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A RESEARCH ON SHOCK PREDICTION METHOD CORRELATED WITH FORMOSAT-2 SATELLITE PYRO-SHOCK TEST RESULTS

机译:与FORMOSAT-2卫星热释电试验结果相关的电击预测方法的研究

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At the beginning of a satellite development program, the system engineers have to define the prospectivecomponent environmental specifications based on the selected launch environments for the successive fightcomponent designs or procurements. A stricter specification normally means more budgets for the program. Thus,how to reasonably define the component environmental specifications is a critical task for system engineers.Shock or pyro-shock is one of the important specifications for shock sensitive components. In a launch vehicleuser's guide, the shock environment is normally expressed by shock response spectrum (SRS). The SRS generallyhas high g (gravity) value in the range of high frequencies. Theoretically, the level of shocks will be attenuated bystructure elements, such as panels, beams, fasteners, etc., when shock waves propagate on a structure. There is nosimple and easy way to predict shock propagation on a satellite structure. This paper proposes an analysis methodthat transfers the SRS at the shock source that is usually provided in a launch vehicle user's guide, to time historythen using LS-DYNA as the analysis tool to predict the shock at the positions where are interested on the satellitestructure. To validate the method, the whole processes are applied on the FORMOSAT-2 satellite (which is the 2ndsatellite of NSPO, National SPace Organization of Taiwan, ROC, launched in 2004) and the predicted SRS curvesare compared with FORMOSAT-2 satellite pyro-shock test data.This method is not a rigorous mathematical analysis, but an engineering approach to provide system engineersimmediate and more accountable information for the component shock environment definition.When the whole process is accomplished, several "representative SRS curves" are created. Those curvesrepresent the shock responses on the selected regions of a structure, which can be directly used in the definition ofthe component shock specification.
机译:在开始进行卫星开发计划时,系统工程师必须定义预期的目标。 根据选定的发射环境进行后续战斗的组件环境规格 组件设计或采购。更严格的规范通常意味着该程序需要更多的预算。因此, 对于系统工程师来说,如何合理定义组件的环境规格是一项至关重要的任务。 震动或热震是震动敏感组件的重要规格之一。在运载火箭中 在用户指南中,冲击环境通常由冲击响应谱(SRS)表示。 SRS一般 在高频范围内具有较高的g(重力)值。从理论上讲,冲击的程度将通过 冲击波在结构上传播时的结构元素,例如面板,梁,紧固件等。没有 预测震动在卫星结构上传播的简便方法。本文提出了一种分析方法 可将通常在运载火箭用户指南中提供的冲击源处的SRS转换为时间历史记录 然后使用LS-DYNA作为分析工具来预测对卫星感兴趣的位置处的震动 结构体。为了验证该方法,将整个过程应用于FORMOSAT-2卫星(这是第二颗卫星)。 NSPO卫星,台湾国家空间组织(ROC),于2004年发射)和预测的SRS曲线 将其与FORMOSAT-2卫星热震测试数据进行比较。 此方法不是严格的数学分析,而是为系统工程师提供的工程方法 提供有关组件冲击环境定义的即时且负责任的信息。 当整个过程完成时,将创建多个“代表性SRS曲线”。那些曲线 代表结构所选区域的冲击响应,可直接用于定义 组件冲击规范。

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