过载下丁羟推进剂压强耦合响应试验研究
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摘要
主要研究在轴向过载下丁羟推进剂的压强耦合响应,基于双脉冲外部激励的方法,建立了T型燃烧器旋转过载试验系统,开展了丁羟推进剂在0g、5g、15g轴向载荷下的压强耦合响应试验研究,获得了丁羟推进剂在T型燃烧室中的燃面增益常数。试验结果表明,轴向过载值越大,T型燃烧器平均工作压强越低,包覆套筒里凝相残渣质量越多,分析认为过载下铝粉在药面过度聚集使得铝粉未充分燃烧,导致丁羟推进剂能量没有充分释放;随着轴向加速度的增加,T型燃烧器燃面增益常数和凝相粒子浓度减小,从而造成阻尼效果明显减弱。
This paper mainly studies the pressure coupled response of HTPB propellant under axial overloading. Based on the double-pulse external exciting method,the T-burner centrifuge rotating test system was established. The pressure coupled response of the HTPB propellant under static,5 g longitudinal and 15 g longitudinal have been carried out to obtain the burn surface grow constants.The results show that the higher the longitudinal overloading is,the lower average operation pressure is obtained and the residues in the adiabatic sleeve is higher.The analysis indicates that aluminum power conglomerate excessively on grain surfaces,which makes the aluminum power not burn sufficiently,and hence the energy of HTPB propellant is not fully released.The higher the longitudinal acceleration results in a lower burn surface grow constant of T-burner and less condensed particles concentration. Then the damping effects is obviously weakened in this case.
This paper mainly studies the pressure coupled response of HTPB propellant under axial overloading. Based on the double-pulse external exciting method,the T-burner centrifuge rotating test system was established. The pressure coupled response of the HTPB propellant under static,5 g longitudinal and 15 g longitudinal have been carried out to obtain the burn surface grow constants.The results show that the higher the longitudinal overloading is,the lower average operation pressure is obtained and the residues in the adiabatic sleeve is higher.The analysis indicates that aluminum power conglomerate excessively on grain surfaces,which makes the aluminum power not burn sufficiently,and hence the energy of HTPB propellant is not fully released.The higher the longitudinal acceleration results in a lower burn surface grow constant of T-burner and less condensed particles concentration. Then the damping effects is obviously weakened in this case.
引文
[1] Coates R L.Application of T-burner to ballistic evaluation of new propellants[J]. Journal of Spacecraft And Rockets,1966,3(12):1793-1796.
[2] Horton M D,Coates R L. T-burners:Experiments compared with theory[J]. Journal of Spacecraft and Rockets,1974,11(1):48-51.
[3] Mihlfeith C M,Sayer L H.Novel high area ratio T-burner for characterizing metalized propellants[J].Journal of Spacecraft and Rockets,1974,11(8):574-578.
[4] Beck W H,Jolleyt W H.Harmonic analysis of piston and pyrotechnic pulsers for T-burners[J].Journal of Spacecraft and Rockets,1988,4(3):283-285.
[5] Jerry C Finlinson,Richard A Stalnaker,Fred S Blomshield.MHD T-burner combustion response test improvements[R].AIAA 99-2363.
[6] Jerry C Finlinson,Richard Stalnaker,Fred S Blomshield.Ultra pure ammonium perchlorate T-burner pressure coupled response at 500,1000 and 1800 psi[C]//34th AIAA Joint Propulsion Conference,July,1998.
[7] Jerry C Finlinson,Richard Stalnaker,Fred S Blomshield.HMX and RDX T-burner pressure coupled response from200 to 1000 psi[C]//36th AIAA Aerospace Sciences Mtg,Jan,1998.
[8]刘佩进,齐宗满,金秉宁,等.两种含铝复合推进剂压强耦合响应的实验对比[J].固体火箭技术,2013,36(1):83-88.LIU Peijin,QI Zongman,JIN Bingning,et al. Experiment comparison of pressure coupled response of the aluminized composite propellants[J]. Journal of Solid Rocket Technology,2013,36(1):83-88.
[2] Horton M D,Coates R L. T-burners:Experiments compared with theory[J]. Journal of Spacecraft and Rockets,1974,11(1):48-51.
[3] Mihlfeith C M,Sayer L H.Novel high area ratio T-burner for characterizing metalized propellants[J].Journal of Spacecraft and Rockets,1974,11(8):574-578.
[4] Beck W H,Jolleyt W H.Harmonic analysis of piston and pyrotechnic pulsers for T-burners[J].Journal of Spacecraft and Rockets,1988,4(3):283-285.
[5] Jerry C Finlinson,Richard A Stalnaker,Fred S Blomshield.MHD T-burner combustion response test improvements[R].AIAA 99-2363.
[6] Jerry C Finlinson,Richard Stalnaker,Fred S Blomshield.Ultra pure ammonium perchlorate T-burner pressure coupled response at 500,1000 and 1800 psi[C]//34th AIAA Joint Propulsion Conference,July,1998.
[7] Jerry C Finlinson,Richard Stalnaker,Fred S Blomshield.HMX and RDX T-burner pressure coupled response from200 to 1000 psi[C]//36th AIAA Aerospace Sciences Mtg,Jan,1998.
[8]刘佩进,齐宗满,金秉宁,等.两种含铝复合推进剂压强耦合响应的实验对比[J].固体火箭技术,2013,36(1):83-88.LIU Peijin,QI Zongman,JIN Bingning,et al. Experiment comparison of pressure coupled response of the aluminized composite propellants[J]. Journal of Solid Rocket Technology,2013,36(1):83-88.