The AWIATOR airborne LIDAR turbulence sensor

The development and first flight tests are described of a short pulse direct measuring UV LIDAR for the measurement of gusts, turbulence and potentially wake vortices. The results of these stage 1 tests confirm that relative wind velocities can be measured with a standard deviation of below 10 m/s even at high altitudes with no appreciable aerosol concentrations. Operating the system under various flight conditions including rain, dense clouds, and clear air up to 24,000 ft was highly successful. Means to push the standard deviation below 1.6 m/s, foremost by increasing the laser output power and the efficiency of the light collecting system, are identified and quantified. Questions of instrument stability are addressed.     

NiCrAlYSi涂层/DD6单晶高温合金界面再结晶和互扩散行为

采用电子束物理气相沉积(EB-PVD)在单晶高温合金DD6基体上沉积NiCrAlYSi涂层.利用X射线衍射(XRD)、扫描电镜(SEM)、能谱仪(EDS)以及透射电镜(TEM)等研究了高温扩散过程中NiCrAlYSi/DD6的界面再结晶和互扩散行为.研究结果表明合金表面喷砂处理后的涂层试样经1 323 K真空热处理4 ...     

Active transmitting phased antenna arrays

The benefits of using transmitting phased array antennas for radar systems are examined. Accurate performance prediction for the transmitting phased array antennas requires theories describing both the antenna system and the power generation devices. These theories were created and applied to the design and performance evaluation of the Russian 3-D mobile solid-state surveillance radar 67N6E (GAMMA-DE), a PAA designed for long-range air defense.     

Preliminary Evaluation of GPS Performance for Low-Cost General Aviation

Preliminary results of a simulation effort to evaluate the requirements and feasibility of the global positioning system (GPS) as a civil air navigation system are presented. Evaluation is made of GPS requirements, from operational considerations, such as application to nonprecision approaches. The conceptual low-cost GPS receiver simulated here does not correct for the ionospheric or trophospheric delay, is sequential in nature, tracks only four satellites, and is not mechanized to make independent range rate measurements based on the Doppler shift of the GPS carrier frequency. The proposed GPS system has significantly different performance characteristics from the presently used VHF omnidirectional range (VOR) solidus distance-measuring equipment (DME) system. The GPS is a low signal level system and many have a relatively slow data rate due to the low-cost sequential receiver design. The results indicate that although the conceptual low-cost GPS receiver/ navigator is potentially more accurate than a VOR, the accuracy may degrade during aircraft turns and satellite shielding periods.     

Estimating the Doppler centroid of SAR data

After reviewing frequency-domain techniques for estimating the Doppler centroid of synthetic-aperture radar (SAR) data, the author describes a time-domain method and highlights its advantages. In particular, a nonlinear time-domain algorithm called the sign-Doppler estimator (SDE) is shown to have attractive properties. An evaluation based on an existing SEASAT processor is reported. The time-domain algorithms are shown to be extremely efficient with respect to requirements on calculations and memory, and hence they are well suited to real-time systems where the Doppler estimation is based on raw SAR data. For offline processors where the Doppler estimation is performed on processed data, which removes the problem of partial coverage of bright targets, the ΔE estimator and the CDE (correlation Doppler estimator) algorithm give similar performance. However, for nonhomogeneous scenes it is found that the nonlinear SDE algorithm, which estimates the Doppler-shift on the basis of data signs alone, gives superior performance     

Thin-film Li-LiMn2O4 batteries

Thin-film rechargeable Li-LiMn₂O₄ batteries have been fabricated and characterized. Following deposition by electron beam evaporation of LiMn₂O₄, the amorphous as-deposited cathode films 1 cm² in area by 0.3to 4-μm thick were annealed at 700°C to 800°C in oxygen in order to form the crystalline spinet phase. The specific capacity of the cells between 4.5 V to 3.8 V ranged from 50 μAh/mg to 120 μAh/mg. When cycled over this range, the batteries exhibited excellent secondary performance with capacity losses as low as 0.001% per cycle. On charging to 5.3 V, a plateau with a median voltage of 5.1 V was observed. The total charge extracted between 3.8 V to 5.3 V corresponded to about 1 Li/Mn₂ O₄     

纯电动城市客车EMB执行机构驱动电机制动性能分析

传统气压制动系统存在压缩机、制动油箱和空气管路,占据较大空间,而采用电子机械制动(EMB)系统代替,不但可以减小空间,还能实现对夹紧力的快速响应和精确控制。以纯电动城市客车为目标车型,讨论了EMB执行机构方案,根据传统气压盘式制动器最大夹紧力推导出电机的堵转转矩和空载转速。据此设计了永磁无刷直流驱动电机,堵转转矩为10 N·m,空载转速为370 r/min。在Maxwell 2D中搭建驱动电机有限元模型,分析电机在消除间隙阶段和夹紧力增加阶段的制动性能。结果表明所设计的驱动电机制动性能可满足要求。     

内混式空气助力喷嘴喷雾水滴尺寸分布建模

获取喷嘴出口喷雾的水滴尺寸分布(DSD)和水滴平均直径(MVD)对地面结冰实验设施云雾参数计算与调试至关重要。采用相位多普勒干涉仪对内混式空气助力喷嘴开展了喷雾实验研究;采用最小二乘法确定了DSD经验函数参数,建立了喷嘴出口喷雾的DSD模型,探究了喷嘴动力参数(NDPs)对DSD的影响;校验了Wigg MVD估算公式及其修正形式,分析其在具体工程应用中的局限性,提出了基于NDPs的MVD估算公式。研究发现:修正Rosin-Rammler分布函数与实验数据更为吻合,可作为描述喷嘴出口喷雾DSD的模型;NDPs对DSD有明显影响,且气压的影响更为显著;基于NDPs的MVD估算公式能提供精度可接受的MVD预估值,且比Wigg MVD估算公式及其修正形式更易于工程应用。     

中空纤维膜分离性能实验与预测

利用机载中空纤维膜分离性能测量台架,针对分离性能随引气压力、引气温度、飞行高度等因素的变化规律开展了实验研究;并采用所获得的实验数据作为训练及验证样本,应用人工神经网络预测技术分析了该型膜的性能.研究结果显示:①所建立的数学模型可实现对中空纤维膜分离性能的有效预测;②制氮体积分数与量纲一制氮量成反比,当要求制氮体积分数较高时,其量纲一制氮量下降,制氮效率降低;③在一定制氮体积分数下,制氮量随引气温度、引气压力的增加而增加;制氮效率随引气压力的增加而增加,但随引气温度的增加而减小;④在飞行高度增加的情况下,量纲一制氮量和制氮效率都增加, 而制氮体积分数的影响随飞行高度增加而减小.      

机载前视式风切变探测,告警系统的发展

较详细地介绍了红外辐射计式、微波多普勒和激光多普勒风切变探测，告警系统的研制发展现状及存在的问题，通过研究给出了一些结论：（１）红外辐射、微波和激光多普勒雷达系统可以用来探测低空风切变，并提供告警时间；（２）红外辐射系统可测量垂直风风速，而微波，激光多普勒协达系统可测量水平风风速，但不论那一种探测系统都无法同时测量水平风和垂直风风速；（３）地杂波是造成微波系统误警的主要因素之一；（４）激波系统对降     

复杂环境下微小飞行器惯性/激光雷达Robust-SLAM方法

针对微小型飞行器在巡检、探测和地图构建等应用中关键的自主导航技术,提出了一种基于惯性辅助的激光雷达Robust-SLAM方法用于微小型飞行器自主导航。相对于传统的激光雷达SLAM方法,该方法在SLAM框架中引入了感知环境突变检测方法,并且加强了惯性与SLAM的组合程度,有效地解决了高程方向感知环境发生突变时激光雷达SLAM定位误差大的问题。室内车库实际飞行实验结果表明,该方法能够实现微小型飞行器在三维空间中实时可靠的自主导航,具有较好的工程应用价值。     

Sikkim's Teesta River fog, mist and dust particle monitoring using monostatic LIDAR

Fog, mist, and atmospheric dust particles, having the dimension of one micrometer or less, play an important role in the deterioration of visibility, as well as in causing local warming in the atmosphere. With an attempt to reduce the deterioration, a scientific approach has to be taken to determine their origins. A monostatic LIDAR may be one of the best instruments for such work. The authors are tempted to develop such a LIDAR for fog, mist, and dust particle monitoring over River Teesta at Sikkim. LIDAR is an acronym for Light Detection And Ranging. What can we do with LIDAR? Measure distance, measure speed, measure rotation, measure chemical composition and concentration, and measure cross-sections of the targets. The digital technique is always utilized for its development which results in better security, lower power consumption, higher power efficiency, higher reliability, lower transmitter power, lower multipath effect, higher interference suppression as compared to an analog system. The commercial systems like disdometer, rain radar, mobile robot, etc., utilizing LIDAR principles are operational in different parts of the world. The authors are highly motivated for such LIDAR development and their development effort follows.     

MEMS inertial rate and acceleration sensor

Development of the μSCIRAS^TM (pronounced micro-Cyrus) multisensor for a period of over six years has produced a practical MEMS Inertial Measurement Unit (IMU). Using only three silicon sensors, a full-up IMU suitable for tactical grade navigation and guidance applications has been achieved. Iterative improvements in silicon sensor design and bulk micromachining processes have matured to the point where an IMU with an attractive price/performance ratio is now producible. This paper summarizes the design features and test results for an IMU with <100 deg/hr performance. Test results are shown for rate bias and acceleration bias over temperature. Production of this initial member of the μSCIRAS product family begins this year to support applications including guided artillery shells, technology insertion to decrease missile costs, navigation of remotely-piloted vehicles, dismounted soldier location devices and other navigation aids. The small size of this silicon multisensor and its ability to measure both angular rotation rate and linear acceleration provides a useful advantage in product packaging, cost, size, and system testing. The μSCIRAS Inertial Sensor Assembly (ISA) is housed in a 2 cubic inch package weighing less than 5 ounces (140 grams) requires less than 0.8 Watts of power. Continuing development will lead to greatly improved performance on the order of 1 deg/hr at low prices in high-volume production     

Effects of flow parameters on thermal performance of an inner-liner anti-icing system with jets impingement heat transfer

The multiple jets impingement heat transfer is widely applied in the wing anti-icing system. It is challenging to apply the similarity criterion to carry out the anti-icing experiments due to the complex flow and heat transfer behavior. In the present study, the full-scale slat model is used to carry out anti-icing experimental researches in a 2 m × 3 m icing wind tunnel of China Aerodynamics Research and Development Center. The effects of icing parameters Liquid Water Content (LWC) and Median Volume Diameter (MVD) and hot air parameters (mass flow rate and temperature) on the thermal performance of an inner-liner anti-icing system with jets impingement heat transfer are studied. The effects of the experimental parameters are analyzed in detail by combining impingement and evaporation heat transfer mechanisms. The impingement hot air mass flow rate dramatically affects the heat transfer performance of the impingement stagnation region within the range of the experimental parameters. The temperature of impingement hot air and that of wing skin are approximately linear correlated. The experimental results show the effects of LWC and MVD on water film formation and runback ice accretion. The formation of water film is analyzed by an analytical method based on the wing skin temperature difference of dry and wet air conditions.     

Airdrop ballistic winds operationally capable lidar

The Airdrop Ballistic Winds (ABW) team at Wright-Patterson AFB, Ohio, conducted flight tests of its 2 μm laser radar (lidar). This system, called the Operationally Capable Lidar (OCL), was installed in a modified C-130 fuel pod. The OCL was designed to: (1) provide real-time, 3-D maps of wind fields between the aircraft and the ground; and (2) significantly improve airdrop accuracy from high altitudes. This paper briefly describes the OCL, the Precision Airdrop simulation (PADS) tool, and flight test activities, including the Precision Airdrop Integrated Demonstration     

Automotive-grade MEMS sensors used for general aviation

The attitude heading reference system (AHRS) provides data for primary flight instruments, head-up displays, autopilots, and moving map navigation systems. Advances in solid-state MEMS rate sensors, coupled with Kalman filter algorithms designed to mitigate high drift rates, provide the basis for low-cost, high-performance AHRS for general aviation. This paper describes the performance of a low cost, miniaturized AHRS using automotive-grade MEMS sensors. The performance of the system is detailed. The implications for certification of this class of system and fault tolerance are discussed.     

平箔片楔形高度对气体止推箔片轴承特性影响

针对波箔型气体止推箔片轴承,建立了箔片结构二维薄板模型,并通过有限差分法和有限元法耦合求解可压缩气体Reynolds方程和气膜厚度方程,获得了给定轴承载荷条件下轴承气膜压力分布、气膜厚度分布、平箔片变形量和功率损耗等轴承特性.通过对比楔形高度分别为25,70,100,200,300μm时的轴承特性仿真结果研究了楔形高度对轴承性能的影响.结果表明:降低楔形高度使轴承气膜压力分布更均匀,并降低了平箔片的局部集中载荷.但楔形高度存在一个最佳值,使得达到相同轴承载荷所需的最小气膜厚度最大,并且轴承具有最小功率损耗,提高了轴承的工作效率.该结果为气体止推箔片轴承的结构设计提供的理论参考.      

旋流杯燃烧室头部流场与喷雾对贫油熄火的影响

对两种不同的燃烧室头部(三旋流杯头部为A型、双旋流杯头部为B型)进行了研究。对有两种头部的燃烧室进行了冷态流场的数值模拟,用粒子动态分析仪(PDA)测量了两种头部的速度场和喷雾场,结合慢车工况的贫油熄火试验结果进行了分析。结果表明:A型头部喷雾的索太尔平均直径(SMD)和均匀度能满足燃烧室的性能要求,比B型头部的要好,但其贫熄特性不理想。而B型头部的贫熄特性好于A型;A型头部的内旋流器气流流通量应减小一些,以利于喷嘴端部低压区的形成,这样有可能进一步降低贫油熄火油气比。      

The Pioneer Anomaly in the Light of New Data

The radio-metric tracking data received from the Pioneer 10 and 11 spacecraft from the distances between 20–70 astronomical units from the Sun has consistently indicated the presence of a small, anomalous, blue-shifted Doppler frequency drift that limited the accuracy of the orbit reconstruction for these vehicles. This drift was interpreted as a sunward acceleration of a _P =(8.74±1.33)×10^?10 m/s² for each particular spacecraft. This signal has become known as the Pioneer anomaly; the nature of this anomaly is still being investigated. Recently new Pioneer 10 and 11 radio-metric Doppler and flight telemetry data became available. The newly available Doppler data set is much larger when compared to the data used in previous investigations and is the primary source for new investigation of the anomaly. In addition, the flight telemetry files, original project documentation, and newly developed software tools are now used to reconstruct the engineering history of spacecraft. With the help of this information, a thermal model of the Pioneers was developed to study possible contribution of thermal recoil force acting on the spacecraft. The goal of the ongoing efforts is to evaluate the effect of on-board systems on the spacecrafts’ trajectories and possibly identify the nature of this anomaly. Techniques developed for the investigation of the Pioneer anomaly are applicable to the New Horizons mission. Analysis shows that anisotropic thermal radiation from on-board sources will accelerate this spacecraft by ～41×10^?10 m/s². We discuss the lessons learned from the study of the Pioneer anomaly for the New Horizons spacecraft.     

The Near-Earth Asteroid Rendezvous Laser Altimeter

In 1999 after a 3-year transit, the Near-Earth Asteroid Rendezvous (NEAR) spacecraft will enter a low-altitude orbit around the asteroid, 433 Eros. Onboard the spacecraft, five facility instruments will operate continuously during the planned one-year orbit at Eros. One of these instruments, the NEAR Laser Rangefinder (NLR), will provide sufficiently high resolution and accurate topographical profiles that when combined with gravity estimates will result with quantitative insight into the internal structure, rotational dynamics, and evolution of Eros. Developed at the Applied Physics Laboratory (APL), the NLR instrument is a direct-detection laser radar using a bistatic arrangement. The transmitter is a gallium arsenide (GaAs) diode-pumped Cr:Nd:YAG (1.064-µm) laser and the separate receiver uses an extended infrared performance avalanche-photodiode (APD) detector with 7.62-cm clear aperture Dall–Kirkham telescope. The lithium-niobate (LiNbO3) Q-switched transmitter emits 15-ns pulses at 15.3 mJ pulse^-1, permitting reliable NLR operation beyond the required 50-km altitude. With orbital velocity of 5 m s^-1 and a sampling rate of 1 Hz, the NLR spot size provides high spatial sampling of Eros along the orbital direction. Cross-track sampling, determined by the specific orbital geometry with Eros, defines the resolution of the global topographic model; this spacing is expected to be <500 m on the asteroid's surface. Combining the various sources of range errors results with an overall range accuracy of 6 m with respect to Eros' center-of-mass. The NLR instrument design, perfomance, and validation testing is decribed. In addition, data derived from the NLR are discussed. Using altimetry data from the NLR, we expect to estimate the volume of 433 Eros to 0.01% and its mass to 0.0001% accuracies; significantly greater accuracies than ever possible before NEAR.