Analysis of nonlinear pressure coupled response function of solid propellant

被引：0
作者：
Liu P.-J. [1 ]
Jin B.-N. [1 ]
Wei X.-G. [1 ]
Yang W.-J. [1 ]
Liu X. [1 ]
Ji X.-T. [1 ]
机构：
[1] Science and Technology on Combustion, Internal Flow and Thermal-Structure Laboratory, Northwestern Polytechnical University, Xi'an
来源：
| 1601年 / Journal of Propulsion Technology卷 / 37期
关键词：
Combustion model; Nonlinear; Pressure-coupled response function; Solid propellant;
D O I：
10.13675/j.cnki.tjjs.2016.09.001
中图分类号：
学科分类号：
摘要：
In order to obtain the characteristics of the pressure-coupled response function which was influenced by the multi-order modes acoustic frequency oscillation, the nonlinear combustion instability characteristics of the multi-order mode oscillation in the solid rocket motor were considered, and based on the Quasi-Steady, Homogenous, One-Dimensional (QSHOD) model, the second-order (2nd) mode acoustic of the nonlinear pressure-coupled response model was developed. The model was analyzed and verified by experiments. The results of model show that, the oscillation amplitude of the first-order (1st) mode frequency has a great influence on the pressure-coupled response function, and with the amplitude increase, the pressure coupled response function was changed from the linear to the nonlinear, the peak value of response function changed from single-modal to bi-modal, and the nonlinear response function peak value was formed in the high frequency region. During the 1st mode frequency oscillation, the 2nd mode frequency makes the response function more nonlinear significantly, and has a great influence on the peak value of nonlinear pressure coupled response function. The results of the model were basically the same as the experimental results of typical T-burner. © 2016, Editorial Department of Journal of Propulsion Technology. All right reserved.
引用
收藏
页码：1601 / 1608
页数：7
相关论文
共 14 条
  • [1] Xie W.-M., He W.-S., Prediction of Combustion Instability in Solid Rocket Engine, Journal of Propulsion Technology, 12, 2, pp. 40-45, (1991)
  • [2] Xu W.-G., Li Y.-S., An Engineering Method and its Necessity in Study on Combustion Instability of Solid Rocket Motor, Journal of Propulsion Technology, 15, 2, pp. 7-11, (1994)
  • [3] Blomshield Fred S., Lessons Learned in Solid Rocket Combustion Instability
  • [4] Culick F.E.C., Internal Aerodynamics in Solid Rocket Propulsion, (2006)
  • [5] Shusser M., Culick F.E.C., Analytical Solution of Pressure-Coupled Combustion Response Functions of Composite Solid Propellant, Journal of Propulsion and Power, 24, 5, pp. 1058-1067, (2008)
  • [6] Shusser M., Culick F.E.C., Cohen N.S., Combustion Response of Ammonium Perchlorate
  • [7] Culick F.E.C., A Review of Calculations for Unsteady Burning of a Solid Propellant, AIAA Journal, 6, 12, pp. 2241-2255, (1968)
  • [8] Beckstead M.W., Derr R.L., Price C.F., A Model of Composite Solid-Propellant Combustion Based on Multiple Flames, AIAA Journal, 8, 12, pp. 2200-2207, (1970)
  • [9] Cohen N.S., Strand L.D., An Improved Model for the Combustion of AP Composite Propellants, AIAA Journal, 20, 12, pp. 1739-1746, (1982)
  • [10] Cohen N.S., Strand L.D., Combustion Response to Compositional Fluctuations
12