小型任务悬挂物接口标准研究

主要研究了小型任务悬挂物接口需求和标准发展情况,系统分析了国外小型任务悬挂物接口标准的主要内容和要求,并总结分析了标准的应用特点,在此基础上结合国内小型任务悬挂物的研制情况,提出编制小型任务悬挂物接口标准,为我国小型任务悬挂物接口标准制定提供支持。     

DSMS悬挂物的初始化和控制流程研究

首先指出了数字式悬挂物管理系统(DSMS)的先进性,分析了其组成和接口,然后重点研究了DSMS悬挂物的初始化和控制,包括各状态系列、接口控制动作、标准消息数据格式,进而以流程图的形式概括了整个过程.     

面向通用武器插件的悬挂物管理软件架构研究

针对机载悬挂物管理系统的特点,提出了一种悬挂物管理软件的架构设计和通用武器插件的接口方法,实现武器发射控制流程在不同飞机平台间的通用化和标准化,提高悬挂物管理软件开发的效率和软件质量。     

气动设计和优化研究——加拿大宇航研究院空气动力学实验室科研简介

文章回顾了空气动力学实验室(IAR)近年来在气动力设计、多学科设计优化、悬挂物运载及投放等项目上的研究活动。这些项目在系统模拟和优化方面无一例外地使用了计算机智能技术，比如气动力设计项目，就是以微量遗传学算法(Micro-Genetic Algorithm(μGA))为基础，开发了模拟神经网格(Artificial Neural Networks(ANN))技术，建立了可靠、高效的设计方法。需要考虑多学科的大型系统设计，研究后发现采取协作优化策略就很合适。对于悬挂物运载及投放项目，发现利用模拟神经网格技术能有效地模拟悬挂物气动载荷，最终能显著改善投放轨迹预测的精度及模型实验的效率。     

基于GJB289A标准的通用总线数据分析

基于GJB289A总线标准协议,采用先进的数据分析解算算法,对总线记录仪记录的总线数据文件进行分析,系统支持多粒度、多种方式的数据分析和显示功能。系统与ICD采用自动对接,针对不同型号提供统一的分析接口;采用C/S模式的系统结构,既满足多用户同时使用,又满足不同型号同时在线分析,真正实现了系统的通用性。     

联合式航空电子系统全数字仿真设计与实现

针对联合式航电系统原理仿真及教学需求,设计并实现了基于实体座舱并嵌入DCS数字战斗模拟软件的全数字仿真系统。系统可模拟航电系统地面准备、导航、空空、空地模式下的操作控制逻辑和显示画面;实体座舱和数字战斗模拟软件通过多路RS422总线和HDMI接口实现信息交互;采用共享内存机制获取飞行状态及航电终端仿真数据作为激励源,模拟航电系统运行过程中各个子系统之间GJB 289A总线的信息流,展示GJB 289A总线通信原理及调度机制。实践证明,系统能有效支撑航空电子综合技术与原理的教学。     

机载嵌入式计算机通用化BIT架构设计技术

设计开发了一种通用化BIT软件架构技术,可应用于机载嵌入式计算机.将BIT软件按照功能分为硬件驱动层、测试算法层、测试配置及控制层、应用接口层等,可极大程度实现不同硬件环境、操作系统环境下,BIT软件的可移植性,还定义了一种操作系统启动前实现硬件BIT检测的方法,可有效提高内存、CPU等硬件资源的故障检测率.     

1553B数据总线接口芯片设计

本文讨论了我们设计的一种符合美国 MIL-STD-1553B 和我国 GJB289-87数据总线标准的总线接口芯片,投片后已获得所要求的功能。该芯片采用全定制设计,约有一万晶体管,芯片面积5.9×6.7mm~2。芯片设计全过程均在我们自己开发的 NPU VLSI CAD 系统上完成的。     

武器外挂模拟器的设计及实现

分析了武器外挂模拟器在航电试验中的必要性;利用工业计算机、接口卡和软件设计技术实现不同类型及数量的导弹、炸弹、火箭弹、航炮等武器接口及发控逻辑的模拟,为外挂武器系统软件投放控制试验提供了一种试验手段.     

航空电子通信系统中MBI模块的测试

1553B多路传输数据总线接口（MBI）模块，能够实现GJB289—87标准和协议操作规程协议，完成通信系统之间的连接，在通信软件的支持下完成各子系统之间的通信。本文叙述了MBI模块的测试功能，使得MBI模块在航空电子系统的应用中，从功能上和性能上的正确性得以保证。     

有翼高超声速再入飞行器气动设计难点问题

有翼高超声速再入飞行器是近年来的研究热点,气动设计是飞行器设计的关键。为了更清楚地认识有翼高超声速再入飞行器气动设计的难点问题,对有翼高超声速再入飞行器的发展、优势及总体任务剖面进行了介绍,从5个方面详细介绍了该类飞行器气动设计的难点问题,包括多约束复杂面对称气动布局设计、高温真实气体效应对气动特性影响、天地差异与天地换算方法、反作用控制系统(RCS)喷流干扰对气动特性的影响以及气动数据不确定度等,简要阐明了这些难点问题对总体设计的重要性以及初步的解决思路,为有翼高超声速再入飞行器气动设计提供了一些参考。     

Simulation and Analysis of Crashworthiness of Fuel Tank for Helicopters

Crashworthiness requirement of fuel tanks is one of the important requirements in helicopter designs. The relations among the protection frame, textile layer and rubber layer of the fuel tank are introduced. Two appropriate FE models are established, one is for an uncovered helicopter fuel tank without protection frame, and the other is for fuel tank with protection frame. The dynamic responses of the two types of fuel tanks impinging on the ground with velocities of 17.3 m/s are numerically simulated for the purpose of analyzing energy-absorbing capabilities of the textile layer and protection frame. The feasibility of the current crashworthiness design of the fuel tank is examined though comparing the dynamic response behaviors of the two fuel tanks.     

The effect of inlet conditions on the flow and heat transfer in multiple rotating cavity with axial throughflow

This paper discusses experimental results from two different build configurations of a heated multiple rotating cavity test rig.Measurements of heat transfer from the discs and tangential velocities are presented.The test rig is a 70% full scale version of a high pressure compressor stack of an axial gas turbine engine.Of particular interest are the internal cylindrical cavities formed by adjacent discs and the interaction of these with a central axial throughflow of cooling air.Tests were carried out for a range of non-dimensional parameters representative of high pressure compressor internal air system flows(Re up to 5×106 and Rez up to 2×105).Two different builds have been tested.The most significant difference between these two build configurations is the size of the annular gap between the(non-rotating) drive shaft and the bores of the discs.The heat transfer data were obtained from thermocouple measurements of surface temperature and a conduction solution method.The velocity measurements were made using a two component,LDA system.The heat transfer results from the discs show differences between the two builds.This is attributed to the wider annular gap allowing more of the throughflow to penetrate into the cavity.There are also significant differences between the radial distributions of tangential velocity in the two builds of the test rig.For the narrow annular gap,there is an increase of non-dimensional tangential velocity V/Ωr with radial location to solid body rotation V/Ωr=1.For the wider annular gap,the non-dimensional velocities show a decrease with radial location to solid body rotation.      

突破技术趋同，波音再现竞争优势

 波音公司面临着来自空客公司的巨大挑战,企业战略性创新才是公司成功的关键。为此波音公司的全部战略性研究集中在扩大产品的差异性上,体现在3个方面：电子化（e-Enabled）运营环境、整体复合材料机身部件的制造技术和支持波音787客机的全球协同环境（GCE）。     

临近空间飞行器测控与信息传输系统频段选择

 临近空间飞行器是高性能信息化武器平台,测控（TT&;C）与信息传输系统是其信息保障的核心,而选择合理、可行的频段是展开系统设计的前提和基础。频段选择影响到整个技术方案的制定,是一个需综合考虑、影响深远并具有战略意义的关键问题,从国际电联（ITU）国际标准、高速数传、接收信噪比（SNR）、“三抗”、超视距中继、黑障、雨衰以及设备研制成熟度8个方面全面、细致论证了近空间平台测控系统的频段选择问题,最终得出在视距链路中以Ka频段为宜,在超视距链路中以Ku/Ka双频段为宜的结论。     

基于弯曲激波压缩系统的高超声速进气道反设计研究进展

总结了近十年来弯曲激波压缩研究的主要成果。提出了弯曲激波压缩系统的新概念,即利用特殊设计的楔形弯曲压缩面或空间弯曲压缩面,产生一系列与前缘弱激波相互交汇或叠加的压缩波系,从而使前缘激波弯曲,形成特殊的弯曲激波,它与波后的等熵压缩波来共同完成对气流的压缩。在此基础上,实现了由给定出口气动参数的超声速内流道反设计,实现了由给定压缩面压力分布和给定压缩面马赫数分布要求的型面反设计,实现了由给定激波波面的压缩型面反设计。研究证明,弯曲压缩面-弯曲激波压缩系统具有良好的综合气动性能,为高性能高超声速进气系统的气动设计提供了一种全新的设计方法。     

Experimental Study on Effects of Fuel Injection on Scramjet Combustor Performance

In order to investigate the effects of fuel injection distribution on the scramjet combustor performance, there are conducted three sets of test on a hydrocarbon fueled direct-connect scramjet test facility. The results of Test A, whose fuel injection is carried out with injectors located on the top-wall and the bottom-wall, show that the fuel injection with an appropriate close-front and centralized distribution would be of much help to optimize combustor performances. The results of Test B, whose fuel injection is performed at the optimal injection locations found in Test A, with a given equivalence ratio and different injection proportions for each injector, show that this injection mode is of little benefit to improve combustor performances. The results of Test C with a circumferential fuel injection distribution displaies the possibility of ameliorating combustor performance. By analyzing the effects of injection location parameters on combustor performances on the base of the data of Test C, it is clear that the injector location has strong coupled influences on combus- tor performances. In addition, an inner-force synthesis specific impulse is used to reduce the errors caused by the disturbance of fuel supply and working state of air heater while assessing combustor performances.     

(高)超声速流动试验技术及研究进展

近年来,与高速飞行器相关的(高)超声速流动受到了极大的关注。这类流动所具有的非定常性、强梯度和可压缩性对试验方法和风洞设计技术提出了挑战。超声速纳米示踪平面激光散射(NPLS)技术是由作者所在团队研发的非接触光学测试技术。它能够以较高的空间分辨率来揭示超声速三维流场的一个瞬态剖面的时间解析的流动结构。介绍了NPLS技术以及基于NPLS开发的密度场测量、雷诺应力测量和气动光学波前测量等方法,并回顾了这些技术在超声速边界层、超声速混合层、超声速压缩拐角、激波/边界层相互作用和光学头罩绕流等流动中的应用,清晰地再现了边界层、混合层、激波等典型流场结构及其时空演化特性。另外,为了模拟和研究高空大气条件下边界层自然转捩和超声速混合层的转捩特性,介绍了高超声速静风洞、超-超混合层风洞的设计技术以及层流化喷管的设计方法。     

Research on Auto-detection for Remainder Particles of Aerospace Relay Based on Wavelet Analysis

Aerospace relay is one kind of electronic components which is used widely in national defense system and aerospace system. The existence of remainder particles induces the reliability declining, which has become a severe problem in the development of aerospace relay. Traditional particle impact noise detection (PIND) method for remainder detection is ineffective for small particles, due to its low precision and involvement of subjective factors. An auto-detection method for PIND output signals is proposed in this paper, which is based on direct wavelet de-noising (DWD), cross-correlation analysis (CCA) and homo-filtering (HF), the method enhances the affectiv-ity of PIND test about the small particles. In the end, some practical PIND output signals are analysed, and the validity of this new method is proved.