The project travels through both the firmware, hardware and analytical techniques that can improve the overall stability and control responses of the air vehicle. This project explores the various stability and control techniques that can be used to stabilize and control a tilt-rotor bi-copter VTOL Unmanned Aerial Vehicle. It can take-off vertically, hover and fly horizontally at high speeds compared to a quadcopter or a helicopter. It uses two tilt enabled prop-rotors for stability and control. A bi-copter is a blend of these two flight realms. They are thus incapable of vertical take-off. However, they need to achieve a certain amount of velocity to generate the lift depending on the aircraft weight and the wing airfoil profile. The fixed-wing air vehicles generate lift from their wings and can offer superior flight velocity, control, and endurance. However, their low horizontal speeds and limited endurance (the maximum time an air vehicle can stay airborne for a given amount of power) makes them incapable of long-range and surveillance operations. Quadcopters which use four fixed prop-rotors for stability is a popular choice. Hence Vertical Take-Off and Landing (VTOL) aircraft is a dominant subject of research among the aerospace community. With light and compact air vehicles making their way into the aerospace industry and the human society, the need for a design which is capable of operation in constricted areas is necessary. In the present day, air vehicles of various mission capabilities and specifications have been developed through extensive studies and research. Indian Institute of Science Banga lore, C V Raman Road, Bengaluru, Karnataka 560012 AbstractĮver since the Wright brothers re-wrote history in the December of 1903 by successfully demonstrating the first controlled, sustained flight of a powered aircraft, man's curiosity for flight continues to be on the rise. Government Engineering College Thrissur, Ramavarmapuram P.O, Thrissur, Kerala 680009
![tilt rotor flight control system tilt rotor flight control system](https://www.uasvision.com/wp-content/uploads/2011/12/Kari2.jpg)
#Tilt rotor flight control system full
A full envelope flight test is planned to carry out further researches on the flight control law.Stability and control of VTOL tilt-rotor bi-copter UAVs
![tilt rotor flight control system tilt rotor flight control system](https://www.wilcopub.com/media/catalog/product/cache/5/image/9df78eab33525d08d6e5fb8d27136e95/t/r/tr_newvc.jpg)
The results have evidenced the credibility of the aircraft design and the effectiveness of the flight control system for the tilt rotor working in the helicopter mode. Now, the flight tests are still underway on a prototype of small unmanned tilt rotor aircraft. The proposed control law has been born out through the construction of the flight control system and the flight tests. The flight control law of the tilt rotor aircraft is designed with the help of an inner/outer loop control structure and an eigenstructure assignment algorithm on the basis of a proper mathematical model already verified by the wind tunnel tests. This article presents the progresses of the research work on the design of flight control system at Nanjing University of Aeronautics and Astronautics (NUAA). Of them, the flight control system might be a critical one. However, there are a great number of important technical problems waiting for settlements. A tilt rotor is an aircraft of a special kind, which possesses the characteristics of a helicopter and a fixed-wing airplane.