首页|Seamless morphing trailing edge flaps for UAS-S45 using high-fidelity aerodynamic optimization

Seamless morphing trailing edge flaps for UAS-S45 using high-fidelity aerodynamic optimization

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The seamless trailing edge morphing flap is investigated using a high-fidelity steady-state aerodynamic shape optimization to determine its optimum configuration for different flight condi-tions,including climb,cruise,and gliding descent.A comparative study is also conducted between a wing equipped with morphing flap and a wing with conventional hinged flap.The optimization is performed by specifying a certain objective function and the flight performance goal for each flight condition.Increasing the climb rate,extending the flight range and endurance in cruise,and decreasing the descend rate,are the flight performance goals covered in this study.Various opti-mum configurations were found for the morphing wing by determining the optimum morphing flap deflection for each flight condition,based on its objective function,each of which performed better than that of the baseline wing.It was shown that by using optimum configuration for the morphing wing in climb condition,the required power could be reduced by up to 3.8％and climb rate increases by 6.13％.The comparative study also revealed that the morphing wing enhances aerody-namic efficiency by up to 17.8％and extends the laminar flow.Finally,the optimum configuration for the gliding descent brought about a 43％reduction in the descent rate.

Seamless morphing trailing edge flapAerodynamic optimizationGradient-based optimiza-tionClimb flight conditionGliding descentFlight rangeEndurance

Mir Hossein NEGAHBAN、Musavir BASHIR、Victor TRAISNEL、Ruxandra Mihaela BOTEZ

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LARCASE Laboratory of Applied Research in Active Controls,Avionics and Aeroservoelasticity,École de Technologie Supérieure,Université du Québec,Montreal H3C1K3,Canada

Natural Sciences and Engineering Research Council of Canada(NSERC)bears special recognition for providing fundingHydra Technologies team in Mexico and the CREATE-UTILI Program

2024

10.1016/j.cja.2023.10.024

中国航空学报(英文版)
中国航空学会

中国航空学报(英文版)

CSTPCDEI
影响因子：0.847
ISSN：1000-9361
年,卷(期)：2024.37(2)
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