ETD

Archivio digitale delle tesi discusse presso l'Università di Pisa

Tesi etd-06282015-154829


Tipo di tesi
Tesi di laurea magistrale
Autore
D'AGOSTO, STEFANO
URN
etd-06282015-154829
Titolo
Further Development of an Analytical Model for Helicopter Main Rotor Wake-Tail Interactions
Dipartimento
INGEGNERIA CIVILE E INDUSTRIALE
Corso di studi
INGEGNERIA AEROSPAZIALE
Relatori
tutor Ing. Ries, Tobias
relatore Prof. Quarta, Alessandro A.
Parole chiave
  • wake
  • vortex
  • vertical stabilizer
  • UTRC
  • tip vortex
  • tail rotor
  • tail
  • swirl
  • mast moment
  • Landgrebe
  • interactions
  • horizontal stabilizer
  • helicopter
  • generalized wake model
  • fin
  • fenestron blade pitch
  • fenestron
  • Eurocopter
  • empennage
  • wake contraction
  • downwash
  • antitorque
  • Airbus Helicopters
  • Airbus
  • wake deformation
  • wake model
  • wake modeling
Data inizio appello
21/07/2015
Consultabilità
Non consultabile
Data di rilascio
21/07/2085
Riassunto
Simulation of aerodynamic and flight mechanic characteristics is essential to
predict helicopter flight behaviour. One of the most important features is certainly
the interactions between the main rotor wake and different helicopter components.
This Master Thesis focuses on an analytical model able to predict and evaluate
main rotor wake interactions with tailboom, empennage and fenestron. This was
implemented in a more general flight mechanical simulation code. The first version
was created in a former master thesis by Airbus Helicopters. Further development
have been requested in order to have a better estimation of computed quantities in
trimmed conditions for a higher range of speeds. The previous model, indeed, was
suitable only for hover and low velocity steady forward flight.
For this purpose, has been fundamental a better estimation of lateral forces and of
wake geometry. Researches about influence of different factors have been conducted
and new physical models considering fin and fenestron interactions and wake
distortion have been derived and implemented.
Two main variables have been considered as quality indicators: mast moment and
fenestron blade pitch. Nevertheless, other quantities like forces and velocities have
always been taken into account as well. Computed results have been compared
with flight test data in order to verify the reliability of the improved simulation
model. Moreover, CFD analysis have been used to clearly understand the wake
behaviour.
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