Small UAV parachute recovery system design

The thesis is focused on the small UAV’s rescue system design. The thesis is divided into related sections reflecting the design process. The first part deals with general problems of parachute equipment. Another part is evaluating critical situations in manual and autonomous control of the airplane. The deceleration device is based on this critical situations as well as the calculated structure loading. Next is the description and evaluation of experiments to verify the performance of modern parachutes. The thesis also includes a simplified proposal ejection mechanism designed in 3D software and documentation of the of model aircraft construction for testing and predicting behaviour in autonomous flight mode