飞行马赫数

本文研究的高超声速飞行器是指有良好气动外形、采用高性能动力系统、飞行马赫数达到5以上的飞行器。

Hypersonic craft is the craft with good aerodynamic shape , high-performance power system and flight Mach number above five .

研究结果表明，当飞行马赫数小于设计马赫数时加速器模式的磁控进气道可以提高进气道的性能。

It can be concluded that the accelerator mode MHD-controlled inlet can improve the inlet performance when the flight Mach number is lower than the design value .

利用空对地武器的弹道表，用遗传算法（GeneticAlgorithm，GA）辨识武器的阻力特性，即阻力系数与武器飞行马赫数之间的参数化函数关系。

Given tabulate ballistics of an air to ground weapon , the genetic algorithm ( GA ) is applied to identity the weapon 's characteristics , namely , a parameterized drag efficient as a function of the mach number of the weapon travelling in atmosphere .

研究发现，随着飞行马赫数的降低，sine-squared桥函数的精度明显下降，而erf-log桥函数始终保持很好的精度。

It appears that with the Mach number decreasing , the accurate of sine-squared bridging decreases , but erf-log bridging prove adequate .

基于飞行马赫数和高度控制的逆升压电子设备冷却系统

Reverse-bootstrap Air Cooling System Control Based on Flying Altitude and Mach Number

最大飞行马赫数3.5的吸气式动力方案初步研究吹吸气流控制大空间粉尘最佳通风参数的研究

Conceptual design of Mach number 3.5 air-breathing propulsion system Optimal ventilating parameters of push-pull flow dust control in large spaces

吸气式高超声速技术是指飞行马赫数大于5、以吸气式发动机及其组合发动机为动力、在大气层和跨大气层中实现高超声速远程飞行的飞行器技术。

Airbreathing hypersonic technology studies the technology of flight vehicle for long-distance hypersonic flight in atmosphere layer or trans-atmosphere layer at flight Mach number above 5 .

分析了炮弹飞行马赫数、自转速度、舵翼张开的初始角速度、弹簧刚度系数和初始压缩量、舵翼长度对舵翼张开过程的影响规律。

The influence of Mach number , spin speed , coefficient of spring stiffness , initial amount of compression and length of rudder wings on the unfolding process is also analyzed .

针对跨大气层飞行器外形，开展了超声速流动中的侧向喷流干扰问题研究。数值模拟了一定高度和飞行马赫数条件下不同喷流控制形式的干扰现象。

Lateral jet interaction in supersonic flow for trans-atmospheric vehicle is studied by numerical method in this paper , and different control methods by jet at different flow conditions are investigated numerically .

在此基础上对固定几何、带隔离段的双模态超燃冲压发动机在不同飞行马赫数下的流场进行了模拟，最后分析了不同的燃料喷射方向对燃烧室和隔离段流场的影响。

Then the flow fields of scramjet combustor with fix geometry and isolator are simulated at different inflow Mach number and the influence of direction of injection fuel to flow structure are analyzed .

由于局部地使用活塞理论假设，这种方法大大地克服了原始活塞理论对飞行马赫数、翼型厚度和飞行迎角的限制。

Because the piston theory is used only locally , this method greatly reduces the limitations of the classical piston theory on flight Mach number , airfoil thickness , and angles of attack .

在该模型中考虑了底排出口面积比，排气固相颗粒质量比，燃料热值，燃气分子量，燃烧室总温，飞行马赫数等因素。

In the model the exit area ratio , solid particle mass ratio , fuel enthalpy of combustion , jet gas molecular weight , chamber stagnation temperature , flight Math number etc. have been considered .

给出了空气燃烧加热器热力计算方程，计算得到了燃烧加热所需燃料流量以及补氧量随模拟飞行马赫数变化曲线，分析了加热器压力对加热所需燃料流量以及补氧量的影响。

The thermodynamic analysis equations of combustion heater are given . The flow rates of fuel and oxygen varying with flight Mach number are calculated , and the effect of heater pressure on the flow rates is analyzed .

该火箭的设计需要考虑取样飞行马赫数、取样扩压器的流量系数和气动特性、取样过滤材料的效率等特殊要求。

Some special requirements must be considered in rocket design , such as the flight Mach number during sampling flight , the flow coefficient and aerodynamic characteristic of sampling diffuser , the efficiency of filter material and others .

给出了一组磁控进气道设计参数，仿真结果表明采用磁控进气道技术可以有效地调节燃烧室进口来流状态，提高比冲，拓宽飞行马赫数范围。

A set of design parameters were given . The simulation results show that the application of MHD control technology to inlet design can effectively regulate combustor incoming flow state , improve specific impulse and extend the operating range of flight Mach number .

其中当飞行马赫数很大时，必须考虑气动热效应因素，因为气动热效应会影响壁板的结构刚度，进而会影响其颤振临界速度。

When the March number of the aircraft flights is quite large , the aerothermal effect factor should be considered for the reason that it affects the structural stiffness of the panel , and finally affects the critical flutter speed of the panel .

采用等激波强度和等激波角度方法设计的进气道在高飞行马赫数下的性能相近，在低飞行马赫数下，采用等激波强度方法设计的进气道起动性能较优。

At high flight Mach number , the performance of the forebody / inlets designed by the two methods is approximate . At low flight Mach number , the starting performance of forebody / inlet designed by the method of constant shock wave intensity is better .

采用FLUENT流动计算软件对某空射型导弹发动机的喷管及羽流流场进行了一体化的数值仿真研究，分析了导弹飞行高度和马赫数对喷管羽流流动的影响。

The numerical simulation of the nozzle and plume flow field of a rocket motor launched from air was performed using FLUENT software . The influence of flying altitude and Ma number on the plume flow was analyzed .

在对结构固有动力特性分析的基础上，分析了结构刚度、飞行高度以及马赫数变化对颤振特性的影响。

Based upon modes analysis , the effect of rigidity variation , Mach number on aeroelastic characteristics is considered .

选取了飞行高度、飞行马赫数、发动机转速以及发动机重心法向过载等4个参数作为分类的原始依据参数。

The categorization is based on 4 parameters , namely , flight height , flight Mach number , engine rotational speed and overload on the engine center of gravity .

在相同飞行高度下随飞行马赫数的增加，导弹羽流边界随之减小，同时导弹羽流结构也随飞行条件变化而有很大的不同。

At the same time , the plume structures change greatly with the variety of flight status parameters .

对飞行时间长，飞行马赫数高的飞行器，提出了以吸热型碳氢燃料为热沉的热管理方案；

For that with longer flight time and higher Mach number , a concept of thermal management system using endothermic fuels as heat sink was advanced .

采用滑翔弹道飞行是一种增加火箭弹射程的方法，但由于受到飞行马赫数、发动机工作时间和发射角度等条件的约束，使得滑翔弹道的弹道特性变得很复杂。

The ballistic flight used gliding flight is a way to increase the range of rocket , but because of the constraint conditions included the flight Mach number , running time of engines and the angle of emission , make the ballistic characteristics of ballistic flight become very complex .