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作为下一代战术导弹高性能危险性小的推进系统,(能够调节燃料流量的)可变流管道火箭很有发展前途。本文结合总体设计观点,对几种控制固体燃料发生器流出速率的方法进行了研究。调节喉部面积的方法,被认为是控制流出速率的最一般的方法。在一项有限的综合研究中,对几种可供选择的活门方案进行了比较。研究了调节喉部面积同推进剂燃速指数n,以及温度敏感度σp的相互关系,因为这两者都是重要的设计参数。为说明采用可变流管道火箭的导弹的性能潜力,提出了结论性的弹道结果。
As the propulsion system for the next generation of tactical missiles with high performance and low danger, the variable flow pipe rocket (which can regulate the fuel flow) has great prospects. Based on the overall design concept, several methods to control the outflow rate of solid fuel generator are studied in this paper. The method of adjusting the laryngeal area is considered as the most general method of controlling the rate of exudation. In a limited synthesis study, several alternative valve options were compared. The interrelationship between the area of the throat and the propellant burning rate index n and the temperature sensitivity σp was studied because both are important design parameters. In order to illustrate the potential performance of a missile using a variable-flow pipe rocket, a conclusive trajectory result was proposed.