尾喷管

Hypersonic vehicle ; afterbody/nozzle ; integrated design ; genetic algorithms

高超声速飞行器；后体/尾喷管；一体化设计；遗传算法

The design and optimization of the nozzle is researched by use of the method of characteristic line and particle swarm optimization method.

应用简易特征线方法和粒子群优化算法对尾喷管的优化设计进行了研究。

It can calculate the distribution of temperature and pressure if the temperature and pressure of tail pipe are known. The model is basically consistent with the simulation which is used by hydromechanics.

该模型可在已知尾喷管压力、温度的条件下计算尾焰的温度场和压力场分布，与计算流体力学在相应条件下模拟的尾焰流场特性基本一致。

The problem of analyzing scattering from cavity with a complex termination, such as jet inlet and exit of airplane, is one of the most important and challenging topics in the research area of aircraft stealth design.

以进气道、尾喷管等为代表的复杂终端腔体的电磁散射分析是当前飞行器隐身设计领域的一个热点和难点。

When the burnt gases run over the exhaust nozzle with limited length, the dissociation energy can not be released fully.

这些解离能在长度受限的尾喷管中难以充分复合形成推力，使冲压发动机性能随飞行马赫数增大而急剧下降。

Physical and numerical models were establishedased on NˉS c ontrol equations and RNG kˉεturbulence model, the interior flow fields of the nozzles were analyzed through num erical method, both the flow parameters change trend and thrust speciality of the asymmetry quadrate nozzle were resea rched.

文中建立了非对称方形尾喷管及传统轴对称尾喷管的物理数学模型，基于N S方程和RNG kε湍流模型，对两种尾喷管三维内流场进行了数值分析，研究了非对称方形尾喷管内部流动参数的变化趋势及其推力特性。

In this paper ,move ment pri nci ple of rocket i n direction pi pe was got by dy— namic si mulation ,and effect characteristic consideri ng contact stiffness ,detent force and nozzle thrust misalignment a— bout pitchi ng angle velocity was analysis .All the study set foundationfor further study of high—lowpressure launch sys— te m.

通 过发射仿真分析，获得了火箭弹在高低压发射系统中的内弹道变化规律，分析了火箭弹与定向器的接触刚度、耳轴扭转刚度、尾喷管推力偏心等因素对俯仰角速度的影响特性，所得结论为火箭武器高低压发射系统的进一步相关研究奠定了基础。

Compared with the conventional take-off and landing F-35A already flying, the F-35B has a shaft-driven lift fan mounted behind the cockpit, roll ducts installed in the wing and swivelling nozzle fitted to the engine.

与已经试飞的常规起降型F-35不同的是，F-35B在紧靠驾驶舱后面装有轴驱动升力风扇，发动机装有可偏转尾喷管，每侧翼根处各有一个发动机引气反作用阀。

3D two-phase internal flow field of SRM with long-tail nozzle was simulated by means of Eulerian-Lagrangian two-phase method.

采用欧拉-拉格朗日两相方法模拟了带长尾喷管的固体火箭发动机三维两相内流场。

Although a dual-mode scramjets configuration is simple and mainly consists of inlet, combustor and wake nozzle, its working process is complicated, especially in the combustor, involving a lot of subjects, including hypersonic aerodynamics, combustion chemistry, etc.

虽然双模态冲压发动机结构简单，主要由进气道、燃烧室和尾喷管三部分组成，但其工作过程却十分复杂，尤以超音速燃烧室的工作规律最为复杂，设计难度最大。

Breath, muscle contraction of the buttocks; arch body, as far as possible to hold his head, right leg straight towards the ceiling (peg-leg knee in order to avoid muscle tension).

呼气，收缩臀部肌肉；拱起身体，尽量抬起头来，右腿伸直朝向天花板（膝微屈，以避免肌肉紧张）。

The cost of moving grain food products was unchanged from May, but year over year are up 8%.

粮食产品的运输费用与5月份相比没有变化，但却比去年同期高8％。