The actual - operating parameter ( level angle , pitching angle , speed etc ) of theodolite are measured by code check of theodolite , and sent to computer by the interface 教练员可通过系统提供的输入界面输入目标的位置参数及目标飞行轨迹的特征点。经纬仪的实际运动参数由经纬仪自身的码盘测出，并通过计算机接口输入到计算机中。
The system was developed by setting the function pages , achieving the management of the data transmission and integrating the geographic information system ( gis ) into system to achieve the planar display of the flying track 系统建立各个功能页面，实现分布仿真系统内部的实时数据通讯管理，集成地理信息系统实现飞行轨迹二维态势显示。
Based on gyro - free inertial navigation theory while revolve about mems accelerometer and dsp , this dissertation mainly focuses on the research of gyro - free inertial measurement unit for shell flight path measurement - the first step for guidance 本文以无陀螺惯性导航理论为基础,以微机械加速度传感器、高性能dsp处理器为核心,研制应用于某型炮弹的无陀螺惯性测量系统,该系统将用于炮弹飞行轨迹的测量,是实现炮弹制导的第一步。
In ccs ' c3x - ' c4x compile environment , using composite programming method of c and assemble language , the author debugs each port of the hardware circuit system , analyses interrupts mechanism and bootloader mechanism of the dsp , develops the system of generating flight orbit data 其次，在ccs ' c3x - ' c4x编译环境下，采用c语言和汇编语言混合编程的方式，初调了硬件电路系统的各个端口，分析了dsp芯片的中断和bootloader机制，开发了飞行轨迹数据生成系统。
Based on this main idea , first the thesis discusses the mathematics model of gyro and accelemeter , the initial alignment of north - pointed strapdown inertial navigation system , the method of calculation navigation , the method of generating flight orbit data , the method of ins / gps integrated navigation in detail . then the thesis develops the system generating flight orbit data and the system of real - time simulating strapdown inertial navigation with vc + + 6 . 0 论文以此为核心展开：首先详细讨论了陀螺和加速度计的数学模型、指北式捷联惯性导航系统初始对准和导航解算的算法、飞行轨迹数据生成算法、 ins gps组合导航算法；然后利用visualc + + 6 . 0开发出飞行轨迹数据生成系统、捷联惯性导航实时仿真系统。
The problem is then fed to a nonlinear programming routine to solve for all parameters . the flight dynamics model with yawing motion of uh - 60a is given , scale factors of state variables and control variables are applied based on the consideration of algorithm convergence . then , the optimization of trajectories is expressed as optimal control problem with a performance index constrained by helicopter performance limits , faa regulation and so on 首先,建立带偏航运动的直升机点质量模型,然后对状态变量和控制变量进行无量纲处理,因为状态变量和控制变量量值相差较大,这使得优化算法收敛效果变差,所以需要选择适当的缩放因子,最后把直升机单台发动机停车后的飞行轨迹表示成一个最优控制问题,即在考虑直升机性能限制和far规范后,指定一个优化性能指标,选择合适的路径约束,然后再解最优控制问题。
In the model of " singer " and " current " , we apply the kalman filtering to simulate and analyze the 8 status and 11 status . besides , we compare the for - and - aft orientation precision of kalman filtering . at the base , with how to improve filter ' s dynamic performance , we advance the improved self - reliant filtering arithmetic and the optimize arithmetic with dissolve factor 然后介绍了卡尔曼滤波的基本原理，在此基础上对动态用户的飞行轨迹进行了仿真，对“ singer ”模型下的8状态和11状态卡尔曼滤波算法进行了仿真分析，同时对“当前”统计模型下11状态卡尔曼滤波算法进行了仿真分析，并对滤波前后的定位精度进行了比较。
Study shows that the effect of the shock of heavy rain on an airplane in the low - level wind shear of thunderstorms is evident , the flight resistance resulted from the roughness of airplane is able to change the flight track and endanger the flight safety , whereas , the increase in the mass of airplane caused by the water film on the airframe and its wings in heavy rain is nigligible 结果表明：雷暴低空风切变中大雨雨滴的冲击作用是明显的，被粗糙化的机体所产生的阻力能显著改变飞行轨迹，并能影响飞行安全；累计在机身和机冀上的水膜厚度造成的飞机质量的增加对飞行的影响可以忽略。
Abstract : a method named multi - times optimization is presented to solve the multi - specification optimization problem , which is difficult to solve using the variational optimal theory . in the method several demands are reduced to some sub - tasks . in every subtask a demand that can not be transformed into bound condition is taken as performance specification for optimazation , and the other demands are taken as bound conditions . by means of the method , the arrival time , number of turn , turn angle of the aircraft in the terminal area are selected as performance specification separately , and the general character of optimal flight route in the terminal area is given 文摘:为了给飞机提供一条能满足多种指标要求的最优飞行轨迹，针对变分最优理论难以求解多指标优化问题，提出了命名为多次优化的方法，即将多要求的优化任务分成先后相继的多次任务，每次任务中选取一种不能边界转化的要求作为最优性能指标，而其余要求转化为边界条件.利用这一方法以时间、转弯次数、转弯角度为最优性能指标给出了终端区最优飞行轨迹的一般特征
Direct side force control ( dsfc ) comes into being with the appearance of act ( active control technology ) . through maneuvering the vertical canard to produce side force , people can control a aircraft easily . so the trajectory of a vehicle can be controlled precisely , and it ' s maneuverability is greatly improved 直接侧力控制是随着主动控制的提出而出现的，采用直接侧力控制，可在不改变飞机姿态的条件下，直接通过控制面造成侧力来操纵飞机机动，从而达到精确控制飞行轨迹和增强机动能力的目的。
