Attitude and orbit control closed-loop semi-physical simulation test method applicable to quick response satellite

A technology of closed-loop testing and attitude control, applied in general control systems, electrical testing/monitoring, testing/monitoring control systems, etc., can solve the problems of insufficient verification and seamless connection, and achieve fast and accurate positioning , improve accuracy, and improve the effect of application rate

Active Publication Date: 2017-12-26
SHANGHAI AEROSPACE CONTROL TECH INST
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AI Technical Summary

Problems solved by technology

If Kinetics is connected directly to serial port 422 on the star, the conversion of 1750 floating-point and IEEE floating-point data formats needs to be converted by on-board software. When communicating, seamless connection cannot be achieved
The sub-system does not have a GPS simulator, and the design and implementation of the GPS part can only be verified when the whole satellite is completed. Due to time constraints, this part of the content cannot be fully verified.

Method used

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  • Attitude and orbit control closed-loop semi-physical simulation test method applicable to quick response satellite
  • Attitude and orbit control closed-loop semi-physical simulation test method applicable to quick response satellite

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Embodiment Construction

[0018] Such as figure 1 As shown, the present invention is suitable for a fast-response satellite attitude and orbit control closed-loop test method, the specific steps are as follows:

[0019] 1) When designing the integrated electronic computer, reserve one RS-422 serial port for communication with the ground equipment, which is used to establish a communication link with the ground. The integrated electronic computer sends force and moment information to the dynamic model actuator and receives the dynamic model sensor. The attitude information sent;

[0020] 2) Build various stand-alone models in the system in dynamics, and consider the performance, function and interface communication mode of each stand-alone. When there is a lack of a single machine, or when a single machine fails, the single machine information in the dynamic model can be used at any time to complete the system test. Each sensor model calculates its own stand-alone measurement data according to the sta...

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Abstract

The invention discloses an attitude and orbit control closed-loop control method applicable to a quick response satellite. The method comprises specific steps: 1) when an integrated electronic computer is designed, an RS-422 serial port is reserved for communication with ground equipment; 2) various virtual single machine models are built in a satellite dynamics model; 3) measurement data calculated by the virtual single machine models are packed and transmitted to the integrated electronic computer through the RS-422 serial port, and a control instruction sent by the computer is received at the same time and is forwarded to each virtual single machine model; and 4) a flag word is set, and through judging the flag word, an information source is selected for each single machine. Adaptation adjustment in a software aspect due to incomplete product match is not needed, a system designer is ensured to focus main time and energy to scheme design and final software realization, test effects of half the work with double results are achieved, and the application and the promotion are further expanded.

Description

technical field [0001] The invention relates to an attitude-orbit control closed-loop semi-physical simulation test method suitable for fast-response satellites. Background technique [0002] According to the system design of the Pujiang-1 satellite, the dual-vector attitude determination based on the sun vector azimuth and the magnetic field vector azimuth is a main control mode of the satellite. In order to simulate the orbital geomagnetic field information on the ground, it was previously set by the attitude and orbital dynamics simulators. A D / A digital-to-analog conversion card is used to simulate the magnetic field intensity information output by the magnetometer, but this method cannot connect the magnetometer stand-alone and the simulated magnetometer information to the system at the same time, and the whole star semi-physical simulation test process It is necessary to frequently plug and unplug the magnetometer stand-alone cable in the process. The test efficiency o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B17/02G05B23/02G06F17/50
CPCG05B17/02G05B23/0213G06F30/367
Inventor 孙锦花王世耀李芳华查理
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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