冲压发动机

可靠性是新型水冲压发动机的重要性能指标之一。

The reliability is an important index in the water ramjet .

冲压发动机燃烧稳定性及瞬态压力测量结果分析

Analysis of transient pressure measurement and stability in ramjet combustion chamber

并找到了冲压发动机燃烧室燃烧效率ηc与Ω之间的定量关系式。

And a quantitative relation between combustion efficiency η c and combustion efficiency parameter Ω is formulated .

固体燃料冲压发动机的燃烧（II）

Combustion of Solid Fueled Ramjet (ⅱ)

MHD能量旁路超燃冲压发动机可行性分析

Feasibility study of MHD energy bypass scramjet

重点介绍了NASALangley研究中心固定几何形状的超燃冲压发动机喷管的气动设计。

It puts emphasis on the aerodynamic de-sign of nozzle of Fixed-Geometry Scramjet at NASA Langley Research Cen-ter .

用FLUENT软件对安装开式壁龛（长深比L/D10）的超燃冲压发动机燃烧室内的高速可压缩流动进行冷态数值模拟，以方便处理试验结果。

Numerical simulation of the inner supersonic compressible flow in a scramjet combustor with open cavities was carried out using FLUENT software to dispose the process of the experimental data .

应用二阶隐式TVD格式对固体火箭冲压发动机增程弹丸超音速进气道内部湍流流场进行了数值仿真。

The numerical simulation of supersonic inlet internal turbulent flow of solid rocket ramjet assisted range projectiles was performed by 2-order implicit TVD .

针对固体火箭冲压发动机的特点，研制了固体火箭冲压发动机CAD软件，该软件系统包括了燃气发生器设计、助推补燃室设计、进气道设计、发动机性能计算和飞行弹道的计算。

The paper presents a CAD system developed for solid propellant ramjet rocket motor design . It includes gas generator design , booster chamber design , air inlet design , performance evaluation of a ramjet rocket motor and missile trajectory demonstration .

得出采用乘波体气动布局、双模态超燃冲压发动机以及BTT转弯控制是高超音速飞行器适合的发展方向。

It is hypersonic developing direction that ride wave body aerodynamic configuration , dual-mode scramjet and BTT ( bank to turn ) control scheme .

用雷诺平均N-S方程和κ-ε双方程湍流模型，对壅塞式固体火箭冲压发动机补燃室内的掺混与燃烧流场进行了数值模拟。

By using Renault averaged Navier-Stokes equation and κ - ε turbulent combustion model , the mixing and combustion flow-field in afterburning chamber of a choked solid ramjet was numerically simulated .

超燃冲压发动机4Ma进气道试验研究

Mach 4 testing of scramjet inlet model

以King模型模化硼粒子燃烧，以几率密度模型模化湍流燃烧，对含硼贫氧推进剂固体火箭冲压发动机补燃室流场进行数值研究，并与试验结果进行了对比。

Boron particle combustion model and turbulent no-premixed combustion model were established by using King theory and probability density function in order to study the reacting fuel-rich flow field laden with boron particle in the ramjet combustor . Some obtained numerical results were tested by examination .

在冲压发动机燃烧室的设计中，给出了V型槽火焰稳定器的设计方法，利用CFD数值模拟的手段，探讨了V型槽火焰稳定器放置位置对气流参数的影响。

In the design of combustor , gave a design method of Vee gutter flame holder , based on CFD software , numerical simulation Vee gutter flame holder internal flow condition , discussed the position of holder in combustor influenced airflow pneumatic parameter .

采用二阶隐式TVD格式，结合区域分解算法对固体火箭冲压发动机增程弹丸超音速进气道内外复杂流场进行了数值模拟。

Applied second-order implicit TVD scheme and zonal method , the numerical simulation of supersonic inlet internal and external complex flow of solid rocket ramjet assisted range projectiles was presented .

数值仿真方面：首先，本文通过与NASA的试验数据对比，验证了该仿真方法运用于超燃冲压发动机流场计算的可行性。

About numerical simulations , at first the numerical results were compared with the experimental data published by NASA to prove the feasibility of the numerical method on the simulation of scramjet nozzle in hypersonic free stream .

应用PHOENICS软件模拟了固体燃料冲压发动机（SFRJ）的冷流和以HTPB、PS为推进剂的简单反应流。

Cold flow field and simple reaction flow field of the combustion of HTPB and PS within the solid fuel ramjet ( SFRJ ) are simulated using PHOENICS program .

用三维两相湍流N-S方程及湍流燃烧PDF模型模拟水冲压发动机补燃室燃烧流场，并探讨了进水流量对冲压发动机补燃室流场的影响。

The combustion field in water ramjet was simulated by means of three-dimension , two-phase and turbulent Navier-Stokes equations and PDF model . And the influence of water flow rate on performance of water ramjet was discussed .

采用LU隐式方法强耦合求解有限体积法离散的完全N－S方程及组分方程，数值模拟超燃冲压发动机燃烧室内的化学反应流场。

A three-dimensional numerical code has been developed to simulate supersonic reacting flows in scramjet combustor . The code employs an implicit , finite volume , Lower-Upper ( LU ), and time-marching method to solve the complete Navier-Stokes and species equations in a fully coupled and efficient manner .

采用基于遗传算法、Powell法和模式搜索法的多方法协作优化方法进行了以非壅塞式固体火箭冲压发动机为动力的导弹总体一体化优化设计。

Multimethod collaborative optimization algorithm based on genetic algorithm 、 Powell method and pattern searching method is used to find the best parameters of the system project of the missile propelled by the unchoked rocket ramjet .

采用矢通量分裂法求解2D－Euler方程组，对亚燃／超燃双重燃烧冲压发动机（DCR）进气分流流场及其双重燃烧的冷态掺混流场进行了数值模拟。

The flux vector splitting method is adopted to solve the 2-D Euler equations and a numerical simulation is conducted for the division-flow inlet of Dual Combustor Ramjet ( DCR ) as well as the cold-mixing flow field of both flows from a dump combustor and from a supersonic inlet .

超燃冲压发动机目前面临的一大难题就是极高的气动力热载荷，燃烧室壁面温度在未经冷却的情况下能达到3000K。这超过了一般结构材料的使用极限。

A major challenge scramjet engines currently faced is the high aerodynamic heat load . The wall temperature of combustion chamber without cooling can reach 3000K , which exceeds the limit of the general material used .

在固体燃料冲压发动机（SFRJ）性能分析基础上，通过数值模拟，研究了入口台阶相对高度、燃烧室和补燃室长度比对发动机推力、比冲的影响。

Based on analysis of performance of solid fuel ramjet ( SFRJ ), effects of relative height of inlet step and ratio of combustion length to aft burner length on thrust and specific impulse are studied by numerical simulation .

本文采用隐式格式强耦合求解有限体积法离散的考虑化学反应的广义一维Euler方程，数值模拟氢或碳氢燃料超燃冲压发动机燃烧室的化学反应流场。

Global one-dimensional finite volume Euler equations coupled with chemical reactions are implicitly solved to simulate the reacting flowfield of the combustor of Scramjet fueled by hydrogen or hydrocarbon .

SFRJ增程炮弹将冲压发动机技术与炮弹增程技术有机结合在一起，具有结构简单，比冲高，增程效果好等诸多优点，具有广阔的应用前景。

Its best work Mach Number approach gun launched projectile , The SFRJ projectile , which combines the advantages of SFRJ and Added-range projectile , is now greatly valued by the virtue of its simple structure , high specific impulse and long range , the SFRJ projectile has good prospects .

超燃冲压发动机煤油燃烧加热器设计中的流场计算

Flow Field Calculation for Designing a Kerosene Heater Used for Scramjet

以超燃冲压发动机为动力的吸气式高超声速飞行器，已成为现阶段的研究热点。

Scramjet-powered air-breathing hypersonic vehicle has become a research focus nowadays .

碳氢燃料超燃冲压发动机点火技术试验

Experimental investigation of ignition technology in liquid hydrocarbon fueled scramjet combustor

超燃冲压发动机燃烧室亚/超燃模态数值研究

Numerical research on subsonic-combustion and supersonic combustion modes in scramjet chamber

冲压发动机增程榴弹绕流流场数值分析

Numerical Analysis on Flow Field Characteristic of Ramjet Assisted Range Projectile