数据记录仪在航空和航天领域的应用

数据记录仪是一种数据采集记录的产品，应用在一些对实验数据或者环境数据有记录需求的场合。在我国的航空航天等高尖端领域，对于相关产品的试验数据记录需求方面很多。本文作者通过接触到的航空航天领域数据记录的应用作简单的阐述。     

Off-Optimum Cure of Aerospace Epoxy Adhesives

Four epoxy film adhesives used in aircraft manufacture and repair have been examined to establish the effect of deviation from the cure cycle specified by the manufacturer. In addition to the variation of the cure cycle, two surface preparations of the aluminium adherends (chromic acid etch or grit blast followed by silane treatment) were evaluated. Thermal analysis was used to examine the cure envelope of the adhesive, and its extent of cure and glass transition temperature. The adhesive properties were assessed by shear strength (in both single lap joints and in Iosipescu configuration), durability (Boeing wedge test) and chemical resistance to selected aggressive fluids. The sensitivity of the performance of a particular adhesive to offoptimum cure conditions depends on its composition and needs to be determined, not predicted.     

基于混合卡尔曼滤波器组的航空发动机双通道传感器故障检测

基于机载非线性模型与分段线性卡尔曼滤波器混合组成的混合卡尔曼滤波器组,结合双通道传感器的特点,建立了民用航空发动机传感器故障诊断系统;给出故障诊断原理及算法的同时,将该系统应用于民用涡扇发动机传感器常见典型故障进行了仿真;仿真结果表明,诊断系统可以在发动机发生健康蜕化后,通过只简单更新机载模型的蜕化因子,而保持线性卡尔曼滤波器的参数不变,便能准确地检测和隔离各类传感器故障而不发生误报;该更新过程可以在线自动完成,省时省力,易于工程实现。     

Tracking control and robustness analysis for planar vertical takeoff and landing aircraft under bounded feedbacks

We study feedback tracking problems for the planar vertical takeoff and landing (PVTOL) aircraft dynamics, which is a benchmark model in aerospace engineering. We provide a survey of the literature on the model. Then we construct new feedback stabilizers for the PVTOL tracking dynamics. The novelty of our work is in the boundedness of our feedback controllers and their applicability to cases where the velocity measurements may not be available, coupled with the uniform global asymptotic stability and uniform local exponential stability of the closed‐loop tracking dynamics and the input‐to‐state stable performance of the closed‐loop tracking dynamics with respect to actuator errors. Our proofs are based on a new bounded backstepping result. We illustrate our work in a tracking problem along a circle. Copyright © 2011 John Wiley & Sons, Ltd.     

The Effect of Surface Engineering Treatments on the Fatigue Behavior of 2024-T351 Aluminum Alloy

The work examines the effect of controlled shot peening (CSP), laser shock peening (LSP) and ultrasonic impact treatment (UIT) on the fatigue behavior of 2024-T351 aluminum alloy. The testing methodology has been designed to extract information regarding specific products of the treatments and their individual affect on fatigue damage. The work concludes that all three surface treatments improve the fatigue resistance of the material with the LSP covering the areas of safe-life and damage tolerance, the control shot peening can only benefit the area of short crack growth while the UIT proved to benefit both the short and long crack growth.     

AI-Li/SiCp composites and Ti-AI alloy powders and coatings prepared by a plasma spray atomization (PSA) technique

There has been increasing use of Al-Li alloys in the aerospace industry, due mainly to the low density and high elastic modulus of this material. However, the problem of low ductility and fracture toughness of this material has limited its present application to only weight- and stiffness-critical components. Development of Al-Li/ceramic composites is currently being investigated to enhance the service capabilities of this material. The Ti-Al alloy is also of interest to aerospace-type applications, engine components in particular, due to its attractive high-temperature properties. Preparation of fine powders by plasma melting of composite feedstock and coatings formed by plasma spraying was carried out to examine the effect of spray parameters on the microstructure and properties of these materials. Characterization of the powders and coatings was performed using the scanning electron microscope and image analyzer. Examination of the plasma-sprayed powders and coatings has shown that in the Al-Li/SiC composite there is melting of both materials to form a single composite particle. The SiC reinforcement was in the submicron range and contributed to additional strengthening of the composite body, which was formed by a cold isostatic press and consolidated by hot extrusion or hot forging processes. The plasma-sprayed Ti-Al powder showed four categories of microstructures: featureless, dendritic, cellular, and martensite-like.     

高性能PAN基碳纤维及其复合材料在航天领域的应用

对高性能PAN基碳纤维的发展历程、现状以及以其为增强体的复合材料进行了综述,并对高性能PAN基碳纤维增强复合材料在航天领域的主要应用情况进行了介绍,最后对我国高性能碳纤维复合材料的现状及发展重点进行了探讨.     

跨音压气机转子多目标气动优化设计

采用基于雷诺平均N-S方程的全三维流场模拟程序和基于多目标遗传算法的数值优化程序,对跨音压气机转子NASA Rotor37进行了优化设计。对所开发的三维N-S方程求解程序进行了实验验证,完善了多目标遗传算法与响应面方法相结合的具有全局寻优能力的优化程序,以总压比和绝热效率最大为设计目标,应用该优化方法对NASA Rotor37进行考虑中弧线和厚度分布的多目标气动优化设计。结果表明:在满足流量约束的条件下,绝热效率提高了0.7%,总压比提高了0.66%,并且优化设计时间大幅减小。     

航天嵌入式软件整数溢出的形式化验证方法

整数溢出引起的软件系统安全性问题屡见不鲜,已有的模型检测技术由于存在状态空间爆炸、不能有效支持中断驱动型程序检测等缺点而少有工程应用.结合真实案例,对航天嵌入式软件整数溢出问题的分布和特征进行了系统性的分析.在有界模型检测技术的基础上,结合整数溢出特征,提出了基于整数溢出变量依赖的程序模型约简技术;同时,针对中断驱动型程序,结合中断函数特征抽象,提出了基于干扰变量的中断驱动程序顺序化方法.经过基准测试程序和真实航天嵌入式软件实验,结果表明：该方法在保证整数溢出问题检出率的前提下,不仅能够提高分析效率,还使得已有的模型检测技术能够适用于中断驱动型程序整数溢出检测.