矢量喷管,thrust vectoring nozzle
1)thrust vectoring nozzle矢量喷管
1.Three typical stages,two sway stage and one backhaul stage,were defined according to the kinetic characteristic ofthrust vectoring nozzle.针对矢量喷管机构的运动特点,将其运动过程分为2个摆动阶段和1个定位阶段,应用概率论和随机过程理论建立了对应这3个阶段的运动功能可靠性分析模型;采用有限元软件ANSYS和机构仿真分析软件ADAMS相结合的办法,得到机构目标变量的分布;根据建立的3个阶段的可靠度数学模型,计算了矢量喷管机构的可靠度。
2.The mathematical model of turbofan engine transient process withthrust vectoring nozzle was established.建立带矢量喷管的涡扇发动机动态数学模型。
英文短句/例句
putation 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
2.Heat shield position on infrared characteristics of a vectored nozzle隔热屏位置对矢量喷管红外特征影响
3.Singularity analysis of axisymmetric vectoring exhaust nozzle轴对称推力矢量喷管运动奇异性分析
4.A Method for Calculating the Effective Vectoring Angle and Flow Coefficient of an Axisymmetric Thrust-Vectoring Nozzle轴对称矢量喷管气动矢量角和流量系数计算方法研究
5.Characteristics of Fluidic Axisymmetric Thrust-vectoring Nozzle without Injection轴对称射流矢量喷管非矢量状态下推力特性研究
6.Study on the Unsteady Flow Calculation & Transient Mathematical Model of Vectoring Nozzle;矢量喷管非定常流场计算与动态数学模型研究
7.Design of Data Acquisition System in Aeroengine Test-run and Simulation of Vectoring Thrust Nozzle;发动机试车台数采系统设计与矢量喷管仿真
8.3D Computational Study of Axisymmetric Dual-throat Fluidic Thrust-vectoring Nozzles轴对称双喉道流体控制矢量喷管三维数值模拟
9.Flow-induced Unsteady Phenomena in Counterflow Vectoring Nozzles逆流矢量喷管流动自身导致的非定常现象
10.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
11.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
12.Design Rules of Dual-throat Fluidic Thrust-vectoring Nozzle and Its Integration with the Afterbody of Aircraft;双喉道射流矢量喷管的设计规律及与后机身一体化的探索
13.Multi-objective Optimization for the Driving Mechanism of an Axial-symmetric Vectoring Exhaust Nozzle轴对称推力矢量喷管驱动机构的多目标优化设计研究
14.Numerical simulation on effects of flight parameters on internal flow of jet vector nozzle飞行参数对射流矢量喷管内流场影响的数值模拟
putational investigation of slot geometric structure effects on the flow-field of shock-induced fluidic vectoring nozzle射流缝对激波诱导矢量喷管三维流场影响的数值模拟
16.The spherical convergent flap nozzle( SCFN) is an advanced hybrid axisymmetric/ nonaxisymmetric thrust- vectoring nozzle.球形收敛调节片喷管(CFN)一种正在研制中的先进的轴对称/轴对称混合式推力矢量喷管。
17.A study for thrust vector control of aerospike nozzle based on second injection塞式喷管二次喷射推力矢量控制研究
18.Analysis of Second Gas Injection Affecting Factor on SRM Thrust Vector Control气体二次喷射SRM推力矢量控制影响因素分析
相关短句/例句
vectoring nozzle矢量喷管
1.Wind tunnel research on statics thrust characteristics ofvectoring nozzle;矢量喷管静推力特性风洞实验研究
2.WT5BZ]The new type of two dimensional thrustvectoring nozzle with the secondary flow injection was studied by using experimental method and CFD method.应用实验和数值模拟的方法 ,对一种新型的推力矢量喷管—基于次流喷射控制的二维推力矢量喷管的推力矢量性能和流场进行了研究。
3)vectoring thrust nozzle矢量喷管
1.Secondary-divergentvectoring thrust nozzle based on secondary fluidic injection was designed and the performance ofvectoring thrust nozzle was studied by using computer simulation method.应用数值模拟的方法对二次扩张型射流矢量喷管进行设计并研究了其推力矢量性能,探讨了二次扩张段注入射流产生推力矢量的机理,分析了二次扩张角度以及次主流压力比(SPR,Secondary to Primary total pressure Ratio)的变化对喷管主喷流偏转特性的影响。
2.A random process model of structural functional function of components attached tovectoring 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。
4)vectoring nozzles矢量喷管
1.Two dimensional internal flow field of thrustvectoring nozzles was calculated at two fluidic thrust vectoring concepts of shock vector control and fluidic throat skewing.在激波诱导和喉道倾斜 2种流体控制方案下 ,对推力矢量喷管的二维内流场进行了数值模拟 。
5)vectoring exhaust nozzle矢量喷管
1.This paper describes a separated communicative indication system developed for aeroenginevectoring exhaust nozzle research.介绍了针对航空发动机矢量喷管研究课题，开发的一套独立通讯显示系统。
2.Thrust-vectoring exhaust nozzle is the key component to realize the deflexion of thrust.矢量喷管是实现推力矢量的关键部件,对矢量喷管的分类和设计方案进行了初步研究,在某型发动机上加装了轴对称矢量喷管,建立了起飞特性的数学模型,得出在不同状态下飞机起飞滑跑距离与推力矢量偏角之间的关系,对减小飞机起飞滑跑距离有重要意义。
6)axisymmetric vectoring exhaust nozzle轴对称矢量喷管
1.Study of internal performance for anaxisymmetric vectoring exhaust nozzle using numerical simulation;基于数值模拟的轴对称矢量喷管内流特性研究
2.Modeling and simulation of anaxisymmetric vectoring exhaust nozzle (AVEN) was implemented.针对航空航天柔性机构运动具有复杂非线性的特点,提出了一种在UG-ANASYS-ADAMS多软件平台下建立柔性机构模型并进行运动仿真的方法,对某轴对称矢量喷管(AVEN)机构进行了建模仿真;采用响应面方法和蒙特卡洛法相结合的方法得到了矢量喷管性能参数的概率分布,并计算了其可靠性。
3.Wall temperature distribution foraxisymmetric vectoring exhaust nozzle(AVEN) has been computed by means of closure cavity theoretic algorithm and numerical computation of internal 3D flow field in AVEN.采用封闭腔理论算法 ,利用矢量喷管的三维内流场数值计算结果 ,对轴对称矢量喷管的壁温分布进行了数值计算。
延伸阅读
传热学：拉瓦尔喷管拉瓦尔喷管：截面积先逐渐收缩后逐渐扩张的喷管﹐用以在出口处获得超声速气流。瑞典工程师拉瓦尔﹐C.G.P.de首先将它用於高速汽轮机﹐后来这种喷管也广泛应用於喷气发动机和火箭发动机。拉瓦尔喷管的上游接大容器或空间较大的通道﹐其中的气体压力可视为滞止压力0(见气体动力学)。喷管的下游压力称为背压﹐用表示。在喷管扩张段中可能產生激波(图中 拉瓦尔喷管内各种流动工况 处)。管内无激波时﹐拉瓦尔喷管内的流动可按一维定常定熵流动处理﹔管内有激波时﹐波前﹑波后的流动仍可按定熵流动处理﹐再用正激波关係把两者连接起来。图 拉瓦尔喷管内各种流动工况 为不同/0值时拉瓦尔喷管内的各种流动工况。图 拉瓦尔喷管内各种流动工况 中为马赫数﹔p 为气流压力。当/0足够小时﹐气流在拉瓦尔喷管中会不断地膨胀﹐压力连续下降﹐速度连续增大﹐马赫数也不断增大﹐收缩段中〈1﹐喉部处=1﹐扩张段中〉1﹐出口处为超声速气流。这种情况对应於图 拉瓦尔喷管内各种流动工况 中﹑﹑﹑﹑等情况。拉瓦尔喷管的理想工况是图 拉瓦尔喷管内各种流动工况 中工况。
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