Have a personal or library account? Click to login
Low-Fidelity Static Aeroelastic Analysis for Jig Shape Optimization of a Solar-Powered Hale Aircraft Wing Cover

Low-Fidelity Static Aeroelastic Analysis for Jig Shape Optimization of a Solar-Powered Hale Aircraft Wing

Transactions on Aerospace Research
Volume 2025 (2025): Issue 2 (June 2025)
By: Pamela Bugała  
Open Access
|Jun 2025

Figures & Tables

Fig. 1.

NASA Helios [11] and Arbus Zephyr Solar High Altitude Platform System [5].
NASA Helios [11] and Arbus Zephyr Solar High Altitude Platform System [5].

Fig. 2.

Diagram of two-way fluid-structure interaction implemented in XAVEL (from [28]).
Diagram of two-way fluid-structure interaction implemented in XAVEL (from [28]).

Fig. 3.

Different levels of structure modelling.
Different levels of structure modelling.

Fig. 4.

Sketches of the jig shape of the solar UAV under analysis. Dihedral angle: 0 deg, −3 deg.
Sketches of the jig shape of the solar UAV under analysis. Dihedral angle: 0 deg, −3 deg.

Fig. 5.

The shape of the MOD-42 airfoil with a flat-upper surface, adopted from [40].
The shape of the MOD-42 airfoil with a flat-upper surface, adopted from [40].

Fig. 6.

Explanation of The D-Box build technology.
Explanation of The D-Box build technology.

Fig. 7.

Uniform structure of the wing along the span.
Uniform structure of the wing along the span.

Fig. 8.

Average wind speeds in m/s vs. altitude in km (figure adapted from [41]).
Average wind speeds in m/s vs. altitude in km (figure adapted from [41]).

Fig. 9.

Lift coefficient vs angle of attack: comparison XAVEL and wind tunnel test (WTT) (from [27]).
Lift coefficient vs angle of attack: comparison XAVEL and wind tunnel test (WTT) (from [27]).

Fig. 10.

Geometry normalized deflection of wing at 8 m/s at sea level.
Geometry normalized deflection of wing at 8 m/s at sea level.

Fig. 11.

Wing geometry at 18 m/s at 20 km for different angles of attack: Deflection (A) and Angle of inclination (B).
Wing geometry at 18 m/s at 20 km for different angles of attack: Deflection (A) and Angle of inclination (B).

Gross specifications of current F1A FAI flyers [38,39]_

Code ClassGeneral TypeBrief Description
F1AGliders (A2 ‘Nordic’)

  • Surface area: 32–34 dm2

  • Minimum weight: 410 g

  • Max length of launching cable: 50 m at 5 kg load with minimum cable pennant area of 2.5 dm2

  • World Championship Class

Wing geometry parameters_

ParameterValue
Span [m]3
Reference area [m2]0.51
Aspect ratio17.65
Mean aerodynamic chord [m]0.17

Flight conditions under analysis and required lift coefficient_

Altitude [km]Air Density [kg/m3]Speed [m/s]Design total lift [N]Angle of attack [deg]Coefficient of Lift
200.089184,940.67
DOI: https://doi.org/10.2478/tar-2025-0008 | Journal eISSN: 2545-2835
Journal RSS Feed
Language: English
Page range: 40 - 56
Submitted on: Mar 12, 2025
Accepted on: May 21, 2025
Published on: Jun 30, 2025
Published by: ŁUKASIEWICZ RESEARCH NETWORK – INSTITUTE OF AVIATION
In partnership with: Paradigm Publishing Services
Publication frequency: 4 issues per year
Keywords:
aeroelasticity,
static aeroelasticity,
HALE,
UAV,
solar-powered.
Related subjects:
Engineering,
Introductions and overviews,
Engineering, other,
Geosciences,
Geosciences, other,
Materials sciences,
Materials sciences, other,
Physics,
Physics, other

© 2025 Pamela Bugała, published by ŁUKASIEWICZ RESEARCH NETWORK – INSTITUTE OF AVIATION
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 License.

Previous articleVolume 2025 (2025): Issue 2 (June 2025)Next article