Design and Flight Testing of H¿ Lateral Flight Control for an Unmanned Air Vehicle

2007 ◽  
Author(s):  
Kannan Natesan ◽  
M. Seetharama Bhat
Keyword(s):  
Flight Control ◽  
Flight Testing ◽  
Unmanned Air Vehicle ◽  
Air Vehicle

scholarly journals Bio-inspired Distributed Strain and Airflow Sensing for Small Unmanned Air Vehicle Flight Control

2017 ◽  
Author(s):  
Sergio A. Araujo-Estrada ◽  
Francis Salama ◽  
Colin M. Greatwood ◽  
Kieran T. Wood ◽  
Thomas S. Richardson ◽  
...  
Keyword(s):  
Flight Control ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
Distributed Strain

Flight Testing of the T-Wing Tail-Sitter Unmanned Air Vehicle

2008 ◽  
Vol 45 (2) ◽  
pp. 673-685 ◽  
Author(s):  
R. Hugh Stone ◽  
Peter Anderson ◽  
Colin Hutchison ◽  
Allen Tsai ◽  
Peter Gibbens ◽  
...  
Keyword(s):  
Flight Testing ◽  
Unmanned Air Vehicle ◽  
Air Vehicle

Aerodynamic performance benefits of utilising camber morphing wings for unmanned air vehicles

2013 ◽  
Vol 117 (1189) ◽  
pp. 315-327 ◽  
Author(s):  
A. García Naranjo ◽  
I. Cowling ◽  
J. A. Green ◽  
N. Qin
Keyword(s):  
Performance Characteristic ◽  
Aerodynamic Performance ◽  
Performance Parameters ◽  
3D Flow ◽  
Flight Testing ◽  
Unmanned Air Vehicle ◽  
Induced Drag ◽  
Air Vehicle ◽  
Morphing Wings ◽  
Realistic Appraisal

Abstract This work considers the effects of camber morphing, both in magnitude and chord position, on the performance of a generic unmanned air vehicle (UAV). The focus is to maximise appropriate aerodynamic factors across the mission by optimising the wing camber. Specifically, the enhancement of range, endurance, and stall speed is sought by means of maximising their aerodynamic performance parameters, CL /CD , CL 3/2/CD , and CLmax respectively. An analysis of the effects of camber morphing is carried out using the vortex panel code, XFOIL, utilising aerofoils from the NACA four-digit family. The results are then adjusted to account for 3D flow factors such as induced drag, offering a more realistic appraisal of their effectiveness. Flight testing is then performed on four wings of fixed aerofoil sections, optimised for each performance characteristic, to validate the trends observed in the XFOIL data onboard a 1·64m span aircraft.

A stability-guaranteed smooth-scheduled MIMO robust emergency autopilot for a lateral surface jammed UAV

2017 ◽  
Vol 232 (12) ◽  
pp. 2286-2299
Author(s):  
İsmail Hakkı Şahin ◽  
Coşku Kasnakoğlu
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Flight Control ◽  
Autonomous Navigation ◽  
Control Laws ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
The Disabled ◽  
Aerial Vehicle ◽  
And Performance ◽  
Control Surfaces

This paper investigates a methodology for autopilot design for an unmanned air vehicle where one of the lateral control surfaces, i.e. the aileron or rudder, becomes jammed and unusable. The autopilot handles the automatic recovery, autonomous guidance and landing of the disabled unmanned aerial vehicle. An accurate nonlinear aircraft model is used to build local flight control laws using loop-shaping to decouple longitudinal and lateral channels. The design is carried out in a way to allow smooth scheduling over the local controllers without losing stability and performance, culminating in a robust emergency autopilot over the full flight envelope. The autopilot is tested on an example distress scenario involving aileron surface jam. It is confirmed through simulations that the autopilot design is capable of resuming safe flight and autonomous navigation under the fault scenario and is able to safely land the unmanned aerial vehicle to a target runway.

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