22 results about "Human spaceflight" patented technology

The invention discloses a space station on-orbit maintenance SA network analysis method based on DSA and a Bayesian network, and the method comprises the steps: firstly building a topological structure of an SA reliability network, then obtaining the structure parameters of the SA reliability network, carrying out the SA reliability analysis, building an applicable proposition network according to a given manned spaceflight extravehicular activity research object, and carrying out the analysis of the SA reliability. And finally, carrying out systematic and qualitative DSA analysis on the researched manned spaceflight extravehicular activity tasks based on the propositional network. The method can effectively provide support for personnel decision making of the task system, provide support for training design of task personnel, evaluate rationality of information interaction design of the current task system, identify key nodes of information interaction and provide support for information interaction design of the task system. The method is suitable for evaluation and optimization of EVA task system design of space stations in China and astronaut ground training system design.

The invention relates to the technical field of manned spaceflight AI data chains, in particular to a self-adaptive control method for a data chain of a motor Weishi rocket engine Tongzenyu PD-9S manned rocket, which can provide more efficient and reliable data transmission and processing, improve the safety and success rate of manned spaceflight, and meanwhile, improve the reliability of the data chain of the motor Weishi rocket engine Tongzenyu PD-9S manned rocket. The method has the advantages of self-adaptability, real-time performance and the like, can better deal with complex and changeable space environment and high reliability and real-time performance requirements, in addition, can realize intelligent functions of fault prediction, autonomous control and the like, improves the autonomy and adaptability of the spacecraft, and improves the reliability of the spacecraft. Therefore, the technical problem that the existing adaptive control technology still has many challenges in the aspects of processing complex and changeable space environments and high reliability and real-time requirements is solved.

The invention relates to the field of aerospace information processing, in particular to a manned spacecraft in-cabin test load interface support system, comprising an instruction forwarding module which communicates with a test load and a spacecraft platform through a 1553B bus network and is used for receiving a bus instruction from the spacecraft platform and forwarding the bus instruction to the test load; the state acquisition module communicates with the test load and the spacecraft platform through a 1553B bus network and is used for acquiring working state information of the test load and forwarding the working state information to the spacecraft platform; and the high-speed data transmission module communicates with the test load through a wireless network, communicates with the spacecraft platform through a high-speed data line, and is used for receiving the test data of the test load and forwarding the test data to the spacecraft platform. According to the invention, a standardized information support interface can be provided for the test load, interface standardization is realized, the wiring scale of the manned spacecraft can be reduced, and the layout flexibility of the test load and the space utilization rate of the manned spacecraft are improved.

The invention provides a spacecraft overall structure suitable for expansion of a T-shaped assembly of a space station. The spacecraft overall structure comprises a working cabin, a multi-purpose cabin, a node cabin and a non-bearing propulsion cabin. On the basis of the configuration scheme, layout area planning of large outboard equipment is provided, and installation of functional equipment such as a large-area semi-rigid plate solar cell wing, a thermal control fluid loop, a radiator and a propelling device can be supported. The configuration enables the spacecraft to fully use the uplink envelope space of a carrier rocket, supports in-cabin carrying of large-scale equipment, and has autonomous flight and active rendezvous and docking capabilities; in the assembly stage, the T-shaped space station assembly forms a cross-shaped structure through the structure, sufficient sealed cabins, energy, heat dissipation and other resources are provided for the whole station, and butt joint and parking support is provided for visiting aircrafts and subsequent cabin sections. A large opening is formed in the radial direction of the multipurpose cabin to the ground, large equipment in the cabin is supported to be deployed out of the cabin, double inner pressure-bearing cabin doors are adopted, and the sealing safety of the space in the cabin is improved; by arranging the large observation window on the inner layer bearing cabin door, the space station has the safe direct ground observation capability.

The invention discloses a virtual simulation and evaluation method for outboard maintenance of large equipment of a manned spacecraft. The method comprises the following steps: S1, establishing a virtual simulation model for outboard maintenance of the large equipment of the manned spacecraft; s2, setting constraint conditions of astronauts; s3, performing virtual maintenance process simulation and multi-person view angle and interactive setting; s4, transfer and installation path planning of the large-scale equipment; and S5, performing man-machine ergonomics analysis and judgment. According to the manned spacecraft large-scale equipment outboard maintenance virtual simulation and evaluation method provided by the invention, an active stereo display technology, a virtual training environment building technology and a virtual operation process model building technology are taken as main research objects; a virtual reality man-machine interaction mode which integrates an operation handle, a stereoscopic display system, a motion tracker and other devices and has immersion performance is constructed, analysis and evaluation of the whole process and multiple factors can be covered, visibility, reachability, operability, maintenance time and the like of the maintenance process outside the cabin are verified, and a reference basis is provided for reasonability of the maintenance process.

The invention relates to a manned spacecraft material exposure experiment platform and experiment method, and the material exposure experiment platform comprises a cabin door thermal control multi-layer thermal insulation material, an exposure platform, a material test piece, and uplink and downlink soft packages. The exposure experiment of the material test piece on the manned spacecraft is realized through six steps of launching the exposure platform along with the manned spacecraft, ascending the material test piece along with the transportation spaceship, deploying the material test piece on orbit by an astronaut, exposing the material test piece on orbit, recovering the material test piece on orbit by the astronaut and descending the material test piece along with the transportation spaceship. Compared with an existing material exposure experiment technology, under the condition that astronauts do not need to go out of the cabin or goods go in and out of the cabin for supporting, the material test piece can be deployed from the inside to the outside of the cabin and recycled from the outside to enter the cabin, the material test piece can roll on the manned spacecraft to carry out exposure experiments in turns, experiment operation is safe, easy and convenient, and the experiment efficiency is high. Cost is low and experiment benefits are high.

The utility model discloses a lighting power supply controller used in a manned spacecraft cabin and an anti-vibration base, the lighting power supply controller comprises a controller housing, and a power supply module and a signal communication module which are arranged in the controller housing, the power supply module is provided with a spectrum adjusting circuit, and high color rendering spectrum output is realized by mixing white light and yellow light; the signal communication module comprises a wireless signal amplifying and transmitting circuit, mounting lugs are respectively arranged on the controller shell, mounting through holes are formed in the mounting lugs, anti-vibration bases with axial and radial buffering are mounted on the mounting through holes, and connecting interfaces are formed in the two sides of the controller shell. The utility model aims to provide the lighting power supply controller and the vibration-proof base for the manned spacecraft cabin, which integrate high-color-rendering spectrum output, low-flicker eye protection design and vibration-proof structure optimization, and on the basis of meeting the requirements of high-color-rendering and low-flicker eye protection of lighting in the cabin, high-efficiency power supply, reliable communication and excellent vibration-proof capability are realized; and a safe and comfortable lighting environment is provided for astronauts.

The present application relates to a kind of manned spacecraft goods automatic access cabin general fixing device, belong to manned spacecraft overall design technical field.It includes upper plate, intermediate connection structure, lower plate, fixed baffle, fixed baffle buffer foam, initial position sensor, control driver, sliding baffle, sliding baffle buffer foam, initial position sensor stop block, limit position sensor stop block, ball nut, limit position sensor, drive motor, bearing, ball screw.The scheme of the present application can realize the fixation of non-cooperative access cabin goods on load transfer mechanism, further realize its egress or access task, and can realize the fixation of access goods on load transfer mechanism in the case of active end failure of quick docking device of cooperative access cabin goods, further realize its access task.

The present application relates to a kind of manned spacecraft application vacuum experiment system, including complex pressure subsystem, experimental container subsystem, vacuum pumping subsystem, exhaust gas subsystem.Complex pressure subsystem includes complex pressure cylinder, cylinder pressure gauge, cylinder manual valve, cylinder disconnecting device, complex pressure electric valve, complex pressure pressure reducing valve, complex pressure pipeline.Experimental container subsystem includes cavity, cavity pressure gauge, cavity balance valve, cavity door.Vacuum pumping subsystem includes vacuum pumping pipeline, vacuum pumping filter, vacuum pumping electric valve.Exhaust gas subsystem includes exhaust gas pipeline, exhaust gas filter, exhaust gas electric valve.The present application can solve the problem of space science experiment in the sealed cabin of manned spacecraft and exhaust gas, effectively expand the type of space science experiment in cabin, greatly improve the application value of manned spacecraft in orbit.

The application discloses a multi-outer shape adaptive outward opening manned spacecraft cabin door device, and belongs to the technical field of manned spacecraft cabin doors. The cabin door device comprises a door frame structure, a door body structure, a door shaft hinge mechanism and a repeated locking mechanism. The door frame structure is arranged on the outer circumferential surface of a cabin body. The door body structure is hinged to the door frame structure through the door shaft hinge mechanism. The repeated locking mechanism is a single-drive multi-latch pin linkage spatial linkage mechanism arranged on the inner surface of the door body structure through a support. After the door body structure is closed inward relative to the door frame structure, the multiple latch pins in the repeated locking mechanism can abut against the inner surface of the door frame structure, and the door body structure can compress an elastic sealing element to realize sealing at the contact position of the door frame structure and the door body structure. The cabin door device makes the transmission efficiency of each compression point close, is beneficial to uniform application of locking load, and is simple and convenient to operate in unlocking and locking, and is beneficial to opening of the cabin door in a short time.

The invention discloses a structure-variable simulation cabin for a light environment test of a manned spacecraft, and relates to the technical field of environment simulation of manned spacecrafts. Comprising a simulation cabin main body composed of replaceable functional wall plates, the outer wall of the simulation cabin main body is provided with a top ring frame, a side ring frame and a bottom ring frame which are used for limiting the spatial configuration of the simulation cabin main body and are detachably connected with the functional wall plates, and the side ring frame comprises a plurality of arc-shaped frame strips; the device further comprises an outer frame provided with a top ring frame installation rod and a telescopic mechanism, and the telescopic mechanism is vertically and movably installed on the outer frame and can adjust the positions of the arc-shaped frame strips in the radial direction of the side ring frame. According to the simulation cabin with the variable structure for testing the light environment of the manned spacecraft, provided by the invention, the simulation cabin can simulate the in-cabin environments of different manned spacecrafts by quickly adjusting the geometric configuration of the internal space of the simulation cabin; therefore, a ground verification platform which is efficient, economical and high in adaptability is provided for in-cabin light environment testing and man-machine work efficiency evaluation.

This invention relates to a decision-making method for handling leaks in the sealed cabin of a manned spacecraft assembly. Upon detecting a leak in the sealed cabin, the spacecraft platform transmits the measured values ​​of the total pressure and pressure drop rate of the sealed cabin to the ground flight control support system via telemetry. Based on the current measured values ​​of the total pressure and pressure drop rate of the sealed cabin, and the health status of the on-orbit personnel, a decision is made regarding whether protective equipment is required. The location and quadrant of the leak are determined, and the on-orbit personnel are guided to locate the leak and repair it. The on-orbit gas supply strategy is optimized to obtain the optimal cabin pressure control point and its corresponding longest operational support time. The cabin pressure control point is introduced as the desired cabin pressure into the closed-loop control for cabin pressure maintenance, and gas supply control is performed to maintain cabin pressure. If leak plugging fails, an evacuation decision is made; if leak plugging has been completed, a decision is made to restore the pressure of the sealed cabin.

The application discloses a manned spacecraft extravehicular activity ground in-situ suspension test verification system and method, which comprises a spacecraft cabin body, a horizontal rotation tool, a vertical support tool, an extravehicular space suit, an extravehicular space suit matching ground equipment, a suspension device and a lifting vehicle; wherein the spacecraft cabin body is parked on the horizontal rotation tool or the vertical support tool; the horizontal rotation tool controls the spacecraft cabin body to rotate along a horizontal axis to adjust the position of the equipment on the spacecraft; the extravehicular space suit is connected with the extravehicular space suit matching ground equipment; the extravehicular space suit matching ground equipment is placed on the first lifting vehicle and moves horizontally and up and down with the first lifting vehicle to cooperate with the movement of the extravehicular space suit; the suspension device lifts the extravehicular space suit and shifts to an operation position; the second lifting vehicle is used for carrying a test person to the vicinity of the extravehicular space suit to assist the test person in the extravehicular space suit to operate. The application solves the problem of verifying the feasibility of extravehicular operation during long-term on-orbit flight of the manned spacecraft.

The application belongs to the technical field of manned spaceflight, and discloses a kind of broken bridge type space station cabin interconnecting device.The device includes: main cabin end component, parking end component and base component;Wherein, the main cabin end component is detachably connected with the main cabin body, the base component is detachably connected with the parking cabin body, and the base component is inserted and connected with the parking end component;The main cabin end component and the parking end component are not directly connected, and together constitute the broken bridge type climbing channel between the main cabin body and the parking cabin body.The device is directly separated in emergency due to the absence of direct physical connection between the main cabin body and the parking cabin body, not only gains the processing time of emergency, improves the safety of space station, but also avoids the risk of emergency egress of astronauts.

This invention discloses an independent temperature and humidity control system and method for a manned spacecraft sealed cabin based on vacuum-driven membrane dehumidification. The system consists of an air circulation subsystem, a vacuum-driven membrane dehumidification subsystem, an external radiative cooling subsystem, and a control subsystem. The core utilizes the external natural vacuum to provide mass transfer driving force for membrane dehumidification. A highly selective vacuum dehumidification membrane is used to achieve pure gas phase isothermal dehumidification, which is combined with dry-condition operation of the surface cooler to complete sensible heat cooling, achieving separate regulation of humidity and heat loads. By adjusting the airflow of the dehumidification and bypass channels and the working fluid flow rate of the radiative cooling subsystem, combined with a multi-strategy control algorithm, complete decoupling and independent precise control of temperature and humidity are achieved. This invention fundamentally avoids the problem of condensate retention under microgravity, fully utilizes the natural space environment to reduce system energy consumption and structural complexity, and has the advantages of no condensation risk, strong microgravity adaptability, high control precision, and lightweight design. It is suitable for temperature and humidity control in manned spacecraft sealed cabins and various sealed cabins.

The invention discloses a device for an astronaut to get on and off the tail end of a mechanical arm during out-of-cabin activity. The device comprises a portable joint foot limiter, an out-of-cabin operation table and a base. The base is fixedly mounted on a mechanical arm or a cabin wall; the portable joint foot limiter is used for being mounted on the base after the astronaut leaves the cabin; the portable joint foot limiter comprises a pedal assembly, wherein the pedal assembly is used for locking the spaceflight boot; the outboard operation table is installed on the portable joint foot limiting stopper and comprises a supporting rod and a carrying assembly. The supporting rod is used for supporting the carrying assembly, and the carrying assembly is used for storing astronaut outboard operation tools and equipment. The invention further discloses a method for the out-of-cabin activity astronaut to get on and off the tail end of the mechanical arm. According to the application of the mechanical arm to transfer the astronaut for the manned spacecraft astronaut out-of-cabin task, the function of supporting transfer and operation of the astronaut and related equipment outside a sealed cabin is achieved, and an on-orbit operation basis is provided for the astronaut to get on and off the mechanical arm.

The present application relates to the field of space technology test evaluation, and more particularly to a method for analyzing necessity of on-orbit verification of load based on space environment, comprising obtaining test requirement data of space technology to be verified, the test requirement data including environment parameter requirement data, on-orbit operation requirement data, manned spacecraft on-orbit platform resource requirement data, and cost and risk data related to the test; based on the obtained test requirement data, respectively calculating environment irreplaceability comprehensive index N E , human-in-the-loop dependence comprehensive index D H , platform support adaptability comprehensive index A P , and comprehensive benefit gain index G B ; based on the four indexes calculated, according to a preset three-level judgment rule, outputting a manned spacecraft on-orbit test necessity judgment conclusion. The present application quantifies the multi-factor coupled environment irreplaceability, human-machine cooperation irreplaceability and platform matching degree, provides objective decision support for test planning, and optimizes the on-orbit resource allocation of manned spacecraft.

The present application relates to a kind of manned spacecraft microbial prevention and control device and method, including air pipe, replacement rod, reverse buckle, charge and exhaust console, clean gas source;Replacement rod adopts telescopic hollow fishing rod structure, reverse buckle is installed at the preset position of air pipe end, air pipe is inserted into the hollow cavity of replacement rod handheld end, and from the end of replacement rod fully deployed, make one end of reverse buckle fixed at the end of air pipe, the other end is stuck in the end of replacement rod, guarantee that air pipe can only move in one direction, air pipe after being connected with replacement rod is deeply inserted into the bottom end of cabin;Charge and exhaust console is set outside the cabin, air inlet is connected with clean gas source, air outlet is connected with air pipe, the pressure and flow of clean air are adjusted by charge and exhaust console, gradually make clean air inject into cabin, contaminated air in cabin is discharged outside the cabin, realize that air in cabin is purified.The problem that the number of air microorganisms in manned spacecraft before launch is more, and cabin is not fully purified is solved.

The application discloses a gravity simulation method for preventing low-gravity or weightlessness syndrome, belongs to the field of space medicine and manned space technology, and aims to solve the technical problems of low-gravity or weightlessness environment, loss of axial compression load of human body, limited effect of existing protection means, and obvious side effects. The application applies opposite forces between two or more axial load-bearing parts of the human body, constructs an axial compression mechanical load close to the physiological state of the earth gravity in the human body, and alleviates and improves the weightlessness syndrome from the mechanical root.

The present application relates to the technical field of manned spaceflight, and particularly relates to a rescue satellite hose compression release device, wherein the rescue satellite hose compression release device comprises a base and a strap; the base is formed with a containing groove and an avoiding groove; the base is suitable for detachable connection with a cabin plate of a rescue satellite; the strap is installed on the base and is suitable for restraining a hose in the containing groove; before launching the rescue satellite, the base is installed on the cabin plate of the rescue satellite, the hose is placed in the containing groove, and the hose is compressed in the containing groove by using the strap to cope with the violent impact and vibration during launching; after orbiting, the strap can be cut by using a cutting tool so that the hose is released and separated from the base. Compared with a traditional compression release device, the structure is simplified, the possibility of failure of a hose fixing and releasing compression release system is greatly reduced, the reliability of the hose fixing and releasing compression release system is improved, and the reliability of the whole satellite system is finally improved.

This invention relates to the field of space technology experiment evaluation, and more particularly to a method for analyzing the necessity of on-orbit verification of payloads based on the space environment. The method includes acquiring experimental requirement data for the space technology to be verified, including environmental parameter requirements, on-orbit operational requirements, manned spacecraft on-orbit platform resource requirements, and cost and risk data related to the experiment. Based on the acquired experimental requirement data, a comprehensive index of environmental irreplaceability is calculated. N E Human-loop dependency comprehensive index D H Platform compatibility comprehensive indicators A P and comprehensive benefit gain indicators G B Based on the four calculated indicators, and according to the preset three-level judgment rules, the necessity judgment conclusion for the on-orbit test of the manned spacecraft is output. This invention quantifies the unsimulability of the multi-factor coupled environment, the irreplaceability of human-machine collaboration, and the platform matching degree, providing objective decision support for test planning and optimizing the on-orbit resource allocation of manned spacecraft.

A manned spacecraft in-orbit state control model and method based on data homology, facing the long-term in-orbit operation of complex large manned spacecraft, proposes a flight state control method based on data homology, mainly used to solve the contradiction between the complex and dynamic change of manned spacecraft in-orbit state and the fine and real-time state control demand, and proposes a manned spacecraft in-orbit state information control model architecture, which optimizes the in-orbit operation control efficiency of manned spacecraft.