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Flexible satellite active vibration suppression method based on component force synthesis and fixed time convergence

A fixed-time, vibration-suppressing technology, used in motor vehicles, transportation and packaging, space navigation equipment, etc.

Active Publication Date: 2020-01-31
SUN YAT SEN UNIV
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Problems solved by technology

[0004] The invention discloses a flexible satellite active vibration suppression method based on component force synthesis and fixed time convergence. New approach to simultaneously guarantee attitude accuracy, response time and vibration suppression

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  • Flexible satellite active vibration suppression method based on component force synthesis and fixed time convergence
  • Flexible satellite active vibration suppression method based on component force synthesis and fixed time convergence
  • Flexible satellite active vibration suppression method based on component force synthesis and fixed time convergence

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Embodiment Construction

[0066] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0067] refer to figure 1 As shown, the present invention is realized through the following technical solutions: the present invention proposes an embodiment of a flexible satellite active vibration suppression method based on component force synthesis and fixed time convergence, and the flexible satellite active vibration suppression method includes the following steps:

[0068] Step 1: Based on the Newton-Eulerian method and the Lagrangian method,...

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Abstract

The invention discloses a flexible satellite active vibration suppression method based on component force synthesis and fixed time convergence. The flexible satellite active vibration suppression method comprises the following steps of step 1, establishing a flexible satellite attitude dynamics model with two pairs of large solar panels, and simultaneously establishing a dynamic model of a piezoelectric intelligent material actuator; step 2, designing a fixed time convergence sliding mold controller; step 3, designing a disturbance observer for ensuring a double-layer self-adaptive law with fixed time convergence characteristics; and step 4, outputting a dynamic model of the piezoelectric intelligent material actuator, implementing processing by adopting a continuous component force synthesis control idea, generating a new control torque command to be applied to a flexible accessory to counteract the influence of elastic vibration, and ensuring the attitude stability of a satellite body. The flexible satellite active vibration suppression method has the advantages of high attitude control precision and strong robustness. Meanwhile, a continuous component force synthesis method is introduced into a closed-loop control process through a piezoelectric sheet attached to the flexible accessory, vibration is inhibited, and the system interference is reduced.

Description

technical field [0001] The invention belongs to the technical field of spacecraft vibration control, in particular to an active vibration suppression method for flexible satellites based on component force synthesis and fixed time convergence. Background technique [0002] In recent years, my country has carried out many spacecraft development tasks in the field of space applications, including space stations, new Fengyun series meteorological satellite systems, ocean observation satellite systems, Beidou navigation satellite systems, lunar / fire detection spacecraft and deep space probes etc., and these spacecraft without exception have used larger-sized solar panels to provide sufficient power supply for the equipment on the spacecraft. The installation of flexible accessories represented by solar panels or large antennas outside the spacecraft body is becoming more and more common in the spacecraft of various countries in the world today, but what follows is that the flexib...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/24B64G1/245Y02T90/00
Inventor 张亮
Owner SUN YAT SEN UNIV
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