Flight Control of a Tilt-Duct UAV

Flight Control System Design for an Unmanned Air Vehicle Yavrucuk, İlkay (null; 2009-08-17)
Flight simulation and control of a helicopter Erçin, Gülsüm Hilal; Tekinalp, Ozan; Department of Aerospace Engineering (2008) In this thesis the development of a nonlinear simulation model of a utility helicopter and the design of its automatic flight control system is addressed. In the first part of this thesis, the nonlinear dynamic model for a full size helicopter is developed using the MATLAB/SIMULINK environment. The main rotor (composed of inflow and flapping dynamics parts), tail rotor, fuselage, vertical stabilizer, horizontal stabilizer of the helicopter are modeled in order to obtain the total forces and moments needed f...
Flight flutter testing and aeroelastic stability of aircraft Kayran, Altan (2007-01-01) Purpose - This paper sets out to provide a general review of the flight flutter test techniques utilized in aeroelastic stability flight testing of aircraft, and to highlight the key items involved in flight flutter testing of aircraft, by emphasizing all the main information processed during the flutter stability verification based on flight test data.
Flight flutter testing and aeroelastic stability of aircraft Kayran, Altan (2007-03-01)
Flight flutter testing and aeroelastic stability of aircraft Kayran, Altan (2007-01-01) Purpose - To provide a general review of the flight flutter test techniques utilized in aeroelastic stability flight testing of aircraft, and to highlight the key items involved in flight flutter testing of aircraft, by emphasizing all the main information processed during the flutter stability verification based on flight test data.

Citation Formats

O. Tekinalp and A. OKAN, “Flight Control of a Tilt-Duct UAV,” 2002, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/69378.