Control system simulation method and system for on-orbit spacecraft

Abstract

The invention discloses a simulation method and system for a control system of an on-orbit spacecraft. The method is applied to an upper computer of a simulation system of an on-orbit spacecraft control system. The system comprises a sensor simulation unit, a GNC controller simulation unit, an actuator simulation unit, a dynamic model and a telemetry data storage unit. The method comprises the following steps: for a first control period, a GNC controller simulation unit constructs an initial parameter of a simulation system based on telemetry data at a preset moment in a telemetry data storage unit, and performs simulation calculation of the control period based on the initial parameter; for other control periods, executing the following steps: judging whether the telemetry data is adopted to participate in the simulation calculation of the control period or not; if yes, the GNC controller simulation unit calls telemetering data at the corresponding moment, and simulation calculation of the control period is carried out based on the called telemetering data; and if not, performing simulation calculation of the control period based on the measurement state. According to the invention, the accuracy of the simulation system can be improved.

Description

Technical Field

[0001] The present invention relates to the field of control simulation technology, and in particular to a control system simulation method and system for an on-orbit spacecraft. Background Art

[0002] The ground simulation of the spacecraft on-orbit control system is mainly used for system debugging, test verification, problem reproduction, etc. Compared with the physical test system, the simulation system has the advantages of easy operation and fast operation. The entire simulation system can be run on one or several high-performance PCs and can be used to simulate the actions of various sensors, GNC controllers, actuators, etc. However, the existing simulation methods cannot reasonably set the initial parameters of the simulation system, such as initial conditions and simulation inputs, resulting in the simulation results being inconsistent with the actual on-orbit state, affecting the accuracy of simulation verification.

[0003] Therefore, there is an urgent need for a control system simulation method and system for an on-orbit spacecraft to solve the above problems. Summary of the invention

[0004] The present invention provides a control system simulation method and system for an on-orbit spacecraft, which can improve the accuracy of the simulation system. The technical solution is as follows:

[0005] On the one hand, a control system simulation method for an on-orbit spacecraft is provided, which is applied to a host computer of a simulation system of an on-orbit spacecraft control system, wherein the simulation system comprises a sensor simulation unit, a GNC controller simulation unit, an actuator simulation unit, a dynamic model and a telemetry data storage unit; the sensor simulation unit, the GNC controller simulation unit, the actuator simulation unit and the dynamic model are connected in sequence, and the telemetry data storage unit is connected to the GNC controller simulation unit; the sensor simulation unit is used to output a measurement state of the spacecraft based on the excitation information output by the dynamic model; the telemetry data storage unit is used to receive and store real telemetry data of the on-orbit spacecraft; the GNC controller simulation unit is used to issue a control instruction based on the measurement state or the telemetry data; the actuator simulation unit is used to calculate mechanical information based on the control instruction; and the dynamic model is used to output excitation information based on the mechanical information;

[0006] The method comprises:

[0007] For the first control cycle, the GNC controller simulation unit constructs initial parameters of the simulation system based on the telemetry data at a preset time in the telemetry data storage unit, and performs simulation calculations for the control cycle based on the initial parameters; the initial parameters include initial conditions and initial simulation inputs;

[0008] For other control cycles, execute:

[0009] Determine whether to use the telemetry data stored in the telemetry data storage unit to participate in the simulation calculation of the control cycle; if so, the GNC controller simulation unit retrieves the telemetry data at the corresponding moment, and performs the simulation calculation of the control cycle based on the retrieved telemetry data; if not, perform the simulation calculation of the control cycle based on the measurement state output by the sensor simulation unit.

[0010] In one possible design, a telemetry data inverse assignment function is stored in the GNC controller simulation unit; the inverse assignment function is used to unpack and assign the telemetry data, and determine the software variables of the GNC controller simulation unit based on the unpacked and assigned data; when working, the GNC controller simulation unit calculates the spacecraft control quantity based on the software variables, and issues control instructions according to the control quantity.

[0011] In a possible design, the GNC controller simulation unit constructs initial parameters of the simulation system based on the telemetry data at a preset time in the telemetry data storage unit, including:

[0012] Retrieving telemetry data at a preset time from the telemetry data storage unit based on the GNC controller simulation unit;

[0013] Unpacking and assigning values ​​to the retrieved telemetry data based on the inverse assignment function;

[0014] The initial parameters of the simulation system are determined based on the unpacked and assigned data.

[0015] In a possible design, the simulation calculation of the control cycle based on the initial parameters includes:

[0016] Based on the initial parameters, the software variables of the GNC controller simulation unit are determined using the telemetry data inverse assignment function; based on the software variables, the spacecraft control quantity is calculated using the GNC controller simulation unit, and a control instruction is issued according to the control quantity;

[0017] Based on the control instruction, using the actuator simulation unit to output mechanical information of the control cycle;

[0018] Based on the mechanical information, using the dynamics simulation unit to output excitation information of the control cycle;

[0019] Based on the excitation information, the sensor simulation unit is used to output the measurement state of the next control cycle.

[0020] In a possible design, the criteria for determining whether to use the telemetry data stored in the telemetry data storage unit to participate in the simulation calculation of a certain control cycle are:

[0021] Whether the difference between the corresponding telemetry data in the control cycle and the measurement state output by the sensor simulation unit exceeds the preset value, if so, the telemetry data is used to participate in the simulation calculation of the control cycle, otherwise, the measurement state output by the sensor simulation unit is used to perform the simulation calculation of the control cycle.

[0022] In a possible design, the criteria for determining whether to use the telemetry data stored in the telemetry data storage unit to participate in the simulation calculation of a certain control cycle are:

[0023] Whether the number of simulation calculations based on the measurement state output by the sensor simulation unit exceeds a preset number, if so, the telemetry data is used to participate in the simulation calculation of the control cycle, otherwise, the measurement state output by the sensor simulation unit is used to perform the simulation calculation of the control cycle.

[0024] In a possible design, a simulation calculation of the control cycle is performed based on the retrieved telemetry data, including:

[0025] Unpacking and assigning values ​​to the retrieved telemetry data based on the inverse assignment function to obtain unpacked and assigned data;

[0026] Based on the unpacked assigned data, the software variables of the GNC controller simulation unit are determined by using the telemetry data inverse assignment function; based on the software variables, the spacecraft control quantity is calculated by using the GNC controller simulation unit, and a control instruction is issued according to the control quantity;

[0027] Based on the control instruction, using the actuator simulation unit to output mechanical information of the control cycle;

[0028] Based on the mechanical information, using the dynamics simulation unit to output the excitation information of the control cycle;

[0029] Based on the excitation information, the sensor simulation unit is used to output the measurement state of the next control cycle.

[0030] In a possible design, performing simulation calculation of the control cycle based on the measurement state output by the sensor simulation unit includes:

[0031] Based on the measurement state, using the GNC controller simulation unit to calculate the spacecraft control quantity, and issuing a control instruction according to the control quantity;

[0032] Based on the control instruction, using the actuator simulation unit to output mechanical information of the control cycle;

[0033] Based on the mechanical information, using the dynamics simulation unit to output the excitation information of the control cycle;

[0034] Based on the excitation information, the sensor simulation unit is used to output the measurement state of the next control cycle.

[0035] In another aspect, a simulation system for an on-orbit spacecraft control system is provided, comprising: a sensor simulation unit, a GNC controller simulation unit, an actuator simulation unit, a dynamics model, and a telemetry data storage unit;

[0036] The sensor simulation unit is used to output the measurement state of the spacecraft based on the excitation information output by the dynamic model, and send the measurement state to the GNC controller simulation unit;

[0037] The telemetry data storage unit is used to receive and store real telemetry data of the on-orbit spacecraft, and send the received telemetry data to the GNC controller simulation unit;

[0038] The GNC controller simulation unit is used to issue a control instruction based on the measurement state or the telemetry data, and send the control instruction to the actuator simulation unit;

[0039] The actuator simulation unit is used to calculate mechanical information based on the control instruction and send the calculated mechanical information to the dynamic model;

[0040] The dynamic model is used to output excitation information based on the mechanical information, and send the excitation information to the sensor simulation unit.

[0041] In a possible design, a telemetry data inverse assignment function is stored in the GNC controller simulation unit, and the inverse assignment function is used to unpack and assign the telemetry data, and determine the software variables of the GNC controller simulation unit based on the unpacked and assigned data; when working, the GNC controller simulation unit calculates the spacecraft control quantity based on the software variables, and issues control instructions according to the control quantity.

[0042] An embodiment of the present invention provides a control system simulation method for an on-orbit spacecraft. The simulation system can receive and store real telemetry data of the on-orbit spacecraft by setting a telemetry data storage unit. In the initial stage of ground simulation, such as the first control cycle, the telemetry data at a preset time in the telemetry data storage unit can be retrieved. Since the telemetry data comes from the data of a real spacecraft flying in orbit, it can accurately represent the real state of the spacecraft. Therefore, by constructing the initial parameters of the simulation system based on the telemetry data and performing simulation calculations based on the simulation parameters, the initial parameters can be made consistent with the on-orbit state, thereby improving the accuracy of the initial parameters. In addition, by performing simulation calculations based on telemetry data in some control cycles of the simulation, the simulation system can be continuously corrected, thereby further ensuring the consistency of the simulation system with the real on-orbit control system state and improving the accuracy of ground simulation system verification. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0044] Figure 1 is a flow chart of a control system simulation method for an on-orbit spacecraft provided by an embodiment of the present invention;

[0045] Figure 2 It is a schematic diagram of a simulation system of an on-orbit spacecraft control system provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0046] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0047] The specific implementation of the above concept is described below.

[0048] Please refer to Figure 1The embodiment of the present invention provides a control system simulation method for on-orbit operation, which is applied to the host computer of the simulation system of the on-orbit spacecraft control system, wherein the simulation system includes a sensor simulation unit, a GNC controller simulation unit, an actuator simulation unit, a dynamic model and a telemetry data storage unit; the sensor simulation unit, the GNC controller simulation unit, the actuator simulation unit and the dynamic model are connected in sequence, and the telemetry data storage unit is connected to the GNC controller simulation unit; the sensor simulation unit is used to output the measurement state of the spacecraft based on the excitation information output by the dynamic model; the telemetry data storage unit is used to receive and store the real telemetry data of the on-orbit spacecraft; the GNC controller simulation unit is used to issue control instructions based on the measurement state or telemetry data; the actuator simulation unit is used to calculate mechanical information based on the control instructions; the dynamic model is used to output excitation information based on mechanical information;

[0049] Methods include:

[0050] Step 100, for the first control cycle, the GNC controller simulation unit constructs initial parameters of the simulation system based on the telemetry data at a preset time in the telemetry data storage unit, and performs simulation calculations for the control cycle based on the initial parameters; the initial parameters include initial conditions and initial simulation inputs;

[0051] Step 102, for other control cycles, execute: determine whether to use the telemetry data stored in the telemetry data storage unit to participate in the simulation calculation of the control cycle; if so, the GNC controller simulation unit retrieves the telemetry data at the corresponding moment, and performs the simulation calculation of the control cycle based on the retrieved telemetry data; if not, perform the simulation calculation of the control cycle based on the measurement state output by the sensor simulation unit.

[0052] In this embodiment, the simulation system can receive and store the real telemetry data of the on-orbit spacecraft by setting a telemetry data storage unit. In the initial stage of ground simulation, such as the first control cycle, the telemetry data at the preset time in the telemetry data storage unit can be retrieved. Since the telemetry data comes from the real on-orbit spacecraft data, it can accurately represent the real state of the spacecraft. Therefore, by constructing the initial parameters of the simulation system based on the telemetry data and performing simulation calculations based on the simulation parameters, the initial parameters can be consistent with the on-orbit state, thereby improving the accuracy of the initial parameters. In addition, by performing simulation calculations based on telemetry data in some control cycles of the simulation, the simulation system can be continuously corrected, thereby further ensuring the consistency of the simulation system with the real on-orbit control system state and improving the accuracy of the ground simulation system verification. It should be noted that the measurement state output by the sensor simulation unit can be the attitude of the spacecraft relative to the orbiting target such as the earth or the sun. The control instruction can be the operation execution of the actuator, such as the switch instruction of the engine. The operating state of the spacecraft is represented by mechanical information.

[0053] In addition, the initial conditions may include the attitude of the spacecraft, and the simulation input may include the mass and inertia of the spacecraft, etc., which can be determined independently by the user according to needs.

[0054] In some embodiments, a telemetry data inverse assignment function is stored in the GNC controller simulation unit, and the inverse assignment function is used to unpack and assign telemetry data, and determine the software variables of the GNC controller simulation unit based on the unpacked and assigned data; when working, the GNC controller simulation unit calculates the spacecraft control quantity based on the software variables, and issues control instructions according to the control quantity.

[0055] In this embodiment, by adopting the telemetry data inverse assignment function, the telemetry data can be used to assign values ​​to corresponding software variables in the controller simulation unit, thereby constructing initial conditions or initial simulation inputs based on the telemetry data, thereby improving the accuracy of the simulation system.

[0056] In some embodiments, the GNC controller simulation unit constructs initial parameters of the simulation system based on the telemetry data at a preset time in the telemetry data storage unit, including:

[0057] Retrieving telemetry data at a preset time from a telemetry data storage unit based on a GNC controller simulation unit;

[0058] Unpack and assign values ​​to the retrieved telemetry data based on the inverse assignment function;

[0059] Determine the initial parameters of the simulation system based on the unpacked assigned data.

[0060] In this embodiment, the preset time is determined according to user needs.

[0061] In some implementations, performing simulation calculation of the control cycle based on initial parameters includes:

[0062] Based on the initial parameters, the software variables of the GNC controller simulation unit are determined using the inverse assignment function of the telemetry data; based on the software variables, the GNC controller simulation unit is used to calculate the spacecraft control quantity and issue control instructions according to the control quantity;

[0063] Based on the control instruction, the actuator simulation unit is used to output the mechanical information of the control cycle;

[0064] Based on the mechanical information, using a dynamics simulation unit to output excitation information of the control cycle;

[0065] Based on the excitation information, the sensor simulation unit is used to output the measurement state of the next control cycle.

[0066] In this step, by setting the inverse assignment function, the unpacked telemetry data can be inverted to obtain the software variables corresponding to the telemetry data, and then the control quantity and control instructions can be calculated based on the software variables.

[0067] In some implementations, the criteria for determining whether to use the telemetry data stored in the telemetry data storage unit to participate in the simulation calculation of a certain control cycle are:

[0068] Whether the difference between the corresponding telemetry data in the control cycle and the measurement state output by the sensor simulation unit exceeds the preset value, if so, the telemetry data is used to participate in the simulation calculation of the control cycle, otherwise, the measurement state output by the sensor simulation unit is used to perform the simulation calculation of the control cycle.

[0069] In this step, when the difference between the telemetry data and the measured state is large, it means that there is a large difference between the simulation system and the actual on-orbit state. At this time, the telemetry data needs to be used to correct the simulation system to improve the calculation accuracy of the simulation system.

[0070] In some implementations, the criteria for determining whether to use the telemetry data stored in the telemetry data storage unit to participate in the simulation calculation of a certain control cycle are:

[0071] Whether the number of simulation calculations based on the measurement state output by the sensor simulation unit exceeds the preset number, if so, the telemetry data is used to participate in the simulation calculation of the control cycle, otherwise, the measurement state output by the sensor simulation unit is used to perform the simulation calculation of the control cycle.

[0072] In this step, as the number of calculations increases, the calculation errors will gradually accumulate. Therefore, when the number of simulation calculations using the measurement state exceeds the preset number, the telemetry data stored in the telemetry data storage unit will be used for simulation calculations in the next control cycle to correct the simulation system, thereby improving the calculation accuracy of the simulation system.

[0073] In some implementations, performing simulation calculation of the control cycle based on the retrieved telemetry data includes:

[0074] Unpack and assign values ​​to the retrieved telemetry data based on the inverse assignment function to obtain the unpacked and assigned data;

[0075] Based on the unpacked assigned data, the software variables of the GNC controller simulation unit are determined using the telemetry data inverse assignment function; based on the software variables, the GNC controller simulation unit is used to calculate the spacecraft control quantity and issue control instructions according to the control quantity;

[0076] Based on the control instruction, the actuator simulation unit is used to output the mechanical information of the control cycle;

[0077] Based on the mechanical information, using a dynamics simulation unit to output excitation information of the control cycle;

[0078] Based on the excitation information, the sensor simulation unit is used to output the measurement state of the next control cycle.

[0079] In some implementations, performing simulation calculation of the control cycle based on the measurement state output by the sensor simulation unit includes:

[0080] Based on the measured state, the GNC controller simulation unit is used to calculate the spacecraft control quantity and issue control instructions according to the control quantity;

[0081] Based on the control instruction, the actuator simulation unit is used to output the mechanical information of the control cycle;

[0082] Based on the mechanical information, using a dynamics simulation unit to output excitation information of the control cycle;

[0083] Based on the excitation information, the sensor simulation unit is used to output the measurement state of the next control cycle.

[0084] In the above embodiment, a closed loop is formed once in each control cycle, and then the measurement state output by the sensor simulation unit is used for the next control cycle until the simulation ends.

[0085] like Figure 2 As shown, an embodiment of the present invention also provides a simulation system for an on-orbit spacecraft control system, including: a sensor simulation unit, a GNC controller simulation unit, an actuator simulation unit, a dynamic model and a telemetry data storage unit;

[0086] The sensor simulation unit is used to output the measurement state of the spacecraft based on the excitation information output by the dynamic model, and send the measurement state to the GNC controller simulation unit;

[0087] The telemetry data storage unit is used to receive and store real telemetry data of the on-orbit spacecraft and send the received telemetry data to the GNC controller simulation unit;

[0088] The GNC controller simulation unit is used to issue control instructions based on the measurement status or telemetry data, and send the control instructions to the actuator simulation unit;

[0089] The actuator simulation unit is used to calculate mechanical information based on the control command and send the calculated mechanical information to the dynamic model;

[0090] The dynamic model is used to output excitation information based on the mechanical information and send the excitation information to the sensor simulation unit.

[0091] In some embodiments, a telemetry data inverse assignment function is stored in the GNC controller simulation unit, and the inverse assignment function is used to unpack and assign telemetry data, and determine the software variables of the GNC controller simulation unit based on the unpacked and assigned data; when working, the GNC controller simulation unit calculates the spacecraft control quantity based on the software variables, and issues control instructions according to the control quantity.

[0092] In some embodiments, the telemetry data storage unit includes two communication interfaces; one communication interface is used to receive telemetry data sent by a real on-orbit spacecraft, and the other communication interface is used to send the telemetry data to the GNC controller simulation unit. In addition, the communication interface can be a hardware interface or a software interface, as long as data transmission can be completed, and this application does not make specific limitations.

[0093] In some embodiments, the telemetry data storage unit and the simulation system operate synchronously.

[0094] In some embodiments, the measured state includes an attitude of the spacecraft relative to the orbiting target.

[0095] In some implementations, the control instructions include control instructions for various actuators on the spacecraft.

[0096] Finally, it should be noted that, in this article, relational terms such as first, second, third and fourth are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the statement "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0097] The above is only a preferred implementation of the present application. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present application. These improvements and modifications should also be regarded as the scope of protection of the present application.

Claims

1. A control system simulation method for an on-orbit spacecraft, characterized in that: In a host computer of a simulation system for an on-orbit spacecraft control system, the simulation system includes a sensor simulation unit, a GNC controller simulation unit, an actuator simulation unit, a dynamics model, and a telemetry data storage unit; the sensor simulation unit, the GNC controller simulation unit, the actuator simulation unit, and the dynamics model are connected in sequence, and the telemetry data storage unit is connected to the GNC controller simulation unit; the sensor simulation unit is used to output a measurement state of the spacecraft based on excitation information output by the dynamics model; The telemetry data storage unit is used to receive and store real telemetry data of the on-orbit spacecraft; The GNC controller simulation unit is used to issue a control instruction based on the measurement status or the telemetry data; The actuator simulation unit is used to calculate mechanical information based on the control instruction; The dynamic model is used to output excitation information based on the mechanical information; The method comprises: For the first control cycle, the GNC controller simulation unit constructs initial parameters of the simulation system based on the telemetry data at a preset time in the telemetry data storage unit, and performs simulation calculations for the control cycle based on the initial parameters; the initial parameters include initial conditions and initial simulation inputs; For other control cycles, execute: Determine whether to use the telemetry data stored in the telemetry data storage unit to participate in the simulation calculation of the control cycle; if so, the GNC controller simulation unit retrieves the telemetry data at the corresponding moment, and performs the simulation calculation of the control cycle based on the retrieved telemetry data; if not, perform the simulation calculation of the control cycle based on the measurement state output by the sensor simulation unit.

2. The method according to claim 1, characterized in that The GNC controller simulation unit stores an inverse assignment function of telemetry data; the inverse assignment function is used to unpack and assign values ​​to the telemetry data, and determine the software variables of the GNC controller simulation unit based on the unpacked and assigned data; when working, the GNC controller simulation unit calculates the spacecraft control quantity based on the software variables, and issues control instructions according to the control quantity.

3. The method according to claim 2, characterized in that The GNC controller simulation unit constructs the initial parameters of the simulation system based on the telemetry data at a preset time in the telemetry data storage unit, including: Retrieving telemetry data at a preset time from the telemetry data storage unit based on the GNC controller simulation unit; Unpacking and assigning values ​​to the retrieved telemetry data based on the inverse assignment function; The initial parameters of the simulation system are determined based on the unpacked and assigned data.

4. The method according to claim 3, characterized in that: The simulation calculation of the control cycle based on the initial parameters includes: Based on the initial parameters, the software variables of the GNC controller simulation unit are determined using the telemetry data inverse assignment function; based on the software variables, the spacecraft control quantity is calculated using the GNC controller simulation unit, and a control instruction is issued according to the control quantity; Based on the control instruction, using the actuator simulation unit to output mechanical information of the control cycle; Based on the mechanical information, using the dynamics simulation unit to output the excitation information of the control cycle; Based on the excitation information, the sensor simulation unit is used to output the measurement state of the next control cycle.

5. The method according to claim 1, characterized in that The criteria for determining whether to use the telemetry data stored in the telemetry data storage unit to participate in the simulation calculation of a certain control cycle are: Whether the difference between the corresponding telemetry data in the control cycle and the measurement state output by the sensor simulation unit exceeds the preset value, if so, the telemetry data is used to participate in the simulation calculation of the control cycle, otherwise, the measurement state output by the sensor simulation unit is used to perform the simulation calculation of the control cycle.

6. The method according to claim 1, characterized in that The criteria for determining whether to use the telemetry data stored in the telemetry data storage unit to participate in the simulation calculation of a certain control cycle are: Whether the number of simulation calculations based on the measurement state output by the sensor simulation unit exceeds a preset number, if so, the telemetry data is used to participate in the simulation calculation of the control cycle, otherwise, the measurement state output by the sensor simulation unit is used to perform the simulation calculation of the control cycle.

7. The method according to claim 2, characterized in that The simulation calculation of the control cycle is performed based on the retrieved telemetry data, including: Unpacking and assigning values ​​to the retrieved telemetry data based on the inverse assignment function to obtain unpacked and assigned data; Based on the unpacked assigned data, the software variables of the GNC controller simulation unit are determined by using the telemetry data inverse assignment function; based on the software variables, the spacecraft control quantity is calculated by using the GNC controller simulation unit, and a control instruction is issued according to the control quantity; Based on the control instruction, using the actuator simulation unit to output mechanical information of the control cycle; Based on the mechanical information, using the dynamics simulation unit to output the excitation information of the control cycle; Based on the excitation information, the sensor simulation unit is used to output the measurement state of the next control cycle.

8. The method according to claim 1, characterized in that: The control cycle is simulated and calculated based on the measurement state output by the sensor simulation unit, including: Based on the measurement state, using the GNC controller simulation unit to calculate the spacecraft control quantity, and issuing a control instruction according to the control quantity; Based on the control instruction, using the actuator simulation unit to output mechanical information of the control cycle; Based on the mechanical information, using the dynamics simulation unit to output the excitation information of the control cycle; Based on the excitation information, the sensor simulation unit is used to output the measurement state of the next control cycle.

9. A simulation system for an on-orbit spacecraft control system, characterized in that: include: Sensor simulation unit, GNC controller simulation unit, actuator simulation unit, dynamic model and telemetry data storage unit; The sensor simulation unit is used to output the measurement state of the spacecraft based on the excitation information output by the dynamic model, and send the measurement state to the GNC controller simulation unit; The telemetry data storage unit is used to receive and store real telemetry data of the on-orbit spacecraft, and send the received telemetry data to the GNC controller simulation unit; The GNC controller simulation unit is used to issue a control instruction based on the measurement state or the telemetry data, and send the control instruction to the actuator simulation unit; The actuator simulation unit is used to calculate mechanical information based on the control instruction and send the calculated mechanical information to the dynamic model; The dynamic model is used to output excitation information based on the mechanical information, and send the excitation information to the sensor simulation unit.

10. The system according to claim 9, characterized in that The GNC controller simulation unit stores a telemetry data inverse assignment function, which is used to unpack and assign values ​​to the telemetry data, and determine the software variables of the GNC controller simulation unit based on the unpacked and assigned data; when working, the GNC controller simulation unit calculates the spacecraft control quantity based on the software variables, and issues control instructions according to the control quantity.

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