High speed propulsion: Performance advantage of advanced materials

High-speed air breathing propulsion systems have many attractive military and civil applications. The high propulsive efficiency of these systems allows the exploitation of speed, distance, and bigger payloads, or any combination of the three. The severe operating conditions of these systems require particular attention to overall thermal management of the engine/air-frame. Fuel-cooling the engine structure is a viable way of maintaining thermal balance over a range of flight conditions. Air Force applications have focused on using endothermic hydrocarbon fuels to address this issue because of their compatibility with the military operations. Recent ground tests of scramjet engines have demonstrated adequate performance utilizing state-of-the-art technology in materials. This progress has paved the way for an expendable flight test vehicle in the near future. In order to take full advantage of the capabilities of this propulsion system, advances in fuel-cooled structures, high temperature un-cooled materials, and increased heat capacity of hydrocarbon fuels will be needed to enable expendable systems to reach higher Mach numbers. An additional benefit would be realized in future reusable systems.     

Simultaneous measurements of multiple flow parameters for scramjet characterization using tunable diode-laser sensors

This paper reports the simultaneous measurements of multiple flow parameters in a scramjet facility operating at a nominal Mach number of 2.5 using a sensing system based on tunable diode-laser absorption spectroscopy (TDLAS). The TDLAS system measures velocity, temperature, and water vapor partial pressure at three different locations of the scramjet: the inlet, the combustion region near the flame stabilization cavity, and the exit of the combustor. These measurements enable the determination of the variation of the Mach number and the combustion mode in the scramjet engine, which are critical for evaluating the combustion efficiency and optimizing engine performance. The results obtained in this work clearly demonstrated the applicability of TDLAS sensors in harsh and high-speed environments. The TDLAS system, due to its unique virtues, is expected to play an important role in the development of scramjet engines.     

物理靶上自由飞流场全息干涉诊断

在马赫数为15的条件下,采用激光全息干涉技术在物理靶上拍摄到直径12mm的球标模自 由飞流场全息干涉图和阴影照片。通过干涉照片获得了流场中六个截面的密度分布曲线,同时从阴影照片上测量出弓形激波的归一化脱体距离为0.046。将实验照片与计算流场干涉图进行比较,二者的激波位置、条纹变化量及条纹连接基本一致。     

高超声速飞行器综合热管理系统方案探讨

高超声速飞行器是当今世界航空航天领域研究的热点,由于其在飞行中遭受的热环境极其严酷,因 而可靠的综合热管理系统是安全飞行的保证。针对不同飞行任务的高超声速飞行器,分别提出了综合热管理系 统方案;对飞行时间短,飞行速度和高度变化快的飞行器,提出了以液氢燃料为主要热沉、相变蓄热材料为辅 助热沉的热管理方案;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; 分别探讨了两套方案涉及的关键技术,指出了未来研究工作的方向。     

Oxidation/degradation of MCrAlY Coatings

One of the major reasons coatings are used in internal combustion engines is to enhance the oxidation/corrosion resistance in contaminated corrosive environments. Such atmospheres are often encountered in diesel and utility gas turbines. Aircraft gas turbines are usually subjected to simple oxidation conditions, since the environment is generally cleaner and the operating temperatures higher than in ground-based engines. The primary source of corrosive species (sulfur, vanadium and even sodium) is in the fuel; but airborne salts are a concern, particularly for those engines operating close to to ocean. Diesel engines in ships may run on fuels containing up to 5% S, 400 ppm V, and 100 ppm Na.     

Application of the method of splitting by physical processes for the computation of a hypersonic flow over an aircraft model of complex configuration

The capabilities of the computing complex developed at the Institute for Problems in Mechanics of the Russian Academy of Sciences are studied by the example of an external hypersonic flow over a model of an unmanned experimental aircraft X-43 of complex configuration. The program complex includes a generator of the unstructured surface and volumetric computational meshes and a series of computer codes that implement the integration of the closed system of Euler and Navier-Stokes equations using the method of splitting by physical processes on an unstructured mesh. The results of application of the developed numerical method on the generated unstructured computational meshes for three-dimensional modeling of the aerothermodynamics of the complex hypersonic aircraft X-43 are presented. The flow field and heat transfer processes in the entire region of the flow from the bow wave to the far wake are investigated. The configuration of the shock waves generated in the flow over a hypersonic flying vehicle (HFV) is studied. The effect of the angle of attack and free stream on the flow flown and the aerodynamic and thermal characteristics of the HFV surface is studied. The integral aerodynamic characteristics of X-43, lift coefficients C _L , and drag coefficients C _D are calculated for each regime of the flow. The HFV lift-drag ratio K dependences on the Mach number and angle of attack are found. The data of the X-43 flight and wind-tunnel tests are compared with the results of numerical modeling.     

近空间高超声速气动力数据天地换算研究

该文针对高升阻比面对称飞行器近空间高超声速飞行环境,考虑马赫数效应、粘性干扰效应和真实气体效应等多种复杂气动效应对飞行器气动力数据的影响,采用CFD数值模拟技术和气动数据相关性理论分析方法,建立了基于地面风洞试验外推获取实际飞行状态下气动力数据的天地换算方法;并采用CFD技术对气动力数据天地换算的精确性进行了验证。     

Analysis of in‐flight vibration of a twin‐engine turbo propeller aircraft

A data recorder was utilized to record in‐flight vibration of a twin engine turbo propeller (feeder) aircraft. The data recorded produced power spectral density (PSD) profiles which are currently used in laboratory settings to drive vibration tables in order to simulate a particular vehicle type. Overall Grms values were averaged and compared to previous research studies. The data collected from this research study could be utilized for packaging research when developing products and packages that will pass through a distribution cycle which includes transportation via a feeder aircraft. One example of this type of distribution cycle is the small parcel shipping environment. The PSD profiles which were analyzed from this research could simulate in‐flight aircraft vibration of the aircraft chassis in a laboratory environment. This will enable further research in the air transport environment. Copyright © 2009 John Wiley & Sons, Ltd.     

Influence of the new refrigerant thermodynamic properties on some refrigerating turbocompressor characteristics

Comparison of the main geometrical and operating parameters of centrifugal compressors working with various refrigerants is realised in this paper. The interdependence between the centrifugal compressor pressure ratio, compression work, impeller peripheral speed, Mach number, compressor capacity, impeller diameter and width, speed of rotation, and refrigerant molecular mass, normal boiling temperature and specific volumetric cooling capacity for various refrigerants are shown and discussed. The flow phenomena in the turbocompressor flow field, caused by high Mach number and high pressure ratio, are analysed. Some theoretical observations for the influence of the substitute of the refrigerant on the turbocompressor performance characteristics are presented. The possibilities for the replacement of the refrigerant in the existing refrigerating machines are discussed.     

单屏式多点气流温度传感器现场校准工况参数影响分析

采用数值仿真的手段对燃烧室试验环境下单屏式多点气流温度传感器进行仿真计算,改变温场、流场环境,分析研究了来流总温、来流总压以及马赫数等工况参数对单屏式多点气流温度传感器的测量结果的影响规律,并用试验进行验证.数值模拟结果表明:在燃烧室试验环境下,单屏式多点气流温度传感器的测温偏差随着来流总温的增大而增大,每增加1000...     

Computer simulation methods for launch vehicle mission and control problems

The flight control system of a launch vehicle is the result of the right tradeoff between different objectives, such as the interaction between the control, guidance and performance aspects of a mission with specified end conditions and the analysis of the mission trajectories and vehicle systems under a variety of normal and failure modes. Hence an evaluation of the design and performance of such a system is not feasible through purely analytical means even with simplified models. This, together with the necessity for step-by-step refinement of the models used for the vehicle and its environment, calls for the computer simulation approach. The various considerations involved in developing and selecting the simulation model and implementing it on a computer are discussed. To illustrate the approach, a hybrid simulation evaluation of the performance of the first stage control system of a satellite launch vehicle and that of the controlled vehicle under different operational modes is presented.     

Tandem Configurations for Automated Guided Vehicle Systems and the Analysis of Single Vehicle Loops

Automated Guided Vehicle (AGV) systems continue to play a significant role in many low to medium flow manufacturing operations, including Flexible Manufacturing Systems (FMS) and other applications. The relatively inexpensive guidepath, coupled with the high degree of flexibility and control offered in vehicle routing, has made AGV systems a proven and viable handling technology for the 90's.

Traditionally, AGV systems have been implemented and analyzed assuming that every vehicle is allowed to visit any pick up/deposit point in the system. We introduce a conceptually simple and intuitive approach where the system is decomposed into non-overlapping, single-vehicle loops operating in tandem. In this paper, we also develop an analytical model to study the throughput performance of a single vehicle loop. The resulting expressions are the first closed form analytical expressions that have been obtained to determine the throughput capacity of a single vehicle operating under a specific dispatching rule in a non-deterministic environment.     

高孔隙率多孔氮化硅构件较高马赫数下流-热-固耦合力学特性分析

以凝胶注模技术制备的固相含量为40%、45%、50%(质量分数,下同),孔隙率高达65.24%、63.26%、61.19%的多孔氮化硅天线罩材料作为研究对象。将测得的材料性能参数作为有限元分析模拟的数据支撑,构件模型载体选择正切尖拱形,使用FLUENT模拟流场,结构场采用ANSYS软件,热力耦合得到不同固相含量的材料在不同马赫数下流-热-固耦合后的热应力强度,对其力学特性进行分析。结果表明,较高马赫数下的飞行构件的尾部连接端是受热应力最大的部位,也是失稳较为严重的部位。飞行构件的结构稳定性需通过加固尾部连接端来提高;气动热是引起天线罩构件失稳的首要问题,解决结构失稳的关键在于解决气动热,可通过在天线罩构件外增加耐热隔层,使其免受气动热;多孔氮化硅材料的孔隙率与失稳时对应的马赫数成正比,热导率是影响多孔氮化硅天线罩构件在较高马赫数下受到热应力大小的关键因素。     

Approximate boundary conditions for the flow of a mixture of reacting gases

Summary Slip boundary conditions are deduced for the Navier-Stokes equations describing the flow of a mixture of gases along a wall. Chemical reactions and changes of the internal energy at the wall are taken into account. A simplified approximation is introduced for a special case of the flow of a binary mixture consisting of atoms and molecules, which can be used as a model in treating the high-altitude flight of a space vehicle. The resulting conditions are compared with those given by other authors.     

DETERMINATION OF OPTIMAL ROTATING FLOAT IN A CLOSED LOOP SYSTEM: A CASE STUDY

The present study relates to a transport organisation operating a fleet of aircraft and aims at determination of the optimal spare float of engines. The flow of the engines is viewed as a queueing problem in a closed loop system with variable demand and supply. The servicing facility consists of three stations in tandem. Two cases of the servicing facility operation are investigated, first when no inter-stage queue is permitted, and second when a queue length of one unit is allowed between the first and second stations. The solution is obtained by the Monte Carlo Simulation technique. The results are compared with those obtained from a reliability theoretical approach and conclusions are drawn.     

几种典型温度传感器跨超音速恢复特性校准

介绍了跨、超音速条件下温度传感器恢复特性的校准设备与校准方法,采用反串、低流速原位互校等方法,针对几种典型结构的温度传感器进行了马赫数0.95～2.0条件下的恢复特性校准,并与美国航空航天局的校准结果进行了比较,结果表明,二者之间的相对偏差在0.1％ ～2.8％之间.通过校准实验揭示了跨、超音速条件下温度传感器恢复特性...     

飞行器动态数据存储测试系统的可靠性分析

本文针对某回收式飞行器动态数据存储测试系统,从可靠性设计理论出发,在建立元器件可靠性模型及分析了飞行器测试系统的应用环境、构成系统可靠性关键元器件工作环境的基础上,对飞行器测试系统进行了详细可靠性预计计算,预测系统是否能达到要求的可靠性指标。在分析了一种可靠性分配算法的基础上,进行可靠性分配,将系统的可靠性指标分配到构成系统的电路单元上。     

Knock characteristics of dual-fuel combustion in diesel engines using natural gas as primary fuel

This paper investigates the combustion knock characteristics of diesel engines running on natural gas using pilot injection as means of initiating combustion. The diesel engines knock under normal operating conditions but the knock referred to in this paper is an objectionable one. In the dual-fuel combustion process we have the ignition stage followed by the combustion stage. There are three types of knock: diesel knock, spark knock and knock due to secondary ignition delay of the primary fuel (erratic knock). Several factors have been noted to feature in defining knock characteristics of dual-fuel engines that include ignition delay, pilot quantity, engine load and speed, turbulence and gas flow rate     

微束等离子喷涂Al2O3陶瓷涂层特性

采用轴向中心送粉式微束等离子喷涂系统在2kW级的小功率条件下制备了Al2O3陶瓷涂层.研究了电弧功率、工作气体流量和喷涂距离对粒子速度与涂层组织结构和性能的影响.采用光学显微镜观察涂层的组织结构,采用X射线衍射分析涂层的相结构,采用磨粒磨损质量损失表征涂层的性能,用热辐射粒子速度温度测量系统测试工艺参数对喷涂粒子速度的影响.结果表明,电弧功率、工作气体流量和喷涂距离对粒子速度的影响都比较明显,粒子速度随着电弧功率和工作气体流量的增加而增加,随着喷涂距离的增加而下降.涂层的磨粒磨损质量损失随电弧功率的增加而减少,而随工作气体流量和喷涂距离的增加而增加.分析表明粒子的温度对涂层磨粒磨损质量损失有较大的影响.采用微束等离子喷涂可以制备磨粒磨损性能与传统等离子喷涂在38kW下制备的涂层相当的Al2O3涂层.     

KL-15A型制氧制氮车高原试车

通过制氧制氮车的高原试车实践,分析高原环境对设备正常工作的影响,提出了保证设备在高原环境下安全、可靠运行的操作要点。