Optimisation, design, production, and testing of a topology of an internal actuation system to deflect a seamless morphing leading edge of a wing are proposed. The actuation system is designed using an aeroelastic optimisation code including sufficient boundary conditions, such as leading edge skin strain allowables, to ensure a practical outcome of the actuation topology. The variation in aeroloading during the deflection is taken into account in order not to design the leading edge only for straight and deflected configuration, but to ensure feasibility of the system during transition. The design is translated into a working actuation system which is to be built and tested. The result of this proposal will not only deliver an optimised topology of the actuation system, which is built and tested, for the wing geometry specified by the GRA member, but also provide the ability to quickly develop new actuation architectures for alternative wing geometries.
Fields of science
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