Aircraft control using fluidic maneuver effectors

P.I.A. Wilde; W.J. Crowther; A. Buonanno; A. Savvaris

doi:10.2514/6.2008-6406

Aircraft control using fluidic maneuver effectors

P.I.A. Wilde, W.J. Crowther, A. Buonanno, A. Savvaris

Research output: Chapter in Book/Conference proceeding › Conference contribution › peer-review

Abstract

Fluidic maneuver effectors provide the opportunity to produce the forces and moments required for flight vehicle trim and maneuvering without using conventional control surfaces. This paper defines the three saturation limits exhibited by fluidic controls. Two are due to geometry and effort/power constraints (similar to geometric issues) and the third type of saturation is due to shock induced separation at high jet Mach numbers. A case study aircraft is analyzed in order to see if the fluidic controls can provide trim/maneuver throughout the flight envelope. Engine bleed air is used for the pneumatic supply of the circulation control (CC) and fluidic thrust vectoring (FTV) effectors. It is shown that the critical flight conditions are climb turns and descending flight where geometric and effort/power saturation limits are met respectively.

Original language	English
Title of host publication	26th AIAA Applied Aerodynamics Conference
Place of Publication	United States
Publisher	American Institute of Aeronautics and Astronautics
ISBN (Electronic)	9781600869877
DOIs	https://doi.org/10.2514/6.2008-6406
Publication status	Published - 2008
Event	26th AIAA Applied Aerodynamics Conference - Honolulu, United States Duration: 18 Aug 2008 → 21 Aug 2008

Conference

Conference	26th AIAA Applied Aerodynamics Conference
Country/Territory	United States
City	Honolulu
Period	18/08/08 → 21/08/08

Keywords

Aerodynamic Force
Flight Control Surfaces
Exhaust Velocity
Flap Deflection
Flight Vehicle
Aircraft Control
Mass Flow Rate
Thrust Vector Angle
Flight Control
Aspect Ratio

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10.2514/6.2008-6406

Cite this

@inproceedings{18a90a54a99b49838f26cae8ff80a3e9,

title = "Aircraft control using fluidic maneuver effectors",

abstract = "Fluidic maneuver effectors provide the opportunity to produce the forces and moments required for flight vehicle trim and maneuvering without using conventional control surfaces. This paper defines the three saturation limits exhibited by fluidic controls. Two are due to geometry and effort/power constraints (similar to geometric issues) and the third type of saturation is due to shock induced separation at high jet Mach numbers. A case study aircraft is analyzed in order to see if the fluidic controls can provide trim/maneuver throughout the flight envelope. Engine bleed air is used for the pneumatic supply of the circulation control (CC) and fluidic thrust vectoring (FTV) effectors. It is shown that the critical flight conditions are climb turns and descending flight where geometric and effort/power saturation limits are met respectively.",

keywords = "Aerodynamic Force, Flight Control Surfaces, Exhaust Velocity, Flap Deflection, Flight Vehicle, Aircraft Control, Mass Flow Rate, Thrust Vector Angle, Flight Control, Aspect Ratio",

author = "P.I.A. Wilde and W.J. Crowther and A. Buonanno and A. Savvaris",

year = "2008",

doi = "10.2514/6.2008-6406",

language = "English",

booktitle = "26th AIAA Applied Aerodynamics Conference",

publisher = "American Institute of Aeronautics and Astronautics ",

address = "United States",

note = "26th AIAA Applied Aerodynamics Conference ; Conference date: 18-08-2008 Through 21-08-2008",

}

TY - GEN

T1 - Aircraft control using fluidic maneuver effectors

AU - Wilde, P.I.A.

AU - Crowther, W.J.

AU - Buonanno, A.

AU - Savvaris, A.

PY - 2008

Y1 - 2008

N2 - Fluidic maneuver effectors provide the opportunity to produce the forces and moments required for flight vehicle trim and maneuvering without using conventional control surfaces. This paper defines the three saturation limits exhibited by fluidic controls. Two are due to geometry and effort/power constraints (similar to geometric issues) and the third type of saturation is due to shock induced separation at high jet Mach numbers. A case study aircraft is analyzed in order to see if the fluidic controls can provide trim/maneuver throughout the flight envelope. Engine bleed air is used for the pneumatic supply of the circulation control (CC) and fluidic thrust vectoring (FTV) effectors. It is shown that the critical flight conditions are climb turns and descending flight where geometric and effort/power saturation limits are met respectively.

AB - Fluidic maneuver effectors provide the opportunity to produce the forces and moments required for flight vehicle trim and maneuvering without using conventional control surfaces. This paper defines the three saturation limits exhibited by fluidic controls. Two are due to geometry and effort/power constraints (similar to geometric issues) and the third type of saturation is due to shock induced separation at high jet Mach numbers. A case study aircraft is analyzed in order to see if the fluidic controls can provide trim/maneuver throughout the flight envelope. Engine bleed air is used for the pneumatic supply of the circulation control (CC) and fluidic thrust vectoring (FTV) effectors. It is shown that the critical flight conditions are climb turns and descending flight where geometric and effort/power saturation limits are met respectively.

KW - Aerodynamic Force

KW - Flight Control Surfaces

KW - Exhaust Velocity

KW - Flap Deflection

KW - Flight Vehicle

KW - Aircraft Control

KW - Mass Flow Rate

KW - Thrust Vector Angle

KW - Flight Control

KW - Aspect Ratio

U2 - 10.2514/6.2008-6406

DO - 10.2514/6.2008-6406

M3 - Conference contribution

BT - 26th AIAA Applied Aerodynamics Conference

PB - American Institute of Aeronautics and Astronautics

CY - United States

T2 - 26th AIAA Applied Aerodynamics Conference

Y2 - 18 August 2008 through 21 August 2008

ER -

Aircraft control using fluidic maneuver effectors

Abstract

Conference

Keywords

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