Relative orbit and attitude tracking control method for final approaching section of rendezvous and docking of spacecrafts

Abstract

The invention discloses a relative orbit and attitude tracking control method for a final approaching section of rendezvous and docking of spacecrafts. The design of a controller in an existing preset performance control scheme depends on an initial value of a system tracking error, under the condition of considering relative orbit and attitude tracking error preset performance constraints, physical structure limitations of executing mechanisms such as a thruster, a control moment gyroscope and a momentum wheel in an actual rendezvous and docking task cannot be met, the above invention just aims to solve the above problem. According to the method, a new performance function is constructed by establishing a relative orbit and attitude tracking dynamics model between a tracking spacecraft and a target spacecraft, known limitations on an initial tracking error are relaxed, a design idea of preset performance is utilized to realize fine steady-state and transient-state control considering relative orbit and attitude tracking errors, and an auxiliary saturation compensation system is designed to compensate saturation nonlinearity of an execution mechanism.

Description

technical field [0001] The invention relates to a relative orbit and attitude tracking control method for the final approach segment of rendezvous and docking of a spacecraft, and belongs to the technical field of spacecraft control. Background technique [0002] With the rapid development of space technology, how to realize the rendezvous and docking of tracking space and target spacecraft is an important guarantee for completing tasks such as on-orbit cleaning, maintenance and space refueling. In addition, in actual space rendezvous and docking operations, it is often required that the relative orbit and attitude control errors of the tracking spacecraft and the target spacecraft have specified transient and steady-state performance. Therefore, how to realize the relative orbit and attitude prediction considering the saturation constraints of the actuator Design performance control is a key technology for rendezvous and docking missions. [0003] Most of the traditional r...

AI Technical Summary

Problems solved by technology

However, the above technology still has technical defects, that is, the traditional preset performance design method is dependent on the initial value of the system tracking error, which limits the application of the preset performance

In addition, in the actual rendezvous and docking mission, due to the physical structure limitations of thrusters, control moment gyroscopes, momentum wheels and other actuators, the relative orbit and attitude control system has a control saturation nonlinearity, and the control system is saturated. The control performance is reduced, and even the stability of the system is destroyed. Therefore, for the rendezvous and docking task, it is necessary to propose a relative orbit and attitude coupling control method that considers the saturation constraints of the actuator and has preset performance.

Images