高压输电线路架线放线方法与技术

介绍了高压输电线路架线放线的一种方法与技术．采用８２ｍｍ炮发射－飞行器牵引放线的方法，解决了飞行器结构、飞行器重量和线断三个技术关键．空中越障放线可达５００ｍ．     

两端固定两梯段任意转角悬挑楼梯的内力分析

近年来有不少文献提出了关于两梯段折板式悬挑楼梯(结构对称,受对称荷载的情况)的计算方法,如文献[1]、[2]、[3]等等,但所解决的问题都有一定的局限性。本文提出了用力法解算悬梯平面转角为任意角度时的计算方法,并具有下列特点:(1) 在计算力法方程中的系数和自由项时有选择地保留了影响较大的各项。这样既使计算达到一定的精度,又使计算得到简化;(2) 用扇形面代替折角形休息平台,这样的计算简图更接近于实际情况;(3) 考虑了平台荷载的偏心。     

飞行仿真演示系统人机交互模块研究与开发

飞行仿真演示系统中人机交互模块分为模拟操纵手柄输入和三维动画显示两部分。为了在实验室现有软、硬件基础上开发实时、快速和模块化的演示系统，使用DirectX SDK做开发工具，以便直接访问底层硬件，充分利用硬件的优化性能。在模拟操纵手柄输入模块开发中使用DirectX的DirectInput组件，借助其与硬件类型及输入端口无关的特性，方便地实现手柄输入信号读取；在三维动画显示模块开发中使用DirectX Graphics组件提供的方法，根据飞行器模型实时运动状态量，对飞行器三维模型进行六个自由度的控制，以动画形式表现人工操纵的飞行器模型实时运动状态。通过这两个模块的开发，实现具有人机交互功能的飞行仿真演示系统。     

高速飞行器瞬态气动热试验模拟系统

为得到高速飞行器表面各部分的热应力，应变，结构膨胀量等高温力学性能参数，须建立高速飞行器瞬态气动热试验模拟系统。针对高速飞行器气动模拟试验瞬态热控过程所具有变化复杂，高度非线性，瞬变，强耦合的特点，将模拟控制方法应用于瞬态气动热模拟控制系统。该系统能够按照高速飞行器飞行过程中表面热流和温度的瞬态连续变化对气动模拟加热过程实施快速，准确的动态控制。     

Computer simulation methods for launch vehicle mission and control problems

The flight control system of a launch vehicle is the result of the right tradeoff between different objectives, such as the interaction between the control, guidance and performance aspects of a mission with specified end conditions and the analysis of the mission trajectories and vehicle systems under a variety of normal and failure modes. Hence an evaluation of the design and performance of such a system is not feasible through purely analytical means even with simplified models. This, together with the necessity for step-by-step refinement of the models used for the vehicle and its environment, calls for the computer simulation approach. The various considerations involved in developing and selecting the simulation model and implementing it on a computer are discussed. To illustrate the approach, a hybrid simulation evaluation of the performance of the first stage control system of a satellite launch vehicle and that of the controlled vehicle under different operational modes is presented.     

导弹转速调节片设计方法研究

本文研究了导弹转速调节片的设计思路与方法。在对其设计思路和设计约束分析基础上，通过气动特性计算与转速特性仿真，对比研究了转速调节片偏折角度参数、长度参数与数目参数三项设计要素的设计效果，得出了其设计方法与步骤。研究结果表明，转速调节片的设计是综合弹体结构、气动与总体设计的一项系统工程。     

Stimulus-response compatibility with pure and mixed mappings in a flight task environment.

The present study examined the stimulus-response compatibility (SRC) effect in a simulated flight environment. Experiments 1 and 2 tested the effect with pure and mixed mappings in flight tasks by using attitude displays with inside-out and outside-in formats, whereas Experiments 3 and 4 used a simplified display and tasks. The SRC effect was obtained with mixed mappings when responses were turns of a flight yoke (Experiments 1-3). In contrast, the SRC effect was absent with mixed mappings when they were buttonpresses (Experiment 4). Analyses of sequential effects suggest that the reduction in Experiments 1-3 can be attributed to reduction in the frequency of trials for which the congruent mapping repeats, but the elimination in Experiment 4 cannot be. Implications of the findings are discussed in the context of aviation cockpit design. (PsycINFO Database Record (c) 2010 APA, all rights reserved)     

Preparation of Nonlinear Optical Aerogels and Xerogels in Parabolic Flights

Second harmonic generation of ferroelectrical nano- and microparticles embedded in a nanostructured silica aerogel and xerogel matrix was observed. A homogenous distribution of the ferroelectrical powder was achieved during microgravity on parabolic flight. The paper describes the synthesis procedures of this new class of random non-linear optical materials. The experimental results on frequency doubling are explained with a simple model of absorption and transmission.     

Modeling and Simulation of Aerial Dispersion on Piston Dispersal Mechanism

For the aerial dispersing interior ballistic process and submunition exterior ballistic initial conditions of cluster munition with piston maximum travel limit, a novel model is established, and the numerical simulation is performed. The piston maximum travel limit and the effect of reaction force on carrier body are researched using the internal ballistic model. Guide tube, cluster munition rotating and submunition assembly are analyzed using the submunition initial external ballistic model. The computational results are consistent with the practical process and the experimental data, and prove the rationality of this model. The theoretical methods are presented for the construction design and dispersion analysis of piston dispersal mechanism.     

一种适用于高动态制导飞行的大气航姿系统算法

为解决高动态制导飞行条件下航姿系统的可用性,从工程应用角度提出一种新的大气航姿自适应滤波算法,采用大气数据信息剔除滤波量测中的运动加速度,解决了内阻尼航姿算法在载体高动态机动时不能正确修正姿态的问题。基于MEMS惯性器件的大气航姿系统跑车试验结果证明,该算法合理可行,具有很好的鲁棒性,可以为高动态运动载体提供准确的姿态/航向信息。