真实操纵下直升机降落轨迹参数沙盲抑制优化

doi:10.7527/S1000-6893.2025.32186

Abstract

Abstract:

To analyze the influence of the descent parameters of the helicopter in the dust environment on the brownout in the real state， the Z-3 helicopter is taken as the research object. Firstly， the free wake method considering the influence of in ground effect is used to calculate the rotor aerodynamic force. The dynamic model of the helicopter is established by components， and the appropriate feature points are selected for trim and small disturbance linearization. Then， based on the trajectory tracking cascade control system and the model switching method， the control quantity and state quantity of the helicopter descent process are obtained. On this basis， the flow field of the descent process is discretized， and the sand field of the descent process is obtained by combining the sand field calculation method， and the visual influence of the sand field on the driver is obtained. Based on the above process， the Kriging surrogate model method is used to establish the mapping relationship model between the helicopter descent parameters and the brownout effect in the real descent state， and the genetic algorithm is used to optimize the descent parameters of the brownout suppression effect of this model. The results show that the proposed method can effectively simulate the control quantity and state quantity of the real helicopter flight process， and obtain the real flow field and brownout situation of the helicopter take-off and landing process. Near-ground tangential airflow tends to raise sand， but brownout effects must be assessed comprehensively based on the overall flow field. For the Z-3 helicopter， a faster vertical descent speed can reduce the amount of sand， but may cause greater sand uplift and retention. Descent profiles such as oblique descent or spatial curve are more effective in brownout suppression. After optimization， the sand concentration of vertical descent， oblique descent and two kinds of spatial curve descent is reduced by 13.41%， 17.52%， 16.45% and 3.44% respectively compared with the sand concentration of vertical benchmark descent.

Key words: free wake method, in ground effect, dynamic model, brownout, trajectory tracking, surrogate model, parameter optimization

CLC Number:

V211.52

Zhuangzhuang CUI, Binwu REN, Xu ZHOU, Zhe CHEN, Guoqing ZHAO. Brownout suppression optimization of helicopter landing trajectory parameters under real control[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(S1): 732186.

Figures/Tables 20

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References 22

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参数	数值
旋翼半径/m	1.57
旋翼桨叶片数	2
旋翼桨叶弦长/m	0.13
旋翼翼型	OA212
旋翼桨叶负扭/（°）	-6
尾桨半径/m	0.275
尾桨桨叶片数	2
尾桨桨叶弦长/m	0.10
尾桨翼型	NACA2408
尾桨负扭/（°）	0

下降方式	下降时间范围/s	前飞距离范围/m	最终/最大偏移距离范围/m
垂直下降方式	［5，16］
斜下降方式	12	［5，25］
空间曲线下降方式1	12	［5，20］	［0，7］
空间曲线下降方式2	12	［5，20］	［0，7］

下降方式	状态参数	视觉提示临界区沙团数量	与基准值的对比/%
基准下降方式	下降6.5 s	2 844.81
垂直下降方式	下降15.95 s	2 463.30	-13.41
斜下降下降方式	前进19.8 m	2 346.52	-17.52
空间曲线下降方式1	（11.62，4.57） m	2 376.76	-16.45
空间曲线下降方式2	（6.13，0.74） m	2 747.06	-3.44

Brownout suppression optimization of helicopter landing trajectory parameters under real control

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