旋转机翼飞机旋翼模式前飞状态干扰气动特性
收稿日期: 2016-01-13
修回日期: 2016-03-14
网络出版日期: 2016-03-23
基金资助
国家自然科学基金（11372254）
Interactive aerodynamic characteristics of canard rotor wing aircraft in helicopter forward flight
Received date: 2016-01-13
Revised date: 2016-03-14
Online published: 2016-03-23
Supported by
National Natural Science Foundation of China (11372254)
和传统直升机相比，旋转机翼（CRW）飞机在旋翼模式前飞时各部件之间存在更为严重的气动干扰。为了获得旋转机翼/机身/鸭翼/平尾之间的非定常气动干扰规律，基于运动嵌套网格技术，通过求解三维非定常雷诺平均Navier-Stokes（URANS）方程，建立了旋翼前飞流场数值模拟方法。首先对传统直升机旋翼/机身干扰模型进行了计算，验证了方法的可靠性，然后对某旋转机翼飞机全机在旋翼模式前飞状态下的非定常流场进行了数值模拟，并对各个气动部件上的非定常气动力和力矩的变化进行了分析。结果表明：飞机在旋翼模式前飞时，机身部件对旋转机翼的干扰较弱，在经过机身上方时拉力峰值仅略有增加；旋转机翼对鸭翼和垂尾干扰较弱，对机身和平尾干扰较强，随着前飞速度增大，旋转机翼对平尾的干扰会产生较大的升力损失和抬头力矩，需要引起重视。计算结果为该类飞行器的总体综合设计提供了参考。
孙威 , 高正红 , 姜杰出 . 旋转机翼飞机旋翼模式前飞状态干扰气动特性[J]. 航空学报, 2016 , 37(8) : 2498 -2506 . DOI: 10.7527/S1000-6893.2016.0092
Compared with the traditional helicopter, the aerodynamic interaction of rotor wing, fuselage, canard and horizontal tail of canard rotor wing (CRW) aircraft in forward flight is severer. In order to get better understanding of the unsteady aerodynamic interaction, the moving structural chimera grid is used to model the moving rotor and three-dimensional unsteady Reynolds averaged Navier-Stokes (URANS) equations are solved to simulate the flow fields of rotor in forward flight. The traditional helicopter's rotor-body interaction model is computed first to validate the method. Then the analyses on rotor wing/fuselage/canard/horizontal tail/vertical tail interactive flow field for an unmanned CRW aircraft in helicopter forward flight are given using the present method. The variations of unsteady aerodynamic forces and moments of the rotor-wing, fuselage, canard, horizontal tail and vertical tail with respect to the rotor azimuth are obtained. The result shows that the fuselage and other components have little effect on the rotor wing, resulting in a slight increase in thrust; the rotor wing has almost no impact on the aerodynamics of canard and vertical tail, but does have strong interference on fuselage and horizontal tail. The horizontal tail produces large vertical force and nose-up pitching moment as the forward flight speed increases, to which great attention should be paid. The research could provide some guidance for the design of a CRW aircraft.
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