59 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 long-life maintainable manned spacecraft full-period reliability verification method, which comprises the steps of designing and optimizing product life and task reliability indexes based on an Ankov system; product life and reliability information is continuously collected and managed, and applicability analysis of life and reliability information of general products and similar products is carried out; according to product life and task reliability requirements, analyzing sufficiency of existing information, determining a life and reliability verification comprehensive scheme, and planning a life and reliability verification test; a multi-subsample part assembly is combined with a small subsample complete machine quantification verification test, and the test opportunity is moved forward; collecting on-orbit flight data, and identifying on-orbit life and reliability characteristics; and analyzing space-ground difference, and carrying out on-orbit service life and task reliability verification by integrating on-orbit flight data and reliability information in a development stage. According to the method, the problem of poor verification effectiveness caused by the fact that in-orbit flight data cannot be effectively fused is solved, the verification cost is remarkably controlled, and the verification opportunity is moved forward.

The invention relates to the technical field of manned spaceflight, in particular to a foldable armrest easy to mount outside a space station cabin, which comprises a base, an armrest, a first limiting mechanism and a locking mechanism, the handrail is rotatably mounted on the base; a limiting groove and a locking hole are formed in the handrail; the first limiting mechanism is mounted on the base and can be inserted into any limiting groove; the locking mechanism is installed on the base and can be inserted into any locking hole. During launching, the foldable unfolding handrail is in a folded state. After injection into a rail, the foldable and unfoldable handrail which is easily mounted outside the space station cabin can be freely switched between a folded state and an unfolded state. And compared with a traditional fixed handrail, the occupied space is small in the launching process, and the use flexibility is high. Compared with a traditional on-track detachable handrail, the on-track mounting process is avoided. Compared with a traditional handrail for the ground, the foldable handrail for the ground is always kept in a folded state and does not deform when bearing large centrifugal force, impact and vibration in the launching stage.

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 a gas-liquid separation device available for microgravity and lunar surface. The gas-liquid separation device comprises a gas-liquid separation cavity, a spiral flow guide structure, a metal net and two layers of porous media. The gas-liquid separation device is applied to a manned spacecraft environment control and life support system and is used for separating urine of astronauts from mixed gas-liquid fluid. A plurality of gas-liquid mixture inlets, an exhaust port and a liquid discharge port are formed outside the gas-liquid separation cavity, a spiral flow guide structure is arranged inside the gas-liquid separation cavity, and a layer of metal net is clamped between two layers of porous media below a flow guide plate. Gas-liquid mixed fluid enters the gas-liquid separation cavity through a plurality of inlet pipelines above and sequentially passes through the spiral flow guide structure, the metal net and the porous medium, finally liquid is discharged through a liquid outlet below the porous medium, gas in the gas-liquid mixed fluid is discharged through an exhaust port above the device, and gas-liquid separation in the urine mixed gas-liquid fluid is achieved.

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 manned spaceflight emergency rescue test launching process configuration method and system, and the method comprises the steps: obtaining a test file and a configuration file, enabling the test file to comprise emergency rescue test items and the minimum time consumption thereof, enabling the configuration file to comprise a strong coupling relation between the emergency rescue test items, analyzing the configuration file and the test file, and transmitting the analysis result to a server. Constructing an emergency rescue test emission process pool and an identification information sequence; importing the emergency rescue test launching process pool into a computing control center; running a test emission process based on the identification information sequence; matching the test result with the total time consumption information; judging whether the emergency rescue test launching process pool is read or not, if not, returning to continue reading, and if yes, obtaining all test results and time consumption information; and analyzing and comparing the time consumption information of all the read test emission flows, and selecting the test emission flow with the shortest time consumption as the optimal test emission flow. According to the invention, the optimal configuration of the launching process of the manned spaceflight emergency rescue test is realized.

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 utility model discloses a passage lighting device used in a manned spacecraft cabin, which comprises a lamp housing, mounting parts arranged on two sides of the lamp housing, a light-transmitting slotted hole arranged on the front end face of the lamp housing, a light-transmitting plate arranged in the lamp housing and capable of covering the light-transmitting slotted hole, and a light guide plate arranged in the lamp housing above the light-transmitting plate. At least one side of the light guide plate is provided with a light inlet face, a light outlet face of the light guide plate is located on one side of the light transmitting plate, a light bar is arranged at the position, corresponding to the light inlet face, in the lamp shell, a first pressing mechanism capable of pressing the end of the light guide plate is arranged at the position, close to the mounting portion, in the lamp shell, and a bottom cover is arranged on the rear end face of the lamp shell. A second pressing mechanism capable of pressing the light guide plate is arranged on the inner side face of the bottom cover. In order to overcome the defects in the prior art, the utility model provides the channel lighting device which is simple in structure, good in stability of internal parts, not easy to loosen and capable of being used in a manned spacecraft cabin for a long time.

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 safety state monitoring system for a manned spacecraft in long-term in-orbit operation. The system comprises a telemetry data receiving module, a dangerous event monitoring module and a dangerous source state monitoring module, the telemetry data receiving module is used for receiving downlink telemetry parameters of the manned spacecraft running in orbit; the dangerous event monitoring module is used for judging whether a dangerous event occurs or not according to environment monitoring telemetry parameters, corresponding to the dangerous event, of the manned spacecraft, and sending a dangerous event judgment result to the comprehensive evaluation module; the danger source state monitoring module is used for judging the safety state of the danger source according to whether the telemetering parameters of the danger source are within a preset value range or not; and the comprehensive evaluation module is used for judging whether the manned spacecraft is in a safe state or not according to the dangerous event judgment result, the consequence severity degree of the dangerous source and the safe state of the dangerous source.

The invention discloses a manual exhaust sealing cover device for emergency of a manned spacecraft, and belongs to the field of pressure control and pressure relief in cabins of manned spacecrafts. The device comprises a sealing cover, a wrench, a sealing valve body, a reed and a pin. The sealing cover is hinged to the sealing valve body through a pin, hot-pressing rubber is arranged on the lower surface of the sealing cover, and a sealing ring is arranged on the upper surface of the sealing valve body and matched with the hot-pressing rubber. The two wrenches are connected to the two sides of the sealing cover through pins, and the reeds are fixed to the inner sides of the wrenches. Under the non-emergency condition, the sealing cover is pressed after the two wrenches buckle the sealing valve body, the hot-pressing rubber is pressed on the sealing ring, and the reed provides sealing force. In emergency, an astronaut opens the wrench firstly when wearing clothes, then the sealing cover is lifted up for pressure relief, and it is guaranteed that the astronaut goes out of a cabin smoothly.

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 invention relates to a manned spacecraft assembly sealed cabin leakage fault disposal decision-making method, which comprises the following steps: after detecting that a spacecraft assembly has a sealed cabin leakage fault, a spacecraft platform sends measured values of total pressure and pressure drop rate of a sealed cabin to a ground flight control support system through telemetering data; according to the measured values of the total pressure and the pressure drop rate of the current sealed cabin of the manned spacecraft assembly and the health state of the on-orbit personnel, making a decision on whether to wear a protective device, determining the area and the quadrant of the leak hole where leakage occurs, prompting the on-orbit personnel to locate the position of the leak hole, and guiding the on-orbit personnel to repair the leakage; optimizing an on-orbit gas resource gas supply strategy to obtain an optimal cabin pressure control point and the longest operation support time corresponding to the optimal cabin pressure control point, introducing the cabin pressure control point into closed-loop control of cabin pressure maintenance as expected cabin pressure, and performing gas supply control of cabin pressure maintenance; if leaking stoppage is not completed, an evacuation decision is made, and if leaking stoppage is completed, a decision for recovering pressure of the sealed cabin is made.

The invention discloses a manned spacecraft extravehicular movable ground in-situ suspension test verification system and method. The manned spacecraft extravehicular movable ground in-situ suspension test verification system comprises a spacecraft cabin, a horizontal rotating tool, a vertical support tool, an extravehicular spacesuit, extravehicular spacesuit matched ground equipment, a suspension device and a lift truck. Wherein the spacecraft cabin is parked on the horizontal rotating tool or the vertical bracket tool; the horizontal rotating tool controls the spacecraft cabin to rotate along the horizontal axis so as to adjust the position of equipment on the spacecraft; the extravehicular spacesuit is connected with the extravehicular spacesuit matched ground equipment; the extravehicular spacesuit matched ground equipment is placed on the first lifting vehicle and translates and moves up and down along with the first lifting vehicle so as to be matched with the extravehicular spacesuit to move; the suspension device lifts the extravehicular spacesuit and transfers the extravehicular spacesuit to an operation position; and the second lift truck is used for carrying the testee to reach the vicinity of the extravehicular spacesuit and assisting the testee in the extravehicular spacesuit to operate. According to the method, the problem of verifying the outboard operation feasibility during the long-term in-orbit flight of the manned spacecraft is solved.

The invention provides a method for determining an outgassing product of a component in a sealed cabin of a manned spacecraft. The method comprises the following steps: pretreating a test component to prepare a test sample; putting the test sample into a prepared closed sample container, putting the sample container into a test box, heating to 48-52 DEG C, and keeping the temperature for 71-73 hours; cooling to room temperature, sampling a gas outlet product generated by release of a test part assembly, adding a lead acetate cotton tube into a sampling tube before sampling, placing absorption liquid of the sampling tube into a 10mL colorimetric tube after sampling, fixing the volume to 10mL scale by using 0.005 mol / L sulfuric acid solution, adding 0.50 mL Nessler reagent, shaking up, measuring absorbance, arranging a blank tube, and measuring the absorbance by using a standard curve. The ammonia concentration in the gas outlet product can be obtained according to the standard curve, and support can be provided for material selection and air environment control of the sealed cabin of the manned spacecraft.

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.