速度矢量滚转的运动学及气动力分析  

Kinematics and Aerodynamics of the Velocity Vector Roll

作　　者：张勇[1] 

机构地区：[1]沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《飞机设计》2014年第6期7-12,共6页Aircraft Design

摘　　要：速度矢量滚转定义为飞机在保持定常迎角的情况下,围绕其瞬时速度矢量所产生的无侧滑、速度保持为常值的旋转运动。对于典型的战术飞机,最大俯仰力矩是飞机方位的函数,在水平轨迹中出现在倾斜90°的情况,此时飞机的滚转速率达到峰值,迎角超过45°。最大滚转力矩依赖于滚转模态时间常数。对于较小的滚转时间常数(快速响应),最大滚转力矩出现在最大滚转加速度、零迎角,基本与飞机的方位无关;对于较大的滚转时间常数,最大滚转力矩出现在最大滚转速率、迎角最大、倾斜角180°的水平飞行中。最大的航向力矩出现在最大滚转加速度、迎角最大时,基本与飞机的方位无关。The velocity vector roll is defined as angular rotation of airplane about its instantaneous velocity vector, constrained to be performed at constant angle-of-attack, no sideslip, and constant velocity. It is shown, for representative tactical airplanes, the conditions of maximum pitching moment are strongly a function of the orientation of airplane, occurring at about 90° of bank in a level trajectory. Maximum required pitching moment occurs at peak roll rate and is achieved at an angle- of-attack in excess 45°. The conditions for maximum rolling moment depend on the value of the roll mode time constant. For a small roll constant （fast response） the maximum rolling moment occurs at maximum roll acceleration and zero angle-of-attack, largely independent of airplane orientation; for a large time constant, maximum rolling moment occurs at maximum roll rate, at maximum angle- of-attack, and 180° of bank in level flight. The maximum yawing moment occurs at maximum roll acceleration, maximum angle-of-attack, and largely independent of airplane orientation.

关 键 词：飞机 速度矢量 滚转 滚转力矩 气动力 

分 类 号：V215-3[航空宇航科学与技术—航空宇航推进理论与工程]