Satellite formation relative orbit adaptive neural network configuration containment control method

A relative orbit and neural network technology, which is applied in the field of satellite formation relative orbit adaptive neural network configuration inclusion control, can solve the problem of buffeting phenomenon, system nonlinear uncertainty and external interference, and satellite formation Problems such as system dynamics generalized interference, to avoid communication burden

Active Publication Date: 2015-11-18
HARBIN INST OF TECH
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Problems solved by technology

[0054] The purpose of the present invention is to solve the problems caused by the non-linear uncertainty and external interference in the system, the generalized interference in the dynamics of the satellite formation system, the chattering phenomenon and the global knowledge of the information in the prior art. In view of the problem of communication burden, a satellite formation relative orbit adaptive neural network configuration inclusion control method is proposed

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  • Satellite formation relative orbit adaptive neural network configuration containment control method
  • Satellite formation relative orbit adaptive neural network configuration containment control method
  • Satellite formation relative orbit adaptive neural network configuration containment control method

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specific Embodiment approach 1

[0096] Specific implementation mode one: combine figure 1 Illustrate this embodiment, a kind of satellite formation relative orbit self-adaptive neural network configuration includes control method, it is characterized in that, a kind of satellite formation relative orbit self-adaptive neural network configuration includes control method is specifically carried out according to the following steps:

[0097] Step 1, establishing the relative orbital dynamics equation following star i;

[0098] Step 2. Design a distributed velocity observer for each following star in step 1;

[0099] Step 3, performing neural network approximation according to the relative orbital dynamics equation and the distributed velocity observer following star i;

[0100] Step 4. According to the neural network approximation result obtained in step 3, design an adaptive neural network configuration including a control algorithm.

specific Embodiment approach 2

[0101] Specific embodiment two: the difference between this embodiment and specific embodiment one is that the relative orbital dynamics equation of following star i is established in said step one; the specific process is:

[0102] Such as image 3 Shown is the satellite formation system and the reference orbit coordinate system of the satellite formation system, that is, the LVLH coordinate system,

[0103] The x-axis of the LVLH coordinate system points from the center of the earth to the reference point, the y-axis of the LVLH coordinate system runs along the speed direction of the reference point, and the z-axis of the LVLH coordinate system is determined by the x-axis and y-axis according to the right-hand rule;

[0104] Considering that the reference point runs on a near-circular orbit, the orbital angular velocity of the reference point is In the LVLH coordinate system, the relative orbit dynamics equation of following star i relative to the reference point is:

[0...

specific Embodiment approach 3

[0114] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is that in the step two, a distributed speed observer is designed for each following star in the step one; the specific process is:

[0115] The present invention considers that all pilot stars have a constant velocity. Since the speed of the pilot star is not globally known, in order to realize the containment control of all follower stars on the pilot star,

[0116] Design a distributed velocity observer for each follower star, as shown in the following formula:

[0117] v ^ · i = - β [ Σ j = 1 N a i j ( v ^ ...

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Abstract

The present invention relates to a satellite formation relative orbit adaptive neural network configuration containment control method, and aims to solve the communication burden problems in the prior art brought by not considering the situations that a system exists the non-linear uncertainty and the external disturbance, not considering the situation that a satellite formation system kinetics exists the generalized interference, not considering a chattering phenomena and the known global information. The method of the present invention is realized by the following technical schemes of a step 1 of establishing a relative orbit kinetic equation of a following satellite i; a step 2 of designing a distributed speed observer for each following satellite in the step 1; a step 3 of carrying out the neural network approximation according to the relative orbit kinetic equation and the distributed speed observer of the following satellite i; a step 4 of designing an adaptive neural network configuration containment control algorithm according to a neural network approximation result obtained in the step 3. The satellite formation relative orbit adaptive neural network configuration containment control method of the present invention is applied to the satellite field.

Description

technical field [0001] The invention relates to a satellite formation relative orbit adaptive neural network configuration inclusion control method. Background technique [0002] 1. Introduction and research significance and value of satellite formation system [0003] In recent years, aerospace technology has had an important impact on all aspects of politics, economy, military affairs and human life in countries all over the world, and has gradually developed into a key technology to measure a country's comprehensive national strength. Satellite technology is an important part of the development of aerospace technology. The Soviet Union launched the first artificial earth satellite in 1957, marking the realization of the dream of human beings to enter outer space for many years. With the continuous maturity of space technology, many satellites for different purposes are providing various convenient services to human beings, such as meteorological satellites, remote sensin...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/10G05D1/08
Inventor 孙延超陈亮名王文佳董振李传江马广富
Owner HARBIN INST OF TECH
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