International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Wing Design Optimization of a Solar-HALE Aircraft

  • Lim, JaeHoon (School of Mechanical and Aerospace Engineering, Seoul National University) ;
  • Choi, Sun (School of Mechanical and Aerospace Engineering, Seoul National University) ;
  • Shin, SangJoon (School of Mechanical and Aerospace Engineering/Institute of Advanced Aerospace Technology, Seoul National University) ;
  • Lee, Dong-Ho (School of Mechanical and Aerospace Engineering, Seoul National University)
  • Received : 2013.11.18
  • Accepted : 2014.07.11
  • Published : 2014.09.30
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Abstract

We develop a preliminary design optimization procedure in this paper regarding the wing planform in a solar-powered high-altitude long-endurance unmanned aerial vehicle. A high-aspect-ratio wing has been widely adopted in this type of a vehicle, due to both the high lift-to-drag ratio and lightweight design. In the preliminary design, its characteristics need to be addressed correctly, and analyzed in an appropriate manner. In this paper, we use the three-dimensional Euler equation to analyze the wing aerodynamics. We also use an advanced structural modeling approach based on a geometrically exact one-dimensional beam analysis. Regarding the structural integrity of the wing, we determine detailed configuration parameters, specifically the taper ratio and the span length. Next, we conduct a multi-objective optimization scheme based on the response surface method, using the present baseline configuration. We consider the structural integrity as one of the constraints. We reduce the wing weight by approximately 25.3 % from that in the baseline configuration, and also decrease the power required approximately 3.4 %. We confirm that the optimized wing has sufficient flutter margin and improved static longitudinal/directional stability characteristics, as compared to those of the baseline configuration.

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