Spacecraft electric propulsion system-level simulation model

Abstract

The invention discloses a spacecraft electric propulsion system-level simulation model, which comprises an industrial personal computer (including test equipment), an EPCU simulator, a ground remote control and telemetering system, a storage and supply subsystem and a PPUamp, a TSU subsystem; the system comprises a ground remote control and telemetering system, a storage and supply subsystem and a PPUamp. The TSU subsystems are all real systems; the EPCU simulator comprises a ground remote control and telemetering system data interaction module, a storage and supply subsystem data communication module and a PPUamp; the TSU subsystem comprises a data communication module and a satellite-borne EPCU application module; the industrial personal computer is used for realizing task scheduling of the satellite-borne EPCU application module, calling of the ground remote control and telemetering system data interaction module, calling of the storage and supply subsystem data communication module and PPUamp; and calling a data communication module of the TSU subsystem. According to the method, the design scheme of the satellite electric propulsion system can be quickly verified on the premise that no satellite-borne electric propulsion control unit (EPCU) exists, and the method is suitable for verifying the feasibility of scheme design and the conformity condition of functional performance indexes of products selected by the system in the early stage of system design.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft technology, and in particular to a spacecraft electric propulsion system-level simulation model. Background Art

[0002] With the increase in the number of spacecraft electric propulsion system missions and the shortening of development cycles, especially for newly developed bidding systems and products, the feasibility of the system design and the compliance of the functional performance indicators of the system selected products need to be verified during the system design phase.

[0003] However, during the system design, the electric propulsion control unit EPCU (Electrical Propulsion Control Unit) was in the design demonstration stage, and it was impossible to develop a practical product in a short period of time. On the other hand, the system lacked a digital simulation model of the electric propulsion product, and it was impossible to implement digital simulation verification of the system solution. How to quickly verify the correctness of the satellite electric propulsion system design without the electric propulsion control unit EPCU, this problem needs to be solved. Summary of the invention

[0004] The purpose of the present invention is to overcome the above difficulties and provide a spacecraft electric propulsion system-level simulation model to solve the problem of lack of system-level simulation environment in the electric propulsion system design stage. The present invention can quickly verify the satellite electric propulsion system design without an onboard electric propulsion control unit EPCU, and is suitable for verifying the feasibility of the design scheme and the conformity of the functional performance indicators of the system selected products in the early stage of system design.

[0005] In order to achieve the above-mentioned object of the invention, the present invention provides the following technical solutions:

[0006] A spacecraft electric propulsion system-level simulation model, including: an industrial computer (including test equipment), an EPCU (Electrical Propulsion Control Unit) simulator, a ground remote control and telemetry system, a storage and supply subsystem, and a PPU&TSU (Power Processing Unit&Thruster Switch Unit) subsystem;

[0007] The ground remote control and telemetry system, storage and supply subsystem, and PPU&TSU subsystem are all real systems;

[0008] The EPCU simulator includes a ground remote control and telemetry system data interaction module, a storage and supply subsystem data communication module, a PPU&TSU subsystem data communication module and an onboard EPCU application module; the storage and supply subsystem data communication module realizes data communication between the onboard EPCU application module and the storage and supply subsystem; the PPU&TSU subsystem data communication module realizes data communication between the onboard EPCU application module and the PPU&TSU subsystem; the ground remote control and telemetry system data interaction module realizes data interaction between the onboard EPCU application module and the ground remote control and telemetry system; the onboard EPCU application module realizes the system-level functional requirements of the electric propulsion system.

[0009] The industrial computer realizes the task scheduling of the onboard EPCU application module, the calling of the ground remote control and telemetry system data interaction module, the calling of the storage and supply subsystem data communication module and the calling of the PPU&TSU subsystem data communication module.

[0010] Furthermore, the data communication module of the storage and supply subsystem is simulated by an analog board connecting the hardware interface chip used to connect the EPCU simulator and the storage and supply subsystem; the data communication module of the PPU&TSU subsystem is simulated by an analog board of the bus interface chip used for data exchange between the EPCU simulator and the PPU&TSU subsystem; the EPCU simulator and the ground remote control and telemetry system run on an industrial computer, and the data interaction module between the EPCU simulator and the ground remote control and telemetry system is a shared memory of the industrial computer.

[0011] Furthermore, the hardware interface chip simulation board of the EPCU simulator simulates the hardware interface chip of the real onboard EPCU, the bus interface chip simulation board of the EPCU simulator simulates the bus interface chip of the real onboard EPCU, and the onboard EPCU application module of the EPCU simulator is a real EPCU application module.

[0012] Furthermore, the DDI (Device Driver Interface) interface of the EPCU simulator hardware interface chip simulation board is identical to the DDI interface definition of the onboard EPCU hardware interface chip;

[0013] The DDI interface of the EPCU simulator bus interface chip simulation board has the same definition as the DDI interface of the bus interface chip for data exchange between the onboard EPCU and PPU&TSU subsystems;

[0014] The shared memory and access interface of the industrial computer between the onboard EPCU application module and the ground remote control and telemetry system are defined by the onboard EPCU application module and are visible to the onboard EPCU application module and the ground remote control and telemetry system.

[0015] Furthermore, the industrial computer implements the task scheduling of the onboard EPCU application module by calling the task scheduling interface of the EPCU;

[0016] Based on the onboard EPCU system requirement document, define the task scheduling interface of the onboard EPCU application module.

[0017] Furthermore, the shared memory and access interface between the onboard EPCU application module and the ground remote control and telemetry system are defined as follows:

[0018] Based on the electric propulsion system remote control command document, define the shared memory and access interface for storing remote control commands (including the starting address, size, and access interface of the shared memory); the ground remote control telemetry system stores the received remote control commands in the shared memory, and the onboard EPCU application module reads the command content through the shared memory access interface every cycle;

[0019] Based on the telemetry parameter document of the electric propulsion system, the shared memory and access interface for telemetry data storage are defined. The onboard EPCU application module updates the telemetry data through the shared memory access interface every cycle. The ground remote control telemetry system obtains the telemetry data through the shared memory access interface every cycle and transmits it to the ground.

[0020] Furthermore, the DDI interface of the EPCU simulator hardware interface chip simulation board is defined as follows:

[0021] Based on the EPCU hardware module instruction manual, obtain the hardware connection interface between EPCU and the storage and supply subsystem, and define the DDI interface of the onboard EPCU hardware interface chip.

[0022] Furthermore, the EPCU simulator PPU&TSU bus interface chip simulates the DDI interface of the board and is defined as follows:

[0023] Based on the EPCU hardware module instruction manual, obtain the bus interface chip type and data transmission protocol for data interaction between the onboard EPCU application module and the PPU&TSU subsystem, and define the DDI of the bus interface chip for data interaction between the onboard EPCU and the PPU&TSU subsystem.

[0024] Furthermore, the present invention provides a spacecraft electric propulsion system-level simulation model for performing electric propulsion system-level test verification, including:

[0025] S1 connects the modules of the electric propulsion system simulation model;

[0026] S2 starts the industrial computer and runs the spacecraft electric propulsion system-level simulation model;

[0027] S3 directly commands the storage and supply subsystem and PPU&TSU subsystem to power on through the industrial computer;

[0028] S4 obtains system telemetry data through the remote control telemetry system and judges the correctness of the communication status and working status of each module of the EPCU simulator;

[0029] S5 injects instructions corresponding to the system-level functions to be verified through the remote control telemetry system;

[0030] S6 obtains system telemetry data through the remote control telemetry system, interprets key parameters of the system-level functions to be verified, and conducts simulation verification of system functions;

[0031] The S7 simulation verification is completed and each functional module is closed.

[0032] Compared with the prior art, the present invention has at least one of the following beneficial effects:

[0033] (1) The present invention provides a spacecraft electric propulsion system-level simulation model, which can quickly verify the satellite electric propulsion system design without an onboard electric propulsion control unit EPCU;

[0034] (2) The present invention clarifies the working interface between the onboard EPCU, PPU & TSU subsystems, and the ground telemetry and remote control system, defines the interface between the modules, decouples the system modules, and reduces the impact of functional module changes;

[0035] (3) The DDI (Device Driver Interface) interface of the EPCU simulator chip of the present invention is exactly the same as the DDI interface definition of the real onboard EPCU hardware interface chip. The user can select one of the two DDI interface implementation methods according to the actual application scenario. It is simple and reliable, and can be switched with one key.

[0036] (4) The present invention adds two commercial simulation boards to the industrial computer used in the real electric propulsion system test equipment, which is low in cost and easy and fast to expand;

[0037] (5) The ground telemetry and remote control system of the present invention can be fully reused in the real electric propulsion system test environment, realizing the early verification of the ground system in the system design phase;

[0038] (6) The onboard EPCU application module in the present invention is a real on-orbit EPCU application module, which realizes the early verification of onboard system-level functions and saves valuable development time for system design verification;

[0039] (7) The interface definitions in the present invention are fully reused (DDI interface definition of the hardware simulation board, DDI interface definition of the bus simulation board, and remote control telemetry data interface definition), with fast environment construction speed, high software reuse rate, strong portability, and can be promoted and applied to all electric propulsion systems, especially suitable for system or product bidding;

[0040] (8) The spacecraft electric propulsion system-level simulation model proposed in the present invention eliminates the coupling between the onboard electric propulsion control unit EPCU application module and the hardware module, solves the problem that system verification depends on the electric propulsion control unit EPCU, and can be used to quickly verify the various indicators of the electric propulsion system solution and product. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 A flow chart for designing a spacecraft electric propulsion system-level simulation model of the present invention;

[0042] Figure 2 This is a schematic diagram of the composition and structure of a real satellite-borne electric propulsion system;

[0043] Figure 3 A schematic diagram of the composition structure of the electric propulsion system simulation model provided by the present invention; DETAILED DESCRIPTION

[0044] The following detailed description of the present invention will make the features and advantages of the present invention more clear and explicit.

[0045] The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Although various aspects of the embodiments are shown in the drawings, the drawings are not necessarily drawn to scale unless otherwise noted.

[0046] The present invention provides a spacecraft electric propulsion system-level simulation model, which is used to verify the feasibility of the electric propulsion system solution and whether the indicators of the system's selected products (such as newly developed products such as proportional flow controllers) meet the design requirements.

[0047] like Figure 2 The real onboard EPCU (Electrical Propulsion Control Unit) includes a processor system, a hardware interface chip for connecting the storage and supply subsystem products, a bus interface chip for data interaction with the PPU&TSU (Power Processing Unit&ThrusterSwitch Unit) subsystem, a bus interface chip for data interaction with the ground remote control and telemetry system, and an EPCU application module.

[0048] like Figure 3The spacecraft electric propulsion system-level simulation model of the present invention includes: an industrial computer, an EPCU simulator, a ground remote control and telemetry system, a storage and supply subsystem, and a PPU&TSU subsystem.

[0049] The industrial computer component unit includes a commercial CPU (Intel series) and a Windows operating system. The EPCU simulator and the ground remote control and telemetry system run on the industrial computer. The industrial computer's Windows operating system completes the scheduling of the EPCU application module, the communication scheduling with the PPU&TSU subsystem, and the scheduling of the ground remote control and telemetry system; the EPCU simulator completes the software and hardware functions of the onboard EPCU; the ground remote control and telemetry system is used for human-computer interaction between the satellite and the ground system;

[0050] The EPCU simulator runs on the industrial computer CPU (Intel series). The main modules include the hardware interface chip simulation board connected to the storage and supply subsystem, the bus interface chip simulation board for data interaction with the PPU&TSU subsystem, and the EPCU application module.

[0051] The storage and supply subsystem, PPU&TSU subsystem are real products of the satellite-borne electric propulsion system.

[0052] In a specific implementation, the windows operating system of the industrial computer is responsible for the task scheduling of the EPCU application module, the DDI call of the bus interface chip simulation board, the data communication call with the PPU&TSU subsystem, the scheduling of the ground remote control and telemetry system, and the management of shared memory between the EPCU application module and the ground remote control and telemetry system.

[0053] In a specific implementation, the hardware interface chip simulation board of the EPCU simulator simulates the real EPCU hardware interface chip, the bus interface chip simulation board of the EPCU simulator simulates the bus interface chip of the real onboard EPCU, and the onboard EPCU application module of the EPCU simulator is a real EPCU application module.

[0054] In a specific implementation, the EPCU simulator application module and the ground remote control telemetry system run on the industrial computer CPU (Intel series), and data exchange is completed between the two through shared memory and access interface, which is different from the way the real electric propulsion control unit EPCU and the ground remote control telemetry system use bus interface chips for data exchange.

[0055] In a specific implementation, the EPCU simulator hardware interface chip simulation board and the bus interface chip simulation board are commercial boards;

[0056] The EPCU application module is a real onboard software product that realizes the system-level functional requirements of the electric propulsion system.

[0057] In a specific implementation, the DDI interface of the EPCU simulator hardware interface chip simulation board is defined identically to the DDI interface of the real onboard EPCU hardware interface chip;

[0058] The DDI interface of the EPCU simulator bus interface chip simulates the board, which has the same definition as the DDI interface of the bus interface chip for data exchange between the real onboard EPCU and PPU&TSU subsystems;

[0059] The shared memory and access interface between the EPCU application module and the ground remote control and telemetry system are defined by the EPCU application module and are visible to the EPCU application module and the ground remote control and telemetry system;

[0060] In a specific implementation, the EPCU task scheduling interface, the shared memory and access interface between the EPCU application module and the ground remote control and telemetry system, and the DDI interface include:

[0061] (1) Define the task scheduling interface of EPCU: Based on the electric propulsion control unit EPCU system requirement document, define the task scheduling interface AppTask of the EPCU application module;

[0062] (2) Define the shared interface between the EPCU application module and the ground remote control and telemetry system:

[0063] Based on the electric propulsion system remote control command document, obtain the type of remote control command, define the corresponding remote control command shared memory and access interface; the ground remote control telemetry system stores the received remote control command into the remote control command shared memory, and the EPCU application module reads the command content through the shared memory access interface every cycle to complete the command processing;

[0064] Based on the telemetry parameter document of the electric propulsion system, the shared memory and access interface for telemetry data storage are defined. The EPCU application module updates the telemetry data through the shared memory access interface every cycle. The ground remote control telemetry system obtains the telemetry data through the shared memory access interface every cycle and transmits it to the ground.

[0065] (3) Define the DDI interface of the EPCU hardware interface chip:

[0066] Based on the EPCU hardware module instruction manual, obtain the bus interface chip type and data transmission protocol for data interaction between the onboard EPCU application module and the PPU&TSU subsystem, and define the DDI of the bus interface chip for data interaction between the onboard EPCU and the PPU&TSU subsystem.

[0067] (4) Define the DDI interface of the bus interface chip for data interaction between the EPCU and the PPU&TSU subsystem: Based on the EPCU hardware module instruction manual, obtain the bus interface chip type and data transmission protocol for data interaction between the onboard EPCU application module and the PPU&TSU subsystem, and define the DDI of the bus interface chip for data interaction between the onboard EPCU and the PPU&TSU subsystem.

[0068] Example:

[0069] like Figure 1 As shown, the present invention provides a spacecraft electric propulsion system-level simulation model, including:

[0070] (1) Define the task scheduling interface of EPCU: Based on the onboard EPCU system requirement document, define the task scheduling interface AppTask of the onboard EPCU application module;

[0071] (2) Define the shared memory and access interface between the EPCU application module and the ground remote control and telemetry system:

[0072] Based on the electric propulsion system remote control command document, obtain the type of remote control command, define the corresponding remote control command shared memory and access interface; the ground remote control telemetry system stores the received remote control command into the remote control command shared memory, and the EPCU application module reads the command content through the shared memory access interface every cycle to complete the command processing;

[0073] Based on the telemetry parameter document of the electric propulsion system, the shared memory and access interface for telemetry data storage are defined. The EPCU application module updates the telemetry data through the shared memory access interface every cycle. The ground remote control telemetry system obtains the telemetry data through the shared memory access interface every cycle and transmits it to the ground.

[0074] (4) Define the DDI interface of the EPCU hardware interface chip:

[0075] Based on the EPCU hardware module instruction manual, obtain the hardware connection interface between EPCU and the storage and supply subsystem, and define the DDI interface of the onboard EPCU hardware interface chip.

[0076] (5) Define the DDI interface of the bus interface chip for data interaction between the EPCU and the PPU&TSU subsystem: Based on the EPCU hardware module instruction manual, obtain the bus interface chip type and data transmission protocol for data interaction between the onboard EPCU application module and the PPU&TSU subsystem, and define the DDI of the bus interface chip for data interaction between the onboard EPCU and the PPU&TSU subsystem.

[0077] (6) Based on the above shared memory and access interface and DDI interface definitions, complete the implementation of the hardware interface module;

[0078] (7) Integrate the EPCU simulator hardware interface chip simulation board and EPCU application module into the industrial computer;

[0079] (8) Task scheduling design: Based on the Windows operating system, complete the scheduling operation of the EPCU application module task AppTask, the communication between the EPCU simulator and the PPU&TSU subsystem, and the scheduling of the ground remote control and telemetry system functions;

[0080] (9) Complete the connection of system modules and start system testing and verification.

[0081] The specific steps are as follows:

[0082] a) Connect the modules of the electric propulsion system simulation model, including the industrial computer (test equipment), EPCU simulator, ground remote control and telemetry system, storage and supply subsystem, and PPU&TSU subsystem;

[0083] b) Start the industrial computer and run the spacecraft electric propulsion system-level simulation model;

[0084] c) Power on the storage and supply subsystem and the PPU & TSU subsystem through direct instructions from the industrial computer;

[0085] d) Obtain system telemetry data through the remote control telemetry system and judge the correctness of the communication status and working status of each module of the EPCU simulator;

[0086] e) Injecting commands corresponding to the “system functions to be verified” (such as electric propulsion autonomous ignition working mode) through the remote control and telemetry system;

[0087] f) Obtain system telemetry data through the remote control and telemetry system, interpret the key parameters of the "system function to be verified", and carry out simulation verification of the system function;

[0088] g) After the simulation verification is completed, close each functional module.

[0089] The present invention has been described in detail above in conjunction with specific implementations and exemplary examples, but these descriptions cannot be understood as limiting the present invention. Those skilled in the art understand that, without departing from the spirit and scope of the present invention, a variety of equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its implementation methods, all of which fall within the scope of the present invention. The scope of protection of the present invention shall be subject to the attached claims.

[0090] 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 spacecraft electric propulsion system-level simulation model, characterized in that: include: Industrial computer, EPCU simulator, ground remote control and telemetry system, storage and supply subsystem and PPU&TSU subsystem; The ground remote control and telemetry system, storage and supply subsystem, and PPU&TSU subsystem are all real systems; The EPCU simulator includes a ground remote control and telemetry system data interaction module, a storage and supply subsystem data communication module, a PPU&TSU subsystem data communication module and an onboard EPCU application module; the ground remote control and telemetry system data interaction module realizes data interaction between the onboard EPCU application module and the ground remote control and telemetry system; the storage and supply subsystem data communication module realizes data communication between the onboard EPCU application module and the storage and supply subsystem; the PPU&TSU subsystem data communication module realizes data communication between the onboard EPCU application module and the PPU&TSU subsystem; the onboard EPCU application module realizes the system-level functions of the electric propulsion system; The industrial computer realizes the task scheduling of the onboard EPCU application module, the calling of the ground remote control and telemetry system data interaction module, the calling of the storage and supply subsystem data communication module and the calling of the PPU&TSU subsystem data communication module.

2. A spacecraft electric propulsion system-level simulation model according to claim 1, characterized in that: The data communication module of the storage and supply subsystem is simulated by an analog board connecting the hardware interface chip used to connect the EPCU simulator and the storage and supply subsystem; the data communication module of the PPU&TSU subsystem is simulated by an analog board of the bus interface chip used for data exchange between the EPCU simulator and the PPU&TSU subsystem; the EPCU simulator and the ground remote control and telemetry system run on an industrial computer, and the data interaction module between the EPCU simulator and the ground remote control and telemetry system is a shared memory of the industrial computer.

3. A spacecraft electric propulsion system-level simulation model according to claim 2, characterized in that: The hardware interface chip simulation board of the EPCU simulator simulates the hardware interface chip of the real onboard EPCU, the bus interface chip simulation board of the EPCU simulator simulates the bus interface chip of the real onboard EPCU, and the onboard EPCU application module of the EPCU simulator is the real EPCU application module.

4. A spacecraft electric propulsion system-level simulation model according to claim 3, characterized in that: The DDI interface of the EPCU simulator hardware interface chip simulation board has the same definition as the DDI interface of the onboard EPCU hardware interface chip; The DDI interface of the EPCU simulator bus interface chip simulation board has the same definition as the DDI interface of the bus interface chip for data exchange between the onboard EPCU and PPU&TSU subsystems; The shared memory and access interface of the industrial computer between the onboard EPCU application module and the ground remote control and telemetry system are defined by the onboard EPCU application module and are visible to the onboard EPCU application module and the ground remote control and telemetry system.

5. A spacecraft electric propulsion system-level simulation model according to claim 4, characterized in that: The industrial computer implements the task scheduling of the onboard EPCU application module by calling the EPCU task scheduling interface; Based on the onboard EPCU system requirement document, define the task scheduling interface of the onboard EPCU application module.

6. A spacecraft electric propulsion system-level simulation model according to claim 4, characterized in that: The shared memory and access interface between the onboard EPCU application module and the ground remote control and telemetry system are defined as follows: Based on the electric propulsion system remote control command document, define the shared memory and access interface for storing remote control commands; the ground remote control telemetry system stores the received remote control commands in the remote control command shared memory, and the onboard EPCU application module reads the command content through the shared memory access interface every cycle; Based on the telemetry parameter document of the electric propulsion system, the shared memory and access interface for telemetry data storage are defined. The onboard EPCU application module updates the telemetry data through the shared memory access interface every cycle. The ground remote control telemetry system obtains the telemetry data through the shared memory access interface every cycle and transmits it to the ground.

7. A spacecraft electric propulsion system-level simulation model according to claim 4, characterized in that: The DDI interface of the EPCU simulator hardware interface chip simulation board is defined as follows: Based on the EPCU hardware module instruction manual, obtain the hardware connection interface between EPCU and the storage and supply subsystem, and define the DDI interface of the onboard EPCU hardware interface chip.

8. A spacecraft electric propulsion system-level simulation model according to claim 4, characterized in that: The EPCU simulator bus interface chip simulates the DDI interface of the board and is defined as follows: Based on the EPCU hardware module instruction manual, obtain the bus interface chip type and data transmission protocol for data interaction between the onboard EPCU application module and the PPU&TSU subsystem, and define the DDI of the bus interface chip for data interaction between the onboard EPCU and the PPU&TSU subsystem.

9. The spacecraft electric propulsion system-level simulation model according to claim 1, characterized in that: The industrial computer contains test equipment.

10. A spacecraft electric propulsion system-level simulation model according to claim 1, characterized in that: Used for electric propulsion system-level test and verification, including: S1 connects the modules of the electric propulsion system simulation model; S2 starts the industrial computer and runs the spacecraft electric propulsion system-level simulation model; S3 directly commands the storage and supply subsystem and PPU&TSU subsystem to power on through the industrial computer; S4 obtains system telemetry data through the remote control telemetry system and judges the correctness of the communication status and working status of each module of the EPCU simulator; S5 injects instructions corresponding to the system-level functions to be verified through the remote control telemetry system; S6 obtains system telemetry data through the remote control telemetry system, interprets key parameters of the system-level functions to be verified, and conducts simulation verification of system functions; The S7 simulation verification is completed and each functional module is closed.

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