A Vibration Suppression Method Using Root Rotation of Flexible Parts

A flexible component and vibration suppression technology, applied in mechanical vibration control, non-electric variable control, motor vehicles, etc., to achieve the effect of reducing disturbance

Active Publication Date: 2021-10-26
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] In order to overcome the deficiencies of the prior art, the present invention provides a vibration suppression method using the root rotation of the flexible component, which can quickly suppress the vibration of the flexible component without greatly increasing the complexity of the system

Method used

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  • A Vibration Suppression Method Using Root Rotation of Flexible Parts
  • A Vibration Suppression Method Using Root Rotation of Flexible Parts
  • A Vibration Suppression Method Using Root Rotation of Flexible Parts

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specific Embodiment

[0038] This embodiment is a satellite with one flexible member. The flexible part can perform three-dimensional rotation relative to the satellite connection root.

[0039] 1. Establishment of satellite dynamics model with flexible rotating parts.

[0040] In this embodiment, the vibration model of the flexible part takes the first 5 orders, and the satellite model parameters are established as follows:

[0041]

[0042]

[0043]

[0044] Ω S =diag{0.67 0.89 1.51 2.54 4.53},

[0045] ζ=diag{0.005 0.005 0.005 0.005 0.005}.

[0046] In the calculation, the initial attitude angle of the satellite is zero, the initial angular velocity is zero, the initial value of the second-order modal coordinate of the flexible component vibration is 0.1, and the initial value of the second-order to fifth-order modal coordinates is zero. Simulates the case where a flexible part has an initial vibrational displacement.

[0047] 2. Calculation of root rotation control of flexible com...

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Abstract

The invention discloses a vibration suppression method utilizing the rotation of the root of a flexible component, which can quickly suppress the vibration of the flexible component without greatly increasing the complexity of the system. First, according to the mass parameters of the satellite and the modal analysis results of the flexible part, a dynamic model of the satellite with flexible rotating parts is established. Next, the root of the flexible component suppresses the flexural vibration through the rotation angular acceleration, and feeds back the rotation angle and angular velocity of the component itself, so as to avoid excessive rotation angle and angular velocity of the flexible component root. Finally, in the attitude control of the satellite body, the disturbance generated by the root motion of the flexible component is compensated to ensure the high-precision control of the satellite body. The method proposed by the invention can quickly suppress the low-order vibration of the flexible component, and at the same time, the rotational motion of the root of the flexible component converges, avoiding the impact on the orientation of the component. In addition, the additional disturbance caused by the rotation of the root of the flexible component is compensated to reduce the influence on the control of the satellite body.

Description

technical field [0001] The invention belongs to the technical field of spacecraft control, and in particular relates to a vibration suppression method. Background technique [0002] In recent years, the structure of spacecraft is developing in the direction of large-scale, low rigidity and flexibility. Due to the characteristics of low structural stiffness and dense modal frequency, the flexible parts on the satellite will be subjected to various disturbances during orbital operation, causing structural vibration. Long-term vibration will reduce the attitude stability and pointing accuracy of the satellite, and affect the performance and imaging quality of the satellite. It is necessary to implement active vibration control on the flexible components of the satellite to quickly suppress structural vibration. [0003] The commonly used active vibration control methods for flexible components include placing piezoelectric elements in flexible structures for vibration control,...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D19/02B64G1/22
CPCB64G1/22G05D19/02
Inventor 刘莹莹李晓云吴永胜周军王光远何德华
Owner NORTHWESTERN POLYTECHNICAL UNIV
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