A manned spacecraft in-orbit state control model and method based on data homology

Abstract

A manned spacecraft in-orbit state control model and method based on data homology, facing the long-term in-orbit operation of complex large manned spacecraft, proposes a flight state control method based on data homology, mainly used to solve the contradiction between the complex and dynamic change of manned spacecraft in-orbit state and the fine and real-time state control demand, and proposes a manned spacecraft in-orbit state information control model architecture, which optimizes the in-orbit operation control efficiency of manned spacecraft.

Description

TECHNICAL FIELD

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

[0002] In a large complex manned spacecraft flight mission, the in-orbit state management is directly related to the success or failure of the mission. To ensure the safety of the manned spacecraft in flight and the safety of the astronauts in orbit, a variety of in-orbit tasks need to be fully controlled to ensure the safety and control of the combination state before, during and after the task, avoid situations caused by improper state setting, and ensure the smooth implementation of long-term operation and subsequent tasks.

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

[0004] 1) There are people in orbit, the platform function and system design are more complex, the state during operation is multiple, the mode is multiple, the coupling is strong, and the in-orbit state baseline needs to be described in more detail to represent the in-orbit running state;

[0005] 2) There are uplink and downlink personnel and cargo transportation interfaces, and the in-orbit state is constantly updated with the docking and withdrawal of the earth-space transportation system; at the same time, astronauts in orbit also play an active role, so the in-orbit state is not fixed and needs dynamic management;

[0006] 3) During the in-orbit operation of the manned spacecraft, the states of various systems are associated and coupled, and a unified state management method and tool are needed to carry out state management and control under unified requirements.

[0007] The in-orbit running state of the early manned spacecraft is relatively single, and the ground mainly judges the in-orbit running state of the manned spacecraft by judging specific telemetry parameters, using telemetry parameters to represent whether the device is working normally, but it does not judge whether the device is working in the required state at a certain moment or flight stage, at which time the telemetry parameters may all be within the normal range, but the working state has exceeded the state requirement range. SUMMARY

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

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

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

[0011] Based on the state data type of manned spacecraft, describe the on-orbit state of the data source;

[0012] Establish safety status requirement envelopes corresponding to the on-orbit status of each manned spacecraft;

[0013] Based on the safety status requirement envelope corresponding to the on-orbit status of each manned spacecraft and the on-orbit status description results of the data source, an information-based 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 and compare it with the on-orbit status description of the data source. Based on the comparison results, determine whether the manned spacecraft has deviated from its current on-orbit status.

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

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

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

[0018] When the status data type is material, the real-time dynamic changes of 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 on-orbit residence resources of spacecraft propellant, gas cylinders, and water are periodically recorded in real time using telemetry information. A resource consumption model is established based on the periodic recording results. The parameters of the resource consumption model are corrected by the on-orbit residence resource data of different spacecraft crews, different metabolic levels of astronauts, and spacecraft missions. The corrected resource consumption model is used to obtain on-orbit resource status data in real time, and the on-orbit status is described by the on-orbit resource status data.

[0020] The on-orbit status of the manned spacecraft includes its on-orbit status during routine flights and its on-orbit status during special missions.

[0021] During routine flight, the manned spacecraft is in orbit and does not perform critical missions but operates normally; the range of operational status parameters of spacecraft equipment and on-orbit products is used as the safety status requirement envelope.

[0022] During the on-orbit status of a special mission, the manned spacecraft performs critical tasks, identifies operational conditions of safety risk points in the on-orbit status, and determines the safety status envelope of spacecraft equipment and on-orbit products based on the actual operational conditions at the time of critical mission execution.

[0023] During routine flight, the operating status parameters of spacecraft equipment and on-orbit products in orbit are as follows:

[0024] Information on the combined configuration of the manned spacecraft, status information of external equipment, on-orbit status information of the spacecraft's functional systems, hardware status information, software status information, interface status information, and the data range of real-time on-orbit resource status data under safe conditions;

[0025] The actual operating conditions during the execution of critical tasks while the special mission is in orbit are as follows:

[0026] Information on the combined configuration of the manned spacecraft, the parking position of the robotic arm, lighting conditions, engine plume conditions, sensor field of view, motion envelope of extravehicular equipment, and the data range under the safe state of the pyrotechnic platform's prohibition of firing commands during the mission.

[0027] The information-based control model uses the following method for real-time control of each manned spacecraft:

[0028] The system collects real-time telemetry parameters of each manned spacecraft at the current moment and compares them with the safety state requirement envelope corresponding to the current on-orbit state of the manned spacecraft. If they are inconsistent, the system performs real-time deviation control on the manned spacecraft; if they are consistent, no action is taken.

[0029] The safety status requirement envelope of each manned spacecraft is traversed until all manned spacecraft are in their current on-orbit state and 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 will be entered into the information control model, and the on-orbit status will be recorded (recording operation). The safety status requirement envelope of the on-orbit status during daily flight or on-orbit status of special missions will be used to judge the current on-orbit telemetry parameters, and deviation control or no control will be performed based on the judgment result.

[0031] When the status data type is material, it records the astronaut's manual operations, the actual on-orbit status of spare parts, consumables, and maintenance tools, and compares it with the safety status requirement envelope of the on-orbit status during daily flight or special mission. Based on the judgment result, deviation control or no control is performed.

[0032] When the status data type is resource type, the consumption of on-orbit materials is recorded, the consumption rate of different resources is analyzed, 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-based control model for implementing on-orbit state control methods for manned spacecraft includes:

[0034] The information-based control model includes a flight status requirements module, a flight status recording module, a flight status control module, and a basic data module, wherein:

[0035] The Flight Status Requirements module, based on the status data type determined by the Basic Data module, centrally formulates the safety status requirement envelopes for operational status parameters under different on-orbit states of manned spacecraft.

[0036] The flight status recording module acquires relevant data on the status of on-orbit materials, on-orbit telemetry, and on-orbit resources simultaneously from space and ground.

[0037] The flight status control module compares the on-orbit relevant data obtained by the flight status recording module with the safety status requirement envelope set by the flight status requirement module, and performs real-time deviation status control or does not perform control based on the comparison results.

[0038] The basic data module analyzes the state data types of manned spacecraft, describes the on-orbit state of the data source, and associates it with various parameter information of the manned spacecraft's on-orbit state. It also records the stage data generated by the flight state requirements module, the flight state documentation module, and the flight state control module.

[0039] When the flight status control module performs real-time deviation control based on the comparison results, it achieves process management by sending electronic approval requests to the external control system.

[0040] The advantages of this invention compared to the prior art are:

[0041] (1) The present invention provides a manned spacecraft on-orbit state control model and method based on data homogeneity. By controlling the manned spacecraft on-orbit state based on data homogeneity between space and ground, it solves the problem of timely grasping the complex and ever-changing on-orbit state of the manned spacecraft on the ground. It can establish standardized information interfaces according to different state types, automatically acquire real-time on-orbit state, improve ground work efficiency, and effectively judge whether the manned spacecraft on-orbit state is correct and meets the requirements. It can also promptly judge state deviation and errors, remind 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 status management method for manned spacecraft proposed in this invention solves the problem of managing and controlling the complex and ever-changing on-orbit status of manned spacecraft. Through on-orbit status management, the technical status of manned spacecraft on-orbit is controlled and traceable. By formulating on-orbit status setting requirements and recording the on-orbit status, status deviations and anomalies can be identified in a timely manner, and timely disposal measures can be formulated. At the same time, through on-orbit status management and control, the on-orbit technical status of manned spacecraft meets expectations. Attached Figure Description

[0043] Figure 1 The present invention provides a flowchart for the daily flight status management and control of manned spacecraft;

[0044] Figure 2 A flowchart is developed for the on-orbit status requirements provided by this invention;

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

[0046] Figure 4 The above is a flowchart of the on-orbit status management information provided by the present invention. Detailed Implementation

[0047] A data-based on-orbit state control model and method for manned spacecraft is proposed. This method is designed for the long-term on-orbit operation of complex and large manned spacecraft. It aims to resolve the contradiction between the complex and dynamically changing on-orbit state of manned spacecraft and the need for refined and real-time state control. Furthermore, it proposes an information-based management and control model architecture for the on-orbit state of manned spacecraft to optimize the efficiency of on-orbit operation and management.

[0048] The information-based control model for on-orbit status control of manned spacecraft based on data homogeneity includes: a flight status requirements module, a flight status documentation module, a flight status control module, a basic data module, and a process management module, among which:

[0049] The Flight Status Requirements module centrally defines the status parameter setting requirements for the on-orbit status of manned spacecraft.

[0050] The flight status recording module acquires the status of on-orbit supplies simultaneously from space and ground.

[0051] The flight status control module compares the status of on-orbit materials with the itemized description of flight status requirements, and performs real-time deviation status control if there is a discrepancy.

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

[0053] The process control module enables process control of each manned spacecraft's flight status corresponding to its on-orbit state.

[0054] The on-orbit state control method for manned spacecraft based on data homology involves the following steps:

[0055] Based on the state data type of manned spacecraft, describe the on-orbit state of the data source;

[0056] Formulate the state parameter setting requirements for each manned spacecraft in its on-orbit state;

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

[0058] The on-orbit telemetry data during the real-time control process is documented and compared with the on-orbit status description of the data source. Based on the comparison results, it is determined whether the manned spacecraft has deviated from its current on-orbit status.

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

[0060] The status data types for manned spacecraft include telemetry parameter classes, material classes, and resource classes. The on-orbit status description of the data source is as follows:

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

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

[0063] When the status data type is resource type, the on-orbit residence resources of spacecraft propellant, gas cylinders, and water are periodically recorded in real time using telemetry information. A resource consumption model is established based on the periodic recording results. The parameters of the resource consumption model are corrected by the on-orbit residence resource data of different spacecraft crews, different metabolic levels of astronauts, and spacecraft missions. The corrected resource consumption model is used to obtain on-orbit resource status data in real time.

[0064] The on-orbit status of a manned spacecraft includes its on-orbit status during routine flights and its on-orbit status during special missions.

[0065] During routine flight, the manned spacecraft does not perform critical missions and operates normally in orbit. The usage status of the spacecraft equipment and on-orbit products is within the safety status requirement envelope.

[0066] When a special mission is in orbit, the manned spacecraft performs critical tasks. After identifying the safety risk points in the in-orbit state, the safety state envelope of the critical mission is determined. During the design phase of each critical mission, the range of usage status parameters of spacecraft equipment and in-orbit products is determined based on the actual operating conditions at the time of execution of the critical mission.

[0067] During routine flight while in orbit, the safety status requirement envelope is as follows:

[0068] Information on the combined configuration of the manned spacecraft, status information of external equipment, on-orbit status information of the spacecraft's functional systems, hardware status information, software status information, interface status information, and the data range of real-time on-orbit resource status data under safe conditions;

[0069] When a special mission is in orbit, the range of status parameters used is as follows:

[0070] Information on the combined configuration of the manned spacecraft, the parking position of the robotic arm, lighting conditions, engine plume conditions, sensor field of view, motion envelope of extravehicular equipment, and the data range under the safe state of the pyrotechnic platform's prohibition of firing commands during the mission.

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

[0072] Based on the data source on-orbit status description of the manned spacecraft and the on-orbit status of each manned spacecraft, data association is performed. The parameter types in the status parameter setting requirements of different manned spacecraft on-orbit status are used. According to the functional status, hardware status, software status, and resource status, the flight status requirements are described in an itemized manner by means of manual input or import of data source on-orbit status description.

[0073] The status of on-orbit supplies is acquired synchronously from space and ground. The status of on-orbit supplies is compared with the flight status requirements described in itemized form. If there is a discrepancy, 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 description, in conjunction with the accompanying drawings and preferred embodiments, provides further details:

[0075] In the current embodiment, such as Figure 1 As shown, the specific means of managing the on-orbit status of manned spacecraft include:

[0076] Based on the state data type of manned spacecraft, describe the on-orbit state of the data source;

[0077] Establish safety status requirement envelopes corresponding to the on-orbit status of each manned spacecraft;

[0078] Based on the safety status requirement envelope corresponding to the on-orbit status of each manned spacecraft and the on-orbit status description results of the data source, an information-based 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 and compare it with the on-orbit status description of the data source. Based on the comparison results, determine whether the manned spacecraft has deviated from its current on-orbit status.

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

[0081] Further:

[0082] Part 1: Designing a state description method for on-orbit state management of manned spacecraft, mainly including telemetry parameter classes, material classes, and resource classes. For different state data types, determining the data source information interface and establishing an information processing database are fundamental to achieving informatized state management.

[0083] Part Two: Formulating flight status setting requirements for manned spacecraft, prioritizing the safe and stable operation of the manned spacecraft, and determining the operational status requirements for each function and piece of equipment. Specifically, it establishes targeted status setting requirements, i.e., relevant envelope designs, for both routine flight and special missions of the manned spacecraft.

[0084] Part Three: For each state setting requirement, specify the state description method and associate it with the data source in the information management and control system. The data source includes on-orbit telemetry parameters, data confirmed in other software databases, etc. Design normal value ranges for manned spacecraft during daily flight and during special missions to realize automatic comparison and interpretation of the state and draw conclusions on whether the current on-orbit state meets the state setting requirements.

[0085] (1) Determine the state description method

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

[0087] 1) Telemetry Parameters: The on / off status, working mode, and other working states of the equipment are all determined by different ranges of telemetry parameters. An information processing database is established for the telemetry parameters that characterize the working state of the equipment.

[0088] 2) Materials: These include spare parts, consumables, and maintenance tools installed and stored in orbit. The status of these materials cannot be characterized by telemetry parameters. At the same time, the status of materials in orbit changes dynamically in real time due to astronauts' consumption, maintenance, and extravehicular activities. The existing on-orbit material management system is used to record the status of materials, including location, quantity, and usage information, and an information processing database is established.

[0089] 3) Resource-related resources: These include on-orbit propellant, gas cylinders, water, etc. These resources change in real time as the astronauts remain in orbit, and are periodically recorded and statistically analyzed using telemetry information and the on-orbit material management system. For resources unique to manned spacecraft, such as water, oxygen, and nitrogen, which are closely related to the crew, resource consumption models are established based on accumulated on-orbit flight data. The model parameters are continuously adjusted using on-orbit data from different crews, different metabolic levels, and missions, enabling real-time deriving of on-orbit resource status data using a digital model.

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

[0091] The on-orbit status requirements for manned spacecraft include routine flight status requirements and mission-specific status requirements. Routine flight status requirements specify reasonable and safe settings for the on-orbit product usage status during normal operation when the manned spacecraft is not performing critical missions. Due to the highly variable external environment such as lighting conditions and configuration of the manned spacecraft during routine on-orbit flight, and the strong coupling of states, the routine flight status requirements are generally an envelope of the safety status requirements for each function of the manned spacecraft.

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

[0093] 1) Assembled configuration;

[0094] 2) Status of large external facilities and equipment;

[0095] 3) System functional status requirements, including the on-orbit status requirements of functions such as control system, propulsion system, energy system, information system, thermal management and control, and manned environmental control;

[0096] 4) Hardware status settings requirements;

[0097] 5) Software status setting requirements;

[0098] 6) Requirements for setting the status of inter-system interfaces;

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

[0100] The specific mission status requirements specify the requirements that should be set in orbit during the critical missions performed by manned spacecraft. When proposing the specific mission status requirements, the first step is to identify the safety risks in the on-orbit state and formulate the overall status elements before mission implementation, which should include at least the following elements:

[0101] 1) Assembled configuration;

[0102] 2) The robotic arm's parking position;

[0103] 3) Lighting conditions;

[0104] 4) Engine plume conditions;

[0105] 5) Sensor field of view;

[0106] 6) The motion envelope of large external equipment;

[0107] 7) Prohibit issuing commands for explosives and other items that affect platform security during the mission.

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

[0109] (3) Design of Information Management and Control System

[0110] The basic principle of designing an information-based control system for on-orbit status management is that the data for on-orbit status management must originate from the same source as other on-orbit data. Utilizing on-orbit telemetry data and material / resource data from on-orbit sources, the system enables comparison and control of on-orbit status. The designed control process is as follows: Figure 2 As shown;

[0111] The information-based management and control system comprises five functional modules:

[0112] 1) "Flight Status Requirements" module

[0113] The requirements for the on-orbit flight status of manned spacecraft should be centrally formulated, describing the requirements in an itemized manner according to aspects such as system functional status, hardware operating status, software operating status, and resource status, using methods such as manual input or database import. Simultaneously, information such as equipment specifications and telemetry parameters from the "Basic Data" module needs to be incorporated, and the normal value ranges of characteristic parameters describing the flight status requirements need to be defined.

[0114] 2) "Flight Status Documentation" module

[0115] Based on the characteristic parameters describing flight status requirements defined in the "Flight Status Requirements" module, the data from the space and ground sources are ensured to be consistent by binding the on-orbit data receiving software with the on-orbit telemetry parameters, obtaining the status of on-orbit materials through the space-ground material synchronization system, and obtaining on-orbit resource records or assessments through manual input or model calculations.

[0116] 3) "Flight Status Control" module

[0117] By comparing the on-orbit status with the flight status requirements in real time, the flight status is routinely managed. If the comparison results in a discrepancy, deviation status control is implemented through the process to manage and control changes and optimizations to the flight status requirements.

[0118] 4) "Basic Data" module

[0119] This includes data such as on-orbit equipment for manned spacecraft, telemetry parameters, material information, and resource information, which are used to correlate characteristic parameters required for flight status with information on flight status records.

[0120] 5) "Process Control" module

[0121] The procedures used in flight status control.

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

[0123] (4) Automated status 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 related to daily flight status requirements and special mission status requirements will be compared in real time to obtain a judgment on whether the current on-orbit status meets the status requirements and to detect deviations in a timely manner; the manual operations of astronauts will be recorded to achieve non-parametric on-orbit status recording.

[0125] Automated documentation and comparison of on-orbit status includes:

[0126] When the status data type is telemetry parameter type, 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 compared in real time to obtain a judgment 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, it records the astronaut's manual operations, the actual on-orbit status of on-orbit spare parts, consumables, maintenance tools and other on-orbit materials, compares them with the material storage status requirements, and draws a judgment on whether the current on-orbit status meets the status requirements, so as to detect deviations in a timely manner.

[0128] When the status data type is resource type, it records the consumption of on-orbit materials, analyzes the consumption rate of different resources, and estimates the remaining quantity and support time. It compares the results with the requirements of indicators such as consumption rate and support time to determine whether the current on-orbit status meets the status requirements and promptly detects deviations.

[0129] (5) Status management and control

[0130] Status management and control include the following:

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

[0132] 2) To manage and control the on-orbit status, implement an application and approval process for deviations, and adopt an electronic approval process for managing and controlling deviations.

[0133] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

[0134] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A method for on-orbit state control of manned spacecraft based on data homology, characterized in that... include: Based on the state data type of manned spacecraft, describe the on-orbit state of the data source; Establish safety status requirement envelopes corresponding to the on-orbit status of each manned spacecraft; Based on the safety status requirement envelope corresponding to the on-orbit status of each manned spacecraft and the on-orbit status description results of the data source, an information-based control model is established to control each manned spacecraft in real time. Record the on-orbit telemetry data during the real-time control process and compare it with the on-orbit status description of the data source. Based on the comparison results, determine whether the manned spacecraft has deviated from its current on-orbit status. If a deviation occurs, the manned spacecraft will be adjusted and controlled according to its deviation status; otherwise, the manned spacecraft mission will continue.

2. The on-orbit state control method for manned spacecraft based on data homology as described in claim 1, characterized in that: The status data types of the manned spacecraft include telemetry parameter classes, material classes, and resource classes. The method for describing the on-orbit status of the data source is as follows: When the status data type is telemetry parameter type, the on-orbit status is described according to the power-on / off status parameters and working status parameters of the spacecraft equipment, and the range of telemetry parameter variation is set; When the status data type is material, the real-time dynamic changes of 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 on-orbit residence resources of spacecraft propellant, gas cylinders, and water are periodically recorded in real time using telemetry information. A resource consumption model is established based on the periodic recording results. The parameters of the resource consumption model are corrected by the on-orbit residence resource data of different spacecraft crews, different metabolic levels of astronauts, and spacecraft missions. The corrected resource consumption model is used to obtain on-orbit resource status data in real time, and the on-orbit status is described by the on-orbit resource status data.

3. The on-orbit state control method for manned spacecraft based on data homology as described in claim 2, characterized in that: The on-orbit status of the manned spacecraft includes its on-orbit status during routine flights and its on-orbit status during special missions. During routine flight, the manned spacecraft is in orbit and does not perform critical missions but operates normally; the range of operational status parameters of spacecraft equipment and on-orbit products is used as the safety status requirement envelope. During the on-orbit status of a special mission, the manned spacecraft performs critical tasks, identifies operational conditions of safety risk points in the on-orbit status, and determines the safety status envelope of spacecraft equipment and on-orbit products based on the actual operational conditions at the time of critical mission execution.

4. The on-orbit state control method for manned spacecraft based on data homology as described in claim 3, characterized in that: During routine flight, the operating status parameters of spacecraft equipment and on-orbit products in orbit are as follows: Information on the combined configuration of the manned spacecraft, status information of external equipment, on-orbit status information of the spacecraft's functional systems, hardware status information, software status information, interface status information, and the data range of real-time on-orbit resource status data under safe conditions; The actual operating conditions during the execution of critical tasks while the special mission is in orbit are as follows: Information on the combined configuration of the manned spacecraft, the parking position of the robotic arm, lighting conditions, engine plume conditions, sensor field of view, motion envelope of extravehicular equipment, and the data range under the safe state of the pyrotechnic platform's prohibition of firing commands during the mission.

5. The on-orbit state control method for manned spacecraft based on data homology as described in claim 3, characterized in that: The information-based control model uses the following method for real-time control of each manned spacecraft: The system collects real-time telemetry parameters of each manned spacecraft at the current moment and compares them with the safety state requirement envelope corresponding to the current on-orbit state of the manned spacecraft. If they are inconsistent, the system performs real-time deviation control on the manned spacecraft; if they are consistent, no action is taken. The safety status requirement envelope of each manned spacecraft is traversed until all manned spacecraft are in their current on-orbit state and is consistent with the real-time telemetry parameters of the manned spacecraft.

6. The on-orbit state control method for manned spacecraft based on data homology as described in claim 5, characterized in that: When the status data type is telemetry parameter type, the on-orbit telemetry parameters will be entered into the information control model, the on-orbit status will be recorded, and the safety status requirement envelope of the on-orbit status during daily flight or on-orbit status of special missions will be used to judge the current on-orbit telemetry parameters. Based on the judgment result, deviation control or no control will be performed.

7. The on-orbit state control method for manned spacecraft based on data homology as described in claim 5, characterized in that: When the status data type is material, it records the astronaut's manual operations, the actual on-orbit status of spare parts, consumables, and maintenance tools, and compares it with the safety status requirement envelope of the on-orbit status during daily flight or special mission. Based on the judgment result, deviation control or no control is performed.

8. The on-orbit state control method for manned spacecraft based on data homology as described in claim 5, characterized in that: When the status data type is resource type, the consumption of on-orbit materials is recorded, the consumption rate of different resources is analyzed, 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-based control model for implementing the on-orbit state control method of a manned spacecraft according to claim 1, characterized in that: The information-based 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 Requirements module, based on the status data type determined by the Basic Data module, centrally formulates the safety status requirement envelopes for operational status parameters under different on-orbit states of manned spacecraft. The flight status recording module acquires relevant data on the status of on-orbit materials, on-orbit telemetry, and on-orbit resources simultaneously from space and ground. The flight status control module compares the on-orbit relevant data obtained by the flight status recording module with the safety status requirement envelope set by the flight status requirement module, and performs real-time deviation status control or does not perform control based on the comparison result. The basic data module analyzes the data types of manned spacecraft's status, describes the on-orbit status of the data source, and associates it with various parameter information of the manned spacecraft's on-orbit status. It also records the stage data generated by the flight status requirements module, flight status recording module, and flight status control module.

10. The information-based control model according to claim 9, characterized in that: When the flight status control module performs real-time deviation control based on the comparison results, it achieves process management by sending electronic approval requests to the external control system.

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