这些特点使得高超声速飞行器的飞行控制设计极具挑战性。
All these features make hypersonic flight control design a great challenge to researchers.
高超声速飞行器设计上的特点带来了一系列的气动弹性新问题。
There are many new problems of aeroelasticity which are introduced by the novel concepts and system characteristics in the design process of hypersonic vehicles.
这对于高超声速飞行器中液固耦合问题的研究具有一定的实际意义。
The research of hypersonic vehicle for liquid-solid coupling problems has some practical significance.
对一个高超声速飞行器设计了滑动模态观测器来估计攻角和航迹倾角。
A sliding mode observer is designed to estimate the Angle of attack and flight path Angle for a hypersonic vehicle.
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.
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.
对高超声速飞行器不同的设计阶段，可有所侧重的选择不同的计算方法。
Different design phases of the hypersonic vehicle can be focused to choose a different calculation methods.
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.
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.
高超声速飞行器有着广阔的应用背景，可以帮助人们实现经济、高效的太空开发和利用。
Hypersonic vehicle has a broad applied prospects, it could help to achieve economic and efficient development of space.
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.
高超声速飞行器的设计工具，即地面试验、计算和飞行试验，在模拟高超声速飞行方面都有其局限性。
The developing tools for hypersonic vehicle, i. e. ground test, computation and flight lest all have limitations for simulating hypersonic flight.
采用后向面判别法和深度缓冲器算法分析面元之间的遮挡关系，计算了整个高超声速飞行器的RCS。
To compute RCS of whole HCV, the shadowing relationship of facet analyzed by the method of backward surface identification and depth-buffer is considered.
针对存在强烈不确定和干扰的近空间高超声速飞行器(NHV)，提出了一种新的非线性自适应控制方法。
A novel nonlinear adaptive control method is presented for a near-space hypersonic vehicle (NHV) in the presence of strong uncertainties and disturbances.
针对高超声速飞行器飞行过程中因干扰造成的飞行轨迹散布问题，提出了采用飞行器飞行轨迹的模糊控制设计方法。
A new method of design hypersonic vehicle trajectory tracking system using fuzzy control is presented to overcome the disadvantage of flight trajectory distribution caused by separation disturbance.
提出了一种基于自适应观测器的故障诊断与容错控制策略，应用到近空间高超声速飞行器(NSHV)上处理执行器故障。
A fault diagnosis and fault-tolerant control scheme using adaptive observer is generalized to near space hypersonic vehicle (NSHV) to deal with actuator fault.
多次数值打靶仿真表明，提出的预测制导方法对高超声速飞行器末端制导初始条件误差以及导航误差影响具有较强的鲁棒性。
Numerical simulation of multiple target practice shows that the presented predictive guidance method for hypersonic craft strong robustness on initial conditions and navigation errors.
“升力推力”飞行器是根据新世纪对高超声速飞行器的需求提出的一种新型飞行器概念，它可以使飞行器的升阻比得以有效提高。
This paper made some analysis on techniques of the concept and power for the "lift-thrust" aircraft, and looked into its future development.
RBCC发动机性能分析模型在高超声速飞行器方案选择、总体设计以及RBCC发动机设计与性能分析等方面具有极其重要的作用。
RBCC engine performance analysis model plays an important part in scheme selection and model design for Hypersonic Flight Vehicle, RBCC engine design and performance analysis.
对一种轴对称形式的高超声速飞行器全流道开展了风洞实验和数值模拟研究，分析了不同来流总压、飞行攻角全流道的流场结构和气动力特性。
This paper presents a numerical simulation of separated flow over an airfoil at large attack angles with oscillating excitations to study separation flow control over an airfoil.
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.
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.
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.
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.
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.
研究了空天飞行器超声速和高超声速飞行条件下六自由度仿真模型，该模型包含了完整的六自由度动力学方程和运动方程。
Six Degrees of Freedom model and simulation of an aerospace vehicle is presented, which includes the whole of kinetic equations and motion equations.
研究了空天飞行器超声速和高超声速飞行条件下六自由度仿真模型，该模型包含了完整的六自由度动力学方程和运动方程。
Six Degrees of Freedom model and simulation of an aerospace vehicle is presented, which includes the whole of kinetic equations and motion equations.
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