WIDE-EYE helmet mounted display system for rotorcraft applications

This paper describes the Kaiser Electronics developed WIDE-EYE helmet mounted display system that uses a Kaiser unique Aircraft Retained Unit/Pilot Retained Unit (ARU/PRU) helmet display unit design. The overall system block diagram is presented and each major subsystem is described in detail. Extensions to the basic design to add full color capability are also described     

二维粒子分离器的流场及分离效率的数值模拟

数值模拟了某型惯性粒子分离器(简称IPS)的二维有粘轴对称流场分布、及各种不同尺寸砂粒的轨迹及分离效率,采用贴体坐标网格,并将多连通域转换成单连通域,在任意非正交曲线坐标系下求解IPS的分叉流动、粒子运动轨迹和分离效率。计算与实验结果吻合良好,表明:本文所采用的方法和编制的程序能反映粒子分离器的主要特征。      

载人航天器显示仪表展望

根据９０年代的先进技术展望载人航天器显示仪表的未来发展。在简单回顾现有航天器仪表之后,介绍９０年代有代表性的先进的波音７７７飞机座舱仪表。接着讨论彩色液晶平板显示仪、大屏幕显示仪与玻璃座舱等９０年代的先进技术,并提出由计算机统一管理的带自然语言输出的仪表,以发挥航天员听觉的作用和减轻航天员的视觉负担。     

基于声震探测技术的靶场炸点坐标测量误差分析

针对靶场试验时需要精确确定弹丸落点（终点）坐标的问题,提出一种声震波联合定位方法,该方法具有监控范围大、不受自然条件影响、能发现未爆弹、性价比高、反应快等特点。该方法按照一定的阵形布设传感器,依据弹丸爆炸时产生的声波（或是未爆弹落地产生的震动波）到达各传感器的时间差,采用TDOA（TimeDifferenceofArrival,到达时间差）方法对弹丸落点坐标进行计算。具体阐述了TDOA方法的定位原理,并给出了整个测量系统的组成,简要叙述了整个测量系统的部署方案;采用GDOP（GeometricalDilutionofPrecision,几何稀释精度因子）方法分析了定位误差的主要影响因素,并对各种影响因素带来的误差量进行了详细分析与计算;最后采用本文设计的测量系统针对大口径火炮弹丸终点坐标的测量在靶场进行了试验,试验结果与理论分析的误差较一致,定位精度满足测量的要求。该方法满足靶场快速测量的要求。     

基于三维激光成像系统的相机标定方法

三维激光成像系统中点云数据与影像数据的融合可以对被扫描物体赋予真彩色.为了获得点云数据与影像数据良好的融合效果,就需要精确的确定载体坐标系与相机坐标系之间的关系.本文针对三维激光成像系统点云模型真彩色处理方法进行研究,提出了一种基于三维激光成像系统的相机标定方法.通过对相机坐标系的标定,建立点云数据与影像数据之间的数学模型.实验结果显示,采用所提出的方法,能够使得三维立体点云数据与影像数据精确融合.最终得到被扫描目标的真彩色3D模型.     

飞机座舱液晶显示系统设计

分析了飞机座舱综合液晶显示系统的特点,采用数字信号处理器ADSP21060搭配FPGA设计了座舱图形液晶显示系统,并已成功应用于实际系统,具有高效、通用、灵活的特点。     

Cockpits for 2010 and Beyond

Truly optimal weapon system performance is highly dependent on the level of man-machine cockpit integration resulting from the intelligent application of crew station technologies. Future cockpits will incorporate a wide range of enhancements. Heavy application of artificial intelligence techniques can be expected to encompass the entire spectrum of crew station technologies; from data fusion, to optimized display resource management, to real-time onboard maintenance and fault reporting, and even to the optimization of pilot physiological needs. Emphasis on exploiting applications of the ultimate human resource, the mind, can be expected through the use of biocybernetics; initially to control previously manual and/or automated cockpit functions, and eventually to allow bidirectional communications. Future enhancements can also be expected to improve aircrew performance by allowing the pilot to take full advantage of aircraft maneuvering capability, and to operate effectively in hostile chemical, biological and radiological environments. New high resolution, full color, three dimensional crew station display devices will complement enlarged sensor suites and enhance aircrew situational awareness. Does the pilot really need to see the outside world to fly and fight effectively? Or, can panoramic display techniques, in an encapsulated environment, coupled with 4? steradian sensor coverage, increase performance? This paper strives to illustrate some ``no holds barred' approaches to making future fighter cockpits an ``in-tune' extension of the operator, based on current and projected tactical needs.     

Developing the next generation cockpit display system

The goal of advanced cockpit display systems is to present large amounts of information quickly and in an understandable format, enabling the aviator to improve mission performance. Current front-line cockpit display systems utilize low-resolution analog video to present two-dimensional (2-D) images on many separate displays. The future cockpit will be capable of integrating large picture digital video with three-dimensional (3-D) and 2-D color images. This system will be capable of rendering icons, maps, and world-views. It will be compatible with head mounted displays and multiple large displays to improve war-planning and combat aviator situational awareness. We are developing a massively parallel 3-D renderer which will be capable of updating 500,000 3-D triangles per second with shading, lighting, transparency, texture mapping, and hidden surface removal. The renderer design employs a massively parallel architecture with 1,024 ALUs per chip to display one million anti-aliased vectors per second. Current high end workstations are capable of these display goals, but fall far short of military reliability, size, and power requirements. The rendering system will be small enough to fit on one board, extensible to dual-seat configuration, and capable of up to eight windows per display channel     

负荷系数0.5 的高负荷单级轴流压气机设计及试验研究

为探索高负荷多级压气机的设计方法,开展了负荷系数0.5的进口级设计及试验研究。该进口级设计流量35.3 kg/s,压 比2.07,叶尖切线速度388 m/s。设计中采用了反预旋、高反力度的设计思路,转子进口相对速度全叶高超音。转静子均采用小展 弦比设计,其中转子展弦比0.68,静子展弦比1.1。该压气机在中国航发沈阳发动机研究所A219试验器上完成试验,录取了1.0和 0.95相对换算转速特性。试验结果表明：在1.0设计转速,工作点换算流量36.37 kg/s,压比2.121,效率0.894,喘振裕度8%,验证了 高反力度、高负荷多级压气机进口级设计方法。给出了流路、转静子叶型几何坐标等气动设计数据,同时也给出了试验数据,这些 数据可用于仿真软件的校核,对提高仿真软件预测精度具有重要意义。     

硅基内衬喷管扩张段烧蚀和温度场的耦合计算方法

本文叙述固体火箭喷管扩张段硅基内衬烧蚀和温度场的耦合计算方法.烧蚀采用非定常的液体层烧蚀模型;温度场计算采用圆柱坐标系下的一维径向瞬态导热模型,考虑材料在高温下形成的炭化层和热解层,而由烧蚀产生的边界移动问题用坐标变换的方法处理.利用烧蚀和导热计算方程组中二者的结合部,通过充分耦合,获得了更准确的预示计算结果.     

Backup radio site identification in air traffic control systems

The identification of backup radio sites, to increase the availability of the future air/ground (A/G) air traffic control (ATC) systems, is investigated, When there is an A/G communications failure, due to a radio site or an ATC controller access failure, another site (or sites) provides the service. The backup site should be capable of providing full coverage of the desired airspace known as the service volume. Meeting the full coverage conditions by one site or a group of sites is analyzed. It is concluded that identification of one site providing full coverage can be determined easily. The identification of a group of sites, each with partial coverage and providing full coverage is analyzed in detail. An algorithm involving both analytical and numerical approaches is described. It determines if two radio sites with given geographical coordinates, and each with partial coverage of a given cylindrical service volume, can provide full coverage. This algorithm can be implemented as a computer program to process a database of radio sites     

The C-17 multifunction display: a building block for avionicsystems

The multifunction display (MFD) developed for use as the primary cockpit display system on the US Air Force C-17A military air transport is described. The 6-in by 6-in color cathode ray tube (CRT) display features a self-contained 1750 processor and vector generator capable of processing MIL-STD-1553B aircraft data and raster video into any of 10 formats as selected by the pilot or copilot. The MFD can display stroke, raster, or hybrid formats in 16 colors. Raster images are driven by sensor inputs with an RS-170 or RS-343 interface. The CRT uses a taut mask delta gun design and provides the best available brightness and line-width performance. The display features small size, low weight, low power, standard interface, and adaptable software. Reconfigurability in the aircraft is enhanced by using four identical cockpit displays     

Effects of input method and display mode of situation map on early warning aircraft reconnaissance task performance with different information complexities

Early Warning Aircraft(EWA) are the main force for air detection and its Human-Machine Interface(HMI) should be designed to support task efficiency and safety. With the application of advanced input method and interface design in EWA, little is known about their actual usability in terms of human factors and ergonomics. The aim of this study was to investigate the effects of the input method and display mode of the situation map on EWA reconnaissance task performance with different information c...     

基于单DSP的双通道图形发生器设计

在某些应用场合需要适应苛刻工作环境要求的高性能、高可靠性嵌入式图形发生器。本文介绍一种基于SHARC数字信号处理器的“一驱二”图形发生器,可实现单处理器同时驱动两路独立的视频通道,完成复杂动态画面的实时生成,并能满足苛刻的使用条件。     

高速数据采集和分析系统研究

为了在地面实验中监测航空发动机的振动情况和进行故障诊断, 研制了高速数据采集系统、信号处理系统以及基于模糊聚类方法上的故障诊断系统。在数据采集系统中采用并行A/D结构以提高采集速度;研制高性能的数字倍频电路以准确实现整周期采样。利用软、硬件结合的方法对测试结果进行补偿, 提高了相位精度。用标准信号和现场试验信号进行考核, 结果表明该系统能很好满足测量要求。      

A flat panel display upgrade solution replaces military CRTtechnology

Successful technology insertion programs must satisfy many system constraints in order to incorporate new capabilities into aging avionics systems while meeting program cost requirements. Such constraints frequently include form, fit, and functional replacement specifications, as well as power and electrical performance restrictions. This paper describes a technology insertion program undertaken with the goal of replacing the 30-year-old azimuth indicator display of a radar warning receiver system. This necessitated the use of electroluminescent (EL) display technology to replace the analog cathode ray tube display currently used in the system. Because of the prohibitively high cost of aircraft wiring modifications, the replacement display was required to be completely form, fit, and functionally equivalent to its replacement. The form, fit, and functional equivalency requirement imposed the following system constraints: (1) power consumption of less than 10 Watts; (2) the need to maintain the same stroke-deflection current electrical interface; and (3) the need to meet the maintenance and repair budget of the existing display unit. Additional requirements included night-vision compatibility and full sunlight readability. The display was also required to be MIL-STD-1553 Remote Terminal communication capable. All requirements posed a challenging technology insertion problem to program personnel. The case study described in this paper illustrates the approach to meeting the particular requirements of this technology insertion program     

Road-map assisted ground moving target tracking

Tracking ground targets with airborne GMTI (ground moving target indicator) sensor measurements proves to be a challenging task due to high target density, high clutter, and low visibility. The exploitation of nonstandard background information such as road maps and terrain information is therefore highly desirable for the enhancement of track quality and track continuity. The present paper presents a Bayesian approach to incorporate such information consistently. It is particularly suited to deal with winding roads and networks of roads. The target dynamics is modeled in quasi one-dimensional road coordinates and mapped onto ground coordinates using linear road segments taking road map errors into account. The case of several intersecting roads with different characteristics, such as mean curvature, slope, or visibility, is treated within an interacting multiple model (IMM) scheme. Targets can be masked both by the clutter notch of the sensor and by terrain obstacles. Both effects are modeled using a sensor-target state dependent detection probability. The iterative filter equations are formulated within a framework of Gaussian sum approximations on the one hand and a particle filter approach on the other hand. Simulation results for single targets taken from a realistic ground scenario show strongly reduced target location errors compared with the case of neglecting road-map information. By modeling the clutter notch of the GMTI sensor, early detection of stopping targets is demonstrated     

风洞试验中模型迎角视觉测量技术研究

 发展了一种基于双相机的风洞试验模型迎角视觉测量技术。即在风洞模型表面绘制或喷涂一些高对比度的标记点,采用两台400万像素的工业相机采集模型的运动图像,然后求解图像的共线方程获得模型表面标记点的三维空间坐标,利用表面标记点坐标最小二乘拟合出一条空间直线,通过不同时刻空间直线单位方向矢量的变化计算出模型的迎角变化。利用精密电子倾斜仪对迎角视觉测量系统进行静态标定,结果表明:迎角视觉测量系统的准确度在0.01°以内。迎角视觉测量系统在2 m超声速风洞中对一尾支撑无主测力天平铰链力矩测量模型的实时迎角进行了测量,结果表明:系统具有很好的响应特性,可以作为风洞试验中迎角测量的一种有效方法,尤其是用于无主测力天平时模型真实迎角和支杆弹性角的测量。     

Ralph: A Visible/Infrared Imager for the New Horizons Pluto/Kuiper Belt Mission

The New Horizons instrument named Ralph is a visible/near infrared multi-spectral imager and a short wavelength infrared spectral imager. It is one of the core instruments on New Horizons, NASA’s first mission to the Pluto/Charon system and the Kuiper Belt. Ralph combines panchromatic and color imaging capabilities with SWIR imaging spectroscopy. Its primary purpose is to map the surface geology and composition of these objects, but it will also be used for atmospheric studies and to map the surface temperature. It is a compact, low-mass (10.5 kg) power efficient (7.1 W peak), and robust instrument with good sensitivity and excellent imaging characteristics. Other than a door opened once in flight, it has no moving parts. These characteristics and its high degree of redundancy make Ralph ideally suited to this long-duration flyby reconnaissance mission.     

Electronic flight progress strip prototype for en route ATC

An electronic flight progress strip (FPS) display and a color plan view display (CPVD) as a laboratory prototype are described. The purposes of prototype development are to examine the effectiveness and problems of the electronic FPS display in comparison to the current system and to identify the controller-workstation requirements, which are necessary to decide a future planning of a production prototype development. The evaluation and additional test were conducted for a typical en route transition sector. It was found that electronic FPS was useful in the normal traffic load. Some possible improvements were identified in the heavy traffic load situations represented in the additional test