基于油气支承自由边界模拟的全箭模态试验技术研究  

Study on Integrated Launch Vehicle Modal Test Techniques Based on Hydraulic Support System

作　　者：张永亮[1] 侯京锋[1] 苏里[1] 任冬辉[1] 贾文成[1] Zhang Yong-liang;Hou Jing-feng;Su Li;Ren Dong-hui;Jia Wen-cheng(Beijing Institute of Structure and Environment Engineering,100076,Beijing)

机构地区：[1]北京强度环境研究所,北京100076

出　　处：《导弹与航天运载技术》2020年第4期107-111,共5页Missiles and Space Vehicles

摘　　要：为了验证基于油气支承自由边界模拟开展全箭模态试验的工程应用,分别开展了基于小型油气支承系统验证方法和全箭模态试验应用可行性研究,对油气支承单元和系统进行了验证方案设计和实施,并对油气支承系统的关键设计指标、系统功能、稳定性和可靠性进行测量验证。最后开展某型号运载火箭的油气支承自由边界模拟和弹簧钢索悬挂自由边界模拟的全箭模态验证对比试验,验证了试验技术的可行性和有效性,也为未来大型运载火箭的研制提供试验技术支撑并积累了工程经验。In order to verify the engineering application of full rocket modal test based on free boundary simulation of oil-gas support, the verification method based on small hydraulic support system and the feasibility study of full rocket modal test application are carried out respectively. The verification scheme design and implementation of hydraulic support unit and system are carried out, and the key design indexes, system function, stability and reliability of hydraulic support system are measured and verified. Finally, integrated launch vehicle modal verification comparative test of a certain type of launch vehicle is carried out, which verified the feasibility and effectiveness of the test technology, and also provided experimental technical support and accumulated engineering experience for the future development of large launch vehicles.

关 键 词：大型运载器 油气支承 模态试验 支承系统设计 

分 类 号：V216.5[航空宇航科学与技术—航空宇航推进理论与工程]