The invention discloses a design method for load conditions of internal components of a spacecraft. Comprising the steps of obtaining an equivalent model with similar dynamic characteristics according to an original model; carrying out response analysis on the equivalent model under each working condition, obtaining the load of each one-dimensional unit, and converting the acceleration equivalent overload of each one-dimensional unit; performing response analysis on the original model under each working condition to obtain mean overload of node acceleration response amplitudes of the internal components; and comparing the equivalent overload with the mean overload to obtain a final load condition of the internal component. According to the method, the load condition magnitude between the spacecraft internal component and the spacecraft main structure under different working conditions can be effectively obtained, the load condition magnitude comprises a time domain transient analysis working condition, a frequency domain vibration analysis working condition and the like, and the amplification effect brought by a conventional solving method is avoided.
本发明公开了一种航天器内部组件载荷条件设计方法。包括:根据原始模型获得动力学特性近似的等效模型;对等效模型进行各工况下的响应分析,获得各个一维单元的载荷并折算其加速度等效过载;对原始模型进行各工况下的响应分析,获得内部组件的节点加速度响应幅值的均值过载;对比等效过载和均值过载,得到最终的内部组件的载荷条件。本发明所述方法可以有效获得航天器内部组件在不同工况下与航天器主结构之间的载荷条件量级,包含时域瞬态分析工况和频域振动分析工况等,避免了常规求解方法带来的放大效果。
Spacecraft internal component load condition design method
一种航天器内部组件载荷条件设计方法
13.08.2024
Patent
Elektronische Ressource
Chinesisch
IPC: | B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung |
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