synthetic jet actuators for aerodynamic control
DESCRIPTION
Synthetic Jet Actuators for Aerodynamic Control. Jeffrey D. Bennett Trinity University Allison K. Jones Rose-Hulman Institute of Technology Anita W. Leung University of Michigan Colleen E. Rainbolt Purdue University. Research Internships in Science and Engineering - PowerPoint PPT PresentationTRANSCRIPT
Synthetic Jet Actuators for Synthetic Jet Actuators for Aerodynamic ControlAerodynamic ControlResearch Internships in Science and EngineeringResearch Internships in Science and Engineering
University of Maryland, College Park, MDUniversity of Maryland, College Park, MD
Jeffrey D. BennettJeffrey D. Bennett Trinity UniversityTrinity University
Allison K. JonesAllison K. JonesRose-Hulman Institute of TechnologyRose-Hulman Institute of Technology
Anita W. LeungAnita W. LeungUniversity of MichiganUniversity of Michigan
Colleen E. RainboltColleen E. RainboltPurdue UniversityPurdue University
Objectives Objectives
BackgroundBackground MethodsMethods
Actuator designActuator designPressure analysisPressure analysisControl algorithmControl algorithmWind tunnel testingWind tunnel testing
ResultsResults AnalysisAnalysis ConclusionConclusion
BackgroundBackground What is a synthetic jet?What is a synthetic jet?
Previous Research
•Smith, B. L. and Glezer, A., 1997
•Lachowizc, J. T. Yao. C-S, and Wlezien, R. W., 1998
•Rathnasingham, R. and Breuer, K. S., 1996
•Hassan, A. A. and JanakiRam, R. D., 1998
BackgroundBackground What is a Micro Air Vehicle (MAV)?What is a Micro Air Vehicle (MAV)?
Project GoalsProject Goals Explore the applications of synthetic jet actuators to the control of the flow about Micro Air Vehicles with the final goal of providing improved aerodynamic performance and flight control
Study the use of synthetic jets for aerodynamic control in a range of fluid dynamic regimes
Perform flow visualization techniques to aid in understanding the interaction effects in arrays of synthetic jets.
Wing DesignWing Design
Airfoil: NACA 0012
Wing Dimensions: 3” x 6”
Shell Fabrication Method:
Sand wings
Bake in mold
Cover with fiberglass
Bake in mold
Remove core
Pressure Tap DesignPressure Tap Design
Designed taps to transfer pressure Designed taps to transfer pressure from airflow over the wing to a from airflow over the wing to a pressure reading devicepressure reading device
Pressure tap design #1 Pressure tap design #2
Actuator DesignActuator Design
Diaphragm attached to Diaphragm attached to individual airfoil sectionsindividual airfoil sections
Actuators designed to:Actuators designed to: Be smallBe small Produce ample Produce ample
displacementdisplacement
Actuator Design #1
Various exit nozzles
What is a PZT?What is a PZT?
Lead Zirconium TitanateLead Zirconium Titanate Ceramic MaterialCeramic Material Expands and contracts with applied AC voltage Expands and contracts with applied AC voltage Prior work demonstrated PZT as useful driver Prior work demonstrated PZT as useful driver
for synthetic jetsfor synthetic jets
Wing FabricationWing Fabrication
Wing sections connected Wing sections connected with threaded rodwith threaded rod
Actuators share common Actuators share common groundground
Covered in fiberglass Covered in fiberglass shell (not shown)shell (not shown)
Control System DesignControl System DesignAllow for precise data acquisition
User varies:
On/Off states
Amplitude
Frequency
Simulink algorithm
dSPACE controls
Control System BenefitsControl System Benefits
Actuators
Flow
WingSurface
Actuators
Actuators
Flow
WingSurface
Roll Control
Varied Jet Control
Locating Resonance FrequenciesLocating Resonance Frequencies
Actuator Resonance
0
1
2
3
4
5
6
1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000 12000
Frequency (Hz)
Xfe
rDat
Actuator 1
Actuator 2
Actuator 3
Actuator 4
Actuator 5
Actuator 6
Actuator 7
Actuator 8
Flow VisualizationFlow Visualization
Using flow visualization, the bubble was observed at 14º angle of attack In theory, using synthetic jet actuators will keep flow attached at higher angles of attack
MeasurementsMeasurements
Applied force causes strain gages produce a voltage drop
Allows measurement of lift and drag
Wind Tunnel SetupWind Tunnel SetupSetup #1
Open wind tunnel
Wing mounted vertically
Setup #2
Closed test section
Wing mounted horizontally
Electronics Setup
Digital pressure sensor
Variable gain amplifiers
Digital multimeters
Function generator
ResultsResults Constructed testable Constructed testable
airfoilairfoil Collected data in wind Collected data in wind
tunnels, varying:tunnels, varying: frequenciesfrequencies angles of attackangles of attack exit nozzle diameterexit nozzle diameter
Pressure vs. Distance at 175 Hz [α=2°,6°,10°]
-6.0
-5.0
-4.0
-3.0
-2.0
-1.0
0.0
1.0
0 0.5 1 1.5 2 2.5
Pressure Tap Distance, in.
Pres
sure
, Cp
α=6
α=10
α=6, piezos
α=10, piezos
a=2
a=2, piezos
a=18
a=18,piezos
a=20
a=20, piezos
Lift vs. Angle of Attack (355 Hz)
0.00
0.05
0.10
0.15
0.20
0.25
0.30
0.35
0.40
0 5 10 15 20 25 30
Angle of Attack in degrees
Lif
t in
lb
s
Without Piezos
With Piezos
Theoretical
AnalysisAnalysis
Some collected data disagreed significantly with Some collected data disagreed significantly with theoretical valuestheoretical values
Actuator effects were often indiscernible from Actuator effects were often indiscernible from signal noisesignal noise
Drag vs. Angle of Attack (175 Hz)
0.0000
0.1000
0.2000
0.3000
0.4000
0.5000
0.6000
0 5 10 15 20 25 30
Angle of Attack in Degrees
Dra
g in
lbs
Without Piezos
With Piezos
Theoretical
ConclusionsConclusions
More testing needed to determine the More testing needed to determine the effect of synthetic jet actuators effect of synthetic jet actuators
More sensitive equipment needed to test More sensitive equipment needed to test on small scaleon small scale
Gained experience in such areas as:Gained experience in such areas as: Wind tunnel testingWind tunnel testing Prototype design and constructionPrototype design and construction Modern research methods and techniquesModern research methods and techniques
Future Work Future Work
Different actuator designDifferent actuator design Multiple rows of actuatorsMultiple rows of actuators Vary exit nozzlesVary exit nozzles
ShapeShape SizeSize AngleAngle
Different pressure sensing apparatusDifferent pressure sensing apparatus Implement fuzzy logic and/or neural networks Implement fuzzy logic and/or neural networks
into the controlsinto the controls
Contact InformationContact Information
Jeffrey D. BennettJeffrey D. Bennett ---- [email protected]@trinity.eduTrinity UniversityTrinity UniversityEngineering SciencesEngineering Sciences
Allison K. Jones -- Allison K. Jones -- [email protected]@rose-hulman.eduRose-Hulman Institute of TechnologyRose-Hulman Institute of TechnologyPhysics and Applied Continuous MathematicsPhysics and Applied Continuous Mathematics
Anita W. Leung -- Anita W. Leung -- [email protected]@umich.eduUniversity of MichiganUniversity of MichiganAerospace EngineeringAerospace Engineering
Colleen E. Rainbolt -- Colleen E. Rainbolt -- [email protected]@purdue.eduPurdue UniversityPurdue UniversityAerospace EngineeringAerospace Engineering