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高空长航时太阳能无人机具有飞行雷诺数低、结构柔性大等设计特点,在气动力设计时,一般采用单设计点的设计思想,即在预定设计状态下具有较为优异的气动特性,但稍微偏离该设计点时,将显著地削弱其气动力特性,为其高效气动力设计带来诸多新挑战。本文首先简要回顾了太阳能飞机的发展历程,并分析了该类飞机的设计特点;随后,重点介绍了该类飞机的高效低雷诺数气动力设计面临的挑战及机翼气动弹性效应对全机气动力特性的影响;最后,分析展望了缩比自由飞验证技术在该类飞机高效气动力设计中的应用。
The high-altitude long-haul solar UAVs have the characteristics of low Reynolds number of flight, large structural flexibility and so on. In the design of aerodynamic forces, the design concept of single design point is generally adopted, that is, the aerodynamic characteristics are superior under the predetermined design state. However, A slight deviation from this design point will significantly weaken its aerodynamic properties, creating many new challenges for its high-efficiency aerodynamic design. This paper briefly reviews the development history of solar powered aircraft and analyzes the design features of this type of aircraft. Subsequently, the challenges of the high efficiency and low Reynolds number aerodynamic design of the aircraft and the effects of aeroelasticity on the whole air Finally, the application of the reduced-ratio free-flight verification technology to the high-efficiency aerodynamic design of such aircraft is prospected.