Due to the location of mountainous areas and highlands , the extremely unfavorable clearance condition of the airfields and the volatile weather , plus the complex terrain of highland airlines and the very high enroute safety altitude , the analysis and management of flight performance stands out to be a critical problem 摘要对位于山地和高原地区的机场，一般净空条件极差、气候复杂多变，高原航线地形复杂、航路安全高度高，飞行性能分析及管理问题尤其突出。
Besides , the design of vane is the major project of the uav research , because the vane is the most important part in power transformation of the uav , the quality of this part will directly affect the capacity of the uav . we should manage to enhance the lift resistance ratio in the same situation 此外,本课题着重对无人机的叶片部分进行设计,因为叶片是无人机的动力转化部分,它的好坏直接影响着飞行器的飞行性能,在相同外部条件下,尽可能使其产生比较大的升阻比。
The optimized shape in the parameter range was obtained . in order to studied the lightcraft ’ s flight performance , the 3 - d lightcraft aerodynamic performance research at different altitudes , velocity and angle of attack were simulated . in subsonic situation , the drag coefficient was reducing with the angle of attack increasing , but in supersonic situation , the drag coefficient was increasing with the angle of attack increasing 分析了激光推进技术的基本原理及其特点,对光船的气动性能进行了数值模拟,在流场分析的基础上,对光船的头部外形进行了优化,并给出了参数变化范围内的优化外形;为了进一步研究光船的飞行性能,对不同高度、不同速度和不同攻角等飞行条件下的三维光船气动性能进行了数值研究,研究表明:在亚声速情况下,阻力系数随攻角的增大而减小;超声速情况下,阻力系数随攻角增大而增大。
The method of wing shape optimization of space shutlle has been developed with penalty function approach in which the objective function is the mass of the wing and the constraints are the hypersonic re - entry flight cross range , lift / drag ratio , and subsonic flight lift / drag ratio , the margin of the longitudial static stability and the magnitude of the horizontal landing speed etc 摘要介绍了在满足高超音速再入横向机动航程，高超音速再入飞行时的升阻比，亚音速进场飞行时的升阻比，纵向静稳定性裕度和水平着陆速度等飞行性能设计要求下，用罚函数法寻求使航天飞机机翼质量为最小的外形优化方法并给出了算例。
The controller for longitudinal short period model of aircraft has been designed and simulated by using those schemes . simulation results are demonstrated to show that the scheme is not only simpleness and easy accomplish , but also enhance the performance of flight and the effectiveness and applicability of the proposed method 仿真结果表明，用此方法，不但使设计过程简单且易于实现，而且用该方法设计出控制器可以有效地改进飞机的飞行性能，提高失速迎角，加快起恢复速度，闭环跟踪效果也令人满意。
