In recent years Unmanned Aerial Vehicles (UAV) has become a significant segment of the aviation industry. They can be chosen to be designed as fixed wing or Rotary wing type. Fixed-wing aircraft has the performance of fast forward movement, long range and superior endurance due to its gliding capabilities with no power. Unlike the fixed wing models, rotary wing mini-copters are able to fly in all directions, hover in a fixed position with minimal space for takeoff and landing. This makes them the perfect instrument for detailed inspection work or surveying. Implementing a hybrid UAV has the advantages of both fixed-wing and rotary wing UAV. This paper aims to brief on the design, development and testing of a hybrid tilt body UAV with four rotors. The hybrid vehicle comprises two units, an aerial unit and a ground unit. The aerial unit consists of an unmanned aircraft system. The ground unit consists of means to view and post-data processing of video/image sent by the UAV if it is used for aerial surveillance and control, navigate and guide the aircraft. To proceed, a novel hybrid UAV with capability of Vertical Take Off and Landing (VTOL) and horizontal flight is developed and its response during the transition from VTOL to horizontal flight is analyzed.
Design and Development of Vertical Takeoff and Horizontal Transition Mini Unmanned Aerial Vehicle
Advanced Materials Research ; 1016 ; 436-440
2014-08-28
5 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Transition , VTOL , Four Rotors , Hybrid UAV , Rotor Craft
Design and Development of Vertical Takeoff and Horizontal Transition Mini Unmanned Aerial Vehicle
British Library Conference Proceedings | 2014
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