacuum environment of the lunar shadow region, achieves significant advancements and beneficial effects through an integrated technical solution encompassing passive heat retention, waste heat self-utilization, active precision control, redundancy and fault tolerance, and a backup heat source: It achieves high-precision, fixed-point constant temperature control in extremely cold environments, solving the core problem of equipment failure. This invention breaks through the limitations of existing technologies in wide-range temperature control, achieving for the first time high-precision, fixed-point constant temperature control of the battery housing cavity at 30°C±3°C under full low-temperature conditions ranging from -230°C to -100°C in the lunar shadow region. This completely eliminates problems such as electrolyte freezing, drastic increase in internal resistance, charge / discharge failure, and permanent damage in extremely cold environments, comprehensively ensuring the long-term stable operation of the energy storage system in the lunar shadow region. Waste heat recovery and adaptive utilization significantly reduce temperature control energy consumption. This invention innovatively recovers the Joule heat generated during the charging and discharging of batteries as a basic constant-temperature heat source. Under normal operating conditions, it can completely eliminate the need for active electric heating. Compared with traditional continuous heating temperature control solutions, temperature control energy consumption is reduced by more than 90%, effectively adapting to the energy-scarce, lightweight, and low-power operation requirements of lunar bases, and significantly extending on-orbit endurance. A comprehensive extreme cold fault-tolerant design greatly improves system reliability. This invention employs cold-resistant special materials, dual-path hardware redundancy, digital twin self-healing algorithms, and a deep hibernation soft-start mechanism, solving the defects of conventional temperature control devices such as ultra-low temperature embrittlement, failure, and control drift. Combined with electrochemical + isotope dual-redundant heat sources, it can achieve decades of maintenance-free stable operation, completely avoiding the risk of temperature control system paralysis under long-term operating conditions in lunar nights and permanently shadowed regions, significantly improving mission reliability. It is adaptable to all scenarios of lunar shadow conditions, exhibiting extremely high versatility and adaptability. This invention is adaptable to all shadowed operating conditions, including lunar base shadowed areas, ordinary lunar night shadowed areas, and ultra-low temperature shadowed areas of permanent polar craters, covering different low-temperature gradient environments. It is compatible with various types of lunar surface energy storage batteries, offering broad structural adaptability and comprehensive operating condition coverage. It can be applied on a large scale to the construction of lunar base energy storage thermal management systems. Precise temperature control response and uniform temperature difference extend battery life. This invention employs global distributed temperature measurement and graded precise heating technology, ensuring a temperature difference of ≤5°C between individual batteries within the cabin, eliminating localized overcooling or overheating. The optimal constant temperature of 30°C minimizes battery cycle losses, effectively extending battery cycle life and on-orbit service life, and reducing the operation and maintenance costs and replacement costs of equipment on the lunar base. With its simple structure and high safety, this invention is compatible with deep space aerospace engineering standards. It adopts a composite architecture with passive heat insulation as the main feature and active heat replenishment as the auxiliary feature. It has no complex moving heat dissipation structure, resulting in low equipment failure rate and excellent resistance to radiation and extreme cold fatigue. The independent sealed cabin provides physical isolation and contains no flammable consumables, meeting the safety standards for fire prevention, heat insulation, and thermal runaway prevention of aerospace energy storage systems. It is highly practical and safe for engineering applications.

[0077] Battery energy storage and power supply, conventional electric heating, temperature sensing, basic PID calculation, and conventional thermal insulation materials are all known functions of existing equipment and do not constitute the innovative effects of this invention. This invention achieves the following unique and significant technical effects through a unique integrated system architecture: a vacuum-sealed cavity bearing capacity, multi-layer passive heat locking, battery waste heat recovery and reuse, autonomous power supply and active heating, dynamic PID precise temperature control, extreme cold fault tolerance protection, redundant heat source backup, and whole-cabin linkage automatic constant temperature control. 1. It achieves a constant and precise 30°C temperature for the battery in lunar shadow areas, completely solving the problem of low-temperature degradation. This invention, through a vacuum-sealed cavity to isolate cold sources, multi-layer thermal insulation to reduce heat loss, and PID dynamic power adjustment for precise temperature control, can stably lock the battery temperature field within the optimal 30°C operating range for a long period in the permanently shadowed areas of the moon and in the extreme low-temperature environment of the lunar night. This significantly avoids industry pain points such as low-temperature capacity degradation, soaring internal resistance, and inability to start at low temperatures. 2. Battery waste heat recovery and reuse significantly reduces energy consumption for deep space self-sufficiency. This invention features a unique battery-generated Joule waste heat recovery and temperature-locking mechanism, which collects and reuses previously lost waste heat to assist in temperature control. This significantly reduces the working time and power consumption of the active electric heating module, greatly improving the self-sufficiency rate of extraterrestrial energy in the absence of ground resupply, and is suitable for long-term unmanned stays. 3. Passive heat locking + active heat replenishment coupling provides temperature control stability far exceeding traditional single thermal control modes. It adopts a dual-mode coupling architecture of "passive multi-layer thermal insulation long-term temperature locking + active dynamic precise heat replenishment," which reduces heat loss and precisely compensates for temperature fluctuations. The temperature field fluctuation is minimal, and the temperature control robustness is extremely strong, making it suitable for the complex conditions of the moon, such as the extreme temperature difference between day and night and the continuous extreme cold in the shadow areas. 4. Dual protection against extreme cold and redundant heat sources ensures zero risk of temperature control failure. Equipped with an extreme cold fault-tolerant protection mechanism and a redundant, uninterrupted heat source architecture, it can withstand lunar electromagnetic interference, radiation interference, instantaneous voltage fluctuations, and sudden extreme cold shocks. The entire system has no single point of failure and extremely high reliability for long-term deployment. 5. Integrated automatic control system adapts to multi-planetary station construction systems. The entire thermal control system integrates and adapts to a nested lunar dust-proof airlock transition module architecture, and is uniformly connected to a manual control module to achieve real-time automatic temperature control across the entire system. It requires minimal manual intervention to achieve high-reliability, constant-temperature self-sufficiency of the battery throughout its entire lifecycle, perfectly suited for rapid station construction during the first lunar landing and long-term unmanned scientific research missions.

[0078] Enhanced control flexibility: This solution significantly improves system operational flexibility by introducing a parallel design of multiple control modes without priority. During actual mission execution, astronauts or the ground control center can switch control sources in real time according to specific needs. For example, manual control mode can be selected when precise operations are required, while switching to remote wireless control mode is used in long-distance or complex mission scenarios. This flexible control approach not only reduces the limitations of a single control mode on mission execution but also greatly improves mission efficiency. Furthermore, because the manual control module can respond to received signals in real time, the system can quickly adjust operating commands regardless of changes in the signal source, ensuring the continuity and efficiency of mission execution. Enhanced reliability: The design of multiple control modes acting as backups significantly enhances the overall reliability of the system. In special environments, equipment may face various emergencies, such as communication interruptions, power failures, or environmental interference. In this solution, when one control mode fails, other control modes can quickly take over the task, ensuring the normal operation of the equipment. For example, if the radio transmitter / receiver fails, the manual control module can still receive commands through the local handheld controller and send electrical control operation execution signals to the electric motion system, thereby avoiding mission interruption. This multi-backup mechanism not only enhances the system's resilience but also provides greater security for mission execution in complex environments. Regarding environmental adaptability, all equipment involved in this solution is designed for special environments (such as airlock transition chambers) to ensure stable operation in harsh conditions. For example, the camera assembly utilizes special materials and protective designs resistant to vacuum and extreme temperatures, maintaining normal shooting functionality in extreme environments; the flat-plate battery pack, through optimized material and circuit design, possesses high energy density, long lifespan, and resistance to harsh environments, providing stable power support for the system. Furthermore, key components of the radio transmitter / receiver device and manual control module have undergone special treatment to reduce the impact of environmental factors on equipment performance. These designs not only improve the system's environmental adaptability but also expand its application scenarios in aerospace, field operations, and other fields, providing reliable technical support for mission execution in complex environments. Detailed Implementation

[0079] Example 1: Nested Double-Layer Aluminum Alloy Box Forming and Assembly Structure: Nested Double-Layer Box Main Structure (Landing Module Core Bearing Shell) The main shell of the multi-planet nested scientific research station landing module of this invention adopts a double-layer 6061 aerospace aluminum alloy nested box structure, including an outer protective box and an inner equipment bearing box. Both boxes are made of 4mm thick 6061 aluminum alloy plates. The corners of the boxes are formed by integral bending with a smooth arc of R100mm, eliminating the stress concentration defects of traditional right-angle boxes and improving the structural fatigue resistance under extreme temperature difference alternation, micro-vibration, and impact conditions. The double-layer box of this invention adopts a size gradient design with the outer layer larger than the inner layer. After the inner and outer boxes are assembled, they achieve a tight fit across the entire plane. No intermediate structures such as heat insulation support columns, vibration isolation structures, gap filling materials, or suspension connectors are set between the two boxes. The overall surface fit and nesting assembly are achieved solely by the difference in contour dimensions. The structure is simple, with high overall rigidity, uniform load transfer, and consistent thermal stress distribution, making it suitable for long-term service in the extreme high and low temperature alternation environments of the Moon and Mars.

[0080] Outer Protective Shell Structure Parameters and Molding Process: The outer shell serves as the primary protective load-bearing shell for the landing module. It is formed by bending a 4mm thick 6061 aluminum alloy sheet into a circular arc shape. The external dimensions of the shell are: length 3000mm, width 2570mm, and height 2570mm. The outer shell is formed using a one-piece bending process, with smooth transitions at the four corners using a large 100mm radius arc. There are no sharp corners, segmented cuts, or welded reinforcement plates. The entire shell is sealed using friction stir welding (FSW), resulting in high weld strength, good airtightness, and excellent structural continuity. It possesses basic protective capabilities against lunar micrometeorite impacts, atomic oxygen erosion, space radiation, and electrostatic lunar dust adhesion. As the overall external protective substrate, the outer shell bears the external mechanical loads of the landing module, environmental erosion, thermal control structure adhesion, and overall shape shaping functions.

[0081] Existing planetary landing modules and research modules mostly employ single-layer metal shells, welded aluminum alloy boxes, or nested composite structures of equal dimensions. Metal materials have high thermal conductivity and a high coefficient of thermal expansion, making them highly susceptible to thermal stress deformation, weld cracking, structural warping, and internal thermal runaway under the extreme temperature fluctuations of the lunar surface (-140°C to +125°C). Existing nested modules generally utilize interlayer thermal support columns, suspension gaps, and filled sandwich structures, resulting in complex structures, large assembly errors, and low overall stiffness. Under thermal cycling, they are prone to interlayer loosening, uneven stress distribution, and localized fatigue failure. Furthermore, the conventional nested boxes have poorly matched internal and external dimensions, failing to achieve full-area planar fit and load-bearing capacity, and their mechanical and thermal stability is insufficient to meet the requirements for long-term multi-planetary deployments. In addition, traditional metal boxes often use right-angle structures at corners, leading to significant stress concentration, poor fatigue and impact resistance, and inability to withstand millions of thermal cycling cycles in deep space. Therefore, there is an urgent need for a nested landing module box structure with precise gradient dimensions (large on the outside and small on the inside), made entirely of carbon fiber, with large, stress-free, rounded corners, and a completely flat, non-layered fit.

[0082] With the rapid development of deep space exploration technology, the in-situ construction of enclosed containerized research stations on exoplanets has become a core piece of equipment for deep space stays and in-situ scientific exploration. The landing module, as the core carrier for the landing, deployment, and sealing of the research station, directly determines the station's airtightness, dust and radiation protection, and resistance to extreme environments based on the reliability of its assembly and sealing structure. Currently, the sealing structures of landing modules for multi-planet research stations mostly adopt two forms: fully rigid butt joint sealing or single flexible gasket flat sealing. The fully rigid butt joint structure uses carbon fiber and aerospace aluminum alloy rigid components directly bonded and locked, resulting in high structural strength and strong resistance to deformation. However, exoplanets present complex conditions such as sudden changes in high and low temperatures, micrometeorite impacts, celestial micro-vibrations, and thermal expansion and contraction deformation of the module. The rigid component docking lacks buffer margin, making it prone to stress concentration at the docking surface, localized warping, and micro-gap leakage. After long-term service, the probability of seal failure increases significantly, failing to meet the airtightness requirements for long-term stays. Single flexible gasket sealing structures rely on rubber and composite flexible materials to fill the gaps between rigid components, which can accommodate slight deformation and buffering. However, they have significant technical drawbacks: First, the flexible materials are directly exposed to the extreme environment of the planet and are subject to long-term effects from cosmic rays, high and low temperature cycles, and vacuum erosion, making them prone to aging, hardening, cracking, and permanent compression deformation, resulting in a rapid decrease in sealing pressure. Second, the purely flexible structure lacks rigid limiting support, making it prone to gasket misalignment and compression during the landing impact and attitude fine-tuning of the landing module, leading to uneven sealing surface compression and localized air leakage due to insufficient pressure. Third, existing sealing structures are all single-level sealing structures and have not designed an adaptive sealing system for the multi-layer assembly structure of the landing module's flexible liner-rigid gable-rigid connectors, making it impossible to achieve graded sealing and graded compression fixing with alternating rigidity and flexibility. For the core assembly structure of the landing module, existing technologies using carbon fiber and aluminum alloy rigid gables offer advantages such as lightweight, high strength, deformation resistance, and suitability for extraterrestrial construction. These are the mainstream load-bearing enclosure structures for planetary research stations. Rigid connecting components are used to secure and lock various modules and gable modules. However, existing assembly sealing solutions cannot solve four core problems: interface compatibility between the flexible liner and the rigid structure, leakage through hard contact between rigid components, stress concentration at the rigid-flexible interface, and maintaining a constant sealing pressure. Existing sealing technologies generally suffer from poor adaptability, weak resistance to environmental interference, short seal life, and insufficient reliability of compression and fixing. They cannot meet the high airtightness, high stability, and long-life sealing requirements of containerized research stations under complex and extreme conditions on multiple planets, which are required for long-term on-orbit and ground-based deployments. This has become a key technological bottleneck restricting the large-scale and routine application of in-situ extraterrestrial research stations.

[0083] The dimensional parameters of the inner and outer box assembly gable surfaces are accurately collected. 6061 aviation aluminum alloy sheet is selected as raw material. The sheet is milled using a machining center to prepare a matching gable component with a stepped groove structure. After the gable component is assembled into the mating position of the inner and outer box gables, double-pass welding is performed from the inside and outside of the component to achieve full circumferential sealing of the assembly joint.

[0084] Inner Layer Load-Bearing Container Structural Parameters and Molding Process: The inner layer load-bearing container is a sealed container for precision equipment inside the landing module. It is also made of 4mm thick 6061 aluminum alloy sheet. The external dimensions of the container are: length 2530mm, width 2500mm, and height 2500mm. The inner layer load-bearing container uses the same manufacturing process as the outer layer, employing an integral bending process with a 100mm radius rounded corner and a friction stir welding sealing process to ensure the structural integrity, dimensional accuracy, high airtightness, and fatigue resistance of the inner layer load-bearing container. It is used to carry core scientific research equipment for internal measurement and control, power supply, thermal control, life support, and data storage.

[0085] In Example 1, the processing steps for the 6061 aluminum alloy box gable wall are as follows: The dimensional parameters of the gable wall surfaces of the inner and outer box are accurately measured. 6061 aerospace aluminum alloy sheet is selected and a matching gable wall component with a stepped groove structure is prepared by milling in a machining center. After the gable wall component is snapped into place at the mating position of the inner and outer box gable walls, double welding is performed from the inside and outside of the component. The double weld seams form a sealing barrier for the assembly gap.

[0086] The double-layer nested assembly relationship: Because the inner cavity of the outer box is larger than the outer dimensions of the inner box, the inner box is inserted into the outer box from top to bottom. After assembly, the outer wall of the inner box and the inner wall of the outer box form a large-scale, full-area planar contact, without gaps, gaps, or intermediate auxiliary structures. After the double-layer boxes are fully nested, they form a single rigid shell structure. During transportation, under the extreme temperature difference of day and night on the planet, the temperature of the inner and outer boxes changes synchronously, thermal deformation is consistent, and stress is evenly distributed, preventing defects such as interlayer misalignment, local warping, stress concentration, and weld fatigue cracking. After assembly, only limiting strips are set on the outer periphery of the upper and lower end faces of the double-layer boxes to restrict the horizontal relative sliding of the double-layer boxes, without changing, interfering with, or isolating the overall planar contact structure of the inner and outer boxes.

[0087] In this invention, the exterior of the enclosure is pre-wrapped with a multi-layer thermal insulation component (MLI) during the overall assembly stage. The MLI is composed of multiple layers of alternating aluminum-coated polyester reflective film and polyester spacer mesh, continuously wrapped around the outer wall of the enclosure to achieve full surface radiation thermal insulation protection. This wrapping can be prefabricated at the factory or applied on-site before assembly. In Example 1: After the overall processing and sealing inspection of the 6061 aluminum alloy nested enclosure are completed and passed, the prefabrication wrapping process begins; the outer wall of each layer of the enclosure is pre-wrapped with a multi-layer thermal insulation component (MLI). Wrapping Operation Steps: Clean all outer surfaces of the enclosure, removing oil stains and metal burrs to ensure a smooth, unprotruding outer wall; continuously wrap the enclosure with standard aerospace-grade MLI thermal insulation rolls around its circumference, controlling the overlap width to 8-15mm. Add 2-3 layers of reinforcing wrapping at the corners and flange protrusions of the enclosure; ensure the MLI completely conforms to the outer contour of the enclosure, with no gaps or bulges. After wrapping, use high-temperature resistant polyimide tape to seal and fix the edges along the wrapping seams; once the entire outer wall is wrapped, a continuous and complete radiant thermal insulation layer is formed. No secondary disassembly or wrapping is required during subsequent assembly; the entire unit can be assembled and used directly.

[0088] 6061 aluminum alloy enclosure: High rigidity of the metal outer wall, good MLI winding fit, not easy to deform and tear the heat insulation film, and low risk of bumps and knocks during transportation after prefabrication and wrapping.

[0089] Structural Environmental Adaptability Description: This invention employs a 4mm thick 6061 aerospace-grade aluminum alloy combined with a 100mm radius arc stress-free structure, featuring a double-layer, integrally nested configuration. This allows it to withstand long-term extreme conditions including alternating loads with extreme temperature differences from -130°C to +120°C on the lunar surface, vacuum environments, atomic oxygen bombardment, micrometeorite impacts, planetary micro-vibrations, and electrostatic dust adsorption. The double-layered structure effectively enhances overall thermal stability and structural rigidity, avoiding the drawbacks of single-layer enclosures such as large thermal deformation, localized temperature stress concentration, and thin, easily vibrating structures. The overall shell structure is also suitable for service on the surfaces of multiple planets, including the Moon, Mars, and asteroids.

[0090] This embodiment discloses a dust-free buffer docking structure with HEPA fine filtration and micro-positive pressure dust control. The entire device is equipped with an internal sealed docking compartment, which is an independent, sealed cavity structure. The side walls of the cavity are sealed and fixedly connected to the top plate, bottom plate, and side plates with sealing plates of 2-15mm thickness, making the entire docking compartment a completely sealed, independent space to prevent airflow from flowing freely. In this embodiment, a high-grade HEPA high-efficiency fine filtration dust removal component is installed inside the sealed docking compartment. The HEPA filter uses a high filtration level of H13 or H14, which can deeply filter the fresh air entering the cavity and remove suspended dust and particulate impurities. At the same time, this device is equipped with a micro-positive pressure air supply structure. Clean air filtered by the HEPA filter is continuously supplied into the sealed docking compartment, so that the interior of the compartment is always in a micro-positive pressure state, with the internal air pressure higher than the external atmospheric pressure. When the equipment is engaged in material handling or chamber opening / closing operations, the sealed chamber structure, combined with continuous HEPA filtration, ensures clean air inside the chamber. Simultaneously, a slight positive pressure barrier allows airflow to escape from the chamber gaps, preventing dusty and polluted air from entering. This embodiment, through the coordinated use of a sealed structure, high-precision HEPA dust removal, and a slightly positive pressure dust control structure, creates a stable and high-precision dust-free buffer environment within the equipment, effectively solving the technical problems of insufficient cleanliness, easy dust intrusion, and inability to remove accumulated dust in traditional cleanroom structures. The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Any modifications, equivalent substitutions, or improvements made within the structural concept and principle of the present invention should be included within the scope of protection of the present invention.

[0091] Example 1: This example discloses a multi-planetary research station landing tiered isolation lunar dust-proof airlock transition chamber with nested box body and flexible sealing liner. It includes an outer box body and an inner box body, with a flexible sealing liner between the inner and outer boxes. The inner box body is divided into outer compartments, inner compartments, and internal sealed docking compartments using a 2-15mm thick sealing plate. Each compartment is sealed and fixed to the top plate, bottom plate, and side plate respectively, achieving independent airtight isolation of each chamber. The outer compartment serves as a coarse dust removal station, equipped with spacesuit dust removal and cleaning equipment. Multiple sets of high-volume blowing nozzles are arranged around the spacesuit placement area, using multi-angle high-speed airflow to peel away spacesuit dust and detect agglomerated and loose large-particle lunar dust on the equipment surface. Downstream of the blowing is a coarse particle adsorption dust removal component, employing a combination of coarse filter bags and adhesive adsorption rollers to instantly trap all coarse dust particles, confining dust emissions only within the outer compartment. After coarse dust removal, the spacesuits and equipment are transferred to the inner fine dust removal compartment. Within this compartment, electrostatic adsorption dust removal components and fine particle filtration dust removal components are arranged sequentially along the airflow direction. High-voltage electrostatic electrodes create a uniform electric field, adsorbing suspended ultrafine charged dust particles onto the collecting plates, while uncharged neutral dust particles are intercepted by downstream multi-layer fine filter membranes. Circulating airflow continuously sweeps the surface of the workpieces, removing stubborn residual dust particles and simultaneously capturing them. After purification, the workpieces are transferred to an inner sealed docking compartment, equipped with H13 / H14 high-grade HEPA fine filtration dust removal components and a micro-positive pressure air supply mechanism. Clean fresh air is continuously delivered into the compartment through HEPA filtration, maintaining a stable micro-positive pressure within the compartment. Airflow overflows through gaps, preventing external dust from seeping in, forming a dust-free transfer buffer space for equipment and personnel docking and transfer. The entire cabin follows a progressive, hierarchical purification logic: coarse dust removal on the outside → fine dust removal on the inside → dust-free buffer zone in the docking compartment. It eliminates planetary dust of different particle sizes step by step, and with a multi-layer sealing structure, it achieves hierarchical isolation and dust prevention, meeting the dust-free protection requirements for lunar and terrestrial planetary scientific research landing operations.

[0092] In this embodiment, an independent internal sealed docking compartment is set up inside the airlock transition chamber. This compartment is the core operating area for multi-chamber nesting docking, end-face sealing, and locking, and is a critical location where lunar dust accumulates and is easily brought into the main cabin during docking. In this embodiment, an independent EDS electric curtain electrostatic dust removal device is independently installed and fixed on the inner wall of the internal sealed docking compartment. The EDS electric curtain dust removal device adopts the existing mature aerospace electrostatic dust removal structure, consisting of built-in electrodes, a high-dielectric substrate, and a high-voltage drive module. It relies on the traveling wave electric field, dielectric force, and electrostatic force to suspend, peel off, and directionally remove fine lunar dust. Its dust removal physical principle, hardware structure, circuit drive method, and electric field parameter control method are all existing known technologies, and this embodiment does not make any structural or principle improvements. The entire EDS electric curtain dust removal system is electrically connected to the cabin's flat battery pack and is stably powered by a unified energy storage power supply inside the cabin; at the same time, the EDS dust removal drive unit is signal-connected to the manual control module, which serves as the sole control terminal for this dust removal unit. During specific operations: This EDS dust removal system has no automatic monitoring startup logic, no dust threshold trigger logic, and no semi-automatic timed operation logic. Only after the astronauts complete the docking and sealing operations is the EDS electrostatic curtain dust removal function activated manually by the manual control module to actively electrostatically remove residual fine lunar dust from the internal sealed docking compartment; after the dust removal operation is completed, the equipment is manually shut down. The core implementation feature of this method is: the existing mature EDS electrostatic dust removal technology is integrated point-to-point, independently, and exclusively into the core compartment of the airlock docking, serving as an internal active dust removal supplementary unit of the multi-level lunar dust prevention system. Combined with the external multi-level physical isolation and flexible sealed inner lining barrier structure, a three-dimensional lunar dust prevention architecture of "external graded interception + internal docking area active electrostatic curtain dust removal" is formed. Moreover, the entire process adopts a purely manual controllable start-stop mode, which is fully adapted to the requirements of the extreme lunar environment with no automatic control malfunctions and high reliability for stay.

[0093] Example 2: This example maintains the same nested box structure, three-layer compartment layout, and three-stage gradient dust removal logic as Example 1, achieving pre-removal of large-particle dust, deep capture of ultrafine charged dust, and micro-positive pressure dust-free buffer. The difference lies in: the outer compartment's high-volume blowing component uses a pulsed intermittent jet mode to reduce airflow disturbance and dust generation; the inner compartment's electrostatic adsorption component uses electret filter material instead of high-voltage electrodes to eliminate ozone generation; the micro-positive pressure differential in the docking compartment can be automatically adjusted according to the external dust concentration. The remaining assembly structure and dust removal principle are the same as in Example 1 and will not be repeated here. The above are merely preferred embodiments of the present invention. All equivalent substitutions and simple structural improvements made based on the technical concept of the present invention fall within the protection scope of the present invention.

[0094] The airlock transition cabin of the scientific research station supporting the manned multi-planet exploration landing is a key isolation structure for personnel and equipment to enter and exit the cabin. Lunar dust is hard and has a large particle size range. Coarse particles can easily scratch the sealing structure and filter material, while ultrafine charged dust can easily be adsorbed on the surface of spacesuits and exploration equipment. Conventional single purification structures cannot handle dust of different particle sizes. Existing dust control solutions for similar planetary landing airlocks have significant shortcomings: 1. They only have a single dust removal station without a graded dust removal logic. Large pieces of coarse lunar dust are mixed with ultrafine charged dust, and coarse particles quickly clog high-precision filters, significantly shortening the filter material's lifespan; 2. The purging dust removal, electrostatic dust removal, and HEPA micro-positive pressure buffer devices are mostly independent and separate devices, unable to be integrated into different compartments within the enclosure. Dust generated during dust removal can easily spread throughout the enclosure, damaging the internal clean environment; 3. They lack a three-stage progressive isolation and purification layout: there is no pre-treatment coarse dust removal station to remove large pieces of floating dust, which directly enters the fine purification area, causing hard coarse particles to wear down the thin panels of the enclosure and the flexible sealing lining; there is no electrostatic composite dust removal for deep capture of ultrafine charged lunar dust; and there is no micro-positive pressure buffer compartment to prevent external dust from flowing back in; 4. Conventional airlocks do not use zoned sealed compartments for graded dust treatment. Lunar dust generated during the dust removal process continuously pollutes the core clean area inside the research station, affecting the accuracy of the exploration equipment and the safety of personnel. Therefore, there is an urgent need for a graded isolation airlock transition chamber that integrates three-level gradient dust removal stations, nested boxes with flexible sealing linings, and sequentially completes coarse dust removal, ultrafine dust deep purification, and dust-free transfer buffering in different sections, achieving graded isolation of lunar dust throughout the entire process.

[0095] Example 1: Aluminum alloy rigid gable wall adapted to a rigid-flexible alternating sealing and clamping structure. This example is suitable for the sealing assembly of landing modules for lunar and Martian surface research stations under high load and strong impact conditions, and is adaptable to extreme environments such as sandstorms, vacuum, low air pressure, strong radiation, and frequent temperature fluctuations. The main structure of this example is the same as that of Example 2, the difference being that the rigid enclosure gable wall is made of 6061 aerospace aluminum alloy, integrally milled, with a wall thickness of 4-15mm, providing high structural strength and strong resistance to impact deformation, adaptable to the impact of lunar and Martian landings and the loads of sandstorm erosion; the rigid connecting flanges at the ends of the aluminum alloy rigid gable wall are thickened to improve the pressure bearing capacity of the docking. The flexible sealing liner uses a modified silicone rubber composite sealing material, which has excellent resistance to sand and dust wear, carbon dioxide corrosion, and strong ultraviolet radiation, with a thickness of 4-6mm, adapting to the thermal expansion and contraction coefficient of the aluminum alloy rigid structure, resulting in a higher deformation matching degree; the limiting grooves on the outer or inner side of the aluminum alloy gable wall are precision milled, resulting in higher fitting accuracy, and there is no loose gap after the flexible liner is installed. The alternating rigid-flexible sealing and clamping mechanism is adapted to the characteristics of aluminum alloy material, and the clamping parameters are optimized: the axial clamping bolt locking preload is increased to 3-3.5MPa, and the elastic constant pressure compensation component adopts a combined spring gasket group, with a larger compensation stroke, which can adapt to the greater thermal deformation range of aluminum alloy material; the annular sealing groove of the rigid flange mating surface is deepened and widened, matched with a thickened flexible sealing ring, improving the resistance of the rigid-rigid mating interface to wind and sand, lunar dust penetration, and leakage prevention. This embodiment adopts an alternating rigid-flexible structure of rigid load-bearing aluminum alloy - flexible adaptive sealing - rigid high-strength locking. The rigid aluminum alloy structure resists the impact and wind and sand loads of lunar and Martian landing, while the flexible inner lining adapts to structural deformation and fills tiny gaps. The constant pressure compensation mechanism offsets the large temperature deformation of lunar and Martian day and night, effectively avoiding sealing surface voids, leakage, and aging failure. The structure's impact resistance, wear resistance, and deformation resistance are significantly improved, making it suitable for the use of long-term in-situ scientific research stations on the moon and Mars.

[0096] In this embodiment, the sealing door adopts a level 3 to 5 direct-through labyrinth seal. The spacing between the sealing teeth and the size of the groove are all based on existing aerospace standard parameters. The teeth and the box are integrally formed, and the clearance fit tolerance follows the existing technology without any special modifications.

[0097] Existing landing module hatches mostly use rubber sealing rings for sealing. However, these are prone to aging and failure due to the high and low temperatures and radiation in space, and are easily damaged by impacts. A single seal failure will result in air leakage. Labyrinth sealing is a well-known aerospace sealing technology with excellent weather resistance and shock resistance, making it suitable for extreme environments on multiple planets.

[0098] In this embodiment 2, the sealing door and the door frame adopt a level 3 to 5 end face bonding seal, and the airtight seal is achieved by automatic compression through the sealing gasket and the air pressure difference inside the cabin. The specifications of the sealing gasket and the air pressure compression parameters all adopt the existing general standards of aerospace. This invention does not innovate or improve the sealing gasket structure or air pressure sealing principle, but only optimizes the fitting and assembly of the sealing structure and the nested split box.

[0099] Example 2: The main body of the box and the matching gable wall components are made of carbon fiber composite material. The processing, assembly and sealing steps are as follows: Precision dimensional mapping: A three-coordinate measuring machine is used to accurately collect a complete set of dimensional data, including the outline, assembly reference dimensions, and fit tolerances of the gable wall surfaces where the inner and outer boxes are connected. The flatness of the gable wall mating surfaces of the inner and outer boxes, the reserved space for the steps, and the sealing assembly allowance parameters are recorded. Stepped groove gable wall integral molding preparation: Carbon fiber composite material sheets are prepared by mold opening according to the measured dimensions. The stepped groove gable wall components that are precisely matched with the gable wall surface of the box are processed by compression molding process. The stepped groove is divided into an outer limiting step and an inner fitting step. The depth and width of the stepped groove are matched one-to-one with the assembly gap of the inner and outer boxes. The assembly process involves several steps: First, the stepped groove gable component is positioned and engaged with the gable surfaces of the inner and outer housings. Second, a double-layer alignment assembly is achieved: the stepped groove gable component is positioned between the mating surfaces of the two sets of gables in the inner and outer housings, with the outer step abutting against the outer housing gable surface and the inner step fitting against the inner housing gable surface, completing both radial and axial positioning. Third, double-sided double-layer bonding and sealing is achieved: structural adhesive is applied to the joint between the inner step of the stepped groove and the inner housing gable surface to form the first sealing layer; environmentally resistant epoxy adhesive is applied to the joint between the outer step of the stepped groove and the outer housing gable surface to form the second sealing layer; the adhesive layer evenly fills the gap between the steps, and after curing at room temperature, a double-layer double-sealing is achieved, completing the integrated assembly of the carbon fiber housing and the stepped groove gable component.

[0100] After curing, an airtight leak test is performed on the bonded and sealed area. The stepped groove structure can contain the adhesive overflow, preventing the adhesive layer from overflowing and contaminating the external MLI multilayer thermal insulation components. The stepped limiting structure can offset the slight dimensional deviations in carbon fiber molding, ensuring that the thickness of the double sealing adhesive layer is uniform.

[0101] Both the gable components and the enclosure are made of carbon fiber, with a matching coefficient of linear expansion. This ensures that under alternating high and low temperatures, there will be no sealing gaps due to differences in thermal expansion and contraction of the materials, resulting in superior long-term sealing reliability compared to aluminum alloy heterogeneous structures. The carbon fiber stepped groove gable is lightweight and has high specific strength, achieving double-layer sealing assembly without significantly increasing the overall load on the enclosure, meeting the lightweight requirements of aerospace applications. The carbon fiber molded stepped groove is integrally formed, ensuring good step dimensional stability and resistance to deformation. During long-term service, there are no warping or detachment issues at the mating surfaces, and the double-layer adhesive sealing layer is less prone to cracking and failure. The carbon fiber substrate exhibits excellent resistance to space radiation and low-temperature mechanical properties. The stepped groove double-seal structure is adaptable to alternating high and low temperature conditions in aerospace, ensuring stable shielding and temperature control within the nested enclosure.

[0102] Example 2: Precise Dimensions of the Enclosure Structure: Outer Enclosure Overall Dimensions: Length: 3000mm, Width: 2570mm, Height: 2570mm, Plate Wall Thickness: 6mm, Corner Radius: R100mm. The outer enclosure is assembled from four carbon fiber plates: a bottom plate, a top plate, and two side plates. It serves as a shield for external micrometeorite protection, thermal control, dust and static electricity protection, atomic oxygen protection, and overall load-bearing and shaping functions. Inner Enclosure Overall Dimensions: Length: 2530mm, Width: 2500mm, Height: 2500mm, Plate Wall Thickness: 6mm, Corner Radius: R100mm. The inner enclosure is also assembled from four plates: a bottom plate, a top plate, and two side plates. It houses deep space scientific research equipment, control systems, power systems, life support systems, and data acquisition payloads, forming a stable and sealed core working chamber.

[0103] The enclosure assembly process: The outer and inner enclosures are each independently assembled using a four-panel overlapping process. The joints between the panels utilize a wide-face overlapping structure, with the overlapping areas fully bonded using aerospace-grade high- and low-temperature resistant polyimide structural adhesive. This is further reinforced by staggered riveting with titanium alloy high-locking rivets, forming a rigid, integrated, sealed structure. The four corners of the enclosure feature a prefabricated R100mm integral rounded transition structure, precisely aligning the panel ends with the rounded contours. There are no seams, breaks, or stress concentrations at the corners, ensuring the continuity and mechanical uniformity of the overall enclosure structure. All joints are filled with deep-space weather-resistant flexible sealant, achieving high airtightness, dustproofing, atomic oxygen protection, and vacuum leakage prevention.

[0104] Carbon fiber composite nested box, fully covered with MLI section: After the carbon fiber composite nested box in this embodiment has been cured and shaped, multi-layer thermal insulation components (MLI) are pre-wrapped on the outside of each box before assembly. Wrapping operation steps: The outer surface of the carbon fiber box is ground to remove burrs to avoid sharp edges piercing the MLI film; the MLI thermal insulation layer is continuously wrapped in multiple layers along the outer circumference of the box, with a single layer wrapped on straight sidewalls, and two layers of MLI overlapped at corners and installation interfaces, with an overlap of 10-12mm; the MLI is kept in close contact with the outer wall of the carbon fiber throughout the wrapping process, and the ends of each wrapping section and the overlap seam are fixed with high-temperature tape to prevent the MLI from slipping or falling off during transportation and assembly; the MLI wrapping process on the outside of the box can be prefabricated at the factory, and the whole machine can be directly hoisted and installed during assembly, reducing on-site thermal control construction procedures. This invention pre-wraps the enclosure with MLI multilayer insulation components before assembly, achieving integrated pre-fabricated insulation and avoiding the shortcomings of traditional on-site wrapping after assembly, such as limited space, incomplete wrapping, and damage to the insulation layer. The continuous wrapping of the MLI on the outside of the enclosure can significantly block high and low temperature radiative heat exchange, reduce internal temperature fluctuations, and improve the temperature stability of internal components. The pre-fabricated wrapping process has a high degree of standardization, with controllable wrapping thickness and overlap dimensions, resulting in good consistency in insulation performance.

[0105] Carbon fiber composite material enclosure: lightweight in itself, combined with MLI thin-layer thermal insulation, the overall weight increase is minimal, meeting the lightweight requirements of aerospace payloads.

[0106] Example 2: Carbon fiber rigid gable wall adapted with a rigid-flexible alternating sealing and clamping structure. This example is suitable for the sealing assembly of lunar orbit and lunar surface box-type scientific station landing modules with low load and lightweight requirements. This example includes a flexible sealing liner assembly, a carbon fiber rigid gable wall, rigid mating interfaces for connecting components, rigid connecting flanges, a rigid-flexible alternating sealing and clamping mechanism, and a limiting and anti-displacement fixing mechanism. The carbon fiber rigid gable wall is integrally molded from continuous carbon fiber composite material, with a wall thickness of 6-12mm. It is lightweight, has low deformation, and is resistant to cosmic ray corrosion. As the core rigid enclosure structure of the landing module box frame, multiple carbon fiber plates are modularly spliced ​​into a rectangular box structure with four long sides and rounded corners. The ends of adjacent gable walls are integrally formed with rigid connecting flanges (rigid connecting components). The flange end face has 4-6 sets of bolt mounting holes and annular sealing grooves evenly opened. The flexible sealing liner is made of a composite material of fluororubber and aramid fiber, with a thickness of 3-5mm. It has an ultra-wide temperature range tolerance of -180°C to 150°C, resistance to vacuum aging, and low compression set. It is integrally wrapped around the inner or outer surface of the carbon fiber rigid gable wall. The inner edge of the carbon fiber rigid gable wall has a circumferential limiting groove with a width of 4mm and a depth of 3mm. The edge of the flexible sealing liner is integrally formed with a protruding edge, which is interference-fitted into the limiting groove to achieve lateral full circumferential limiting and prevent slippage of the flexible layer. At the same time, the outer surface of the flexible sealing liner is set with uniform dot matrix micro-protrusions with a protrusion height of 0.3-0.5mm, which are tightly fitted with the inner surface of the carbon fiber gable wall to eliminate the fine gaps in the processing of the rigid wall surface. The rigid-flexible alternating sealing and pressing mechanism adopts a three-stage rigid-flexible alternating layout: the first stage is the rigid-flexible bonding and sealing between the flexible sealing liner and the carbon fiber rigid gable wall, which achieves full airtightness of the inner side through natural bonding and pre-compression; the second stage is the annular flexible sealing ring embedded in the flange sealing groove, which achieves gap filling and sealing at the interface of the hard-hard connection between adjacent rigid gable walls; the third stage is the rigid flange locking and pressure-bearing structure, which achieves overall structural fixation through axial compression. The limiting and anti-deviation fixing mechanism includes three sets of symmetrically arranged positioning anti-misalignment bosses and matching grooves on the flange end face. During assembly, automatic alignment ensures the coaxiality and flatness of the multi-gable module splicing, with assembly errors controlled within 0.1mm. The axial clamping bolts are made of titanium alloy anti-loosening bolts, equipped with a set of butterfly springs as an elastic constant pressure compensation component. After the bolts are tightened, the elastic deformation of the butterfly springs compensates in real time for the slight deformation of the carbon fiber gable and the compression deformation of the sealing layer caused by the lunar day-night temperature difference (-173°C~127°C), continuously maintaining a constant sealing clamping force of 2.5-3MPa. After assembly in this embodiment, a rigid carbon fiber matrix-flexible inner lining seal-rigid flange locking alternating rigid and flexible sealing system is formed. There is no stress concentration or sealing blind spot, and it can withstand long-term lunar vacuum, high and low temperature cycles, and micrometeorite dust impact conditions. The cabin airtight leakage rate is ≤10--Pa·m³ / s, meeting the sealing standards for long-term scientific research operations.

[0107] To reduce weight, the aluminum alloy nested box uses aluminum alloy plates with a thickness of 4-6 mm welded to form the gable wall, while the carbon fiber composite nested box uses carbon fiber composite plates with a thickness of 4-6 mm bonded together to form the gable wall. Because Example 1 uses a level 3 to 5 direct-through labyrinth sealing structure, and Example 2 uses a level 3 to 5 end-face bonding seal, both requiring thicker sealing door frames and doors, this invention uses a rectangular hole cut into the gable wall with a height of 2 m and a width of 1.2 m. Then, a sealing door frame with a stepped platform and a thickness of 0.1 m is inserted into the rectangular hole, with the edges of the stepped platform embedded in the inner wall of the gable wall, and the edges of the stepped platform of the intermediate isolating gable wall embedded in one side of the outer wall of the intermediate isolating gable wall. (See Figure 4 in the specification). A sealing gasket is placed between the stepped platform of the aluminum alloy nested box and the gable wall, and then the box is sealed and fixed by welding and riveting. A sealing gasket is placed between the carbon fiber composite nested box-shaped stepped platform and the gable wall, and then sealed and fixed by means of adhesive bonding and riveting. The sealing door and the sealing door frame are matched and fitted together, and after closing, they are fixed by 3-5 sets of hinges that fix the sealing door and the sealing door frame.

[0108] The sealed doors installed on the gable walls at both ends of the enclosure open inwards. Because they open outwards, they need to overcome the internal air pressure after closing. Before opening the doors inwards, simply open the sealing valve on the gable wall to achieve the same air pressure as the external vacuum environment, and then the sealed doors can be opened. One side of the inner wall of the sealed door has 3-5 sets of hinges, each consisting of three sections. Each section is connected to the previous one by a pin and bushing, allowing free rotation along the axis. The upper and lower sides of the hinges, fixed to the door frame, are engaged in grooves, allowing them to slide within these grooves. This allows the sealed door to first be pushed upwards, separating the labyrinthine multi-layered sealing surfaces, and then rotated towards one side of the hinges to open the sealed door and enter the research station.

[0109] The door frame of the sealed door is made of multiple rectangular platforms with progressively smaller dimensions, which are then bonded together for sealing. The sealed door is designed to fit the door frame perfectly and is made of multiple rectangular alloy plates or aerospace-grade carbon fiber composite panels with progressively smaller dimensions. The panels are sealed and fixed together by methods such as bonding, riveting, and welding. The parts of the sealed door that come into contact with the door frame are pressed together by sealing rings or gaskets fixed on the sealed door and / or door frame to achieve an airtight seal.

[0110] The lunar airlock transition chamber's environmental control auxiliary system includes electronic barometers, electromagnetically controlled sealing valves, water electrolysis hydrogen-oxygen production equipment, a sealed water tank, electric heating equipment, a flat-plate battery pack, and a high-pressure carbon dioxide gas injection device. All of these devices are electrically connected to the airlock's integrated manual control module via wires. The manual control module centrally outputs various operational control signals to drive the corresponding equipment to complete actions such as opening / closing, adjustment, injection, gas production, and heating. The electronic barometers collect real-time air pressure parameters inside the airlock and transmit them to the manual control module's display screen, serving only as visual reference data for the operator. The control system does not autonomously trigger any equipment operation based on air pressure values. The entire control system lacks automatic and semi-automatic control modes and does not have autonomous operation programs such as timed operation, pressure-linked start / stop, intelligent purging, or automatic temperature regulation. All equipment related to media control, airtight protection, temperature and humidity regulation, and gas preparation within the chamber can only be started or stopped by the operator issuing commands through the manual control module; the system itself does not actively generate any equipment operation commands. Operators can individually control the opening and closing of electromagnetic sealing valves, start and stop the water electrolysis hydrogen-oxygen production equipment, turn on the electric heating equipment, and start the high-pressure carbon dioxide injection device through the manual control module. They can also simultaneously issue multi-device linkage operation commands. Upon receiving a manual command, the circuit immediately activates the corresponding equipment circuit and executes the action, without any system-automatic interception, correction, or overriding of manual operation logic. The electronic barometer signal acquisition circuit, electromagnetic valve drive circuit, water electrolysis equipment power supply line, electric heating control circuit, high-pressure injection device electrical control unit, and the electrical wiring between the equipment and the manual control module are all mature and well-known technologies used in lunar habitation capsule equipment. Those skilled in the art can directly select existing standard electrical control components to implement the entire electrical connection architecture. The attached diagram is a simplified view omitting the electrical connection lines between the devices. Those skilled in the art, combining the text of this specification with common circuit knowledge, can completely reproduce the equipment connection and control scheme. The substantial improvement of this invention lies in…

[0111] A multi-planetary research station landing, tiered isolation, and lunar dust-proof airlock transition cabin with a nested enclosure and flexible sealed liner is disclosed. The cabin integrates a flat-plate battery pack, a manual control module, a water electrolysis hydrogen-oxygen production device, an electric heating device, a sealed water tank, an electronic barometer, and electromagnetically controlled sealing valves. The lithium battery energy storage power supply structure, manual control switch circuit, water electrolysis gas production principle, resistance electric heating structure, sealed water storage structure, pressure sensing detection principle, and electromagnetic valve opening and closing sealing structure are all mature and well-known technologies in existing aerospace and deep space equipment. This embodiment does not make any modifications to the above-mentioned equipment structure, working principle, or hardware composition. Those skilled in the art can directly select existing standard aerospace equipment to complete the assembly and electrical connections. In the specific assembly layout: the flat-plate battery pack, manual control module, water electrolysis hydrogen and oxygen production equipment, electric heating equipment, and sealed water tank are fixedly installed at pre-set fixed points on the airlock transition cabin wall, forming a self-sufficient environmental protection unit for the entire cabin; the electronic barometer and electromagnetically controlled sealing valve are fixedly installed on the connecting pipeline on the cabin gable wall for real-time monitoring of cabin pressure and to achieve airlock pipeline opening and closing and airtight isolation. All equipment is electrically connected to the flat-plate battery pack, which provides unified operating power; all equipment is also electrically connected to the manual control module, achieving centralized electrical control. This implementation does not employ any automatic linkage control logic, nor does it set up semi-automatic operation programs. The pressure data collected by the electronic barometer is only used for manual observation and reference and does not participate in any autonomous equipment control. During the lunar landing and station construction and stay operations, all equipment opening and closing, parameter adjustment, gas production, heating, water storage, and pipeline opening and closing sealing operations are all completed by the astronauts manually operating the manual control module. The system has no autonomous operation, no program intervention, and no automatic false triggering actions. The core innovation of this implementation method lies in: adapting and integrating various existing mature environmental control, power supply, electrical control, and airtight equipment into the airlock transition chamber, which features a unique structure with nested expansion, flexible sealing, and multi-level lunar dust protection. This constructs a highly reliable stationing support system that is well-organized in its zones, has a unified power supply, centralized manual control, zero risk of self-control errors, and is adaptable to extreme environments on multiple planets. This enables the low-difficulty, high-efficiency, and high-safety establishment of a base and long-term stationing operations for the first lunar landing.

[0112] In addition, the radio transmitting and receiving equipment, dual-mode controlled electric motion system, camera components, sealing valves, barometers, electronic barometers, rotary motors, water electrolysis equipment and sealed water tanks, electric heating equipment, high-pressure carbon dioxide gas injection device, electromagnetic sealing valves, signal transmission and equipment linkage control system carried on the landing module all adopt mature technical solutions from existing aerospace lunar surface equipment, without structural improvements or functional innovations, and are only used as auxiliary systems to support the overall equipment.

[0113] To meet the high reliability and low malfunction requirements of the lunar sealed airlock, all environmental auxiliary equipment is uniformly managed by a local manual control module, completely eliminating automatic and semi-automatic intelligent control logic and realizing a minimally simplistic and safe control system driven by purely manual commands.

[0114] This embodiment describes a multi-planetary research station landing, tiered isolation, and lunar dust-proof airlock transition cabin with a nested enclosure and flexible sealing liner. Various environmental support auxiliary equipment is fixedly installed at pre-defined mounting points on the inner sidewalls and gables of the cabin, specifically including: electric heating equipment, water electrolysis hydrogen-oxygen production equipment, a sealed water tank, an electronic barometer, electromagnetically controlled sealing valves, and a high-pressure carbon dioxide gas injection device. All of the above equipment adopts mature standard equipment from existing aerospace deep-space dwelling cabins. The structural form, working principle, media handling process, sealing structure, and electrical drive method of the equipment are all common knowledge in the field. This embodiment does not make any modifications to the equipment's main structure. All auxiliary equipment is electrically connected to a flat-plate battery pack to obtain working power, and is also electrically connected to a manual control module, which serves as the sole control terminal for all auxiliary equipment in the cabin. During operation of this embodiment: the system does not carry any automatic or semi-automatic control programs, and does not have autonomous operation functions such as timed operation, delayed start / stop, threshold triggering, or intelligent linkage. The electronic barometer collects real-time air pressure data inside the airlock transition chamber and displays it on the manual control module. This data is for operator visual reference only and does not participate in any automatic control logic or trigger any autonomous equipment actions. All environmental control, airtight protection, media preparation, dust removal and purging, and temperature control operations within the chamber require on-site manual control module operation by the operator, issuing corresponding manual commands for opening, closing, parameter adjustment, and on / off purging. Upon receiving the manual command, the equipment immediately executes the corresponding operation; the system does not generate any control commands autonomously or interfere with the equipment's operating status. This implementation completely abandons the complex architecture of "multi-priority control + intelligent automatic control + sensor linkage" commonly used in existing similar scientific research airlock chambers. It constructs a minimalist and reliable control system with all equipment operated purely manually, without automatic control, semi-automatic operation, or sensor linkage, perfectly adapting to the high safety, high stability, low failure rate, and on-site maintenance requirements of scientific research stays in extreme environments on the moon and other planets. The core improvements of this invention focus on the integrated assembly layout of multiple types of known auxiliary equipment and a dedicated purely manual control logic architecture; it does not constitute an improvement to the hardware structure of any single auxiliary equipment.

[0115] A lunar-surface nested shielding box device for integrated electric curtain dust removal is disclosed. The nested box has a 4mm thick lead plate, and a 30° welding bevel is machined on one side at the joint between the box and the gable wall. During assembly, M8 stainless steel bolts are used for pre-tightening at 80mm intervals around the flange circumference. Spot welding is performed for positioning, followed by full penetration welding using argon arc welding. After welding, the seam is polished and vacuum leak-tested. The inner side of the flange is filled with 3mm thick vacuum weather-resistant silicone rubber sealant to form a double-layer sealing barrier. The door frame and door body frame are first continuously welded around their circumference. After the weld cools, a 2mm thick insulating adhesive is evenly applied to the mating surface, cured at room temperature for 24 hours, and then pressed tightly together. The electric curtain dust removal electrodes use ITO flexible conductive film with a 2mm electrode spacing and a 500V three-phase alternating electric field. A thin lead shielding layer is installed on the back of the electric curtain to prevent electric field leakage. The outer side of the box is equipped with an MLI multi-layer heat insulation assembly consisting of 15... The system is constructed by alternating layers of reflective film and spacer layers, with each layer overlapping by 100mm. It is fixed to the outer wall of the enclosure using non-metallic anchors. Sealing strips are added at the corners, and small ventilation channels are provided for vacuum exhaust. After assembly, the entire unit is placed in a lunar simulated vacuum high-low temperature chamber, where dust removal efficiency tests are conducted under cyclic conditions of -180°C to 120°C. The dust removal efficiency consistently exceeds 96%.

[0116] The lunar surface is subjected to a high vacuum, extreme temperature variations of ±180°C, and radiation from galactic cosmic rays and solar particles. Lunar dust particles are fine and continuously charged due to ultraviolet radiation, making them highly susceptible to adsorption and deposition on the surface and structural gaps of the probe payload's shielding enclosure. Lunar dust is highly abrasive, which can wear down the enclosure's sealing interface. Simultaneously, its deposition obstructs heat dissipation surfaces, reducing radiation shielding effectiveness. Long-term operation can easily lead to seal failure, equipment overheating, and degraded shielding performance. Currently, the mainstream active dust removal solution for the lunar surface is electric curtain dust removal (EDS). This method relies on multiphase electrodes to generate an alternating traveling wave electric field, using dielectric force to drive the directional removal of charged lunar dust. This dust removal mechanism is a well-known dust removal method in the field, and several independent flat-panel electric curtain dust removal devices have been disclosed in existing technologies, mainly used on the surfaces of solar cell arrays and optical lenses for dust removal. However, existing electric curtain dust removal equipment has significant engineering shortcomings: 1. The electric curtain is an independent module and cannot be integrated with the radiation shielding lead-sheathed enclosure. There is no matching radiation shielding protection structure, and leakage from the high-voltage electric field easily interferes with the enclosure's shielding performance; 2. There is a lack of dedicated fixing, welding, and multi-layer sealing structures suitable for connecting the lead enclosure to the gable wall, making it easy for lunar dust to accumulate in the gaps between the enclosure joints, creating dust removal dead zones; 3. The matching sealing door only uses a single bonding or welding method, which cannot simultaneously meet the requirements of vacuum sealing, electric field insulation, and radiation shielding; 4. There is no external MLI multi-layer thermal insulation covering structure suitable for the electric curtain dust removal system, which can easily cause the electric curtain insulation layer to crack and significantly reduce dust removal efficiency due to extreme lunar surface temperatures; 5. Independent electric curtains require additional mounting brackets, resulting in a large overall size and heavy payload. Therefore, there is an urgent need for an integrated device that combines electric curtain dust removal, a lead shielding enclosure, integrated sealing welding, and external MLI thermal control to solve the problems of poor integration, incompatibility between shielding and dust removal, and weak adaptability to high and low temperatures in existing technologies.

[0117] Example 1: 30°C Constant Temperature Control in the Shadowed Area of ​​a Lunar Base (Routine Operating Conditions) This example is applied to the shadowed area of ​​the lunar base's bottom structure, where the external environment has a steady-state temperature of -120°C to -100°C and an ultra-high vacuum environment. It utilizes a conventional lunar surface energy storage lead-acid / lithium battery pack, aiming to maintain a constant internal temperature of 30°C. This example employs the aforementioned complete temperature control system architecture: 1. The outer wall of the cabin is covered with 50 layers of vacuum-plated aluminized multi-layer insulation blankets + 10mm aerospace-grade aerogel felt. A high-infrared-reflective heat-insulating coating is sprayed onto the outer wall to eliminate thermal bridges and heat leakage. The overall heat transfer coefficient of the cabin is ≤0.02W / (㎡·K), significantly preventing heat loss from the cabin to the extremely cold environment. 2. The battery operates normally during charging and discharging, generating 15-30W of heat. The internal heat storage chamber completely locks in self-generated Joule waste heat as a basic constant temperature heat source, maintaining an internal temperature of 28°C-31°C without activating the active heating module. 3. Distributed temperature sensors collect real-time temperature data across the entire area. A PID algorithm dynamically fine-tunes the internal heat dissipation damping. When instantaneous heat generation causes the temperature to rise to 32°C, a micro-heat dissipation channel is opened to release a small amount of heat; when the temperature drops back to 30°C, the heat dissipation channel is closed, achieving adaptive constant temperature. 4. Dual-path sensors and heating modules are redundantly on standby throughout the process. The PHM algorithm monitors the operating status of the devices in real time, ensuring low-energy steady-state operation under fault-free conditions. Results of this embodiment: The cabin temperature remained stable between 29°C and 31°C for an extended period, with an average constant temperature of 30.2°C and a temperature control accuracy of ±1.2°C. No active electric heating was required throughout the process; constant temperature operation was achieved solely through the battery's self-generated waste heat. Temperature control energy consumption was reduced by over 90%, and the battery exhibited no issues with increased internal resistance or performance degradation at low temperatures, demonstrating stable operation.

[0118] Example 2: Long-Term Standby Temperature Control During Lunar Night in Extreme Cold This example is applied to a 14-day lunar night shadow scenario on the moon, with an external ambient temperature of -170°C to -150°C. The battery is in low-power standby mode, with self-generated heat power ≤5W, insufficient to maintain a constant temperature independently. 1. A multi-layer composite insulation structure locks in heat throughout, minimizing heat loss in low-temperature environments. 2. The intelligent temperature control system detects that the cabin temperature has dropped to the 27°C threshold and activates the array-type polyimide flexible heating film in stages, providing low-power, uniform heat replenishment. The heating power is dynamically adjusted from 5W to 15W. 3. A PID algorithm precisely controls the temperature, stabilizing the cabin temperature between 29°C and 33°C, with a core steady-state temperature of 30°C, preventing excessive local temperature differences. 4. A deep sleep mode is activated, shutting down unnecessary functional modules, retaining only the temperature measurement, temperature control, and redundant heat source units; the isotope heat source continuously outputs basic heat to provide antifreeze insulation for the control motherboard and sensors. 5. The hardware redundancy system provides real-time online monitoring to prevent low-temperature component embrittlement and malfunction. Results of this embodiment: 14 days of uninterrupted operation throughout the lunar night; the cabin temperature remained stable between 28.8°C and 32.5°C, with an average temperature of 30°C. There were no issues with temperature runaway, electrolyte freezing, or battery failure. The system reported no faults, and the low-temperature start-up response time was ≤2 seconds, demonstrating fast temperature control response and strong stability.

[0119] Example 3: Ultra-low Temperature Control in Permanently Shadowed Lunar Polar Regions. This example is applied to the permanently shadowed region of a lunar polar crater, where the lowest ambient temperature reaches -230°C, representing the most extreme low-temperature conditions on the moon. The battery is in long-term standby mode, with self-generated heat approaching zero. 1. A triple-layer composite insulation structure operates at full load, maximally blocking the penetration of cold energy and heat loss through deep-space ultra-low temperature radiation. 2. The system maintains an active and precise heating mode throughout, dynamically adjusting the heating power based on the cabin temperature to maintain a steady-state constant temperature of 30°C. 3. All core components rely on cold-resistant SiGe and GaN material architectures to prevent ultra-low temperature material failure; a digital twin PHM algorithm predicts the heat loss rate in advance and pre-adjusts the heating power to eliminate temperature lag deviations. 4. An isotope heat source continuously outputs basic insulation heat as a final backup heat source to prevent the entire temperature control system from freezing and failing. 5. A low-temperature soft-start mechanism is adopted to prevent damage to equipment from instantaneous temperature shocks. The results of this embodiment show that under ultra-low temperature extreme environment, the internal temperature of the cabin is stably maintained at 27.5°C to 32.8°C, with a reference temperature of 30°C. It has been running continuously for a long time without failure. The battery performance parameters are consistent with those under normal temperature conditions, with no permanent damage. The system is adapted to the extreme low temperature conditions in the lunar shadow area.

[0120] This embodiment describes a 30°C constant-temperature thermal control system for batteries in lunar shadow regions. It is adapted for integrated assembly and use in the airlock transition chamber of a nested multi-planetary research station. The entire system comprises a sealed, temperature-controlled flat-plate battery pack mounting cavity with a vacuum jacket, multi-layer passive heat insulation components, a battery waste heat recovery and temperature-locking module, a high-precision active heating module, an intelligent PID temperature control module, an extreme cold fault-tolerant protection module, and a redundant power supply heat source module, all working together to form the overall thermal control architecture. The flat-plate battery pack energy storage and power supply structure, electric heating elements, temperature sensor acquisition structure, PID basic calculation circuit, heat insulation substrate, and conventional power supply line connection methods are all well-known and mature technologies in the deep space aerospace field. This embodiment does not modify any hardware structure, materials, or circuit principles; those skilled in the art can complete the basic assembly using existing standard aerospace components. The core of this implementation lies in the system-level constant temperature control logic and integrated architecture that integrates seven modules working in tandem: A vacuum-sealed constant temperature cavity independently encapsulates the flat-plate battery pack, utilizing the vacuum sandwich structure to isolate external deep-space cold radiation and lunar soil low-temperature conduction, constructing an independent, sealed constant temperature base environment; the cavity is externally covered with multi-layer passive heat-locking components, which significantly reduce the outward conduction and radiation loss of internal heat through a multi-layer gradient heat insulation structure, achieving passive long-term temperature lock-in. The battery waste heat recovery and temperature lock-in module collects Joule waste heat generated during the battery charging and discharging process in real time, conducting and retaining the waste heat inside the cavity to help balance the reference temperature and reduce active heating energy consumption. The high-precision active heating module is self-powered by the flat-plate battery pack, requiring no external power supply, and outputs matching heating power based on the low temperature difference in the cavity to achieve precise heat source compensation. The intelligent PID temperature control module continuously collects real-time temperature signals inside the cavity, dynamically compares them with the preset 30℃ constant temperature target value, and adaptively adjusts the waste heat recovery and temperature lock-in efficiency, active heating output power, and working sequence to form a closed-loop dynamic precise constant temperature control. The extreme cold fault-tolerant protection module provides low-temperature fault-tolerant protection for the electrical components, sensor signals, and control logic of the entire temperature control system, preventing equipment failure, signal distortion, and control malfunctions in extreme cold environments. The redundant power supply and heat source module provides backup energy and a fallback heat source, ensuring uninterrupted operation of the temperature control system under extreme conditions. All functional modules of the entire constant temperature thermal control system are electrically connected and signal-interfaced to the manual control module configured in the airlock transition chamber. The manual control module uniformly completes data acquisition, logic judgment, parameter adjustment, and fully automatic real-time temperature control operation. This implementation method, through its unique multi-module coupled constant temperature architecture, waste heat recovery and reuse mechanism, and extreme cold redundancy fallback system, achieves long-term stable operation of batteries at a constant 30°C in lunar shadow regions without relying on complex and high-cost aerospace temperature control hardware. It is suitable for the needs of rapid station construction, low maintenance, high reliability, and long-term station stay operations in extreme environments on multiple planets. The improvements of this invention focus on the integration and matching relationship of the entire thermal control system, the multi-module collaborative temperature control strategy, the waste heat utilization logic, the extreme cold fault-tolerant redundancy architecture, and the closed-loop control system linked with the entire cabin electrical control system. It does not belong to the structural improvement of individual components or hardware devices.

[0121] In complex environments such as aerospace and field operations, the application of radio transmitting and receiving devices, camera components, flat-plate battery packs, and electric motion systems is becoming increasingly widespread. For example, in the aerospace field, large spacecraft need to address the issue of unequal potential within the cabin during rendezvous and docking and the execution of special missions, requiring high precision and reliability from the potential control system. Simultaneously, in field launch scenarios, the telemetry, tracking, and command (TT&C) system needs to meet the requirements of short deployment times, long launch distances, and the ability to transmit security control commands, placing higher demands on wireless TT&C technology. Furthermore, camera components, as key equipment for environmental monitoring and operational assistance, require particularly important designs to withstand harsh environments such as vacuum and extreme temperatures. Flat-plate battery packs, due to their high energy density and long lifespan, have become the core device for energy supply in special environments. Electric motion systems are widely used in the autonomous capture and repositioning operations of space station modules or target spacecraft, and their modular design significantly improves operational flexibility and reusability. However, with increasing mission complexity, existing equipment still faces many challenges in terms of control accuracy, reliability, and environmental adaptability, requiring further optimization and innovation.

[0122] Despite the significant progress made by the aforementioned technologies in their respective fields, existing equipment control methods still have many shortcomings in special environments (such as airlock transition chambers). First, traditional control schemes typically employ complex multi-level priority settings, resulting in cumbersome and inflexible control logic, especially when multiple control signals coexist, easily leading to conflicts or delays and impacting task execution efficiency. Second, the control logic of some equipment lacks sufficient adaptability and cannot cope with changes in the extreme external and internal environments of the airlock transition chamber; conditions such as high vacuum and drastic temperature differences can significantly affect equipment performance. Furthermore, the switching mechanism between manual and remote wireless control in current schemes is not yet perfect, failing to meet the dual requirements of real-time performance and reliability in practical tasks. Therefore, researching a novel composite control scheme to fill these gaps is particularly necessary.

[0123] This research aims to propose a composite control scheme with no control priority and multiple control methods operating in parallel, to improve the control efficiency, flexibility, and reliability of equipment in special environments. Specifically, this scheme combines the technological advantages of radio transmitters and receivers, camera components, flat-plate battery packs, and electric motion systems, achieving unified management and coordination of each device through a manual control module. In this scheme, manual control and remote wireless control signals have equal priority. The manual control module dynamically adjusts control commands based on the real-time received signals, ensuring that the electric motion system can respond quickly and execute operational tasks. It is expected that this scheme will not only significantly improve the control accuracy and reliability of equipment in complex environments but also provide important technical reference and practical guidance for similar tasks in the future.

[0124] Radio control technology, as a crucial component of modern wireless communication, relies on the transmission and reception of signals through electromagnetic waves. In complex environments, the performance of radio control systems depends on antenna design, frequency band selection, and optimization of modulation and demodulation techniques. Furthermore, the control theory of electro-mechanical systems is primarily based on feedback mechanisms from classical control theory. It uses sensors to collect real-time data and dynamically adjusts actuators to ensure system stability and accuracy. For equipment design in special environments, the selection of materials resistant to harsh conditions is critical. For example, in extreme conditions such as airlock transition chambers, materials need to be able to withstand vacuum, high temperatures, and low temperatures, typically requiring the use of high-performance composite materials or metal alloys. These theories provide a solid foundation for this research and play a key role in the subsequent technical solution design.

[0125] In recent years, scholars both domestically and internationally have made significant progress in radio control, camera monitoring, energy supply, and electric motion systems under special environments. In the field of radio control, frequency-hopping wireless remote controllers are widely used in spacecraft and field equipment due to their strong anti-interference capabilities. Meanwhile, wireless telemetry and control systems suitable for field environments have achieved long-distance telemetry and control through spread-spectrum uplink and frequency-modulated downlink, with the longest uplink distance for security control commands reaching 100km. In camera monitoring, camera components resistant to harsh vacuum and high / low temperature environments have been successfully applied to the monitoring of spacecraft external structures, but their layout and viewing angle still require further optimization. Research in the field of energy supply shows that flat-plate battery packs, due to their high energy density and long lifespan, have become one of the preferred power supply solutions for equipment in special environments. However, existing research still has limitations in control logic and connection methods; for example, the priority setting is complex when multiple control methods are used in parallel, making it difficult to meet the needs of flexible operation.

[0126] While existing research has yielded some results in equipment control under special environments, there remains a significant gap in the development of parallel control schemes with multiple control modes without priority and composite control schemes adapted to special environments such as airlock transition chambers. Existing literature largely focuses on single control modes or fixed priority designs, lacking support for real-time switching between multiple control modes. Furthermore, for complex environments such as airlock transition chambers, the control logic of existing equipment is relatively rigid and cannot be flexibly adjusted according to actual needs. This research aims to fill this gap by proposing a composite control scheme with multiple control modes operating in parallel without control priority, thereby improving the flexibility, reliability, and adaptability of equipment control under special environments. This innovative scheme not only expands the application scenarios of existing technologies but also provides new ideas for equipment control in future complex environments.

[0127] Equipment Installation and Layout: The installation positions and layout of all equipment, both inside and outside the airlock transition chamber, require careful design to ensure the system's functional integrity and structural stability. The antenna portion of the radio transmitting and receiving device is mounted on the end face of the external longitudinal beam chassis of the airlock transition chamber to minimize the impact of the chamber on signal transmission. It is reinforced with a fixing bracket made of high-strength vacuum-resistant material to withstand harsh high and low temperature environments. The camera assembly is also arranged on the end face of the external longitudinal beam chassis, with a field of view covering key areas around the chamber, used for real-time monitoring of astronauts' extravehicular activities or equipment maintenance operations. The flat-plate battery pack is installed inside the airlock transition chamber and fixed with heat insulation and shock absorption devices to avoid the impact of the external environment on its performance and improve safety. The drive components of the electric motion system are connected to the inner wall of the airlock transition chamber and adopt a modular design for easy maintenance and replacement. The layout relationship between the various devices is shown in the attached diagram, ensuring maximum space utilization while reducing the possibility of signal interference and mechanical collisions. Furthermore, during equipment installation, all fasteners were made of high-strength, low-magnetization materials meeting aerospace-grade standards, and their stability in microgravity environments was further enhanced through multi-point, multi-directional fixing methods. For example, the external mounting of the radio transmitter / receiver and camera components employed a triangular distributed fixing structure to improve impact resistance; while the flat battery pack was connected to the internal frame of the cabin via an L-shaped bracket, ensuring reliability under complex mechanical conditions. These design details not only meet the requirements of use in special environments but also provide valuable engineering experience for similar missions in the future.

[0128] Electrical Connections: The electrical connections between the various devices are crucial for the stable operation of the composite control system. The radio transmitter and receiver are connected to the manual control module via shielded twisted-pair cables, using standard SMA connectors to ensure low-loss transmission of high-frequency signals. The power and video signal cables of the camera assembly are made of copper core cables wrapped with high-temperature resistant silicone insulation, and connected to the flat battery pack and manual control module via waterproof aviation plugs to ensure reliable signal transmission and environmental adaptability. The flat battery pack, as the core power supply unit of the system, is equipped with multiple DC-DC converters at its output, providing stable voltage support for the electric motion system, manual control module, and other loads. Overcurrent and short-circuit protection mechanisms are incorporated into the circuit design to enhance system safety and fault tolerance. The electrical connection of the electric motion system is achieved through a dedicated motor drive interface, which uses the CAN bus communication protocol to support high-speed data transmission and real-time control command interaction. The manual control module, serving as the system's central hub, integrates multiple communication interfaces at its input terminals. These include an RS-232 serial port for receiving radio signals, an NRF24L01 wireless communication module for processing handheld controller signals, and an I2C bus for exchanging status monitoring data with the flat battery pack. All electrical connections have undergone rigorous electromagnetic compatibility testing, and filter capacitors and ferrite beads have been added at critical points to suppress the impact of external interference on signal quality. As can be seen from the circuit schematic, this multi-layered, modular electrical connection design not only simplifies system maintenance but also significantly improves overall operational stability and reliability.

[0129] Control Operation Examples: To verify the feasibility of this solution, the following two typical scenario examples demonstrate the specific operation process of manual control and remote wireless control, as well as the response of the electric motion system. First, consider the scenario of an astronaut's extravehicular activity (EVA): When an astronaut prepares to perform maintenance on extravehicular equipment, their handheld controller sends start / stop, forward, backward, and turn commands to the manual control module via the NRF24L01 wireless communication module. Upon receiving the signal, the manual control module immediately converts it into the corresponding electrical control operation execution signal and transmits it to the electric motion system via the CAN bus, driving the relevant mechanical components to complete the predetermined actions. During this process, the camera component continuously captures the extravehicular environment and transmits the video signal back to the Earth-based remote wireless control and monitoring terminal, providing intuitive operational feedback to the Earth-based remote control center and the astronaut. Experimental results show that this control method has a rapid response and high operational accuracy, meeting the needs of complex tasks. Secondly, in the scenario of space station equipment maintenance, the Earth-based remote control center sends control signals to the radio transmitter and receiver device via frequency hopping technology. After receiving the signal, the device forwards it to the manual control module. Because this solution employs a no-priority control logic, both manual and remote control signals can be recognized and executed by the system in real time. For example, in a simulation experiment, the remote control center issued a command to adjust the position of a certain device. Upon receiving the signal, the electric motion system quickly started and completed the specified action, with a delay of less than 500 milliseconds, fully demonstrating the system's efficiency and flexibility. The above scenario verifies the solution's ability to work collaboratively under multiple control methods and also proves its reliability and practicality in special environments.

[0130] The frequency hopping communication module used in this embodiment is a mature existing technology in the field (such as a module that conforms to Bluetooth or a specific military frequency hopping protocol). Those skilled in the art can directly purchase commercially available standard parts or use conventional circuit design to implement it according to the communication requirements of this system. Its internal underlying principle will not be described in detail here.

[0131] The entire process of manufacturing, assembling, and final assembly of the machine.

[0132] First, construct a double-layered nested enclosure. Install a fixed crossbeam 60 at the bottom of the outermost enclosure 6, and a fixed longitudinal beam 73 at the bottom of the crossbeam 60. Install and fix the camera assembly 7 to one end of the longitudinal beam 73. Install and fix a wheel axle bracket 3 on the longitudinal beam 73, and install and fix wheels 4 on the wheel axle bracket 3, ensuring the center hole of the wheel 4 passes through the wheel axle 1 for fixation. Next, construct a connecting component body 2 made of flexible material. When no docking operation is required, the connecting component body 2 made of flexible material can be fixed close to the edge of the enclosure. The flexible sealing connection component 51 is installed and fixed on the rigid interface 43 of the connection component by: the component 50 that fixes the flexible sealing connection component on the outer wall of the gable wall and the fixing frame 52 that connects the flexible sealing connection component and the rigid interface of the connection component; the connection hole 10 is drilled on the rigid interface of the connection component at the part 54 that is filled with the diamond-shaped cross-section line; a film made of a specific material is pasted on the rigid interface 43 of the connection component to prevent lunar dust or dust from entering; and a radio transmitting and receiving device 5 is installed and fixed on the top of the outermost box 6.

[0133] Install fixed gable walls 45 and intermediate partition gable walls 46 at both ends of the inner box 23. Install and fix the following components on the top wall and floor between the gable walls at both ends of the inner box and the intermediate partition wall: Component 42 with right-angle folded edges to reinforce the gable walls (one right-angle folded edge is welded, riveted, or glued to the top of the intermediate partition wall of the inner box near the side wall, and the other right-angle folded edge is welded, riveted, or glued to the top of the gable wall at one end of the inner box near the side wall. The long side of the component is firmly fixed to the top wall of the inner box by welding, riveting, or gluing, which strengthens the gable wall body and weld seams to withstand air pressure. One of these components is installed on each side of the top wall and floor of each compartment, for a total of 4; or one more can be installed in the middle of the top wall, for a total of 6). Install fixed gable walls 49 at one end of the outermost box 6, and install reinforcing fasteners 53 to fix the outer box gable walls and top walls. A fixed sealing door frame 15 is installed on top. On the sealing door frame 15, a fixed sealing door 14 is installed via a hinge 48 that fixes the sealing door to the sealing door frame. A fixed sealing door handle 13 is installed on the sealing door 14. (The outermost enclosure's gable wall 49 is larger than the inner enclosure's gable wall 45, but the sealing door frames and sealing doors installed on both gable walls are the same size.) A fixed flat battery pack 8 and a manual control module 56 are installed at one end of the outer enclosure's gable wall 49. The manual control module is electrically connected to the flat battery pack and to the electric motion systems of all electrical instruments inside and outside the enclosure. It can manually control the various electrical devices inside and outside the research station, or receive radio control signals from the radio transmitting and receiving device. The manual control module controls the corresponding circuits to be turned on or off, executes the commands of the radio control signals, and is used to power the electric motion system and control the movement mode of the electric motion system. A fixed high-pressure oxygen cylinder 11 and a fixed high-pressure nitrogen cylinder 12 are installed on the gable wall 49. A fixed sealing door frame 15 is installed on the gable wall 49. A fixed sealing door 14 is installed on the sealing door frame 15. A fixed sealing door handle 13 is installed on the sealing door 14.

[0134] Install and fix the following on the inner gable wall of the inner box: a sealing door frame 15; a sealing door 14 is installed and fixed on the sealing door frame 15 via a hinge 48 that fixes the sealing door to the sealing door frame; a sealing door handle 13 is installed and fixed on the sealing door 14. Install and fix the reinforcing fastener 9 on one side of the outer box gable wall, and nest the inner box 23 inside the outermost box 6. Install and fix the following on the outer gable wall of the inner box: a pressure gauge 16 on the inner box gable wall; a sealing valve 17 on the inner box gable wall; a through pipe 18 above the inner box gable wall; a flexible connecting pipe 19 on the inner box gable wall; a sealing interface 20 for the connecting pipe; a sealing valve 21 for the through pipe; and a through pipe 22 below the inner box gable wall. Install and fix the following on the inner wall of the outer gable wall of the inner box: a sealing valve 24 on the inner wall of the pipe passing through the lower part of the inner box gable wall, and a sealing valve 25 on the inner wall of the pipe passing through the upper part of the inner box gable wall.

[0135] Install and fix the following on the inner wall of the inner partition gable: A sealing valve 26 for the inner wall of the penetrating pipe. Install and fix the following pipe 58 connecting the spacesuit dust removal and cleaning equipment inside and outside the inner compartment. Install and fix the following on the outer wall of the inner partition gable: A sealing valve 27 for the outer wall of the penetrating pipe. Install and fix the following on the outer wall of the inner side gable: A light 47 on the sealing door frame of the outer compartment, a sealing valve 29 above the penetrating pipe on the other side gable of the inner compartment, and a sealing valve 31 below the penetrating pipe on the other side gable of the inner compartment. Install and fix the following on the inner wall of the inner side gable: A sealing valve 28 above the penetrating pipe on the other side gable of the inner compartment, and a sealing valve 30 below the penetrating pipe on the other side gable of the inner compartment. The following components are installed and fixed on the outer wall of one end of the outermost housing 6: a sealing valve 33 on the outer wall of the through-pipe above the outer wall of the outer housing; a sealing valve 35 on the outer wall of the through-pipe below the outer wall of the outer housing; a pressure gauge 36 on the outer wall of the through-pipe above the outer housing; a flexible connecting pipe 37 on the outer wall of the outer housing; and a sealing interface 38 for the connecting pipe. The following components are installed and fixed on the inner wall of one end of the outermost housing 6: a light 47 mounted on the door frame of the sealing door of the outer housing; a sealing valve 32 on the inner wall of the through-pipe above the outer housing; and a sealing valve 34 on the inner wall of the through-pipe below the outer housing. The following components are installed and fixed: A flexible sealing connection component 51 is installed and fixed between the inner wall of the outermost box and the outer wall of the inner inner box, using a component 50 that fixes the flexible sealing connection component on the outer and inner walls, and a fixing frame 52 that provides a rigid interface between the flexible sealing connection component and the connecting component. A flexible connecting hose 39 is also installed and fixed between the upper part of the outer box's gable wall and the upper part of the inner box's gable wall, located between the inner wall of the outermost box and the outer wall of the inner inner box. Finally, a wall lamp 41 is installed and fixed on the top wall of the inner box compartment.

[0136] Install and fix the following in the two compartments of the inner casing: Spacesuit dust removal and cleaning equipment 40 in the inner compartment, which internally integrates an electrostatic adsorption dust removal component and a fine particle filtration dust removal component (Figure 4 shows a view of the entire unit without being cut to the inside when the door is closed); and spacesuit dust removal and cleaning equipment 44 in the outer compartment of the inner casing (Figure 4 shows a view cut to the inside). Install and fix the pipes 58 connecting the spacesuit dust removal and cleaning equipment in the inner and outer compartments of the inner casing to the bottom of each spacesuit dust removal and cleaning device. The spacesuit dust removal and cleaning equipment, cut into its interior, includes: an electrostatic dust generator 55 inside the outer compartment of the inner box; a vertical pipe 64 within the spacesuit dust removal and cleaning equipment; nozzles 65 on the vertical pipe; a connecting pipe 66 between the high-pressure carbon dioxide gas storage device and the vertical pipe; a sealing valve 67 on the connecting pipe; a support 68; a small motor 69; a rotating component 70 driven by the small motor; a vertical rod 71 rotated by the rotating component; and a horizontal bar 72 connecting the vertical rod. The exterior of the spacesuit dust removal and cleaning equipment, cut into its interior, includes: a high-pressure carbon dioxide gas storage device 61; a sealing valve 62; and a connecting pipe 63. The spacesuit dust removal and cleaning equipment 40 inside the inner compartment of the inner box has a composite electrostatic adsorption dust removal component and a fine particle filtration dust removal component installed internally; the high-pressure carbon dioxide gas storage device 61, the sealing valve 62, and the connecting pipe 63 are installed externally in the spacesuit dust removal and cleaning equipment 40 inside the inner compartment of the inner box. The spacesuit dust removal and cleaning equipment 44 in the outer compartment of the inner box is connected to the external lunar vacuum environment via a through pipe 59 under the gable wall of the inner box. When the spacesuit dust removal and cleaning equipment is cleaning with high-pressure carbon dioxide gas, the sealed valve on the pipe can be opened to allow the carbon dioxide gas mixed with lunar dust to be discharged into the lunar vacuum through negative pressure.

[0137] The following components are installed and fixed on the side walls of the two compartments of the inner enclosure: a manual control module, a flat battery pack 57 (located on the side wall of the inner enclosure), a water electrolysis hydrogen-oxygen production device, a sealed water tank, and an electric heating device. The water electrolysis hydrogen-oxygen production device, sealed water tank, electric heating device, and manual control module are electrically connected to the flat battery pack and to all electrical instruments inside and outside the enclosure, allowing for manual control of all electrical instruments and equipment inside and outside the research station. The hydrogen outlet of the water electrolysis hydrogen-oxygen production device can be connected to a pipeline in the gable wall to discharge gas outside the enclosure. All sealing valves can use ordinary sealing valves or existing electromagnetic sealing valve products, equipment, and technologies, including wirelessly controlled electromagnetic sealing valve products, equipment, and technologies. Automatic or manual control is achieved through electrical connection with the manual control module 56 and the flat battery pack 57 (located on the side wall of the inner enclosure).

[0138] The logic for preventing lunar dust intrusion.

[0139] A multi-planetary research station landing staged isolation and lunar dust-proof airlock transition capsule with a nested box body and flexible sealed liner is proposed. This device can be installed inside the lunar lander and launched to the lunar surface by rocket. Multiple pre-launches are conducted to bring the landing sites of various docking research stations closer together. When the astronauts finally arrive on the moon, the lunar lander hatch is automatically opened, and then the airlock transition capsule is wirelessly controlled to move along the transition plate to the lunar surface. Under remote wireless control from Earth and the control of the astronauts, the airlock transition capsule moves towards the docking site of the main research station. When the airlock transition module (landing module) reaches the docking point with the main research station, it is only about one meter away from the connecting parts on the outer side of the main research station's gable wall. The astronauts remove the high-pressure oxygen and nitrogen cylinders and connect them to the connecting pipes located below the outer side of the landing module's outer casing. They then open sealing valve 35 to inflate the inner compartment of the outer casing. At this time, sealing valves 31, 34, and 30 are initially open, as are sealing valves 32, 29, and 28. The astronauts observe the reading on pressure gauge 36. When the internal pressure reaches 1.5-2 atmospheres, inflation stops, and sealing valve 35 is closed. The astronauts then manipulate the flexible connecting pipe 37 on the outer casing's gable wall to connect and secure it to the external gas connecting pipe of the main research station, ensuring no leakage. The astronauts then mate the rigid interface 43 of the connecting component on the outer wall of the landing module's outer casing with the rigid interface of the connecting component on the outer wall of the main research station, and tighten and seal it, completing the modular docking and sealing installation. At this point, the astronauts can open or not open the sealing valve on the external gas communication pipe of the main research station, allowing the gas inside the main research station to enter the compartment on the inner side of the landing module's outer casing through the gas communication pipe. The main research station has already been filled with oxygen and nitrogen by the astronauts using high-pressure oxygen and high-pressure nitrogen cylinders, and the internal pressure has reached 1 standard atmosphere. The astronauts then manipulate another landing module or a moving device with connecting components to move to the other end of the installed landing module. They mate and seal the connecting components of the other landing module or the moving device with the connecting components at the other end of the installed landing module. The astronauts then manipulate the other landing module or the moving device with connecting components to move in the opposite direction, pulling out the installed inner casing of the landing module, placing a support and leveling assembly at the bottom of the casing, and covering the top of the casing with a radiation shield. The astronauts detach the connecting components of the other landing module or the motion equipment from the landing module's connecting components and maneuver them to other suitable positions. At this point, the astronauts, wearing full lunar spacesuits, helmets, and shoes, and carrying oxygen supply equipment, first open the outer compartment's sealed door and enter the outer compartment. Because the sealing valve 26 is initially closed, and because the astronauts opened the sealed door, the outer compartment is in a vacuum environment. The astronauts then close the sealed door on the outside of the outer compartment for entering and exiting the lunar surface.By opening the sealing valve 26 of the connecting pipe on the middle partition wall, the sealing valve 27 of the connecting pipe on the other side of the middle partition wall is initially open. This allows air from the inner compartment to enter the outer compartment. Once the air pressure reaches the required level, the astronaut can remove their helmet. At this time, the astronaut must hold their breath, remove the oxygen tank hanging on the side wall and the breathing mask connected to the oxygen tank via a flexible tube, put on the breathing mask and secure it to their head, and open the sealing valve on the flexible tube to breathe oxygen from the oxygen tank. This is to prevent the inhalation of lunar dust brought into the outer compartment by the astronaut. Wearing the breathing mask, the astronaut removes their spacesuit and space shoes, changes into slippers, and places the spacesuit, helmet, shoes, and other equipment into the spacesuit dust removal and cleaning device 44 in the outer compartment of the inner box. The sealing door is closed, and the operation button is pressed to start the dust removal function. The astronaut, wearing a breathing mask, arrived outside the sealed door of the intermediate partition wall. After closing sealing valve 26 and opening the sealed door, the astronaut entered the intermediate isolation buffer compartment, removed their slippers, put on new ones, and closed the sealed door again. The astronaut then used a handheld device to clean their body. Afterward, they entered the inner clean compartment and finally entered the main research station module through the clean docking passage. Through multi-level zoning, step-by-step dust removal, and segmented isolation, lunar dust is completely prevented from penetrating into the core module of the main research station, achieving end-to-end prevention of lunar dust intrusion.

Claims

1. A multi-planetary research station landing, hierarchical isolation, and lunar dust-proof airlock transition chamber with a nested box body and a flexible sealing liner, characterized in that: The research station uses a double-layered nested box structure as its main body. The outer box structure has a gable wall at one end, with a flexible connecting component and a sealed door on the gable wall. The other side does not have a gable wall and serves as the entrance to the inner box structure. The inner box structure has a gable wall at the opposite end of the outer box structure, with a sealed door and a flexible connecting component on the gable wall. The bottom of the nested box structure is equipped with a chassis, and a motion system for overall displacement is located below the chassis.

2. The multi-planetary research station landing graded isolation lunar dust-proof airlock transition chamber with nested box body and flexible sealing liner as described in claim 1, characterized in that: The inner box can be nested inside the outer box; gable walls are provided at both ends of the inner box; a middle isolation gable wall is provided in the middle of the inner box, and a sealed door is provided on the middle isolation gable wall; a flexible sealing liner is provided between the inner wall of the outer box and the corresponding outer wall of the inner box; one end of the flexible sealing liner is sealed and fixedly connected to the inner wall of the outer box and the other end is sealed and fixedly connected to the corresponding outer wall of the inner box; when the inner box is completely housed inside the outer box, the flexible sealing liner is compressed and housed between the two gable walls; when the inner box is pulled out for docking, the flexible sealing liner can be extended and unfolded to adapt to the pulling-out docking operation stroke of the inner box.

3. The multi-planetary research station landing graded isolation lunar dust-proof airlock transition chamber with nested box body and flexible sealing liner as described in claim 2, characterized in that: The nested chamber is divided into an outer compartment, an inner compartment, and an internal sealed docking compartment. The outer compartment is equipped with a spacesuit dust removal and cleaning device, which is fitted with a high-volume blowing component and a coarse particle adsorption dust removal component to remove and collect large loose lunar dust particles adhering to the surface of spacesuits and work equipment. The inner compartment is equipped with a purification and dust removal mechanism, which integrates an electrostatic adsorption dust removal component and a fine particle filtration dust removal component to capture suspended ultrafine charged lunar dust in the cabin and remove residual micro-dust from the surface of workpieces. The internal sealed docking compartment is equipped with a high-precision HEPA fine filtration dust removal component and an internal micro-positive pressure dust control mechanism to create a sealed, dust-free buffer transit environment.

4. The multi-planetary research station landing graded isolation lunar dust-proof airlock transition chamber with nested box body and flexible sealing liner as described in claim 2, characterized in that: The outer box gable wall is provided with two sets of connecting pipes, one above the other, which run through the gable wall. Both ends of the connecting pipes are equipped with sealing valves. The upper connecting pipe is equipped with valves (33) and (32). Valve (33) is initially closed and valve (32) is initially open. The lower connecting pipe is equipped with valves (35) and (34). Valve (35) is initially closed and valve (34) is initially open. On the connecting pipe on the upper part of the outer wall of the outer box gable wall, a pressure gauge is provided downstream of the corresponding sealing valve, and an extended sealing hose is connected upstream of the corresponding sealing valve. The end of the extended sealing hose is equipped with a rigid sealing interface. When this airlock transition chamber docks with other research station chambers, docking and sealing are completed through the rigid sealing interface, so that the sealing hoses on both sides are connected, and gas communication between the two chambers is realized. The outer box gable wall is equipped with a total of four sets of sealing valves for gas connection between each compartment and for regulating the air pressure inside the chamber.

5. The multi-planetary research station landing graded isolation lunar dust-proof airlock transition chamber with nested box body and flexible sealing liner as described in claim 2, characterized in that: The inner chamber has two sets of connecting pipes on its two gable walls, one above the other. These connecting pipes penetrate the gable walls, and sealing valves are installed on both the inner and outer walls of each connecting pipe, resulting in a total of eight sealing valves on the two gable walls of the inner chamber. Valves (17, 21) are initially set to the closed state, while valves (24, 25, 28, 29, 30, 31) are initially set to the open state. On the connecting pipe on the upper part of the outer wall of one end of the inner chamber, a pressure gauge is installed downstream of the corresponding sealing valve, and an extended sealing hose is connected upstream of the corresponding sealing valve. The end of the extended sealing hose is equipped with a rigid sealing interface. When this airlock transition chamber docks with other research station chambers, the rigid sealing interface enables sealed docking and connection, connecting the air passages of the sealing hoses on both sides, thus achieving gas exchange and pressure balance adjustment between different research station chambers.

6. The multi-planetary research station landing graded isolation lunar dust-proof airlock transition chamber with nested box body and flexible sealing liner as described in claim 2, characterized in that: The inner top wall of the inner box is equipped with lighting fixtures; the middle partition wall of the inner box is provided with two sets of connecting pipes, the connecting pipes pass through the middle partition wall, and the connecting pipes are provided with sealing valves at the inner and outer sides of the wall, and the middle partition wall is equipped with a total of four sealing valves; the sealing valves corresponding to the lower connecting pipes are initially closed; the upper connecting pipes are provided with valves (26) and (27), the valve (26) is initially closed, and the valve (27) is initially open.

7. The multi-planetary research station landing graded isolation lunar dust-proof airlock transition chamber with nested box body and flexible sealing liner as described in claim 2, characterized in that: The pipeline upstream of the sealing valve (29) on the outer wall of one end of the inner box is sealed and connected to the pipeline upstream of the sealing valve (32) on the inner wall of the outer box through a flexible connecting hose; the flexible connecting hose is retractable and adaptable to the stroke requirements of the inner box being pulled outward for docking and assembly.

8. The multi-planetary research station landing graded isolation lunar dust-proof airlock transition chamber with nested box body and flexible sealing liner as described in claim 2, characterized in that: The weld seams between the top and bottom ends of the outer wall of the outer box and the top and bottom plates are provided with reinforcing fasteners (9, 53) that are sealed and fixed by welding or bonding to strengthen the weld seams between the outer wall of the outer box and the top and bottom plates. The top and bottom ends of the inner walls of the two ends of the inner box are provided with connecting and reinforcing components (42) with right-angle folded edges that are sealed and fixed by welding, bonding or riveting to strengthen the weld seams between the inner and outer walls of the two ends of the inner box and the top, bottom and side plates.

9. The multi-planetary research station landing graded isolation lunar dust-proof airlock transition chamber with nested box body and flexible sealing liner as described in claim 2, characterized in that: The gable walls at both ends of the inner box, the middle partition gable wall, and the gable wall of the outer box are all made of thin plates with a thickness of 2-15mm, and the thin plates are sealed and fixedly connected to the top plate, bottom plate, and two side plates; square holes are opened in the gable walls, and sealing door frames with a thickness of 15-100mm are embedded in the square holes, and the size of the square holes is adapted to the sealing door frames; the stepped joints of the sealing door frames are provided with sealing and fixing structures on both the inner and outer sides of the gable walls; the sealing door is installed on the sealing door frames.

10. The multi-planetary research station landing graded isolation lunar dust-proof airlock transition chamber with nested box body and flexible sealing liner as described in claim 2, characterized in that: High-pressure oxygen cylinders and high-pressure nitrogen cylinders are fixedly installed on the outer wall of the outer casing; high-pressure oxygen cylinders and high-pressure nitrogen cylinders are fixedly installed on the outer wall of the opposite side of the inner casing, for astronauts to fill the research station cabin with breathable gases.

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