High-alpha flight maneuverability enhancement of a fighter aircraft using thrust-vectoring control

Atesoglu, Oezguer
Oezgoeren, M. Kemal
This study focuses on high-alpha flight maneuverability enhancement of a fighter-bomber aircraft for air combat superiority using thrust-vectoring control. Two basic air superiority maneuvers are studied as test cases, which are the Cobra maneuver with longitudinal motion and the Herbst maneuver with both longitudinal and lateral motions. The necessary mathematical models are built to describe the nonlinear 6-degree-of-freedom flight dynamics, the nonlinear aerodynamics, the engine, and the thrust-vectoring paddles of the aircraft. High-alpha aerodynamics of the aircraft is studied and the integrated Bihrle-Weissmann chart is plotted to determine the stall effected regions. The method employed to control the aircraft is based on feedback linearization with nonlinear dynamic inversion. Both of the test case maneuvers are simulated with two control modes using aerodynamic control only and thrust-vectoring control only. Then the performances of these control modes are compared. This study demonstrates that an additional thrust-vectoring control system integrated to the conventional aerodynamic flight control system of a fighter aircraft turns out to be highly effective in increasing its high-alpha maneuvering capability.


Design and analysis of a mode-switching micro unmanned aerial vehicle
Cakici, Ferit; Leblebicioğlu, Mehmet Kemal (SAGE Publications, 2016-12-01)
In this study, design and analysis of a mode-switching vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) with level flight capability is considered. The design of the platform includes both multirotor and fixed-wing (FW) conventional airplane structures; therefore named as VTOL-FW. The aircraft is modeled using aerodynamical principles including post-stall conditions. Trim conditions are obtained by solving constrained optimization problems. Linear analysis techniques are utilized for trim ...
Accurate position control of a flapping-wing robot enabling free-flight flow visualisation in a wind tunnel
Karasek, Matej; Perçin, Mustafa; Cunis, Torbjorn; van Oudheusden, Bas W.; De Wagter, Christophe; Remes, Bart D. W.; de Croon, Guido C. H. E. (SAGE Publications, 2019-10-02)
Flow visualisations are essential to better understand the unsteady aerodynamics of flapping wing flight. The issues inherent to animal experiments, such as poor controllability and unnatural flapping when tethered, can be avoided by using robotic flyers that promise for a more systematic and repeatable methodology. Here, we present a new flapping-wing micro air vehicle (FWMAV)-specific control approach that, by employing an external motion tracking system, achieved autonomous wind tunnel flight with a maxi...
Aero-structural design and analysis of an unmanned aerial vehicle and its mission adaptive wing
İnsuyu, Erdoğan Tolga; Şahin, Melin; Department of Aerospace Engineering (2010)
This thesis investigates the effects of camber change on the mission adaptive wing of a structurally designed unmanned aerial vehicle (UAV). The commercial computational fluid dynamics (CFD) software ANSYS/FLUENT is employed for the aerodynamic analyses. Several cambered airfoils are compared in terms of their aerodynamic coefficients and the effects of the camber change formed in specific sections of the wing on the spanwise pressure distribution are investigated. The mission adaptive wing is modeled struc...
High-lift design optimization using Navier-Stokes equations
Eyi, Sinan; Rogers, SE; Kwak, D (American Institute of Aeronautics and Astronautics (AIAA), 1996-05-01)
This article presents a design optimization method for maximizing lift without increasing the drag of multielement airfoils at takeoff and landing configurations. It uses an incompressible Navier-Stokes dow solver (INS2D), a chimera overlaid grid system (PEGSUS), and a constrained numerical optimizer (DOT). Aerodynamic sensitivity derivatives are obtained using finite differencing. The method is first validated with single-clement airfoil designs and then applied to three-element airfoil designs. Reliable d...
Flight control system design for an over actuated UAV against actuator failures
Işık, Sinem; Tekinalp, Ozan; Department of Aerospace Engineering (2010)
This thesis describes the automatic flight control systems designed for a conventional and an over actuated unmanned air vehicle (UAV). A nonlinear simulation model including the flight mechanics equations together with the interpolated nonlinear aerodynamics, environmental effects, mass-inertia properties, thrust calculations and actuator dynamics is created; trim and linearization codes are developed. Automatic flight control system of the conventional UAV is designed by using both classical and robust co...
Citation Formats
O. Atesoglu and M. K. Oezgoeren, “High-alpha flight maneuverability enhancement of a fighter aircraft using thrust-vectoring control,” JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, pp. 1480–1493, 2007, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/65316.