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首页> 外文期刊>Journal of aerospace engineering >Computational Fluid Dynamic Study on a Novel Propulsive System: ACHEON and Its Integration with an Unmanned Aerial Vehicle (UAV)
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Computational Fluid Dynamic Study on a Novel Propulsive System: ACHEON and Its Integration with an Unmanned Aerial Vehicle (UAV)

机译：新型推进系统的计算流体动力学研究：ACHEON及其与无人飞行器（UAV）的集成

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In the present paper, numerical investigations are carried out in a newly proposed propulsive system Aerial Coanda high-efficiency orienting jet nozzle (ACHEON), which supports thrust vectoring and its application to prototype unmanned aerial vehicles (UAVs). The ACHEON system is presently being proposed for propelling a new vertical and short takeoff (V/STOL) airplane in the European Union. This system is powered by two axial electric turbofans and uses the Coanda effect (attachment of the jet to a curved surface) to achieve precise control of the thrust angle. The present study investigates the thrust vectoring efficiency of this newly patented nozzle and its integration with UAVaircraft. This study numerically investigates the 3D effects on this new machine and proposes remedies to solve the associated problems. Further, swirling effects generated by electric turbofans were studied in great detail. The effect of uniform and nonuniform velocity profiles were investigated on thrust vectoring efficiency of the nozzle. Then, the aerodynamic features of prototype UAVs were determined under various flow conditions. The interaction of the exit nozzle flow with incoming airstream was studied. Computational fluid dynamics (CF) calculations were carried out using Reynolds averaged Navier-Stokes (RANS) equations. A numerical method based on finite volume formulation (FVM) was used. Turbulent flow is modeled by using the SST k-omega model. Numerical results show that the presence of swirling velocities in the flow field significantly affects the thrust vectoring efficiency of the nozzle. From numerical simulations of the aircraft, it was found that the aerodynamic characteristics are strongly affected by the exit air jet angle. (C) 2015 American Society of Civil Engineers.
机译：在本文中，数值研究是在一个新提出的推进系统空中柯恩达高效定向射流喷嘴（ACHEON）中进行的，该系统支持推力矢量化及其在无人飞行器原型中的应用。目前正在提议使用ACHEON系统来推动欧盟的新型垂直和短距起飞（V / STOL）飞机。该系统由两个轴向电动涡轮风扇提供动力，并利用柯恩达效应（将射流附接到曲面）来实现对推力角的精确控制。本研究调查了该新专利喷嘴的推力矢量效率及其与UAVaircraft的集成。这项研究通过数值研究了这种新机器上的3D效果，并提出了解决相关问题的补救措施。此外，还对电动涡轮风扇产生的旋流效应进行了详细研究。研究了均匀和不均匀速度分布对喷嘴推力矢量效率的影响。然后，在各种流动条件下确定了原型无人机的空气动力学特征。研究了出口喷嘴流与进气流的相互作用。使用雷诺平均Navier-Stokes（RANS）方程进行计算流体动力学（CF）计算。使用了基于有限体积公式（FVM）的数值方法。湍流是通过使用SSTk-ω模型建模的。数值结果表明，流场中旋流速度的存在显着影响喷嘴的推力矢量效率。通过飞机的数值模拟，发现空气动力学特性受出口空气射流角度的强烈影响。 （C）2015年美国土木工程师学会。

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