In order to determination the thrust , the thrust definition and many control parameters are analyzed discussed , which mass flow rate and flight altitude are involved . it is difficult to measure the flight thrust of solid rocket ramjet directly 通过讨论高空飞行推力与地面可测试参数的关系，得到了固体火箭冲压发动机高空飞行状态下推力折算方法，并开发相应的计算程序。
The research project of the middle - long and hypersonic missile with solid rocket - ramjet engine has been launched . the measurement and control technologies are the important basis of developing engine , which is one of the key technologies of the research 我国发展中远程、高超声速固体冲压导弹已经启动，其关键技术之一是研制性能优良的固体火箭冲压发动机，而试验测控技术是发动机研制中不可或缺的重要基础。
The solid rocket ramjet , which combines the techniques of ramjet propulsion and solid rocket propulsion , offers the following advantages for missile propulsion : high specific impulse , simple configuration , high credibility , convenient using and high maneuverability 固体火箭冲压发动机结合了冲压技术和固体火箭技术,具有比冲高、结构紧凑、工作可靠、使用方便、机动性好等优点,是新一代超声速战术导弹的优选动力装置。
According to the definition and expression of the thrust , as well as the condition derived from them , a method of solid rocket ramjet thrust determination and its program are provided on the basis of engine ground simulation test 本文以西北工业大学固体火箭冲压发动机直连式试车台为研究对象，探讨固体火箭冲压发动机地面试验技术。首先，从推力的定义出发，建立了试验中来流空气流量、燃料流量与固体火箭冲压发动机推力之关系。
This thesis is aimed at providing the complete details of the combustion processes and flowfields in the second combustor , and seeking ways to improve the combustion efficiency in order to provide theoretical basis and direction for the design of second combustor 本文研究的主要目的就是了解固体火箭冲压发动机补燃室内的掺混燃烧过程，探索提高补燃效率的方法和途径，从而为固体火箭冲压发动机补燃室的设计提供理论依据和指导。
It is determined now by calculation with mathematical relationship of the flight thrust to the physical quantities which can be measured directly . the optimization of the software development platform is also analyzed inspect of the solid rocket - ramjet developmental program 其次，为满足固体火箭冲压发动机试验技术进一步研究需要，在深入分析labview图形化编程软件优化方法的基础上，改进了现有的固体火箭冲压发动机试验测控程序，并应用于发动机试验中。
Design of two propulsion systems is studied - solid rocket ramjet and liquid ramjet . the performance analysis models and design methods are set up for these two kinds of engines . the different characteristics are analyzed and compared , which provide basis for farther trajectory computation and conceptual optimization design ( 4 )研究了两种动力装置? ?固体火箭冲压发动机和液体燃料冲压发动机的设计问题，建立了两种发动机的性能分析模型和计算方法，对固体火箭冲压发动机和液体燃料冲压发动机的特性进行计算分析及比较，为弹道计算及总体优化设计提供依据。
This thesis is aimed at the pilot study about the integrated flow field of inlet and combustor , which is based on the optimized design and the performance analysis of supersonic inlet , in order to provide theoretical basis and direction for extension of flight enveloping and improvement of the synthetic performance of ramjet 本文的主要目的即是对超声速进气道进行优化设计和性能分析,并以此为基础开展超声速进气道/补燃室流场一体化的初步研究,为拓宽固体火箭冲压发动机的工作范围、提高其综合性能提供理论依据和指导。
The evolution course of chinese solid rocket propulsion technology for space missions since 1950s is presented . the technical features , development process , ground tests and flight records of nine typical solid motors are described . these motors were developed for sounding rockets , upper stages of launch vehicles and orbit transfer systems in application satellites respectively . the evolution of basic technology of chinese solid rocket motors and future developing concept are briefly introduced . the information in the paper are all based on the published literatures 叙述了20世纪50年代以来中国航天固体火箭推进技术的发展历程,介绍了9种最具代表性的固体火箭发动机的技术特征、研制过程、地面试验和飞行情况,这些发动机分别应用于中国的探空火箭、运载火箭上面级和应用卫星变轨系统.文中还简要地评述了中国固体推进各单项技术的发展水平
With computations and analysis , the comprehension on the mixing and combustion process is increased , and some significative results are listed below : a ) there are three recirculation regions and one vortex region in the combustor , and these recirculation regions affect the combustion process deeply , b ) increasing side - arm angle and moving side - air inlet position toward the fuel inlet can improve mixing and combustion characteristics , and increase the combustion efficiency , c ) when the angle between two air - inlets equals to 180 通过计算与分析，增进了对补燃室内掺混燃烧过程的理解，为固体火箭冲压发动机补燃室设计提供了一些有意义的结果： 1补燃室内的流动十分复杂，存在三个回流区和一个旋涡区，回流区对掺混燃烧过程有重要影响； 2增大空气入射角度、向前移动进气道出口位置有利于增强头部回流区强度，增强掺混效果，燃烧效率上升； 3
