Dynamics response analysis method and system of satellite frame system
A technology of system dynamics and response analysis, applied in the field of dynamic response analysis of satellite gantry system, can solve problems such as payload response amplification, boundary connection stiffness change, stiffness design does not necessarily meet stiffness requirements, etc., to improve design efficiency and , meet the design requirements, improve the effect of design and dynamic analysis level
Active Publication Date: 2018-08-24
BEIJING INST OF SPACECRAFT SYST ENG
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[0003] At present, the design of the bracket mostly takes the component-level payload bracket structure as the research object, but when the payload bracket is installed with the satellite main structure, the stiffness of its boundary connection will change, resulting in the dynamics of the payload bracket structure in the whole satellite state. Properties differ significantly from their structural dynamics in component-level states
Therefore, the stiffness design for the component-level payload bracket does not necessarily meet the stiffness requirements of the payload bracket in the full-star state, and may even further amplify the payload response
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[0047] In order to make the objectives, technical solutions, and advantages of the present invention clearer, the disclosed embodiments of the present invention will be described in further detail below in conjunction with the accompanying drawings.
[0048] At present, the design of the support mostly takes the component-level payload support structure as the research object, but when the payload support is installed with the main structure of the satellite, the boundary connection stiffness will change, resulting in the dynamics of the payload support structure in the whole star state The characteristics are quite different from the structural dynamics in the component-level state. Therefore, the rigidity design for the component-level payload bracket may not necessarily meet the rigidity requirements of the payload bracket in the whole star state, and may even further amplify the payload response. The present invention considers the main structure of the satellite and the sens...
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The invention discloses a dynamics response analysis method and system of a satellite frame system. The method includes: carrying out modal analysis on a support frame according to a finite-element modeling result of the support frame, and when a modal analysis result of the support frame satisfies design demand, carrying out modal analysis on a satellite frame coupling system to obtain frequencyof the satellite frame coupling system; when the frequency of the satellite frame coupling system meets set frequency, carrying out modal analysis on a satellite to obtain acceleration response valuesat feature points of a satellite frame coupling body; determining an acceleration response value at a mounting place of the support frame according to the acceleration response values at the featurepoints of the satellite frame coupling body, and calculating and obtaining pulling force at the mounting place of the support frame; and if the calculated and obtained pulling force at the mounting place of the support frame is smaller than embedded-part pulling force, carrying out redesign until a requirement is satisfied. Through the method, levels of structure design and dynamics analysis of the satellite frame system are increased.
Description
Technical field [0001] The invention belongs to the technical field of dynamic analysis, and in particular relates to a method and system for analyzing the dynamic response of a satellite frame system. Background technique [0002] The payload support structure widely used in satellite engineering may be dynamically coupled with the main structure of the satellite, resulting in a significant amplification of the payload response. Furthermore, the payload bracket and the main structure of the satellite are considered as a whole system (called the star rack system). Because the support structure has the advantages of light weight, simple configuration and less space occupied by the plane, it can reduce the overall mass of the satellite, reduce the difficulty of component processing, and is beneficial to the installation and layout of the instrument. Therefore, the support structure is widely used in modern satellite structure design. As the installation base of payload or equipmen...
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IPC IPC(8): G06F17/50
CPCG06F2111/10G06F30/17G06F2119/06G06F30/23
Inventor 马健王成伦刘凤晶王杰利陈卓一余快苏浩
Owner BEIJING INST OF SPACECRAFT SYST ENG