A novel force control traverse for simulating UAV flight in a wind tunnel

Date

2008-01-01

Author

Muse, Jonathan A.
Kutay, Ali Türker
Calise, Anthony J.

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

161
views

0
downloads

Wind tunnel testing methods often infer aerodynamic performance via quasi-steady predictions, driving a wind tunnel model through predetermined trajectories, or quasi- steady integration of the applied aerodynamic forces and moments. This paper focuses on a new testing approach that allows the simulation and study of the true longitudinal dynamics of a wind tunnel model. The system design allows an experimentalist to carry heavy models with all of the needed sensors for evaluating true unsteady aerodynamic flight qualities. Controlling the forces and moments applied to the model allows the experimentalist to remove effects such as gravity and traverse friction. Using feedback on the applied force and moments, the dynamic characteristics of the model can be actively modified to alter dynamic characteristics such as the system's natural frequency, damping, c.g. location, and/or effective model inertia. All dynamic effects can be set arbitrarily but must be within traverse limits. The model does not have to be balanced because the control system actively restricts motion to be within the longitudinal plane. An example experimental simulation flight is shown using a NACA 4415 wing section with a servo motor in torque mode to simulate the effect of a conventional tail surface. Copyright © 2008 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

URI

https://hdl.handle.net/11511/56194

Journal

AIAA Atmospheric Flight Mechanics Conference and Exhibit

DOI

https://doi.org/10.2514/6.2008-6714

Collections

Department of Aerospace Engineering, Article

Suggestions

OpenMETU
Core

A closed-loop flight control experiment using active flow control actuators Kutay, Ali Türker; Muse, Jonathan A.; Brzozowski, Daniel P.; Glezer, Ari; Calise, Anthony J. (2007-07-02) Closed-loop pitch control on a moving 1-DOF wing model is investigated in wind tunnel experiments. The model's attitude is controlled over a broad range of angles of attack when the baseline flow is fully attached using bi-directional pitching moment that is effected by flow-controlled trapped vorticity concentrations on the pressure and suction surfaces near the trailing edge. In the present work, the model is trimmed using a position feedback loop and a servomotor actuator. Once the model is trimmed, the ...
A Hybrid Method to Estimate Velocity and Acceleration using Low-Resolution Optical Incremental Encoders Baser, Ozgur; Kilic, Ergin; Konukseven, Erhan İlhan; Dölen, Melik (2010-09-10) Accurate velocity and acceleration estimates are required for model-reduced disturbance compensation in motion and force control applications. Such paradigms mostly rely on the position measurements of optical incremental encoders that are known to suffer from the quantization effects introduced by these devices (and their accompanying interfaces). Fixed-time (FT) and fixed-position (FP) methods are used to estimate velocity and acceleration from the quantized position signal. Using Field Programmable Gate ...
A parallel aerostructural shape optimization platform for airplane wings Oktay, Erdal; Arpacı, Anıl; Şehitoğlu, Onur Tolga; Akay, Hasan Umur (null; 2019-05-17) A parallel design platform is developed for aerostructural shape optimization of airplane wings. The developed tools consist of a panel method-based aerodynamic solver, a finite element-based structural solver, geometry and mesh generation modules and a parallel genetic algorithm optimizer, with emphasis given to automation and fast solutions
A new method to measure vehicle pass-by noise in a finite dimensioned semi-anechoic room Arslan, Ersen; Çalışkan, Mehmet; Department of Mechanical Engineering (2010) In this study, a method to predict vehicle pass-by noise in a finite dimensioned, semi-anechoic chamber with chassis dynamometer has been developed. Vehicle noise has been modeled as the summation of the individual contributions regarding the principal noise components, namely, engine including air intake, front tire and rear tire noises. This method employs wave propagation, Doppler shift, and time delay in the estimation of the sound pressure due to each component at points of interest specified by releva...
Investigations on blade tip tilting for hawt rotor blades using CFD Elfarra, Monier A.; Sezer Uzol, Nilay; Akmandor, I. Sinan (2015-02-26) The main purpose of this paper is to study the aerodynamic effects of blade tip tilting on power production of horizontal-axis wind turbines by using Computational Fluid Dynamics (CFD). For validation and as a baseline rotor, the NREL Phase VI wind turbine rotor blade is used. The Reynolds-Averaged Navier-Stokes Equations are solved and different turbulence models including the Spalart-Allmaras, Standard k-ε, k-ε Yang-Shih and SST k-ω models are used and tested. The results are shown in terms of power gener...

Citation Formats

J. A. Muse, A. T. Kutay, and A. J. Calise, “A novel force control traverse for simulating UAV flight in a wind tunnel,” AIAA Atmospheric Flight Mechanics Conference and Exhibit, pp. 0–0, 2008, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/56194.