巡航飞行

民用飞机在巡航飞行时，由于可能会受到阵风的干扰。

Civil airplane is often disturbed by gust when it cruises .

您不一定牵涉到维护具体空速在巡航飞行。

You 're not necessarily concerned with maintaining a specific airspeed in cruise flight .

由这两个定理建立了最优起飞巡航飞行轨迹。

The trace of optimal flying and taking off is described on the conditions of two theorems .

现在，我们已经开始我们本次航班的最后一段航程，飞机正在11000米的高空进行巡航飞行。

We have now started the last leg of our journey and are cruising at an altitude of11,000 meters .

本论文研究了适合星际巡航飞行的天文导航方法，并对其精度影响因素进行了针对性研究。

This paper studies the autonomous celestial navigation method suitable for interplanetary cruise flight and analyses its accuracy influential factors .

分别模拟目标作巡航飞行、平飞加速、跨越障碍机动、水平蛇行机动飞行时的动作。

The target actions of cruise flying , level accelerating , resolving obstacle move , level hunting move flying were simulated .

在此基础上对典型高超声速飞行器在无动力巡航飞行状态下的气动力和气动热进行了数值预测。

The aerodynamic force and heat of a hypersonic vehicle are predicted in the power off , cruise conditions basing on the numerical confirmations described above .

由于防区外空面导弹具有防区外发射、巡航飞行和精确打击等诸多优点，因此在战争中发挥着越来越重要的作用。

Stand-off air to surface missiles have a lot of advantages such as stand-off launch , cruise flying and precision attack etc , and are becoming more and more important in modern wars .

针对高超声速飞行器的大包络巡航飞行，研究了两种多模型预测控制器设计方法。

The simulation results show that the application of predictive control in hypersonic vehicle is feasible . Thirdly , considering large envelope flight of hypersonic vehicle , two multi-model predictive control schemes are studied .

根据牵引飞行实际过程，推导出载机、运载器在起飞阶段，巡航飞行阶段的数学模型，以及相应的参数计算模型。

According to actual course of the towed flight , deriving mathematics model of the course of taking off and towed flight of the towing plane and of carrier rocket , and corresponding parameter calculate models .

巡航导弹飞行撞地概率的一种计算方法

A Calculation Method of Bumping Ground Probability of Cruise Missle Flight

巡航导弹飞行捷径、高度及速度对突防影响的仿真研究

Emulational study on the effect on the cruise missile penetration by shortcut flight course , flight altitude and flight velocity

通过建立杂波模型、电子干扰模型以及大气衰减模型，分析了巡航弹飞行环境对雷达探测性能的影响。

By sea clutter and ground clutter modeling , electron jammer modeling atmosphere attenuation modeling , the cruise missile flight con .

直升机能垂直起降，能够灵活敏捷地完成悬停和巡航等飞行动作。

Rotorcraft can take off and land vertically , and can perform flight ranging from hovering to airplane-like cruising with agility and maneuverability .

当马来西亚航空交通管制中心与这架飞机失去联络时，它正在正常巡航高度飞行。如今，专家们提出了多种可能解释这架飞机为何失踪的理论。

Experts have suggested various theories that might explain how the aircraft , which was at normal cruising altitude when Malaysian air traffic control lost touch with it , disappeared .

并运用仿真工具得到了纵向和横侧向模态的气动参数和特征值，计算出了在不同飞行速度和高度下巡航平衡飞行的状态值，获取了整个飞行过程中近似的飞行包线。

The simulation tool is used to calculate the aerodynamic coefficients and eigenvalues in the longitudinal and lateral motion modes , and compute the flight trim points in the different flight velocities and altitudes , then approximately get fight envelope of the whole flight process .

激光成像雷达是保障巡航导弹低空飞行和末制导目标识别目前比较有效的探测工具之一。

The research is on imaging lidar , which is one of the effective detection tools for assuring cruise missile low-flying and terminal guidance target identification .

通过给出的部分仿真结果可以看出，本文得出的巡航式飞行器飞行控制系统结构合理，设计方法可靠，系统参数可以满足该飞行器控制的总体性能要求。

It can be seen that the structure and parameters of the flight control system are reasonable ; the performance can meet the need of the task .

详细分析了巡航导弹末段飞行环境约束、飞行性能约束和作战任务约束，给出了障碍和威胁的处理方法，建立了约束条件对导弹飞行影响的数学模型。

In this thesis , the detailed constraints analysis has been done , such as cruise missile 's flight environment , maneuverability , combat tasks , the modeling of threats . Then the mathematical model of constraints ' effect on cruise missile 's flight is developed .

由于巡航导弹在飞行过程中，飞行高度、速度和飞行环境等是时变的，使得导弹动态特性也随之变化，因此，弹体的参数是时变的，普通的线性控制器难以满足系统要求。

As the dynamics characteristics of the cruise missile would change along with the movement of the flight altitude , speed and circumstance , the parameter of the missile body is time variable , the common kind of linear control method is difficult to suit the object .

巡航导弹跨海飞行高度跟踪系统仿真

Height Tracking System Simulation of Cruise Missile Cross Sea Flight

为检验该类系统的技术性能，配合防御作战训练，就需要了解超声速巡航导弹的各种特性，建立能模拟超声速巡航导弹飞行特性的靶弹系统。

In order to test the technology characteristics of the system and cooperate with defense tactical training , all characteristics of SCM should be known , and a target missile system which can simulate flight characteristics of SCM must be built .

根据以上建立的模型，本文重点论述了采用经典控制理论分析此巡航式飞行器控制系统的方法，并计算出此巡航式飞行器飞行控制系统的参数。

According to the models mentioned above , this paper lays emphasis on accounting the method of analyzing and designing the cruise aircraft 's control system adopting the classical control theory , and then calculates the parameters of it .

利用VC、MATLAB软件设计了巡航段最优性能计算程序，并根据某型飞机性能数据进行了仿真运算，生成了优化的巡航段飞行轨迹。

The optimal trajectory computing program written in VC and Matlab is developed , and the optimal flight trajectory for cruise phase is carried out with the performance date of a specific aircraft .