A Control Method of Forced Flying Around Non-cooperative Targets

Abstract

The invention relates to the control method of non-cooperative target forced fly-around. The method comprises the following steps of establishing the kinetic equation of a forced fly-around process; calculating the deviation kinetic equation of the expected pose of the forced fly-around process; using a first order instruction filter to acquire an unknown state variable; estimating the uncertaintyof the system model of the fly-around process and calculating the adaptive input ua of a system; and calculating the optimal control input uop of the system and the total input u of the system. In the invention, the optimal control method is adopted; and under the condition that an error reaches a requirement, the fuel consumption of the system is minimum; the first order instruction filter is used to acquire an unknown state variable value so that the influence of noise measurement on the state variable can be effectively reduced; and the uncertainty of a fly-around process model is estimated so that the influence brought by the uncertainty can be effectively compensated, a overshoot amount in a control process is less, convergence time is short and control precision is high.

Description

technical field [0001] The invention belongs to the field of spacecraft control technology research and relates to a control method for forcing non-cooperative targets to fly around. Background technique [0002] Space orbiting missions are divided into natural orbiting, impulse orbiting and forced orbiting. Natural orbiting refers to the orbiting without exerting control force on the accompanying spacecraft, and only relying on the relative initial conditions between the accompanying spacecraft and the target spacecraft. The advantage is that the fuel consumption is very small, and the disadvantage is that the orbiting period is long (equal to the orbital period), the flying trajectory is fixed and the requirements for the initial value are very high. Pulse orbiting means that when the relative position reaches a specific point, a specific duration of control force is applied to the accompanying spacecraft. Its advantage is that the orbiting trajectory and orbiting period ...

AI Technical Summary

Problems solved by technology

This method is suitable for short-period, high-precision fly-around missions. Its advantage is high precision, and the orbit and period of the fly-around can be adjusted in real time. The disadvantage is that it is not suitable for long-term fly-around missions.

[0003] Due to problems such as unknown external interference, strong nonlinearity, and measurement noise, the use of conventional controllers may cause the fly-around mission to fail to meet the low fuel consumption and high-precision requirements, and may even cause relative position or attitude divergence, resulting in the failure of the fly-around mission

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