Effects of flow separation on the performance of thrust-vectoring nozzle

1、

The unsteady flow as thrust vectoring nozzle deflecting dynamically is investigated. The method of calculating the unsteady flow in the nozzle is given and the flow of the nozzle in the maximum power setting and maximum A/ B power setting of the engine is calculated.

研究了矢量喷管动态偏转过程中气流的非定常流动和矢量喷管非定常流动计算方法，计算了矢量喷管在发动机某中间状态和加力状态下的非定常流场。

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2、

The affecting factors of the performance parameters of the thrust vectoring nozzle are investigated. And the affect of nozzle pressure ratio, nozzle area ratio and geometric defected angle on the performance parameters is also investigated.

研究了影响矢量喷管性能的因素，研究了压比、面积比以及几何偏角对矢量喷管性能的影响。

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3、

Lastly, the results of unsteady flow point out, counterflow thrust vectoring nozzle is a efficiency fluidic vectoring nozzle.

最后，非定常流的结果进一步表明，逆流喷管是一种较高效率的射流式矢量喷管。

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4、

As thrust vectoring nozzle is the feature of advanced fighters, the difficulties in implementing thrust vectoring are summarized.

矢量喷管是先进战斗机的特征，本文讨论了实现推力矢量存在的技术难点。

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5、

Based on these two real time models, the real time mathematical model of the turbofan engine with thrust vectoring nozzle was acquired.

在以上两个模型的基础上建立了带轴对称矢量喷管的涡扇发动机数学模型。

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6、

Based on this method the transient mathematical model of the thrust vectoring nozzle which has three free variables is established.

以此为基础，建立了轴对称矢量喷管的三自由参数动态数学模型。

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7、

Effect of geometric parameters on performance of counterflow thrust vectoring nozzle

几何参数对逆流矢量喷管性能的影响研究

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8、

Research of Turbofan Engine Transient Process with Thrust Vectoring Nozzle

带矢量喷管的涡扇发动机动态过程研究

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9、

Computation of three-dimensional flow field in secondary gas injection for thrust vectoring nozzle

气体二次喷射矢量喷管三维流场计算

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10、

A Study on the Two-Dimensional Thrust Vectoring Nozzle with Secondary Flow Injection

基于次流喷射控制推力矢量喷管的实验及数值研究

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11、

A random process model of structural functional function of components attached to vectoring thrust nozzle was employed, in which strength and stress of components were respectively taken as random variable and stochastic process.

本文将矢量喷管构件的强度考虑为随机变量，将构件的应力考虑为随机过程，建立了构件结构功能函数的随机过程模型。

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12、

A methodology based upon the H ∞ principle of weighting sensitivity function loop-shaping is given to design the robust controller of flight control system for vector thrust nozzle.

采用加权灵敏度函数环路成形的H∞准则，给出了矢量推力喷管飞行控制系统的一种鲁棒控制器设计方法。

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13、

In this paper, employing rigorous variational calculus, equations of control surface at maximum thrust nozzle exit are derived.

本文用严格的变分法导出了最大推力喷管出口控制面方程。

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14、

Principle of Maximum Thrust Nozzle

最大推力喷管原理

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15、

Unsteady internal performance study of counterflow vectoring thrust nozzle

逆流推力矢量喷管的非定常内流性能研究

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16、

Transonic vibration induced by mismatching between engine and thrust nozzle

发动机和尾喷管匹配引起的跨音振动

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17、

Design of Optimum Thrust Nozzle Contour

最佳推力喷管型面设计

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18、

A study of the maximum solid rocket engine thrust nozzle surface for one-dimensional two-phase flows

固体火箭发动机一元两相流动最大推力喷管型面研究

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19、

The condition of the existence of solution of functional extreme value problem applied to maximum thrust nozzle is also presented.

同时，还导出了最大推力喷管这个泛函极值问题解存在的条件。

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20、

A calculation method for the rocket engine's optimum thrust nozzle contour design

火箭发动机最佳推力喷管型线的计算方法

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