CAJ | 학술논문

新型旋翼气囊复合动力无人飞行器在总体设计方案的基础上，应用了变距旋翼技术。本文以参考旋翼模型为研究对象，利用Spalart-Allmaras湍流模型，采用三维Navier-Stokes方程，并通过数值模拟研究不同旋翼翼型的转速、桨距角在悬停状态下的气动特性。经过对比拉力系数、扭矩系数以及悬停效率，得到马刀型旋翼在6000r/min，桨叶角12°具有最大的悬停效率，并且计算结果与试验结果吻合良好。为旋翼气囊无人飞行器的整体优化以及工程应用提供了参考依据。
신형선익기낭복합동력무인비행기재총체설계방안적기출상，응용료변거선익기술。본문이삼고선익모형위연구대상，이용Spalart-Allmaras단류모형，채용삼유Navier-Stokes방정，병통과수치모의연구불동선익익형적전속、장거각재현정상태하적기동특성。경과대비랍력계수、뉴구계수이급현정효솔，득도마도형선익재6000r/min，장협각12°구유최대적현정효솔，병차계산결과여시험결과문합량호。위선익기낭무인비행기적정체우화이급공정응용제공료삼고의거。
Based on the overall design scheme, variable pitch rotor technology is applied to unmanned aerial vehicles. In this paper,the reference rotor is the objective of the study. Effects of different airfoils on hovering aerodynamic performance were simulated by changing rotation speeds and pitch angles, and its aerodynamic characteristics were analyzed, in which the three-dimensional Navier-Stokes equations and Spalart-Allmaras turbulence model was used. Comparisons of lift coefifcient, torque coefifcient and rotor hover efifciency in 6000r/min, pitch angle of 15 degree. The simulation results are in good agreement with test results, and provides reference basis for the whole optimization of unmanned aerial vehicle compounded by rotor and gas bag and the engineering application.