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Office National d’Études et de Recherches Aérospatiales
www.onera.fr
Wake vortex characterization byLidar technics : catapult and field trials.
Wake vortex characterization byWake vortex characterization byLidar Lidar technicstechnics : catapult and field trials. : catapult and field trials.
J-P. J-P. CariouCariou,, A. A. DolfiDolfi,,D. D. GoularGoular, D. , D. FleuryFleury, B , B AugereAugere, M. , M. JallotJallot, JP , JP LafforgueLafforgue
ONERA, ONERA, PalaiseauPalaiseau, France, France..11/02/05
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Working plan during Joint ProjectWorking plan during Joint Project
MINI LIDARS for wake vortexmeasurements in catapultfacilities B10 and B20
LIDAR for full scale wake vortexmeasurement
SIMULATION software of lidarDoppler signature in a wind fieldrepresentative of a vortex pair
LIDABEMO
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DOTA DepartmentDOTA Department
DOTA : Applied and Theoretical Optics Department120 employees, 90 scientistslocated at Palaiseau, Châtillon, Toulouse and Salon
SLS : Laser Sources and Lidars Research Unit (15p)coherent lidars for remote sensingfibre sources for aerospace applications
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Working plan during PRFWorking plan during PRF
CATAPULT MEASUREMENTS
-1997-98 : development and improvements of SYLVA CO2 cw miniLIDAR for vortex measurement in catapult facility B10
-1999 : new measurement campaign & comparison between lidar andPIV measurements at catapult facility
-2003 : development of a new mini-lidar set-up with triangulationconfiguration for autonomous measurements in the B20 catapultfacility.
- 2004 : test of a new mini lidar technology, with an all fibre lidararchitecture at 1.5 µm .
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Working plan during PRFWorking plan during PRF
FIELD TEST MEASUREMENTS
- 2000 : development of DASH2 CO2 LIDAR for field test measurement.Measurement campaign in La Cépière TOULOUSE
- 2001 : improvement of DASH2 Lidar
SIMULATION SOFTWARE
- 2002 : development of the SLAVA software architecture
- 2003 : exploitation of the software
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Principle of coherent lidar measurementPrinciple of coherent lidar measurement
Laser anemometer :
A cw single frequency laser source (ν) is focused in the wind fieldAerosols, present in the vortex flow, backscatter part of incidentradiation, with a frequency shift fD corresponding to Doppler effect(fD= 2 Vr /λ) (Vr line-of-sight velocity)this Doppler shift fD is measured with coherent detection
LASER
°
°
°
V
Vr
Localoscillator
Mixer
Detector
Signalprocessing
ν
ν
ν
ν+fd
fd
v
-15
-10
-5
0
5
10
15
-40 -20 0 20 40
r(m)v(
m/s
)
22max.2)(
c
c
rrrVrrV
+=
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OUTLINEOUTLINE
CATAPULT MEASUREMENTS
FIELD TEST MEASUREMENTS
SIMULATION SOFTWARE
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MINI LIDAR CATAPULT MEASUREMENTSMINI LIDAR CATAPULT MEASUREMENTS
Lidarsystem
A 300model
lidar beam scanningseeding with smokeor oil droplets
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Lidar experimental set up at the B10
θ = 40°
Scanning mirror
2 m
3,7m
CO2 Lidar
mirrormirror
alignement laser
MCT detector
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5Lidar characteristics for catapult
measurements
aircraft :• 1/20 th scale (span = 2 m)• speed 23 m/s• distance between model departure plan and laser plan (lidar+PIV) : 8 m• distance between model departure plan and arrival plan: 22 m
lidar :• wavelength : 10.6 µm• laser Power : 3 W• Doppler sensitivity: 189 kHz/m.s-1
• speed range : 0 - 10 m/s• angular resolution : 0.05°• speed resolution : 0.05 m/s• pupil diameter : 15 mm• focus distance : 5 m• measurement volume length : 4.5 m• measurement volume diameter : 2.6 m
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5First measurement results in homodyne
configuration
0
5
1 0
1 5
2 0
2 5
3 0
3 5
4 0
4 5
5 0
a n g le °
Vite
sses
en
m/s
V it e s s e V o r t e x ( s p e c t re lo g )
1 0 1 5 2 0 2 5 3 0 3 5 4 0 4 50
1
2
3
4
5
6
7
8
9
1 0
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5Lidar/PIV comparison :PIV vector projection on lidar axis
0.5
1
1.5
2
2.5
3
3.5
4
4.5
5
5.5PIV21
850 900 950 1000 1050 1100
2900
2950
3000
3050
3100
PIV21
850 900 950 1000 1050 1100
2900
2950
3000
3050
3100
PIV vectors + Lidar axis Intensity of PIV vector projection on lidar axis
m/s
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Comparaison Lidar/PIV
-8
-6
-4
-2
0
2
4
6
8
10
12
angle °
Vite
sses
en
m/s
Vortex lidar:ts t11510e - piv:env=21
28 29 30 31 320
1
2
3
4
5
6
7
8
9
10
0
5
10
15
20
25
30
35
40
angle °
vite
sses
en
m/s
ts t1510e-datel5
28 28.5 29 29.5 30 30.5 31 31.5 320
1
2
3
4
5
6
7
8
9
10
PIV data Lidar data
dB
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5SYLVA MINI Lidar improvement
Heterodyne detection implementationSYLVA MINI Lidar improvement
Heterodyne detection implementation
LASER
telescope
mixerLocal oscillator
ν
νν + FD
FD +νol
ZV
Vr
ν+ νol
Detection
Signalprocessing
ννν
•wavelength : 10.6 µm•laser power : 3 W•pupil diameter : 15 mm•measurement volume length : 4,5 mat 5 m•measurement volume diameter : 3mm•scanning time : 0.4 s (4 wingspans)
Doppler sensitivity: 189 kHz/m.s-1
speed range : -10 +10 m/sangular resolution : 0.05°speed resolution : 0.05 m/s
AOM
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New optical Optical lidar layoutNew optical Optical lidar layout
CO 2 LASER
M2
M3
Lc
M1
Ld
LS1
LS2
Pg
AOMScanningmirror
λ/2
λ/4
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Measurement exemple (A300)Measurement exemple (A300)
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5Example of lidar measurement :
velocity spectra as a function of wing spans
Spee
d m
/s
Wing spans & (scanning angle)
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Angular position of core centre and diameterAngular position of core centre and diameter
0
5
10
15
20
25
30
35
40
0 5 10 15 20 25 30 35
wing spans
angl
e (°
)flight 106 m106 m
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Cores trajectories : repeatabilityCores trajectories : repeatability
time in seconds
Ang
le °
Repeatability : 4 successive flights, same model, same configuration
0
5
10
15
20
25
30
35
40
0 0.5 1 1,5 2 2,5 3 3,5 4 4,5
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Comparison of TOMOSCOPY & LIDAR data Comparison of TOMOSCOPY & LIDAR data
Angle °
Wing spans0 10 20 30 40 50 60
10
15
20
25
30
35
40F 13
Tomoscopy cores angular positions
Lidar cores angular positions
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Circulation calculation
• Circulation : good parameter to estimate thevortex strength and effects on potential wakeencounters
•Γ= 2.π.r.V(r) for 2.rc < r < rmaxr is the distance from the core centre2rc : core diameter
• Absolute core position given by Tomoscopy
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Circulation calculationCirculation calculation
3.5 4 4.5 5 5.5 6 6.5 70
wingspans
circ
ulat
ion
Wake vortex profile
right core position
left core position
scanning angle
vortex radius
circulation
Circulation 2rc:2
0,00
0,50
1,00
1,50
2,00
2,50
3,00
3,50
4,00
4,50
5,00
0,00 5,00 10,00 15,00 20,00 25,00 30,00 35,00
wing span
circ
ulat
ion
(m2/
s)
A300
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Circulation calculation
In B10 , lidar is side viewingPart between the cores are
mixed.
For circulation, only outerparts of the vortex are used
circulation values arebiased by superposition ofthe two vortices
In B10, altitude of flight is too low to see vortex decay
in circulation values
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New B20 facility ( 90 m x 20 m x 20 m) is operational since 2002
The lidar is set under the model trajectory good separation
between vortices accurate circulation estimation.
Catapult measurements : New B20 facility
Lidar
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B20 and B10 lidar measurements comparisonB20 and B10 lidar measurements comparison
Wing spans
Spee
d m
/s
*10
*10
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Lidar CO2Continuous Wave
Velocity resolution5cm/s
Cores localisation :10 cm
Measurements upto 100 spans
The CO2 mini-Lidar comprises two scanning mirrors for measuringvortex cores trajectories, velocity profiles and vortex circulation behinda catapulted model.
M1
B20 mini-lidar set-upwith triangulation configuration
Mobile along the track
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B20 catapult facility at LilleB20 catapult facility at Lille
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Mini lidar installation at the B20 facilityMini lidar installation at the B20 facility
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B20 mini-lidar configurationB20 mini-lidar configuration
Focus =8m
Relative sensitivity of detection (dB) for the 2 points of view
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5Example of time evolution of a vortex pair velocity spectra
measured by the mini-LIDAR (viewed from M1)
Vel
ocity
(m/s
)
span
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-0.5 -0.4 -0.3 -0.2 -0.1 0 0.1 0.2 0.3 0.4 0.5-6
-4
-2
0
2
4
6
r/span
v m
/s
flight n°21. spe e d evolution in left vortex
t/t0=0.354 span=13.861t/t0=0.578 span=22.617t/t0=0.801 span=31.328t/t0=1.023 span=40.048t/t0=1.247 span=48.795t/t0=1.472 span=57.604t/t0=1.697 span=66.405t/t0=1.924 span=75.286t/t0=2.151 span=84.149
Wake Vortex Characterisation By Lidar Triangulation inB20 facility within AWIATOR Project : example of results
Temps en s
Vitesse en m/s
0 2 4 6 8 10 12 14 16
-4
-3
-2
-1
0
1
2
3
4
0 0.5 1 1.5 2 2.5 3 3.5 40
0.5
1
1.5flight n°27....c irculation integra ted be tween b/12 & b/4
t/t0
gam
a/ga
m0
a ve rage of right and le ft vortex c ircula tionright core c ircula tionleft core c ircula tion
-2000 -1500 -1000 -500 0 500 1000 1500 20003000
3500
4000
4500
5000
5500
6000
6500
7000
7500
8000
Y(mm)
Z (m
m)
flight n°22....tria ngulation tra jec tory
right vortexle ft vortex
18 s long lidar measurement
Vortex cores trajectories Velocity profile Circulation
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5Test of a new mini lidar technology, with an allfibre lidar architecture at 1.5 µmTest of a new mini lidar technology, with an allfibre lidar architecture at 1.5 µm
Ps EErbiumLaser@1.5 µm
POL
Ps
ObjectiveTilted face
DetectionG
CirculatorT
R
Det
Lidar volume and weight divided by 10Doppler sensitivity multiplied by 7
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image globale -23112004-141501102416-vol0-global.mat
temps en s econdes (16 moyennages )
vite
sses
en
m/s
4.1 4.2 4.3 4.4 4.5 4.6
0.5
1
1.5
2
2.5
3
3.5
4
4.5
5
10
15
20
test of a new mini lidar technology, with an allfiber lidar architecture at 1.5 µmtest of a new mini lidar technology, with an allfiber lidar architecture at 1.5 µm
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OUTLINEOUTLINE
CATAPULT MEASUREMENTS
FIELD TEST MEASUREMENTS
SIMULATION SOFTWARE
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5FIELD TEST MEASUREMENTSFIELD TEST MEASUREMENTS
Dash2 : CO2 CW coherent lidar
Bemol : truck platform
Topac : optronic pointing / scanning / tracking system
Gargantua : ADC and data storage
Weather station
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Dash 2 LIDARDash 2 LIDAR10.6 µm ,coherent CW lidar
30 cm aperture
focus distance : from 50 m up to ∞longitudinal size of the probe volume :12 m at 200 m
velocity range : ± 37 m/s
velocity resolution : 10 cm/s(with 100 spectra averaged)
angular resolution : 0.17 °
real time display with a SAW spectrumanalyser
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5 LIDAR
BEMOL
BemolBemol
stabiliser
Crane +Power generator
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02/05/01 F0 n°5
time in second s
radi
al v
eloc
ity m
/s2.6404 2.6405 2.6405 2.6406 2.6406 2.6406 2.6407 2.6408
x 104
-10
-8
-6
-4
-2
0
2
4
6
8
10
Before After
LIDAR DASH II improvement (2000 2001)LIDAR DASH II improvement (2000 2001)
No speed signPoor contrast
Speed signGood contrast
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0
5
10
15
20
25
30
35-26/04/2001- FO n°10
Time in s
Rad
ial v
loci
ty m
/s
3.5727 3.5728 3.5728 3.5728 3.5729 3.573 3.573x 104
-25
-20
-15
-10
-5
0
5
10
Mesurable speed > 25 m/s in the early (wrap-up) period ( scan speed = 20 °/s)
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60
80
100
120
140
160
180
200
220
240
Temps en s
Vite
sse
en m
/s
Run0x05.vor
0 10 20 30 40 50 60
-15
-10
-5
0
5
10
15
0
50
100
150
200
250
300
350
Temps en s
Vite
sse
en m
/s
Run0x05.vor-ima5
12 12.5 13 13.5 14 14.5 15 15.5 16
-15
-10
-5
0
5
10
15 Close-up of two pairs
Over 30 intersections of lidar beamwith vortex pair
(ONERA data from C-Wake trial)
Time0 60s
0
+15m/s
-15
Fast scan: multiple intersections with vortices
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5TRIANGULATION CONFIGURATION with QinetiQ LIDAR
during WAKEOP campaign at Munich April 2001
0
40
80
120
160
200
240
120
TOPAC
LIDAR
BEMOL
Onera QinetiQ
LIDAR
wind
triangulation zone
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5Vortex trajectory computation by
triangulationVortex trajectory computation by
triangulation
-20 -10 0 10 20 30 4095
100
105
110
115
120
125
130
135triangulation Qinetiq-ONERA du : Vol 5 02/05/2001
X (m)
Z (m
)
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Strategy of lidar measurements at Tarbes airfield
Onera lidar DLR lidar
Onera lidar DLR lidar
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B20B20
-1 -0.8 -0.6 -0.4 -0.2 0 0.2 0.4 0.6 0.8 1-0.2
-0.15
-0.1
-0.05
0
0.05
0.1
0.15
0.2
r/(s pan/2)
V/V
0
flight n°10. s peed evolution in le ft vortex
t/t0=0.32 s pan=013.5t/t0=0.53 s pan=022.2t/t0=0.74 s pan=031.0t/t0=0.95 s pan=039.7t/t0=1.16 s pan=048.5t/t0=1.37 s pan=057.2t/t0=1.58 s pan=065.9t/t0=1.79 s pan=074.7t/t0=2.00 s pan=083.4t/t0=2.21 s pan=092.2
TarbesTarbes
-1 -0.8 -0.6 -0.4 -0.2 0 0.2 0.4 0.6 0.8 1-0.2
-0.15
-0.1
-0.05
0
0.05
0.1
0.15
0.2
r/(s pan/2)
V/V
0 m
/s
flight n°:1-13. s peed evolution in le ft vortext/t0=0.47 s pan=017.8t/t0=0.61 s pan=023.4t/t0=0.76 s pan=029.0t/t0=0.91 s pan=034.7t/t0=0.91 s pan=034.7t/t0=1.06 s pan=040.3t/t0=1.21 s pan=045.9t/t0=1.35 s pan=051.5t/t0=1.50 s pan=057.1t/t0=1.65 s pan=062.7t/t0=1.80 s pan=068.3t/t0=1.94 s pan=074.0
Comparison betweeen B20 and fieldmeasurements
Comparison betweeen B20 and fieldmeasurements
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OUTLINEOUTLINE
CATAPULT MEASUREMENTS
FIELD TEST MEASUREMENTS
SIMULATION SOFTWARE
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Organisation chart of SLAVALidar inputs Atmospheric
inputsVortex inputs
Backscatteringcoefficient in the lidaranalysis plan
radial velocity alongthe line of sight
Wind field in the lidaranalysis plan
Theoreticalvelocity
profile V(r)
Velocity histogram
Temporal heterodynesignal
Spectral processing
Doppler image of thewind field function ofthe scanning angle.
Vmaxpoints
positionsTheoreticalcirculation
Lidar sensitivityalong the line ofsight
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Atmospheric inputs
Aerosol profile Wind profile
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Vortex inputs : theoretical model
Comparison of ideal modelswith experimentalmeasurements made in 2002on wakes of a A340 Airbus.
Hallock-Burnham : Γ0= 436 m/s², rc=3.3m
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Vortex inputs : vortex wind field
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Lidar inputs : heterodyne detection sensitivity
Measurement volume
Axial sensitivity
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Lidar inputs : scanning pattern
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5 0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1
x 10-4
-100
-50
0
50
100
signal temporel codé 8 bits
4 4.2 4.4 4.6 4.8 5 5.2 5.4 5.6 5.8 6
x 106
0
10
20
30
40
50
60
70spectres moyennés sur Ns - échelle en dB
Heterodyne signal time serie
Spectral processing
Doppler image ofthe wind field vsscanning angle.
Outputs
TF
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Intermediate outputs : theoretical circulation
Theoretical circulation(b/12-b/4) of an Hallock-Burnham ( Γ0= 436 m2/s,rc=3.3m ):0.93*Γ0.
-0.2 -0.1 0 0.1 0.2 0.30.8
0.85
0.9
0.95
1
1.05
1.1
%
circulation as a function of core position error vortex type : Hallock-Burman : Γ0=436 m2/s ; rcore=3.3 m
circulation / theoretical circulation circulation / circulation with no core position errorVortex profil (arbitrary unit )
core position error / span
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5 Intermediate outputs : Vmax points positions
function of angle of view
mean angle of view = 90°(lidar under the vortex)
mean angle ofview = 45°
mean angle ofview = 43°
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5 Intermediate outputs :circulation vs angle of view
example of velocity spectrafor vortices at 200 m, mean angle of view= 45 °, a focusing lidar to 282 m and a signal tonoise ratio on of -5 dB
circulation functionof angle of view
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Output : velocity profiles function of SNR
S/B=10 dB
Examples : vortex altitude= 200 m , Focus distance = 200 m , angle of view =90°Profile extraction level = 2 dB above the noise level.
S/B=0 dB
S/B= -10 dB S/B= -15 dB
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Measurement strategy for unseeded vortexMeasurement strategy for unseeded vortex
-Measurement of signal to noise ratio on wind on a spectrumanalyser ( narrow bandwidth)
- Extrapolation of signal to noise ratio to the vortex analyserbandwidth.
- -
circulation as a function of SNR and focalisation
-20
-15
-10
-5
0
5
10
15
20
25
0 100 200 300 400 500 600
focalisation distance
SNR
(dB
)
ninimum signal to noise ratio for a good circualtionevaluation (circulation value between 0.9 et 1)maximum signal to noise ratio for a good circualtionevaluation (circulation value between 0.9 et 1)
vortex at 100 m
vortex at200 m
vortex at400 m
possible altitude for aircraft
tolerable defocusing
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Simulation
Atmospheric parameters : -horizontal wind speed :-5 m/s - vertical wind speed :0m/s - wind shear :
height : 100 m thickness: 5m speed gradient : 2.5 m/s
Vortex parameters :-altitude : 200 m
Lidar parameters :-mean angle of view = 74 °-focus distance = 150 m
Interpretation of real signals Interpretation of real signals
Tarbes 02 measurementSimulated velocity spectrum Experimental velocity spectrum
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Summary of lidar modelingSummary of lidar modeling
≡ SLAVA : simulation software of lidar Doppler signaturein a wind field representative of a vortex pair
≡ Main Applications for cw heterodyne lidar :- error on measured parameters estimation (core diameter,
velocity profile, circulation)- lidar measurement domain for vortex detection
≡ signal interpretation help≡ signal processing optimisation
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ConclusionsConclusions
≡ Since 1997, DST Joint Program has been an efficientsupport to :
∨ to develop first lidars at Onera for vortex monitoring∨ to improve the tools for participating to international
campaigns (C-Wake, AWIATOR)∨ to test new generation lidars at the B20 facility∨ to develop modeling tools∨ To participate to a common effort at Onera in the field of
Wake Vortex understanding.Harris, M., Young, R. I., Köpp, F., Dolfi, A., and Cariou, J.-P.Aerospace Science and Technology, Vol. 6, 2002, pp. 325-331Wake Vortex Detection and MonitoringKöpp, F., Smalikho, I., Rahm, S., Dolfi, A., Cariou, J.-P., Harris, M., Young, R. I., Weekes, K., and Gordon, N.AIAA Journal, Vol. 41, 2003, pp. 1081-1088.Characterisation of Aircraft Wake Vortices by Multiple-Lidar TriangulationHolzäpfel, F., Gerz, T., Köpp, F., Stumpf, E., Harris, M., Young, R. I., and Dolfi, A.Journal of Atmospheric and Oceanic Technology, Vol. 20, 2003, pp. 1183-1195.Strategies for Circulation Evaluation of Aircraft Wake Vortices Measured by Lidar