Effects of pressure oscillation on aerodynamic characteristics in an aero-engine combustor

The effects of pressure oscillation on aerodynamic characteristics in an aero-engine combustor are investigated. A combustor test rig is designed to simulate the pressure drop characteristics of a practical annular combustor. The pressure drop characteristics are firstly measured under atmosphere condition with non-reacting flow (or cold flow), and the air mass flow proportion of each component (dome/liner) are obtained; these properties are base lines for comparison with combustion state. The combustion tests are then carried out under conditions of inlet temperature 340–450 K, fuel air ratio 0.010–0.028. The stability map and the oscillation frequencies are obtained in the tests, the results show that pressure oscillation amplitude increases with the increase of fuel air ratio. Phase trajectory reconstruction is applied to classify the pressure oscillation motion; there are three motions captured in the tests including: “disk”, “ring” and “cluster”. The pressure drops across the dome under strong pressure oscillation are distinctly divergent from the cold flow, and the changes of pressure drops are mainly affected by pressure oscillation amplitude, but is less influenced by pressure oscillation motion nor oscillation frequencies. Based on the mass flow conservation, the reduction of effective flow area of combustor under strong pressure oscillation is demonstrated. Liner wall temperatures are analyzed through Multiple Linear Regression (MLR) method to estimate the reduction of the air mass flow proportion of the liner cooling under strong pressure oscillation. Finally, the air mass flow proportions of each component under strong pressure oscillation are estimated, the results show that the pressure oscillation motion also has influence on air mass flow proportion.     

一种动目标检测的优化设计及应用

文章提出一种新的动目标检测(MTD)滤波器组设计方法,即信号处理系统分为目标处理通道和气象处理通道;目标通道采用自适应动目标检测(AMTD)处理方式,实时检测杂波的存在,判定杂波强度(如强、中、弱),根据杂波的强度自动产生或选择滤波器加权因子,以期保证对地杂波高度抑制的前提下,尽量减少信噪比损失,提高对弱小目标的检测能力。该方法可提高雷达在杂波环境中的自适应性能,具有一定的实用价值。     

基于PHD未知杂波密度多机动目标跟踪

基于随机有限集（RFS）的跳变马尔可夫系统（JMS）是多机动目标跟踪的有效方法。但现有的方法假设杂波密度是先验已知的,而实际中杂波密度是未知且可能随着环境的改变而变化。针对这一问题,提出了一种适用于线性高斯模型的未知杂波密度下多机动目标跟踪算法。该算法以未知杂波密度高斯混合概率假设密度（λ-GMPHD）滤波为基础建模杂波和真实目标,采用线性高斯JMS模型描述目标机动,推导了未知杂波密度下多机动目标跟踪的GMPHD迭代解析表达式。仿真结果表明,所提算法可实现对于杂波密度以及目标数和目标状态的准确估计。      

基于回归分析的低空空域资源可用性评价方法

低空空域资源一直是通用航空产业发展的瓶颈,是制约我国通用航空发展的关键因素之一。基于理论研究和实地调研,构建低空空域资源可用性评价指标体系,运用多元线性回归法对影响低空资源的军/民航各项因素进行系统分析,确定各级指标权重;以江苏省为例,深入分析该省低空可利用资源的现状,总结各地区实际情况和大量数据,通过多元线性回归结果显示各项因素对该地区的影响值;最后得出低空空域资源可用性结果。结果表明:采用回归分析方法分析低空空域资源,所得结果是科学且有效的,可为我国低空空域资源合理利用以及通用航空活动空域申报提供参考。     

对空间多目标多次接近的轨道设计

基于单航天器对空间多目标单次接近轨道设计的研究结果, 讨论了单航天器对空间 多目标多次接近的轨道设计问题. 提出了接近指标用于设计能多次接近多个空间目标的航天器轨道;以二体接近轨道为基础, 给出了接近轨道解空间的求取方法; 利用三种轨道调整方法构造了三种复杂度不同的新解并产生算子, 分析了它们的解空间和最优解分布, 采用改进的模拟退火算法求解出最优接近轨道. 仿真实验验证了轨道设计算法的正确性.      

高超声速巡航导弹的神经网络虚拟目标微分对策中制导律

针对高超声速巡航导弹的高空巡航飞行段,采用虚拟目标的定义方法,结合微分几何知识以及运动学方程建立了导弹与目标的相对运动模型,并在此基础上视其与虚拟目标之间的运动为单目标微分对策问题。利用哈密尔顿函数求解方法推导了开环微分对策中制导律,同时建立了一种新的闭环微分对策中制导律结构图,并对反向传播神经网络的训练样本进行了设计。通过反向传播神经网络的函数逼近功能实现了高超声速巡航导弹微分对策中制导律的智能化。仿真验证表明了其有效性。     

基于流固耦合方法的柴油机排气管热机疲劳寿命研究

由于高功率大缸径柴油机的排气管处于高温、高压、强冲击的工作环境,承受复杂恶劣的热机载荷,使得疲劳失效问题日渐突出.为解决工程中的排气管疲劳失效故障,基于流固耦合仿真分析的方法,研究了多通排气管在热载荷、机械载荷和热机耦合载荷三种不同条件下的疲劳损伤机理以及低周疲劳寿命.结果表明,单纯交变热载荷不足以造成排气管低周疲劳失...     

A compositional method to model dependent failure behavior based on PoF models

In this paper, a new method is developed to model dependent failure behavior among failure mechanisms. Unlike the existing methods, the developed method models the root cause of the dependency explicitly, so that a deterministic model, rather than a probabilistic one, can be established. Three steps comprise the developed method. First, physics-of-failure(PoF) models are utilized to model each failure mechanism. Then, interactions among failure mechanisms are modeled as a combination of three basic relations, competition, superposition and coupling. This is the reason why the method is referred to as ‘‘compositional method". Finally, the PoF models and the interaction model are combined to develop a deterministic model of the dependent failure behavior. As a demonstration, the method is applied on an actual spool and the developed failure behavior model is validated by a wear test. The result demonstrates that the compositional method is an effective way to model dependent failure behavior.     

交会对接光学成像敏感器中合作目标的分析与设计

交会对接技术是实现太空梭、太空平台和空间运输系统的装配、回收、补给、维修、太空人交换及营救等在轨服务的先决条件,交会对接光学成像敏感器是两航天器交会对接近距离平移靠拢段唯一能够提供六自由度相对导航信息的敏感器,由安装于追踪飞行器上的相机和安装于目标飞行器上的合作目标组成,采用角反射器作为合作目标标志,完成两飞行器间的相对位姿的解算.对其需求分析、设计方案、回光能量测试等进行了讨论,该方案已在神舟十一号载人飞船、天舟一号货运飞船与天宫二号的交会对接任务中成功验证,后续针对空间站及光学舱任务进行适应性修改.     

基于TANA函数的非概率可靠度分析方法

建立一种基于TANA(Two-Point Adaptive Nonlinear Approximation)函数的高效稳定非概率型可靠度分析方法。首先,对随机变量采用凸集合非概率多椭球模型进行描述,在可靠度指标法框架下,采用增强混沌控制(Enhanced Chaos Control,ECC)方法,在逼近最佳设计点时,利用两点自适应非线性逼近的TANA2函数拟合强非线性的功能函数,减少了可靠度分析中功能函数的调用次数,有效提高了算法的效率及稳定性。还对不同非线性程度的功能函数进行了可靠度求解以及优化的算例验证。