44 results about "Human spaceflight" patented technology

The invention relates to a manned spacecraft on-orbit health state evaluation method, which comprises the steps of manned spacecraft on-orbit state evaluation: evaluating the on-orbit state of manned spacecraft key equipment according to telemetry parameter evolution characteristics representing manned spacecraft function indexes; evaluating the technical capability of the manned spacecraft: before the manned spacecraft executes a key on-orbit task, evaluating whether a cabin sealing function, an attitude control function, an orbit control function, a docking function, and a mechanical arm and a pressure relief and recompression device related to execution of the key task are normal or not; carrying out task evaluation on the manned spacecraft: carrying out task execution condition evaluation on a key on-orbit task during the on-orbit operation period of the manned spacecraft; reliability and safety evaluation: evaluating the on-orbit safety, reliability, maintainability and life condition of the manned spacecraft, and identifying internal and external risks possibly existing in the long-term on-orbit operation period; and guarantee condition evaluation: evaluating whether the ground flight control team guarantee condition meets the flight control task requirement or not.

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, in particular to an atmosphere adjusting device for a manned spaceflight scientific test, which comprises a mounting bracket, a main gas source gas cylinder, an adjusting gas source gas cylinder, a first control module and a second control module, a main air source output joint and an adjusting air source output joint are arranged at the front end of the side wall of the mounting bracket; the main gas source gas cylinder is arranged on one side of the top of the mounting bracket through the gas cylinder fixer, and the adjusting gas source gas cylinder is arranged on the other side of the top of the mounting bracket through the gas cylinder fixer; a main air source pipeline and an adjusting air source pipeline are arranged in the lower part of the mounting bracket; the first control module is arranged on the main air source pipeline, and the second control module is arranged on the adjusting air source pipeline. Various test gases can be provided for manned spaceflight scientific tests, high-pressure storage and accurate supply of the gases can be realized, and quick replacement and on-orbit disassembly and movement of the gas cylinders can also be realized.

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.

In order to solve the problem that the existing panoramic image shooting method cannot take clear images at different depths of field, resulting in blurred areas in the stitched panoramic image, which affects the effect of the manned spacecraft panoramic image, the present invention provides a manned spacecraft AIT process ultra-high-definition panoramic image multi-depth fusion technology, including the following steps: S1: shooting multi-depth original images; S2: using image similarity recognition technology to group multi-depth original images; S3: panoramic image stitching; S4: using a blur recognition algorithm to identify the blurred area of ​​the panoramic image; S5: using a multi-depth fusion method to generate a clear panoramic image. The present invention shoots multi-depth images at different focal points at each position through the above steps, and generates a clear panoramic image through the multi-depth fusion technology.

1. The name of this design product: Spacecraft cabin lighting power controller. 2. Purpose of this design product: used as a lighting power controller in a manned spacecraft cabin. 3. The key point of the design of this product lies in its shape. 4. The picture or photo that best illustrates the design points: three-dimensional picture.

The invention relates to the technical field of spaceflight launching, and provides a data processing method and system for manned spaceflight launching, electronic equipment and a medium, and the method comprises the steps: S1, obtaining a process item set of a manned spaceflight on-duty launching technology; s2, acquiring four modes of manned spaceflight on-duty launching; s3, setting a security recovery point; s4, setting emission technology process item sets corresponding to the four modes; s5, acquiring a current transmitting condition; if the emergency rescue launching condition is met, launching is carried out according to an emergency rescue technical process item set; s6, if the conventional rescue launching conditions are met, launching is carried out according to a conventional rescue technology project set; s7, in the implementation process, if emergency rescue launching conditions are met, launching is carried out according to an emergency rescue technology project set; if conventional rescue launching conditions are met, launching is implemented according to conventional rescue technology and process projects; and S8, repeating the steps S5 to S7 until the emission is completed. According to the scheme, on the premise that reliability and safety are guaranteed, the task process cycle is shortest.

The invention discloses a manned spacecraft distributor circuit modeling method based on a new generation power distribution switch, and belongs to the field of spacecraft system simulation. According to requirements of system energy matching simulation, the method realizes simulation of working steady-state characteristics and a dynamic process of the distributor by establishing a contactor switch module, an SSPC intelligent switch module and a signal interface module, and adopts a modular modeling method to realize simulation of the working steady-state characteristics and the dynamic process of the distributor. On the basis of an established contactor switch module, an SSPC intelligent switch module and a signal interface module, a power distributor model is constructed according to system construction, and can be used for accurately simulating complex characteristics of a novel power distributor.

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 manned spacecraft cabin lighting power supply controller and an anti-vibration base, the manned spacecraft cabin lighting power supply controller comprises a controller shell, and a power supply module and a signal communication module which are arranged in the controller shell, and the power supply module is provided with a spectrum adjusting circuit which can realize high color rendering spectrum output by mixing white light and yellow light; the signal communication module comprises a wireless signal amplifying and transmitting circuit, a plurality of 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 invention aims to provide the manned spacecraft in-cabin lighting power supply controller integrating high-color rendering spectrum output, low-flicker eye protection design and anti-vibration structure optimization, and the anti-vibration base, on the basis of meeting the in-cabin lighting high-color rendering and low-flicker eye protection requirements, realize efficient power supply, reliable communication and excellent anti-vibration capability, and improve the reliability of the in-cabin lighting power supply controller and the anti-vibration base of the manned spacecraft on the basis of meeting the in-cabin lighting high-color rendering and low-flicker eye protection requirements. And a safe and comfortable lighting environment is provided for astronauts.

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 visiting aircraft on-orbit parking charging system and method, and belongs to the technical field of on-orbit parking charging. The system comprises a manned spacecraft assembly main power supply, a docking device, a grid-connected controller, a grid-connected charging controller, a power distribution device and a visiting aircraft main power supply. Under normal conditions, the main power supply system of the visiting aircraft keeps the original working mode, and the grid-connected charging controller is not connected to the energy system. When the main power supply of the visiting aircraft has a serious fault, grid-connected power supply is performed on the parked fault visiting aircraft through the power supply of the manned spacecraft assembly, and meanwhile, the main power supply unit can be slowly charged to ensure that the main power supply unit is fully charged before separation. The method can effectively save the electric quantity of the main power supply of the visiting aircraft, improves the supporting capability of the main power supply during the execution of subsequent flight tasks, and powerfully guarantees the stopping tasks such as return of astronauts.

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.

This paper proposes a comprehensive management and control method for space safety and mission risks. It improves traditional risk management methods from four aspects: risk classification, risk quantification, risk dynamic characteristics, and risk judgment and decision support. This improves the effectiveness of comprehensive risk management and control, and reduces space mission and safety risks. By simultaneously considering both space safety and mission risks, the paper offers promising prospects for promotion and application from non-manned to manned space models. It prioritizes the quantitative evaluation of mission and safety risks, enabling more effective support for risk response through ranking by importance. It explicitly addresses the dynamic characteristics of risks, identifying key safety and mission risks under dynamic circumstances through risk propagation prediction. It also explicitly addresses the issue of ordering party risk management, supporting ordering parties in making comprehensive risk trade-offs based on factors such as time and funding through risk judgment and decision making.

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 invention discloses an on-orbit voltage stabilization source supporting manned spacecraft maintenance power-on, which comprises a power supply system, a discharge switch K1, an on-orbit voltage stabilization source module, a maintenance power supply switch K2 coil, a power supply bus A and a power supply bus B. The power supply system is converged into the power supply bus B through the discharge switch K1 and provides energy for remote control and telemetering loads and other loads on a spacecraft; the power supply bus A is connected with the on-orbit voltage stabilization source module; the on-orbit voltage stabilization source module is connected with a maintenance power supply switch K2 coil, and the maintenance power supply switch K2 coil is connected with the power supply bus B. According to the on-orbit voltage stabilization source for maintenance power-on of the manned spacecraft, after on-orbit power-off maintenance of the power supply system is carried out, power supply of the power supply system is restored through on-orbit operation of an astronaut, the electrical safety of on-orbit maintenance operation of the power supply system of the spacecraft is guaranteed, an on-orbit maintenance scheme of the power supply system on the manned spacecraft is feasible, and the maintenance efficiency of the power supply system on the manned spacecraft is improved. Therefore, the purpose of prolonging the on-orbit service life of the manned spacecraft is achieved.

The application discloses an energetic wave impedance gradient material for space debris super-high-speed impact protection, which is based on inert metal component materials and adds an energetic active material layer as a component material. In the application, the inert metal material and the energetic active material are combined according to a certain rule through wave impedance gradient matching design and impact initiation threshold adjustment, so that the new composite material has both wave impedance gradient and impact initiation reaction under super-high-speed impact, and the two effects jointly promote the fragmentation and dispersion of the projectile, thereby further improving the protection capability. The new high-performance space debris protection material combines the two protection mechanisms of wave impedance gradient and impact initiation reaction, has higher protection capability under the same mass, and can be directly applied to the space debris protection design of manned spacecraft and high-value satellites, so as to ensure the long-life and high-reliability operation of on-orbit spacecraft of China.

The present invention relates to the field of space launch technology and provides a data processing method, system, electronic device, and medium for manned space launches. The method comprises the following steps: S1: obtaining a set of technical and process items for manned space launch duty; S2: obtaining four modes of manned space launch duty; S3: setting a safe recovery point; S4: setting a set of launch technical and process items corresponding to the four modes; S5: obtaining current launch conditions; if the emergency rescue launch conditions are met, launching is carried out in accordance with the emergency rescue technical and process item set; S6: if the conventional rescue launch conditions are met, launching is carried out in accordance with the conventional rescue technical and process item set; S7: during the launch process, if the emergency rescue launch conditions are met, launching is carried out in accordance with the emergency rescue technical and process item set; if the conventional rescue launch conditions are met, launching is carried out in accordance with the conventional rescue technical and process items; S8: repeating S5 to S7 until the launch is completed. This solution minimizes the mission process cycle while ensuring reliability and safety.

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 invention relates to a method for identifying safety key projects of a long-term in-orbit operation multi-cabin manned spacecraft, which comprises the following steps of: performing mission profile analysis, determining safety key programs in an in-orbit flight process of the manned spacecraft, and listing the safety key programs into a system-level safety key project list; performing function analysis on the system, determining safety key functions of the manned spacecraft, and listing the safety key functions into a system-level safety key item list; performing function analysis on the subsystems, determining safety key functions of the manned spacecraft, and listing the safety key functions into a subsystem-level safety key item list; carrying out danger analysis on the equipment, determining safety key equipment of the manned spacecraft, and listing the safety key equipment into an equipment-level safety key item list; and summarizing and comprehensively analyzing system-level, subsystem-level and equipment-level key item lists, determining equipment for realizing safety key programs and safety key functions as safety key equipment, removing repeated items, and finally forming a manned spacecraft key item list.

The present application provides a kind of manned spacecraft reusable propulsion system related to space propulsion system technical field, including gas cylinder module, storage tank module, gas circuit valve module, blowing module, discharge module and engine module, gas cylinder module downstream is connected gas circuit valve module, gas circuit valve module is connected storage tank module and blowing module respectively, storage tank module downstream is connected discharge module, blowing module, storage tank module and discharge module are connected engine module respectively;Spacecraft before return, gas cylinder module is pressurized to storage tank module by gas circuit valve module;Spacecraft before landing ground, the discharge of propellant is realized by discharge module, blowing module is blown to engine module;Spacecraft after landing, storage tank module is cleaned, dried, blown, gas circuit valve module carries out pressure reducing valve performance test, engine module carries out inspection, maintenance, realizes system reuse.The present application uses green non-toxic propellant, safety is good, has reusable capacity, has universal applicability.

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 quick switching mechanism of a manned space flight seat support rod and the manned space flight seat and belongs to the technical field of aerospace. The quick switching mechanism comprises a locking clamp seat, an inclined support clamping block, a torsion pin shaft and a shear-resistant pin, the inclined support clamping block is provided with a rod groove, the shear-resistant pin is connected with one end of the torsion pin shaft, the other end of the torsion pin shaft extends out of the locking clamp seat to form a shaft operating end, the torsion pin shaft comprises a rotating shaft body, a locking structure and an unlocking structure, the locking clamp part and the locking structure are matched with the shear-resistant pin, the shear-resistant pin can pass through a rod hole of the support rod to lock the support rod, the unlocking structure can be turned to the clamping position of the locking clamp part, the torsion pin shaft is in the unlocking position, and the torsion pin shaft and the shear-resistant pin can be axially moved to release the support rod. The seat posture switching operation is simple, only needs one twist, two pulls and three kicks to complete the posture switching action, special tools are not needed for the operation, the structure is small and light, mechanical structure is adopted, and the stability is high.

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 present invention relates to a model-based hierarchical fault analysis method for complex manned space systems. While using SysML for the design and analysis of complex manned space systems, potential faults are identified through the decomposition of the hierarchical system functions or structures, and the fault mode analysis of each layer of the system is carried out based on the model. Then, through the iteration of the models between the layers, the fault analysis of the entire system is completed. The present invention provides a new approach for fault identification in the model-based design and demonstration of future manned space engineering and other complex systems, which is beneficial to the traceability, control, and future system safety and reliability analysis of complex manned space system faults, and guides the system design, and can meet the needs of future model-based system engineering development.

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.