| 高空飞艇螺旋桨优化设计与气动性能车载试验 |
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| 引用本文： | 焦俊,宋笔锋,张玉刚,李育斌.高空飞艇螺旋桨优化设计与气动性能车载试验[J].航空动力学报,2017,32(1):196-202. |
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| 作者姓名： | 焦俊 宋笔锋 张玉刚 李育斌 |
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| 作者单位： | 西北工业大学 航空学院,西安 710072 |
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| 基金项目： | 国家自然科学基金（11402204） |
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| 摘 要： | 结合某高空飞艇螺旋桨的总体设计方案要求,完成螺旋桨的优化设计以及气动性能车载试验.采用叶素动量理论作为螺旋桨气动性能的计算方法,并通过风洞试验验证了该方法的可靠性.结合遗传算法对螺旋桨的弦长和扭转角进行了优化,使螺旋桨更加高效轻质,优化后螺旋桨设计点的气动效率增加了2.3%.建立螺旋桨车载试验测控系统,可以改变试验海拔高度和大气参数,得到优化设计螺旋桨不同工况的气动性能.试验结果表明,相同转速和来流条件下,海拔越高,螺旋桨的推力和扭矩越小.海拔为3-6km时,全尺寸高空飞艇螺旋桨计算推力和扭矩与试验结果的平均相对误差分别为2.8%和9.2%,两者基本吻合,从而验证了高空飞艇螺旋桨车载试验的准确性.
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| 关 键 词： | 航空发动机 燃烧室高空飞艇 螺旋桨 叶素动量理论 罚函数 优化设计 车载试验 |
| 收稿时间： | 2015/4/16 0:00:00 |
Optimal design and truck mounted testing of aerodynamic performance for the propeller of high altitude airship |
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| JIAO Jun,SONG Bi-feng,ZHANG Yu-gang,LI Yu-bin.Optimal design and truck mounted testing of aerodynamic performance for the propeller of high altitude airship[J].Journal of Aerospace Power,2017,32(1):196-202. |
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| Authors: | JIAO Jun SONG Bi-feng ZHANG Yu-gang LI Yu-bin |
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| Abstract: | Considering the overall requirements of the propeller of a high altitude airship, the propeller was optimized and a truck mounted testing of aerodynamic performance was carried out. The blade element momentum theory was used to calculate the aerodynamic performance of propeller and verify it by wind tunnel test. By combining blade element momentum theory with genetic algorithm, the chord and twist angle of the original propeller can be optimized, making the propeller more efficient and lightweight,and the aerodynamic efficiency at design point of propeller increased by 23%. Then, a truck mounted testing system was proposed and applied into the acquired propeller test in different altitudes and atmosphere parameters, and the aerodynamic performance of optimized propeller at different conditions was acquired. The results obtained from the truck mounted testing for the propeller of high altitude airship show that the higher altitude means the smaller thrust and torque with the same rotational speed and free flow. The average relative error of the thrust and torque of the full scale propeller are 28% and 92% at altitude of 36km. Thus, the test results are in good agreement with the numerical simulation, verifying the accuracy of the system. |
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| Keywords: | aero engine combustorhigh altitude airship propeller blade element momentum theory penalty method optimal design truck mounted testing |
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