Fast and high-precision relative pointing control method based on feed-forward pid control for crossing fast-changing tracks on different planes

Abstract

The invention relates to a rapid high-precision relative pointing control method of a noncoplanar rendezvous orbit, in particular to a feedforward PID (proportion, integration and differentiation) control based rapid high-precision relative pointing control method of the noncoplanar rendezvous orbit, and aims to solve the problem that rapid high-precision tracking-pointing control methods related to satellite attitudes under the noncoplanar rendezvous orbit do not exist in the prior art. The feedforward PID control based rapid high-precision relative pointing control method including adopting an Euler angle for attitude description of a spacecraft, creating dynamical and kinematical equations of the spacecraft, and acquiring an precise expected angle theta according to a noise-containing expected angle z by a Kalman filtering algorithm of a spaceborne computer; designing an attitude control law of each axis according to a formula of ; selecting two parallelly-placed single-frame control moment gyroscopes to control a yaw axis, and selecting two flywheels to control a rolling axis and a pitch axis respectively; calculating gyroscopic moment T and flywheel actual output moment uw to complete rapid high-precision relative pointing control of the noncoplanar rendezvous orbit. The feedforward PID control based rapid high-precision relative pointing control method is applicable to rapid high-precision relative pointing control of the noncoplanar rendezvous orbit.

Description

technical field

[0001] The invention relates to a fast and high-precision relative pointing control method for intersecting fast-changing tracks with different planes. Background technique

[0002] With the development of aerospace science and technology, space technology has been widely used in various fields. It can be said that space has existed as a resource that human beings rely on for survival and development. In order to make the satellite payload point to a specific target with a certain accuracy, it is first necessary to calculate the desired attitude when the satellite load line-of-sight axis points to the target according to the target position, and then track the desired attitude so that the satellite is in line with the commanded attitude under the influence of orbital motion and disturbance torque The deviation and relative rotation speed are kept within the allowable range.

[0003] "Robust Backstepping Adaptive Attitude Maneuvering and Active Vibration Supp...

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