| 导弹/固体火箭发动机一体化设计 |
| |
| 引用本文： | 方国尧,郭志勇.导弹/固体火箭发动机一体化设计[J].推进技术,1989,10(5):35-40,74. |
| |
| 作者姓名： | 方国尧 郭志勇 |
| |
| 作者单位： | 北京航空航天大学
(方国尧)，北京航空航天大学(郭志勇) |
| |
| 摘 要： | 本文以两级推力固体火箭发动机为动力的某空-空导弹作为算例,研究了导弹/固体火箭发动机一体化设计的问题.为此,建立了固体火箭发动机的能量模型、质量模型和导弹与目标的数学模型.利用优化理论,成功地完成了九个设计变量的优化问题.优化结果表明,导弹的起飞质量减轻23.3kg(约占总重的9%).
|
| 关 键 词： | 导弹 固体火箭发动机 最佳设计 |
INTEGRAL OPTIMUM DESIGN OF MISSILES AND SOLID ROCKET MOTORS |
| |
| Fang Guoyao and Guo Ziyong.INTEGRAL OPTIMUM DESIGN OF MISSILES AND SOLID ROCKET MOTORS[J].Journal of Propulsion Technology,1989,10(5):35-40,74. |
| |
| Authors: | Fang Guoyao and Guo Ziyong |
| |
| Institution: | Beijing University of Aeronautics and Astronautics |
| |
| Abstract: | In this paper, according to the calculation example of air-to-air missile powered by a two-stage solid rocket motor, the integral optimum design of missiles with solid rocket motors is studied.Therefore,the energy model, the mass model of solid rocket motor and the mathematical model of missile and objection are established,and the optimization of nine design variables are conducted successfully based on the optimization theory. The gross weight of missile reduces by23.3kg. the optimization results show that the models established are correct. |
| |
| Keywords: | Missile Solid rocket engine Optimum design |
| 本文献已被 CNKI 维普 等数据库收录！ |
| 点击此处可从《推进技术》浏览原始摘要信息 |
| 点击此处可从《推进技术》下载免费的PDF全文 |
