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Spacecraft attitude control testing system and method adopting actual moment of control moment gyro

A technology for controlling torque gyroscopes and testing systems, which is applied in electrical testing/monitoring, etc., and can solve the problem that the control of torque gyroscopes cannot be introduced into closed-loop experiments.

Active Publication Date: 2016-12-07
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0008] The technical solution problem of the present invention is: overcome the deficiencies in the prior art, provide a kind of spacecraft attitude control test system and method that adopts the real torque of the control torque gyroscope, solve the problem that the real output torque of the control torque gyroscope cannot be introduced into the closed-loop experiment, reduce The difference between the ground closed-loop experiment and the real attitude control of the orbit operation improves the authenticity of the ground verification of the control moment gyroscope

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  • Spacecraft attitude control testing system and method adopting actual moment of control moment gyro

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Embodiment Construction

[0052] The present invention will be described in detail below in conjunction with the accompanying drawings.

[0053] 1. Specific design and implementation of key components

[0054] (1) GNC controller 1, actuators and sensors

[0055] The GNC controller 1, actuators and sensors are real products in the sky, which are used to complete the GNC task during the orbit of the spacecraft, and are the tested objects in the spacecraft attitude control test system.

[0056] (2) Static moment measuring platform 3 and its calibration algorithm

[0057] The static torque measuring platform is used to measure the torque output by the control torque gyroscope fixed on its measuring surface, such as figure 2 As shown, its key components are 4 two-dimensional force sensors, 1 universal joint, 1 base and 1 upper table. According to the maximum torque output N produced in the working process of the control torque gyroscope, taking into account the sensitivity of the force sensor, 1.2 times...

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Abstract

The invention relates to a spacecraft attitude control testing system which is composed of a sensor simulator, an actuating mechanism simulator, a front station, an outer system equivalent device and a data display and storage system. The front station is responsible for dynamic calculation and outputs a sensor simulator excitation signal. A static control moment gyro simulator in the actuating mechanism simulator measures actual moment generated by the control moment gyro by adopting a static moment measuring table and leads the actual moment into dynamic calculation. The static moment measuring table is composed of a base, a tabletop, four symmetric crossed two-dimensional force sensors and a universal joint for measuring the output moment of the control moment gyro fixed to the tabletop. According to the spacecraft attitude control testing system, the GNC system control algorithm can be truly and efficiently verified, and compared with semi-physical stimulation and all-physical stimulation experiments, the method is simple and easy to implement and low in cost.

Description

technical field [0001] The invention relates to a spacecraft attitude control test system and method using the real torque of a control moment gyroscope, which can be used for the GNC system ground test of the spacecraft using the control moment gyroscope as an actuator for attitude control. Background technique [0002] The control moment gyroscope has the advantages of large control torque, fast response speed and low power consumption. Therefore, more and more spacecraft choose the control moment gyroscope as the actuator for the rapid maneuvering of the attitude. Especially for large and long-lived spacecraft, the control moment gyro is its necessary actuator, which has been widely and maturely applied. [0003] As an actuator with high control precision, stability and high maneuverability, the control moment gyro needs a higher performance simulation system for ground verification. In the traditional spacecraft attitude control test system, the frame angular position a...

Claims

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Application Information

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IPC IPC(8): G05B23/02
CPCG05B23/02
Inventor 蒋金哲宋明超张录晨蔡彪高亚楠范松涛于丹宋晓光徐春
Owner BEIJING INST OF CONTROL ENG
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