Trajectory planning method for autonomous and safe approaching to rolling fault satellite

A trajectory planning and fault technology, applied in the direction of adaptive control, instrumentation, control/adjustment system, etc., can solve problems such as poor real-time performance, single tumbling state, and no research on tumbling motion state

Active Publication Date: 2016-10-26
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

There are two main problems in the current research: First, optimization theory is often used to solve this problem in domestic and foreign literature. Although feasible trajectory and control schemes can be obtained, the calculation is usually large and t...

Method used

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  • Trajectory planning method for autonomous and safe approaching to rolling fault satellite
  • Trajectory planning method for autonomous and safe approaching to rolling fault satellite
  • Trajectory planning method for autonomous and safe approaching to rolling fault satellite

Examples

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Effect test

Embodiment 1

[0127] Example 1 is that the faulty satellite with the first type of rolling motion is at ω b =[0,0,0]rad / s,k 1 =0.1,k 2 =0.2, ρ=diag(0.1,0.1,0.1), ε=diag(1,1,1), the service spacecraft approaches the relative trajectory of the faulty satellite autonomously;

Embodiment 2

[0128] Embodiment 2 is that the faulty satellite with the first type of rolling motion is at ω b =[0,0,0.1]rad / s,k 1 =0.2,k 2 =0.5, ρ=diag(0.1,0.1,0.1), ε=diag(1,1,1), the service spacecraft approaches the relative trajectory of the faulty satellite autonomously;

Embodiment 3

[0129] Embodiment 3 is that the faulty satellite with the second type of tumbling motion is at ω b =[0.3,0.1,0.1] T rad / s,k 3 =10, ρ=diag(0.01,0.01,0.01), ε=diag(0.01,0.01,0.01), the service spacecraft is approaching the relative motion track of the faulty satellite.

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Abstract

Provided is a trajectory planning method for the autonomous and safe approaching to a rolling fault satellite. A dynamics model is established, by using an artificial potential field method and combining with the different rolling conditions of the fault satellite, the expected velocity of a service spacecraft is determined, a trajectory plan for the autonomous and safe approaching to the rolling fault satellite is made, and a sliding mode controller is designed to control the spacecraft to approach to the fault satellite through the planned trajectory. For the trajectory planning method for the safe approaching to the rolling fault satellite, a trajectory planning method based on artificial potential field idea is proposed. According to the geometrical outline features of the target, the corresponding path security constraints are designed, and thus the trajectory planning and control method are more accurate, the scope of application is widened, and the closed loop with respect the environment is realized; and meanwhile, the computational complexity is small, the online calculation is convenient, the trajectory planning can be carried out online in real time, the real-time property is good, and the control effect is optimal.

Description

【Technical field】 [0001] The invention belongs to the technical field of aerospace equipment control, and in particular relates to a trajectory planning method for autonomously and safely approaching a rolling fault satellite in the on-orbit service technology. 【Background technique】 [0002] With the development of aerospace technology, on-orbit service technology has attracted more and more attention. It can not only effectively save mission costs, improve the performance and life of spacecraft, but also perform on-orbit maintenance for space faulty satellites, and repair fuel-exhausted satellites. Satellites are refueled on-orbit, so it can bring huge economic benefits. Most of the satellites in the tumbling state are due to the failure of the attitude control system, or the failure of attitude stability control due to exhaustion of fuel. On-orbit maintenance or refueling of such faulty satellites can effectively improve their life and bring economic benefits. The autono...

Claims

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 袁建平葛菊祥陈建林马川
Owner NORTHWESTERN POLYTECHNICAL UNIV
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