Effect of Symmetric & Asymmetric Span Morphing on Flight Dynamics

ight performance and dynamic analysis can be performed. This framework prospectively enables development of morphing concepts, in addition to assessment activities from a conceptual design phase. An example small/ medium Unmanned Air Vehicle (UAV) (mass of 25 kg and nominal aspect ratio of 6.67) is used to demonstrate the tool, presenting results for both symmetric and asymmetric span retraction. The span retraction is performed using the outboard 50% of the main wing, with up to 50% allowable span retraction. Results presented are for a loiter mission. The loiter is at 55 (km/r) where the high speed cruise is from 75-110 km/hr. Span retraction is used to optimise the conguration performance for these ight phases. LTrim and dy- namic (both longitudinal and lateral) results are presented for both high speed cruise and loiter for straight and level conditions. Loiter results include lateral coordinated turn with varying strategies, which include using either rudder span retraction, to trim the UAV. Final results show the eect of modelling _ Ixx using a reduced model for roll dynamics. This investigation shows that the maximum error occurs where the roll and inertia dynamics are matched.