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Multi-microsatellite attitude takeover method for failed spacecraft based on robust differential game control

A micro-satellite and micro-satellite technology, applied in attitude control and other directions, can solve the problems of not considering external interference, neural network for a long time, unsuitable for space missions, etc., to avoid control allocation, avoid allocation, and reduce communication and effects.

Active Publication Date: 2022-02-08
NORTHWESTERN POLYTECHNICAL UNIV
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  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The convergence of neural network parameters in the method described in the literature takes a long time, which is not suitable for space missions; and the literature does not consider external interference

Method used

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  • Multi-microsatellite attitude takeover method for failed spacecraft based on robust differential game control
  • Multi-microsatellite attitude takeover method for failed spacecraft based on robust differential game control
  • Multi-microsatellite attitude takeover method for failed spacecraft based on robust differential game control

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specific Embodiment approach

[0144] The following simulation scenario is used, assuming that there are three micro-satellites performing attitude takeover control on the target spacecraft in geostationary orbit, and the transformation matrices from their respective body coordinate systems to the reference coordinate system are:

[0145]

[0146] The moment of inertia matrix of the assembly is

[0147]

[0148] Disturbance torque is

[0149]

[0150] The initial value of the combination state quantity is x 0 =[0.087; 0.087; 0.087; 0; 0; 0], where the unit of angle is radian. The maximum single-axis control torque of the microsatellite is 0.04N.m. The simulation parameters of the trigger are α=0.5, β=0.0, and the parameters of the 1 controller are T 1 =T 2 =T 3 =0.01I 3 , Q 1 =Q 2 =Q 3 =0.003I 6 , R 11 =R 12 =R 13 =0.01I 3 , R 21 =R 22 =R 23 =0.01I 3 , R 31 =R 32 =R 33 =0.01I 3 .

[0151] The specific implementation process is

[0152] The first step, initialization;

[015...

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Abstract

The invention relates to a multi-microsatellite attitude takeover method for a failed spacecraft based on event-triggered robust differential game control. For a combination of multiple microsatellites attached to the surface of a failed spacecraft and a failed spacecraft, the The attitude takeover control problem is modeled as a game problem between multiple microsatellites and interference, which avoids the distribution of control and effectively suppresses interference. The differential game model is obtained by establishing the linearized attitude dynamic model of the assembly and the performance index function of each microsatellite; after that, the HJ equation is obtained and solved by optimizing the performance index function, and the state feedback control strategy expression can be obtained directly online use. By designing the trigger mechanism, the controller can only get the updated state of the system when it is triggered, and update the state feedback control amount. When it is not triggered, it adopts the control at the trigger time, which not only ensures stability, but also reduces the communication and control between individuals. Frequent calculations of the device.

Description

technical field [0001] The invention belongs to an attitude takeover method of a failed spacecraft, and relates to a multi-microsatellite attitude takeover method for a failed spacecraft based on event-triggered robust differential game control. Background technique [0002] The document "Integrated identification and control for nanosatellites reclaiming failed satellite, Acta Astronautica, 2018" discloses a Dona satellite attitude takeover control method that integrates identification and control. The control part of the method is based on the Lyapunov stability law to design the control law, and the problem of control torque distribution is summarized as the QP problem to solve, which better solves the problem of multi-satellite takeover control. The method described in the literature first solves the total control and then distributes it to the nano-satellite, which puts a lot of calculation pressure on the central node; frequent control changes will lead to rapid aging ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
Inventor 罗建军柴源韩楠
Owner NORTHWESTERN POLYTECHNICAL UNIV