【摘要】 总结了自1965年以来固体火箭冲压发动机研制技术的总体发展特征和趋势,结合当前新一代战术导弹提出的大空域、宽Ma数和大机动性等越来越高的设计需求,从冲压发动机热力循环技术本质要求出发,分析了当前工程上普遍采用的固定几何进气道、固定几何喷管、燃烧室共用、无喷管助推器和变流量燃气发生器等5项主体设计技术固有的技术缺陷、不足和局限性,明确指出现行的折中设计思想是产生问题的根源,提出未来应遵循"开源节流"设计思想,优先突破喷管调节技术,积极开发进气道调节技术,努力提高现有燃气发生器变流量调节技术水平,切实完善固体火箭冲压发动机热力循环,以促其成功应用。更多还原

【Abstract】 The design characteristics and trends of ducted rockets since 1965 are summarized.Aiming at demanding design requirements posed by new generation tactical missiles,namely,long range,wide Mach number range,and high maneuverability,etc.,the inherent limitations and disadvantages of five commonly used major design techniques,i.e.the design of fixed-geometry inlet,fixed-geometry nozzle,common combustion chamber,nozzleless booster,and variable flow gas generator,are analyzed from the viewpoint of essential requirements of ramjet thermodynamic cycle.The paper clearly points out that the compromise philosophy is the source of these problems and suggests that the optimum control idea,i.e.,making breakthrough in nozzle regulation technique first,actively developing inlet regulation technique,and improving gas generator flow control technique should be followed to perfect ramjet thermodynamic cycle and facilitate the application successfully.更多还原