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Parameter optimization method for spacecraft double-loop sliding mode variable structure attitude control

A sliding mode variable structure and attitude control technology, applied in the field of aerospace control, can solve problems such as excessive control torque, and achieve the effect of low energy consumption

Active Publication Date: 2017-01-04
DALIAN UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

In addition, if the dual-loop sliding mode variable structure controller is used to realize the attitude control tracking of the spacecraft, there will be a problem of excessive control torque

Method used

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  • Parameter optimization method for spacecraft double-loop sliding mode variable structure attitude control
  • Parameter optimization method for spacecraft double-loop sliding mode variable structure attitude control
  • Parameter optimization method for spacecraft double-loop sliding mode variable structure attitude control

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Embodiment 1

[0064] The embodiments of the present invention are implemented on the premise of the technical solutions of the present invention, and detailed implementation methods and specific operation processes are given, but the protection scope of the present invention is not limited to the following embodiments.

[0065] First set the spacecraft physical parameter data. The main moment of inertia J of the spacecraft xx =86kg.m 2 , J yy =85kg.m 2 , J zz =113kg.m 2 . Inertia reduction ΔJ xx , ΔJ yy , ΔJ zz Both are set to 5kg.m 2 ;Disturbance torque d=0.005[cost costcost] T ;Initial attitude angle The equivalent attitude angle is [50° -60° 70°] T ; initial angular velocity ω 0 Set to 0; desired attitude angle θ e and the desired angular velocity ω e Both are 0; set the parameter μ=10 in the inner loop control law. The parameter of the double-loop sliding mode control law to be optimized in the simulation is k 1 、k 2 , ρ 1 , ρ 2 . During the simulation calculation,...

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Abstract

The present invention relates to an attitude control parameter optimization method, in particular to a spacecraft double-loop sliding mode variable structure attitude control parameter optimization method, which establishes a multi-objective genetic algorithm based on weight coefficients to optimize sliding mode variable structure controller parameters Model, the model takes the controller parameters as variables, the control torque as constraints, and the optimal time and power consumption as the goal. The problem that this method focuses on is to obtain a set of optimal controller parameters under the control torque output constraints, so that the control system has the performance of low power consumption and faster convergence speed.

Description

technical field [0001] The invention relates to an attitude control parameter optimization method, in particular to a spacecraft double-loop sliding mode variable structure attitude control parameter optimization method, which belongs to the field of aerospace control. Background technique [0002] When the spacecraft is doing space rendezvous and docking missions, it is required that the spacecraft can perform fast maneuvers with large angle attitudes and low power consumption. In addition, due to the large range of attitude angle changes and drastic changes in angular velocity of this mission, and with the consumption of fuel and changes in flexible accessories, its moment of inertia changes greatly, and at the same time, it is affected by external disturbance torques, resulting in very difficult control of the spacecraft. big uncertainty. Therefore, the spacecraft control system with better robustness is a research hotspot nowadays. [0003] Because sliding mode variabl...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08G05B13/04B64G1/24
Inventor 张强黄强张建新
Owner DALIAN UNIV
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