Manned spacecraft on-orbit state control model and method based on data homology

Abstract

The invention relates to a data homology-based manned spacecraft on-orbit state control model and method, and provides a data homology-based flight state control method for long-term on-orbit operation of a complex large manned spacecraft. The method is mainly used for solving the contradiction between the complex and dynamically changing manned spacecraft on-orbit state and the refined and real-time state management and control requirement, providing a manned spacecraft on-orbit state informatization management and control model architecture, and optimizing the manned spacecraft on-orbit operation management and control efficiency.

Description

Technical Field

[0001] The present invention relates to an on-orbit state control model and method of a manned spacecraft based on data homology, and belongs to the field of overall design of on-orbit operation of spacecraft. Background Art

[0002] In large and complex manned spacecraft missions, the quality of on-orbit status control is directly related to the success or failure of mission implementation. It is necessary to ensure that manned spacecraft are in a safe flight state at all times and to ensure the safety of astronauts on orbit; in the face of a variety of on-orbit missions, it is necessary to fully control the on-orbit state of manned spacecraft, ensure that the state of the assembly before, during and after the mission is safe and controlled, avoid situations caused by inadequate status settings, and ensure the smooth implementation of long-term operation and subsequent missions.

[0003] Compared with satellites and other spacecraft, the management of the on-orbit technical status of manned spacecraft has the following characteristics:

[0004] 1) For manned on-orbit operation, the platform functions and system design are more complex, with multiple states, multiple modes and strong coupling during operation, which requires a more detailed description of the on-orbit state baseline to characterize the on-orbit operation state;

[0005] 2) There are interfaces for uplink and downlink transportation of personnel and cargo, and the on-orbit status is constantly updated with the docking and evacuation of the earth-to-space transportation system. At the same time, astronauts will also exercise their subjective initiative on orbit, so the on-orbit status is not static and requires dynamic management of the status;

[0006] 3) During the on-orbit operation of a manned spacecraft, the states of various major systems are interrelated and coupled, and unified state management methods and tools are required to carry out state management and control work under unified requirements.

[0007] The on-orbit operating status of early manned spacecraft was relatively simple. When monitoring and judging the on-orbit operating status of manned spacecraft, the ground mainly judged the specific telemetry parameters and used the telemetry parameters to characterize whether the working status of the equipment was normal. However, it did not judge whether the equipment was working in the required state at a certain moment or flight stage. At this time, the telemetry parameters may be within the normal range, but the working status has exceeded the required range. Summary of the invention

[0008] The technical problem solved by the present invention is: in view of the problem that the telemetry parameters and flight status involved in the working state of traditional manned spacecraft are difficult to control in the current existing technology, a manned spacecraft on-orbit state control model and method based on data homology are proposed.

[0009] The present invention solves the above technical problems by the following technical solutions:

[0010] A method for controlling the on-orbit state of a manned spacecraft based on data homology, comprising:

[0011] Describe the on-orbit status of the data source according to the status data type of the manned spacecraft;

[0012] Formulate the safety state requirement envelope corresponding to the on-orbit state of each manned spacecraft;

[0013] According to the safety state requirement envelope corresponding to the on-orbit state of each manned spacecraft and the on-orbit state description results of the data source, an information control model is established to control each manned spacecraft in real time;

[0014] Record the on-orbit telemetry data during the real-time control process (record operation) and compare it with the on-orbit state description of the data source, and determine whether the manned spacecraft deviates from the current on-orbit state based on the comparison results;

[0015] If a deviation occurs, the deviation status of the manned spacecraft will be controlled and adjusted, otherwise the manned spacecraft mission will continue to be executed.

[0016] The state data types of the manned spacecraft include telemetry parameter type, material type, and resource type. The method for describing the on-orbit state of the data source is:

[0017] When the status data type is telemetry parameter type, the on-orbit status is described according to the on / off status parameters and working status parameters of the spacecraft equipment, and the telemetry parameter variation range is set;

[0018] When the status data type is material type, the real-time dynamic changes of the on-orbit materials such as spare parts, consumables, and maintenance tools installed and stored on the spacecraft are recorded, and the on-orbit status is described using the location, quantity, and usage information of various on-orbit materials;

[0019] When the status data type is resource type, the real-time changes of the on-orbit resident resources such as on-orbit propellant, gas cylinders, and water of the spacecraft are regularly recorded using telemetry information. A resource consumption model is established based on the regular recording results. The parameters of the resource consumption model are corrected through the on-orbit resident resource data of different spacecraft crews, astronauts with different metabolic levels, and spacecraft missions. The corrected resource consumption model is used to obtain the on-orbit resource status data in real time, and the on-orbit status is described through the on-orbit resource status data.

[0020] The on-orbit status of the manned spacecraft includes the on-orbit status during routine flight and the on-orbit status during special missions;

[0021] In the on-orbit state during routine flight, the manned spacecraft does not perform critical tasks on orbit and operates normally; the operating state parameter range of spacecraft equipment and on-orbit products is used as the safety state requirement envelope;

[0022] When a special mission is in-orbit, the manned spacecraft performs key tasks, identifies the working conditions of the safety risk points in the on-orbit state, and determines the safety status envelope range of the spacecraft equipment and on-orbit products based on the actual working conditions at the time of executing the key mission.

[0023] During routine flight, the operating status parameters of spacecraft equipment and on-orbit products are within the following ranges:

[0024] The data range of the manned spacecraft's assembly configuration information, extravehicular equipment status information, on-orbit status information of the spacecraft's functional systems, hardware status information, software status information, interface status information, and real-time on-orbit resource status data in a safe state;

[0025] When the special mission is on-orbit, the actual working conditions at the critical mission execution time are:

[0026] The manned spacecraft assembly configuration information, robotic arm parking position information, lighting condition information, engine plume condition information, sensor field of view angle information, extravehicular equipment motion envelope information, and the data range in the safe state of the pyrotechnic platform safety prohibition command during the mission.

[0027] The method for the information control model to perform real-time control on each manned spacecraft is as follows:

[0028] Collect the real-time telemetry parameters of each manned spacecraft at the current moment, and compare them with the safety state requirement envelope corresponding to the current on-orbit state of the manned spacecraft. If they are inconsistent, the manned spacecraft will be controlled in real time to deviate from the state. If they are consistent, no processing will be performed;

[0029] Traverse each manned spacecraft until the safety state requirement envelope of all manned spacecraft in the current on-orbit state is consistent with the real-time telemetry parameters of the manned spacecraft.

[0030] When the status data type is telemetry parameter type, the on-orbit telemetry parameters are entered into the information control model to record the on-orbit status (record operation), and the current on-orbit telemetry parameters are judged using the safety status requirement envelope of the on-orbit status during daily flight or the on-orbit status of special tasks. Deviate control or no control is performed based on the judgment result.

[0031] When the status data type is material type, the astronauts' manual operations are recorded, as well as the actual on-orbit status of on-orbit spare parts, consumables, and maintenance tools. These are compared with the safety status requirement envelope of the on-orbit status during routine flight or the on-orbit status of special missions, and deviation control or no control is performed based on the judgment result.

[0032] When the status data type is resource type, the consumption of on-orbit materials is recorded, data analysis is performed on the consumption rates of different resources, and the remaining quantity and support time are estimated; the remaining quantity and support time are compared with the safety status requirement envelope, and deviation control or no control is performed based on the judgment result.

[0033] An information control model for realizing an on-orbit state control method of a manned spacecraft, comprising:

[0034] The information control model includes a flight status requirement module, a flight status record module, a flight status control module, and a basic data module, wherein:

[0035] The flight status requirement module centrally formulates the safety status requirement envelope of the operating status parameters of different manned spacecraft in orbit according to the status data type determined by the basic data module;

[0036] The flight status record module synchronously obtains data related to the status of on-orbit materials, on-orbit telemetry, and on-orbit resources;

[0037] The flight status control module compares the on-orbit related data obtained by the flight status recording module with the safety status requirement envelope formulated by the flight status requirement module, and performs real-time deviation status control or no control based on the comparison results;

[0038] The basic data module analyzes the state data type of the manned spacecraft, describes the on-orbit state of the data source, and associates it with various parameter information of the on-orbit state of the manned spacecraft, and records the phase data generated by the flight state requirement module, the flight state recording module, and the flight state control module.

[0039] When the flight status control module performs real-time deviation status control according to the comparison result, process management is achieved by sending an electronic approval request to the external control system.

[0040] The advantages of the present invention compared with the prior art are:

[0041] (1) The present invention provides a manned spacecraft on-orbit state control model and method based on data homology. Through the on-orbit state control of the manned spacecraft based on the homology of ground and earth data, the problem of timely grasping the complex and changeable on-orbit state of the manned spacecraft on the ground can be solved. According to different state types, a standardized information interface can be established to automatically obtain the real-time on-orbit state, improve the ground work efficiency, and effectively judge whether the on-orbit state of the manned spacecraft is correct and whether it meets the requirements. It can timely judge the state deviation and error, remind the ground personnel to correct the state in time, and ensure the on-orbit safety of the manned spacecraft and astronauts.

[0042] (2) The on-orbit state management method for manned spacecraft proposed in the present invention solves the problem of management and control of the complex and changeable state of manned spacecraft on-orbit. Through on-orbit state management, the on-orbit technical state of the manned spacecraft is controlled and traceable. By formulating on-orbit state setting requirements and recording the on-orbit state, state deviations and anomalies are identified in a timely manner, and disposal measures are formulated in a timely manner. At the same time, through on-orbit state management and control, the on-orbit technical state of the manned spacecraft meets expectations. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1 A flow chart for daily flight status control of a manned spacecraft provided by the present invention;

[0044] Figure 2 Formulate a flow chart for the on-orbit status requirements provided by the present invention;

[0045] Figure 3 A functional schematic diagram of the on-orbit status information model provided by the present invention;

[0046] Figure 4 This is an information flow chart of the on-orbit status control provided by the present invention. DETAILED DESCRIPTION

[0047] A manned spacecraft on-orbit state control model and method based on data homology is proposed for the long-term on-orbit operation of complex and large manned spacecraft. A flight state control method based on data homology is proposed, which is mainly used to resolve the contradiction between the complex and dynamically changing on-orbit state of manned spacecraft and the refined and real-time state control requirements. An informatization control model architecture for the on-orbit state of manned spacecraft is proposed to optimize the on-orbit operation and control efficiency of manned spacecraft.

[0048] The information control model of manned spacecraft on-orbit state control based on data homology includes: flight state requirement module, flight state record module, flight state control module, basic data module, and process control module, among which:

[0049] The flight status requirement module centrally formulates the status parameter setting requirements for the on-orbit status of manned spacecraft;

[0050] The flight status record module obtains the status of on-orbit materials synchronously between the ground and the space;

[0051] The flight status control module compares the status of on-orbit materials according to the itemized description of the flight status requirements. If there is any inconsistency, real-time deviation status control is performed;

[0052] The basic data module associates data with the on-orbit status of each manned spacecraft based on the on-orbit status description of the data source of the manned spacecraft;

[0053] The process control module realizes the process control of the flight status corresponding to the on-orbit status of each manned spacecraft.

[0054] The on-orbit state control method of a manned spacecraft based on data homology includes the following specific steps:

[0055] Describe the on-orbit status of the data source according to the status data type of the manned spacecraft;

[0056] Formulate the state parameter setting requirements corresponding to the on-orbit state of each manned spacecraft;

[0057] According to the state parameter setting requirements corresponding to the on-orbit state of each manned spacecraft and the on-orbit state description results of the data source, an information control model is established for real-time control;

[0058] Record the on-orbit telemetry data during real-time control and compare it with the on-orbit state description of the data source, and judge whether the manned spacecraft deviates from the current on-orbit state based on the comparison results;

[0059] If a deviation occurs, the deviation status of the manned spacecraft will be controlled and adjusted, otherwise the manned spacecraft mission will continue to be executed.

[0060] The state data types of manned spacecraft include telemetry parameter type, material type, and resource type. The on-orbit state of the data source is described as follows:

[0061] When the state data type is telemetry parameter type, the telemetry parameter variation range is set according to the on / off state parameters and working state parameters of the spacecraft equipment, and an information processing database is established;

[0062] When the status data type is material type, the real-time dynamic changes of the on-orbit materials such as spare parts, consumables, and maintenance tools installed and stored on the spacecraft are recorded, and the location, quantity, and usage information of various on-orbit materials are established in an information processing database;

[0063] When the status data type is resource type, the telemetry information is used to regularly record the real-time changes of the on-orbit propellant, gas cylinders, and water resident resources of the spacecraft. A resource consumption model is established based on the regular recording results. The parameters of the resource consumption model are corrected through the on-orbit resident resource data of different spacecraft crews, astronauts with different metabolic levels, and spacecraft missions. The corrected resource consumption model is used to obtain the on-orbit resource status data in real time.

[0064] The on-orbit status of manned spacecraft includes the on-orbit status during routine flight and the on-orbit status for special missions;

[0065] In the on-orbit state during routine flight, the manned spacecraft does not perform critical tasks on orbit and operates normally, and the use status of spacecraft equipment and on-orbit products is within the safety state requirement envelope;

[0066] When a special mission is in-orbit, the manned spacecraft performs key tasks. After identifying the safety risk points in the on-orbit state, the safety state envelope range of the key mission is formulated. During the design stage of each key mission, the usage status parameter range of the spacecraft equipment and on-orbit products is determined according to the actual working conditions at the time of executing the key mission.

[0067] During routine flight, the safety status requirement envelope is:

[0068] The data range of the manned spacecraft's assembly configuration information, extravehicular equipment status information, on-orbit status information of the spacecraft's functional systems, hardware status information, software status information, interface status information, and real-time on-orbit resource status data in a safe state;

[0069] When the special mission is in orbit, the use status parameter range is:

[0070] The manned spacecraft assembly configuration information, robotic arm parking position information, lighting condition information, engine plume condition information, sensor field of view angle information, extravehicular equipment motion envelope information, and the data range in the safe state of the pyrotechnic platform safety prohibition command during the mission.

[0071] The real-time control method of the information control model is:

[0072] According to the on-orbit state description of the data source of the manned spacecraft, data is associated with the on-orbit state of each manned spacecraft, and the parameter types in the requirements are set using the state parameters of the on-orbit states of different manned spacecraft. According to the functional state, hardware state, software state, and resource state, manual input or import of the on-orbit state description of the data source is used to describe the flight state requirements through entry.

[0073] The status of on-orbit materials is obtained synchronously between the ground and the space, and compared with the itemized description of the flight status requirements. If there is any inconsistency, real-time deviation status control is performed until the flight status control corresponding to the on-orbit status of each manned spacecraft is completed.

[0074] The following is further described in conjunction with the accompanying drawings and preferred embodiments of the specification:

[0075] In the current embodiment, if Figure 1 As shown in the figure, the specific means of controlling the on-orbit status of manned spacecraft include:

[0076] Describe the on-orbit status of the data source according to the status data type of the manned spacecraft;

[0077] Formulate the safety state requirement envelope corresponding to the on-orbit state of each manned spacecraft;

[0078] According to the safety state requirement envelope corresponding to the on-orbit state of each manned spacecraft and the on-orbit state description results of the data source, an information control model is established to control each manned spacecraft in real time;

[0079] Record the on-orbit telemetry data during the real-time control process (record operation) and compare it with the on-orbit state description of the data source, and determine whether the manned spacecraft deviates from the current on-orbit state based on the comparison results;

[0080] If a deviation occurs, the deviation status of the manned spacecraft will be controlled and adjusted, otherwise the manned spacecraft mission will continue to be executed.

[0081] Further:

[0082] Part 1: Design a state description method for on-orbit state control of manned spacecraft, mainly including telemetry parameter class, material class, resource class, etc. According to different state data types, determine the data source information interface and establish an information processing database, which is the basis for realizing the informatization of state control.

[0083] Part II: Formulate the flight status setting requirements for manned spacecraft, with the primary principle of ensuring the safe and stable operation of manned spacecraft, and determine the working status requirements of various functions and equipment of manned spacecraft. Targeted status setting requirements, namely relevant envelope design, are formulated for the daily flight of manned spacecraft and the execution of special missions.

[0084] Part 3: For each status setting requirement, specify the status description method and associate it with the data source in the information management and control system. The data source includes on-orbit telemetry parameters, confirmed data in other software databases, etc.; design the normal value range for the daily flight of manned spacecraft and the execution of special missions respectively, realize automatic comparison and interpretation of the status, and draw a conclusion on whether the current on-orbit status meets the status setting requirements.

[0085] (1) Determine the state description method

[0086] According to the design characteristics of manned spacecraft, the description methods used to determine the on-orbit status include:

[0087] 1) Telemetry parameter category: The power on / off status, working mode and other working states of the equipment are all corresponding to different telemetry parameter variation ranges. The telemetry parameters that characterize the working state of the equipment are used to establish an information processing database.

[0088] 2) Materials: including spare parts, consumables, maintenance tools, etc. installed and stored in orbit. The status of these materials cannot be represented by telemetry parameters. At the same time, as astronauts consume, maintain, and perform extravehicular activities on orbit, the on-orbit status of materials changes dynamically in real time. The existing on-orbit material management and control system is used to record the status of materials, including location, quantity, usage, and other information, and to establish an information processing database.

[0089] 3) Resources: including on-orbit propellants, gas cylinders, water and other resources. As astronauts stay in orbit, these resources change in real time, and are regularly recorded and counted using telemetry information and on-orbit material control systems. For manned spacecraft-specific resources such as water, oxygen, and nitrogen that are closely related to the crew, a resource consumption model is established based on the accumulation of on-orbit flight data, and the model parameters are continuously corrected through on-orbit data of different crews, different metabolic levels and missions, so that the on-orbit resource status data can be obtained in real time using a digital model.

[0090] (2) On-orbit status requirements setting

[0091] The on-orbit state requirements of manned spacecraft include daily flight state requirements and special mission state requirements. Daily flight state requirements put forward reasonable and safe setting requirements for the use state of on-orbit products when manned spacecraft is not performing key tasks and is operating normally. Since the external environment such as lighting conditions and assembly configuration during the daily on-orbit flight of manned spacecraft is changeable and the state coupling is strong, when establishing daily flight state requirements, it is generally an envelope of the safety state requirements of various functions of manned spacecraft.

[0092] On-orbit status requirements during routine flight include the following elements:

[0093] 1) Assembly configuration;

[0094] 2) Status of large facilities and equipment outside the cabin;

[0095] 3) System functional status requirements, including on-orbit status requirements for control systems, propulsion systems, energy systems, information systems, thermal management, manned environmental control, etc.;

[0096] 4) Hardware status setting requirements;

[0097] 5) Software status setting requirements;

[0098] 6) Requirements for setting the interface status between systems;

[0099] 7) Requirements for the status of on-orbit materials and resources, including the storage status of on-orbit materials, resource consumption model, and on-orbit life requirements for consumables.

[0100] The special mission status requirements propose the requirements that should be set on orbit during the manned spacecraft's key missions. When proposing the status requirements for special missions, first identify the safety risk points of the on-orbit state and formulate the overall status elements before the mission is implemented, including at least the following elements:

[0101] 1) Assembly configuration;

[0102] 2) Robot arm parking position;

[0103] 3) Lighting conditions;

[0104] 4) Engine plume conditions;

[0105] 5) Sensor field of view;

[0106] 6) Motion envelope of large extravehicular equipment;

[0107] 7) During the mission, it is forbidden to issue instructions related to pyrotechnics and other matters that may affect the safety of the platform.

[0108] Based on this, the safety status envelope range of the special task is formed. During each special task design phase, matching status requirements are selected according to the specific task conditions at that time to form the status requirements for the implementation of a single task.

[0109] (3) Design of information management and control system

[0110] Design an information control system for on-orbit status control. The basic principle is that the data for on-orbit status control should be the same as the on-orbit data. Use on-orbit telemetry data and material and resource data from on-orbit to achieve on-orbit status comparison and control. Design the post-control process as follows: Figure 2 As shown;

[0111] The information management and control system includes five functional modules, namely:

[0112] 1) "Flight Status Requirements" module

[0113] Centrally formulate the on-orbit flight status requirements for manned spacecraft, and describe the flight status requirements in an itemized manner by manual input or database import in accordance with the system function status, hardware working status, software working status, resource status, etc. At the same time, it is necessary to introduce the equipment matching, telemetry parameters and other information in the "basic data" module to define the normal value range of the characteristic parameters that describe the flight status requirements.

[0114] 2) "Flight Status Recording" Module

[0115] According to the characteristic parameters that describe the flight status requirements defined in the "Flight Status Requirements" module, the on-orbit data receiving software is bound to the on-orbit telemetry parameters, the on-orbit material status is obtained through the ground-to-space material synchronization system, and the on-orbit resource documentation or evaluation is obtained through manual entry or model calculation, ensuring that the ground and space data have the same source.

[0116] 3) "Flight status control" module

[0117] The flight status is managed and controlled on a regular basis through real-time comparison of the on-orbit status with the flight status requirements. If the comparison is inconsistent, deviation status control is performed through the process to manage and control changes and optimizations to the flight status requirements.

[0118] 4) "Basic Data" module

[0119] It includes data such as on-orbit equipment support, telemetry parameters, material information, resource information, etc. of manned spacecraft, which are used to associate the characteristic parameters required for flight status with information documenting the flight status.

[0120] 5) “Process Control” Module

[0121] The process used in the flight status control work process.

[0122] The functional relationship between modules is as follows Figure 3 The information flow diagram of the on-orbit status control information system is shown in Figure 4 shown.

[0123] (4) State Automation Recording and Comparison

[0124] The on-orbit telemetry parameters will be entered into the information system to record the on-orbit status. The normal value range of telemetry parameters associated with daily flight status requirements and special mission status requirements will be used for real-time comparison to obtain a conclusion on whether the current on-orbit status meets the status requirements, and deviations will be discovered in a timely manner. The manual operations of astronauts will be recorded to achieve non-parametric on-orbit status recording.

[0125] The on-orbit status automated documentation and comparison work includes:

[0126] When the status data type is telemetry parameter type, the on-orbit telemetry parameters are entered into the information system to record the on-orbit status. The normal value range of telemetry parameters associated with daily flight status requirements and special mission status requirements are used for real-time comparison to obtain a conclusion on whether the current on-orbit status meets the status requirements and to detect deviations in a timely manner.

[0127] When the status data type is material type, record the astronauts' manual operations, record the actual on-orbit status of on-orbit spare parts, consumables, maintenance tools and other on-orbit materials, compare them with the material storage status requirements, and draw a conclusion on whether the current on-orbit status meets the status requirements, and discover deviations in time;

[0128] When the status data type is resource type, the consumption of on-orbit materials is recorded, data analysis is performed on the consumption rates of different resources, and the remaining quantity and supportable time are estimated. These are compared with the consumption rate, supportable time and other indicator requirements to draw a conclusion on whether the current on-orbit status meets the status requirements and to detect deviations in a timely manner.

[0129] (5) Status management and control

[0130] State management and control include the following:

[0131] 1) Manage and control status requirements, implement the approval process for changes to flight status requirements, and use an electronic approval process to control changes to flight status requirements.

[0132] 2) Manage and control the on-orbit status, implement the application approval process for deviation status, and use electronic approval process to manage and control the deviation status.

[0133] 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.

[0134] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A method for controlling the on-orbit state of a manned spacecraft based on data homology, characterized in that include: Describe the on-orbit status of the data source according to the status data type of the manned spacecraft; Formulate the safety state requirement envelope corresponding to the on-orbit state of each manned spacecraft; According to the safety state requirement envelope corresponding to the on-orbit state of each manned spacecraft and the on-orbit state description results of the data source, an information control model is established to control each manned spacecraft in real time; The on-orbit telemetry data in the real-time control process is recorded and compared with the on-orbit state description of the data source, and the manned spacecraft is judged whether there is any deviation in the current on-orbit state according to the comparison result; If a deviation occurs, the deviation status of the manned spacecraft will be controlled and adjusted, otherwise the manned spacecraft mission will continue to be executed.

2. The method for controlling the on-orbit state of a manned spacecraft based on data homology according to claim 1, characterized in that: The state data types of the manned spacecraft include telemetry parameter type, material type, and resource type. The method for describing the on-orbit state of the data source is: When the status data type is telemetry parameter type, the on-orbit status is described according to the on / off status parameters and working status parameters of the spacecraft equipment, and the telemetry parameter variation range is set; When the status data type is material type, the real-time dynamic changes of the on-orbit materials such as spare parts, consumables, and maintenance tools installed and stored on the spacecraft are recorded, and the on-orbit status is described using the location, quantity, and usage information of various on-orbit materials; When the status data type is resource type, the real-time changes of the on-orbit resident resources such as on-orbit propellant, gas cylinders, and water of the spacecraft are regularly recorded using telemetry information. A resource consumption model is established based on the regular recording results. The parameters of the resource consumption model are corrected through the on-orbit resident resource data of different spacecraft crews, astronauts with different metabolic levels, and spacecraft missions. The corrected resource consumption model is used to obtain the on-orbit resource status data in real time, and the on-orbit status is described through the on-orbit resource status data.

3. The method for controlling the on-orbit state of a manned spacecraft based on data homology according to claim 2, characterized in that: The on-orbit status of the manned spacecraft includes the on-orbit status during routine flight and the on-orbit status during special missions; In the on-orbit state during routine flight, the manned spacecraft does not perform critical tasks on orbit and operates normally; the operating state parameter range of spacecraft equipment and on-orbit products is used as the safety state requirement envelope; When a special mission is in-orbit, the manned spacecraft performs key tasks, identifies the working conditions of the safety risk points in the on-orbit state, and determines the safety status envelope range of the spacecraft equipment and on-orbit products based on the actual working conditions at the time of executing the key mission.

4. The method for controlling the on-orbit state of a manned spacecraft based on data homology according to claim 3, characterized in that: During routine flight, the operating status parameters of spacecraft equipment and on-orbit products are within the following ranges: The data range of the manned spacecraft's assembly configuration information, extravehicular equipment status information, on-orbit status information of the spacecraft's functional systems, hardware status information, software status information, interface status information, and real-time on-orbit resource status data in a safe state; When the special mission is on-orbit, the actual working conditions at the critical mission execution time are: The manned spacecraft assembly configuration information, robotic arm parking position information, lighting condition information, engine plume condition information, sensor field of view angle information, extravehicular equipment motion envelope information, and the data range in the safe state of the pyrotechnic platform safety prohibition command during the mission.

5. The method for controlling the on-orbit state of a manned spacecraft based on data homology according to claim 3, characterized in that: The method for the information control model to perform real-time control on each manned spacecraft is as follows: Collect the real-time telemetry parameters of each manned spacecraft at the current moment, and compare them with the safety state requirement envelope corresponding to the current on-orbit state of the manned spacecraft. If they are inconsistent, the manned spacecraft will be controlled in real time to deviate from the state. If they are consistent, no processing will be performed; Traverse each manned spacecraft until the safety state requirement envelope of all manned spacecraft in the current on-orbit state is consistent with the real-time telemetry parameters of the manned spacecraft.

6. The method for controlling the on-orbit state of a manned spacecraft based on data homology according to claim 5, characterized in that: When the status data type is telemetry parameter type, the on-orbit telemetry parameters are entered into the information control model to record the on-orbit status. The safety status requirement envelope of the on-orbit status during daily flight or the on-orbit status of special tasks is used to judge the current on-orbit telemetry parameters, and deviation control or no control is performed based on the judgment results.

7. The method for controlling the on-orbit state of a manned spacecraft based on data homology according to claim 5, characterized in that: When the status data type is material type, the astronauts' manual operations are recorded, as well as the actual on-orbit status of on-orbit spare parts, consumables, and maintenance tools. These are compared with the safety status requirement envelope of the on-orbit status during routine flight or the on-orbit status of special missions, and deviation control or no control is performed based on the judgment result.

8. The method for controlling the on-orbit state of a manned spacecraft based on data homology according to claim 5, characterized in that: When the status data type is resource type, the consumption of on-orbit materials is recorded, data analysis is performed on the consumption rates of different resources, and the remaining quantity and support time are estimated; the remaining quantity and support time are compared with the safety status requirement envelope, and deviation control or no control is performed based on the judgment result.

9. An information control model for implementing the on-orbit state control method of a manned spacecraft according to claim 1, characterized in that: The information control model includes a flight status requirement module, a flight status recording module, a flight status control module, and a basic data module, wherein: The flight status requirement module centrally formulates the safety status requirement envelope of the operating status parameters of different manned spacecraft in orbit according to the status data type determined by the basic data module; The flight status recording module can synchronously obtain data related to the status of on-orbit materials, on-orbit telemetry, and on-orbit resources. The flight status control module compares the on-orbit related data obtained by the flight status recording module with the safety status requirement envelope formulated by the flight status requirement module, and performs real-time deviation status control or no control according to the comparison result; The basic data module analyzes the state data type of the manned spacecraft, describes the on-orbit state of the data source, and associates it with various parameter information of the on-orbit state of the manned spacecraft, and records the stage data generated by the flight state requirement module, flight state recording module, and flight state control module.

10. The method for controlling the on-orbit state of a manned spacecraft based on data homology according to claim 1, characterized in that: When the flight status control module performs real-time deviation status control according to the comparison result, process management is achieved by sending an electronic approval request to the external control system.

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