Hubble Space Telescope Goddard Space Flight Center Hubble Ultra-Wide-Field Imager (HUFI) David...
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Hubble Space Telescope
Goddard Space Flight Center
LOGO.049
Hubble Ultra-Wide-Field Imager (HUFI)
David Leckrone
Senior Project Scientist for HST
December 16, 2001
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Hubble Space Telescope
Goddard Space Flight Center
LOGO.049
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Hubble Space Telescope
Goddard Space Flight Center
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Hubble Space Telescope
Goddard Space Flight Center
LOGO.049
(69 arcmin2)
HUFI(90 arcmin2)
(5.7 arcmin2)
(11.3 arcmin2)
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Hubble Space Telescope
Goddard Space Flight Center
LOGO.049
Field of View
FOV Footprint at CCD FPA
-40
-30
-20
-10
0
10
20
30
40
-110 -100 -90 -80 -70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 80 90 100 110
X image (mm)
y i
ma
ge
(m
m)
FOV at CCD CCD 1
CCD 2 CCD 3
4 K x 4 K CCD (3 each)
90 square arcminute FOV
hstfullfd.14,11/14/01, p. 44
4K x 4K CCD’s (3)
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Hubble Space Telescope
Goddard Space Flight Center
LOGO.049
Optical Schematic15:43:51
HST Full Field.14, 11/12/01, p44-45, 90 Scale: 0.09 raw 14-Nov-01
277.78 MM
M1 MirrorM3 Mirror
M2 Mirror
Radial “Pickle”Pick Off Mirror (POM)
HST OTA
CCD FPA
Filters, CCD Shutter Location
Pupil
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Goddard Space Flight Center
LOGO.049
Geometric ray trace compared to two-pixel and four-pixel width scale-bars shows a well-corrected design.
09:13:30
0.000,0.202 DG 0.00, 0.86
0.000,0.233 DG 0.00, 1.00
0.000,0.130 DG 0.00, 0.56
0.165,0.165 DG 1.00, 0.71
0.130,0.130 DG 0.79, 0.56
-0.17,0.165 DG-1.00, 0.71
-0.13,0.130 DG-0.79, 0.56
.0893,0.216 DG 0.54, 0.92
.0570,0.130 DG 0.35, 0.56
FIELDPOSITION
DEFOCUSING 0.00000
HST Full Field.14, 11/12/01, p44-45, 90
.300E-01 MM
09:16:27
0.000,0.202 DG 0.00, 0.86
0.000,0.233 DG 0.00, 1.00
0.000,0.130 DG 0.00, 0.56
0.165,0.165 DG 1.00, 0.71
0.130,0.130 DG 0.79, 0.56
-0.17,0.165 DG-1.00, 0.71
-0.13,0.130 DG-0.79, 0.56
.0893,0.216 DG 0.54, 0.92
.0570,0.130 DG 0.35, 0.56
FIELDPOSITION
DEFOCUSING 0.00000
HST Full Field.14, 11/12/01, p44-45, 90
.600E-01 MM
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Hubble Space Telescope
Goddard Space Flight Center
LOGO.049
Optical Performance09:24:39
raw 19-Nov-01DEFOCUSING 0.00000
HST Full Field.14, 1
1/12/01, p44-45, 90
DIAMETER OF CIRCLE (MM)
ENCIRCLED ENERGY
0.0E+00 7.6E-02 1.5E-01 2.3E-01 3.0E-01 3.8E-01 4.5E-01 5.3E-01 6.1E-01 6.8E-01 7.6E-01 0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
(0.000,0.202) DEGREES (0.000,0.233) DEGREES (0.000,0.130) DEGREES (0.165,0.165) DEGREES (0.130,0.130) DEGREES
Diffraction PSF encircled energy @ =632.8 nm for center field and 4 other fieldpositions show that PSF is diffraction-limited and is uniform over full FOV
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Hubble Space Telescope
Goddard Space Flight Center
LOGO.049
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Hubble Space Telescope
Goddard Space Flight Center
LOGO.049
Instrument Layout
Pick Off Mirror
M3
M1 Corrector Mechanism
Filter Mechanism
Shutter Mechanism
CCD Heat Pipes
M1
Calibration Door Mechanism
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Hubble Space Telescope
Goddard Space Flight Center
LOGO.049
Instrument Layout
CPL Saddle To AS Radiator
Optical Bench
Radiator
Point C(Point B Opposite Side)
Strut
FGS Enclosure Side
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Goddard Space Flight Center
LOGO.049
Instrument Layout
M2
M2 SupportFGS Enclosure
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Hubble Space Telescope
Goddard Space Flight Center
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+V2 SIDE OF HST
FGS3 BAYNCS RADIATOR
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Goddard Space Flight Center
LOGO.049
HUFI Design Features
• All-Reflective Design
– Four surfaces – one flat, three powered
• Well-Corrected Aberrations
– Wavefront error 0.0451 to 0.0523 waves rms at 632.8nm
• Flat Focal Surface
– Requires three 4Kx4K CCD’s similar to ACS and WFC3 detectors
• Cooling Via HUFI External Radiator Plus Coupling To NCS Radiator
• Replaces FGS #3 Without Compromising Current Pointing Performance
• Does Not Interfere With Other Instruments
– Amenable to parallel observing
– Follow-up observations with WFC3, COS, ACS, STIS
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Goddard Space Flight Center
LOGO.049
HUFI Scientific Performance
• FOV – 90 arcmin2 (8xACS, 16xWFPC2)
• Pixel Scale – 0.10 arcsec (same as WFPC2)
• Sensitivity – Comparable to ACS in I-band, 5x WFPC2 in I-band
• Discovery Efficiency – 8xACS, 80xWFPC2
• SNe Ia Discovery Rate - ~1 per day with follow-up
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Goddard Space Flight Center
LOGO.049
POTENTIAL OBSERVING STRATEGY
• 3-6 Month campaigns dedicated to high galactic latitude fields
• Deep exposures with WFC3, COS, ACS broken into multiple visits – HUFI parallel exposures for “free”
• SN detected in HUFI fields followed with other HST instruments
– STIS spectra for redshifts and classifications up to z=1.2
– WFC3 near-IR images and grism spectroscopy up to 1.7 microns
– ACS higher resolution images for host galaxy morphology
200 SNe la + M = 10%200 SNe la
200 SNe la + MAP + Ho = 10%200 SNe la
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Goddard Space Flight Center
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Wild Field Planetary Camera 2COSTARGyrosSolar Arrays
Launch!
Imaging SpectrographNear Infrared CameraFine Guidance Sensor
GyrosAdvanced ComputerFine Guidance Sensor
Advanced CameraSolar ArraysPower Control UnitNICMOS Cooling System
Wide Field Camera 3Fine Guidance SensorAft Shroud Cooling SystemBatteriesGyros
SM1
SM2
SM3A
SM3B
SM4End ofMission
?HUBBLE
MISSIONSHUBBLE
MISSIONS
1990 1993 1997 1999 2002 20042010
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Goddard Space Flight Center
LOGO.049
RETIREMENT OPTIONS FOR HST
• One Shuttle flight allocated to HST after Servicing Mission 4 in 2004
• Current baseline plan is to return HST to the ground in 2010
– Exhibit in National Air & Space Museum
– Requires partial disassembly and disposal of multiple pieces in orbit (e.g. solar arrays, external radiators, possibly instruments)
– 5 EVA mission
– Requires HST to be stable and commandable
– Less than 50/50 chance that HST will function to 2010
• Alternative option
– “Light” servicing mission in 2007 instead of 2010
– Maximizes probability of zero downtime between HST and NGST
– Attach propulsion module to HST for end-of-mission controlled re-entry
– Provides possible opportunity for new instrument, e.g. HUFI
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Hubble Space Telescope
Goddard Space Flight Center
LOGO.049
.0
.5
1.0
0 1 2 3 4 5 6 7
Elapsed Time - Years
Pro
ba
bil
ity
Probability of HST Science Operations vs. Time Since Last Servicing Mission
9/10/01 HST Reliability Indicator from theRefined Aerospace Corporation Model
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Hubble Space Telescope
Goddard Space Flight Center
LOGO.049
SUMMARY
• We’ve identified an instrument design which provides a major increase in FOV compared to prior HST cameras
• A systematic campaign should yield ~1 SNe per day with follow up provided by full suite of HST instruments
• Flight opportunity requires change in current baseline retirement plan for HST and willingness of Code S to support a new HST instrument
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Hubble Space Telescope
Goddard Space Flight Center
LOGO.049
Thermal Block Diagram
NCSRadiator
ExistingInserts
40 wattsto AS
120 watts to NCS Radiatorusing HP/VCHP to carryheat from CEB and CCDs
90 watts electronics tomodified “door radiator”
using HPs
HUFIRadial SI
“New”Radiator/
Door
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Hubble Space Telescope
Goddard Space Flight Center
LOGO.049
Power Flow
NCSRadiator
Diode BoxAuxilary
Power Ports
60 wattsFrom HST
190 watts from NCS Radiatorauxiliary power supply
HUFIRadial SI
Total estimated power requirement of 250 W