Actuating mechanism configuration and control method for attitude reciprocating fast swing of agile satellite

Abstract

The invention discloses an actuating mechanism configuration and control method for attitude reciprocating fast swing of an agile satellite attitude, wherein the actuating mechanism is a composite attitude control actuating mechanism and comprises two control moment gyroscopes and two reaction flywheels; a right-angle three-dimensional coordinate system Oxyz is constructed by using an agile satellite platform as a center; the two reaction flywheels are respectively arranged on y axis and z axis; the positive rotation directions of rotors of the two reaction flywheels are respectively towards the negative directions of the y axis and the z axis; the mounting directions of the two frame axes of the control moment gyroscopes are parallel to the y axis, and a dual-control moment gyroscope structure is formed. The output control moment applie on the x-axis direction. The control method comprises the following steps of: constructing a dynamics equation and a kinematics equation, designing acontroller, and then controlling the attitude maneuver of the satellite. The configuration and control method of the actuating mechanism effectively achieves the large-angle reciprocating fast swing of the satellite attitude.

Description

technical field [0001] The invention relates to the technical field of aerospace control, in particular to the configuration and control method of an actuator for agile satellite attitude reciprocating and rapid swing. Background technique [0002] Remote sensing satellites currently play an irreplaceable role in both civil and military applications. In order to improve the rapid response and imaging capabilities of remote sensing satellites, shorten the revisit cycle of ground targets, and take into account high-resolution and wide-format imaging, it has high-speed attitude and large angle Agile remote sensing satellites with maneuverability have received more and more attention. Since agile satellites need to complete rapid attitude maneuvers and large-angle maneuvers within a specified time, the system presents strong nonlinearity, and at the same time must ensure high-precision attitude stability, which poses a great challenge to the design of satellite attitude control ...

AI Technical Summary

Problems solved by technology

How to achieve long-term and large-angle rapid maneuvering under the condition of limited load and limited output control torque of the actuator poses a new challenge to the design of the agile satellite attitude control system

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