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

Pamela Bugała

Pamela Bugała

Łukasiewicz Research Network – Institute of AviationWarsaw, Poland
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Bugała, Pamela
  
30 cze 2025
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Data publikacji: 30 cze 2025
Zakres stron: 40 - 56
Otrzymano: 12 mar 2025
Przyjęty: 21 maj 2025
DOI: https://doi.org/10.2478/tar-2025-0008
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© 2025 Pamela Bugała, published by Sciendo
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

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 Class General Type Brief Description
F1A Gliders (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_

Parameter Value
Span [m] 3
Reference area [m2] 0.51
Aspect ratio 17.65
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
20 0.089 18 4,9 4 0.67
Język:
Angielski
Częstotliwość wydawania:
4 razy w roku
Dziedziny czasopisma:
Inżynieria, Wstępy i przeglądy, Inżynieria, inne, Nauki o Ziemi, Nauki o Ziemi, inne, Nauka o materiałach, Nauka o materiałach, inne, Fizyka, Fizyka, inne
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