Transcript Document 7856493

JWST-PRES-012900
JWST OTE
Development Status
Ritva Keski-Kuha
JWST Deputy OTE Manager
May 19, 2009
1
Topics
1.
OTE Architecture Refresher
2.
Mirror Status
3.
Backplane Status
4.
I&T Status
5.
Schedule
6.
Summary
2
OTE Architecture Overview
SM Support Structure (SMSS)
• Deployable four-bar linkage strut assembly
• Secondary Mirror Mount (SMM)
Aft Optics Subsystem (AOS)
• Fixed tertiary mirror
OTE Electronics Subsystem
• Fine steering mirror
Thermal Management
• Baffle and pupil mask • CMU Boxes
• CJB Box
Subsystem (TMS)
• Panel Roof Radiators
• Panel +/- V2 Radiators
• ISIM Enclosure (MLI)
• Parasitic Tray Radiator
SM Assembly (SMA)
• Low mass Beryllium mirror
• 6 DoF pose control
PM Segment Assembly (PMSA)
• 18 low mass Beryllium mirrors
• 6 DoF pose control
• Radius of curvature control
PM Backplane Assembly (PMBA)
• Fixed Center Section supports 12 segments
• Two deployable wings support 3 segments each
Not Shown
• PMBA thermal management (SLI)
• WFS&C Subsystem
TMS (continued)
• Deployable “bat wings”
• Fixed diagonal shield
• Deployable stray light “bib”
Deployable Tower Assembly
• Deployable telescoping tube
• Two deployable harness trays
• Cryocooler line accommodation
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Three Mirror Anastigmat Optical Design
Provides a Wide Field-of-View
B1
C6
C1
B6
6.6 meters flat
to flat
A1
B2
A6
A2
C5
OTE
C2
A5
V3 (anti-spacecraft)
A3
B5
A4
B3
C4
ISIM
V1
C3
V2
(V1, V3)
origin
Cassegrain
focus
B4
Secondary
mirror
Tertiary
Mirror
1.32 meters
flat to flat
Focal
Surface
Fine
Steering
Mirror
f/#: 20.0
Effective Focal Length: 131.4 m
PM diameter = 6.6 m (circumscribed circle)
Primary
Mirror
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Mirror Status
 First Cryo test of Flight mirrors has been completed
 Hexapod performed well at cryo, cryo distortions of A1 and
EDU at XRCF as expected.
 All PMSAs have completed grinding and are in the polishing
and testing phase which includes fabrication at Tinsley,
Integration and Test at Ball, Testing at the XRCF.
 The secondary mirror-1 was shipped from Tinsley to Ball.
The mirror figure is below the specification.
 Tertiary mirror and Fine Steering Mirror making good
progress at Ball.
5
Completed 1st PMSA Tests at XRCF
Photo Credit MSFC
JWST_ISIM.May.MPR/6
JWST_ISIM.May.MPR/1
Cryotest #1 Summary
EDU
 First Cryo Conditioning Cycle,
–
–
Mirrors taken to <25K
Measurements made at 28K
A1
Temperature (K)
250
200
150
100
50
Measurement Cycle
Cryo-Conditioning Cycle #1
300
Cryo-Conditioning Cycle #2
XRCF Cryogenic Test #1 Timeline
0
0
5
10
15
20
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MEASUREMENTS
Cryo-Deformation of EDU
EDU AMBIENT
Figure
163.3 nm rms
EDU CRYO
(Piston, Tilt, Power,
Astigmatism, & Gravity
Removed)
Astigmatism
124.7 nm rms
(Piston, Tilt, Power,
Astigmatism, Gravity
Removed)
-3.832 mm
182.0 nm rms
Astigmatism
79.4 nm rms
As-Measured 
ROC
Temperature = 292K
Dataset: 7040.407AB
Cryo-Deformation
(Piston, Tilt, Power
Removed)
DIFFERENCE
As-Measured 
ROC
Figure
RoC Change
-18.997 mm
-2.636 mm
Temperature = 29K
Dataset: 7040.410
Total Cryo-deformation = 142.7 nm rms
Astigmatism
RMS: 115.4 nm rms
Mid/Low Figure
RMS: 82.0 nm rms
High Freq Figure
RMS 25.0 nm rms
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Significant Accomplishments/Status
L-3 SSG-Tinsley
Pathfinder
EDU
Flight
Flight
TM1
C7
EDU
B2
LEGEND
SM1
B8
FSM
C1
C6
B3
A1
Not at L-3 SSG-Tinsley
A6
Even Slice
A2
Figure Grind
Smooth Out Grind
C5
Rough / Smooth Out
Polish Interleave
A5
Fine Figure Polish
Shipped to BATC
Cryo Null Figure
Final Optical Test
Delivered
– – – – – Pathfinder
BATC MSR 04/29/09
SM2
B7
C2
A3
A4
C4
B5
C3
As of 4/18/09
B6
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Secondary Mirror Assembly Progress
SM substrate
Ball SM Test Optics
mjm-09-tms-0852
SM Hexapod ready for assembly to substrate
Tinsley SM Test Optics
10
Tertiary Mirror and Fine Steering Mirror
TM substrate and sub-bench
TM testing
mjm-09-tms-0852
TM in optical test stand
FSM in vibration testing
11
Mirror Coating Preparation is Progressing
at QCI-Denton
Coating GSE being loaded into Chamber
New JWST Coating Chamber
mjm-09-tms-0852
12
Structures Status
 Backplane making good progress at ATK
– Flight Center Section bonding in progress
– Pathfinder CS bonding going well
 Completed layup and cure of the first Pathfinder SMSS strut
 Completed SMM (Secondary Mirror Mount) CDA 4/28/09
 Near term reviews
– SMSS/PMBA CDA August 2009
– DTA CDA August 2009
– PMBSS CDA September 2009
SMM
13
Tube Billets and SMSS Pathfinder Strut
Tube billet storage rack
First SMSS Pathfinder Strut
14
Pathfinder and Flight Backplane
Assembly
15
I & T Status
 Completed CDA for majority of the SSDIF Alignment and Integration
Hardware and JSC Test Hardware.
 Null lens optics have been ordered
 ACF#1 Skip Test execution starting in November 2009
– ACF Mirror Blanks are in procurement
 Chamber isolator demonstration is in progress.
 PIT Review scheduled for July 2009
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Ambient Assembly Stand
Assembly Support Structures
Optics Integration Gantry
System
+V1-down Configuration
HP Struts
+V1-up Configuration
Ambient OTE Assembly Stand
& Hardpoint Struts
mjm-09-tms-0852
HP Struts
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Test GSE Architecture and Subsystems
N
• Isolation System
• Down Rods
• Upper Suspension Frame (USF)
• Telescope Tension Rods
• Space Vehicle Thermal Simulator
(SVTS) by NG
• Hardpoint Offloader Support
System (HOSS)
Center of Curvature Optical
Assembly (COCOA)
• COCI (MWL interferometer, null,
calibration equipment)
Autocollimating Flat Mirrors (ACF
Assembly)
• 3 ACFs (actuated motion)
• Rogue Path
• Cryo Position Metrology
•
• Fiber fed PM Lights
LN2 and Helium Cryogenic
Shrouds
Optical Telescope Element (OTE
Integrated Science Instrument
Assembly (ISIM) – (OTIS)
E
mjm-09-tms-0852
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Architecture Layout
Chamber Isolation
Assembly
26.3 ft
(8.0 m)
COCOA
Upper Suspension
Frame
Ref. - JSC Chamber A
ACF 3X
COCOA to
PM
Distance
52.1 ft
(15.9 m)
Port Flange
to
GHe Shroud
89.4 ft
(27.2 m)
56.2 ft
(17.1 m)
Telescope Rod
Assembly
ACF to PM
39.0 ft
(11.9 m)
+V1
+V2
OTIS
HOSS
Top of HOSS to GHe Shroud
5.8 ft (1.8 m)
mjm-09-tms-0852
Ref. - OTIS and Thermal Sim(s).
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NGST OTE Intermediate Schedule
BATC MSR 04/29/09
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Summary
 First Cryo test of Flight mirrors has been completed
 All PMSAs have completed grinding and are in the polishing
and testing phase which includes fabrication at Tinsley,
Integration and Test at Ball, Testing at the XRCF
 The flight backplane fabrication is in progress
 CDA for the majority of the SSDIF Alignment and Integration
Hardware and JSC Test Hardware has been completed
 OTE CDA Scheduled for October 2009
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