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Estimation Method for Pitching Moment Non-linearities of Cranked Arrow Wing at Low Speed
Hiroki Ishibashi,Taro Imamura,Kenichi Rinoie 한국항공우주학회 2022 International Journal of Aeronautical and Space Sc Vol.23 No.4
Cranked arrow wing is a wing planform often used for supersonic transport (SST) to satisfy both low-speed characteristics during takeoff/landing and supersonic flight characteristics. During take-off and landing, an angle of attack (AoA) of the SST becomes high to generate sufficient lift. Leading-edge vortices generate additional lift (vortex lift) in such a situation. Additionally, vortex breakdown and outboard flow separation caused by the interference of leading-edge vortices occur. The wing’s aerodynamic forces change non-linearly with increasing AoA due to these phenomena. An estimation program based on potential flow for aerodynamic forces of the wing has been developed to investigate wing planforms and high-lift devices in past studies. The estimation program has three methods for modifying the results of potential flow to estimate the non-linear change of aerodynamic forces. In this study, a method to estimate the outboard flow separation is developed, and a method to estimate the vortex breakdown is improved to reduce differences between estimated and experimental results. By comparing estimated results using the present method with some experimental results, improvement of estimated results is observed.
Aeroservoelastic Characteristics of a Corrugated Morphing Control Surface
Kensuke Soneda,Natsuki Tsushima,Tomohiro Yokozeki,Taro Imamura 한국항공우주학회 2022 International Journal of Aeronautical and Space Sc Vol.23 No.4
Aeroservoelastic characteristics of a morphing control surface with corrugated structures are investigated in this paper. The finite element structural model and the aerodynamic model with an unsteady vortex lattice method are used to analyze the aeroelastic response of a corrugated morphing control surface. The equation of motion for the corrugated morphing control surface is derived in the state-space form, and a classic LQR control technique is integrated to function the morphing structures as control surfaces. Considering the structural and control design parameters, the aeroservoelastic response of corrugated morphing control surfaces under continuous gusts is analyzed. Simulation results demonstrate that the flexible design of corrugations may lead to undesirable vibrations even with actuation control. It is also shown that the structural modes which play important roles in the lift control can change according to the structural design parameters. This work provides important insights into designing a morphing control surface with flexible structures such as corrugated structures.