Calibration of antenna arrays for aeronautical vehicles on ground

Elbir, Ahmet M.
Tuncer, Temel Engin
Antenna pattern and characteristics change significantly when antenna arrays are placed on platforms like aeronautical vehicles. Calibration of antenna arrays is an important and costly process for such cases. In this paper, a method is proposed for the offline calibration of a direction finding antenna array mounted on a UH-60 helicopter. The calibration is done on an open-field test area with a flat ground plane. Ground reflections are the main sources of error corrupting the calibration data. The proposed method eliminates the ground reflections by employing a time-gating technique. Calibration data is generated by considering the platform effects. Complete calibration scenario is simulated by using numerical electromagnetic simulation tools. It is shown that the proposed approach is very effective and can be used to calibrate direction finding algorithms like the MUSIC algorithm. Crown Copyright (C) 2013 Published by Elsevier Masson SAS. All rights reserved.


Low velocity impact analysis of a composite mini unmanned air vehicle during belly landing
Yüksel, Serhan; Kayran, Altan; Department of Aerospace Engineering (2010)
Mini unmanned Air Vehicles (UAV) have high significance among other UAV's, in different categories, due to their ease of production, flexibility of maintenance, decrease in weight due to the elimination of landing gear system and simplicity of use. They are usually built to meet 'hand launching' and 'belly landing' criteria in order to have easy flight and easy landing features. Due to the hand take-off and belly landing features there is no need to have a runway and this feature is a very significant advan...
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 ...
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...
Optimization of Flapping Motion Parameters for Two Airfoils in a Biplane Configuration
Kaya, Mustafa; Tuncer, İsmail Hakkı; Jones, Kevin D.; Platzer, Max F. (American Institute of Aeronautics and Astronautics (AIAA), 2009-03-01)
Flapping motion parameters of airfoils in a biplane configuration are optimized for maximum thrust and/or propulsive efficiency. Unsteady, viscous flowfields over airfoils flapping in a combined plunge and pitch are computed with a parallel flow solver on moving and deforming overset grids. The amplitudes of the sinusoidal pitch and plunge motions and the phase shift between them are optimized for a range of flapping frequencies. A gradient-based optimization algorithm is implemented in a parallel computing...
Simulation of Rapidly Maneuvering Airfoils with Synthetic Jet Actuators
Jee, SolKeun; Lopez Mejia, Omar D.; Moser, Robert D.; Muse, Jonathan A.; Kutay, Ali Türker; Calise, Anthony J. (American Institute of Aeronautics and Astronautics (AIAA), 2013-08-01)
Synthetic jet actuators are investigated for rapidly maneuvering airfoils that are regulated by a closed-loop control system. To support active flow-control simulations performed here, the closed-loop system and vehicle dynamics are coupled with computational fluid dynamics. High-frequency sinusoidal pitching simulations with and without synthetic jet actuation indicate that the current synthetic jet actuators provide bidirectional change in aerodynamic forces during rapid maneuvers whose time scales are of...
Citation Formats
A. M. Elbir and T. E. Tuncer, “Calibration of antenna arrays for aeronautical vehicles on ground,” AEROSPACE SCIENCE AND TECHNOLOGY, pp. 18–25, 2013, Accessed: 00, 2020. [Online]. Available: