Analog simulation system for solar panel driving mechanism

Abstract

The invention discloses an analog simulation system for a solar panel driving mechanism. A software system of the analog simulation system comprises an SADA mathematical model module and an SADA interface module. The SADA mathematical model module can simulate the operation principle and the actual output of a real SADA product to the greatest extent; the SADA interface module is divided into a. Dll file algorithm calling sub-module, a fault configuration sub-module, a package sub-module, an RS422 interface sub-module and a visual operation interface; a. Dll file generated by the SADA mathematical model module is called based on the LABVIEW control function, the file output is subjected to fault selectable setting processing, packaging is carried out again according to a real product protocol, a program frame is simulated through an RS422 serial port, and real SADA product output simulation is completed; and finally, drawing a visual operation interface of the SADA analog simulator. Under the condition that a satellite platform system does not have a real solar panel driving structure, the functions of hardware interface accuracy testing between satellites, interface protocol rationality iteration, on-orbit control algorithm correctness verification and the like are achieved instead of the real solar panel driving structure.

Description

Technical Field

[0001] The present invention designs a solar sail panel driving mechanism, and specifically relates to a solar sail panel driving mechanism simulation system, which is applicable to the field of satellites equipped with a solar sail panel driving mechanism. Background Art

[0002] At present, most spacecraft are equipped with a sailboard drive device, namely the "solar array drive assembly (SADA)", which is used to drive the solar sailboard to achieve sun orientation, improve the power generation efficiency of the solar array, and ensure the energy supply of the satellite. In the prior art, a satellite using a two-dimensional dual-axis sailboard drive SADA device has two degrees of rotational freedom, the A axis can achieve 360° rotation, and the B axis can achieve swing within a limited angle range. However, in response to the needs of different application scenarios, such as the design and testing process of on-board SADA health management, it is necessary for the product to communicate with the satellite computer, and the special parameters returned by the product should be set to an abnormal state. The real product cannot meet this demand. At this time, the development of a digital SADA simulator is particularly important. At present, the development of a simulation simulator for a solar sailboard drive structure (abbreviated as SADA) on the market is basically blank. The proposal of this method can fill the gap in the market and provide technical reference and support for subsequent similar products. Summary of the invention

[0003] In view of the problems existing in the prior art, the present invention provides a solar panel drive mechanism simulation system, which solves the problem that when the satellite platform system does not have a real solar panel drive structure (SADA for short), it can replace it to realize the functions of hardware interface accuracy testing between the satellite and the satellite, rationality iteration of the interface protocol, and correctness verification of the on-orbit control algorithm.

[0004] The technical solution of the present invention is: a solar sail panel driving mechanism simulation system, wherein the software system includes a SADA mathematical model module and a SADA interface module;

[0005] The SADA mathematical model module can simulate the operating principle and actual output of the real SADA product to the maximum extent. The SADA mathematical model module uses the S-FUNCTION function in simulink to implement the model algorithm encapsulation, and generates a .dll file through compilation for the SADA interface module to call;

[0006] The SADA interface module is divided into a .dll file algorithm calling submodule, a fault configuration submodule, a package assembly submodule, an RS422 interface submodule and a visual operation interface; based on the LABVIEW control function, the .dll file generated by the SADA mathematical model module is called, the file output is processed by optional fault settings, and the package is reassembled according to the real product protocol. The real SADA product output simulation is completed through the RS422 serial port simulation program box; finally, the SADA simulation machine visual operation interface is drawn.

[0007] Furthermore, the calling .dll file algorithm submodule implements the SADA mathematical model by calling Take ModelTime Step VI in LABVIEW software.

[0008] Furthermore, the fault configuration submodule triggers the conditional structure control to enter the corresponding selection logic under different fault settings by calling the conditional structure control and the fault selection setting control in the LABVIEW software, thereby outputting the corresponding expected parameters.

[0009] Furthermore, the function of the packet assembly submodule is to recombine the SADA model output values ​​through the specified format of the SADA product communication protocol to form a packet format recognizable by the star service computer, thereby achieving normal communication with the star service computer.

[0010] Furthermore, the RS422 interface submodule calls the relevant functions in the VISA control library in the LABVIEW software according to the communication protocol between SADA and the satellite computer, so as to establish a data transmission channel for the communication between the SADA simulator and the satellite computer.

[0011] Furthermore, its hardware system includes a host computer, a MOXA box and supporting cables.

[0012] The beneficial effects of the present invention are: providing a solar panel drive mechanism simulation system, which solves the problem of the satellite platform system having no real solar panel drive structure (referred to as SADA), replacing it to implement the hardware interface accuracy test between the satellite and the satellite, the rationality iteration of the interface protocol, the correctness verification of the on-orbit control algorithm and other functions.

[0013] Advantages: 1. The development of this product fills the gap in the market and will provide technical reference and support for subsequent similar products; 2. The simulated output of fault output that cannot be achieved by a real single machine has a great auxiliary effect on the design and verification of autonomous health management of satellite platforms on orbit. 3. The interface is simple, visual and easy to operate; 4. The development and use of this product will greatly save the test and verification time of the satellite platform for the real SADA, and the test efficiency, comprehensiveness and reliability will be greatly improved; 5. It forms a closed-loop control with the on-orbit SADA control algorithm, responds to the control algorithm control instructions, and simulates the real SADA product to feedback the angle, speed and other information of SADA rotation to the control algorithm, providing strong support for the on-orbit whole satellite control algorithm; 6. The SADA mathematical model can reflect the actual output of the real SADA product, and has strong matching; 7. The product is designed with a unique fault configuration module, which can arbitrarily configure the fault state that the real product cannot output, supplement the limitations of the real product, and has stronger functions. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is the specific form of the SADA mathematical model module;

[0015] Figure 2 The specific application process for calling the .dll algorithm submodule;

[0016] Figure 3 Specific application process for fault configuration submodule;

[0017] Figure 4 To group the specific application process of the submodule;

[0018] Figure 5 The specific application process of RS422 serial port submodule;

[0019] Figure 6 This is a diagram of the visual operation interface;

[0020] Figure 7 It is the overall structure diagram of the SADA simulator;

[0021] Figure 8 is a schematic diagram of Example 1;

[0022] Fig. 9 is a schematic diagram of Example 2;

[0023] Fig.10 is a schematic diagram of Example 3;

[0024] Fig.11 and Fig.12 This is a schematic diagram of Example 4. DETAILED DESCRIPTION

[0025] The present invention will be further described below in conjunction with the accompanying drawings.

[0026] like Figure 7 As shown, the SADA simulation machine is divided into two parts, namely the hardware system and the software system. The hardware system includes the host computer, MOXA box and supporting cables; the software system includes the SADA mathematical model module and the SADA interface module.

[0027] The SADA mathematical model module can simulate the operating principle and actual output of the real SADA product to the greatest extent. This module uses the S-FUNCTION function in simulink to implement the model algorithm encapsulation and generates a .dll file through compilation for the interface module to call. The specific form is as follows Figure 2 shown.

[0028] The SADA interface module can be divided into a calling .dll file module, a fault configuration module, a package module, an RS422 interface module, and a visual operation interface. Based on the LABVIEW control function, the .dll file generated by the SADA mathematical model module is called, and the file output is processed with optional fault settings, and the package is reassembled according to the real product protocol. Through the RS422 serial port simulation program box, the real SADA product output simulation is completed. Finally, the visual operation interface of the SADA simulation machine is drawn.

[0029] The design of calling the .dll algorithm submodule implements the SADA mathematical model by calling the Take Model Time Step VI in the LABVIEW software. The specific application process is as follows Figure 2 shown.

[0030] The fault configuration submodule calls the conditional structure control and fault selection setting control in the LABVIEW software to trigger the conditional structure control under different fault settings to enter the corresponding selection logic, thereby outputting the corresponding expected parameters, such as Figure 3 shown.

[0031] The function of the packet assembly submodule is to reassemble the SADA model output values ​​into a packet format recognizable by the satellite computer through the specified format of the SADA product communication protocol, so as to achieve normal communication with the satellite computer. Figure 4 shown.

[0032] The RS422 serial port submodule is based on the communication protocol between SADA and the satellite computer, calling the relevant functions in the VISA control library in the LABVIEW software to establish a data transmission channel for the communication between the SADA simulator and the satellite computer. Figure 5 shown.

[0033] Visual operation interface such as Figure 6 shown.

[0034] Example 1

[0035] Secondary power supply abnormal configuration: when the parameter "Secondary power supply 24V" in the SADA telemetry data frame is not in the range of [22v, 26v], or the parameter "Secondary power supply 5V" is not in the range of (4.5v, 5.5v), it is considered that the SADA product has a secondary power supply abnormality, but the actual delivered product cannot simulate this fault state. In this case, the SADA simulator can replace the actual SADA product, and set "24V manual setting-fault, 24V setting constant value 40" and "5V manual setting-fault, 5V setting constant value 10" in the visual operation interface, such as Figure 8 shown.

[0036] Example 2

[0037] Overcurrent fault configuration: if the parameter "+Y_A axis overcurrent fault" in the SADA telemetry data frame is "1-fault", the +YA axis effective state is set to "+Y_A axis overcurrent abnormality"; -Y_A axis / +Y_B axis / -Y_B axis overcurrent abnormality judgment is the same as +Y_A axis; the actual delivery of SADA products cannot achieve this fault output on the ground, so the SADA simulator can replace it to achieve this function, form a closed loop with the control algorithm, and realize autonomous handling of on-orbit abnormalities. Fig. 9 shown.

[0038] Example 3

[0039] Over-temperature fault configuration, if the parameter "+Y_A axis drive over-temperature fault" in the SADA telemetry data frame is "1-fault", then the +YA axis effective state is set to "+Y_A axis drive over-temperature abnormality"; -Y_A axis / +Y_B axis / -Y_B axis drive over-temperature abnormality judgment is the same as +Y_A axis; the actual delivery of SADA products cannot achieve this fault output on the ground, so the SADA simulator can replace it to achieve this function, form a closed loop with the control algorithm, and realize autonomous handling of on-orbit abnormalities. Fig.10 shown.

[0040] Example 4

[0041] The fault configuration of excessive angle measurement deviation is as follows: if the absolute value of the difference between the parameter return value "+YA axis current angle - potentiometer" and "+Y_A axis current angle - motor" in the SADA telemetry data frame is greater than or equal to 2°, the effective state of the +YA axis is set to "+Y_A axis measurement deviation is too large".

[0042] The measurement deviation of -Y_A axis / +Y_B axis / -Y_B axis is too large and is judged to be the same as +Y_A axis.

[0043] Before configuration, the motor value and potentiometer value are both SADA mathematical model output values.

[0044] After configuration, the motor value and potentiometer value are both fault setting values, not SADA mathematical model outputs. The fault is manually set, and the angle output can be arbitrarily configured to achieve the threshold requirement of 2°, create an abnormal state of excessive angle measurement deviation, form a closed loop with the control algorithm, realize autonomous handling of on-orbit abnormalities, and identify stalls. Fig.11 , 12 shown.

[0045] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A solar panel driving mechanism simulation system, characterized in that: Its software system includes SADA mathematical model module and SADA interface module; The SADA mathematical model module can simulate the operating principle and actual output of the real SADA product to the maximum extent. The SADA mathematical model module uses the S-FUNCTION function in simulink to implement the model algorithm encapsulation, and generates a .dll file through compilation for the SADA interface module to call; The SADA interface module is divided into a .dll file algorithm calling submodule, a fault configuration submodule, a package assembly submodule, an RS422 interface submodule and a visual operation interface; based on the LABVIEW control function, the .dll file generated by the SADA mathematical model module is called, the file output is processed by optional fault settings, and the package is reassembled according to the real product protocol. The real SADA product output simulation is completed through the RS422 serial port simulation program box; finally, the SADA simulation machine visual operation interface is drawn.

2. The solar panel driving mechanism simulation system according to claim 1, characterized in that: The calling .dll file algorithm submodule implements the SADA mathematical model by calling the Take Model Time Step VI in the LABVIEW software.

3. The solar panel driving mechanism simulation system according to claim 1, characterized in that: The fault configuration submodule calls the conditional structure control and the fault selection setting control in the LABVIEW software to trigger the conditional structure control under different fault settings to enter the corresponding selection logic, thereby outputting the corresponding expected parameters.

4. The solar panel driving mechanism simulation system according to claim 1, characterized in that: The function of the packet assembly submodule is to recombine the SADA model output values ​​through the specified format of the SADA product communication protocol to form a packet format recognizable by the star service computer, thereby achieving normal communication with the star service computer.

5. The solar panel driving mechanism simulation system according to claim 1, characterized in that: The RS422 interface submodule calls the relevant functions in the VISA control library in the LABVIEW software according to the communication protocol between SADA and the satellite computer, and establishes a data transmission channel for the communication between the SADA simulator and the satellite computer.

6. The solar panel driving mechanism simulation system according to claim 1, characterized in that: Its hardware system includes a host computer, a MOXA box and supporting cables.

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