It includes esm and t - esm and some flying quality evaluating laws such as the bandwidth law ( bwl ) , the neal - smith law ( nsl ) , the chalk law ( cl ) and the c * law . this software is useful for the design of flight control systems 该软件包可以用频域等效系统方法、时域等效系统方法、带宽准则、闭环准则、俯仰角速率准则、 c准则等进行飞行品质的计算及评估，对飞控系统设计有实用价值。
In this dissertation , radar detection in hrr has been taken as background . the followings are main contents of this dissertation : ( 1 ) based on analyzing the targets and the clutter ’ s specific characteristics of hrr radar , the echo models of targets and clutter have been studied respectively ; the changes of targets ’ echoes in different elevation angles , azimuth angles and attitude angles have been analyzed ; then , the echo models of lfm radar clutter have been established 本文针对高距离分辨雷达目标检测开展研究,主要完成了以下几方面的工作: ( 1 )分析了高距离分辨雷达目标和杂波回波特征,在此基础上分别研究了高距离分辨雷达目标和杂波的回波模型,分析了不同俯仰角、不同方位角以及不同姿态下目标回波模型的变化,并建立了线性调频脉冲压缩雷达的杂波模型。
In the following part , trajectory design and computation are given , including fight scheme and control & navigation laws . through the design and computation , the profile of attack angle , trajectory angle and pitch angle are designed . these works provide theoretical fundamentals for dynamics analysis and practical trajectory design 第三部分内容是对导弹的弹道进行设计与计算，给出导弹在各段的飞行方案或导引规律。设计出导弹在整个飞行过程中的质点弹道，迎角、弹道倾角和俯仰角等参量在导弹攻击目标过程中的变化规律，为进一步的质点系弹道和动态分析提供理论基础。
Based on the research of the complex angle and the bias compensation techniques , the dynamic compenstion with relative phase is developped for elevation tracking & measure with the amplitude - comparison monopulse radars , and it is proved to be a optimum technique by thoery and simulations 因此，在深入研究复角法和固定偏差补偿法的优缺点基础上，本文针对单脉冲比幅测角体制的雷达，提出了一种新的俯仰角测量算法?联合相位的动态偏差补偿法，理论分析和计算仿真证明这种算法了这种算法的优越性。
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。
The laser radar sub - system determines the heights of the tsp according to the slant height and the oblique angle measured by the laser range finder and the electronic theodolite simultaneously . by lucubrating the motion law of tsp , we decided to compute decent velocities with least - squares procedure & two ranks curve fitting 地面激光雷达跟踪测量分系统根据测量到的斜距离和俯仰角确定末敏弹伞弹系统的高度，在深入研究末敏弹稳态扫描过程的运动规律后，通过最小二乘法的二阶分段曲线拟合，计算出落速。
Taking no account of the non - uniformity of the detector , this paper analyzed the performance of the traditional four - quadrant angle - measurement algorithm and two other algorithms in calculating the pitch angle and the deflection angle of the incident ray , and also compared the error curve of the pitch angle calculated by each algorithm in the full plane 摘要在不考虑探测器非均匀性影响的情况下，本文分析了传统四象限测角算法和另外几种算法在计算入射光的俯仰角和偏转角时的性能，还比较了在整个平面内各个算法得到的俯仰角的误差曲面。
According to the characteristic of movement which velocity of agricultural machinery is lower as well as near a level in farm , it is studied attitude determination with lower pitch and the speed determination , in order to achieve the high - accuracy ' s piuposes of gps positioning , navigation and measure 根据农业机械田间作业低速动态和近似平面运动的特点，研究运动载体的低俯仰角姿态搜索方法和行走速度的测量方法，以实现高精度的gps定位、导航以及测量的目标。
Second , by computing the trajectory of the missile and the method of analyzing cep , influences that the fighter ' s height , speed , pitch angle , the deflection angle between fighter and target , and the target moving characters make on the times of fighter attack and missile launch are deeply developed . third , by relating the motion of the missile and the fighter , the influences that fighter ' s dive angle and the deflection angle between fighter and target make on the attack field of the fighter are discussed in this paper when the fighter perform vertical and horizontal attack . criterion of attack effect is proposed focusing on attack time of the fighter , trajectory of the missile and destruction probability to the target 本文主要完成了以下几个方面的工作：对导弹可发射区和飞机可攻击区进行建模，通过对导弹弹道的仿真计算，并运用典型的圆概率偏差精度分析方法，详细讨论了飞机实施攻击时，飞机的飞行高度h 、速度v 、俯仰角、与目标的偏离角_ x及目标运动特性等对飞机攻击时机和导弹发射时机的影响；因此，将飞机和导弹结合起来，详细研究了飞机在垂直平面和水平平面内实施攻击时，飞机俯冲角和与目标的偏离角_ x对飞机的攻击范围的影响；以飞机实施攻击的时间t 、弹道特性和对目标的杀伤概率p来评判对地攻击的效果；最后给出典型算例，通过对空地攻击过程的仿真实现，对飞机飞行过载提出要求。
Its main contributions include the following several aspects : firstly , the dissertation constructs the mathematic model of short baseline orientation determination using two geostationary satellites and analyses the applicable conditions of carrier phase interferometry . orientation determination precision is analysed in depth through both the conventional linearized method and monte - carlo computer simulation method , and the mathematical simulation results show that the linearized method has the shortcoming of fairly low elevation error analysis precision in high latitude area so as not to be very appropriate there . by analyzing the definite factors influencing orientation precision , the dissertation develops the concept of orientation dilution of precision , which uncovers the internal cause of exotic error behavior of bi - satellite orientation , and has important guiding significance for practical engineering applications 本文系统地研究了基于“北斗一号”卫星载波相位干涉测量原理实现地球静止双星定向的相关技术,主要研究成果包括以下几方面:首先,建立了利用两颗地球静止轨道卫星进行短基线定向的数学模型,分析了载波相位干涉测量的适用条件;采用传统的线性化解析法及蒙特卡洛随机模拟法两种途径对双星定向的精度进行了详细分析,数学仿真结果表明在高纬度地区线性化解析法由于俯仰角误差分析精度略有下降而不太适合;在分析定向精度确定性影响因素的基础上,提出了双星定向精度衰减因子odop的概念,揭示了双星定向误差特殊表现的内部机理,对实际工程应用具有重要的指导意义。
