| 微型固体火箭发动机点火增压过程瞬态燃速辨识 |
| |
| 引用本文： | 樊超,李晓斌,张为华,王中伟.微型固体火箭发动机点火增压过程瞬态燃速辨识[J].固体火箭技术,2007,30(6):498-501. |
| |
| 作者姓名： | 樊超 李晓斌 张为华 王中伟 |
| |
| 作者单位： | 国防科技大学,航天与材料工程学院,长沙,410073 |
| |
| 摘 要： | 建立了微型固体火箭发动机点火增压过程一维非定常仿真模型;基于发动机点火增压物理过程,采用拉丁超立方设计方法进行了仿真试验设计,得到了传热模型参数和不同压强范围瞬态燃速模型参数的最优估计。计算和试验结果的对比表明,辨识所得模型参数合理,修正后的dp/dt燃速模型适用于微型固体火箭发动机升压速率较高的情况。
|
| 关 键 词： | 固体火箭发动机 增压过程 瞬态燃速 参数辨识 拉丁超立方设计 |
| 文章编号： | 1006-2793（2007）06-0498-04 |
| 收稿时间： | 2006-10-11 |
| 修稿时间： | 2006年10月11 |
Identification of transient burning rate during ignition pressurization of micro-solid rocket motor |
| |
| FAN Chao,LI Xiao-bin,ZHANG Wei-hua,WANG Zhong-wei.Identification of transient burning rate during ignition pressurization of micro-solid rocket motor[J].Journal of Solid Rocket Technology,2007,30(6):498-501. |
| |
| Authors: | FAN Chao LI Xiao-bin ZHANG Wei-hua WANG Zhong-wei |
| |
| Abstract: | One-dimensional unsteady simulation model during ignition pressurization of micro-SRM was derived.Based on physical process of motor ignition pressurization,simulation test was designed by means of Lartin hypercube design.The optimum estimations on heat-transfer model parameters and transient burning rate model parameters within different pressure range were obtained.The comparison between calculation results and experimental results shows that identified model parameters are reasonable,and the modified dp/dt burning rate model is suitable for higher pressurization rate of micro-SRM. |
| |
| Keywords: | solid rocket motor pressurization process transient burning rate parameter identification Lartin hypercubes design |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ |
