摘要
火箭整流罩为薄壁结构,在分离过程中易发生形变,可能与有效载荷发生干涉,影响任务安全性。为评估整流罩分离的可靠性,文章针对某型火箭整流罩建立多柔性体动力学模型,开展旋抛分离过程仿真分析。采用SolidWorks构建三维模型,结合ANSYS Workbench与ADAMS软件进行刚柔耦合模拟,分析整流罩的分离特性与呼吸变形响应。结果表明,整流罩下端为主要变形区域,最大位移约为4.5mm,未超出设定安全分离间隙,分离过程稳定可靠。研究验证了该结构设计该足分离要求,为后续整流罩分离方案的优化提供了理论依据和工程参考。
Rocket fairings are thin-walled structures susceptible to deformation during separation,potentially leading to interference with the payload.To assess separation reliability,a multi-flexible-body dynamics model of a specific rocket fairing was developed.The three-dimensional model was created in SolidWorks,and the spin-off separation process was simulated via ANSYS-ADAMS co-simulation.The results indicate that the maximum deformation,approximately 4.5 mm,occurs at the lower end of the fairing.The separation process is stable and collision-free.This study validates the structural design and provides a theoretical basis and engineering guidance for future fairing optimization.
作者
孙伟
崔哲
巩瑞琦
刘芃山
SUN Wei;CUI Zhe;GONG Ruiqi;LIU Pengshan(School of Mechanical Engineering,North China University of Science and Technology,Tangshan 063210,China)
出处
《航天器环境工程》
2025年第4期362-370,共9页
Spacecraft Environment Engineering
