A composite anti-jamming
attitude control method for a
flexible spacecraft, which is characterized in that it includes the following steps: First, by considering the vibration of the flexible attachment, the change of the
spacecraft moment of inertia caused by the expansion of the flexible attachment and the
space environment disturbance torque on the attitude In order to control the influence of control, a
flexible spacecraft dynamics model including neutral uncertain dynamic items and external equivalent disturbance variables is established; secondly, in view of the serious influence of
structural vibration on the stability of the
spacecraft, and the large existence of flexible accessories such as sailboards, With the characteristics of flexibility and low damping, the PPF active vibration controller is constructed to reduce the
impact of vibration
modes on the
spacecraft body; thirdly, the H∞ anti-jamming controller is designed to suppress vibrations from
flexible mechanisms such as sailboards and extension rods. The disturbance caused by the change of the spacecraft rotational
inertia caused by the deployment and the bounded disturbance such as the
space environment disturbance moment; finally, based on the convex optimization
algorithm, the composite anti-jamming
output feedback attitude and the vibration
composite controller are solved; Design and other advantages, can be used for high stability control of
flexible spacecraft.