燃烧室空腔对固体火箭发动机结构阻尼特性的影响

doi:10.7527/S1000-6893.2025.32527

Abstract

Abstract:

Solid rocket motors with a large aspect ratio are prone to acoustic instability combustion in the combustion chamber， leading to abnormal engine operation. To gain a clearer understanding and effective suppression of acoustic instability combustion， from the perspective of system damping， damping numerical simulations were conducted using the OSCILOS solver. These simulations were conducted based on acoustic damping theory， compactness assumptions， and nozzle acoustic boundary conditions， considering different cavity parameters and operating conditions. The variation of damping with the regression of the combustion surface， the influence of different cavity positions and head cavity sizes on the engine damping coefficient， and the impact on acoustic instability were comparatively analyzed. The study found that changing the tail charge to a head charge can significantly increase structural damping at the initial ignition moment by approximately 2 times， provided that the combustion chamber length and acoustic cavity natural frequency remain unchanged. Properly increasing the size of the head cavity can significantly enhance structural damping at the initial ignition moment. The results indicate that reasonably adopting a head cavity in solid rocket motors and appropriately increasing the size of the head cavity according to actual conditions can effectively suppress combustion instability phenomena.

Key words: solid rocket engine, cavity, combustion chamber, damping, unstable sound

CLC Number:

V435

Aohua CHEN, Linquan CHEN, Qiu WU, Junwei LI, Qiang LI, Yi LI. Influence of combustion chamber cavity on structural damping characteristics of solid rocket motors[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(6): 132527.

Figures/Tables 23

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References 29

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内径/mm	阻尼系数/s^-1		误差/%
内径/mm	实验值	仿真值	误差/%
60	-25	-25.786	3.144
80	-18	-18.029	0.161
100	-9	-9.167	1.856
120	-4	-4.167	4.175

声学模态	固有频率/Hz		误差/%
声学模态	实验值	计算值	误差/%
1阶	220	229.05	4.11
2阶	460	465.24	1.13

时刻阶数	0 s	1 s	3 s	最大误差/%
1	218.73	220.33	225.42	2.46
2	463.81	463.73	461.71	2.96
3	670.69	674.26	682.71	1.01
4	869.93	885.96	910.31	2.43
5	1 138.32	1 145.91	1 147.90	0.34

时间/s	平均流速（Ma）	反射系数 R
0	0.012 0	0.71
1	0.013 3	0.68
2	0.015 4	0.64
3	0.017 7	0.60

燃烧时间/s	1阶阻尼/s^-1	2阶阻尼/s^-1
0	-210.627	-200.697
1	-179.331	-172.604
2	-161.241	-158.27
3	-146.097	-144.234

Influence of combustion chamber cavity on structural damping characteristics of solid rocket motors

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燃烧时间/s	头部空腔对应阻尼/s^-1	中部空腔对应阻尼/s^-1	尾部空腔对应阻尼/s^-1
1	-211.296	-109.543 4	-99.018 1
2	-158.298 1	-101.386	-93.748 1
3	-122.697 6	-93.663 7	-88.672 8
4	-97.347	-86.318 8	-83.681

燃烧时间/s	阻尼系数/s^-1
燃烧时间/s	无空腔	30 mm空腔	40 mm空腔	50 mm空腔	60 mm空腔	70 mm空腔	80 mm空腔
0	-87.902 6	-95.870 2	-103.595 9	-110.900 3	-118.731 4	-127.455 2	-137.234
1	-79.915 9	-91.664 1	-99.095 5	-104.969 7	-110.532 7	-116.305 7	-122.528 4
2	-75.390 9	-87.400 6	-95.273 5	-100.829 6	-105.481 2	-109.883 6	-114.354 1
3	-71.551 4	-83.372 2	-91.723	-97.463 1	-101.864 9	-105.676 2	-109.283 1
4	-68.408 4	-79.761 4	-88.335 2	-94.471 6	-98.972 3	-102.622	-105.859 4

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