A hybrid multidimensional Riemann solver to couple self-similar method with MULTV method for complex flows

Since proposed, the self-similarity variables based genuinely multidimensional Riemann solver is attracting more attentions due to its high resolution in multidimensional complex flows. However, it needs numerous logical operations in supersonic cases, which limit the method’s applicability in engineering problems greatly. In order to overcome this defect, a hybrid multidimensional Riemann solver, called HMTHS (Hybrid of MulTv and multidimensional HLL scheme based on Self-similar structures), is proposed. It simulates the strongly interacting zone by adopting the MHLLES (Multidimensional Harten-Lax-van Leer-Eifeldt scheme based on Self-similar structures) scheme at subsonic speeds, which is with a high resolution by considering the second moment in the similarity variables. Also, it adopts the MULTV (Multidimensional Toro and Vasquez) scheme, which is with a high resolution in capturing discontinuities, to simulate the flux at supersonic speeds. Systematic numerical experiments, including both one-dimensional cases and two-dimensional cases, are conducted. One-dimensional moving contact discontinuity case and sod shock tube case suggest that HMTHS can accurately capture one-dimensional expansion waves, shock waves, and linear contact discontinuities. Two-dimensional cases, such as the double Mach reflection case, the supersonic shock / boundary layer interaction case, the hypersonic flow over the cylinder case, and the hypersonic viscous flow over the double-ellipsoid case, indicate that the HMTHS scheme is with a high resolution in simulating multidimensional complex flows. Therefore, it is promising to be widely applied in both scholar and engineering areas.     

全极化微波辐射计模拟复相关器研究

全极化微波辐射计是一种新型的微波遥感器,制约其发展的关键部件是相关器。提出了一种应用在此新系统中的模拟复相关器,其具有灵敏度高,体积小,功耗低等优点。对模拟复相关器进行误差分析,给出减少复相关幅度误差和相位误差的方案。按此方案对模拟复相关器进行了设计、研制。得到了模拟复相关器整体测量结果及全极化微波辐射计噪声测量结果。结果表明采用此模拟复相关器的全极化微波辐射计具有较好的极化测量性能。     

末制导雷达/惯性复合导航算法

研究了末制导雷达/惯导的复合导航算法,当导弹攻击慢速移动目标时,可以根据惯导输出和雷达信息,采用Calson滤波算法估计出目标的位置信息和惯导误差,从而修正目标运动和惯导误差。仿真表明,Calson滤波算法能较好地提高制导精度。     

板和型材均含有裂纹的加筋板应力强度因子计算

本文应用复变应力函数和分区广义变分原理,提出了确定型材和板有裂纹的加筋板应力强度因子的计算方法。采用复变应力函数使裂纹的边界条件精确地得到满足,应用分区广义变分原理使其它边界条件近似地得到满足。本文应用加筋条为角材,其中一根角材含有边缘裂纹,板含有中心裂纹的加筋板,在垂直裂纹平面的远处受均匀拉伸载荷为例,给出了应力强度因子的计算公式。对一特定的结构参数,给出了应力强度因子随裂纹长度变化曲线。     

基于观测器的上面级姿控发动机时间滞后补偿控制方法

针对上面级姿控发动机响应延迟导致姿态角速度控制精度下降的问题,建立了系统动力学模型,分析姿控发动机响应延迟对姿态控制的影响,采用Smith预估补偿算法提高系统控制精度,对于理论模型的不确定性,采用鲁棒观测器对姿态发动机输出进行估计。仿真结果表明:所提出的方法可有效减小姿控发动机响应延迟对控制精度的影响,为上面级长期在轨高精度飞行提供技术支撑。     

提高地形图测绘精度与速度方法探讨

通过对地形图重要性的简要描述,提出了在实际测绘工作中比较实用的几种简便而迅速的测绘方法。它们对提高地形图测绘的精度及速度有很好的效果。     

某型飞机进气道斜板加载测控系统的研究

在飞机进气道斜板位置控制系统的地面试验过程中,需要模拟实际飞行状态中斜板所受到的气动载荷谱。     

Performance evaluation of complex systems using evidential reasoning approach with uncertain parameters

The composition of the modern aerospace system becomes more and more complex. The performance degradation of any device in the system may cause it difficult for the whole system to keep normal working states. Therefore, it is essential to evaluate the performance of complex aerospace systems. In this paper, the performance evaluation of complex aerospace systems is regarded as a Multi-Attribute Decision Analysis (MADA) problem. Based on the structure and working principle of the system, a new Evidential Reasoning (ER) based approach with uncertain parameters is proposed to construct a nonlinear optimization model to evaluate the system performance. In the model, the interval form is used to express the uncertainty, such as error in testing data and inaccuracy in expert knowledge. In order to analyze the subsystems that have a great impact on the performance of the system, the sensitivity analysis of the evaluation result is carried out, and the corresponding maintenance strategy is proposed. For a type of Inertial Measurement Unit (IMU) used in a rocket, the proposed method is employed to evaluate its performance. Then, the parameter sensitivity of the evaluation result is analyzed, and the main factors affecting the performance of IMU are obtained. Finally, the comparative study shows the effectiveness of the proposed method.     

机场协同决策的应用历史与研究趋势综述

机场协同决策可以有效提升机场的运行效率,进而提升整个民航运输网络的运行效率。本文查阅整理了机场协同决策的相关标准、政策文件与研究论文,梳理了机场协同决策的发展历程以及国内外学界业界有关协同决策的研究及应用现状;分析讨论了机场协同决策未来的发展趋势与当前时期协同决策所面临的挑战;同时基于我国的实际情况,给出了一些机场协同决策的发展建议;总结了机场协同决策的理论与应用价值以及协同决策在我国面临的问题与挑战。本文研究可以为提升机场与整个航空交通网络的运行效率与经济效益提供理论支撑和依据。     

民用飞机后机身壁板控制失效模式和控制载荷工况分析

为了明确载荷对典型民用飞机的后机身加筋壁板结构设计的影响,建立低平尾式飞机后机身的有限元模型,计算分析了壁板的应力应变分布,计算分析了壁板不同区域的控制载荷工况、控制失效模式。通过对比不同失效模式各自所占的比例,证明后机身壁板结构的主要失效模式是屈曲以及最大应变准则。通过对比不同控制载荷工况各自所占的比例,选出后机身壁板结构的主要控制载荷工况。