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论文:2019,Vol:37,Issue(6):1138-1147 |
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引用本文： |
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严旭飞, 陈仁良, 辛冀. 直升机不同尾桨距卡滞后的着陆轨迹和操纵优化[J]. 西北工业大学学报 |
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YAN Xufei, CHEN Renliang, XIN Ji. Helicopter Landing Trajectory Optimization after Tail Rotor Control Failure in Different Collective Pitch[J]. Northwestern polytechnical university |
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| 直升机不同尾桨距卡滞后的着陆轨迹和操纵优化 |
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| 严旭飞1, 陈仁良1, 辛冀2 |
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1. 南京航空航天大学 直升机旋翼动力学国家级重点实验室, 江苏 南京 210016;
2. 中国直升机设计研究所, 天津 300000 |
| 摘要: |
| 计算并分析直升机遭遇不同尾桨距卡滞后的最优安全着陆和操纵过程。首先，将直升机不同尾桨距卡滞后的安全着陆问题表示成最优控制问题。然后，采用直接多重打靶法将最优控制问题离散为非线性规划问题，并进行数值求解。最后，分别计算样例直升机遭遇大尾桨距卡滞与小尾桨距卡滞后的最优安全着陆过程和操纵策略。结果表明：当尾桨卡滞在大桨距时，尾桨提供侧向力大，有利于使用较大的功率状态以较小的速度和下降率着陆，期间可以通过侧滑来保持航向稳定；当尾桨卡滞在小桨距时，尾桨提供侧向力小，有利于在经济速度附近飞行，但不利于着陆机动。若此时采用常规着陆，则触地时偏航角速度很大，容易造成危险。若此时采用自转着陆，则触地时偏航角速度很小，因此着陆更为安全。直升机尾桨距卡滞后安全着陆的轨迹优化方法可以得到直升机遭遇不同尾桨距卡滞后的最优着陆轨迹和操纵，从而为尾桨距卡滞飞行试验提供一定的参考。 |
| 关键词:
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
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| Helicopter Landing Trajectory Optimization after Tail Rotor Control Failure in Different Collective Pitch |
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| YAN Xufei1, CHEN Renliang1, XIN Ji2 |
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1. 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 |
| Abstract: |
| 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
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| 收稿日期: 2018-11-02
修回日期:
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| DOI: 10.1051/jnwpu/20193761138 |
| 基金项目: 国家自然科学基金（11672128）资助 |
| 通讯作者:
Email： |
| 作者简介: 严旭飞(1990-),南京航空航天大学博士研究生,主要从事直升机飞行力学与控制、直升机空气动力学研究。
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| 作者相关文章 |
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| 严旭飞 在本刊中的所有文章 |
| 陈仁良 在本刊中的所有文章 |
| 辛冀 在本刊中的所有文章 |
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