Experimental investigation of boundary layer transition over a delta wing at Mach number 6

An experimental study on the boundary layer transition over a delta wing was carried out at Mach number 6 in a quiet wind tunnel. The Nano-tracer-based Planar Laser Scattering (NPLS) and Temperature-Sensitive Paints (TSP) techniques were used to measure the fine flow field structure and the wall Stanton number of the delta wing. The influence of factors such as the angle of attack and the Reynolds number was studied. The following results were obtained. The boundary layer transition between the leading edge and the centerline was dominated by the crossflow instability. At the location of the initial appearance of the traveling crossflow waves, the Stanton number began to rise. The Stanton number reached a maximum when the crossflow waves were broken up to turbulence. Increasing the angle of attack increased the spanwise pressure gradient at the windward side of the delta wing, thereby increasing the crossflow instability and advancing the boundary layer transition front. However, increasing the angle of attack caused the transition front to move backward at the leeward side. In addition, the sensitivity of the boundary layer transition to the Reynolds number varied with the angle of attack and the region.     

一种运载火箭时变结构模态参数辨识的确定性演化方法

针对运载火箭的时变结构模态参数辨识问题进行研究，基于时变自回归滑动平均(TARMA)模型，提出一种时变结构模态参数辨识的确定性演化方法。该方法利用小波基函数的良好局部函数拟合能力，将墨西哥帽小波函数作为TARMA模型时变系数的空间基底，构建了基于小波函数的泛函序列时变自回归滑动平均(FS-TARMA)模型，并发展了两步最小二乘估计方法，实现了时变系数的解耦估计。通过有限单元法，建立了阿里安V号芯级运载火箭时变有限元模型，对所提辨识方法进行了验证，结果表明：墨西哥帽小波基FS-TARMA方法能够有效地辨识系统的时变模态参数；与传统傅里叶基FS-TARMA方法相比，具有更好的辨识精度，并且能够准确地反映出模态局部细节特征。     

Hypersonic vehicle aerodynamic design using modified sequential approximate optimization

Hypersonic vehicles are receiving increased attention within the aerospace community due to their high cruise speed and long-range capabilities. In this paper, a modified Sequential Approximate Optimization method is proposed for an optimized aerodynamic design of a hypersonic vehicle. As part of this approach, a constrained experimental design method is developed to handle the constraints more efficiently. A radial basis function is used to surrogate time-consuming CFD analysis. An efficient and more robust numerical mesh morphing scheme for the hypersonic vehicle is developed for the generation of high-quality meshes. Within this paper, a novel adaptive infilling strategy is proposed which uses an inaccurate search technique coupled with an elite archive. This allows the location of a more promising sample region and hence improves the surrogate accuracy, thereby further enhancing the optimization efficiency. A hypersonic vehicle aerodynamic design problem is solved using the proposed approach and satisfactory results are obtained at much lower computational costs. The lift-to-drag ratio is increased by 23.8% when compared with the base configuration while also satisfying the volume and lift constraints. The pressure and Mach contours have been compared with those of the base configuration and the results demonstrate the strength of the optimized configuration. The modified sequential approximate optimization for designing an improved hypersonic vehicle is worth referencing in future work.     

飞机过载与过载表的指示

阐述了飞机过载和过载指标值的意义，指出过载表正确测试飞机过载的条件，并说明了Ｌ８飞机前、后舱中过载表指示的不一致性及仪表指示值的修正计算问题。     

3D STUDIO在飞机机动飞行科目中的应用研究

简述了采用３ＤＳＴＵＤＩＯ软件后，给飞机机动飞行科目试飞结果分析带来的重要变化。并从实际应用的角度论述了３ＤＳＴＵＤＩＯ辅助提高飞机设计完善性的原因；展望了将３ＤＳＴＵＤＩＯ软件，应用于辅助完善飞机设计的前景。     

应急救生系统逃逸动力装置的性能分析

载人航天中，应急救生分系统是火箭一飞船系统的重要组成部分，以联盟号应急救生系统为例介绍了其组成、工作程序并研究分析了逃逸动力装置──主逃逸发动机和控制发动机的性能参数与逃逸飞行弹道特性之间的相互关系；从逃逸弹道设计技术指标出发来选取动力装置的主要性能参数（推力大小及工作时间）。仿真计算得出了有益的结论。     

半自动担架车的运动仿真

在讨论半自动担架车工作原理的基础上，应用运动学原理将担架车整个运动过程进行了分析。应用矩阵理论对担架车任意位置的13个关键点进行运动求解和运动仿真。     

航模驱鸟设备的综合安全性研究

综合分析了影响航模驱鸟设备安全性的航模、操纵者及环境三方面的因素,为了提高航 模驱鸟设备的综合安全性,结合专家经验及数据,提出了相应的保证安全的措施。     

直升机－舰组合风限图计算方法研究

首先简要叙述了国外风限图的研究概况及国内现状，在分析影响安全起降的各种因素的基础上，建立了风限图模拟计算的数学模型，并针对某直升机－舰组合风限图进行了计算。计算结果表明：所建立的数学模型切合实际，计算过程正确合理，得到的风限图比较真实地反映了直升机－舰配合能力。该方法较国外主要通过试飞得到风限图的方法相比可节省人力、物力和财力，具有安全性，为风限图的研制提供了新的途径。     

A CALCULATION OF OPTIMAL FLIGHT TRAJECTORY USING THE PARAMETERIZED OPTIMIZATION METHOD

ＡＣＡＬＣＵＬＡＴＩＯＮＯＦＯＰＴＩＭＡＬＦＬＩＧＨＴＴＲＡＪＥＣＴＯＲＹＵＳＩＮＧＴＨＥＰＡＲＡＭＥＴＥＲＩＺＥＤＯＰＴＩＭＩＺＡＴＩＯＮＭＥＴＨＯＤＡＣＡＬＣＵＬＡＴＩＯＮＯＦＯＰＴＩＭＡＬＦＬＩＧＨＴＴＲＡＪＥＣＴＯＲＹＵＳＩＮＧＴＨＥＰＡＲＡ...