基于失效概率的涡轮后机匣全局灵敏度分析

涡轮后机匣是航空发动机安全的关键部件,但是其具有工况复杂、不确定性因素多的缺点。为了探究输入随机变量的不确定性对涡轮后机匣结构失效概率的影响,建立参数化有限元模型进行确定性分析。考虑材料性能、几何参数及外部载荷的不确定性,对涡轮后机匣两种典型失效模式：强度失效以及刚度失效建立极限状态函数;通过构造自适应Kriging 代理模型并结合重要抽样方法评估涡轮后机匣结构失效概率,利用基于失效概率的全局灵敏度方法对涡轮后机匣结构可靠度的不确定性来源进行分析,对各输入随机变量重要性进行排序,构建一种涡轮后机匣全局灵敏度分析框架。结果表明：涡轮后机匣在两种失效模式以及系统失效模式下,发动机推力以及线性膨胀系数对结构失效概率影响最为显著,应对其重点考虑;内外机匣长度以及材料弹性模量对涡轮后机匣结构失效概率影响较小,可对其适当忽略。     

l1-based calibration of POD-Galerkin models of two-dimensional unsteady flows

This paper discusses a physics-informed methodology aimed at reconstructing efficiently the fluid state of a system. Herein, the generation of an accurate reduced order model of two-dimensional unsteady flows from data leverages on sparsity-promoting statistical learning techniques. The cornerstone of the approach is l₁ regularised regression, resulting in sparsely-connected models where only the important quadratic interactions between modes are retained. The original dynamical behaviour is reproduced at low computational costs, as few quadratic interactions need to be evaluated. The approach has two key features. First, interactions are selected systematically as a solution of a convex optimisation problem and no a priori assumptions on the physics of the flow are required. Second, the presence of a regularisation term improves the predictive performance of the original model, generally affected by noise and poor data quality. Test cases are for two-dimensional lid-driven cavity flows, at three values of the Reynolds number for which the motion is chaotic and energy interactions are scattered across the spectrum. It is found that: (A) the sparsification generates models maintaining the original accuracy level but with a lower number of active coefficients; this becomes more pronounced for increasing Reynolds numbers suggesting that extension of these techniques to real-life flow configurations is possible; (B) sparse models maintain a good temporal stability for predictions. The methodology is ready for more complex applications without modifications of the underlying theory, and the integration into a cyber-physical model is feasible.     

“系统工程”辨析

系统工程(Systems Engineering)是成功实现系统的方法,也是应对技术复杂性的有效方法。系统工程从需求出发,综合多种专业技术,通过分析-综合-试验的反复迭代过程,开发出一个满足使用要求、整体性能优化的系统。在国内,对"系统工程"有不同的理解和定义,例如"社会系统工程"、"系统工程学"、"系统工程是工程项目"等概念。航天领域的系统工程(航天系统工程方法)具有如下特点:强调总体设计,遵循研制程序,是反复应用的系统工程过程和定量的方法。     

小卫星瞬态外热流下动态传热特性分析

为揭示小卫星瞬态外热流下的动态传热特性规律,以小卫星双层集总参数模型为研究对象,推导得到动态热平衡方程。类比阻尼振荡系统,采用时频变换和传递函数分析的新思路,对温度与热流波动量间的幅值特性和相位特性变化规律进行理论研究,并利用数值方法进行验证。结果表明:推导获得了小卫星传热系统自然频率和阻尼比的热参数准则式,并证明了小卫星传热系统在热激励下振荡特性为过阻尼。阻尼比和频率比的增大及热流静位移的减小均可降低温度的波动幅度,不同频率比范围下阻尼比对热流的波动量与温度波动量间的相位差的影响呈相反规律,数值结果与解析分析结果一致。可为低热惯性小卫星的热控优化设计提供理论参考。     

一种主动液压滤波器的理论分析

针对目前被动式液压滤波器所存在的问题,提出了主动控制式滤波的概念.在简要介绍其工作原理的基础上,对一种由双蓄能器-压电晶体(PZT)驱动的静平衡可变容腔液压主动滤波器进行了理论分析,弄清了其滤波机理.为了正确描述泵-管路-负载所组成的液压系统的联合工作特性,提出了泵和负载的确切数学模型以及两者的匹配方法.最后,给出了在合理考虑液压源特性和液压负载特性的前提下为达到希望滤波性能所需控制律的选择方法.      

随机系统的后验椭球条件滤波方法

针对在随机系统中存在着不确知的控制输入,且系统的状态以及随机干扰的分布和参数未知情况下,基于后验椭球逼近的原理,提出了随机系统的后验椭球条件滤波方法,以保证所求解的椭球序列是包含着系统状态估值域的最小椭球序列.该方法是当先验统计信息不足时,尤其当系统状态及随机干扰的分布形式未知时,是解决随机系统状态估计的有效途径之一.      

自修复飞控系统的可靠性估计

给出了故障检测与诊断算法（ＦＤＩ）的故障检测覆盖率、漏报率及操纵面故障下控制律重构的成功率的定义;提出了建立在ＦＤＩ和重构基础上的自修复飞控系统的故障监控覆盖率的估计方法。以某型机的四余度电传飞控系统为例,比较了传统飞控系统和自修复飞控系统在两种故障下的可靠性。结果表明,在执行机构进行了部分简化,考虑了故障覆盖率之后,自修复飞控系统比传统飞控系统具有更高的可靠性。若故障覆盖率可达到９７．５％,利用     

攻击机机群多步骤对地攻击模拟数学模型

以平均动态学理论为基础,研究讨论了攻击机机群在整个战斗飞行过程中作战效能评估的基本原理,建立了战效评估的顶层分析数学模型,导出了效能指标与对地攻击靶场效能指标、国土防空系统突防效能指标及要地防空系统突防效能指标间的关系式,给出了完成作战任务集所需飞机架数、被击毁的总架数,总战斗飞行架次数以及武器总消耗量等的计算式,为评价攻击机机群在整个战斗飞行过程中的作战效能奠定了理论基础。     

旅客机环境控制系统的发展

回顾了飞机环境控制系统在民用旅客机应用中的技术发展过程,介绍了现役各种民用飞机的不同技术方案的环境控制系统特点,比较讨论了３种不同中型民用旅客机的环境控制系统方案,展望了民用飞机的环境控制系统的发展趋势。     

Morphological Structure and Chemical Composition of Cometary Nuclei and Dust

The chemical composition of comet nuclei derived from current data on interstellar dust ingredients and comet dust and coma molecules are shown to be substantially consistent with each other in both refractory and volatile components. When limited by relative cosmic abundances the water in comet nuclei is constrained to be close to 30% by mass and the refractory to volatile ratio is close to 1:1. The morphological structure of comet nuclei, as deduced from comet dust infrared continuum and spectral emission properties, is described by a fluffy (porous) aggregate of tenth micron silicate core-organic refractory mantle particle on which outer mantles of predominantly H₂O ices contain embedded carbonaceous and polycyclic aromatic hydrocarbon (PAH) type particles of size in the of 1 - 10nm range. This revised version was published online in June 2006 with corrections to the Cover Date.