飞机座舱空气调节分系统测试仪设计

分析了飞机座舱空气调节分系统功能和性能测试需求,设计出由单片机、带RS485总线的工控仪表和程控电阻模块等构成的测试仪,实现对被测对象电源、增／减压电阻和阀门动作时间等重要指标的检测。实际应用表明,测试仪测试指标精确、操作使用简便、性能稳定可靠,能够很好满足空气调节分系统的测试需求。     

基于某型航牢发动机的综合控制系统试验平台设计

针对多数半物理仿真试验平台系统的结构简单、功能单一、无法模拟控制系统在发动机上真实工作的情况,设计了基于真实外部管路的控制系统综合半物理试验平台,对试验平台的重要环节进行了建模和仿真分析,并进行调试试验。测试结果表明:半物理仿真试验平台可满足控制系统综合试验的性能调试、功能验证和故障复现等要求,对某型航空发动机控制系统的研制具有重要指导意义。     

HB-3000型布氏硬度计换向系统的改造

介绍了ＨＢ－３０００型布氏硬度计换向系统的改造方法及改造后硬度计的工作程序，并就改进效果进行了论述。     

机上电缆无线测试仪设计

在分析目前机上电缆传统测试方法所存在弊端的基础上,提出了机上电缆无线测试仪的硬件设计方法;描述了关键的电缆连接关系测量方法及其电路实现方法;根据测试仪软件的需要,构建了电缆连接信息数据结构。实际样机对多芯电缆的测试结果表明,测试仪可以很好地满足机上电缆的测试需要。     

基于IEEE1149．1标准的通用测试机的设计与实现

针对板级或系统级电路的测试问题,本文提出了一种基于IEEE1149．1标准的通用测试机的设计方案,从而实现了对被测电路的在线和离线测试。此外,由于DSP、FPGA等嵌入式技术的使用,使整个系统具有体积小、功耗低、通用性好和便于嵌入到被测电路板等特点。     

固体燃料冲压发动机连管试验器设计方案探讨

分析了虚拟固体燃料冲压发动机连管试验的基础技术,归纳了其试验器方案设计任务。重点探讨了连管试验器各部件的设计方案。     

航空发动机涡轮机匣轮盘包容性研究

为研究某航空发动机辅助动力装置涡轮盘在预定转速范围内破裂后涡轮机匣的包容能力,在高速旋转试验器上进行了涡轮机匣的包容性试验.试验采用轮盘周向3个对称位置预制裂纹的方式,使轮盘在预定转速范围内破裂成均匀3块,得到了轮盘碎块撞击涡轮机匣的高速摄影照片.试验结果表明轮盘碎块击穿机匣撞击包容环,包容环发生大塑性变形,包住轮盘碎块.采用LS-DYNA软件对涡轮机匣包容性进行数值仿真,仿真结果与试验结果吻合良好,研究结果对航空发动机轮盘包容性设计有一定的参考价值.      

An approach to radiated testing of installed airborne Doppler radarwith weather/windshear detection capability

Numerous documents were reviewed to verify radar parameters needed to analyze and present the tester concept described herein. The weather and windshear models defined use the identical criteria established for the Doppler radar in terms of F-factor. The basic concept of the tester is to transmit coherent simulated radar returns in response to the airborne radar's transmission while mounted on a tripod in the far field of the radar when parked on the ramp. The varying amplitude of the received radar pulses are analyzed and put into memory as the tester antenna is illuminated by the scanning main beam and side lobes of the radar's antenna patterns. The tester controls the power of its outputted simulated radar returns in inverse relation to the power of the received radar pulses. These simulated radar returns, outputted into the main beam and/or side lobes of the scanning radar antenna, are interpreted by the radar system as received in the main lobe. The tester transmissions, incorporating microburst, storm and gust front models, previously defined, can thereby test the aircraft radar system performance in various hazard environments. The tester is designed to: verify operational performance of the radar; demonstrate installed radar performance; verify crew reports and minimize radar or LRU's removal for maintenance; test before and after a repair; and verify radome effects on radar performance     

飞机碱性电瓶释压阀压力测试仪的研制

根据飞机维护手册中对碱性电瓶释压阀压力的测试要求,研制成功了一台专用释压阀压力测试仪。讨论了该测试仪的基本机构,气压的产生和压力信号的采集,信号放大器和报警电路的设计方法。     

韦氏硬度计算公式分析及铝合金标准韦氏硬度块设计

研制数字式铝合金韦氏硬度计,必须依据正确的韦氏硬度计算公式,并采用适合的铝合金韦氏标准硬度块进行校准与标定。本文依据实验结果指出了目前使用的韦氏硬度计算公式和铝合金韦氏标准硬度块存在的差错和缺陷,提出了新的韦氏硬度计算公式,并设计和制造了新的铝合金韦氏标准硬度块。以上成果已经成功应用于数字式铝合金韦氏硬度计的研制。     

基于通用电路测试仪的专用总线电路模件测试维修平台

针对专用总线电路板模件,利用一种通用电路测试仪,设计了一个专用总线电路模件测试维修平台。     

涡轮动力装置闭环仿真试验器的设计与应用

针对涡轮动力装置电子控制器的控制逻辑检测和调试问题,本文提出了一种采用电子仿真试验器替代真实涡轮动力装置的方法。将电子仿真试验器与电子控制器构成闭环控制同路,从而实现对涡轮动力装置闭环运行过程的模拟。仿真试验表明,利用该电子闭环仿真试验器能较好地模拟涡轮动力装置系统的实际工况,为涡轮动力装置电子控制器的调试和检测提供了‘种简便、有效的途径,且能显著降低试验成本和危险性。     

立式轮盘变幅循环旋转试验器

为了较精确地预示轮盘低循环疲劳寿命,我们将轮盘超转、破裂试验器改造成应用微机自动控制的变幅循环旋转试验器,成功地完成了一个轮盘的变幅低循环疲劳旋转试验,给出了轮盘幅板偏心孔的裂纹起始寿命和扩展寿命。      

航空发动机单管燃烧室试验器测控系统设计

为满足新型燃烧试验需求,针对航空发动机燃烧室试验中单管试验器的特点,提出并设计了1种基于以太网的分布式测控系统。详细阐述了该系统的总体设计方案,分别从软件和硬件两方面研究分析了该系统的详细设计过程,并对其进行了测量不确定度分析。目前该系统已经完成试验前调试,并已顺利完成了多项单管燃烧室燃烧试验任务。结果表明:该系统可靠性高、稳定性良好、通用性强,满足试验器测控需求,具有较高的工程应用价值。     

新一代轻合金车轮试验设备

轻合金整体轮是摩托车上的重要安全部件，必须经过强度性能耐久性能试验，合格后才能使用。     

基于AD598模块的圆度仪数字化改造

以Talyrond 73型圆度仪为例,详细介绍了基于AD598模块的圆度仪数字化改造方法.测试结果表明改造后的仪器在保持原有精度的前提下,实现了检测过程的自动化、数字化及可视化.     

钛合金表面镍包石墨喷涂层的耐磨性能

为了提高钛合金的表面耐磨性,利用氧乙炔热喷涂枪,在TC4合金表面上制备出镍包石墨涂层。采用MXP-2000型销盘式摩擦磨损实验机,进行钛合金及其镍包石墨涂层的干摩擦磨损实验,并利用扫描电镜对磨损表面进行观察和分析。实验结果发现,镍包石墨涂层的摩擦系数只有钛合金的一半左右,前者磨损量为后者的1/6,说明镍包石墨涂层可以大大提高钛合金的表面耐磨性能。TC4合金的磨损机制以黏着磨损为主,喷涂层的磨损机制以磨粒磨损为主,喷涂层中的石墨润滑相是其耐磨性高的主要原因。     

Containment ability and groove depth design of U type protection ring

High-energy rotor uncontained failure can cause catastrophic damage effects to aircraft systems if not addressed in design. In this paper, numerical simulations of three high-energy rotor disk fragments impacting on U type protection rings are carried out using LS-DYNA. Protection rings with the same mass and different groove depths are designed to study the influence of the groove depth. Simulation results including kinetic energy and impact force variation of single fragment are presented. It shows that the groove depth infects both the axial containment ability of the protection ring and the transfer process of energy. The depth of groove ought to be controlled to an appropriate value to meet both the requirement of axial containment and higher safety factor. Verification test on high-speed spin tester has been conducted and shows that protection ring with appropriate U structure can resist the impact of the disk burst fragments. The ring is inflated from a circular to an oval-triangle shape. The corresponding simulation shows good agreement with the test.     

航空电瓶温度传感器校验仪的研制

提出了将半导体制冷制热技术用于航空电瓶温度传感器校验的新设想。采用单片机技术并通过运用模糊-PID控制方法实现校验过程中的恒温控制。实验结果表明,该校验仪能够全自动地检测出电瓶温度传感器在各恒温点的动作情况,并且具有较高的温度检测精度和稳定性。     

Containment of soft wall casing wrapped with Kevlar fabric

Aramid fabrics have been commonly used in the civil turbofan engine fan blade containment system for its excellent performance. To investigate the behavior and capability of soft wall containment casing, a series of fan blade released tests were conducted on the high-speed spin tester.The soft wall casing was fabricated by wrapping multiple layers of Kevlar49 plain woven fabric around a thin steel ring. Casings with different inner metal ring and outer fabric layers number were compared. The method of using the explicit dynamic software LS-DYNA to establish the finite element analysis model for the quantitative analysis of the containment process was developed and conducted. The simulation results are in good agreement with the test results. It is shown that the containment process of the soft wall casing can be divided into three impact stages. The casing with low-stiffness inner metal ring will get severe overall deformation and lose the structural integrity when it suffers the blade impact. Kevlar fabric layers will appear large bulge on outside surface and absorb the most impact dynamic energy of the high speed released fan blade. By summing up the results of the test and simulation, an empirical critical equation was derived to describe the relationship between the released blade dynamic energy and the Kevlar fabric thickness.