High-precision orbit control attitude maintaining method and system based on CMG and medium

Abstract

The invention discloses a high-precision orbit control attitude maintaining method and system based on CMG and a medium, and belongs to the technical field of spacecraft attitude control. The method comprises the following steps of according to each working period of a rail-controlled engine, firstly, calculating the disturbance torque innovation according to the angular velocity acquisition information in the current period and a control signal in the last period, then carrying out filtering correction on the disturbance torque estimation, orderly calculating the star gyro torque and the feedback control torque based on attitude angle and angular velocity collection information, and combining with a disturbance torque estimation to calculate the CMG instruction torque, and then real-timely resolving a pseudo-inverse control law to convert the instruction torque into a frame angular velocity maneuvering instruction according to the CMG configuration. By adopting the method, the problemof high-precision orbit control attitude maintenance is well solved.

Description

technical field [0001] The invention belongs to the technical field of spacecraft attitude control, and in particular relates to a CMG-based high-precision orbit control attitude maintenance method, system and medium. Background technique [0002] The attitude control accuracy during the satellite orbit control has a direct impact on the orbit control accuracy. Satellites with high requirements for business continuity hope to maintain the attitude control accuracy of normal work during the orbit control period. All of these have put forward requirements for high-precision orbit control attitude control. , the traditional jet phase plane control cannot be realized. Since the CMG can provide a large control torque, the use of CMG attitude control during orbit control can improve the accuracy of orbit control. Therefore, a scheme of using CMG for attitude maintenance during the operation of the orbit control engine is designed to achieve high-precision attitude control and save...

AI Technical Summary

Problems solved by technology

However, compared with the normal operating conditions of the satellite, there is a large disturbance moment during the orbit control period, which is mainly due to the deviation of the installation position of the orbit control engine and the angle of the nozzle and the thrust eccentricity caused by the change of the center of mass of the whole satellite in orbit.

When using the general attitude control method, the attitude fluctuates greatly during the orbit control, which cannot guarantee the high-precision attitude control requirements

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