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Satellite time optimal posture maneuvering method with reaction flywheel

An attitude maneuvering and time-optimized technology, applied in the field of spacecraft control, can solve the problems of dynamic considerations and the accuracy needs to be improved, and achieve the effect of high accuracy

Inactive Publication Date: 2012-02-08
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The optimal attitude redirection maneuver in the prior art does not consider the dynamics of the actuator in the attitude dynamics of the satellite, and the accuracy needs to be improved

Method used

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  • Satellite time optimal posture maneuvering method with reaction flywheel
  • Satellite time optimal posture maneuvering method with reaction flywheel
  • Satellite time optimal posture maneuvering method with reaction flywheel

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Experimental program
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Embodiment

[0153] In the embodiment, a rigid satellite with three reaction wheels is taken as an example, and the three reaction wheels are installed on the inertial axis of the satellite. Satellite dynamics include the dynamics of the reaction wheels. The parameters of the rigid body satellite are shown in Table 1 below, and the initial and terminal state values ​​are shown in Table 2.

[0154] Table 1 Relevant parameters of rigid body satellites

[0155]

[0156] Among them, I xx , I yy , I zz are the moments of inertia of the satellite on the three main axes of inertia respectively, I w is the moment of inertia of the reaction wheel.

[0157] Table 2 Initial and terminal conditions of this example

[0158]

[0159] q(t 0 ), ω(t 0 ), Ω(t 0 ), q(t f ), ω(t f ), Ω(t f ) represent the values ​​of attitude quaternion, attitude angular velocity and reaction wheel rotational angular velocity at the initial moment and terminal moment, respectively.

[0160] The open-loop op...

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Abstract

The invention discloses a satellite time optimal posture maneuvering method with a reaction flywheel. The method comprises the following steps of: (1) establishing a spacecraft posture motion model considering reaction wheel dynamics, and establishing a satellite time optimal posture maneuvering model on this basis; (2) obtaining an open-loop optimal control for the spacecraft posture motion model considering reaction wheel dynamics; and (3) obtaining a robust feedback controller to realize spacecraft redirection posture maneuvering. According to the invention, fastest posture maneuvering of the spacecraft is realized; moreover, high accuracy and strong robustness of the maneuvering control are obtained; and moment saturation and momentum saturation restriction of an executing mechanism can be satisfied.

Description

technical field [0001] The invention relates to a fast and high-precision maneuvering control method for a spacecraft, in particular to a time-optimized attitude maneuvering method for a satellite with a reaction flywheel, and belongs to the technical field of spacecraft control. Background technique [0002] The shortest time redirection maneuver problem of spacecraft with reaction wheels is to find a control that makes the spacecraft maneuver from a stable attitude to another stable attitude in the shortest time. Some optimal control laws are obtained by using direct methods or indirect methods. K.D.Bilimoria, and B.Wie, "Time-Optimal Three-Axis Reorientation of a Rigid Spacecraft," Journal of Guidance Control and Dynamics, Vol.16, No.3, 1993, pp.446-452. Bang-bang control for three-axis reorientation of a spacecraft, and demonstration that the rotation around the characteristic axis is not time-optimal. H. Shen, and P. Tsiotras, "Time-Optimal Control of Axisymmetric Rig...

Claims

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Application Information

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IPC IPC(8): B64G1/24
Inventor 周浩刘冠南陈万春
Owner BEIHANG UNIV