| 飞翼无人机进舰下滑纵向固有模态特性研究 |
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| 引用本文： | 张旭,韩维,王允良,陈志刚. 飞翼无人机进舰下滑纵向固有模态特性研究[J]. 海军航空工程学院学报, 2016, 31(4): 461-466 |
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| 作者姓名： | 张旭 韩维 王允良 陈志刚 |
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| 作者单位： | 海军航空工程学院研究生管理大队,山东烟台 264001,海军航空工程学院飞行器工程系,山东烟台 264001,海军航空工程学院飞行器工程系,山东烟台 264001,海军航空工程学院飞行器工程系,山东烟台 264001 |
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| 摘 要： | 针对舰载飞翼布局无人机与常规布局飞行器不同的气动外形,建立无人机飞行状态下附近流场的网格模型,并计算了该型无人机的气动参数。基于插值函数计算得出该型无人机的升力系数、阻力系数和俯仰力矩系数对于迎角变化的曲线。建立纵向小扰动方程进行仿真计算,求解出该型无人机在进舰下滑状态时的固有模态特性。计算结果表明,该模型在配平条件下可用于舰载飞翼布局无人机的着舰气动适配性研究。
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| 关 键 词： | 飞翼无人机；进舰下滑；固有模态 |
Intrinsic Mode Characteristic Research on the Flying-Wing UAV During Carrier Landing |
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| ZHANG Xu,HAN Wei,WANG Yunliang and CHEN Zhigang. Intrinsic Mode Characteristic Research on the Flying-Wing UAV During Carrier Landing[J]. Journal of Naval Aeronautical Engineering Institute, 2016, 31(4): 461-466 |
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| Authors: | ZHANG Xu HAN Wei WANG Yunliang CHEN Zhigang |
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| Abstract: | A grid model of flow field around UAV flying was established for the flying-wing configuration different from theconventional configuration aerodynamic shape, and the UAV aerodynamic parameters could be calculated. The lift coeffi.cient, drag coefficient and pitching moment coefficients for angles of attack curve of the UAV by was got the interpolationfunction. The equation of longitudinal direction small-disturbance motion could be simulated, and the natural mode fea.ture of the flying-wing UAV was solved when the UAV was during in carrier landing. The results of the calculation showedthat the model could be used in a simulation research of a carrier landing pneumatic suitability of carrier flying-wing UAVunder trimmed condition. |
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| Keywords: | flying-wing UAV during carrier landing intrinsic mode |
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