原文传递
Coupled Vortex-Lattice Flight Dynamic Model with Aeroelastic Finite-Element Model of Flexible Wing Transport Aircraft with Variable Camber Continuous Trailing Edge Flap for Drag Reduction.
| 题名： | Coupled Vortex-Lattice Flight Dynamic Model with Aeroelastic Finite-Element Model of Flexible Wing Transport Aircraft with Variable Camber Continuous Trailing Edge Flap for Drag Reduction. |
| 作者： | Dao, T.; Nguyen, D.; Nguyen, N.; Ting, E.; Trinh, K. |
| 关键词： | Active Control; Aeroelasticity; Drag Reduction; Dynamic Models; Finite Element Method; Flexible Wings; Trailing Edge Flaps; Transport Aircraft; Wing Camber |
| 摘要： | This paper presents a coupled vortex-lattice flight dynamic model with an aeroelastic finite-element model to predict dynamic characteristics of a flexible wing transport aircraft. The aircraft model is based on NASA Generic Transport Model (GTM) with representative mass and stiffness properties to achieve a wing tip deflection about twice that of a conventional transport aircraft (10% versus 5%). This flexible wing transport aircraft is referred to as an Elastically Shaped Aircraft Concept (ESAC) which is equipped with a Variable Camber Continuous Trailing Edge Flap (VCCTEF) system for active wing shaping control for drag reduction. A vortex-lattice aerodynamic model of the ESAC is developed and is coupled with an aeroelastic finite-element model via an automated geometry modeler. This coupled model is used to compute static and dynamic aeroelastic solutions. The deflection information from the finite-element model and the vortex-lattice model is used to compute unsteady contributions to the aerodynamic force and moment coefficients. A coupled aeroelastic-longitudinal flight dynamic model is developed by coupling the finite-element model with the rigid-body flight dynamic model of the GTM. |
| 报告类型： | 科技报告 |
相关文献
- Aeroelastic Analysis of a Flexible Wing Wind Tunnel Model with Variable Camber Continuous Trailing Edge Flap Design.
- Initial Assessment of a Variable-Camber Continuous Trailing-Edge Flap System on a Rigid Wing for Drag Reduction in Subsonic Cruise.
- Investigation into Active Spanwise Camber Deformation on the Lateral Stability and Roll Control of the X-56A Compared to Conventional Ailerons.
- Automation of Structural Sizing of Aircraft Concepts Under Static Aeroelastic Constraints [STUB].
- Aeroelastic Airworthiness Assesment of the Adaptive Compliant Trailing Edge Flaps.
- Airframe noise reduction studies and clean-airframe noise investigation
检索历史
应用推荐
