ARINC659总线在IMA架构中的适用性分析

综合模块化航电系统在飞机航电设备的研制中逐渐得到应用,实现综合化模块化航电的一个关键技术是系统内部总线的选择,通过论述综合模块化航电系统对系统内部总线的要求、介绍ARINC659总线的特点,分析ARINC659总线在综合模块化航电系统中的适用性,可以得出ARINC659总线能够满足综合模块化航电系统的要求,目前ARINC659总线已经开始广泛应用于综合模块化航电系统中.     

大型飞机航电系统总线研究

介绍了大型飞机航电系统采用的总线构型,ARINC429总线和AFDX总线的原理、特点和相关技术,并在此基础上提出了相应的实现方案,可作为航电系统及其检测设备的研制参考.     

基于AFDX网络的SNMP协议实现

航空全双工交换式以太网(AFDX/ARINC664)是适用于航电系统信息传输的确定性飞机数据网路总线系统,目前广泛应用于各个机型的航电系统中。由于AFDX网络的确定性,需要对该网络的消息传输、故障检查等项目进行实时的监控管理,以维护该网络系统的正常运行。本文阐述了在某型直升机综合任务处理系统的开发过程中,使用简单网络管理协议(SNMP)对AFDX网络中各个设备的数据信息进行网络管理的设计与实现。     

基于USB转ARINC429总线传感器测试系统的设计

采用FPGA设计了USB转ARINC429总线数据转换板,通过该板卡搭建便携式传感器测试系统,可以实时地将传感器采集数据通过USB总线上传给上位机软件存储、分析、显示;同时,可使用该系统进行传感器环境试验、机上功能的检查和测试使用.     

两栖飞机航电与机电交联自动化检测系统的开发

本文论述了一种模拟飞机压力、温度、转速、角度等多路多种传感器信号的控制输出与实时显示给航电系统用于交联检测,并通过ARINC 429总线进行信号回采与解析,实施闭环半实物仿真的检测系统。分析了系统构成及使用虚拟仪器技术作为软件开发平台,该系统现已应用于大型水陆两栖飞机的交联测试,极大提高了测试效率和准确性。     

ARINC429测试系统设计与总线数据描述方法研究

数据总线作为航空电子系统各子系统间数据传输通道,为航空、航天技术领域的通信、导航等方面带来了巨大的变革,它已作为现代航空电子系统的重要组成部分,并以其高速和高可靠性,必将成为民用和军用飞机智能化发展的主流,先进的ARJ21航电系统大量采用了ARINC429标准.本文阐述了ARINC429总线测试分析系统的组成、应用、软件设计和总线数据描述方法.     

基于ARINC 825总线的测试系统终端设计与实现

针对目前航空总线arinc825的总线完整性问题,设计了测试终端系统;方案采用模块化设计,详细叙述了系统的软件设计。系统实现了数据监听、数据发送、数据解析、数据记录、数据分析、数据过滤、数据显示等功能,可最大程度满足航空电子系统的测试需求;可实时查看总线数据情况,方便实时监控飞机航电总线数据以及机载测试系统故障排查。实验结果表明,该航空总线测试终端系统稳定性好、可靠性高、使用便捷,满足设计需求。     

飞机MIL-STD-1553B总线的测试系统

从MIL -STD - 1 5 5 3B总线在综合航电系统的作用入手 ,分析了国内外总线测试系统的功能和特点 ,并针对将来飞机航电系统设计及发展的方向 ,提出了一种新型的MIL -STD - 1 5 5 3B总线测试系统的设计思想     

ARINC 629总线实际应用及排故分析

ARINC 629总线是航空电子系统中最常见的通信总线之一,广泛应用于波音等飞机上,本文主要介绍了ARINC 629总线与飞机系统之间的交联,并结合实际工作经验就几个常见的ARINC 629总线故障进行分析。     

飞机导航数据仿真系统设计

某型航空相机系统为了清晰地获取目标图像,需要机载导航设备实时提供飞机的姿态和运动信息。某型相机飞机导航数据仿真系统提供了相机需要的ARINC429总线及ARINC407总线数据,满足相机研制和调试的要求。试验证明,系统运行稳定,数据接收准确,可靠性高。     

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.     

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）。     

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.      

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.