Decision-making method for handling leakage fault of sealed cabin of manned spacecraft assembly

Abstract

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.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft overall design, and in particular to a decision-making method for handling leakage failure of a sealed cabin of a manned spacecraft assembly. Background Art

[0002] Large manned spacecraft are in orbit for a long time, and there may be dangerous incidents of sealed cabin leakage due to space debris impact and other reasons. The total pressure drop in the sealed cabin directly threatens the life safety of personnel and is an emergency major failure. Manned spacecraft are important space assets. In the event of a sealed cabin leak, the space and the ground need to coordinate and do their utmost to carry out emergency measures such as positioning and plugging the leak, and do their utmost to save them.

[0003] Since my country has no experience in long-term in-orbit operation of large manned spacecraft, although all previous manned spacecraft have completed safety design and verification, due to the relatively short in-orbit flight time, the probability of space debris collision is small, and there has been no dangerous incident of sealed cabin leakage after space debris collision. However, as the in-orbit flight time of large manned spacecraft assemblies increases significantly, the number of in-orbit missions increases, and the time personnel stay in orbit increases, the probability of dangerous incidents of sealed cabin leakage after collision increases. In addition, as the system design of manned spacecraft assemblies becomes increasingly complex, and the operations to complete in-orbit emergency disposal increase, simply applying the methods in the existing technology to large manned spacecraft assemblies may cause the following problems:

[0004] 1. It is impossible to quickly confirm the specific location of the leak in the sealed cabin;

[0005] 2. It is impossible to form a coordinated effort between the heaven and earth to jointly support fault handling in the shortest possible time;

[0006] 3. It is impossible to fully utilize on-orbit resources and handle faults to the best of one's ability while ensuring the safety of on-orbit personnel. Summary of the invention

[0007] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art and provide a method for making decisions on the handling of leakage faults in the sealed cabin of a manned spacecraft assembly, which solves the problem that when a leakage occurs in the manned spacecraft assembly, the maximum capability of the spacecraft can be fully utilized to support the on-orbit personnel in carrying out fault handling, the safety of the on-orbit personnel can be guaranteed, and the manned spacecraft assembly can be saved to the greatest extent possible.

[0008] The solution to the technical problem of the present invention is: a decision-making method for handling leakage failure of a sealed cabin of a manned spacecraft assembly, the method comprising: after detecting leakage failure of a sealed cabin of a spacecraft assembly, the spacecraft platform executes the following steps:

[0009] (1) Send the measured values ​​of the total pressure and pressure drop rate of the sealed cabin to the ground flight control support system through telemetry data;

[0010] (2) Based on the measured values ​​of the total pressure and pressure drop rate of the sealed cabin of the manned spacecraft assembly, determine the severity of the leakage fault and the impact of the leakage fault of the spacecraft assembly on the health status of the on-orbit personnel, monitor the health status of the on-orbit personnel in real time, make a decision on whether to wear protective equipment, and push it to the on-orbit personnel;

[0011] (3) The manned spacecraft platform obtains the measurement data of the acoustic sensors, vibration sensors, pressure sensors, and temperature sensors installed in each spacecraft and each compartment of the manned spacecraft assembly, determines the area and quadrant where the leak is located, prompts the on-orbit personnel to locate the location of the leak, and sends the location information of the leak to the ground flight control support system through telemetry information;

[0012] (4) The manned spacecraft platform calculates the time required for on-orbit fault handling based on the leakage fault handling operation information preset in the sealed cabin where the leak hole is located; the leakage fault handling operation information includes the division of operation areas in the sealed cabin of the aircraft, the equipment to be operated in each operation area and the operation sequence, and the specific operation information required for each equipment;

[0013] (5) The manned spacecraft platform optimizes the on-orbit gas resource supply strategy based on the total pressure of the sealed cabins in each spacecraft of the spacecraft assembly, the pressure drop rate parameters, and the remaining amount of on-orbit gas resources parameters, with the longest operation support time as the control target, and obtains the optimal cabin pressure control point and its corresponding longest operation support time. The cabin pressure control point is introduced into the closed-loop control of cabin pressure maintenance as the expected cabin pressure, and the air supply control for cabin pressure maintenance is performed;

[0014] (6) If the longest operation support time corresponding to the optimal cabin pressure control point is less than the time required for on-orbit fault handling, an evacuation decision is made; otherwise, an on-orbit fault handling decision is made, and the on-orbit personnel are prompted to manually complete the on-orbit leak plugging operation through the head-mounted display device;

[0015] (7) When the time required for on-orbit fault handling has arrived, the manned spacecraft platform determines whether the leak has been plugged based on the pressure drop rate. If the leak has not been plugged, it will independently decide on the evacuation time of the on-orbit personnel and send telemetry information to the ground support personnel and on-orbit personnel to warn them in advance and prompt them to initiate the emergency evacuation support procedure. If the leak has been plugged, it will make a decision to restore the pressure of the sealed cabin based on the remaining amount of gas resources on orbit.

[0016] Preferably, the severity levels of the leakage fault include from high to low: level 1, level 2, and level 3. Level 1 means that personnel cannot survive and equipment cannot work; level 2 means that personnel cannot survive and equipment can work normally; level 3 means that personnel are in normal condition and equipment works normally.

[0017] Preferably, the health status of the on-orbit personnel includes: heart rate, blood oxygen, respiratory rate, movement speed, and reaction speed.

[0018] Preferably, the principle for determining the leak position is:

[0019] The gas temperature at the leak location is lower than the air temperature in the sealed cabin;

[0020] The pressure at the leak location is lower than the pressure in the sealed cabin;

[0021] The leak hole continuously produces a sound signal of a specific frequency;

[0022] If the leak is caused by impact, a vibration signal will be generated at the leak position when the impact occurs.

[0023] Preferably, the above-mentioned decision-making method for handling leakage failure of sealed cabin of manned spacecraft assembly further comprises the steps of ground support system:

[0024] The severity of leakage hazards in spacecraft assemblies is determined through telemetry parameters, and the impact on the health of on-orbit personnel and the functions of manned spacecraft are independently assessed, and the results are pushed to ground support personnel.

[0025] Compare the flight status of the spacecraft before and after the leakage failure occurs to determine the lost or degraded functions of the spacecraft, and find out the impact of the lost or degraded functions of the spacecraft on the on-orbit fault handling, and push it to the ground support personnel;

[0026] Based on the progress of on-orbit operations, the health status of on-orbit personnel and the sustainable time of on-orbit gas resources, a decision on whether to carry out an emergency evacuation is made and sent to the manned spacecraft via remote control commands.

[0027] Preferably, after receiving the decision of emergency evacuation, the manned spacecraft platform immediately warns the on-orbit personnel, prompting the on-orbit personnel to initiate the emergency evacuation support procedure.

[0028] Preferably, the method by which the ground support system makes a decision on emergency evacuation is:

[0029] Monitor the health status of on-orbit personnel in real time and evaluate their operational capabilities. If it is determined that the health status of on-orbit personnel cannot guarantee that they can complete on-orbit fault handling operations within the time that on-orbit gas resources can maintain, make a decision to execute emergency evacuation.

[0030] The beneficial effects of the present invention compared with the prior art are:

[0031] (1) The present invention uses the measurement data of acoustic sensors, vibration sensors, pressure sensors, and temperature sensors configured on each aircraft and each compartment of the manned spacecraft assembly to achieve rapid positioning of the leakage hole area. Compared with the method in the prior art of checking and confirming the pressure changes of each aircraft and each compartment one by one, the present invention simplifies the operating steps of the on-orbit personnel and saves the time of leak positioning while meeting the requirements of fault handling.

[0032] (2) The present invention uses the parameters of the total pressure of the sealed cabin of the manned spacecraft, the pressure drop rate, and the remaining amount of on-orbit gas resources to obtain the optimal cabin pressure control point with the longest operation support time as the control target, and introduces it into the closed-loop control of the cabin pressure maintenance system as the desired cabin pressure. It can cope with leakage from leaks of different sizes through limited gas resources. Compared with the method of maintaining cabin pressure according to a fixed cabin pressure control point in the prior art, the operation support time is increased while ensuring the safety of on-orbit personnel. More on-orbit operations can be completed, and the fault recovery capability is enhanced.

[0033] (3) The present invention adopts a method of comprehensively judging whether emergency evacuation is needed based on the progress of on-orbit operation and disposal, the health status of on-orbit personnel and the sustainable time of on-orbit gas resources, thereby achieving effective prediction of the results of handling leakage failures in the sealed cabin of a manned spacecraft. Compared with the prior art method that does not consider the impact of leakage on the operating ability of on-orbit personnel and only decides on emergency evacuation based on the function recovery of the spacecraft, the accuracy of the estimated handling results is improved while meeting the handling time constraints, while ensuring the safety of on-orbit personnel. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 The present invention is a flowchart of emergency fault handling decision-making for leakage in the sealed cabin of a manned spacecraft assembly according to an embodiment of the present invention.

[0035] Figure 2 The invention discloses a decision-making system for emergency failure handling of a sealed cabin leakage of a manned spacecraft assembly according to an embodiment of the present invention. DETAILED DESCRIPTION

[0036] The description of the embodiments of this specification should be combined with the corresponding drawings, which should be considered as part of the complete specification. In the drawings, the shape or thickness of the embodiments may be enlarged and indicated for simplification or convenience. Furthermore, the parts of each structure in the drawings will be described separately. It is worth noting that the elements not shown in the drawings or not described in words are in a form known to ordinary technicians in the relevant technical field.

[0037] The description of the embodiments herein and any reference to directions and orientations are only for the convenience of description and are not to be construed as any limitation on the scope of protection of the present invention. The following description of the preferred embodiments may involve combinations of features, which may exist independently or in combination, and the present invention is not particularly limited to the preferred embodiments. The scope of the present invention is defined by the claims.

[0038] Figure 1 A flowchart schematically shows a decision flow for handling leakage failure of a sealed cabin of a manned spacecraft assembly according to the present invention. Figure 1 As shown, the present invention provides a method for decision-making on leakage fault handling of a sealed cabin of a manned spacecraft assembly, the method comprising steps of a spacecraft platform and steps of a ground support system.

[0039] The spacecraft platform uses on-orbit personnel operation support equipment to provide on-orbit operators with protection under low total pressure conditions in a sealed cabin and monitor their physical health status. It also provides ground-to-space communication support during on-orbit operations and virtual environment prompts for on-orbit operation steps.

[0040] After detecting a leak in the sealed compartment of the spacecraft assembly, the spacecraft platform performs the following steps:

[0041] (1) Send the measured values ​​of the total pressure and pressure drop rate of the sealed cabin to the ground flight control support system through telemetry data;

[0042] (2) Based on the measured values ​​of the total pressure and pressure drop rate of the sealed cabin of the manned spacecraft assembly, determine the severity of the leakage fault and the impact of the leakage fault of the spacecraft assembly on the health status of the on-orbit personnel, monitor the health status of the on-orbit personnel in real time, make a decision on whether to wear protective equipment, and push it to the on-orbit personnel;

[0043] The severity levels of leakage failures are from high to low: Level 1, Level 2, and Level 3. Level 1 means that personnel cannot survive and equipment cannot work; Level 2 means that personnel cannot survive but equipment can work normally; Level 3 means that personnel are normal and equipment works normally.

[0044] (3) The manned spacecraft platform obtains the measurement data of the acoustic sensors, vibration sensors, pressure sensors, and temperature sensors installed in each spacecraft and each compartment of the manned spacecraft assembly, determines the area and quadrant where the leak is located, prompts the on-orbit personnel to locate the location of the leak, and sends the location information of the leak to the ground flight control support system through telemetry information;

[0045] The principle for determining the leak location is:

[0046] The gas temperature at the leak location is lower than the air temperature in the sealed cabin;

[0047] The pressure at the leak location is lower than the pressure in the sealed cabin;

[0048] The leak hole continuously produces a sound signal of a specific frequency;

[0049] If the leak is caused by impact, a vibration signal will be generated at the leak position when the impact occurs.

[0050] (4) The manned spacecraft platform calculates the time required for on-orbit fault handling based on the leakage fault handling operation information preset in the sealed cabin where the leak hole is located; the leakage fault handling operation information includes the division of operation areas in the sealed cabin of the aircraft, the equipment to be operated in each operation area and the operation sequence, and the specific operation information required for each equipment;

[0051] (5) During the on-orbit personnel handling process, the manned spacecraft platform optimizes the on-orbit gas resource supply strategy based on the total pressure of the sealed cabins in each spacecraft of the spacecraft assembly, the pressure drop rate parameters, and the on-orbit gas resource remaining parameters, with the longest operation support time as the control target, and obtains the optimal cabin pressure control point and its corresponding longest operation support time. The cabin pressure control point is introduced as the expected cabin pressure into the closed-loop control of cabin pressure maintenance, and the cabin pressure maintenance gas supply control is performed;

[0052] (6) If the longest operation support time corresponding to the optimal cabin pressure control point is less than the time required for on-orbit fault handling, an evacuation decision is made; otherwise, an on-orbit fault handling decision is made, and the on-orbit personnel are prompted to manually complete the on-orbit leak plugging operation through the head-mounted display device;

[0053] (7) When the time required for on-orbit fault handling has arrived, the manned spacecraft platform determines whether the leak has been plugged based on the pressure drop rate. If the on-orbit leak has not been plugged, it will independently decide on the evacuation time of the on-orbit personnel and send telemetry information to the ground support personnel and on-orbit personnel to warn the ground and on-orbit personnel in advance, prompting the ground personnel to initiate the emergency evacuation support procedure to ensure the safety of the personnel. If the leak has been plugged, it will make a decision to restore the pressure of the sealed cabin based on the remaining amount of on-orbit gas resources, and prompt the personnel through the head-mounted display device to manually complete the operation of restoring the pressure of the sealed cabin.

[0054] The health status of the on-orbit personnel includes: heart rate, blood oxygen, respiratory rate, movement speed, and reaction speed.

[0055] Steps of Ground Support System:

[0056] The severity of leakage in the spacecraft assembly is judged through telemetry parameters such as total pressure in the sealed cabin and pressure drop rate. The impact on the health of on-orbit personnel and the function of manned spacecraft is independently assessed and pushed to ground support personnel.

[0057] Compare the flight status of the spacecraft before and after the leakage failure occurs to determine the lost or degraded functions of the spacecraft, and find out the impact of the lost or degraded functions of the spacecraft on the on-orbit fault handling, and push it to the ground support personnel;

[0058] Based on the progress of on-orbit operations, the health status of on-orbit personnel and the sustainable time of on-orbit gas resources, a decision on whether to carry out an emergency evacuation is made and sent to the manned spacecraft via remote control commands.

[0059] The method by which the ground support system makes decisions on emergency evacuation is:

[0060] Monitor the health status of on-orbit personnel in real time and evaluate their operational capabilities. If it is determined that the health status of on-orbit personnel cannot guarantee that they can complete on-orbit fault handling operations within the time that on-orbit gas resources can maintain, make a decision to execute emergency evacuation.

[0061] After the manned spacecraft platform receives the decision to evacuate urgently, it immediately warns the on-orbit personnel and prompts them to initiate the emergency evacuation support procedure.

[0062] The on-orbit personnel can also carry out fault handling with the support of the ground. The ground support personnel monitor the status of the manned spacecraft platform and the physical condition of the on-orbit personnel in real time, and provide guidance to the on-orbit personnel through the support of space-ground communication.

[0063] According to one aspect of the present invention, the on-orbit personnel operation support equipment can provide protection under low total pressure conditions in the sealed cabin, isolate the on-orbit personnel from the low-pressure environment after the sealed cabin leaks, and ensure the safety of the on-orbit personnel during the operation. In addition, the operation support equipment is equipped with personnel health status monitoring sensors to monitor the physical parameters of the personnel during the on-orbit operation, and estimate the operation ability of each on-orbit personnel based on the measured parameters, and push them to the ground support personnel for decision support.

[0064] In addition, the operation support equipment has the functions of ground-to-space communication and operation information display. During the operation, it dynamically prompts the on-orbit operation steps through the display screen, categorizes and displays the uplink data information of the ground support personnel, and maintains voice communication with the ground support personnel.

[0065] According to one aspect of the present invention, in the step e, the spacecraft platform collects in real time the total pressure of the sealed cabin, the pressure drop rate parameters and the remaining quantity parameters of the on-orbit gas cylinder resources in each aircraft through the control computer, completes the comparative analysis of the operation support time after the cabin pressure maintenance and gas supply control is implemented on multiple control points, and independently decides on the cabin pressure control point with the longest operation support time, introduces it into the closed-loop control of cabin pressure maintenance, and realizes the efficient use of on-orbit gas resources.

[0066] like Figure 2As shown, the present invention provides a pressure emergency fault handling decision support system for realizing pressure emergency fault handling decision of a manned spacecraft assembly, comprising:

[0067] The basic information module includes the normal on-orbit operation status of each vehicle in the manned spacecraft assembly, the division of operating areas in the sealed cabin of each vehicle, the equipment to be operated in each operating area and the operating sequence, the specific operating information required for each device, and the physical condition information of on-orbit personnel; among which the normal on-orbit operation status of the vehicle and the physical condition of the on-orbit personnel are independently determined by the system based on real-time collected data, the division of operating areas in the sealed cabin, the equipment to be operated in each operating area and the operating sequence are preset, and the specific operating information required for each device supports dynamic display by virtual reality devices.

[0068] The flight monitoring module is used to complete real-time monitoring of space debris impacts, sealed cabin leakage, loss of spacecraft function, and the status of on-orbit personnel during the in-orbit flight of a manned spacecraft, and to issue alarm prompts for pressure emergency failures.

[0069] The fault handling module is used to determine the location of the leak when a pressure emergency fault occurs, provide the required operational information for the leak area, determine the time required for on-orbit fault handling, and make autonomous decisions to maximize the use of on-orbit gas resources. The module monitors the physical condition of on-orbit personnel during operation, estimates the operating ability of each on-orbit personnel based on the measured parameters, and provides decision support on whether emergency evacuation is required after comprehensively analyzing the progress of on-orbit operations, the physical condition of personnel, and the sustainable time of on-orbit gas resources.

[0070] According to a scheme of the present invention, when a pressure emergency fault occurs in a manned spacecraft assembly, the on-orbit operation support time required for the ground to make a fault handling decision, whether the leakage is repairable, and the specific issues of how to implement the on-orbit operation are comprehensively considered. On this basis, the various information required for the fault handling decision is matched with the real-time telemetry data, and the required fault handling decision information is automatically prompted by the telemetry value at the time of the fault occurrence. It can support the ground support personnel to carry out fault handling decisions in the shortest time, and gain the most time for the personnel to operate on the orbit, realizing the maximum operation ability of the on-orbit personnel and the maximum support ability of the ground. In addition, the scheme of the present invention is simple, easy to implement, fast and convenient to operate, and can support the handling decision when a pressure emergency fault occurs at any time during the long-term on-orbit operation of a manned spacecraft.

[0071] According to one solution of the present invention, each module in the manned spacecraft assembly pressure emergency fault handling decision system has a clear division of labor, the system layout is simple and clear, and the emergency major fault handling decision efficiency for pressure emergency is high.

[0072] The manned spacecraft pressure emergency fault handling decision system according to the present invention has a simple and clear layout, is accurate in judging the manned spacecraft pressure emergency fault, and has high handling decision efficiency.

[0073] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

[0074] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A decision-making method for handling leakage failure of a sealed cabin of a manned spacecraft assembly, characterized in that: After detecting a leak in the sealed compartment of the spacecraft assembly, the spacecraft platform performs the following steps: (1) Send the measured values ​​of the total pressure and pressure drop rate of the sealed cabin to the ground flight control support system through telemetry data; (2) Based on the measured values ​​of the total pressure and pressure drop rate of the sealed cabin of the manned spacecraft assembly, determine the severity of the leakage fault and the impact of the leakage fault of the spacecraft assembly on the health status of the on-orbit personnel, monitor the health status of the on-orbit personnel in real time, make a decision on whether to wear protective equipment, and push it to the on-orbit personnel; (3) The manned spacecraft platform obtains the measurement data of the acoustic sensors, vibration sensors, pressure sensors, and temperature sensors installed in each spacecraft and each compartment of the manned spacecraft assembly, determines the area and quadrant where the leak is located, prompts the on-orbit personnel to locate the location of the leak, and sends the location information of the leak to the ground flight control support system through telemetry information; (4) The manned spacecraft platform calculates the time required for on-orbit fault handling based on the leakage fault handling operation information preset in the sealed cabin where the leak hole is located; the leakage fault handling operation information includes the division of operation areas in the sealed cabin of the aircraft, the equipment to be operated in each operation area and the operation sequence, and the specific operation information required for each equipment; (5) The manned spacecraft platform optimizes the on-orbit gas resource supply strategy based on the total pressure of the sealed cabins in each spacecraft of the spacecraft assembly, the pressure drop rate parameters, and the remaining amount of on-orbit gas resources parameters, with the longest operation support time as the control target, and obtains the optimal cabin pressure control point and its corresponding longest operation support time. The cabin pressure control point is introduced into the closed-loop control of cabin pressure maintenance as the expected cabin pressure, and the air supply control for cabin pressure maintenance is performed; (6) If the longest operation support time corresponding to the optimal cabin pressure control point is less than the time required for on-orbit fault handling, an evacuation decision is made; otherwise, an on-orbit fault handling decision is made, and the on-orbit personnel are prompted to manually complete the on-orbit leak plugging operation through the head-mounted display device; (7) When the time required for on-orbit fault handling has arrived, the manned spacecraft platform determines whether the leak has been plugged based on the pressure drop rate. If the leak has not been plugged, it will independently decide on the evacuation time of the on-orbit personnel and send telemetry information to the ground support personnel and on-orbit personnel to warn them in advance and prompt them to initiate the emergency evacuation support procedure. If the leak has been plugged, it will make a decision to restore the pressure of the sealed cabin based on the remaining amount of gas resources on orbit.

2. A method for handling leakage failure of a sealed cabin of a manned spacecraft assembly according to claim 1, characterized in that: The severity levels of leakage failures are from high to low: Level 1, Level 2, and Level 3. Level 1 means that personnel cannot survive and equipment cannot work; Level 2 means that personnel cannot survive but equipment can work normally; Level 3 means that personnel are normal and equipment works normally.

3. The method for handling leakage failure of a sealed cabin of a manned spacecraft assembly according to claim 1, characterized in that: The health status of the on-orbit personnel includes: heart rate, blood oxygen, respiratory rate, movement speed, and reaction speed.

4. A method for handling leakage failure of a sealed cabin of a manned spacecraft assembly according to claim 1, characterized in that: The principle for determining the leak location is: The gas temperature at the leak location is lower than the air temperature in the sealed cabin; The pressure at the leak location is lower than the pressure in the sealed cabin; The leak hole continuously produces a sound signal of a specific frequency; If the leak is caused by impact, a vibration signal will be generated at the leak position when the impact occurs.

5. The method for handling leakage failure of a sealed cabin of a manned spacecraft assembly according to claim 1, characterized in that: Also included are steps for ground support systems: The severity of leakage hazards in spacecraft assemblies is determined through telemetry parameters, and the impact on the health of on-orbit personnel and the functions of manned spacecraft are independently assessed, and the results are pushed to ground support personnel. Compare the flight status of the spacecraft before and after the leakage failure occurs to determine the lost or degraded functions of the spacecraft, and find out the impact of the lost or degraded functions of the spacecraft on the on-orbit fault handling, and push it to the ground support personnel; Based on the progress of on-orbit operations, the health status of on-orbit personnel and the sustainable time of on-orbit gas resources, a decision on whether to carry out an emergency evacuation is made and sent to the manned spacecraft via remote control commands.

6. A method for handling leakage failure of a sealed cabin of a manned spacecraft assembly according to claim 5, characterized in that: After the manned spacecraft platform receives the decision to evacuate urgently, it immediately warns the on-orbit personnel and prompts them to initiate the emergency evacuation support procedure.

7. A method for handling leakage failure of a sealed cabin of a manned spacecraft assembly according to claim 1, characterized in that: The method by which the ground support system makes decisions on emergency evacuation is: Monitor the health status of on-orbit personnel in real time and evaluate their operational capabilities. If it is determined that the health status of on-orbit personnel cannot guarantee that they can complete on-orbit fault handling operations within the time that on-orbit gas resources can maintain, make a decision to execute emergency evacuation.

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