Overall Design Of Morphing Wing UAV And Control Experiment

Compared to the traditional UAV, the morphing UAV enlarge the flight envelope with changingits shape, which can satisfy the requirements of various missions. At the present time, morphing aircraftaerodynamics, mechanism and control system are still the focus of this research field.This thesis concentrated on the integration of long distance cruise performance and highlymotivated defense penetration ability. A folding wing UAV overall configuration was designed withflying wing and tailless configuration. The CFD method based on the N-S formula was used to evaluatethe aerodynamics characteristic, stability and controllability. In order to get accurately measure andcontrol of the wing folding angle during the folding process, a mechanism combined with worm gearand parallelogram linkage was designed，an angle measure algorithm based on multi accelerators wasstudied and the wing folding scheme based on DSP was presented.The UAV prototype model was made. The MEMS-based accelerometer used in folding anglemeasurement has the advantage of real-time and accuracy. The control system under the morphingwing UAV also proved its ability in the flying test. The effectiveness of folding wing mechanism,measure algorithm and control system were validated with the experiments.The studies proved that, the designed morphing wing UAV met the requirements of variousmissions, the angle measure algorithm based on multi accelerations can make accurately control withthe designed system.