三角机翼的热应力计算

本文根据В.И.Фигуровский方法, 给出了计算具有对称剖面的三角形机翼在任意温度分布下的热应力的公式。在本文中, 将Φигуровский方法加以发展, 以包括温度的效应。为了使所得的线性联立方程能具备更佳的求解条件并加快级数的收敛性, 作者将Фигуровскийй所提出的冪级数的形式作了一些改进。计算结果表明, 文中提出的新的级数形式是有成效的。给出了具有对称翼剖面的双梁三角形机翼 (蒙皮腹板均承受正应力) 在不均匀温度分布作用下的热应力计算的数值例题; 计算结果说明沿厚度方向温度分布不均匀的效应并不如预期的那么严重。     

直升机/涡轴发动机综合系统鲁棒抗扰控制设计

提出了一种直升机/涡轴发动机综合系统鲁棒抗扰控制方法。分别设计了基于线性矩阵不等式(LMI)的鲁棒保性能控制的直升机四通道多变量控制器和涡轴发动机转速控制器;为了进一步提高发动机自由涡轮转速环的抗扰能力,结合自抗扰控制(ADRC)方法,构建了涡轴发动机转速鲁棒保性能控制+扭矩ADRC补偿的控制方案,充分利用了ADRC控制强的干扰补偿能力,避免了鲁棒设计方法的保守性。在UH-60直升机/涡轴发动机综合模型仿真环境下通过模拟直升机大幅急速升降操作,验证了直升机/涡轴发动机综合系统所采用的鲁棒抗扰控制,尤其是涡轴发动机鲁棒自抗扰控制,具有理想的抗扰控制效果,能够抑制直升机机动操作过程中大的扭矩扰动对涡轴发动机造成的不利影响,从而使直升机具有更好的机动能力。     

Random signal radar - a winner in both the military and civilian operating environments

Besides some general requirements, modern military radars should possess excellent LPI (low probability of intercept) properties. And civilian radars should satisfy the rigorous requirement of EMC (electro-magnetic compatibility) performance. The special features of random signal radar are analyzed here based on the different requirements for military and civilian use. Results show that random signal radar has excellent LPI property and EMC performance simultaneously, which can satisfy both military and civilian requirements.     

基于X射线脉冲星的深空探测自主导航方法

自主导航是实现深空探测任务的关键技术,基于X射线脉冲星的导航方法可靠、稳定、精度高,不受近地空间的限制,为深空自主导航提供了全新的思路。文章分析了X射线脉冲星导航的基本原理,提出了脉冲到达时间预报算法和整周模糊度求解方法,基于最小二乘理论研究了位置估计算法。仿真算例表明该方法在脉冲星方位误差为0.001弧秒、脉冲到达时间测量误差为1μs的情况下,140d飞行时间中定位精度优于10km,且对初始误差不敏感,可以满足深空探测的导航需要。     

Ultra-lightweight space power from hybrid thin-film solar cells

The development of hybrid inorganic/organic thin-film solar cells on flexible, lightweight, space-qualified, durable substrates provides an attractive solution for space power generation with high mass specific power (W/kg). The high-volume, low-cost fabrication potential of organic cells will allow for square miles of solar cell production at one-tenth the cost of conventional inorganic materials. Plastic solar cells take a minimum of storage space and can be inflated or unrolled for deployment. We explore a cross-section of NASA in-house and sponsored research efforts that aim to provide new hybrid technologies that include both inorganic and polymer materials as active and substrate materials. For NASA applications, any solar cell or array technology must not only meet weight and AMO efficiency goals, but also must be durable enough to survive launch and space environments. Also, balance of system technologies must be developed to take advantage of ultra-lightweight solar arrays in power generation systems.     

Layer-oriented Element Integration Algorithm of Conformal Perfectly Matched Layer

As an efficient artificial truncating boundary condition, conformal perfectly matched layer (CPML) is a kind of multilayer anisotropic absorbing media. To reduce computing effort of CPML, this article proposes a layer-oriented element integration algorithm. In this algorithm, the relative dielectric constant and permeability are considered as constants for each the very thin monolayer of CPML, and the element integration of multilayer along the normal direction is substituted by the element integration of monolayer. The CPML is divided into multilayer elements, whose element matrixes are evaluated by monolayer integration. Numerical examples show that the layer-oriented element integration algorithm is reliable and the CPML formed with this algorithm possesses high-efficient absorbing performance.     

发动机全面性能诊断的随机搜索模型

提出了求解发动机亚定故障方程组整体优化解的随机搜索模型。该数学模型可以在同时发生的故障模式的数目小于、等于、特别是大于测量参数个数的各种复杂情况下给出全面的故障诊断信息。以JT9D发动机全面性能诊断问题为例,利用随机模拟样本对随机搜索模型的诊断有效性进行了评估,并且利用JT9D发动机的24个实际故障样本对随机搜索模型进行了检验。研究结果表明,利用4个测量参数可以对发动机主要部件同时发生的6～10个故障进行诊断。诊断有效性指标可达0.89～0.94.     

基于子空间法的小型直升机飞行力学模型辨识

研究了直升机飞行力学模型辨识方法。首次将状态子空间系统辨识法应用于直升机飞行力学模型的辨识,并对其进行了改进。通过辨识成功地得到了悬停状态下小型直升机的高阶飞行力学模型,并进行了算例直升机仿真验证。结果表明,状态子空间法辨识具有良好的鲁棒性,不会出现经典辨识算法寻优过程中出现的局部极小现象,以及迭代带来的收敛性问题,对于辨识直升机飞行力学模型是非常适用和有效的。