Research Fellows
Rejish Jesudasan
Early Stage Researcher 1 at Queen Mary University of London
Adjoint based optimisation method has been applied extensively for aerodynamic shape optimisation. However, there are some issues that prevent the use of CAD based parametrisation methods in a real aircraft design process. These issues are simply a lack of functionalities for handling intersecting components and geometrical constraints, and difficulties of computing sensitivity of the geometric shape to the design variables which is an essential measure for gradient based shape optimisation. In this work, NURBS based parametrisation with complex constraints (NSPCC) framework is extended to overcome these issues and proposed surrogate patch intersection algorithm to handle multiple intersecting NURBS patches in the design loop. Complete CAD sensitivities of the design loop is computed by differentiating all components including moving intersection and surface grid morphing approach using Automatic Differentiation(AD) tools in reverse mode. The resulting exact and cost effective CAD sensitivities will be demonstrated on the DLR-F6 wing-body junction optimisation using simultaneous time-stepping methods for KKT system (‘one-shot’) where gradient evaluations occur more frequently.