Helicopter Design for Handling Qualities Enhancement

Date

2009-09-22

Author

Yavrucuk, İlkay

Metadata

Show full item record

Item Usage Stats

50
views

0
downloads

This research aims to bring HQ's (Handling Qualities) assessment according to ADS-33E-PRF into early stages of helicopter design process, namely late conceptual and early preliminary design phase. Effects of three design parameters, namely disc loading, rotor tip speed and blade loading coefficient, on bandwidth phase delay criterion of the ADS-33E-PRF for pitch channel is investigated for the hover condition flown by a 10 degrees of freedom Bo-105 like simulation model. After setting practical design constraints, the variation of each design parameter has been plotted in bandwidth-phase delay graphs. The results indicate that disc loading eventuated as the "grouping" parameter, forming isoline maps for tip speed and blade loading coefficient. Furthermore, the different sets of disc loading isoline maps generate a curved non-linear pattern, inherently with a three dimensional translation. High disc loading with high tip speed and low blade loading coefficient configuration resulted in Level 1 handling qualities. Low disc loading cases provide a wide spectrum of phase delay values with a small interval of possible bandwidth, visa versa for high disc loading case. The paper provides an insight into the design space available in means of bandwidth-phase delay analysis in hovering flight

Subject Keywords

Transect, Tropical forests, Belowground biomass

URI

https://hdl.handle.net/11511/73365

Conference Name

35th European Rotorcraft Forum 2009, ERF 2009 (22 - 25 Eylül 2009)

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Conceptual design of a stealth unmanned combat aerial vehicle with multidisciplinary design optimization Çakın, Uğur; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2018) The present study aims to develop a methodology for multi-disciplinary design optimization (MDO) of an unmanned combat aerial vehicle. At the current stage of optimization study, three disciplines are considered, which are aerodynamics, structural weight and radar cross section (RCS) signature. As objective functions, maximum range and minimum RCS signature are employed. To generate pareto-optimal solutions, multi-objective particle swarm optimization (MOPSO) function of MATLAB® is performed. To get aerodyn...
Aeroelastic behaviour of UAV wings due to morphing Unlusoy, Levent; Yaman, Yavuz (2017-01-01) Purpose - The purpose of this paper is to analyse the effects of morphing on the aeroelastic behaviour of unmanned aerial vehicle (UAV) wings to make an emphasis on the required aeroelastic tailoring starting from the conceptual design of the morphing mechanisms.
Flight control system design of an uncommon quadrotor aerial vehicle Baskın, Mehmet; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2021-9-01) In this thesis, design of a flight control system for an uncommon quadrotor aerial vehicle is discussed. This aerial vehicle consists of two counter-rotating big rotors on longitudinal axis to increase the lift capacity and flight endurance, and two counter-rotating small tilt rotors on lateral axis to stabilize the attitude. Firstly, full nonlinear dynamic model of this vehicle is obtained by using Newton-Euler formulation. Later, derived approximate linear model around hover is statically decoupled to sim...
Aerodynamic parameter estimation using flight test data Kutluay, Ümit; Platin, Bülent Emre; Mahmutyazıcıoğlu, Gökmen; Department of Mechanical Engineering (2011) This doctoral study aims to develop a methodology for use in determining aerodynamic models and parameters from actual flight test data for different types of autonomous flight vehicles. The stepwise regression method and equation error method are utilized for the aerodynamic model identification and parameter estimation. A closed loop aerodynamic parameter estimation approach is also applied in this study which can be used to fine tune the model parameters. Genetic algorithm is used as the optimization ker...
Hovering Control of a Tilt-Wing UAV Çakır, Hasan; Kurtuluş, Dilek Funda (2019-09-20) In this study, the design and analysis of hovering controller of an UAV which is capable of doing vertical take-off and landing using the fixed six rotors placed on the tilt-wing and tilt-tail will be explained. The aircraft will have four rotors on the wing and two rotors on the tail. The main wing and horizontal tail will be capable of 90° tilting. Whole flight is separated into three flight modes, which are VTOL, Transition and Forward Flight, to have a robust control on aircraft. Only hover control of t...

Citation Formats

İ. Yavrucuk, “Helicopter Design for Handling Qualities Enhancement,” presented at the 35th European Rotorcraft Forum 2009, ERF 2009 (22 - 25 Eylül 2009), Hamburg; Germany, 2009, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/73365.