Simulation research of Pogo suppression of liquid rocket based on fluid active control method
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摘要:
针对传统Pogo被动抑制方法难以满足新型运载火箭由于运载能力提升带来的新的脉动抑制需求，研究液体火箭Pogo主动抑制的方案与控制方法，并开展仿真验证工作。首先建立液体火箭流体-结构闭环耦合模型，利用Matlab/Simulink在时域上仿真了液体火箭Pogo振动现象。提出了高压溢流式和低压活塞式两种主动抑制方案，研究了基于次级通道在线辨识的自适应滤波控制方法。搭建了基于AMESim和Matlab/Simulink联合仿真环境的仿真验证模型，开展Pogo主动抑制仿真。仿真结果表明：高压溢流式和低压活塞式均能对流体压力脉动实现90%以上的幅值衰减，同时消除了火箭的Pogo振动，验证了主动抑制方案的有效性。
Abstract:The conventional Pogo suppression method uses the installation of accumulators in the fluid system, however, the improvement of the carrying capacity of new launch vehicles is a challenge to the conventional passive accumulator, since it is unable to meet the suppression needs of larger flow pulsations. Therefore, the scheme and control method of Pogo active suppression were studied, and simulation validation was achieved. Firstly, a closed-loop coupling model of propulsion system and structural system of liquid rocket was established by using software Matlab/Simulink, and the Pogo vibration was reproduced in the time domain. Secondly, two active suppression schemes, including piston type control for low-pressure pulsation and relief type control for high pressure pulsation, were proposed. The control method of adaptive filtering algorithm based on secondary path online identification was studied. The simulation validation was modelled with software AMESim and Matlab/Simulink, and active suppression of Pogo was achieved. The simulation results showed that both relief scheme for high-pressure pulsation and piston scheme for low-pressure pulsation can achieve more than 90% amplitude attenuation, and eliminate the Pogo vibration of liquid rocket, verifying the effectiveness of the active suppression scheme.
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Key words:
- Pogo /
- liquid rocket /
- vibration suppression /
- active control /
- adaptive filter
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图 9 Pogo闭环耦合系统振动仿真模型
Figure 9. Simulation model of the Pogo closed-loop coupled system
图 12 高压溢流式Pogo主动抑制方案示意图
Figure 12. Schematic diagram of active Pogo suppression using high pressure relief control
图 13 低压活塞式Pogo主动抑制方案示意图
Figure 13. Schematic diagram of active Pogo suppression using piston-type control
图 15 变频工况主动控制参考信号频率更新流程图
Figure 15. Flow chart of reference signal frequency update for active control under variable frequency operation
图 16 高压溢流式主动抑制仿真模型
Figure 16. Simulation model of active control of high pressure relief control
图 17 高压溢流式Pogo抑制仿真泵出口处压力脉动曲线
Figure 17. Simulation result of pump outlet pressure pulsation using high pressure relief control for Pogo suppression
图 18 低压活塞式主动抑制仿真模型（AMESim中的液压系统模型）
Figure 18. Simulation model of piston active suppression for low pressure operation （hydraulic system model in AMESim）
图 19 低压活塞式Pogo抑制仿真泵入口处压力脉动曲线
Figure 19. Simulation result of pump inlet pressure pulsation using low pressure piston control for Pogo suppression
表 1 液体火箭推进系统参数
Table 1. Parameters of liquid rocket propulsion system
参数 数值 参数 数值 推进剂密度$ \rho $/10−3 （kg/cm3） 1.115 燃烧室阻抗$ [{C^*}/ （{A_{\mathrm{t}}}g） ] $/10−4 （N·s/cm5） 1.459 泵前管路横截面积$ {A_{\mathrm{s}}} $/cm2 92 燃烧室特征系数$ {A_{{\mathrm{th}}}}{C_{\mathrm{f}}} $/cm2 1838.6 泵前管路长度$l$/cm 104 燃烧室时滞$ {\tau _{\mathrm{c}}} $/s 0.0025 泵及泵后管组件阻抗$ {R_{\text{p}}} + {R_{\text{d}}} $/10−4 （kg·s/cm5） 4.719 贮箱、泵、燃烧室模态比 1 泵及泵后管组件惯性$ {L_{\text{p}}} + {L_{\text{d}}} $/10−6 （kg·s/cm5） 3.861 模态阻尼比$ \xi $ 0.01 
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表 2 飞行过程时变参数
Table 2. Time-varying parameter during the flight
燃烧时间
百分比/%模态频率
$ \omega $/（rad/s）广义质量
$ M $/（kg·s2·cm）泵增益系数
m+1贮箱液位高度
${h_{\text{t}}}$/cm泵汽蚀柔度
$ {C_{\mathrm{b}}} $/（cm5/kg）0 72 464.31 1.0 634.99 9.322 60 92 89.29 1.3 279.39 46.61 80 104 32.14 1.8 160.02 93.32 95 126 8.929 3.0 68.58 174.49 100 148 4.466 5.4 38.1 349.58
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表 3 高压溢流式主动控制算法参数
Table 3. Parameters of active control algorithm of high pressure relief control
滤波器 滤波器阶数 迭代步长 控制滤波器$W （{\textit{z}}） $ 2 0.0006 辨识滤波器$\hat S （{\textit{z}}） $ 4 0.01
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