Manned spacecraft in-orbit health state assessment method

Abstract

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.

Description

Technical Field

[0001] The present invention relates to the technical field of overall design of spacecrafts, and particularly to a method for evaluating the on-orbit health state of a manned spacecraft. Background Art

[0002] Evaluating the on-orbit health state is an important task for the long-term operation management of manned spacecrafts, and is of great significance for ensuring the long-life, high-reliability, safe and stable operation of manned spacecrafts. There are mutual couplings between key systems of manned spacecrafts. In order to improve the reliability of manned spacecrafts during system design, a large number of redundant fault-tolerant technologies are applied, which further deepen the system complexity, making the on-orbit anomalies that occur often be the fault phenomena after multiple devices or multiple functional modules inside the devices, increasing the difficulty of fault location. In addition, to meet the needs of space science experiments and technical tests, manned spacecrafts need to support longer-term on-orbit stays of personnel to complete on-orbit tasks. The increase in the on-orbit time of manned spacecrafts is accompanied by changes in the on-orbit health state.

[0003] With the increase in the on-orbit operation time of manned spacecrafts, the complexity of the spacecrafts themselves increases, resulting in many difficult problems that need to be solved in the evaluation of the on-orbit health state of manned spacecrafts:

[0004] (1) There are many devices that make up the manned spacecraft. The spacecraft itself has the characteristic of high redundancy. After multiple spacecrafts form a combined body in orbit, it constitutes functional redundancy at the vehicle level. How to accurately evaluate the functional characteristics at different stages in the health state evaluation is a difficult point;

[0005] (2) During the on-orbit operation of manned spacecrafts, special tasks such as rendezvous and docking and extravehicular activities need to be performed. The execution of the tasks is closely related to the on-orbit state of the platform devices, and has multiple couplings and time-varying characteristics. It is necessary to evaluate the current spacecraft state before the execution of the special tasks to reflect the exact relationship between the special tasks and the platform devices. Summary of the Invention

[0006] The technical problem solved by the present invention is: overcoming the deficiencies of the prior art, and proposing a method for evaluating the on-orbit health state of a manned spacecraft, which solves the problem of evaluating the on-orbit health state for different tasks during the long-term on-orbit operation of the manned spacecraft.

[0007] The solution of the present invention to solve the technical problem is: a method for evaluating the on-orbit health state of a manned spacecraft, the method comprising:

[0008] In-orbit status assessment of manned spacecraft: According to the evolution characteristics of telemetry parameters representing the functional indicators of the manned spacecraft, assess the in-orbit status of key equipment of the manned spacecraft; by comparing the changes in telemetry parameters representing the functional indicators of the manned spacecraft over time, whether the in-orbit status of key equipment of the manned spacecraft is stable, and assess whether the in-orbit status of the manned spacecraft is normal;

[0009] Technical ability assessment of manned spacecraft: Before the manned spacecraft performs key in-orbit tasks, assess the airtight function, attitude control function, orbit control function, docking function of the cabin, as well as whether the robotic arm and pressure relief and recompression equipment related to the execution of key tasks are normal, so as to assess whether the manned spacecraft has the technical ability to perform key tasks;

[0010] Assessment of mission execution of manned spacecraft: For key in-orbit tasks during the in-orbit operation of the manned spacecraft, conduct an assessment of mission execution to obtain the execution results of key in-orbit tasks of the manned spacecraft;

[0011] Reliability and safety assessment: Assess the in-orbit safety, reliability, maintainability and lifespan of the manned spacecraft, and identify possible internal and external risks during long-term in-orbit operation;

[0012] Assessment of support conditions: Assess whether the support conditions of the ground flight control team during the execution of the flight control task of the manned spacecraft meet the requirements of the flight control task.

[0013] Preferably, the method for assessing the airtight function of the cabin is as follows:

[0014] Before the execution of the extravehicular activity task of the astronaut, use the telemetry parameter of the total pressure of the sealed cabin to assess whether the airtight function of the cabin is normal; specifically: if the peak change amount of the total pressure of the sealed cabin within one month before the execution of the extravehicular activity task of the astronaut is less than 1%, the airtight function of the manned spacecraft cabin is normal.

[0015] Preferably, the assessment method of the pressure relief and recompression equipment is as follows:

[0016] Use the telemetry parameter of the working state of the pressure relief and recompression equipment to assess whether the pressure relief and recompression equipment is normal. If both the primary and backup of the pressure relief and recompression equipment work normally, the pressure relief and recompression function is normal, otherwise it is abnormal.

[0017] Preferably, the assessment method of the robotic arm is as follows:

[0018] Before the execution of the extravehicular activity task of the payload, use the telemetry parameter of the robotic arm to assess whether the robotic arm is normal; specifically: if all the telemetry parameters of the robotic arm are normal, it is considered that the robotic arm works normally, otherwise it is considered that the robotic arm works abnormally.

[0019] Preferably, the key on-orbit tasks include: orbit maintenance, extravehicular activities of astronauts, extravehicular activities of payloads, rendezvous and docking of visiting spacecraft, and separation of visiting spacecraft.

[0020] Preferably, for the extravehicular activities of astronauts, use the ground statistical data on the execution time of a single mission to evaluate whether the mission design process meets the requirements; use the telemetry parameters of the astronaut voice data downlink to evaluate whether the voice support function meets the requirements; use the telemetry parameters of the extravehicular operation point equipment of the astronaut to evaluate whether the completion of the extravehicular mission meets the requirements; use the telemetry parameters of the attitude angle and attitude angular velocity of the manned spacecraft during the extravehicular activities of astronauts to evaluate whether the spacecraft attitude control meets the design requirements; if the deviation between the actual execution time of the mission and the designed time is less than 30 minutes, there is no interruption in the voice during the whole process of mission execution, the extravehicular operation point equipment works normally after the mission execution, and the attitude angle and attitude angular velocity of the spacecraft are within the designed range during the whole process of mission execution, then the execution of the extravehicular activities of astronauts is normal, otherwise the execution of the extravehicular activities of astronauts is abnormal.

[0021] Preferably, the on-orbit state of the manned spacecraft includes the total pressure of the sealed cabin, the oxygen partial pressure of the sealed cabin, the carbon dioxide partial pressure of the sealed cabin, and the humidity inside the sealed cabin.

[0022] Preferably, for the total pressure of the sealed cabin, use the pressure telemetry parameters of the gas storage equipment and the switch state telemetry parameters of the gas supply control component to evaluate whether the working performance of the total pressure control equipment meets the requirements; use the monthly average change amount of the total pressure telemetry parameter inside the sealed cabin to evaluate whether the total pressure control function is stable; use the telemetry parameters of the working states of the main and backup hosts of the total pressure control computer to evaluate whether there is a situation deviating from the designed state; specifically: if the pressure telemetry parameter of the gas storage equipment is higher than the safety threshold and the gas supply control components are all in the open state, then the working performance of the total pressure control equipment is normal, otherwise it is abnormal; if the monthly average change amount of the total pressure telemetry parameter of the sealed cabin is less than 1%, then the total pressure control function works stably, otherwise it is unstable;

[0023] If the total pressure control computer has always been in the main working state, then there is no design deviation; if the working performance of the total pressure control equipment is normal, the total pressure control function works stably and there is no design deviation, then the evaluation result of the total pressure of the sealed cabin is normal, otherwise it is considered that the total pressure of the sealed cabin is abnormal.

[0024] Preferably, for the carbon dioxide partial pressure in the sealed cabin, the monthly average change of the telemetry parameter of the carbon dioxide partial pressure in the sealed cabin is used to evaluate whether the carbon dioxide partial pressure control function works stably; the matching situation between the telemetry parameter of the carbon dioxide partial pressure and the activity time period of the astronaut observed through the image is used to judge whether the working performance of the carbon dioxide control equipment is normal; if the monthly average change of the peak value of the carbon dioxide partial pressure is less than 5%, the evaluation result of the carbon dioxide partial pressure control function is stable, otherwise it is unstable; if the carbon dioxide partial pressure shows an upward trend during the astronaut's activity period and the increase does not exceed 5%, and shows a downward trend during the astronaut's rest period, the working performance of the carbon dioxide control equipment is normal, otherwise it is abnormal.

[0025] Preferably, for the humidity in the sealed cabin, the daily average change of the telemetry parameter of the humidity in the sealed cabin is used to evaluate whether the humidity control function works stably; the matching situation between the telemetry parameter of the humidity and the exercise time period of the astronaut observed through the image is used to judge whether the working performance of the humidity control equipment is normal; specifically: if the daily average change of the peak value of the humidity is less than 5%, the evaluation result of the humidity control function is stable, otherwise it is unstable;

[0026] If the humidity shows an upward trend during the astronaut's exercise period and a downward trend after the astronaut's exercise ends, the working performance of the humidity control equipment is normal, otherwise it is abnormal.

[0027] The beneficial effects of the present invention compared with the prior art are as follows:

[0028] (1) By evaluating the on-orbit state, technical capabilities, and mission execution of the manned spacecraft, the present invention realizes the evaluation of long-term on-orbit operation tasks and the implementation results of key tasks. Compared with the prior art method of state evaluation based on the normal working state of equipment, on the premise of meeting the evaluation requirements, it can consider the health state under the condition of dynamic reconstruction of various functions of the manned spacecraft, ensuring the accuracy of the evaluation results.

[0029] (2) By combining the on-orbit state, key mission execution, and technical capabilities of the manned spacecraft, the present invention realizes the linkage between the health assessment results and the key missions and technical capabilities of the manned spacecraft. Compared with the prior art that only analyzes the impact on subsequent missions based on the evaluation results, on the premise of meeting the requirements of the manned spacecraft operation mission, by changing the function recovery level after combining the key missions and technical capabilities of the manned spacecraft, the mission execution ability of the manned spacecraft is continuously ensured. Description of the Drawings

[0030] To more clearly illustrate the technical solutions in the embodiments of the present invention or in the prior art, the following will briefly introduce the drawings required in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0031] Figure 1 Schematically shows a working diagram of the on-orbit health status assessment of a manned spacecraft according to the present invention. Detailed implementation manners

[0032] The following further elaborates on the present invention in combination with embodiments.

[0033] The description of the implementation manners of this specification should be combined with the corresponding drawings, and the drawings should be part of the complete specification. In the drawings, the shape or thickness of the embodiments can be enlarged and simplified or conveniently marked. Furthermore, each part of the structure in the drawings will be described separately. It should be noted that the elements not shown or not described in words in the drawings are in the forms known to those of ordinary skill in the art.

[0034] Any reference to directions and orientations in the description of the embodiments herein is only for convenience of description and should not be construed as any limitation on the protection scope of the present invention. The following description of the preferred embodiments involves combinations of features, which may exist independently or in combination. The present invention is not particularly limited to the preferred embodiments. The scope of the present invention is defined by the claims.

[0035] Figure 1 Schematically shows a working diagram of the on-orbit health status assessment of a manned spacecraft according to the present invention. As Figure 1 shown, the method for on-orbit health status assessment of a manned spacecraft according to the present invention includes the following aspects:

[0036] a. Determine the assessment purpose. Determine the assessment purpose according to the on-orbit flight mission of the manned spacecraft. Generally, for a manned spacecraft operating in orbit for a long time, it is necessary to carry out health status assessment for the safe and stable operation, efficient operation management and on-orbit application development of the manned spacecraft;

[0037] b. Determine the assessment entities. The health assessment is carried out at different levels, covering the overall manned spacecraft and each subsystem. The assessment entities are the system-level research and development units and the research and development units of each subsystem respectively;

[0038] c. Formulate the assessment procedure. Specify the procedure for the on-orbit health status assessment of the manned spacecraft, including all process work items from planning, implementation, implementation to continuous improvement, and form an on-orbit health status assessment procedure document for the manned spacecraft;

[0039] When carrying out the evaluation planning, in combination with the characteristics of the manned spacecraft mission, an evaluation working group is established to clarify the specific personnel and the corresponding evaluation items. Adopt a method combining regular evaluation, dynamic evaluation and special mission evaluation, and carry out the evaluation work systematically and continuously in stages. In the evaluation planning, clarify the specific items of regular evaluation, the evaluation interval, the evaluation content of dynamic evaluation, the implementation timing of special mission evaluation and the degree of association with the mission.

[0040] During the evaluation implementation, for the long-term in-orbit operation of the manned spacecraft, evaluations are carried out in the forms of daily evaluation, weekly evaluation, monthly evaluation, quarterly evaluation and annual evaluation; when the manned spacecraft executes special missions, mission evaluations are carried out in combination with the mission implementation timing; when there are major changes in the in-orbit state of the manned spacecraft, stage evaluations are carried out.

[0041] The content for implementing the evaluation results includes aspects such as in-orbit missions, ground development, working systems and specifications, and ground support capabilities. Finally, an evaluation report and evaluation conclusions are formed to clarify whether the manned spacecraft can support the implementation of subsequent missions, and improvement opinions and suggestions are put forward.

[0042] d. Determine the evaluation content, including the in-orbit state of the manned spacecraft, technical capability evaluation, mission execution situation evaluation, reliability and safety evaluation, and support condition evaluation.

[0043] Evaluation of the in-orbit state of the manned spacecraft: According to the evolution characteristics of the telemetry parameters representing the functional indicators of the manned spacecraft, evaluate the in-orbit state of the key equipment of the manned spacecraft; by comparing the changes in the telemetry parameters representing the functional indicators of the manned spacecraft over time, evaluate whether the in-orbit state of the manned spacecraft is normal by checking whether the in-orbit state of the key equipment of the manned spacecraft is stable.

[0044] Evaluation of the technical capabilities of the manned spacecraft: Before the manned spacecraft executes key in-orbit missions, evaluate the functions of the cabin seal, attitude control, orbit control, docking, as well as the manipulator and pressure relief and pressure recovery equipment related to the execution of key missions to determine whether the manned spacecraft has the technical capabilities to execute key missions.

[0045] Evaluation of the mission execution situation of the manned spacecraft: For the key in-orbit missions during the in-orbit operation of the manned spacecraft, carry out an evaluation of the mission execution situation to obtain the execution results of the key in-orbit missions of the manned spacecraft.

[0046] The content of reliability and safety assessment includes evaluating the in-orbit safety, reliability, maintainability and lifespan of manned spacecraft, identifying potential internal and external risks during long-term in-orbit operation, as well as risks for the reliable operation of key functions such as energy, control and propulsion, manned environment, and thermal management. Combining means such as simulation analysis and dynamic prediction, lifespan prediction and assessment are carried out, and improvement suggestions are put forward for the development of subsequent mission products, in-orbit maintenance and upgrade, and related work on long-term safe operation.

[0047] The content of support condition assessment includes whether the support conditions of the ground flight control team during the execution of the manned spacecraft flight control mission meet the requirements of the flight control mission, specifically including aspects such as the ground support system, simulation verification system, and mission planning system.

[0048] (1) In-orbit status assessment of manned spacecraft

[0049] The in-orbit status of manned spacecraft includes the total pressure of the sealed cabin, the oxygen partial pressure of the sealed cabin, the carbon dioxide partial pressure of the sealed cabin, and the humidity inside the sealed cabin.

[0050] For the total pressure of the sealed cabin, using the pressure telemetry parameters of the gas storage equipment and the switch status telemetry parameters of the gas supply control component, evaluate whether the working performance of the total pressure control equipment meets the requirements; using the monthly average change of the total pressure telemetry parameters inside the sealed cabin, evaluate whether the total pressure control function is stable; using the telemetry parameters of the working status of the main and backup units of the total pressure control computer, evaluate whether there is a situation deviating from the design status; specifically: if the pressure telemetry parameter of the gas storage equipment is higher than the safety threshold and the gas supply control components are all in the open state, the working performance of the total pressure control equipment is normal, otherwise it is abnormal; if the monthly average change of the total pressure telemetry parameters of the sealed cabin is less than 1%, the total pressure control function works stably, otherwise it is unstable;

[0051] If the total pressure control computer has always been in the main unit working state, there is no design deviation; if the working performance of the total pressure control equipment is normal, the total pressure control function works stably and there is no design deviation, the assessment result of the total pressure of the sealed cabin is normal, otherwise it is considered that the total pressure of the sealed cabin is abnormal.

[0052] For the oxygen partial pressure of the sealed cabin, using the pressure telemetry parameters of the oxygen storage equipment and the switch status telemetry parameters of the gas supply control component, evaluate whether the working performance of the oxygen partial pressure control equipment meets the requirements; using the monthly average change of the oxygen partial pressure telemetry parameters inside the sealed cabin, evaluate whether the oxygen partial pressure control function is stable; using the telemetry parameters of the working status of the main and backup units of the oxygen partial pressure control computer, evaluate whether there is a situation deviating from the design status; specifically: if the emergency pressure telemetry parameter of the oxygen storage equipment is higher than the safety threshold and the gas supply control components are all in the open state, the working performance of the oxygen partial pressure control equipment is normal, otherwise it is abnormal; if the monthly average change of the oxygen partial pressure telemetry parameters of the sealed cabin is less than 1%, the oxygen partial pressure control function works stably, otherwise it is unstable;

[0053] If the oxygen partial pressure control computer has been in the primary working state all the time, there is no design deviation. If the oxygen partial pressure control equipment has normal working performance, the oxygen partial pressure control function works stably and there is no design deviation, the evaluation result of the oxygen partial pressure in the sealed cabin is normal; otherwise, it is abnormal.

[0054] For the carbon dioxide partial pressure in the sealed cabin, use the monthly average change of the telemetry parameters of the carbon dioxide partial pressure in the sealed cabin to evaluate whether the carbon dioxide partial pressure control function works stably; use the matching situation between the telemetry parameters of the carbon dioxide partial pressure and the activity time period of the astronauts observed through images to judge whether the working performance of the carbon dioxide control equipment is normal; if the monthly average change of the peak value of the carbon dioxide partial pressure is less than 5%, the evaluation result of the carbon dioxide partial pressure control function is that it works stably; otherwise, it works unstably; if the carbon dioxide partial pressure shows an upward trend during the activity period of the astronauts and the increase does not exceed 5%, and shows a downward trend during the rest period of the astronauts, the working performance of the carbon dioxide partial pressure control equipment is normal; otherwise, it is abnormal.

[0055] For the humidity in the sealed cabin, use the daily average change of the telemetry parameters of the humidity in the sealed cabin to evaluate whether the humidity control function works stably; use the matching situation between the telemetry parameters of the humidity and the exercise time period of the astronauts observed through images to judge whether the working performance of the humidity control equipment is normal; specifically: if the daily average change of the peak value of the humidity is less than 5%, the evaluation result of the humidity control function is that it works stably; otherwise, it is unstable;

[0056] If the humidity shows an upward trend during the exercise period of the astronauts and shows a downward trend after the exercise of the astronauts ends, the working performance of the humidity control equipment is normal; otherwise, it is abnormal.

[0057] (2) Evaluation of the technical capabilities of manned spacecraft

[0058] The technical capabilities of manned spacecraft include: cabin sealing function, attitude control function, orbit control function, docking function.

[0059] The evaluation method of the cabin sealing function is as follows:

[0060] Before the execution of the extravehicular activity task of the astronauts, use the telemetry parameters of the total pressure of the sealed cabin to evaluate whether the cabin sealing function is normal; specifically: if the peak change of the total pressure of the sealed cabin within one month before the execution of the extravehicular activity task of the astronauts is less than 1%, the cabin sealing function of the manned spacecraft is normal.

[0061] The evaluation method of the attitude control function is as follows:

[0062] Before the execution of the visiting spacecraft separation mission, use the telemetry parameters of the attitude control equipment to evaluate whether the attitude control function is normal. Specifically: if all the telemetry parameters of the attitude control equipment are normal, then the attitude control function is normal; otherwise, the attitude control function is abnormal.

[0063] The method for evaluating the orbit control function is as follows:

[0064] Before the execution of the orbit maintenance mission, use the telemetry parameters of the working states of the host and standby computers of the orbit control computer to determine the available quantities of the host and standby computers, and evaluate whether the orbit control function is normal. Specifically: if the available quantities of the host and standby computers of the orbit control computer are greater than or equal to 2, then it is considered that the orbit control function is normal; otherwise, it is considered that the orbit control function of the manned spacecraft is abnormal.

[0065] The evaluation of the docking function is as follows:

[0066] Before the execution of the visiting spacecraft rendezvous and docking mission, use the telemetry parameters of the working state of the docking mechanism equipment to evaluate whether the docking function is normal. Specifically: if all the telemetry parameters of the docking mechanism are normal, then it is considered that the docking function is normal; otherwise, it is considered that the docking function is abnormal.

[0067] The evaluation method of the pressure relief and repressurization equipment is as follows:

[0068] Use the telemetry parameters of the working state of the pressure relief and repressurization equipment to evaluate whether the pressure relief and repressurization equipment is normal. If both the primary and backup of the pressure relief and repressurization equipment are working properly, then the pressure relief and repressurization function is normal; otherwise, it is abnormal.

[0069] The evaluation method of the robotic arm is as follows:

[0070] Before the execution of the payload extravehicular activity mission, use the telemetry parameters of the robotic arm to evaluate whether the robotic arm is normal. Specifically: if all the telemetry parameters of the robotic arm are normal, then it is considered that the robotic arm is working properly; otherwise, it is considered that the robotic arm is working abnormally.

[0071] (3) Evaluation of the execution of the manned spacecraft mission

[0072] The key on-orbit missions include: orbit maintenance, astronaut extravehicular activity, payload extravehicular activity, visiting spacecraft rendezvous and docking, and visiting spacecraft separation.

[0073] For orbit maintenance missions, telemetry parameters such as the engine startup duration, velocity increment, propellant consumption, spacecraft attitude angle, and attitude angular velocity of a manned spacecraft are used to evaluate whether the orbit maintenance mission is normal. Specifically, if during the entire process of executing the orbit maintenance mission, the engine startup duration, spacecraft velocity increment, propellant consumption, spacecraft attitude angle, and attitude angular velocity are all within the design allowable range, then the execution of the orbit maintenance mission is normal; otherwise, it is considered that the execution of the orbit maintenance mission is abnormal.

[0074] For the mission of an astronaut's extravehicular activity, statistical data on the execution time of a single mission on the ground is used to evaluate whether the mission design process meets the requirements; telemetry parameters of the astronaut's voice data downlink are used to evaluate whether the voice support function meets the requirements; telemetry parameters of the equipment at the astronaut's extravehicular operation point are used to evaluate whether the completion of the extravehicular mission meets the requirements; during the astronaut's extravehicular activity mission, telemetry parameters of the manned spacecraft's attitude angle and attitude angular velocity are used to evaluate whether the spacecraft attitude control meets the design requirements; if the deviation between the actual execution time of the mission and the designed time is less than 30 minutes, there is no voice interruption during the entire process of mission execution, the equipment at the extravehicular operation point works normally after the mission is executed, and the spacecraft attitude angle and attitude angular velocity are within the design range during the entire process of mission execution, then the execution of the astronaut's extravehicular activity mission is normal; otherwise, the execution of the astronaut's extravehicular activity mission is abnormal.

[0075] For the mission of a payload's extravehicular activity, telemetry parameters of the payload equipment are used to evaluate whether the payload can work normally during the entire extravehicular mission process; telemetry parameters of the spacecraft's attitude angle and attitude angular velocity during the entire process of mission execution are used to evaluate whether the spacecraft attitude control meets the design requirements; if the payload equipment works normally during the entire mission process and the spacecraft attitude angle and attitude angular velocity are within the design range, then the evaluation result of the payload's extravehicular activity mission is normal; otherwise, the execution of the payload's extravehicular activity mission is abnormal.

[0076] For the mission of a visiting spacecraft's rendezvous and docking, telemetry parameters of the spacecraft's attitude angle and attitude angular velocity during the entire process of mission execution are used to evaluate whether the spacecraft attitude control meets the requirements; telemetry parameters of the total pressure in the sealed cabin during the entire process of mission execution are used to evaluate whether the total pressure control meets the requirements; if the spacecraft attitude angle and attitude angular velocity are within the design range during the entire process of mission execution, and the deviation between the actual change in the total pressure of the sealed cabin and the designed value is less than 5%, then it is considered that the execution of the visiting spacecraft's rendezvous and docking mission is normal; otherwise, it is considered that the execution of the visiting spacecraft's rendezvous and docking mission is abnormal.

[0077] For the visiting vehicle separation mission, the telemetry parameters of the total pressure in the docking channel are used to evaluate whether the pressure relief control of the docking channel meets the requirements; the telemetry parameters of the spacecraft attitude angle and attitude angular velocity during the entire mission execution are used to evaluate whether the spacecraft attitude control meets the requirements. If the deviation between the time when the total pressure in the docking channel drops to the vacuum level and the designed time is less than 5%, and the spacecraft attitude angle and attitude angular velocity are within the designed range during the entire mission execution, the execution of the visiting vehicle separation mission is normal; otherwise, it is considered that the execution of the visiting vehicle rendezvous and docking mission is abnormal.

[0078] (4) Reliability and Safety Assessment of Manned Spacecraft

[0079] The reliability and safety assessment includes: equipment failure state assessment and space environment risk assessment.

[0080] For the equipment failure state assessment, the telemetry parameters of the working state of the manned spacecraft equipment are used to evaluate whether the equipment is working properly. Specifically, if all equipment is in the primary working state and the backup performance is normal, the manned spacecraft is in a fault-free state; otherwise, the manned spacecraft is considered to be in a faulty state.

[0081] For the space environment risk assessment, the ground monitoring results and trend prediction information of the space environment, as well as the telemetry information of the on-orbit personnel's body radiation dose monitoring results, are used to evaluate whether there is a situation where the on-orbit personnel's radiation exceeds the limit. Specifically, based on the telemetry information of the human body radiation dose monitoring results, the allowable radiation dose limit for on-orbit personnel is judged. According to the space environment monitoring results and trend prediction information, the radiation dose within the remaining time is calculated. If the radiation dose within the remaining time does not exceed the radiation limit, it is considered that there is no space environment risk; otherwise, it is considered that there is a space environment risk.

[0082] (5) Support Condition Assessment of Manned Spacecraft

[0083] The support condition assessment includes: on-orbit material support assessment, ground personnel support assessment, and ground system support assessment. For the on-orbit material support, the statistical data of the resource consumption of on-orbit personnel are used to evaluate whether the on-orbit resources meet the requirements of the personnel stay mission. Specifically, the resource consumption and stay time of on-orbit personnel are statistically analyzed to obtain the daily average value of the resource consumption of on-orbit personnel. The remaining on-orbit resources are allocated according to the number of on-orbit personnel and the remaining time of the on-orbit mission. If the allocated value is lower than 1.5 times the statistical daily average value, it is considered that there is a risk of on-orbit material support; otherwise, there is no risk of on-orbit material support.

[0084] For the ground personnel support, the duration information of the ground personnel performing tasks is used to evaluate whether there is a risk of ground personnel support. Specifically, if the average duration of the ground personnel performing tasks is less than 30 days, it is considered that there is a risk of ground personnel support; otherwise, it is considered that there is no risk of ground personnel support.

[0085] For the ground system guarantee, the continuous normal operation duration and fault recovery time of the ground system are used to evaluate whether there is a ground system guarantee risk. Specifically: if the continuous normal working time of the ground system is greater than 180 days and the fault recovery time is less than 5 minutes, it is considered that there is no ground system guarantee risk; otherwise, it is considered that there is a ground system guarantee risk.

[0086] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included in the protection scope of the present invention.

[0087] By adopting a method combining regular evaluation, dynamic evaluation and special task evaluation, mission evaluation, on-orbit status and technical ability evaluation, reliability and safety evaluation, and guarantee condition evaluation are carried out on the manned spacecraft, and an evaluation method for the health status of the manned spacecraft is comprehensively obtained.

[0088] Although the present invention has been disclosed above with preferred embodiments, it is not used to limit the present invention. Any person skilled in the art can 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 decorations 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 method for evaluating the on-orbit health status of a manned spacecraft, characterized in that Including: On-orbit status assessment of manned spacecraft: According to the evolution characteristics of telemetry parameters representing the functional indicators of the manned spacecraft, assess the on-orbit status of key equipment of the manned spacecraft; By comparing the changes in telemetry parameters representing the functional indicators of the manned spacecraft over time, whether the on-orbit status of key equipment of the manned spacecraft is stable, and assess whether the on-orbit status of the manned spacecraft is normal; Technical capability assessment of manned spacecraft: Before the manned spacecraft performs key on-orbit tasks, assess whether the cabin sealing function, attitude control function, orbit control function, docking function, and manipulator and pressure relief and recompression equipment related to the execution of key tasks are normal, so as to assess whether the manned spacecraft has the technical capability to perform key tasks; Assessment of the mission execution of manned spacecraft: For the key on-orbit tasks during the on-orbit operation of the manned spacecraft, conduct an assessment of the mission execution to obtain the execution results of the key on-orbit tasks of the manned spacecraft; Reliability and safety assessment: Assess the on-orbit safety, reliability, maintainability and life of the manned spacecraft, and identify possible internal and external risks during long-term on-orbit operation; Assessment of support conditions: Assess whether the support conditions of the ground flight control team during the execution of the manned spacecraft flight control task meet the requirements of the flight control task.

2. The method for evaluating the on-orbit health status of a manned spacecraft according to claim 1, wherein, The method for assessing the cabin sealing function is as follows: Before the execution of the astronaut extravehicular activity mission, use the total pressure telemetry parameter of the sealed cabin to assess whether the cabin sealing function is normal; specifically: if the peak change amount of the total pressure of the sealed cabin within one month before the execution of the astronaut extravehicular activity mission is less than 1%, the cabin sealing function of the manned spacecraft is normal.

3. A method for evaluating the on-orbit health state of a manned spacecraft according to claim 1, characterized in that, The assessment method for the pressure relief and recompression equipment is as follows: Use the telemetry parameters of the working state of the pressure relief and recompression equipment to assess whether the pressure relief and recompression equipment is normal. If both the primary and backup of the pressure relief and recompression equipment work normally, the pressure relief and recompression function is normal, otherwise it is abnormal.

4. The method for evaluating the on-orbit health state of a manned spacecraft according to claim 1, wherein, The assessment method for the manipulator is as follows: Before the execution of the payload extravehicular activity mission, use the telemetry parameters of the manipulator to assess whether the manipulator is normal; specifically: if all the telemetry parameters of the manipulator are normal, it is considered that the manipulator works normally, otherwise it is considered that the manipulator works abnormally.

5. A method for evaluating the on-orbit health state of a manned spacecraft according to claim 1, characterized in that, The key on-orbit tasks include: orbit maintenance, astronaut extravehicular activity, payload extravehicular activity, rendezvous and docking of visiting spacecraft, and separation of visiting spacecraft.

6. The method for evaluating the on-orbit health state of a manned spacecraft according to claim 5, characterized in that, For the extravehicular activity mission of astronauts, use the ground's statistical data on the execution time of a single mission to evaluate whether the mission design process meets the requirements; use the telemetry parameters of the astronaut voice data transmitted downlink to evaluate whether the voice support function meets the requirements; use the telemetry parameters of the equipment at the extravehicular operation points of the astronauts to evaluate whether the completion of the extravehicular mission meets the requirements; use the telemetry parameters of the attitude angle and attitude angular velocity of the manned spacecraft during the extravehicular activity mission of the astronauts to evaluate whether the spacecraft attitude control meets the design requirements; if the deviation between the actual execution time of the mission and the designed time is less than 30 minutes, there is no interruption in the voice throughout the mission execution, the equipment at the extravehicular operation points works normally after the mission execution, and the attitude angle and attitude angular velocity of the spacecraft are within the designed range throughout the mission execution, then the execution of the extravehicular activity mission of the astronauts is normal, otherwise the execution of the extravehicular activity mission of the astronauts is abnormal.

7. A method for evaluating the on-orbit health status of a manned spacecraft according to claim 2, characterized in that, The on-orbit state of the manned spacecraft includes the total pressure of the sealed cabin, the oxygen partial pressure of the sealed cabin, the carbon dioxide partial pressure of the sealed cabin, and the humidity inside the sealed cabin.

8. A method for evaluating the on-orbit health status of a manned spacecraft according to claim 6, characterized in that, For the total pressure of the sealed cabin, use the pressure telemetry parameters of the gas storage equipment and the switch state telemetry parameters of the gas supply control components to evaluate whether the working performance of the total pressure control equipment meets the requirements; use the monthly average change amount of the total pressure telemetry parameters inside the sealed cabin to evaluate whether the total pressure control function is stable; use the telemetry parameters of the working states of the main and standby computers of the total pressure control computer to evaluate whether there is a situation deviating from the designed state; specifically: if the pressure telemetry parameters of the gas storage equipment are higher than the safety threshold and the gas supply control components are all in the open state, then the working performance of the total pressure control equipment is normal, otherwise it is abnormal; if the monthly average change amount of the total pressure telemetry parameters inside the sealed cabin is less than 1%, then the total pressure control function works stably, otherwise it is unstable; If the total pressure control computer has always been in the main working state, then there is no design deviation; if the working performance of the total pressure control equipment is normal, the total pressure control function works stably, and there is no design deviation, then the evaluation result of the total pressure of the sealed cabin is normal, otherwise it is considered that the total pressure of the sealed cabin is abnormal.

9. The method for evaluating the on-orbit health state of a manned spacecraft according to claim 6, wherein, For the carbon dioxide partial pressure of the sealed cabin, use the monthly average change amount of the carbon dioxide partial pressure telemetry parameters inside the sealed cabin to evaluate whether the carbon dioxide partial pressure control function works stably; use the matching situation between the carbon dioxide partial pressure telemetry parameters and the activity time period of the astronauts observed through images to judge whether the working performance of the carbon dioxide control equipment is normal; if the peak monthly average change amount of the carbon dioxide partial pressure is less than 5%, then the evaluation result of the carbon dioxide partial pressure control function is that it works stably, otherwise it works unstably; if the carbon dioxide partial pressure shows an upward trend during the astronauts' activity period and the increase amount does not exceed 5%, and shows a downward trend during the astronauts' rest period, then the working performance of the carbon dioxide control equipment is normal, otherwise it is abnormal.

10. A method for evaluating the on-orbit health state of a manned spacecraft according to claim 6, characterized in that, For the humidity inside the sealed cabin, the daily average change amount of the humidity telemetry parameters inside the sealed cabin is used to evaluate whether the humidity control function works stably; the matching situation between the humidity telemetry parameters and the exercise time period of the astronauts observed through images is used to judge whether the working performance of the humidity control equipment is normal; specifically: if the daily average change amount of the humidity peak value is less than 5%, the evaluation result of the humidity control function is stable, otherwise it is unstable; If the humidity shows an upward trend during the exercise of the astronauts and a downward trend after the exercise of the astronauts ends, the working performance of the humidity control equipment is normal, otherwise it is abnormal.

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