高超声速飞行器高温流场数值模拟面临的问题

随着高超声速飞行器目标光辐射和电磁散射特性研究的发展和深入,高温流场特性日益引起人们的关注。由于高温流场特性研究中涉及到非常多的复杂气动现象,如气动加热、烧蚀、辐射、燃烧、化学反应以及湍流等,因此其数值模拟面临着诸多挑战。这里基于连续流计算流体力学(CFD)技术和稀薄气体蒙特卡罗直接仿真(DSMC)方法,从化学物理模型建模、方法稳定性与数值求解效率出发,分析了高超声速飞行器外部绕流、尾迹和发动机喷焰三方面的流场特性数值模拟在不同弹道、热防护手段和飞行流域环境下所面临的问题。在此基础上提出了数值求解技术和化学物理模型建模今后需要发展的方向,为有效提高高超声速高温流场特性数值模拟效率、增加流场特性预测精度提供了指导,从而为研究流场对高超声速飞行器目标光辐射和电磁散射特性影响提供有效的基础数据。     

The Galileo Plasma wave investigation

The purpose of the Galileo plasma wave investigation is to study plasma waves and radio emissions in the magnetosphere of Jupiter. The plasma wave instrument uses an electric dipole antenna to detect electric fields, and two search coil magnetic antennas to detect magnetic fields. The frequency range covered is 5 Hz to 5.6 MHz for electric fields and 5 Hz to 160 kHz for magnetic fields. Low time-resolution survey spectrums are provided by three on-board spectrum analyzers. In the normal mode of operation the frequency resolution is about 10%, and the time resolution for a complete set of electric and magnetic field measurements is 37.33 s. High time-resolution spectrums are provided by a wideband receiver. The wideband receiver provides waveform measurements over bandwidths of 1, 10, and 80 kHz. These measurements can be either transmitted to the ground in real time, or stored on the spacecraft tape recorder. On the ground the waveforms are Fourier transformed and displayed as frequency-time spectrogams. Compared to previous measurements at Jupiter this instrument has several new capabilities. These new capabilities include (1) both electric and magnetic field measurements to distinguish electrostatic and electromagnetic waves, (2) direction finding measurements to determine source locations, and (3) increased bandwidth for the wideband measurements.Deceased     

从飞机总体角度规划试飞工作

随着飞机设计技术难度的加大, 对新机进行飞行试验的工作量和复杂程度也日益提高, 试飞工作涉及的因素也越来越多。如何从飞机设计的总体角度出发, 对飞行试验的各项工作进行规划, 用以影响设计, 提前安排相关工作, 是本文研究的主题。本文将试飞纳入到型号研制的全局中, 从试飞内容、测试改装、试飞样机数量及状态、关键试飞技术、试飞保障、试飞支持等10个方面提出试飞规划内容。     

基于时间推进的涡扇发动机整机通流数值模拟

为实现航空发动机整机流场与性能快速分析,基于准三维控制方程模型,开发了整机通流数值模拟程序。程序基于计算流体力学理论,并考虑了引气、冷却和喷油等发动机中的物理现象。为模拟叶片对气流偏转作用,推导了一种鲁棒的无粘叶片力模型,同时采用粘性力模型模拟粘性损失效应。采用该程序对某型双轴分排涡扇发动机一个地面试车工况点进行了整机数值仿真,并与实验数据进行了对比验证。结果表明,所发展程序求解稳定,能够自动捕捉激波,并且可以快速获得完全收敛的航空发动机整机准三维流场,单工况点计算时长不大于30min。其中计算截面平均参数与实验测量偏差不大于8%,符合工程应用精度需求。     

Preparation of CF/Ni-Fe/CNT/silicone layered rubber for aircraft sealing and electromagnetic interference shielding applications

To meet the needs of preventing information leakage in space engineering and military industry, an efficient method was introduced to obtain layered electromagnetic shielding sealing rubber. The carbon fiber, Ni-Fe coating, and Carbon NanoTube (CNT) were combined by chemical plating and in-situ polymerization to obtain a lightweight (0.14 g/cm²) and thin (1 mm thick) Carbon fiber Fabric (CF)/Ni-Fe/CNT/silicone layered electromagnetic shielding composites. The layered material obtained by adjusting the electroless plating time exhibited a high Shielding Efficiency (SE) of 60.2–85.5 dB in the range of 0–4800 MHz, which can be used for aviation electromagnetic shielding. Carbon fibers and carbon nanotubes mainly attenuated electromagnetic waves through absorption loss, while the nickel-iron alloy coating through reflection loss interacted with the magnetic vector of incident ElectroMagnetic (EM) radiation and magnetic dipoles, therefore, the EM Interference (EMI) shielding composite attenuated EM waves with the “absorption-reflection-absorption” cooperative interaction. Moreover, the flexible fabric substrate adhered with silicone rubber possessed a breaking elongation of 52.3%, which can be utilized as a good sealing material. Simultaneously, the outstanding exothermicity (67.2 °C under the applied voltage of 5 V) makes it possible to be applied in electric heating area. The electromagnetic shielding composites prepared in this paper have good potential in the fields of precision electronic equipment and aviation systems.     

飞行器RCS近场测试技术研究进展与工程应用

雷达散射截面(RCS)测试是隐身技术和目标特性研究的基础。无论是研究物体的电磁散射特性还是研制具有突防能力的隐身武器系统,RCS测试都具有非常重要的意义。通过RCS测试可以验证电磁散射计算的理论和方法,更重要的是,对部分飞行器目标进行电磁散射理论计算非常困难,而通过测试可以直观地获得目标的电磁散射特性数据,从而避开复杂的电磁仿真计算。与外场、紧缩场RCS测试方法相比,近年来得到广泛应用与发展的RCS近场测试方法在飞行器目标的散射特性测试方面具有效率高、成本低的优势。介绍了飞行器RCS测试评估方法,综述了国内外RCS近场测试技术研究的最新进展与工程应用实例,分析展望了飞行器RCS近场测试技术面临的机遇与挑战。     

航空发动机矢量喷管控制系统试验研究

为验证航空发动机轴对称矢量喷管控制系统的阶段性研究成果,开展了配装轴对称矢量喷管的航空发动机地面整机试车验证研究工作。试验选取了几个具有代表性的航空发动机典型工作状态点进行,首次进行了在阶跃输入条件下的航空发动机整机动态性能测试,获取了航空发动机矢量喷管控制系统静态性能和动态性能的基本数据,验证了航空发动机轴对称矢量喷管控制系统的有效性,总结了该系统的油源压力和流量对控制系统性能的综合影响,具有一定的工程应用价值。     

Modelling mesoscale processes in the global geospace system

Intermediate or mesoscale processes mediate the transfer of mass, momentum, and energy across the dynamic solar wind-magnetosphere interface, and the propagation of this input through the system to the ionosphere and atmosphere. The Dartmouth-Berkeley-Minnesota theory team has identified a number of mesoscale phenomena to be investigated as part of the GGS program, including: (1) effects of upstream density fluctuations on magnetopause dynamics, (2) three-dimensional reconnection, (3) magnetopause depletion layer studies, (4) ring current interaction with Pc 1 and Pc 5 waves, (5) generation of ion Larmor-scale current layers in the near Earth plasmasheet, (6) test particle studies in the magnetotail, (7) simulation of magnetosphere- ionosphere coupling including effects of kinetic Alfvén waves and (8) auroral acceleration region studies of the effects of kinetic Alfvén waves on particle distribution functions. A broad range of techniques will be implemented including ideal and reduced MHD, two fluid, hybrid, particle-in-cell and test particle simulations. Detailed comparison of simulation results with GGS satellite and ground based data will be undertaken.     

ISTP science data systems and products

The International Solar-Terrestrial Physics (ISTP) program will provide simultaneous coordinated scientific measurements from most of the major areas of geospace including specific locations on the Earth's surface. This paper describes the comprehensive ISTP ground science data handling system which has been developed to promote optimal mission planning and efficient data processing, analysis and distribution. The essential components of this ground system are the ISTP Central Data Handling Facility (CDHF), the Information Processing Division's Data Distribution Facility (DDF), the ISTP/Global Geospace Science (GGS) Science Planning and Operations Facility (SPOF) and the NASA Data Archive and Distribution Service (NDADS).The ISTP CDHF is the one place in the program where measurements from this wide variety of geospace and ground-based instrumentation and theoretical studies are brought together. Subsequently, these data will be distributed, along with ancillary data, in a unified fashion to the ISTP Principal Investigator (PI) and Co-Investigator (CoI) teams for analysis on their local systems. The CDHF ingests the telemetry streams, orbit, attitude, and command history from the GEOTAIL, WIND, POLAR, SOHO, and IMP-8 Spacecraft; computes summary data sets, called Key Parameters (KPs), for each scientific instrument; ingests pre-computed KPs from other spacecraft and ground basel investigations; provides a computational platform for parameterized modeling; and provides a number of data services for the ISTP community of investigators. The DDF organizes the KPs, decommutated telemetry, and associated ancillary data into products for duistribution to the ISTP community on CD-ROMs. The SPOF is the component of the GGS program responsible for the development and coordination of ISTP science planning operations. The SPOF operates under the direction of the ISTP Project Scientist and is responsible for the development and coordination of the science plan for ISTP spacecraft. Instrument command requests for the WIND and POLAR investigations are submitted by the PIs to the SPOF where they are checked for science conflicts, forwarded to the GSFC Command Management Syntem/Payload Operations Control Center (CMS/POCC) for engineering conflict validation, and finally incorporated into the conflict-free science operations plan. Conflict resolution is accomplished through iteration between the PIs, SPOF and CMS and in consultation with the Project Scientist when necessary. The long term archival of ISTP KP and level-zero data will be undertaken by NASA's National Space Science Data Center using the NASA Data Archive and Distribution Service (NDADS). This on-line archive facility will provide rapid access to archived KPs and event data and includes security features to restrict access to the data during the time they are proprietary.     

疏导式热防护结构传热极限特性

疏导式热防护结构通过高温热管将前缘驻点等高热流部位的热量快速疏导至大面积区域,可有效降低防热压力,实现新型飞行器前缘非烧蚀防热。然而,疏导结构内部液体工质回流受到飞行器加速过载的显著影响。通过理论评估与地面试验获得了典型过载条件下尖前缘热疏导结构的抗过载性能。结果表明,维持加热条件不变,当过载环境大于4g后,热疏导性能受到明显影响,但过载减小后疏导性能得以快速恢复。研究结论对于一体化疏导结构的设计具有重要的指导意义。     

A computing model and its experimental testing for an evaluation of electromagnetic interferences created by interfering circuits on transmission or high-voltage lines above a dissipative ground

In this paper we present useful calculations for a prediction of the electromagnetic field created by interfering circuits on a linear horizontal transmission line over an imperfectly conducting ground. The interfering circuits are assimilated to antennas and treated by using the dipole-radiation theory. The current distribution is determinated by the transmission-line theory. We present here the computational procedure allowing a fast and accurate calculation of the electromagnetic fields components of a series of dipoles. We give the linear characteristics Z, Y of the transmission line by incorporating the ground effects. The response of a terminated one-wire transmission line set over the ground and excited by a non-uniform field is given. A comparison between computed results given by the model and experimental measurements is provided.     

A Numerical Model of the SEIS Leveling System Transfer Matrix and Resonances: Application to SEIS Rotational Seismology and Dynamic Ground Interaction

Both sensors of the SEIS instrument (VBBs and SPs) are mounted on the mechanical leveling system (LVL), which has to ensure a level placement on the Martian ground under currently unknown local conditions, and provide the mechanical coupling of the seismometers to the ground. We developed a simplified analytical model of the LVL structure in order to reproduce its mechanical behavior by predicting its resonances and transfer function. This model is implemented numerically and allows to estimate the effects of the LVL on the data recorded by the VBBs and SPs on Mars. The model is validated through comparison with the horizontal resonances (between 35 and 50 Hz) observed in laboratory measurements. These modes prove to be highly dependent of the ground horizontal stiffness and torque. For this reason, an inversion study is performed and the results are compared with some experimental measurements of the LVL feet’s penetration in a martian regolith analog. This comparison shows that the analytical model can be used to estimate the elastic ground properties of the InSight landing site. Another application consists in modeling the 6 sensors on the LVL at their real positions, also considering their sensitivity axes, to study the performances of the global SEIS instrument in translation and rotation. It is found that the high frequency ground rotation can be measured by SEIS and, when compared to the ground acceleration, can provide ways to estimate the phase velocity of the seismic surface waves at shallow depths. Finally, synthetic data from the active seismic experiment made during the HP³ penetration and SEIS rotation noise are compared and used for an inversion of the Rayleigh phase velocity. This confirms the perspectives for rotational seismology with SEIS which will be developed with the SEIS data acquired during the commissioning phase after landing.     

民用飞机防火系统研究

防火系统由探测系统和灭火系统组成。色机防火系统对指定防护区的过热、烟雾或着火状况进行探测、监控和告警,并提供有效的灭火或者火情抑制措施。一且探测到防护区发生过热、烟雾或火情等危险情况,系统向驾驶员发出告警,以便驾驶员采取相应处理程序。系统提供灭火措施,可对火情进行抑制或扑灭,保证飞机和人员的安全。系统对设备的工作进行状...     

高空低气压下电晕放电电磁脉冲辐射特性模拟实验

为研究高空低气压下飞行器表面电晕放电电磁脉冲辐射特性,以尖端导体电晕放电为研究对象,进行了低气压下电晕放电电磁脉冲辐射特性模拟实验,给出了辐射电场幅值与气压的关系表达式,并基于气体放电和电磁场理论总结了电晕放电电磁脉冲辐射特性随电压极性、气压以及测试距离的变化规律。结果表明:电晕放电电磁脉冲辐射电场时域波形呈衰减振荡形式,持续时间约为600 ns,首脉冲方向随电压极性的不同而不同,且辐射电场分量主要集中在与放电针相同的极化方向;辐射电场频谱主要分布在500 MHz以内,在35 MHz和170 MHz处出现稳定的波峰;在气压为4~30 kPa范围内,随着气压的降低,放电电磁脉冲辐射电场增强;随着测试距离的增加,电晕放电电磁脉冲辐射电场逐渐衰减。该研究结论可为低气压下飞行器电晕放电电磁脉冲辐射特性研究提供有益参考。     

Choosing software and replacing ATE: lessons learned

When tasked to ensure the Minuteman Intercontinental Ballistic Missile system remains fully operational and supportable through 2020, the Air Force realized that the support capability of its legacy automated test system for the operational ground support electronics subsystem would need to be completely replaced. The legacy test system, while fully operational, was rapidly becoming non-supportable. Unless replaced with new hardware and upgraded test program sets, the needed long-term support could not be provided to the weapon system. To address this issue within the scope of available program funding constraints, the Air Force selected an approach of combining the technical and programmatic expertise of the weapon system prime contractor, the program control responsibilities of the weapon system Program Office, and the technical capability of an Air Force technical organization. The program was divided into two phases: a prototype phase and a production/rehost phase. This paper gives an overview of the program and presents valuable lessons learned during the prototype phase.     

Applications and frustrations in using ground penetrating radar

In this paper the author concentrates on the narrow portion of the electromagnetic spectrum from a few MHz to a few GHz where geophysicists used ground penetrating radar which is sometimes called georadar, ground probing radar, or subsurface radar. Ground penetrating radar is deployed today from the space shuttle, aircraft, on the surface, in and between boreholes and sometimes from within or between mine shafts. The author discusses these applications and some of the problems involved     

UAVSAR: New NASA Airborne SAR System for Research

NASA's Jet Propulsion Laboratory is currently building a reconfigurable, polarimetric L-band synthetic aperture radar (SAR), specifically designed to acquire airborne repeat track SAR data for differential interferometric measurements. Differential interferometry can provide key deformation measurements, important for studies of earthquakes, volcanoes, and other dynamically changing phenomena. Using precision real-time GPS and a sensor controlled flight management system, the system will be able to fly pre-defined paths with great precision. The expected performance of the flight control system will constrain the flight path to be within a 10 m diameter tube about the desired flight track. The radar will be designed to be operable on a Unpiloted Arial Vehicle (UAV) but will initially be demonstrated on a NASA Gulfstream III. The radar will be fully polarimetric, with a range bandwidth of 80 MHz (2 m range resolution), and will support a 16 km range swath. The antenna will be electronically steered along track to assure that the antenna beam can be directed independently, regardless of the wind direction and speed. Other features supported by the antenna include elevation monopulse and pulse-to-pulse re-steering capabilities that will enable some novel modes of operation. The system will nominally operate at 45,000 feet (13,800 m). The program began as an Instrument Incubator Project (IIP) funded by NASA Earth Science and Technology Office (ESTO).     

基于计算机图形学的仿真系统设计与分析

针对工程中的计算机实体仿真需要，为满足各种工程领域具体仿真对象仿真设计和实验的要求，应用计算机图形学原理，采用高级编程语言提出进行计算机仿真系统软件设计的思想和方法，论述这种仿真系统中几何信息、功能信息、实体模型、特征模型所具有的功能以及各程序模块的作用及建立方法，并给出程序设计的主要流程图。     

Design and applications of airborne radars in the VHF/UHF band

The simultaneous need for ground penetration and high resolution dictates the use of frequencies less than 500 MHz for imaging ground penetrating radar (GPR) designs. It is possible to build such systems with good performance and yet not interfere with ground installations operating in the same bands. The total number of airborne GPR systems needed to saturate the market is small, (possibly less than ten), and so the buildup of noise in this spectral region occupied by these radars will be negligible. This is fortunate, since there is a clear need for such radars in such areas as humanitarian demining and unexploded ordnance (UXO) mapping. Some formal set of guidelines is needed beyond that given in Part 15 of the FCC regulations, which both recognizes the need for airborne UWB radar operations, and still protects licensed users in the band     

电磁混响室高强度辐射场下机载电台敏感度研究

机载电台作为飞机典型用频机载设备,对其进行高强度辐射场(HIRF)辐照效应试验研究具有重要意 义。为了解决混响室高强度辐射场环境的快速构建、快速调控及机载设备敏感度有效测试问题,依托混响室高 强度辐射场辐射敏感度测试系统,以某型直升机机载电台为试验对象,在400 MHz~2GHz频段内,通过改变 混响室内部场强,分别确定混响室连续与步进两种工作模式下机载电台的典型故障类型和敏感度阈值。结果 表明:在试验环境场强相同的条件下,相比步进工作模式,连续工作模式更容易测试出机载电台的敏感度阈值; 搅拌器连续工作模式下,搅拌速度越快测试得到的机载电台敏感度阈值越低,随脉冲波脉宽的增加其敏感度阈 值的测试结果呈下降趋势。