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论文:2016,Vol:34,Issue(5):747-753 |
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引用本文： |
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许军, 马晓平. 飞翼无人机静气弹参数分析及操纵效率计算[J]. 西北工业大学学报 |
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Xu Jun, Ma Xiaoping. Flying Wing UAV Static Aeroelastic Parameter Analysis and Control Efficiency Calculation[J]. Northwestern polytechnical university |
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| 飞翼无人机静气弹参数分析及操纵效率计算 |
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| 许军1,2, 马晓平3 |
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1. 西北工业大学 航空学院, 陕西 西安 710072;
2. 中国电子科技集团公司第三十八研究所 浮空平台部, 安徽 合肥 230088;
3. 西北工业大学 无人机所, 陕西 西安 710065 |
| 摘要: |
| 耦合流体控制方程与结构动力学方程求解飞翼式无人机的静气动弹性参数响应及不同舵面的操纵效率。首先通过气动结构松耦合技术研究了飞翼无人机静气动弹性响应，对比分析刚性与弹性气动特，分析高度、马赫数、迎角及侧滑角对静气动弹性的影响；其次研究单一舵面偏转与组合舵面偏转的静气弹性，并分析结构几何非线性对静气动弹性的影响；然后分析阻力方向舵开裂角对静气弹的影响；最后计算不同马赫数不同舵面的操纵效率。研究表明迎角增大位移幅值也增大，不同高度位移响应频率形式是一样的，侧滑角对无人机半模静气动弹性响应并没有影响；开裂角增大位移幅值减小，且振荡收敛时间越短；方向舵操纵效率与组合舵面操纵效率相比差异较小，组合舵面操纵效率与单一舵面相比较高，不同组合舵面操纵效率比较接近。 |
| 关键词:
飞翼无人机
静气动弹性
CFD/CSD
操纵效率
阻力方向舵
开裂角
弹性变形
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| Flying Wing UAV Static Aeroelastic Parameter Analysis and Control Efficiency Calculation |
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| Xu Jun1,2, Ma Xiaoping3 |
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1. College of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. Department of Aerostat Platform, No. 38 Research Institute of CETC, Hefei 230088, China;
3. UAV Research Institute, Northwestern Polytechnical University, Xi'an 710065, China |
| Abstract: |
| The flying wing UAV static aeroelastic parameters responses and different rudders control efficiency, based on the fluid control equation and structural dynamics equation coupling model, were solved. Firstly the flying wing UAV static aeroelastic responses based on the aerodynamic structural loosely coupling method were studied, the rigid and elastic aeordynamic characteristic were analysis, the effect of height, Mach numbers, attack angle, sideslip angle on the static responses were also analysis. Secondly the single rudder and combination rudders deflection static aeroelastic were given, and the linear and nonlinear on the static aeroelastic responses were also studied. And then effect of rudder crack initiation angles on the static aeroelastic were given; Finally different rudders control efficiency at different Mach numbers were calculated. The research results showed that:(1) the displacement amplitude increased as the attack angle increased, the displacement response frequency was the same at different heights, and the sideslip angle had no effect on the UAV semi model static aeroelastic responses; (2) the displacement amplitude decreased as the cracking angle increased, and the oscillation convergence time was shorter; (3) the rudder control efficiency were closed to the combination rudders control efficiency, which had higher control efficiency compared with the single rudder, and the different rudders control efficiency were almost the same. |
| Key words:
flying wing UAV
static aeroelasticity
CFD/CSD
control efficiency
drag rudder
crack initiation angle
elastic deformation
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| 收稿日期: 2016-03-17
修回日期:
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| DOI: |
| 基金项目: 陕西省自然科学基金（2013JM015）资助 |
| 通讯作者:
Email： |
| 作者简介: 许军(1987-),西北工业大学工程师,主要从事无人机总体及气动弹性的研究。
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| 作者相关文章 |
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| 许军 在本刊中的所有文章 |
| 马晓平 在本刊中的所有文章 |
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相关文献: |
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1．许军, 马晓平.飞翼无人机嗡鸣气动弹性响应分析[J]. 西北工业大学学报, 2015,33(4): 588-595 |
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