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Attitude control IP core based on PD control law and satellite attitude control moment calculation system using the same

A satellite attitude control and attitude control technology, applied in the field of aerospace electronics, can solve the problems of low reusability and unfavorable rapid design of aerospace electronic systems, etc., and achieve the effects of increased calculation speed, good reusability, and good design foundation

Inactive Publication Date: 2013-04-10
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, this design method has low reusability, which is not conducive to the rapid design of aerospace electronic systems.

Method used

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  • Attitude control IP core based on PD control law and satellite attitude control moment calculation system using the same
  • Attitude control IP core based on PD control law and satellite attitude control moment calculation system using the same
  • Attitude control IP core based on PD control law and satellite attitude control moment calculation system using the same

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specific Embodiment approach 1

[0078] Specific implementation mode one, see figure 1 This embodiment will be described. A kind of attitude control IP core based on PD control law described in this embodiment comprises two subtractors and two multipliers, and this attitude control IP core adopts FPGA external input clock as calculation clock;

[0079] Among them, the reference attitude angle θ input by the positive input terminal of the first subtractor 11 c , the negative input terminal of the first subtractor 11 inputs the current attitude angle parameter, the output terminal output data of the first subtractor 11 is given to the first multiplier 12, and the first multiplier 12 is proportional to the data in the PD control algorithm Coefficient K P After multiplication, output product result data to the positive input end of the second subtractor 13;

[0080] The second multiplier 14 combines the input attitude angular velocity ω parameter with the differential coefficient K in the PD control algorithm ...

specific Embodiment approach 2

[0084] Specific Embodiment 2. Referring to FIG. 2, this embodiment will be described. This embodiment is a further description of the attitude control IP core based on the PD control law described in the first embodiment. Each calculation cycle of the attitude control IP core based on the PD control law in this embodiment is 5 clock cycles , the specific process is:

[0085] In the first clock cycle, the input reference attitude angle θ c Pass to the positive input end of the first subtractor 11, the current attitude angle passes to the negative input end of the first subtractor 11, and the attitude angular velocity ω passes to an input end of the second multiplier 14;

[0086] In the second clock cycle, the first subtractor 11 and the second multiplier 14 complete subtraction and multiplication respectively;

[0087] In the third clock cycle, the first multiplier 12 completes the multiplication operation, and the result of the second multiplier 14 is delayed by one cycle; ...

specific Embodiment approach 3

[0091] Specific implementation mode three, see image 3 To illustrate this embodiment, 2 in the figure is the satellite attitude control moment calculation system described in this embodiment. The satellite attitude control moment calculation system adopts the attitude control IP based on the PD control law described in the first or second embodiment. To achieve nuclear realization, the satellite attitude control moment calculation system described in this embodiment includes:

[0092] The processor core 21 is used to read the data required for calculating the attitude control moment through the external bus, and the data includes the reference attitude angle θ c , the current satellite attitude angle θ and angular velocity, and write the data into the data acquisition register; it is also used to read the attitude control torque data from the data output register through the on-chip bus and output it to the external data bus;

[0093] The data acquisition register unit 22 is...

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Abstract

The invention relates to a satellite attitude control moment calculation system of an attitude control IP core based on a PD control law, which relates to the aerospace electronics field, are disclosed. A purpose of the invention is to provide the attitude control IP core based on the PD control law with a fast calculating speed and high reusability and the satellite attitude control moment calculation system using the IP core. A FPGA external input clock is used as a calculating clock in the IP core. A subtracter is used to calculate difference between an input reference attitude angle theta c and a current attitude angle parameter and the difference is output to a multiplier. The multiplier is used to multiply the data by a proportionality coefficient KP so as to obtain a product. The multiplier is used to multiply an attitude angle speed omega by a P differential coefficient KD so as to obtain a result. The subtracter is used to calculate the difference between the result and the product so as to obtain an attitude moment. The control moment calculating system of the invention adopts the IP core to realize the moment operation. By using the IP core, compared to utilization of a current software method, the calculating speed at least is increased by 5 times. Reusability is good.

Description

technical field [0001] The invention relates to the field of aerospace electronics, in particular to a satellite attitude control-specific IP core and a design method based on a PD control law and implemented by a hardware description language for satellite applications. Background technique [0002] With the development of technology, there have been many discussions on the use of FPGA to implement various filtering algorithms and controllers at home and abroad, and the application of FPGA in the aerospace field is also increasing. Large-scale SRAM-based FPGAs, like antifuse-based FPGAs, can already be used in the aerospace field. The attitude control system based on FPGA is established, which utilizes the advantages of fast processing speed, simple structure and portability of FPGA, and replaces software calculation with hardware processing. It not only reduces the burden of the on-board computer, but also reduces the dependence of the attitude control on the on-board com...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
Inventor 张相宇张志刚于文进兰盛昌张锦绣曹喜滨林晓辉潘瑞马玉海
Owner HARBIN INST OF TECH
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