重型运载火箭是一个国家进入太空能力的重要标志，也是我国载人登月和深空探测等任务的重大需求；其结构系统低频模态密集的特点造成了Pogo被动抑制设计的“低频灾难”，而推进系统新型液氧/煤油补燃循环发动机的复杂气路则增加了Pogo建模与机理分析的困难。对此本项目将首先考虑重型火箭推进系统特有的气路熵波特性及气-液两相流问题，建立起适用于控制系统设计和机理分析的气路-液路-结构耦合动力学模型,并通过频域稳定性分析和时域仿真等开展Pogo振动机理研究；然后，针对Pogo振动模型参数的大偏差和时变性特点，将自适应控制理论和LQR基准控制器结合，提出Pogo主动抑制的自适应增广控制方法；最后研制Pogo主动抑制器，开展Pogo主动抑制实验研究。本项目的实施将为一般的气-液-固多学科耦合振动控制问题提供新思路和方法，进而推动我国重型运载火箭Pogo主动抑制技术的发展。

Heavy launch vehicle(HLV) is an important symbol of a country's ability to enter space, and it is also a great demand for manned lunar landing and deep space exploration in China. The structure system of HLV has the characteristics of low-frequency-mode density, which result in the ‘low frequency disaster’ for passive Pogo suppression design, and the complex gas parts of the new LOX/kerosene staged combustion cycle engine of the propulsion system greatly increase the difficulty of Pogo modeling and its mechanism analysis. To solve the above problems, the lumped-parameter gas-liquid-structure coupling dynamic model, which is applicable for control system design and mechanism analysis, is firstly derived by considering the entropy-wave characteristic and gas-liquid two-phase flow problems in the propulsion system of HLV. The mechanism of Pogo vibration is studied based on frequency-domain stability analysis, time-domain simulation and sensitivity analysis. Secondly, considering the large deviation and time-varying characteristics of Pogo parameters, a robust adaptive augmenting control method for active Pogo suppression is proposed by combining the adaptive control theory with the LQR baseline controller. Finally, the active Pogo suppressor is developed and the experimental study of active Pogo suppression is carried out. The implementation of this project will provide new solutions and methods for the vibration suppression of the gas-liquid-solid multi-disciplinary coupling system, and further promote the development of active Pogo suppression technology for the HLV in China.