An automatic geometry and mesh generation tool for helicopter rotor aerodynamic design and analysis

Download
2021-9-08
Uzun, Halit Eldem
Helicopter rotors in various flight regimes constitute a fairly complex wing geometry and exhibit motion affected by the rotor wake with strong tip vortices. As a result, rotor motion creates highly three-dimensional flow patterns, and unlike fixed wings, flow around each rotor blade interacts with each other. Due to these complexities, the rotor flow analysis can be very challenging for CFD solvers. The challenge starts with very high-quality requirements on the computational mesh around the rotor geometry. A modern helicopter rotor geometry involves several different airfoil profile sections, profile blending, twists, and other parameters. Moreover, blade tip geometry can be selected from a wide variety of candidates. This thesis presents the development and results of fully automatized rotor geometry and solution domain generation/decomposition tool. A rotor with a very high complexity with any number of blades can be generated with the new tool. The rotor is assumed to be articulated for each blade, and the rotor blades are considered rigid. Very high-quality multi-block and conformal meshes in the flow domain can be generated automatically. The new tool is tested with known helicopter rotors in the literature, and CFD solutions are obtained.

Suggestions

A helicopter rotor modelling and meshing system
Uzun, Halit Eldem; Yutük, Kaan; Baran, Özgür Uğraş; AKSEL, MEHMET HALUK (2021-09-08)
Helicopter rotors in flight constitute a fairly complex wing geometry and exhibit motion in several axes. As a result, rotor motion creates quite complex flow patterns, and unlike fixed wings, flow around each rotor blade interacts with each other. These complexities make the analysis of the rotor flow is a challenge for CFD solvers. The challenge starts with very high requirements on the quality of the computational mesh. A modern helicopter rotor involves a number of different airfoil sections, complex pr...
High angle attack maneuvering and stabilization control of aircraft
Ateşoğlu, Özgür; Özgören, Mustafa Kemal; Department of Mechanical Engineering (2007)
In this study, the implementation of modern control techniques, that can be used both for the stable recovery of the aircraft from the undesired high angle of attack flight state (stall) and the agile maneuvering of the aircraft in various air combat or defense missions, are performed. In order to accomplish this task, the thrust vectoring control (TVC) actuation is blended with the conventional aerodynamic controls. The controller design is based on the nonlinear dynamic inversion (NDI) control methodologi...
Development of a comprehensive and modular modelling, analysis and simulation tool for helicopters
Yücekayalı, Arda; Kutay, Ali Türker; Department of Aerospace Engineering (2011)
Helicopter flight dynamic, rotor aerodynamic and dynamic analyses activities have been a great dispute since the first helicopters, at both design and test stages. Predicting rotor aerodynamic and dynamic characteristics, helicopter dynamic behavior and trimmed flight conditions is a huge challenge to engineers as it involves the tradeoff between accuracy, fidelity, complexity and computational cost. Flight dynamic activities such as; predicting trim conditions, helicopter dynamic behavior and simulation of...
Development of an autopilot for automatic landing of an unmanned aerial vehicle
Arıbal, Seçkin; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2011)
This thesis presents the design of an autopilot and guidance system for an unmanned aerial vehicle. Classical (PID) and modern control (LQT, Sliding Mode) methods for autonomous navigation and landing in adverse weather conditions are implemented. Two different guidance systems are designed in order to navigate through waypoints during normal and/or emergency flight. The nonlinear Pioneer UAV model is used in controller development and simulations. Aircraft is linearized at different trim points and total a...
Modeling and experimental identification of quadrotor aerodynamics
Kaya, D. Derya; Kutay, Ali Türker; Department of Aerospace Engineering (2014)
The aim of this study is to obtain mathematical models for aerodynamic forces and moments of rotors of a quadrotor helicopter, and estimate their parameters through wind tunnel tests for hover, vertical climb, and forward flight conditions. The main factors which determine the movement of a quadrotor UAV are the aerodynamic forces and moments in three axes created by four rotors of the vehicle. Hence, accurate calculation of rotor forces and moments in varying flight conditions are essential to establish a ...
Citation Formats
H. E. Uzun, “An automatic geometry and mesh generation tool for helicopter rotor aerodynamic design and analysis,” M.S. - Master of Science, Middle East Technical University, 2021.