Mathematical Modeling of the NOTAR Antitorque System for Flight Simulation

Date

2013-04-01

Author

Yavrucuk, İlkay
Uzol, Oğuz

Metadata

Show full item record

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

Item Usage Stats

247
views

0
downloads

In this paper, a mathematical model of a helicopter NO TAil Rotor (NOTAR) antitorque system is developed for real-time flight simulations. The model consists of the circulation control tail boom, direct jet thruster, and the vertical stabilizers. The airflow inside the tail boom is modeled by dividing the flow into aerodynamic control volumes. The model features a bladeelement-type approach for modeling the mass flow through the axial fan blades as well as aerodynamic mass and momentum conservation calculations in each control volume. The side force produced by the direct jet thruster and circulation control tail boom is calculated at different flight conditions. A simple rectangular plan form with symmetrical airfoil shape is used to model the vertical tail. The developed NOTAR antitorque model is integrated with a nonlinear helicopter model. Flight tests are performed on the MD600N, and the data obtained are used for verification. Results show a reasonable match between the model and flight-test data in the antitorque response in hover and forward flight to pilot pedal input.

URI

https://hdl.handle.net/11511/42183

Journal

JOURNAL OF THE AMERICAN HELICOPTER SOCIETY

DOI

https://doi.org/10.4050/jahs.58.022002

Collections

Department of Aerospace Engineering, Article

Suggestions

OpenMETU
Core

Numerical investigations of lateral jets for missile aerodynamics Ağsarlıoğlu, Ekin; Albayrak, Kahraman; Department of Mechanical Engineering (2011) In this thesis, effects of sonic lateral jets on aerodynamics of missiles and missilelike geometries are investigated numerically by commercial Computational Fluid Dynamics (CFD) software FLUENT. The study consists of two parts. In the first part, two generic missile-like geometries with lateral jets, of which experimental data are available in literature, are analyzed by the software for validation studies. As the result of this study, experimental data and CFD results are in good agreement with each other...
Nonlinear modeling and flight control system design of an unmanned aerial vehicle Karakaş, Deniz; Balkan, Raif Tuna; Department of Mechanical Engineering (2007) The nonlinear simulation model of an unmanned aerial vehicle (UAV) in MATLAB®/Simulink® environment is developed by taking into consideration all the possible major system components such as actuators, gravity, engine, atmosphere, wind-turbulence models, as well as the aerodynamics components in the 6 DOF equations of motion. Trim and linearization of the developed nonlinear model are accomplished and various related analyses are carried out. The model is validated by comparing with a similar UAV data in te...
Numerical simulation of lateral jets in supersonic crossflow of missiles using computational fluid dynamics Dağlı, Efe Can; Aksel, M. Haluk.; Department of Mechanical Engineering (2019) In this thesis, numerical simulation method for modelling lateral jet in supersonic crossflow is presented. Lateral jet control provides high maneuverability to the missile at difficult flow conditions. Besides, jet in a crossflow case has a highly complicated flow domain which should be examined using numerical or experimental methods. In this study, numerical methods are used. The thesis consists of two main sections. In the first section, a validation study is conducted for numerical simulation method us...
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...
Numerical Simulation of a Flapping Micro Aerial Vehicle Through Wing Deformation Capture Tay, W. B.; de Baar, J. H. S.; Perçin, Mustafa; Deng, S.; van Oudheusden, B. W. (American Institute of Aeronautics and Astronautics (AIAA), 2018-8) Three-dimensional numerical simulations of a four-wing flapping micro aerial vehicle (FMAV) with actual experimentally captured wing membrane kinematics have been performed using an immersed boundary method Navier-Stokes finite volume solver. To successfully simulate the clap and fling motion involving the wing intersection, the numerical solver has been specifically modified to use a newly improved interpolation template searching algorithm to prevent divergence. Reasonable agreement was found between the ...

Citation Formats

İ. Yavrucuk and O. Uzol, “Mathematical Modeling of the NOTAR Antitorque System for Flight Simulation,” JOURNAL OF THE AMERICAN HELICOPTER SOCIETY, pp. 0–0, 2013, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/42183.