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Finite time fault-tolerant control method for approaching and tracking space non-cooperative target

A non-cooperative target, fault-tolerant control technology, applied in the field of limited-time fault-tolerant control, which can solve the problems of large tracking control error and low tracking monitoring accuracy.

Active Publication Date: 2015-12-16
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] The purpose of the present invention is to solve the problem of low tracking and monitoring accuracy caused by large tracking control error when the existing tracking spacecraft performs line-of-sight tracking on non-cooperative targets, and propose a limited time fault-tolerant method for approaching and tracking non-cooperative targets in space Control Method

Method used

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  • Finite time fault-tolerant control method for approaching and tracking space non-cooperative target
  • Finite time fault-tolerant control method for approaching and tracking space non-cooperative target
  • Finite time fault-tolerant control method for approaching and tracking space non-cooperative target

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specific Embodiment approach 1

[0035] The finite-time fault-tolerant control method of approaching and tracking space non-cooperative targets in this embodiment, such as figure 1 Shown flow chart, described method is realized through the following steps:

[0036] Step 1. Establish the relative orbital dynamics model in component form under the line-of-sight coordinate system: ρ ·· - ρ ( q · ϵ 2 + q · β 2 cos ...

specific Embodiment approach 2

[0051] The difference from Embodiment 1 is that in the finite-time fault-tolerant control method of approaching and tracking space non-cooperative targets in this embodiment, the process of establishing the relative orbital dynamics model in the form of components described in Step 1 is as follows: set the geocentric inertial coordinate system o i x i the y i z i and line of sight coordinate system O l x l the y l z l and its relationship, such as figure 1 The relative position vectors of the Earth, the target spacecraft, and the tracking spacecraft are shown, O l is the origin of the line-of-sight coordinate system, located at the center of mass of the tracking spacecraft, x l The axis coincides with the line of sight, that is, the tracking spacecraft points to the target spacecraft, y l axis is located by x l axis and y i axes together form the longitudinal plane, with the x l Axis vertical, z l The axes are determined by the right-hand rule; q ε is the line-of...

specific Embodiment approach 3

[0053] Different from the first or second specific embodiment, the finite-time fault-tolerant control method for approaching and tracking a space non-cooperative target in this embodiment is characterized in that: the process of obtaining the derivative relationship between the attitude angular velocity and the attitude angle described in step one As, define the rotation angles of the tracking spacecraft around the x, y, and z axes of the body as θ, ψ, the attitude matrix described by the Euler angles is:

[0054] Track the attitude angular velocity of the spacecraft:

[0055]

[0056] For simplicity, define the matrix:

[0057]

[0058] Then there is the attitude angle:

[0059]

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Abstract

A finite time fault-tolerant control method for approaching and tracking a space non-cooperative target belongs to the field of orbit control and attitude control, and aims to solve the problem of low tracking supervision precision caused by big tracking control error of an existing tracking spacecraft which performs line-of-sight tracking for a non-cooperative target. The finite time fault-tolerant control method is characterized in that dynamical and kinematical equations are established under a line-of-sight coordinate system, the situations such as nondeterminacy of a system, partially unknown motion parameters of the non-cooperative target, control input saturation and dead zone are taken into consideration, self-adaptive estimation and compensation can be performed through adoption of an RBF neural network, and a back-stepping thought is adopted to design a controller so that the tracking spacecraft can converge to an expected attitude and orbit within finite time and can keep the attitude and the orbit. The finite time fault-tolerant control method of the present invention has the advantages of quick control convergence, good robustness and high tracking control precision.

Description

technical field [0001] The invention relates to a limited-time fault-tolerant control method for approaching and tracking a space non-cooperative target. Background technique [0002] With the rapid development of the aerospace industry, space technology has gradually been upgraded from the initial use of space to space control, and the research on issues such as space strikes, tracking and monitoring, and rendezvous and docking has attracted more and more attention and attention from space powers. The problem of approaching and close-range tracking and monitoring has become a very important research hotspot in the aerospace field today. Space non-cooperative targets generally refer to some space objects that cannot provide effective cooperative information, including space debris, invalid aircraft, and enemy aircraft. With the enhancement of spacecraft mobility, the requirements for tracking and monitoring accuracy and range are getting higher and higher, and the difficulty...

Claims

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Application Information

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IPC IPC(8): G05D1/08G05D1/10
Inventor 凌惠祥孙延超马广富龚有敏赵天睿李传江
Owner HARBIN INST OF TECH
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