液体火箭的POGO振动研究与参数分析  

Research and Parameter Analysis of POGO Vibration in Liquid Rocket

作　　者：严海[1] 方勃[1] 黄文虎[1] 

机构地区：[1]哈尔滨工业大学航天学院,哈尔滨150001

出　　处：《导弹与航天运载技术》2009年第6期35-40,共6页Missiles and Space Vehicles

基　　金：国防科工委民用航天预研项目资助(C4120062301)

摘　　要：通过建立一个蓄压器-推进系统的耦合动力学模型,研究了蓄压器对推进系统振动频率的影响,并利用临界阻尼法分析了蓄压器-推进系统的稳定性。分析结果表明,临界阻尼比的增大会导致火箭结构系统失稳,而增大蓄压器气蚀柔度可降低临界阻尼比,提高系统稳定性;产生POGO振动时,结构振动的加速度响应最大,且推力脉动与加速度响应的相位差为-π/2;蓄压器在推进系统上的安装位置对POGO抑制有重要影响,给出了蓄压器安装的最佳位置。A dynamical model of the accumulator-propulsion coupling systems is established. The influence of the accumulator to the frequencies of the propulsion system is researched, and the critical damping is introduced to analyze the stability of system. Analytical results show that the liquid rockets may lose stability as the critical damping increasing. To avoid the coupling vibration, the cavitation factor must be increased. The acceleration response of the vibration reaches maximum when the POGO vibration happens, and the phase difference between the pulsatory thrust force and the acceleration response is equal to -n/2. Moreover, because the position of the accumulator installation in the propulsion is important for the control of the POGO vibration, an optimal position is obtained.

关 键 词：液体火箭 POGO振动 蓄压器 稳定性 

分 类 号：V444.33[航空宇航科学与技术—飞行器设计] TB664[一般工业技术—制冷工程]