Design and Development of Vertical Takeoff and Horizontal Transition Mini Unmanned Aerial Vehicle

Abstract:

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.

• Periodical: Advanced Materials Research (Volume 1016)
• Pages: 436-440
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.1016.436
• Online since: August 2014
• Authors: R. Krishnakumar*, K. Senthil Kumar, T. Anand
• Keywords: Four Rotors, Hybrid UAV, Rotor Craft, Transition, VTOL

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