航迹角

其次对具有完全非线性特征的慢模态，设计了航迹角跟踪指令飞行控制器。

Afterward a track angle tracking flight controller is designed for the completely non-linear characteristics of the very slow mode .

在铅垂平面内通过俯仰角程序控制以间接控制航迹角，而在侧向平面内则由侧向位置偏差信号生成侧向过载控制指令。

The pitch angle program control is formed to dominate the track angle indirectly in the vertical plane , while in the horizontal plane , the location deviation creates the side over loading control instruction .

这组控制规律通过解耦控制飞机的飞行速度（V）、滚转角（φ）、航迹角（γ）和偏航角（φw），使飞机能够精确地跟踪期望的三维突防航迹。

This control law could guarantee aircraft accurately capturing desired 3-dimension penetration trajectory by decoupling control the flight velocity ( V ) , bank angle (φ), path angle (γ) and yaw angle (ψ w ) .

这里的载体姿态信息包括关于载体飞行速度矢量轴的航迹角和伪滚转角，即伪姿态。

The attitude information consists of flight path angle and roll angle about the aircraft velocity vector axis .

适当地结合规划-跟踪算法和航迹角控制器可给再入制导带来极大的灵活性和适应性。

Proper combination of planning-tracking algorithm and FPA controller can bring great flexibility and adaptability to reentry guidance .

四维下降飞行技术的研究与仿真&定常航迹角法下降剖面解算

The Study and Simulation of the Four-dimensional Descent and Approaching Techniques ── The Profile Computation of the Constant-Flight-Path-Angle Descent

采用航迹角迭代法，讨论了固定时间拦截有限推力初始变轨段的制导问题。

Guidance problem in initial orbit-change stage of fixed-time interception with limited thrust is discussed , using the iteration of the flyout angle .

然后分析了对数螺旋线表达式中的关键参数与航迹角的关系，得到了相应轨道的基本性质；

In addition , essential characteristics of the logarithmic spiral were developed by means of analyzing the relation between the key parameter and flight angle .

此算法另一有别于传统方法的特点在于算法可使用一个航迹角控制器来增加航程，以满足大航程需要。

Another typical feature of this algorithm is the strategy of downrange extension using FPA ( flight path angle ) controller to fulfill the requirement of large downrange .

结果显示无人机的速度、迎角、俯仰角以及航迹角输出均能按照预期的目标渐进跟踪控制指令，并且具有很好的动态响应。

Simulation results for a certain model show that the outputs of velocity , incidence angle , pitching angle , and vertical path angle can asymptotically track the control instruction according to the anticipative target , and have good performances .

本文针对这一事实提出了用直接测定姿态角加计算航迹角间接确定飞机迎角的方法，解决了Y&7飞机失速试飞中的迎角测量问题。

Based on this , the method that determine the AOA indirectly by measuring the pitch angle and estimating flight track angle is proposed . The problem of measurement of AOA in stall speed flight test of Y-7 aircraft is solved .