All Outputs (3)

Integrating operators’ preferences into decisions of unmanned aerial vehicles: Multi-layer decision engine and incremental preference elicitation (2019)
Conference Proceeding
Khannoussi, A., Olteanu, A., Labreuche, C., Narayan, P., Dezan, C., Diguet, J., …Meyer, P. (2019). Integrating operators’ preferences into decisions of unmanned aerial vehicles: Multi-layer decision engine and incremental preference elicitation. In S. Pekeč, & K. B. Venable (Eds.), International Conference on Algorithmic Decision Theory (49-64). https://doi.org/10.1007/978-3-030-31489-7_4

Due to the nature of autonomous Unmanned Aerial Vehicles (UAV) missions, it is important that the decisions of a UAV stay consistent with the priorities of an operator, while at the same time allowing them to be easily audited and explained. We there... Read More about Integrating operators’ preferences into decisions of unmanned aerial vehicles: Multi-layer decision engine and incremental preference elicitation.

Influence of non-iterative time-advancement schemes on the aerodynamic prediction of pitching airfoils using dynamic mesh (2019)
Presentation / Conference
Abdessemed, C., Yao, Y., Bouferrouk, A., & Narayan, P. (2019, June). Influence of non-iterative time-advancement schemes on the aerodynamic prediction of pitching airfoils using dynamic mesh. Paper presented at 8th International Symposium on Physics of Fluids (ISPF8), Xian, China

A pitching airfoil problem is addressed in this paper to assess the use of a non-iterative time-advancement (NITA) scheme with dynamic mesh method, and also to estimate possible CPU time savings. Simulations have shown that using a combination of dyn... Read More about Influence of non-iterative time-advancement schemes on the aerodynamic prediction of pitching airfoils using dynamic mesh.

Flow response to rapid morphing flap deflection (2019)
Presentation / Conference
Abdessemed, C., Yao, Y., Bouferrouk, A., & Narayan, P. (2019, March). Flow response to rapid morphing flap deflection. Paper presented at 54th 3AF International Conference on Applied Aerodynamics, Paris - France

Flow response to rapid morphing flap deflection is investigated at a Reynolds number based on chord of 0.62×10^6 for a 2D NACA 0012 airfoil fitted with a morphing Trailing-edge flap (TEF) at a range of angles of attack and morphing frequencies. T... Read More about Flow response to rapid morphing flap deflection.