4 . designing and realizing a missile testing and training view simulation system , that can simulate the flight trajectory real time and reappear the entire testing process after experiment . at last , this thesis provides the summarization of the work and the content of the future research 4 、设计并实现了一个导弹试验训练视景仿真系统,既可以实时的模拟导弹的飞行状态,又可以在试验后直观地重现整个试验过程,便于分析试验结果和数据。
According to the requirement on the testing of recoil caused by weapon launching during helicopter flighting , this paper puts forward the dynamic measurement method based on the practical situation , and resolves the problem of recoil ’ s measurement of weapon launching during helicopter ’ s flight 本文根据直升机飞行中武器发射后坐力测量的需要,从实际情况出发,提出并设计了相应的动态测试方案,解决了在飞行状态下武器发射后座力的测量问题。
The echolocating calls in the state of fly were compared with those in the state of hang in two kinds of bats , r . yunanensis and h . pratti , and the doppler compensation effect was described . the analyzing result indicated that the frequency in hang was higher that that in fly , the duration and interpulse duration in hang were longer than those in fly , and the fm bandwidth in hang was narrower than that in fly 比较了云南菊头蝠和普氏蹄蝠飞行状态和悬挂状态下的回声定位声波，描述这2种蝙蝠的多普勒补偿效应，悬挂状态声波频率显著高于飞行状态，声脉冲时间和间隔时间显著长于飞行状态， fm带宽窄于飞行状态。
Because of the complicated flight state of the aircrafts , there rests a critical demand for high speed operation of flight data in the synthetical graphical display system : we must finish all computations of the flight data and send them into the display panel in a very short time which is critically specified by the display instruments 在机载综合显示系统中，由于飞行状态复杂，对飞行数据的处理和显示都提出了比较严格的时间要求：需要在显示器的一帧时间内完全计算数据并完成显示任务。因而在工程中，硬件设计的运算速度成为至关重要的因素之一。
This paper , in advantage of modern control theories , designed the pitch control system and the altitude holding system of the x armed helicopter , and present digital simulation , coupling analysis , sensitivity analysis , system performance analysis under different input and initial condition 本文应用现代控制理论设计了某型武装直升机的俯仰角控制系统和高度保持系统，并进行了数字仿真、耦合分析、飞行状态变化对控制系统性能的影响分析，及在不同输入初始条件下的系统性能分析。
Some technique issues concerned to the scene simulation system of the launch vehicle was discussed and developed in this thesis . in this scene simulation system , the established 3 - dimension ( 3d ) model of the objects are imported to scene simulation environment by programming to create a vivid virtual scene . scene simulation technique can objectively describe the simulation process , realize the flight simulation as well as real time roam of launch vehicle , etc . 其中,视景仿真系统是整个系统最有显示度的部分,它采用视景仿真技术,根据仿真的目的,构造仿真对象的三维模型和场景驱动,达到客观、实时的再现仿真过程,实现火箭飞行状态的可视化仿真和火箭测试状态的实时漫游等功能。
This paper studies optimal helicopter flight operations in the event one - engine failure . a three - dimensional point mass with a yawing motion of uh - 60a has been used to study rto and cto from an elevated heliport or from a heliport , a first order dynamic of the oei contingency power is considered . flight after engine failure are formulated as nonlinear optimal control problems 双发及多发直升机单发失效后,直升机飞行所需要的功率由剩余发动机提供,而在某些需要大功率的飞行状态时,如起飞状态、着陆状态等,剩余发动机提供的功率可能满足不了,这就需要对剩余发动机的可用功率进行合理利用。
Here , the aircraft is in extreme flight conditions that is high angles of attack and high angular rates . it can encounter severe nonlinear effects . detailed descriptions of the flight dynamic , aerodynamic models , inverse dynamic and the choice of the control variable are given 2 、应用经典的微分几何方法研究了一般的飞行状态下飞机飞行的控制律，指出不利用矢量推力的飞行系统的控制方程一般都是可以逐步通过动态状态反馈，适当的坐标变换和正则静态反馈等三个步骤得以线性化。
Either to be a platform for originating an attack to the enemy or to be a vehicle for landing force , the wig vehicle must fly with low altitude in martial action . it is also a valuable topic that how to take advantage of the good interaction and avoid the potential dangers as flying at lower altitude in demotic application 在军事上，地效翼船无论是作为实施袭击的平台还是登陆作战的工具，保持低空飞行状态都是必须的；在民用上，如何在充分利用低空飞行的有利因素的同时规避低空飞行时潜在的风险也是一个值得研究的问题。
The paper discusses the questions in operating and training of existent theodolite , and devises an emulational system of training theodolite operator through studying the space - relation between object and theodolite during the objective acutual tracking process . the system is founded two dimension - three dimension spacial coordinate - transform model , and polyfit fight track in basis on the method of subsection cubic spline , and put forword the control method of separating size and direction from speed , realized the all - real simulation of objective flight state . the trainer can input objective position parameter and the characteristic points of objective flight track 本文探讨了现行经纬仪操控训练中存在的问题。通过研究经纬仪对目标实际跟踪过程中目标与经纬仪间的空间关系，设计了一套训练经纬仪操作手的实景仿真系统。该系统建立了二维?三维的空间坐标变换模型；利用分段三次样条插值的方法拟合出了目标飞行轨迹；并对速度的控制提出了一种将速度矢量的大小与方向分离的控制方法，实现了对目标飞行状态的全真模拟。
