注气式POGO抑制系统模型研究  

Model Study on Gas-injected POGO Suppression System

作　　者：王楠 容易 胡久辉 张青松 秦旭东 Wang Nan;Rong Yi;Hu Jiu-hui;Zhang Qing-song;Qin Xu-dong(Beijing Institute of Astronautical Systems Engineering,Beijing,100076)

机构地区：[1]北京宇航系统工程研究所,北京100076

出　　处：《导弹与航天运载技术》2020年第5期32-37,共6页Missiles and Space Vehicles

摘　　要：注气式POGO抑制系统具有能量值高、结构紧凑、制造成本低等特点,可满足大型液体运载火箭的POGO抑制需求。以某运载火箭的注气式POGO抑制系统为研究对象,推导建立了注气式POGO抑制系统的动力学模型,研究表明排气效应对蓄压器东特性的影响可忽略,基于动力学模型讨论注气式蓄压器相比于贮气式蓄压器的性能优势,最后通过试验验证了注气式蓄压器线性化动特性模型的正确性。Gas-injected POGO suppression system is of high energy,compact structure and low manufacturing cost,which can meet the POGO suppression demand of liquid launch vehicle.Taking the POGO suppression system of one liquid launch vehicle as research object,the dynamic model of the POGO suppression system is established.Research shows that exhaust effect of accumulator dynamic characteristics is negligible.The performance advantages of the gas-injected accumulator compared with the gas-stored accumulator are discussed based on the dynamic model.The correctness of the model deduction assumption is verified by the test.

关 键 词：POGO 蓄压器 动力学模型 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]