某型飞机法兰盘表面缺陷的无损检测方法

法兰盘是飞机着陆装置的关键部件,采用超声表面波检测技术对其进行检测,并分析了试验的影响因素,给出了法兰盘的超声表面波检测方法,同时采用磁轭法进行了复检验证。经应用表明,超声表面波法对于法兰盘的检测具有较大的优势。     

用于热密封组件的编织弹簧弹性性能分析

针对耐高温动态热密封组件中的常用元件弹性支架编织弹簧,研究了其压缩率、装配方式、热暴露温度等参数对其弹性性能的影响,并讨论了编织弹簧高温弹性失效的原因。研究结果表明,合金的氧化是编织弹簧高温回弹率降低的主要原因,在温度低于800℃、压缩率小于50%的服役条件下,编织弹簧的回弹率不小于95%,在航天热密封领域有广阔的应用前景。     

基于PIC的航空电源相序检测器的设计

在不改变连接设备原有硬件的情况下,采用单片机PIC12F675为控制核心,设计了一套具有保护和故障指示功能的115V/400Hz航空三相交流电源相序检测器,分析了电路的结构组成以及工作原理,给出了相应的软件流程,同时在multi-sim11.0中建立相应的仿真模型进行仿真验证。     

Adaptive trajectory generation based on real-time estimated parameters for impaired aircraft landing

ABSTRACT

This paper is motivated by a need to address the challenge of securing a safe landing after suffering from inflight impairment. In this paper, a new adaptive generalised model predictive static programming (G-MPSP) is developed to generate a safe emergency landing trajectory for impaired aircraft. Utilising the computationally efficient G-MPSP framework, the proposed algorithm enables adaptation of model parameters based on the prediction errors to ensure reasonable guidance performance. Based on the estimated parameters, a feasible landing trajectory is then generated by the flexible finite-horizon G-MPSP with input constraints. The integrated approach features explicit closed-form solutions for both parameter estimation and trajectory generation. Its effectiveness is demonstrated by simulations in the presence of parameter uncertainties and noises and by comparison studies with the non-adaptive G-MPSP.     

Modeling and control of an airbrake electro‐hydraulic smart actuator

In this paper, an accurate model of an airbrake electro‐hydraulic smart actuator is obtained by physical considerations, and then different control strategies (variable‐gain proportional control, PT₁ control with switching integrator, and second order sub‐optimal sliding mode control) are proposed and analyzed. This application is innovative in the avionic field, and is one of the first attempts to realize a fly‐by‐wire system for airbrakes, oriented to its immediate employment and installation on current aircraft. The project was carried on with the participation of the Italian Ministry of Defense, and was commissioned to MAG, a leading provider of integrated systems and aviation services for aerospace. Copyright © 2011 John Wiley and Sons Asia Pte Ltd and Chinese Automatic Control Society     

飞机电源系统综合实验平台设计与实现

针对军用飞机电源系统种类多,为保证在一种实验平台上实现多种电源装备的实验训练,满足机务维护人员能力培训的要求,研究设计了飞机电源系统综合实验平台。实验平台采用综合化、通用化的设计思路,综合运用计算机测控、虚拟仪器等现代测试技术,可实现飞机主电源系统、二次电源、控制保护类附件的性能测试实验,并具备新型设备的拓展实验能力。通过开展实验教学,证明该实验平台功能完善,性能稳定,设计方案合理,能够满足飞机电源系统通用性实验要求,具有很强的推广应用价值。     

50th Anniversary Article: Seeing Stresses through the Thermoelastic Lens—A Retrospective and Prospective from an Australian Viewpoint

Thermoelastic stress analysis (TSA) has been around for the past 30 years, but to date, it is still a very much underrated and under‐utilised experimental technique. Although there are devoted groups of practitioners in some industries, this technology is not well known within the aerospace sector. In contrast, the Aerospace Division of the Defence Science and Technology Organisation (DSTO) in Australia has been in the forefront of this technology for some time, achieving many pioneering feats. This paper gives a brief introduction to the development of this technology from a historical perspective, then focuses on a number of innovations that have stemmed from DSTO, including the development and application of the world's first focal plane array based TSA system and, more recently, the development of small and robust microbolometer based systems. For the latter, it is shown that despite nominally poorer temperature sensitivities, they make ideal TSA devices and can in some cases outperform their much more expensive photon detector counterparts. Because of this, together with the enormous practical advantages of microbolometers, the future of TSA is shown to be brighter than ever. Specifically, it is argued that such TSA systems can play a major role in the pervasive and persistent surveillance of full scale fatigue testing of aircraft structures. By detecting both design and developing faults early, it can effectively relieve cost and schedule penalties that are often associated with unanticipated failures. To realise this capability, integration of this technology with autonomous systems will be important, and some preliminary but promising results from a technology demonstrator program are presented.     

载机偏航运动对大视场红外扫描装置成像质量影响的仿真分析

某航空大视场红外扫描装置采用TDI-CCD 探测器、以整机摆扫工作方式扫描成像,由于扫描装置为滚动-俯仰结构的两轴稳定平台,对偏航扰动没有稳定作用,其成像质量易受载机偏航运动的影响.通过运动学分析方法建立扫描装置的视轴运动方程及视轴旋转约束条件,得出不影响成像质量的载机偏航运动范围.在载机实际飞行数据输入条件下进行仿真验证,当载机直线飞行时,其偏航运动不影响成像质量.飞行试验验证表明:摆扫扫描图像清晰,航空大视场扫描装置具有良好的载机偏航运动适应性.     

蒙皮反射的背景辐射对亚声速飞机红外特征的影响研究(一):方法

基于CFD计算得到的流场、温度场结果和Modtran计算得到了环境辐射数据,建立了典型背景下的飞行器红外辐射特征计算模型。计算中考虑了波段、季节、发射率和双向反射函数等因素。通过地面试验数据,对计算方法进行了验证,计算值与试验数据吻合较好。该模型为更准确地分析飞行器的红外辐射特征,以及更合理地评价红外抑制措施的抑制效果提供了方法和工具。     

飞机强度试验舵面偏角测量方法的研究

为满足飞机结构强度试验中舵面偏角测量的要求,提出了一种基于位移测量的舵面偏角测量方法。该方法通过安装于舵面悬挂支臂上的两个拉线式位移传感器,测量相对于舵面悬挂接头上同一个测量点的位移,利用三角公式进行计算,得到舵面的偏转角度。对比验证试验表明,该方法的测量性能指标满足飞机结构强度试验要求,解决了传统利用倾角传感器无法测量方向舵偏角的难题,提高了试验数据采集的效率。