THE DECENTRALIZED ROBUST FAULT TOLERANT CONTROL FOR THE SENSOR FAILURE OF THE FIGHTER

ＴＨＥＤＥＣＥＮＴＲＡＬＩＺＥＤＲＯＢＵＳＴＦＡＵＬＴＴＯＬＥＲＡＮＴＣＯＮＴＲＯＬＦＯＲＴＨＥＳＥＮＳＯＲＦＡＩＬＵＲＥＯＦＴＨＥＦＩＧＨＴＥＲＨｕＳｈｏｕｓｏｎｇ；ＪｉｎＬｏｎｇ（Ｄｅｐｔｏｆ．ＡｕｉｏＣｏｎｉｒｏｌ，ＮａｎｊｉｎｇＵｎｉｖｅｒｓ...     

A MODEL FOR THE RELIABILITY ANALYSIS OF STRUCTURE UNDER RANDOM STRESS RANGE LOADINGS（RDCDR MODEL）

ＡＭＯＤＥＬＦＯＲＴＨＥＲＥＬＩＡＢＩＬＩＴＹＡＮＡＬＹＳＩＳＯＦＳＴＲＵＣＴＵＲＥＵＮＤＥＲＲＡＮＤＯＭＳＴＲＥＳＳＲＡＮＧＥＬＯＡＤＩＮＧＳ（ＲＤＣＤＲＭＯＤＥＬ）ＡＭＯＤＥＬＦＯＲＴＨＥＲＥＬＩＡＢＩＬＩＴＹＡＮＡＬＹＳＩＳＯＦＳＴＲＵＣＴＵＲ...     

NONLINEAR INVERSE SIMULATION FOR THE MANEUVERING FLIGHT OF COAXIAL ROTOR HELICOPTERS

ＮＯＮＬＩＮＥＡＲＩＮＶＥＲＳＥＳＩＭＵＬＡＴＩＯＮＦＯＲＴＨＥＭＡＮＥＵＶＥＲＩＮＧＦＬＩＧＨＴＯＦＣＯＡＸＩＡＬＲＯＴＯＲＨＥＬＩＣＯＰＴＥＲＳＣａｏＹｉｈｕａ（ＩｎｓｔｉｔｕｔｅｏｆＡｉｒｃｒａｆｔＤｅｓｉｇｎ，ＢｅｉｊｉｎｇＵｎｉｖｅｒｓｉｔ...     

FINITE ELEMENT ANALYS IS AND OPTIMUM DESIGN FOR THE FRONT－FUSELAGE WITH SANDWICH CONSTRUCTIONS

ＦＩＮＩＴＥＥＬＥＭＥＮＴＡＮＡＬＹＳＩＳＡＮＤＯＰＴＩＭＵＭＤＥＳＩＧＮＦＯＲＴＨＥＦＲＯＮＴ－ＦＵＳＥＬＡＧＥＷＩＴＨＳＡＮＤＷＩＣＨＣＯＮＳＴＲＵＣＴＩＯＮＳＤｉｎｇＹｕｎｌｉａｎｇ；ＬｉｕＹｉ（Ｄｅｐｔ．ｏｆＶｅｈｉｃｌｅ，ＮａｎｊｉｎｇＵｎ...     

THE SPILLOVER MANAGEMENT IN THE DYNAMIC OUTPUT FEEDBACK CONTROL OF FLEXIBLE SPACECRAFT

ＴＨＥＳＰＩＬＬＯＶＥＲＭＡＮＡＧＥＭＥＮＴＩＮＴＨＥＤＹＮＡＭＩＣＯＵＴＰＵＴＦＥＥＤＢＡＣＫＣＯＮＴＲＯＬＯＦＦＬＥＸＩＢＬＥＳＰＡＣＥＣＲＡＦＴＴＨＥＳＰＩＬＬＯＶＥＲＭＡＮＡＧＥＭＥＮＴＩＮＴＨＥＤＹＮＡＭＩＣＯＵＴＰＵＴＦＥＥＤＢＡＣＫＣＯ...     

CYCLIC VISCOPLASTIC DESCRIPTION FOR THE MEAN STRAIN EFFECT

ＣＹＣＬＩＣＶＩＳＣＯＰＬＡＳＴＩＣＤＥＳＣＲＩＰＴＩＯＮＦＯＲＴＨＥＭＥＡＮＳＴＲＡＩＮＥＦＦＥＣＴＣＹＣＬＩＣＶＩＳＣＯＰＬＡＳＴＩＣＤＥＳＣＲＩＰＴＩＯＮＦＯＲＴＨＥＭＥＡＮＳＴＲＡＩＮＥＦＦＥＣＴ￥ＹａｎｇＸｉａｎｊｉｅ（ＳｏｕｔｈｗｅｓｔＪ...     

SPECIAL HIGH-ORDER BENDING CRACK TIP FINITE ELEMENT FOR THE REISSNER PLATE

ＳＰＥＣＩＡＬＨＩＧＨ┐ＯＲＤＥＲＢＥＮＤＩＮＧＣＲＡＣＫＴＩＰＦＩＮＩＴＥＥＬＥＭＥＮＴＦＯＲＴＨＥＲＥＩＳＳＮＥＲＰＬＡＴＥＪｉａｎｇＣｈｉｐｉｎｇ（ＤｅｐａｒｔｍｅｎｔｏｆＦｌｉｇｈｔＶｅｈｉｃｌｅＤｅｓｉｇｎａｎｄＡｐｐｌｉｅｄＭｅｃｈａｎｉ...     

NUMERICAL SIMULATION OF THE FLOW PAST WING-BODY USING EULER EQUATIONS

ＮＵＭＥＲＩＣＡＬＳＩＭＵＬＡＴＩＯＮＯＦＴＨＥＦＬＯＷＰＡＳＴＷＩＮＧ－ＢＯＤＹＵＳＩＮＧＥＵＬＥＲＥＱＵＡＴＩＯＮＳＮＵＭＥＲＩＣＡＬＳＩＭＵＬＡＴＩＯＮＯＦＴＨＥＦＬＯＷＰＡＳＴＷＩＮＧ－ＢＯＤＹＵＳＩＮＧＥＵＬＥＲＥＱＵＡＴＩＯＮＳ￥Ｃｈｅｎ...     

AERODYNAMIC DESIGN PROBLEM SOLVED BY THE THREE－DIMENSIONAL STREAM FUNCTION FORMULATlON

ＡＥＲＯＤＹＮＡＭＩＣＤＥＳＩＧＮＰＲＯＢＬＥＭＳＯＬＶＥＤＢＹＴＨＥＴＨＲＥＥ－ＤＩＭＥＮＳＩＯＮＡＬＳＴＲＥＡＭＦＵＮＣＴＩＯＮＦＯＲＭＵＬＡＴｌＯＮＧｕＣｈｕｎｗｅｉ；ＸｕＪｉａｎｚｈｏｎｇ；ＤｕＪｉａｎｙｉ（ＩｎｓｉｉｔｕｔｅｏｆＥｎｇｉｎｅ...     

A CALCULATION OF OPTIMAL FLIGHT TRAJECTORY USING THE PARAMETERIZED OPTIMIZATION METHOD

ＡＣＡＬＣＵＬＡＴＩＯＮＯＦＯＰＴＩＭＡＬＦＬＩＧＨＴＴＲＡＪＥＣＴＯＲＹＵＳＩＮＧＴＨＥＰＡＲＡＭＥＴＥＲＩＺＥＤＯＰＴＩＭＩＺＡＴＩＯＮＭＥＴＨＯＤＡＣＡＬＣＵＬＡＴＩＯＮＯＦＯＰＴＩＭＡＬＦＬＩＧＨＴＴＲＡＪＥＣＴＯＲＹＵＳＩＮＧＴＨＥＰＡＲＡ...     

利用前缘旋转控制边条翼外翼分离

边条翼在边条较小时中等迎角以上外翼就会出现分离,现提出用转动前缘表面来控制边条翼外翼分离。通过测力、油流和烟丝实验研究了转动前缘对机翼气动特性的影响。结果表明,在这种机翼上转动前缘对控制分离是有效的,升力增量最大可达３０％。可以预期,转动前缘与边条的综合作用,机翼的分离特性将有较大的改善     

后掠机翼的前缘吸力

本文应用三元亚音速升力面理论求出了后掠翼前缘附近的流场。该流场是一连续部分与一奇异部分之和。由此解析地导出了前缘吸力的公式,从而证明了在空气动力学中长期广泛应用的前缘吸力仅取决于垂直于前缘的速度性质的假设是正确的。本文并证明该假设与前缘吸力的公式可推广到非定常可压缩流场。     

单孔冲击式帽罩前缘流动换热特性数值分析

为了提高航空发动机帽罩冲击防冰结构的设计分析水平,对单孔冲击式帽罩前缘结构的流动换热特性进行数值研究,分析了不同冲击孔径与不同冲击雷诺数对帽罩前缘速度流场、换热系数与努塞尔数的分布规律。结果表明:在冲击雷诺数一定的条件下,冲击孔径越大,射流核心速度和前缘壁面附近的气流速度越小,前缘冲击区形成的涡流团越大,当孔径D=6 mm时,小孔径冲击下前缘区整体换热效果不如大孔径的,而在滞止区的换热效果则要优于大孔径的;当D>12 mm时,孔径大小对壁面换热基本没有影响;在冲击孔径相同时,增大冲击雷诺数使得冲击射流、前缘壁面附近及侧壁曲面通道内的气流流速增大,冲击区内的涡流团则逐渐减小;冲击雷诺数的增大也增强了前缘冲击区的换热特性。     

Effects of coarse riblets on air flow structures over a slender delta wing using particle image velocimetry

This research investigates the aerodynamic performance and flow characteristics of a delta wing with 65° sweep angle and with coarse axial riblets,and then compares with that of a smooth-surface delta wing.Particle Image Velocimetry(PIV)were utilized to visualize the flow over the wing at 6 cross-sections upright to the wing surface and parallel to the wing span,as well as 3 longitudinal sections on the leading edge,symmetry plane,and a plane between them at Angles of Attack(AOA)=20°and 30°and Re=1.2×10~5,2.4×10~5,and 3.6×10~5.The effects of the riblets were studied on the vortices diameter,vortex breakdown location,vortices distance from the wing surface,flow lines pattern nearby the wing,circulation distribution,and separation.The results show that the textured model has a positive effect on some of the parameters related to drag reduction and lift increase.The riblets increase the flow momentum near the wing’s upper surface except near the apex.They also increase the flow momentum behind the wing.     

旋转螺桨叶面流场显形实验

本文介绍了旋转螺桨叶面流场显形实验。粘贴丝线在旋转桨叶表面作流场显形。从实验结果看,在桨叶由根到尖的五分之四部分,气流由前缘向后缘与弦线方向倾斜某个角度向外流动。而在桨叶尖部五分之一区域出现叶面气流分离和倒流现象,严重时甚至出现反向环流,从而产生负拉力使螺桨效率明显下降。      

典型特征参数对大转折APU进气道飞行性能影响的数值研究

为了给一种迎风开门式的辅助动力系统（APU）进气系统设计提供参考,采用基于后缘线轮廓及面积变化规律的参数化设计方法,通过对唇边顺滑修型,可以与唇口的锯齿前缘配合形成斜向下的进口段,利用数值模拟研究了进口形状、前缘面曲率和喉道位置这三个特征参数对此类大转折APU进气道性能的影响。计算结果表明：APU进气道损失主要来自于分离损失,进口形状主要影响导流面转折程度和进气道内压力梯度变化,前缘面曲率影响了分离区的尺度和强度,其中,前缘面曲率对出口气动性能影响较大,在设计状态下,适当增大前缘面曲率可使得出口总压恢复系数增大0.81%。在后缘面曲率不变的情况下,通过合理安排进口形状、前缘面曲率和喉道位置,可有效推迟分离的发生,减弱分离区强度。另外,在正攻角和侧滑状态下也表现出相同的趋势。     

低雷诺数下50°后掠三角翼的旋涡流动

采用数值模拟和流动显示的方法研究了50°后掠角三角翼在低雷诺数下的旋涡流动,结果表明:低雷诺数下,非细长三角翼在5°攻角时就形成了稳定的前缘涡,较小攻角时前缘主涡就开始破裂,并观察到泡型和螺旋型两种旋涡破裂方式。另外,在一定的攻角范围内,前缘主涡的外侧又生成一对新的集中涡,构成双涡结构;随着攻角的增大,前缘涡涡核不断升高,主再附线向中心移动,二次分离区扩大。     

基于耗散函数的低速扩压叶栅损失机理探讨

推导了含耗散函数项的总压输运方程,利用总压损失,熵增,耗散函数等参数分析某扩压叶栅流动与损失特性,探讨其损失产生机理.研究表明:栅内损失主要来源于叶片前缘附近、流道表面、尾迹区、分离区与主流交界区的流动耗散;分离区仅是高总压损失和高熵值的低能流体聚集区,而非高损失来源区;通过减小分离区以提高叶栅件能的控制方法本质是通过...     

扩压叶栅角区-吸力面造型设计及流动控制机理

通过数值模拟,分别针对扩压叶栅的设计工况与角区失速工况进行叶身/端壁融合与吸力面优化造型设计,分析其流场结构与性能的变化,并探究两种优化造型对压气机性能改善的机理。优化结果表明:在设计工况下,优化造型吸力面凹陷,使得吸力面附面层厚度变薄,最大端壁融合位置靠近尾缘,角区低能流体在压力梯度的作用下转移并减少,分离结构得到明显控制,损失降低;在角区失速工况下,优化造型吸力面凸起,最大端壁融合位置靠近前缘,使得前缘分离结构显著减弱,当流体在进入吸力面前缘时提前附着,前缘分离区减小甚至消失,损失降低。根据两种造型流场结构特点与控制机理,可构造出在多工况下具有显著作用的叶身-端壁融合造型。     

Experimental study of the aerodynamics of a wing with various configurations of wingtip triangular extension

In this paper, we discuss the main ways of improving the aircraft aerodynamics. The results of a physical experiment are presented that is aimed to verify the theoretical results obtained earlier on the possible improvement in a seaplane wing model lift-to-drag ratio, by using a deflectable triangular extension along the wing leading edge near the wingtip. We confirm the slight effectiveness of using the wingtip leading edge triangular extensions on the nature of flow around the wing.