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本文给出阿里安3运载器在飞行期间作用在有效载荷上的动态载荷的预测方法。这种研究通常称之为“耦合分析”,它限于较高的纵向激振:发生在主活门关掉之后的第二级推力衰减。整个结构当做有效载荷和运载器的组装结构对待;前者用简化的“有效质量”模型,后者用详细的“有限元”模型表示。运载器/有效载荷界面的加速度用以下两种方法计算:——第一个方法用模态迭加法,它要求完整系统(运载器+有效载荷)动特性的全部信息。——第二个方法是基于直接积分的方法,它可以不通过动态特性的模态计算而直接求解运动方程。这种分析是在 L01、L03和 L04次飞行中观测的若干次推进衰减情况下进行的,而且考虑了激励的散度,并采用综合的发动机关机情况。方法应用于第一次 Ariane3(L10次飞行)任务,这次任务是进行 ECS2和WESTAR6双星发射,并考虑了 SYLDA 双星发射连接架。
This paper presents a method of predicting the dynamic load of Ariane 3 payload during payload flight. This type of research, often referred to as “coupling analysis,” is limited to higher longitudinal excitations: the second stage thrust decay occurs after the main valve is switched off. The whole structure is treated as a payload and as an assembly structure of the carrier; the former uses a simplified “effective mass” model, the latter with a detailed “finite element” model. The acceleration of the carrier / payload interface is calculated in two ways: - The first method uses a modal superposition method, which requires full information of the dynamic behavior of the complete system (carrier + payload). - The second method is based on the method of direct integration which directly solves the equations of motion without modal computation of dynamic properties. This analysis was carried out for several propulsive attenuations observed in flights L01, L03 and L04, taking into account the divergence of the incentives and the use of a comprehensive engine shutdown. The method was applied to the first mission of Ariane 3 (L10 flight), which was to launch the binary launch of ECS2 and WESTAR6 and to consider the SYLDA binary launch launch.