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Satellite posture track control system based on SmartFushion 2 and PID control method of satellite posture track control system

An attitude control and satellite technology, applied in three-dimensional position/channel control, etc., can solve the problems of high cost, complex hardware circuit, large size, etc., and achieve the effect of low power consumption, small size, and simple design

Active Publication Date: 2014-11-19
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] The purpose of the present invention is to solve the problems of complex hardware circuits, large volume and high cost of the current spacecraft atti

Method used

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  • Satellite posture track control system based on SmartFushion 2 and PID control method of satellite posture track control system
  • Satellite posture track control system based on SmartFushion 2 and PID control method of satellite posture track control system
  • Satellite posture track control system based on SmartFushion 2 and PID control method of satellite posture track control system

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Experimental program
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specific Embodiment approach 1

[0051] Specific implementation mode one: combine figure 1 Describe this embodiment, the satellite attitude and orbit control system based on SmartFusion2 described in this embodiment, it comprises core processor, AD module, gyro module, wireless module and base plate module;

[0052] The core processor is realized by a SmartFusion2 chip that integrates an inherently reliable flash FPGA architecture, a 166MHz ARM Cortex-M3 processor, a security processing accelerator, a DSP module, SRAM, eNVM and multiple communication interface modules on a single chip of;

[0053] The core processor is used to control data acquisition and reception, process the received data, and output commands to control satellite attitude and satellite orbit;

[0054] The gyro module is used to measure the angular velocity information of the three axes of the satellite, and sends the angular velocity information to the core processor module;

[0055] AD module, used for telemetry acquisition channel, col...

specific Embodiment approach 2

[0074] Specific implementation mode two: combination figure 2 Describe this embodiment, this embodiment is the further limitation to the satellite attitude control system based on SmartFusion2 described in specific embodiment one, described multiple communication interface modules also include MSS unit peripheral interface module and FPGA unit peripheral interface module;

[0075] MSS unit peripheral interface module includes CAN protocol communication interface module, SPI protocol communication interface module, synchronous serial port communication interface module, I2C protocol communication interface module and peripheral 32-bit GPIO module,

[0076] CAN protocol communication interface module, SPI protocol communication interface module, synchronous serial port communication interface module, I2C protocol communication interface module and peripheral 32-bit GPIO module are all drawn from the MSS unit of the core processor;

[0077]CAN protocol communication interface m...

specific Embodiment approach 3

[0090] Embodiment 3: This embodiment is a further limitation of the SmartFusion2-based satellite attitude and orbit control system described in Embodiment 2. The gyro module is realized by using a CRG20 single-axis micro-gyroscope.

[0091] In this embodiment, the characteristics of CRG20 single-axis micro-gyroscope:

[0092] Unique COS2θ silicon ring MEMS technology;

[0093] Full digital closed-loop control;

[0094] Work in the full temperature range, stable performance, small drift, no need for temperature compensation and calibration;

[0095] Built-in temperature sensor;

[0096] There are two ways of SPI and analog rate output;

[0097] Digital resolution 0.03125° / s;

[0098] Angular random walk coefficient is very small, 0.3° / rt hr;

[0099] Strong resistance to vibration and impact;

[0100] Two auxiliary ADC inputs;

[0101] Measuring range: ±75° / s and ±300° / s optional;

[0102] Sensitive polarity: clockwise rotation, the output is positive;

[0103] Small s...

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Abstract

The invention belongs to the field of satellite posture track control, and relates to a satellite posture track control system based on SmartFusion2 and a PID control method of the satellite posture track control system to solve the problems that an existing spacecraft posture track control system is complex in hardware circuit, large in size and high in cost. One single chip is integrated with inherent reliability quick flashing FPGA architecture, a 166 MHz ARM Cortex-M3 processor, a safe processing accelerator, a DSP module, an SRAM, an eNVM and a SmartFusion2 chip of a plurality of communication interface modules, an AD module, a gyro module, a wireless module and a baseplate module are matched, and then the satellite posture track can be controlled. The baseplate module comprises a plurality of communication interfaces, a control power source, a state input interface, an OC drive interface, a debugging interface and a reset circuit. According to the PID control method, received data are judged, resolved and packaged through a core processor and an upper computer respectively to form a closed loop. The satellite posture track control system based on SmartFusion2 and a PID control method of the satellite posture track control system are used for controlling the satellite posture track.

Description

technical field [0001] The invention belongs to the field of satellite attitude control. Background technique [0002] With a series of advantages such as flexible radiation, low cost, high functional density, and short development cycle, microsatellites have become a hot spot in the current international space technology research. Developed countries are at the forefront of this technology, benefiting both civilian and military applications. As the potential of micro-satellites in remote sensing, communication, navigation, and space attack and defense is constantly being tapped, people hope that micro-satellites can respond quickly and do not need ground maintenance after launch. These capabilities are closely related to the attitude control system. of. [0003] The attitude control computer plays an important role in the attitude control system. It needs to complete multiple functions such as sensor data acquisition, attitude control, and orbit control. At present, in t...

Claims

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Application Information

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IPC IPC(8): G05D1/10
Inventor 杜少鹤郭延宁李伦波陈辰孙延超马广富李传江
Owner HARBIN INST OF TECH
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