Building on its ramjet experience , china is embracing the much more difficult task of developing mach 5 air vehicle concepts in which propulsion and aerodynamics are highly coupled 在其冲压发动机发展经验基础之上，中国着手于更为艰巨的5马赫高超音速概念飞行器的开发，推进技术和空气动力将高度耦合。
In recent years , the most of new fighters and strategic missiles require fly with supersonic or hypersonic speed , and this make a lot of researchers think much of this kinds of phenomena 近年来，新一代的战斗机及新型的战略导弹对超音速、高超音速飞行的要求，引起了国内外许多研究人员对这一类流动的重视。
Ramjet has been widely used in all kinds of supersonic and high - supersonic aircraft . it has caught more and more attention recently because there is no need for rotating impeller machine 而冲压发动机不需转动的叶轮机械,结构简单,高速性能优良,被广泛用于各类超音速和高超音速飞行器,愈来愈受到人们的关注。
The return of a reusable spacevehicle into earth ' s atmosphere with high - supersonic is gas - heated intensely , which requiring the high performance of thermal protection provided by the hot - structure composite materials 可重复使用空天飞行器以高超音速再入大气层时受到强烈的气动加热，对结构的防热性能提出了很高的要求。
Several non - linear phenomena are also analyzed . by using uncoupled thermal - structure analyzing method , with the consideration the additional stiffness caused by thermal stress , the finite element model for thermal - vibration analysis is obtained and two typical hypersonic wing structures are computed 运用非耦合热-结构分析方法，考虑热应力引起的附加刚度，得到热环境下的结构分析的有限元模型，并计算了两种典型结构的高超音速翼面热结构。
The method of wing shape optimization of space shutlle has been developed with penalty function approach in which the objective function is the mass of the wing and the constraints are the hypersonic re - entry flight cross range , lift / drag ratio , and subsonic flight lift / drag ratio , the margin of the longitudial static stability and the magnitude of the horizontal landing speed etc 摘要介绍了在满足高超音速再入横向机动航程，高超音速再入飞行时的升阻比，亚音速进场飞行时的升阻比，纵向静稳定性裕度和水平着陆速度等飞行性能设计要求下，用罚函数法寻求使航天飞机机翼质量为最小的外形优化方法并给出了算例。
Using the engineering methods of supersonic and hypersonic flow or local piston theory developed in this paper to compute unsteady aerodynamic loads , and coupling structural equations , the supersonic or hypersonic aeroelasticity with a typical servo system under thermal environment is simulated in time - domain 运用超音速、高超音速气动力工程计算方法和本文发展的当地流活塞理论计算非定常气动力，耦合结构运动方程，实现了热环境中带有伺服机构的气动弹性的时域仿真。
A numerical simulation software is developed that can be used to simulate standing oblique detonation waves in hypervelocity flight conditions . reasonable parameters and advanced method are provided for the application of standing detonation propulsion technology . the main points are as follows : the mathematical model is developed that can be used to analyze the properties of planar standing oblique detonation waves 通过对驻定斜爆轰波形念的理论分析和数值模拟，对高超音速条件下斜爆轰波的稳定性现象进行了系统研究，探讨了产生驻定斜爆轰波的临界条件，开发了平面和锥形驻定斜爆轰波流场数值模拟软件，为驻定爆轰推进技术的应用提供合理的系统参数和先进手段。
