Quad Tilt Wing VTOL UAV

Authors

  • Bharati V. Agasibagil Student, Department of Aeronautical Engineering, Srinivas Institute of Technology, Valachil, India
  • V. M. Kanakashreegandhi Student, Department of Aeronautical Engineering, Srinivas Institute of Technology, Valachil, India
  • Mohammed Hifaaz Student, Department of Aeronautical Engineering, Srinivas Institute of Technology, Valachil, India
  • P. D. Sachin Student, Department of Aeronautical Engineering, Srinivas Institute of Technology, Valachil, India
  • P. Ramesh Kumar Professor, Department of Aeronautical Engineering, Srinivas Institute of Technology, Valachil, India

Keywords:

Tilt wing, UAV, VTOL (vertical takeoff and landing)

Abstract

A Tilt Wing Vertical Take-off and Landing (VTOL) UAV, which highlights Tilt wings alongside each other and propellers fitted at the mid-span of every wing, is one of the better reassuring UAV configurations having both vertical take-off and landing capability and high cruise performance. A small prototype TW UAV has been constructed to prove the concept and full transition between vertical and horizontal flight has been successfully demonstrated under remote manual control. The essential aerodynamic characteristics of the TW i.e. Tilt wing derived from ANSYS data are summarized, and a tandem wing concept which achieves both hovering and cruising stability has been applied to design the prototype UAV. A flight control system (FCS) enabling continuous sway through all flight phases enabled a pilot to carry out vertical take-off, accelerating transition, cruise, decelerating transition and hover landing, all these phases with sufficient flying qualities.

Downloads

Download data is not yet available.

Downloads

Published

13-08-2020

How to Cite

[1]
B. V. Agasibagil, V. M. Kanakashreegandhi, M. Hifaaz, P. D. Sachin, and P. R. Kumar, “Quad Tilt Wing VTOL UAV”, IJRESM, vol. 3, no. 8, pp. 193–196, Aug. 2020.

Issue

Section

Articles