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Accession Number ADA564094
Title Aero-Effected Flight Control Using Distributed Active Bleed.
Publication Date Jan 2012
Media Count 38p
Personal Author A. Glezer A. Leonard
Abstract A novel, scalable approach to aero-effected flight control of lifting surfaces using distributed active bleed was investigated experimentally and theoretically. Aerodynamic control is achieved by large-area surface bleed of air that is driven by the pressure differences in flight and is regulated by low-power surface-integrated louver actuators. The joint numerical-experimental investigation focused on the flow mechanisms of the interaction between the bleed and the cross flow and aerodynamic effects of unsteady bleed on a 2-D wing model. Particular emphasis was placed on the generation and regulation of vorticity concentrations that alter the wing s apparent aerodynamic shape and thereby its aerodynamic performance over a range of (static) angles of attack, and under time-periodic pitch oscillations. Wind tunnel investigations of the mechanisms of the time-dependent interactions between the bleed and cross flows used a 2-D Clark-Y model integrated with addressable arrays of piezoelectric louvers for regulating leading and trailing edge bleed. The resulting time- dependent forces and moment were measured over a wide range of angles of attack from pre- to post-stall using load cells, and the induced changes in surface vorticity concentrations were measured using PIV.
Keywords Active control
Aerodynamic bleed
Aerodynamic forces
Bleed systems
Flight control systems
Flow fields
Lift
Lift and pitch control
Louvers
Pitch(Motion)
Vortex based reduced order model

 
Source Agency Non Paid ADAS
NTIS Subject Category 51E - Avionics
Corporate Author Georgia Inst. of Tech., Atlanta. School of Mechanical Engineering.
Document Type Technical report
Title Note Final technical rept. 31 Aug 2008-30 Sep 2011.
NTIS Issue Number 1302
Contract Number FA9550-08-1-0398

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