| 三轴承偏转喷管驱动力矩计算及动态特性分析 |
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| 引用本文： | 刘帅,王占学,周莉,刘增文.三轴承偏转喷管驱动力矩计算及动态特性分析[J].航空动力学报,2016,31(12):2851-2858. |
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| 作者姓名： | 刘帅 王占学 周莉 刘增文 |
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| 作者单位： | 西北工业大学 动力与能源学院, 西安 710072,西北工业大学 动力与能源学院, 西安 710072,西北工业大学 动力与能源学院, 西安 710072,西北工业大学 动力与能源学院, 西安 710072 |
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| 基金项目： | 国家自然科学基金（51306151，51576163） |
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| 摘 要： | 基于三轴承偏转喷管（3BSN）运动规律模型及给定的三轴承偏转喷管偏转规律，建立三轴承偏转喷管各段旋转喷管的驱动力矩计算模型.分别对3段旋转喷管进行了受力分析，得出了喷管重力及燃气气动力对各段喷管旋转瞬轴的力矩随喷管偏转角度的变化规律.改变喷管可实现最大偏转角度及第2，3段喷管长度得出了喷管几何参数对各段喷管旋转瞬轴力矩的影响.第2，3段喷管气动力对喷管旋转瞬轴的最大力矩随喷管可实现最大偏转角度的增大而增大，且位置发生在最大偏转角度的约70%角度位置.第2，3段喷管气动力对喷管旋转瞬轴的力矩随第2，3段喷管长度的增加而增大.
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| 关 键 词： | 三轴承偏转喷管 短距/垂直起降 力矩 偏转规律 动态特性 |
| 收稿时间： | 2015/4/14 0:00:00 |
Calculation and dynamic characteristics analysis for the driving moment of three bearing swivel nozzle |
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| LIU Shuai,WANG Zhan-xue,ZHOU Li and LIU Zeng-wen.Calculation and dynamic characteristics analysis for the driving moment of three bearing swivel nozzle[J].Journal of Aerospace Power,2016,31(12):2851-2858. |
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| Authors: | LIU Shuai WANG Zhan-xue ZHOU Li and LIU Zeng-wen |
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| Institution: | School of Power and Energy, Northwestern Polytechnical University, Xi''an 710072, China,School of Power and Energy, Northwestern Polytechnical University, Xi''an 710072, China,School of Power and Energy, Northwestern Polytechnical University, Xi''an 710072, China and School of Power and Energy, Northwestern Polytechnical University, Xi''an 710072, China |
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| Abstract: | The dirving moment calculation model of each nozzle segment of the three bearing swivel nozzle(3BSN) was built based on the deflection law model and the given deflection law of the 3BSN. The changing law of the moment produced by each nozzle segment''s gravity and gas aerodynamic force to the instantaneous rotation axis with the varying nozzle deflection angle was obtained by respective force analysis for each nozzle segment. The effect of the nozzle geometrical parameters on the moment to the nozzle instantaneous rotation axis was obtained by changing the realizable maximum nozzle deflection angle and the length of the second and third nozzle segments. The maximum moment of the second and third nozzle segments'' aerodynamic force to the instantaneous rotation axis increased with the realizable maximum deflection angle of the nozzle and occurred at the location in approximately 70% of the maximum deflection angle. The moment of the second and third nozzle segments'' aerodynamic force to the instantaneous rotation axis increaseed with the nozzle segment''s length increases. |
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| Keywords: | three bearing swivel nozzle short/vertical takeoff and landing moment deflection law dynamic characteristics |
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