基于旋转阀的固体推进剂压强耦合响应测试方法

doi:10.3969/j.issn.1000-1093.2021.03.007

摘要/Abstract

摘要： 针对固体发动机燃烧不稳定问题，提出一种基于旋转阀的固体推进剂压强耦合响应测试方法，并对应设计了一套可开展冷气和推进剂点火实验的旋转阀实验系统。通过23 Hz、46 Hz、69 Hz 3种不同振荡频率的冷气实验及理论计算，发现两种结果对比误差最大值为4.35%，验证了圆光栅定位组件测试旋转阀次级排气通道面积和压强延迟时间的有效性。进行23 Hz、46 Hz、69 Hz、 115 Hz、138 Hz 5种振荡频率的固体推进剂点火实验，结果表明：燃烧室平均压强受振荡频率的影响，由23 Hz的2.88 MPa减小至138 Hz的2.523 MPa；被测推进剂的压强耦合响应函数受振荡频率影响较小，维持在0.80±0.13；该旋转阀方案可行和可靠。

关键词: 固体发动机, 旋转阀, 固体推进剂, 压强耦合响应, 燃烧不稳定

Abstract: For the combustion instability of solid motors, an experimental method of pressure-coupled response of solid propellant based on rotary valve is proposed, and a rotary valve experimental system for cold gas and solid propellant ignition experiments is designed. In the cold gas experiments and theoretical calculations of 23 Hz, 46 Hz and 69 Hz oscillation frequencies, the maximum error of the two methods is 4.35%, which verifies the effectiveness of the circular grating positioning assembly to obtain the secondary exhaust passage area and pressure delay time of the rotary valve. Five ignition experiments of solid propellant at 23 Hz, 46 Hz, 69 Hz, 115 Hz and 138 Hz oscillation frequencies were carried out. The results show that the mean pressure of the combustion chamber is affected by the oscillation frequency, which is reduced from 2.88 MPa at 23 Hz to 2.523 MPa at 138 Hz. The pressure-coupled response function of the measured solid propellant is less affected by the oscillation frequency, which is maintained at 0.80±0.13. The rotary valve scheme is feasible and reliable.

Key words: solidmotor, rotaryvalve, solidpropellant, pressure-coupledresponse, combustioninstability

中图分类号:

V512⁺.2

席运志, 李军伟, 陈雪莉, 韩磊, 王宁飞. 基于旋转阀的固体推进剂压强耦合响应测试方法[J]. 兵工学报, 2021, 42(3): 511-520.

XI Yunzhi, LI Junwei, CHEN Xueli, HAN Lei, WANG Ningfei. Experimental Method for Pressure-coupled Response of Solid Propellants Based on Rotary Valve[J]. Acta Armamentarii, 2021, 42(3): 511-520.

参考文献

［1］颜密. AP/HTPB复合推进剂压力耦合响应测试方法与数值模型研究[D].北京：北京理工大学, 2017.
YAN M. Research on testing methods and numerical models of pressure-coupled response of AP/HTPB composite propellant [D]. Beijing：Beijing Institute of Technology, 2017. (in Chinese)
[2] 叶振威,余永刚.脉冲点火射流与高氯酸铵/端羟基聚丁二烯固体推进剂耦合燃烧的试验研究及数值模拟[J].兵工学报,2018,39(8):1507-1514.
YE Z W, YU Y G. Experimental research and numerical simulation of coupling combustion of pulsed jet and AP/HTPB propellant [J]. Acta Armamentarii, 2018, 39(8): 1507-1514. (in Chinese)
[3] 刘佩进，何国强. 固体火箭发动机燃烧不稳定及控制技术[M]. 西安:西北工业大学出版社, 2015.
LIU P J, HE G Q. Solid rocket motor combustion instability and control technology [M]. Xi'an: Northwestern Polytechnical University Press, 2015. (in Chinese)
[4] CULICK F E C, PAUL K. Unsteady motions in combustion chambers for propulsion systems: AG-AVT-039 [R]. Amsterdam, the Netherlands: Advisory Group for Aeronautical Research and Deve- lopment North Atlantic Treaty Organization, 2006.
[5] STRAND L D, BROWN R S. Laboratory test methods for combustion stability properties of solid propellants[M]∥ DELUCA L T， PRICE E W， SUMMERFIELD M. Nonsteady Burning and Combustion Stability of Solid Propellants. Reston,VA , US: AIAA, 1992: 689-718.
[6] ANDREPONT W, SCHONER R. The T-burner test method for determining the combustion response of solid propellants[C]∥Proceedings of the 8th Joint Propulsion Specialist Conference. New Orleans, LA, US: AIAA, 1972: 72-1053.
[7] SU W X, WANG N F, LI J W. Improved method of measuring pressure coupled response for composite solid propellants[J]. Journal of Sound and Vibration, 2014, 333(8): 2226-2240.
[8] CULICK F E C. Interactions between the flow field combustion and wave motions in rocket motors: NWC TP 5349 [R]. China Lake, CA,US:Naval Weapons Center, 1972.
[9] MICHELI P L. Evaluation of pulsed t-burner for metallized propellants: No. 191 [R].Sacramento, CA，US: Aerojet Solid Propulsion Co., 1973.
[10] BROWN R S, ERICKSON J E, BABCOCK W R. Combustion response function measurements by the rotating valve method [J]. AIAA Journal, 1974, 12(11): 1502-1510.
[11] BROWN R S,WILLOUGHBY P G, KELLY V L. Rotating valve for velocity coupled combustion response studies [C] ∥ Proceedings of the 13rd Propulsion Conference. Orlando, FL, US: AIAA, 1977.
[12] BROWN R S,WAUGH R C, KELLY V L. Rotating valve for velocity-coupled combustion response measurements [J].Journal of Spacecraft and Rockets, 1982, 19(5): 437-444.
[13] 赵崇信，王宁飞. 固体推进剂压力耦合响应函数手册[M]. 北京:兵器工业出版社,1994.
ZHAO C X, WANG N F. Solid propellant pressure-coupled response function manual [M]. Beijing: Publication House of Ordnance Industry, 1994. (in Chinese)
[14] FRED S B. Lessons learned in solid rocket combustion instability[C]∥Proceedings of the 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Cincinnati, OH, US: AIAA, 2007.
［15］席运志，王宁飞，李军伟. 基于旋转阀的固体火箭发动机燃烧室压强振荡特性［J］.兵工学报, 2021, 42(1):33-44.
XI Y Z, WANG N F, LI J W. Oscillation characteristics of pressure in combustor with rotary valve for solid rocket engine［J］. Acta Armamentarii, 2021, 42(1):33-44. (in Chinese)
[16] 苏万兴. 大长径比固体火箭发动机不稳定燃烧预示及抑制方法研究[D].北京：北京理工大学, 2015.
SU W X. Prediction and suppression methods of combustion instability in large aspect ratio solid rocket motors [D]. Beijing：Beijing Institute of Technology, 2015. (in Chinese)
[17] KATHIRAVAN B, RAJAK R, SENTHILKUMAR C, et al. Oscillatory pressure effect on mean burning rates of solid propellant combustion at low frequency conditions [J]. Propellants, Explosives, Pyrotechnics, 2019, 44(3): 369-378.
[18] KUENTZMANN P, NADAUD L. Réponse des propergols solides aux oscillations de pression et de vitesse [J]. Combustion Science and Technology, 1975，11(3/4): 119-139.
[19] SEHGAL R, STRAND L. A theory of low-frequency combustion instability in solid rocket motors [J]. AIAA Journal, 1964, 2(4): 696-702.
[20] RENIE J P, OSBORN J R. Pressure and velocity coupled response of composite solid propellants based upon a small perturbation of analysis [C] ∥ Proceedings of the 17th Joint Propulsion Conference. Colorado Springs, CO, US: AIAA, 1981.
[21] HOU C W, QIAN J Y, CHEN F Q. Parametric analysis on throttling components of multi-stage high pressure reducing valve [J]. Applied Thermal Engineering, 2018, 128: 1238-1248.
[22] WHITE F M. Viscous fluid flow [M]. New York，NY，US: McGraw-Hill, 1974: 248-249.
[23] BREWSTER M Q, SAARLOOS B. Unsteady stolid propellant pressure combustion responses using a piston burner [J]. Journal of Propulsion and Power, 2004, 20(1): 127-134.
[24] WEBSTER S, HARDI J, OSCHWALD M. Characterisation of acoustic energy content in an experimental combustion chamber with and without external forcing [J]. CEAS Space Journal, 2015，7(1): 37-51.

[1]	席运志，王宁飞，李军伟，张智慧. 基于旋转阀的固体火箭发动机燃烧室压强振荡特性[J]. 兵工学报, 2021, 42(1): 33-44.
[2]	侯宇菲，许进升，周长省，陈雄，李宏文. 复合固体推进剂颗粒与基体初始界面有无缺陷的细观模型对比[J]. 兵工学报, 2020, 41(9): 1800-1808.
[3]	王鑫，赵汝岩，卢洪义，刘磊，伍鹏. 基于加速老化和实测载荷的立式贮存固体发动机药柱寿命评估[J]. 兵工学报, 2019, 40(11): 2212-2219.
[4]	叶振威，余永刚. 脉冲点火射流与高氯酸铵/端羟基聚丁二烯固体推进剂耦合燃烧的试验研究及数值模拟[J]. 兵工学报, 2018, 39(8): 1507-1514.
[5]	王维伦，李建民，杨荣杰，刘筑，李世鹏. 含氟有机添加剂对含铝聚醚推进剂燃烧凝聚相产物的影响[J]. 兵工学报, 2017, 38(4): 704-710.
[6]	李吉祯，樊学忠，张国防，蔚红建，唐秋凡，付小龙. 含能黏合剂3-硝酸酯甲基-3-甲基氧丁环聚合物的固化体系研究[J]. 兵工学报, 2016, 37(8): 1401-1408.
[7]	杨后文，余永刚，叶锐. 不同火焰环境下固体火箭发动机烤燃特性数值模拟[J]. 兵工学报, 2015, 36(9): 1640-1646.
[8]	邹权, 邓国栋, 郭效德, 姜炜, 李凤生. 近红外在线监测改性双基吸收药混合均匀度研究[J]. 兵工学报, 2014, 35(7): 977-981.
[9]	宋秀铎，郑伟，裴江峰，张军，王江宁，赵凤起. 黑索今含量对BAMO-AMMO基推进剂力学性能的影响[J]. 兵工学报, 2014, 35(6): 828-833.
[10]	王伟臣，李世鹏，张峤，王宁飞，王长健，许毅. 工作条件对固体发动机羽流温度场的影响[J]. 兵工学报, 2011, 32(12): 1493-1498.
[11]	封锋₁，陈军₁，宋洪昌₂，郑亚₁. 高氯酸铵/铝粉/端羟基聚丁二烯推进剂催化燃烧模型研究[J]. 兵工学报, 2010, 31(10): 1327-1332.
[12]	徐司雨，赵凤起，仪建华，高红旭，宋洪昌，李上文. 含CL-20的改性双基推进剂燃速数值模拟[J]. 兵工学报, 2009, 30(5): 535-540.
[13]	高红旭，赵凤起，李上文. 用均匀设计和回归分析法研究燃烧催化剤的作用规律[J]. 兵工学报, 2007, 28(2): 158-162.
[14]	李颖，宋武林，谢长生，王爱华，曾大文. 纳米铝粉在固体推进剂中的应用进展[J]. 兵工学报, 2005, 26(1): 121-125.
[15]	1:赵凤起，陈沛，李上文,王百成;2:杜恒,邓敏智. 四唑类化合物的金属盐作为徽烟推进剂燃烧催化剂的研究[J]. 兵工学报, 2004, 25(1): 30-33.