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Sun sensor simulator for satellite closed cycle simulation test

A solar sensor and closed-loop simulation technology, applied in the field of satellite testing, can solve the problems of complex operation and high cost, and achieve the effects of flexible control, reduced development cost, and shortened development cycle.

Inactive Publication Date: 2010-06-09
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The sun sensor used by the existing satellites in the ground simulation test is based on the scene-driven method. Only when it is irradiated by light can it output the corresponding signal. The operation is complicated and the cost is high.

Method used

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  • Sun sensor simulator for satellite closed cycle simulation test
  • Sun sensor simulator for satellite closed cycle simulation test
  • Sun sensor simulator for satellite closed cycle simulation test

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Experimental program
Comparison scheme
Effect test

specific Embodiment approach 1

[0014] Specific implementation mode one: the following combination Figure 1-Figure 3 To illustrate this embodiment, this embodiment consists of normal command control computer 1, fault command control computer 2, first RS422 chip 3, second RS422 chip 4, FPGA field programmable gate array 5, 0-1 solar signal source unit 6 , an analog sun signal source unit 7, a digital sun signal source unit 8 and a total power processing circuit 9,

[0015] The control signal output end of the normal command control computer 1 connects the normal command control signal input end of the FPGA field programmable gate array 5 through the first RS422 chip 3, and the fault command control signal input and output end of the FPGA field programmable gate array 5 passes through the second The RS422 chip 4 is connected to the failure signal output and input terminals of the fault command control computer 2; the 0-1 solar control signal output terminal of the FPGA field programmable gate array 5 is conne...

specific Embodiment approach 2

[0025] Specific implementation mode two: the following combination Figure 4 and Figure 7 To describe this embodiment, the difference between this embodiment and Embodiment 1 is that the 0-1 sun signal source unit 6 is composed of a first power processing circuit 6-1, a voltage conversion chip 6-2, and a reverse decay circuit 6 -3, composed of five first relays 6-4 and five first voltage-controlled current source circuits 6-5,

[0026] The power output end of the first power processing circuit 6-1 is connected to the power input end of the voltage conversion chip 6-2, and the power output end of the voltage conversion chip 6-2 is connected to the power input end of the reverse attenuation circuit 6-3, and the reverse attenuation The power output end of the circuit 6-3 is connected to the power input ends of five first relays 6-4, and the power output end of each first relay 6-4 is connected to the power input end of a first voltage-controlled current source circuit 6-5 ; Th...

specific Embodiment approach 3

[0036] Specific implementation mode three: the following combination Figure 5 To illustrate this embodiment, the difference between this embodiment and Embodiment 2 is that the simulated sun signal source unit 7 is composed of a digital-to-analog conversion chip 7-1 and four second voltage-controlled current source circuits 7-2,

[0037] The digital signal input end of the digital-to-analog conversion chip 7-1 is connected to the analog sun control signal output end of the FPGA field programmable gate array 5, and the analog signal output end of the digital-to-analog conversion chip 7-1 is connected to four second voltage-controlled current source circuits 7-2's power input. Other components and connections are the same as those in Embodiment 2.

[0038]The simulated sun signal source unit 7 is different from the 0-1 sun signal source unit 6, and what the simulated sun signal source unit 7 needs to obtain is a continuous output of current. Therefore, a digital-to-analog con...

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Abstract

The invention relates to a sun sensor simulator for satellite closed cycle simulation test, belonging to the field of satellite test; the sun sensor simulator simulates the signal output of three kinds of the sun sensors simultaneously; a normal instruction control computer and a fault instruction control computer transmit a normal work instruction and a fault work instruction to a FPGA field programmable gate array, a module in the FPGA field programmable gate array receives and processes the two instructions respectively, a data selection module ensures the preferential execution of the fault work instruction, and an error frame counting module counts the number of the fault work instructions in the normal work instruction and transmits to the fault instruction control computer, and the FPGA field programmable gate array outputs control data to a 0-1 sun signal source unit, a simulation signal source unit and a digital sun signal source unit respectively to lead the corresponding sun signal source unit to output the current. The sun sensor simulator is applied to the satellite closed cycle simulation test.

Description

technical field [0001] The invention relates to a sun sensor simulator used for satellite closed-loop simulation test, which belongs to the field of satellite test. Background technique [0002] The sun sensor (sun sensor) is a kind of sensor widely used in the field of satellites, and almost all satellites are equipped with sun sensors. It is an optical attitude sensor that determines the orientation of the sun vector in star coordinates by sensing the orientation of the sun vector, thereby obtaining the satellite's orientation information relative to the sun. Satellites are orbiting in outer space. Due to the strong solar radiation and clear outline, the solar sensor can easily sense the solar radiation and thus obtain the satellite's orientation relative to the sun. Solar sensors usually have the characteristics of simple structure, wide detectable field of view, reliable operation, low power consumption and small mass, and its resolution ranges from several degrees to s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/24
Inventor 赵光权马云彤彭宇乔立岩马勋亮彭喜元
Owner HARBIN INST OF TECH
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