Wing Design Optimization of a Solar-HALE Aircraft

Abstract

We develop a preliminary design optimization procedure in this paper regarding the wing planform in a solar-powered highaltitude 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. A preliminary design optimization procedure was developed in this paper regarding the wing planform in a solar-powered high-altitude long-endurance unmanned aerial vehicle. Due to both a high lift-to-drag ratio and a lightweight design, a high-aspect-ratio wing has been widely adopted in this type of a vehicle. Its characteristics need to be addressed correctly and analyzed in an appropriate manner in the preliminary design. In this paper, the three-dimensional Euler equation was used to analyze the wing aerodynamics. An advanced structural modeling approach based on a geometrically exact one-dimensional beam analysis was also used. Regarding the structural integrity of the wing, detailed configuration parameters were determined, specifically the taper ratio and the span length. Next, a multi-objective optimization scheme based on the response surface method was conducted using the present baseline configuration. The structural integrity was considered as one of the constraints.

Experimental Evaluation of the Critical Flutter Speed on Wings of Different Aspect Ratio

“…surveillance, emergency, etc.). Modern HALE aircraft design uses High Aspect Ratio Wings (HARWs) that are flexible to increase their lift and endurance (Lim et al (2014)). In contrast, HARWs have higher potential to flow induced vibration known as "flutter" and the associated instabilities (Tang and Dowell (2002)).…”

Descriptive analysis of viability of fuel saving in commercial aircraft through the application of photovoltaic cells

“…In recent years there have been done developments on airships, with the resurgence of these vehicles as a viable alternative of multipurpose platforms [35,36]. Several models and studies regarding the application of PV technology to airships were developed by [37][38][39][40][41][42][43]. These models can be extrapolated to the analysis of non-stratospheric aircrafts, such as radiation models [41], thermal behavior of the solar panels models [42], design and management of hybrid systems models, among others.…”