摘要
本文给出了一种直升机机动飞行的逆模拟方法以计算跟随预定飞行轨迹的驾驶员操纵。根据这一方法可以确定为完成直升机机动飞行所需的驾驶员操纵输入及直升机的飞行速度、角速度和飞行姿态的变化历程。直升机飞行动力学模型没有作任何线化假设，其中考虑了旋翼入流的时滞效应、前行桨叶的压缩性和后行桨叶的失速特性及旋翼桨叶的非定常挥舞运动，引入了旋翼尾迹对直升机机身、尾翼和尾桨的气动干扰。最后以黑鹰直升机为例计算了鱼跃越障机动飞行时驾驶员操纵输入及直升机速度、角速度和飞行姿态的变化规律。
This paper presents an inverse simulation algorithm of determining the pilot control law as well as the time histories of helicopter velocity, angular velocity and flight altitudes to follow a given helicopter maneuver flight path. Many factors were considered in the algorithm such as the helicopter nonlinear flight dynamic model, the time delay of rotor wake, the air compressibility at advancing blade, the stall of retreating blade, the unsteady flapping motion of rotor blades and the aerodynamic interaction among rotor, fuselage, tail rotor and empennage. The validation of the inverse simulation algorithm was made by input the pilot control law to follow the given Dolphin maneuver flight path of Black Hawk helicopter. In addition, a series of reasonable time histories of helicopter velocity, angular velocity and flight attitude were shown during the given Dolphin maneuver flight.
出处
《空气动力学学报》
CSCD
北大核心
1999年第3期339-345,共7页
Acta Aerodynamica Sinica
