高超声速飞行器非线性建模及开环特性分析

根据美国NASA Langly研究中心提供的有关Winged-Cone飞行器的文献资料,建立和完善了一类近空间高超声速飞行器的六自由度非线性模型.开环仿真分析结果表明,所建模型能够体现出高超声速飞行器复杂的非线性、强耦合性以及快速时变性等特点,可以为开展近空间高超声速飞行器控制问题的研究提供测试平台.     

Accessing NASA technology with the World Wide Web

NASA Langley Research Center (LaRC) began using the World Wide Web (WWW) in the summer of 1993, becoming the first NASA installation to provide a center-wide home page. This coincided with a reorganization of LaRC to provide a more concentrated focus on technology transfer to both aerospace and non-aerospace industry. Use of WWW and NCSA Mosaic not only provides automated information dissemination, but also allows for the implementation, evolution and integration of many technology transfer and technology awareness applications. This paper describes several of these innovative applications, including the on-line presentation of the entire Technology Opportunities Showcase (TOPS), an industrial partnering showcase that exists on the Web long after the actual 3-day event ended. The NASA Technical Report Server (NTRS) provides uniform access to many logically similar, yet physically distributed NASA report servers. WWW is also the foundation of the Langley Software Server (LSS), an experimental software distribution system which will distribute LaRC-developed software. In addition to the more formal technology distribution projects, WWW has been successful in connecting people with technologies and people with other people     

基于DES方法的三角翼激波-涡干扰流场数值模拟

采用基于Spalart-Allmaras湍流模型的脱体涡模拟（DES）方法,数值求解Navier-Stokes方程,模拟绕尖前缘三角翼的跨音速流动,并对三角翼上翼面的复杂激波-旋涡干扰流场进行了分析。与NASA兰利研究中心的NTF风洞实验结果对比分析表明,DES方法能很好地模拟跨音速三角翼上的旋涡流动。随着攻角由中度攻角增加到大攻角,支架附近的激波越来越强,对主分离涡的干扰作用越来越大,直至出现激波干扰导致的涡破裂。激波的形状、位置及涡破裂位置均与实验结果吻合良好。     

四种飞行器绕流的三维DSMC计算与传热分析

在地球大气层与火星大气层中,使用自己编制的DSMC(direct simulation Monte Carlo)源程序完成了四种飞行器(即Apollo,Orion,Mars Pathfinder以及Mars Microprobe)高超声速穿越稀薄气体时的三维绕流计算,给出了上述飞行器42个典型飞行工况(其中包括在地球大...     

高温高速稀薄流的DSMC算法与流场传热分析

在非结构网格下,研究了热力学碰撞传能的6种方式和化学反应的8种类型,详细给出了上述碰撞传能和化学反应碰撞类型的子程序计算框图.在可变硬球(VHS)分子模型、Borgnakke-Larsen唯象模型、Bird的化学反应几率模型以及壁面CLL(Cercignani-Lampis-Lord)反射模型的基础上,用Fortran语言编制了能够模拟内能松弛、热力学非平衡和化学非平衡的稀薄气体DSMC(direct si mulation Monte-Carlo)源程序,在地球大气层和火星大气层中完成了Ballute减速装置的8个工况计算(其中Knudsen数从0.05变到30.0,飞行Mach数从26.3变到11.2),并与NASA Langley研究中心2007年发表的计算结果作了比较,本文的结果令人满意.另外,这里用|T-T_v|/T去分析热力学非平衡,用Damk hler数去分析化学反应非平衡,用Stan-ton数去分析飞行器壁面的传热效果,所有这些分析对高温部件的热防护设计十分有益.      

Vortical flow management techniques

‘Vortex management’ refers to the purposeful manipulation and re-ordering of stable and concentrated vortical structures (e.g., resulting from flow separations from highly-swept leading edges and slender forebodies at moderate to high angles of attack) in order to enhance the aerodynamic performance and controllability of advanced, highly-maneuverable supersonic configurations. Exploratory experiments based on this approach have been conducted on generic research models at NASA Langley Research Center during recent years, investigating practical vortex flow control concepts and devices aimed at maneuver drag reduction, high angle of attack, pitch yaw and roll control, trimmed lift enhancement for short-field landing, etc. This paper reviews a selection of results attempting to clarify the basic aerodynamics of those concepts, and to evaluate their potential for improving performance and control. The vortex management concepts discussed herein include: aerodynamic compartmentation of highly-swept leading edges for alleviation of pitch non-linearities; capturing the leading edge vortex suction on forward-sloping flap surfaces for maneuver drag reduction; vortex lift modulation with articulated leading edge extensions for pitch-down and roll control at high angles of attack; vortex lift augmentation in the wing apex region to trim trailing edge flaps allowing shorter landing; and forebody vortex manipulation to alleviate uncontrolled asymmetry and also to generate yaw control in post-stall maneuvering. The precursor studies discussed here generally substantiated the vortex control concepts; questions such as configuration-sensitivity and scale effects are under continued investigation at NASA Langley and elsewhere.     

绝对式恒光源24位光电轴角编码器在光电经纬仪上的应用

为满足某型光电经纬仪的使用要求,设计了某绝对式恒光源 24位光电轴角编码器分系统。该编码器采用 16位绝对式光学码盘,码盘刻划有粗码道、通圈码道、中精码道和精码道。精码道的线对数为 16 384(14位)。方位和高低编码器的处理电路设计在一块电路板上,采用一片 DSP为主机,6个读数头输出 64路码盘光电信号分别经放大整形、A/D转换输入至 DSP。DSP完成数据采集、细分、译码、校正等处理,把轴的转角变换成 24位自然二进制角度代码输出和上传。使用情况表明:该编码器的光机结构布局合理、性能稳定,电路板和元器件少、操作简单、测角精度高,满足某型光电经纬仪对于编码器系统的要求,具有较高的实用价值。     

某型发动机的单片机控制系统

某型发动机转速调节器是气动液压式的开闭式混合调节系统, 其结构复杂、重量大。为了研制新的控制系统, 采用16位单片机8098, 它是专门为具有16位微控制器的速度和具有8位外部总线而设计的。具有质量高、功能全且易于调整特点, 最适用于步进电机的控制。系统仿真和半物理模拟试验表明, 数字控制系统的时间响应, 在相同干扰情况下, 优于气动液压式控制系统。      

美国推进系统数值仿真(NPSS)计划综述

通过对国外有关献资料的收集，整理和分析，综合介绍了由美国NASAGlenn研究中心（GRC）组织实施的“推进系统数值仿真”（NPSS）计划的发展历程，研究意义。研究目标，研究进度，组成和构架，主要关键技术及应用等情况，并对我国航空发动机数值仿真系统的发展提出了建议。     

一种基于三维粘性流场的乘波体生成方法

为了便于乘波体的优化设计工作,本文实现了一种基于任意三维粘性流场,在激波面上截取乘波体前缘线来生成乘波体外型的设计方法,并与NASA Langley研究中心的CFL3D软件的算例结果进行了比较检验,误差满足工程计算要求.由于在流场计算中直接计入了粘性,而不像大多数的研究方法那样通过无粘计算再进行粘性修正,而且对于高超声速乘波体设计,可以在程序中考虑真实气体效应、化学反应等因素,因此本文的设计方法更接近工程实际,更具有推广价值.     

太空环境下电子束原位制造技术

美国国家航空航天局（NASA）载人探索计划的提出给载人登月和载人火星等带来了机会和风险,NASA的工程师和科学家正在开展在月球或火星表面利用当地提炼的材料进行原位制造工艺技术的研究。首先,介绍了太空原位制造和修复（ISFR）技术的概念和特点,结合该技术的发展背景,介绍了电子束原位制造技术的概念、特点以及在太空环境下应用的优势和潜力。然后,根据所用原材料和成形工艺原理的不同,电子束原位制造技术又分为电子束熔融（EBM）和电子束自由成形制造（EBF³）技术两个分支,分别介绍了这两个分支技术的概念、原理、特点以及采用该技术研制出的零件的性能,结合硬件设备的情况介绍了在太空环境下应用的适用性,同时也详细介绍了NASA利用兰利研究中心的C-9抛物线飞行试验系统进行电子束原位制造微重力试验的研究成果、试验数据和未来的发展趋势。最后,结合中国未来空间事业发展的需要,提出了关于发展太空环境下电子束原位制造技术的设想与建议。     

ATS-6 Experiment Summary

The ATS-6 is the most advanced experimental satellite that has evolved from the Application Technology Satellite Program conducted and implemented by NASA Goddard Space Flight Center (NASA/GSFC). This project utilizes a state-of-the-art spacecraft and ground terminal network to perform advance studies and to conduct technological demonstrations in a large number of scientific areas. The design and implementation of this unique spacecraft permitted multiple experimentation simultaneously. The control of the spacecraft is performed at ATS Operational Control Center (ATSOCC) located at NASA/GSFC. Experimentation which was performed covered a wide spectrum of communications, technological, meterorological, and scientific subjects. Three principal ground terminals are utilized to assist the experimenters to acquire data. Data reduction and analysis are performed by the many facilities at NASA/GSFC in support of the experimenters.     

CRM-WBPN风洞试验模型数值模拟

基于雷诺平均Navier-Stokes（RANS）方程和多块对接结构网格技术,采用亚跨超CFD软件平台（TRIP 3.0）,研究了共同研究模型（CRM）风洞模型支撑装置对CRM翼/身/架/舱（CRM-WBPN）模型压力分布及气动特性的影响。构造了一个包含小、粗、中、细网格的4套网格,并进行了网格收敛性研究,在升力系数为0.50条件下,开展了固定升力系数下模型支撑对CRM-WBPN模型和CRM-WB模型压力分布及挂架短舱阻力增量的影响,以及不同来流迎角下模型支撑对CRM-WBPN模型气动特性的影响。通过与NASA国家跨声速风洞设备（NTF）试验结果和CRM-WB模型数值模拟结果的对比分析,表明模型支撑对固定升力系数下挂架短舱阻力增量影响较小;在计算构型中考虑模型支撑的影响,引起升力系数和阻力系数下降、俯仰力矩系数增加,数值模拟结果更加接近相应的试验结果。     

一种用于高频疲劳试验机的程控系统

本文介绍了一种用于高频疲劳试验机的程控系统,阐述了系统的性能特点、工作原理、硬件结构和软件设计方法,同时对载荷的模糊控制进行了讨论。     

Radiation exposure predictions for short-duration stay Mars missions

The human radiation environment for several short-duration stay manned Mars missions is predicted using the Mission Radiation Calculation (MIRACAL) program, which was developed at NASA Langley Research Center. This program provides dose estimates for galactic cosmic rays (GCR) and large and ordinary solar proton flare events for various amounts of effective spacecraft shielding (both operational and storm shelter thicknesses) and a given time history of the spacecraft's heliocentric position. The results of this study show that most of the missions can survive the most recent large flares (if they were to occur at the missions' perihelion) if a 25 g/cm2 storm shelter is assumed. The dose predictions show that missions during solar minima (when solar flare activity is the lowest) are not necessarily the minimum dose cases, due to increased GCR contribution during this time period. The direct transfer mission studied has slightly lower doses than the outbound Venus swingby mission [on the order of 10-20 centi-Sieverts (cSv) lower], with the greatest dose differences for the assumed worst case scenario (when the large flares occur at perihelion). The GCR dose for a mission can be reduced by having the crew spend some fraction of its day nominally in the storm shelter (other than during flare events).     

Synopsis: Horizons in Guidance Computer Component Technology

An extensive survey of semiconductor and memory component manufacturers conducted by the Electronics Research Center of NASA and industry has resulted in estimates of the state of the art of components available to designers of on-board guidance and control computers for long-term, deep-space missions for the 1970-1972 period. The vehicle for the survey was the mission requirements for the synchronous satellite, lunar orbiter, Mars orbiter, and Jupiter fly-by solar probe missions.     

软开关组合式变换器建模与校正

针对电流控制离散脉冲调制方式下的一种软开关组合式变换器,借助于时域仿真和付里叶变换建立系统频域模型（频率特性曲线）,并在此基础上导出等效解析模型,为软开关组合式变换器系统性能分析提供了一种方便可行的方法,特别是解决了其电压调节器设计盲目性的问题。并给出了电压调节器设计及系统性能分析实例。     

Design of the TRIO system-on-chip for aerospace

Several design and testing aspects of the TRIO smart sensor data acquisition chip, developed by JHU/APL for NASA spacecraft applications are presented. TRIO includes a 10 bit self-corrected analog-to-digital converter (ADC), 16/32 analog inputs, a front end multiplexer with selectable aquisition time, a current source, memory, serial and parallel bus, and control logic. So far TRIO is used in many missions including Contour, Messenger, Stereo, Pluto, and the generic JPL X2000 spacecraft bus.     

冲压式翼伞气动性能研究

随着计算流体动力学(CFD)的发展、空投系统以及航天器回收过程对定点回收精度要求的提高,精确计算冲压式翼伞的气动参数必不可少。首先,采用有限体积元法求解N-S湍流模型的κ-ε控制方程,对NASA兰利研究中心采用的三维翼伞进行了气动性能分析,验证了方法的可行性;然后将该方法应用于某型翼伞中,分析了翼伞周围的绕流特性,得到了不同迎角来流条件以及伞衣后缘不同程度下偏的气动力数据,为翼伞系统的数学建模提供了准确的参数,从而克服了传统经验公式获得气动参数不准确的缺点。     

基于随机子空间方法的模态参数识别研究

随机子空间识别 (StochasticSubspaceIdentification ,以下简称SSI)方法是一种新的时域识别方法 ,该方法仅用自然响应数据 ,通过QR分解和SVD分解等一套正交投影算法识别系统模型。研究了SSI方法在模态参数识别领域的应用。采用NASAmini mast模型 ,仿真分析了SSI算法控制参数选择技巧 ,论证了其参数识别精度。通过处理日本CFT大楼实测数据 ,研究了SSI方法识别真实结构模态参数的问题。应用Kalman滤波器 ,测量响应可以分解为模态空间响应 ,将信号功率谱分解成多条单自由度系统功率谱。