Volume 37, Number 6, December 2019
|Page(s)||1138 - 1147|
|Published online||11 February 2020|
Helicopter Landing Trajectory Optimization after Tail Rotor Control Failure in Different Collective Pitch
National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2 China Helicopter Design and Research Institute, Tianjin 300000, China
This paper studies helicopter optimal landing and control procedure after tail rotor control failure (TRCF) in different collective pitch. The optimal control problem of landing after tail rotor control failure was solved numerically by direct multiple shooting method and sequential quadratic programming. A sample helicopter optimal landing procedures after tail rotor control failure in large collective pitch and small collective pitch were investigated respectively. As can be seen from the results, when the tail rotor is stuck at large collective pitch, the tail rotor provides a large lateral force, which facilitates landing with small forward speed and descent rate in a large power state. The pilot can maintain stability of heading by side slipping. When the tail rotor is stuck at small collective pitch, the tail rotor provides a small lateral force, which is favorable for flying near economic speed, but difficult for a safe landing. A normal landing maneuver will cause a high yaw rate at touchdown, which is dangerous. Therefore, autorotation is preferred during touchdown because the landing is more secure with small yaw rate. The trajectory optimization method of helicopter safe landing after tail rotor control failure can provide a reference for flight test.
Key words: helicopter / tail rotor control failure / flight dynamics model / optimal control / autorotation
关键字 : 直升机 / 尾桨距卡滞 / 飞行动力学模型 / 最优控制问题 / 自转着陆
© 2019 Journal of Northwestern Polytechnical University. All rights reserved.
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