Session: 02-06-01: Structural Dynamics and Control of Morphing Wing and Smart Structures

Paper Number: 106523

106523 - Dynamic Aeroelastic Response of Camber Morphing Aircraft 

Morphing technologies have been intensively studied for the last decades. Among different types of morphing methods, camber morphing is one of the promising candidates for its simplicity and effectiveness. The aerodynamic advantages of camber morphing have been demonstrated through numerical and experimental studies. However, these aerodynamic advantages can cause undesired aeroelastic deformation on the morphing wings. It has been known that morphing high-lift devices can lead to aeroelastic wing twisting and may not be able to increase the total lifts on the wing [1]. In addition, compared to conventional aircraft, the high-lift devices themselves can change their shape due to the aeroelastic deformation of the morphing structures. Therefore, the coupling between aeroelasticity and flight dynamics is more important for the dynamics of morphing aircraft; In morphing aircraft, the flight dynamics can have great impacts on the aeroelastic response of the wing and the morphing structures. A detailed study is necessary to understand these complicated coupling effects.

Aeroelastic-flight simulations that can provide fast solutions are necessary to analyze the transient response of the morphing aircraft. The common efficient modeling strategy is to model the wing structure as a beam, but it cannot consider the camber deformation of the morphing structures, and additional steps are necessary to consider it [2]. On the other hand, using a shell model for the wing structure, camber deformation can also be considered. If homogenization is applicable to the morphing structures, this strategy offers a simple and efficient structural model. For the aerodynamic model, an unsteady vortex lattice method (UVLM) has been shown to provide fast, yet accurate, unsteady aerodynamic forces in the time domain. With UVLM, the coupling procedures with the structural model can be also implemented in a simple manner.

In this study, an aeroelastic flight simulation framework developed by the authors is used to simulate the response of the morphing aircraft. This simulation framework couples a structural model with shell finite elements, an aerodynamic model with an unsteady vortex lattice method, and rigid-body flight dynamics. For the morphing structures, a corrugated panel is used, which is one of the promising candidate structures for camber morphing. Their mechanical properties are incorporated using the homogenization method [3]. Using the high-lift flight conditions, the aeroelastic flight response of the morphing airplanes with different structural designs will be compared, and the coupled aeroelastic flight performance will be demonstrated.

References

1. Tsushima, N., Yokozeki, T., Su, W., and Arizono, H. "Geometrically nonlinear static aeroelastic analysis of composite morphing wing with corrugated structures," Aerospace Science and Technology, Vol. 88, 2019, pp. 244-257.

2. Shearer, C. M., and Cesnik, C. E. S. "Nonlinear flight dynamics of very flexible aircraft," Journal of Aircraft, Vol. 44, No. 5, 2007, pp. 1528-1545.

3. Xia, Y., Friswell, M. I., and Flores, E. I. S. "Equivalent models of corrugated panels," International Journal of Solids and Structures, Vol. 49, No. 13, 2012, pp. 1453-1462.

Presenting Author: Natsuki Tsushima Japan Aerospace Exploration Agency

Presenting Author Biography: a. Name: Natsuki Tsushima
b. Biography:
- Researcher/Japan Aerospace Exploration Agency/2018 – Present
- Project Associate Professor/The University of Tokyo/2020 – Present
- Postdoctoral Research Fellow (Guest Researcher in JAXA)/The University of Tokyo/2017 - 2018
- Ph.D. in Aerospace Engineering and Mechanics/The University of Alabama/2013 - 2017
- M.S. in Aerospace Engineering and Mechanics/The University of Alabama/ 2015
- Application Engineer/Volvo Group Trucks Technology, Volvo Group Powertrain Engineering, Control systems/2011 – 2013

Research Interest:
Aeroelasticity, structural dynamics, additive manufacturing, multifunctional structure, flexible structure, aerodynamics

Authors:

Kensuke Soneda The University of Tokyo
Natsuki Tsushima Japan Aerospace Exploration Agency
Tomohiro Yokozeki The University of Tokyo
Taro Imamura The University of Tokyo