基于故障分辨能力的火箭发动机测量参数选择方法

doi:10.7527/S1000-6893.2023.28522

Abstract

Abstract:

To address the problem of measuring parameters selection of liquid rocket engines， we propose a model-based method to improve fault recognition and system reliability. The nonlinear and static mathematical model of the engine system is built， the fault feature list metrics of fault recognition， robustness and system reliability of the engine measurement feature subset are then established respectively， and the optimization design is proposed based on the improved multi-objective binary particle swarm optimization （MOBPSO）. With the optimized measuring parameters， the number of distinguishable faults has increased from 9 to 13， the robustness is equivalent to the original layout， and the risk criterion has increased slightly. The important role of the subsystem mixture ratio in fault recognition is further explored and its mechanism analyzed. The method proposed in this paper has a good application value for the selection of measurement characteristics of other complex， closed-loop dynamic systems.

Key words: liquid rocket engine, model-based method, measuring parameters selection, particle swarm optimization, agglomerative hierarchical clustering, principal component analysis

CLC Number:

V434+.11

Xiaopu ZHANG, Feng REN, Pengli XU, Zhimin LI, Caihong SU. Selection method of measuring parameters for rocket engine based on fault recognition[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(22): 128522.

Figures/Tables 15

Table 1

Mathematical definition of faults

故障类型	故障模拟方式	故障的数学定义	故障系数取值范围/%
泄漏故障	管路、阀门泄漏点下游流量q'为上游流量q的ζ_x倍（ζ_x<1）	$q' = ζ x q$	0~30
堵塞故障	节流元件堵塞点流阻系数k'为设计值k的ζ_d倍（ζ_d>1）	$k' = ζ d k$	100~3 000
转子效率下降（结构破坏、碰磨）	涡轮、泵转子效率η'为设计值η的ζ_e倍（ζ_e<1）	$η' = ζ e η$	70~100
入口压力异常	入口压力p $o'$ 为设计值p_o的ζ_o倍（ζ_o<1）	$p o' = ζ o p o$	90~120

Table 1

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故障发生概率评级	不同严酷度评级下的风险指数
故障发生概率评级	Ⅰ 灾难的	Ⅱ 致命的	Ⅲ 严重的	Ⅳ 轻度的
A级（P>10^-1）	1	3	7	13
B级（10^-2<P≤10^-1）	2	5	9	16
C级（10^-4<P≤10^-2）	4	6	11	18
D级（10^-6<P≤10^-4）	8	10	14	19
E级（P≤10^-6）	12	15	17	20

测量方式	故障模式	局部影响	最终影响	严酷度	可能性	风险指数
氧化剂喷注前压力传感器	氧化剂外漏	推力室性能降低	入轨精度降低	Ⅲ	E	17
转速线圈	元器件失效	转速线圈测量功能失效	对飞行无影响	Ⅳ	D	20

序号	权重取值	I₁	I₂
1	ω=0.9	4.53	50.15
2	ω=0.4	4.60	47.35
3	自适应权重	4.47	44.05

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Selection method of measuring parameters for rocket engine based on fault recognition

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