Abstract
In this work we explore the initial design space for composite kites, focusing on the configuration of the bridle line system and its effect on the aeroelastic behaviour of the wing. The computational model utilises a 2D cross sectional model in conjunction with a 1D beam model (2+1D structural model) that captures the complex composite coupling effects exhibited by slender, multi-layered composite structures, while still being computationally efficient for the use at the initial iterative design stage. This structural model is coupled with a non-linear vortex lattice method (VLM) to determine the aerodynamic loading on the wing. In conjunction with the aerodynamic model, a bridle model is utilised to determine the force transfer path between the wing and the bridles connected with the tethers leading to the ground station. The structural model is coupled to the aerodynamic and bridle models in order to obtain the equilibrium aero-structural-bridle state of the kite. This computational model is utilised to perform a design space exploration to assess the effects of varied load introduction to the structure and resulting effects on the kite.
Highlights
Airborne wind energy (AWE) is the conversion of wind energy into electricity using tethered flying devices
In this work we explore the initial design space for composite kites, focusing on the configuration of the bridle line system and its effect on the aeroelastic behaviour of the wing
The computational model utilises a 2D cross sectional model in conjunction with a 1D beam model (2+1D structural model) that captures the complex composite coupling effects exhibited by slender, multi-layered composite structures, while still being computationally efficient for the use at the initial iterative design stage
Summary
Airborne wind energy (AWE) is the conversion of wind energy into electricity using tethered flying devices. To generate power efficiently over the entire cycle, the airborne wing is required to maximise the forces on the tether during the power phase, and minimise the force during retraction phase. The aim to maximise the traction power leads to a design problem with conflicting requirements. This results in a design goal to maximise the net power output per pumping cycle. This design goal results in high-lift wings which are typically subjected to a tether force an order of magnitude larger than the weight of the wing, leading to much larger wing loading compared to conventional aircraft. Similar to the cut-in speed for traditional turbines, the take-off speed
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