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Flexible-spacecraft-attitude control method based on event driving

A flexible spacecraft and attitude control technology, applied in attitude control, non-electric variable control, control/regulation system, etc., can solve the transient and steady performance problems of spacecraft attitude system, and cannot achieve attitude stabilization and maneuver control, etc. problems, to achieve the effect of strong engineering application value and reducing the number of updates

Inactive Publication Date: 2019-03-15
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In the current technology: space flexible spacecraft, in the presence of uncertain inertial parameter information, there are certain problems in the transient and steady-state performance of the spacecraft attitude system, and it is impossible to achieve attitude stabilization and maneuver control

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  • Flexible-spacecraft-attitude control method based on event driving
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  • Flexible-spacecraft-attitude control method based on event driving

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Embodiment Construction

[0049] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0050] This embodiment is aimed at the flexible spacecraft attitude system, and the specific simulation parameters are as follows: the inertia matrix parameter J and the coupling matrix parameter β are:

[0051]

[0052] Flexible attachment parameters:

[0053] ι 1 =0.0056,ι 2 =0.0086,ι 3 =0.08,ι 4 =0.025,

[0054]

[0055] Performance function parameters:

[0056] kappa i =0.3,η i,0 =1,η i,∞ =0.01,

[0057] λ=diag{2,2,2}

[0058] δ 0 =10, ζ = 0.004

[0059] Υ 1 =Y 2 =0.1

[0060] Initial attitude simulation parameters:

[0061] σ=[0.3,-0.3,0.3] T ,ω=[0,0,0] T rad / s

[0062] Initial elastic modal parameters:

[0063] χ=[0.001,0.001,0.001,0.001] T ,

[0064] Control method of the present invention:

[0065] Step 1: capture system vibration model

[0066] The kinematics model of the flexible spacecraft aimed at by the present i...

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Abstract

The invention relates to a flexible-spacecraft-attitude control method based on event driving. Under the condition that uncertain inertial parameter information exists, an attitude control method based on event driving is provided, and on the basis that the transient state and steady-state performance of an attitude system are guaranteed, low frequency updating of the control law is achieved. Theflexible-spacecraft-attitude control method based on event driving has the advantages that under the condition that inertial parameter information is unknown, transient state protection and steady-state performance control of the flexible-spacecraft-attitude system are achieved; based on event driving controlling, the updating number of times of the control law is greatly decreased, responding ofan actuator in practical engineering is facilitated, and the flexible-spacecraft-attitude control method based on event driving has the high engineering application value.

Description

technical field [0001] The invention belongs to the field of spacecraft control, and relates to an event-driven flexible spacecraft attitude control method. Background technique [0002] In recent years, with the continuous development of space exploration missions, the high-precision, safe and reliable control of spacecraft has attracted more and more attention. Among them, for the control of spacecraft attitude, the existing PID control method, sliding mode control method, model predictive control method, state Riccati equation-dependent control method, etc.: See literature: Liu Fucheng, Zhu Dongfang, Huang Jing. Spacecraft Dynamics Review of research on attitude determination and control[J].Shanghai Aerospace,2017,34(2):1-29.;Markley F L,Crassidis JL.Fundamentals of spacecraft attitude determination and control[M].New York:Springer,2014.;Silani E ,Lovera M.Magnetic spacecraft attitude control: a survey and some new results[J].Control Engineering Practice,2005,13(3):357-3...

Claims

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Application Information

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IPC IPC(8): G05D1/08
CPCG05D1/0808
Inventor 罗建军魏才盛马卫华王明明袁建平
Owner NORTHWESTERN POLYTECHNICAL UNIV
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