Your SlideShare is downloading. ×
Hover Ige
Upcoming SlideShare
Loading in...5
×

Thanks for flagging this SlideShare!

Oops! An error has occurred.

×
Saving this for later? Get the SlideShare app to save on your phone or tablet. Read anywhere, anytime – even offline.
Text the download link to your phone
Standard text messaging rates apply

Hover Ige

935
views

Published on


0 Comments
0 Likes
Statistics
Notes
  • Be the first to comment

  • Be the first to like this

No Downloads
Views
Total Views
935
On Slideshare
0
From Embeds
0
Number of Embeds
1
Actions
Shares
0
Downloads
0
Comments
0
Likes
0
Embeds 0
No embeds

Report content
Flagged as inappropriate Flag as inappropriate
Flag as inappropriate

Select your reason for flagging this presentation as inappropriate.

Cancel
No notes for slide

Transcript

  • 1. Methodology for estimating the control derivatives of a helicopter in ground effect from flight test data Presented by Andrei Popov Sep 7, 2009
  • 2. In ground effect (IGE) theory Sep 7, 2009
    • The momentum theory treats the rotor as an actuator disk through which a uniform flow passes. For a given gross weight it is required a certain airspeed of the wake which is named “induced velocity”.
    • Blade element theory states that the rotor blades function as high aspect ratio wings constrained to rotate around a central mast as the rotor system advances through the air.
    • The induced velocity is given by the blades collective pitch angles and is controlled by the collective stick. To maintain the helicopter in the air, the pilot must displace the collective stick in a certain position.
    • In the proximity of the ground ( h < D main rotor diameter), the air wake forms a cushion under the helicopter which is the “in ground effect” (IGE)
  • 3. In ground effect (IGE) theory Sep 7, 2009
    • In ground effect for same thrust as OGE:
    • Less induced velocity (inflow ratio)
    • Less collective blade pitch angle
    • When altitude decrease, what is the effect on the derivative of CT versus collective control position ?
    ? In ground effect aerodynamical phenomenon when altitude Helicopter in hover: Thrust coefficient [1],[2],[3]:
  • 4. Linear Model Sep 7, 2009 Helicopter linear and angular accelerations in 6 degrees of freedom State vector Control vector Stability derivatives Control derivatives influenced by IGE Forces and Moments x,u, X y,v, Y z,w, Z M,q L,p N,r
  • 5. Flight Test Data used Sep 7, 2009 Ladder altitude 1 Ladder altitude 2 Altitude OGE Altitude IGE For our analysis we used the mean values of the significant parameters.
    • Two sets of records with altitude in ladder with steps of 5 ft from 0 to 50 ft
    • One set at altitude of 50 ft out of ground effect (OGE) with a decrease of gross weight, at different rotor speeds (96%, 100%, 104%)
    • One set at altitude of 5 ft in ground effect (IGE)
  • 6. Data processing Sep 7, 2009 Torque coefficient for helicopter in hover [1],[2]: Polynomial fitting of C Q ( C T ) out of ground effect: Polynomial fitting of C Q (collective) : C Q vs. H C Q vs. C T C Q vs. collective
  • 7. Data processing 2 Sep 7, 2009 K(H) – Constant of ground effect vs. altitude [3]: Polynomial fitting of K(H) : Polynomial fitting of C Q (C T ,H) :
  • 8. Results validation Sep 7, 2009
    • Surface obtained by functions C Q (C T ,H) and C Q (collective) where from we obtain C T (collective,H) and its derivatives dC T /d(collective) (H)
  • 9. Final conclusion
    • Derivative dC T /d(collective)
      • 10% greater @ 5 ft altitude
      • 20% greater @ 0 ft altitude.
    • Important for the linear model of a helicopter simulator:
      • Take Off
      • Landing dynamics.
    Sep 7, 2009
  • 10.
    • Bibliography
      • Seddon, J. (1990). Basic helicopter aerodynamics an account of first principles in the fluid mechanics and flight dynamics of the single rotor helicopter . Washington, D.C.: American Institute of Aeronautics and Astronautics.
      • Bramwell, A. R. S., Done, G., & Balmford, D. (2001). Bramwell's helicopter dynamics (2nd ed.). Reston, Va. Oxford, England: American Institute of Aeronautics and Astronautics Butterworth-Heinemann.
      • Prouty, R. W. (2002). Helicopter performance, stability, and control . Malabar, Flor.: R. E. Krieger.
    Sep 7, 2009