自动控制故障注入设备的设计与实现

 设计实现了一种自动控制故障注入设备,给出了设备的结构框图和主要模块的功能框图。阐述了该设备在设计上具有的通用性、可扩展性、无破坏性和易操作性等特点,以及对应的设计措施。利用该设备进行了故障注入试验,给出了典型故障注入的信号波形,验证了故障注入设备的可用性和效果。     

1台微型三角转子发动机的研制与试验研究

介绍了微型三角转子发动机的研制及其在试验台架上的性能测试。在转速为7800 r/m in时,其输出功率可达220W;通过燃料的对比试验得知,在航模燃料(甲醇为主)中添加一定量的柴油,在基本保证动力性的同时,其经济性有一定改善。     

气固两相喷嘴平面叶栅能量损失的试验研究

通过对气固两相压气机平面叶栅后,沿栅距和叶高分布的气流压力和速度的测量与分析,研究了气固两相流流经压气机平面叶栅时的速度系数和能量损失系数随粒子浓度和攻角改变而变化的规律。试验是在攻角i=-10°、0°气流速度c=10m/s及粒子质量浓度α=0％、2.0％和2.7％的工况下进行的。结果表明:气固两相流流经压气机平面叶栅时能量损失比单相纯气流的大;而且随着粒子浓度和攻角增大,两者的差别也愈大。     

基于分布估计算法的翼型稳健设计(英文)

A transonic airfoil designed by means of classical point-optimization may result in its dramatically inferior performance under off-design conditions. To overcome this shortcoming, robust design is proposed to find out the optimal profile of an airfoil to maintain its performance in an uncertain environment. The robust airfoil optimization is aimed to minimize mean values and variances of drag coefficients while satisfying the lift and thickness constraints over a range of Mach numbers. A multi-objective estimation of distribution algorithm is applied to the robust airfoil optimization on the base of the RAE2822 benchmark airfoil. The shape of the airfoil is obtained through superposing ten Hick-Henne shape functions upon the benchmark airfoil. A set of design points is selected according to a uniform design table for aerodynamic evaluation. A Kriging model of drag coefficient is constructed with those points to reduce computing costs. Over the Mach range from 0.7 to 0.8, the airfoil generated by the robust optimization has a configuration characterized by supercritical airfoil with low drag coefficients. The small fluctuation in its drag coefficients means that the performance of the robust airfoil is insensitive to variation of Mach number.     

GB／HDPE复合材料的拉伸性能及其影响因素

通过ＧＢ／ＨＤＰＥ的拉伸实验和断口形貌分析, 研究了颗粒体积分数、拉伸速率、界面强度对ＧＢ／ＨＤＰＥ复合材料力学性能的影响。研究表明：当填料表面处理方式适当时,ＧＢ／ＨＤＰＥ的拉伸强度和杨氏模量均随颗粒体积分数的增加、拉伸速率的提高、界面粘结强度的增强而提高。     

单载机相位差无源定位系统可观测性分析(英文)

With a pair of antennas spaced apart, an airborne passive location system measures phase differences of emitting signals. Regarded as cyclic ambiguities, the moduli of the measurements traditionally are resolved by adding more antenna elements. This paper models the cyclic ambiguity as a component of the system state, of which the observability is analyzed and compared to that of the bear- ings-only passive location system. It is shown that the necessary and sufficient observability condition for the bearings-only passive location system is only the necessary observability condition for the passive location system with phase difference measurements, and that when the system state is observable, the cyclic ambiguities can be estimated by accumulating the phase difference measurements, thereby making the observer able to locate the emitter with high-precision.     

马尔可夫分析在系统安全性评估中的应用研究

安全性分析是适航符合性验证的重要方法。对马尔可夫分析在系统安全性评估中的应用进行了深入研究,阐明了马尔可夫分析的作用与应用时机,结合功能危险状态“V1速度后起落架无指令收起”分别给出了在初步系统安全性评估与系统安全性评估中进行马尔可夫分析的一般方法,将马尔可夫分析与故障树分析的结论进行了对比,袁明了本文方法的适用性。     

国产民用飞机系统和成品的维修改革

 本文简要分析了国产民用飞机维修现状,根据国内外民航部门的先进维修经验提出了国产民用飞机系统和成品（以下简称民用飞机产品）的维修改革方案。     

几何非线性样条单元

 <正>结构的有限变形与稳定性分析具有重要意义。有限元法的应用,促进了几何非线性研究工作的开展。本文在线性样条单元C’〕的基础上提出一种几何非线性样条板壳单元,壳体的应变位移关系采用Von一K巨rmon方案,以分片样条Hermite插值构造单元的位移模式。对于弱非线性问题,采用修正的Newton一Raphson法解非线性方程组。对于极值点失稳情况,以固定弧长法追踪屈曲路径,并用曲线拟合的方法确定结构的临界载荷值。     

均匀来流下声控机翼分离流动机理研究

介绍均匀来流下声控机翼流动的试验装置、低速大攻角下的声控效果、特征参数的影响,以及附面层中流动参数的变化。文章清楚地展示出声控机翼分离流动的机理。