A closed-loop semi-physical simulation test method for attitude and orbit control suitable for fast-response satellites

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...

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.

Images