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A closed-loop joint test method of satellite control system and electric propulsion system

A satellite control system and electric propulsion technology, applied in jet engine testing, electrical testing/monitoring, gas turbine engine testing, etc., can solve problems such as the inability to effectively verify the joint working function of the satellite control system and electric propulsion system, and achieve cost savings , the effect of general adaptation

Active Publication Date: 2022-03-04
CHINA ACADEMY OF SPACE TECHNOLOGY
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The technical problem solved by the invention is: Aiming at the problem that the current satellite ground test cannot effectively verify the joint working function of the satellite control system and the electric propulsion system in the current prior art, a closed-loop joint test method of the satellite control system and the electric propulsion system is proposed , a comprehensive validation of the hardware and software interface between the control system and the electric propulsion system

Method used

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  • A closed-loop joint test method of satellite control system and electric propulsion system
  • A closed-loop joint test method of satellite control system and electric propulsion system

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Effect test

Embodiment

[0063] 1. Complete the connection between the ground test system and the satellite, power on the ground test system and complete its own status setting.

[0064] 2. Power up the satellite through remote control commands, power up the satellite control system and electric propulsion system, and set the working mode of the control system to remote ignition mode.

[0065] 3. Set up the satellite ground simulation dynamics software. The starting time is t0 = 9:00 on March 25, 2020. The initial orbital position under the Earth’s equatorial inertial system is X0 = 42164km, Y0 = 0km, Z0 = 0km, and the initial three The axial velocity is VX0=0km / s, VY0=3.074km / s, VZ0=0km / s, the initial triaxial angular Euler angular velocity is AX0=0, AY0=0, AZ0=0, and the initial triaxial angular velocity is WX0 =0, WY0=0.004° / s, WZ0=0. Start the dynamics simulation run.

[0066] 4. When the dynamics simulation runs to T1 time, such as T1 = 9:10 on March 25, 2020, the satellite position, velocity, ...

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Abstract

A closed-loop joint test method of a satellite control system and an electric propulsion system, which conducts a closed-loop joint test of the electric propulsion system and control system of a real satellite through ground testing, and uses a comprehensive simulation of the timing of on-orbit work to verify that the control system calls electric propulsion for on-orbit The complete workflow of the orbital ignition, the function of the control system calling the electric propulsion ignition process is tested, which solves the problem that the current satellite ground test cannot effectively verify the joint working function of the satellite control system and the electric propulsion system, the verification process is complete, sufficient, and economical better.

Description

technical field [0001] The invention relates to a closed-loop joint test method of a satellite control system and an electric propulsion system, belonging to the field of spacecraft ground testing. Background technique [0002] The main task of the satellite attitude and orbit control subsystem is to complete the attitude control and orbit control of the satellite from launch to normal in-orbit operation to the end of its life. The satellite electric propulsion subsystem is the executive mechanism of the satellite, which accelerates the working medium carried by electric energy to make it eject at high speed to generate thrust. The timing and direction of thrust generated by the electric propulsion subsystem can be adjusted. This process is completed under the command of the control subsystem. The joint work of the two can realize the orbit control of the satellite. When the electric propulsion subsystem is working in orbit, its thrust adjustment mechanism will be adjusted ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M15/14G05B23/02
CPCG01M15/14G05B23/02
Inventor 段传辉宋可桢柏芊任立新常雅杰何艳
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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