基于航迹的飞机姿态角建模与仿真  

Modeling and simulation of aircraft attitude angle based on air-path

作　　者：袁修久[1] 赵学军[1] 李嘉林[1] 

机构地区：[1]空军工程大学理学院,陕西西安710051

出　　处：《系统工程与电子技术》2016年第4期889-894,共6页Systems Engineering and Electronics

基　　金：国家自然科学基金(11371369);陕西省重点实验室基金(2014zd06)资助课题

摘　　要：基于飞机的动力学方程、运动学方程等给出了用航迹向量函数一阶、二阶导数计算飞机姿态角的方法。重点讨论了飞机气流倾斜角的计算方法。首先给出了气流倾斜角正切的计算公式,然后利用飞机在飞行过程中,左右翼下沉与航迹曲线主法向向量的指向之间的关系,给出了确定气流倾斜角正负号的方法,在此基础上给出了飞机气流倾斜角的计算公式。利用该公式推导了斜平面上飞机做变加速圆周运动气流倾斜角的计算公式。通过对比六自由度飞机运动模型姿态角的计算结果,验证了姿态角计算公式的有效性。The aircraft attitude angle calculation formulae represented by one order and two order derivatives of the air-path vector function are derived by using the aircraft dynamic equation,the aircraft kinematics equation and so on.The calculation formula of air-path bank angle of an aircraft is discussed.First of all,the calculation formula of the tangent of an air-path bank angle is derived,then a method of determining the sign of the air-path bank angle is established by using the relationship between the left wing or right wing sinking and direction of the principal normal vector of the air-path vector function.On the basis of them,the calculation formula of air-path bank angle of an aircraft is given.By using the derived formula,the air-path bank angle calculation formula of varying accelerated circular motion of an aircraft in the oblique plane is provided.Compared with the attitude angle calculation results of the six-degree-of-freedom aircraft kinematics model,the effectiveness of these attitude angle calculation formulae is verified.

关 键 词：航迹 姿态角 气流倾斜角 迎角 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]