本论文进行了高超声速弹丸的气动热研究。
In this thesis, the aerodynamic heating methods of hypersonic projectile are presented.
轨迹优化是高超声速滑翔式飞行器关键技术之一。
Trajectory optimization is a key technology of hypersonic glide vehicle.
高超声速气流条件下，尖楔前缘的热环境非常恶劣。
The thermal environment of the wedge leading edge is rigorous in hypersonic flow.
本文描述绕锐前缘平板高超声速流动的数值模拟结果。
The results of numerical simulation of the hypersonic flow around a plate with a sharp leading edge are presented.
建立了基于参数方法的高超声速巡航飞行器MDO模型。
A hypersonic cruise vehicle MDO model based on parametric method is established.
轨迹优化是新型高超声速滑翔式再入飞行器方案设计的关键技术之一。
Trajectory optimization is one of the key factors in scheme planning of the new type of hypersonic gliding reentry vehicles.
本文给出钝头细长锥无粘、平衡和非平衡高超声速绕流流场的数值分析。
This paper presents a numerical analysis of inviscid equilibrium and nonequilibrium hypersonic flow past blunt-nosed slender cones.
阐述了在进行高超声速飞行器外形设计中，应用试验设计方法的必要性。
The essential of using experimental design method to configuration design of hypersonic aircraft are expounded.
最后，初步分析了高超声速弹翼表面发生烧蚀后对其外弹道特性的影响。
At last, the effect on the outer ballistic trajectory characteristic after the ablation of hypersonic projectile wing has been analyzed.
针对不同飞行任务的高超声速飞行器，分别提出了综合热管理系统方案；
Concept of integrated thermal management system was put forward respectively, based on the characteristics of hypersonic vehicles with different missions.
高超声速化学非平衡尾流的分析与计算是空气动力学中的一个重要课题。
The analysis and computation of chemical nonequilibrium hypersonic wakes are important tasks of aerodynamics.
本文给出了高超声速飞行器表面摩阻和传热系数(斯坦顿数)的计算结果。
In this paper the results of calculations of the coefficients of skin friction and heat transfer (Stanton number) on the surface of hypersonic flight vehicle are presented.
亚声速气动力采用面源法计算，高超声速气动力采用修正的牛顿流理论计算。
Panel Method was used for subsonic aerodynamic analysis, and the Modified Newtonian Impact Theory was used for hypersonic aerodynamic analysis.
吸气式高超声速飞行器是下一代单级入轨和高超声速巡航研究的重点飞行器。
Air-breathing hypersonic vehicle(AHV) has been the next generation single stage to orbit vehicle and hypersonic cruise vehicle.
通过响应面近似模型的优化，完成了高超声速巡航飞行器的多学科设计优化。
The response surface approximation models are used to replace the original complex vehicle performance model, the optimization is conducted using a sequential quadratic programming algorithm.
针对高超声速再入飞行器最远距离滑翔制导关键技术，设计了一种新型制导律。
A novel guidance law is devised for developing the guidance technology of optimal glide of a hypersonic reentry vehicle.
高温非平衡化学反应对高超声速再入飞行器绕流流场的气动热特性有较大影响。
High temperature chemical non equilibrium phenomena have a great effect on the flow field around a reentry vehicle.
本文讨论了高超声速粘性激波层方程数值计算时差分格式引起的物理失真问题。
The problems of physical distortion due to the finite-difference scheme are studied in numerical solutions of the hypersonic viscous shock-layer equations.
本文介绍了高超声速风洞引射器阀门系统采用计算机控制的设计思想和原理框图。
The design concept and principle of injector valve system of hypersonic wind tunnel controlled by the computer are introduced in this paper.
通过地面试验和高超声速非平衡流的研究，取得了再入突防气动物理的重要进展。
Through ground test and hypersonic flow research, he made great progress in air-breathing hypersonic technology.
本文提出了一个高超声速非烧蚀钝体尾流全流场的简化模型和简化的空气化学模型。
A simplified flow field model and simple air chemical model for the chemical nonequilibrium wakes of hypersonic non-ablating blunt-body are presented.
而高超声速风洞喷管的设计和计算则对解决这一类问题具有重要的科学意义和实用价值。
The design and computation of the hypersonic nozzle have scientific and practical value to solve these problems.
超燃冲压发动机是高超声速飞行器理想的动力装置，是当前高超声速技术领域的研究热点。
Scramjet is the perfect propulsive device to hypersonic vehicle, and is a hot issue in current hypersonic technology area.
笔者自行设计研制了用于高超声速推进风洞流场测量的带有水冷装置的可移动式扫描总压耙。
A kind of scan pitot-pressure rake with water cooler was designed in IMCAS for the hypersonic propulsion wind tunnel flow measurement.
高超声速进气道是高超声速吸气式推进系统的重要组成部分，对实现高超声速飞行起着关键作用。
Scramjet inlet is of great importance in the hypersonic airbreathing propulsion system and plays significant role in the realization of hypersonic flight.
在超声速或高超声速绕流中，一种很严重的脉动压力环境是由激波边界层相互作用引起的激波振荡。
One of the more severe fluctuating pressure environments encountered in supersonic or hypersonic flows is the shock wave oscillation driven by interaction of a shock wave with boundary layer.
通过理论分析、实验测量和数值模拟，研究高超声速粘性相互作用对实验段自由流静压测量的影响。
Hypersonic viscous interaction effects on measurement of free stream pressure in test section are studied through theoretical analysis, experiment measurement and numerical simulation.
分布参数控制体系的新原理、方法、实现手段将对高超声速发动机系统的运行和设计产生重要影响。
The new principles and methods of distributed parameter control may have an impact on the operation and design of hypersonic jets.
分布参数控制体系的新原理、方法、实现手段将对高超声速发动机系统的运行和设计产生重要影响。
The new principles and methods of distributed parameter control may have an impact on the operation and design of hypersonic jets.
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