Attitude control method for underactuated spacecraft actively assisted by light pressure torque

Abstract

The invention relates to an attitude control method for an underactuated spacecraft actively assisted by a light pressure torque. The method comprises the following steps of taking the spacecraft witha flywheel and two pairs of solar panels as an object, and firstly establishing a kinetic model of a flexible spacecraft with a flexible attachment and a attitude kinematics equation of the spacecraft; establishing a simplified analytical model of a solar pressure torque; designing a linear quadratic optimal controller to obtain a three-axis desired torque, analyzing characteristics of the solarpressure torque, and distributing the three-axis torque to the solar pressure torque and a flywheel torque; under the assumption that the surface characteristics of the panels are constant, solving aninverse solution according to the simplified solar pressure torque model of the panels to directly obtain a corner steering law of the solar panels; and obtaining a corner steering law of the solar panels based on numerical optimization by solving constrained nonlinear programming problems. The attitude control method provided by the invention can effectively improve the controllability of the attitude and improve the control performance, and is more suitable for the engineering practice by adopting a control scheme in which the steering law and the control law are separated.

Description

[0001] 【Technical field】 [0002] The invention relates to an attitude control method of an underactuated spacecraft actively assisted by a light pressure moment, in particular to an attitude control method designed to actively assist an underactuated spacecraft using a flywheel as an attitude control actuator The method belongs to the field of spacecraft dynamics and attitude control. [0003] 【Background technique】 [0004] An underactuated spacecraft refers to a spacecraft in which the number of independent control moments provided by the actuator is less than the system's motion degrees of freedom. For satellites that need to work for a long time, such as microsatellites and deep space probes, the research on the attitude dynamics and control of underactuated spacecraft can improve the reliability of its attitude control system and prolong the working life of the spacecraft. It is beneficial to reduce the configuration of the actuator, thereby reducing the mass and power c...

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Problems solved by technology

[0008] The purpose of the present invention is to solve the problem that the research on the underactuated spacecraft using the angular momentum exchange device in the prior art is carried out under the condition of ignoring the environmental disturbance torque, so the research results are difficult to apply to engineering practice, and propose a The attitude control method of underactuated spacecraft under the active assistance of light pressure torque is specifically a control scheme in which a spacecraft with a flywheel as the actuator performs joint attitude control under the active assistance of light pressure torque, and the control law is separated from the control law. Achieving attitude control for underactuated spacecraft with flywheel failure

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