| 多级固体火箭发动机总体优化设计 |
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| 引用本文： | 张鸿涛.多级固体火箭发动机总体优化设计[J].推进技术,1989,10(2):8-14,70. |
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| 作者姓名： | 张鸿涛 |
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| 作者单位： | 航空航天部四院41所 |
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| 摘 要： | 本文在文献1]的基础上提出了一种多级固体火箭发动机总体优化数学模型,并对三级定容发动机进行了计算.对中远程弹道式导弹利用优化模型比经验设计主动段终点速度提高了4%.
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| 关 键 词： | 固体推进剂 火箭发动机 最佳设计 |
INTEGRAL PERFORMANCE OPTIMUM DESIGN FOR MULTISTAGE SOLID PROPELLANT ROCKET MOTORS |
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| Zhang Hongtao.INTEGRAL PERFORMANCE OPTIMUM DESIGN FOR MULTISTAGE SOLID PROPELLANT ROCKET MOTORS[J].Journal of Propulsion Technology,1989,10(2):8-14,70. |
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| Authors: | Zhang Hongtao |
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| Institution: | Shaanxi Power Machinery Institute |
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| Abstract: | A mathematical model for integral performance optimization of multistage solid propellant rocket motors is established, based on referance1],and a calculation with a three-stage volume-fixed solid propellant rocket motor,as a example, is presented in this paper.It is shown that the velocity at burnout ef intermediate/long range ballistic missile calculated with this model is 4% greater than that with usual empirical method. |
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| Keywords: | Solid rocket engine Optimization Optimum design Parameter optimization |
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