Rocket modal parameter determination method, device and equipment and storage medium

A modal parameter and determination method technology, applied in the field of aircraft, can solve the problems of the same-order bending mode shape and the conflict of control system design ideas, and achieve the effect of reducing complexity and improving efficiency

Active Publication Date: 2021-02-05
北京星河动力航天科技股份有限公司 +1
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Problems solved by technology

[0004] In view of the shortcomings of the existing methods, this application proposes a method, device, equipment and storage medium for determining the modal parameters of a rocket, so as to solve the problem of the same-order bending mode shape and control system obtained by the existing modal parameter calculation method. Contradictory technical issues with design ideas

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  • Rocket modal parameter determination method, device and equipment and storage medium
  • Rocket modal parameter determination method, device and equipment and storage medium
  • Rocket modal parameter determination method, device and equipment and storage medium

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[0026] The present application is described in detail below, and examples of embodiments of the present application are shown in the drawings, wherein the same or similar reference numerals denote the same or similar components or components having the same or similar functions throughout. Also, detailed descriptions of known technologies will be omitted if they are not necessary to illustrate the features of the present application. The embodiments described below by referring to the figures are exemplary only for explaining the present application, and are not construed as limiting the present application.

[0027] Those skilled in the art can understand that, unless otherwise defined, all terms (including technical terms and scientific terms) used herein have the same meanings as commonly understood by those of ordinary skill in the art to which this application belongs. It should also be understood that terms, such as those defined in commonly used dictionaries, should be ...

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Abstract

The invention provides a rocket modal parameter determination method, device, equipment and a storage medium. The rocket modal parameter determination method comprises the steps: when a whole rocket modal model of a rocket vibrates under the action of an excitation pulse signal, acquiring the modal shape of at least one order of bending mode; and converting the modal shape of each order of bendingmode into a modal shape of a pitching plane and a modal shape of a yawing plane, and determining the bending mode quality of the pitching plane and the bending mode quality of the yawing plane, the whole rocket modal model being a computer simulation model of a rocket overall structure system. The method is suitable for the situation that the rocket is not strictly axisymmetric, accords with theidea that the control system is independently designed according to the pitching direction and the yawing direction, facilitates the design and use of the control system, facilitates the development and design of the rocket, and can simplify the modal test.

Description

technical field [0001] The present application relates to the field of aircraft technology, and in particular, the present application relates to a method, device, equipment and storage medium for determining modal parameters of a rocket. Background technique [0002] The modal parameters of the launch vehicle (including modal shape, modal mass, modal frequency, etc.) are the input conditions for the design of the rocket control system, and are crucial to the servo-elastic stability of the rocket flight. [0003] When determining the modal parameters based on the rocket model, since the mass and stiffness distribution of the rocket is not strictly axisymmetric, the calculated two bending mode shapes of the same order will not be completely along the pitch direction and yaw direction, and most modes The mode shape exists in a plane at any angle with the pitch direction and yaw direction, which contradicts the idea that the control system is designed separately according to th...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20
CPCG06F30/20
Inventor 刘百奇董威利刘建设
Owner 北京星河动力航天科技股份有限公司
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