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Thirty Meter Space Telescope (TMST)
Conceptual Mechanical Design Development
J.Budinoff/544
March 2007
PRE-IDC EELV Concept
• EELV class packaging
• How do we do this? Can we? Will they
laugh?
█ = advantage
TMST Launch Packaging Trade
Effects
Trade
Sequential Packaging
Optimal Packaging
higher stack height
lower stack height
FSE Structures
More FSE/carriers
Less FSE carriers
Launch Mass
Higher (due to above)
Lower
Robotic Assembly
Timeline
Faster Assembly, less
intermediate steps
Slower Assembly
Temporary Stowage
of Components
Stack is temporary
storage site
Requires intermediate
temporary stowage site(s)
Post-Assembly FSE
Utilization
To many FSE units for
solar sail
Adequate amount of GSE for
solar sail
Robotic Access to
Components
Simple due to sequential
packaging
Requires robotic prearrangement of work
packages
Launch
Launch Stack Height
Configurat
& CG
ion
Orbital
Assembly
•
Conclusion: Pursue Optimal Packaging Approach
–
–
Minimizes required fairing volume & launch mass, and take the orbital assembly efficiency hit
Higher packing efficiency minimizes FSE “inert” mass
Mirror Segment Map
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Concentric Circles
Diameter 37.5m
966 1m segments with 50mm min gap
68% fill factor
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Isogrid
Diameter 41.8m
1014 1m segments with 200mm min
gap
58% fill factor
Optical Telescope Assembly (OTA)
Side View
OTA structure
OTA Truss Structures
Looking up the inside of the metering tower from the primary to the
secondary
F2 Gregorian
Observatory Layout
45 degree
FOR
1m lasercomm
3m
HGA
Main Solar
Array
Radiators
Early
Assembly
Solar
Panel
Launch Manifest
• TMUST can be broken into 10 Delta
IV/Atlas V (EELV-class) launch packages
EELV Launch Kits
10 ISIM
09 Edge Panels & 2ndry
08 Edge Panels &
cables
07 Mirror & Met. Truss
06 Mirror & Met. Truss
05 Mirror & Met. Truss
04 Mirror & Met. Truss
03 Mirror & Met. Truss
02 Solar Array & Shield
01 Bus
Kit 1 Bus
• Bus structure
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–
–
–
–
Deployable Radiators
Deployable Solar Array
3m HGA
1m Lasercomm gimballed telescope
Propulsion
Kit 2 Sunshield, Main Solar Array
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Mated to bus
Able mast deploys sunshield & main solar array using bus power
Thermal Isolation interface
Backplane Edge Panels
Kit 3-7 Mirror & Metering Truss
Stacks
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Mirror segment groups pre-integrated onto backplanes
Backplanes “puzzle-piece” together to form complete mirror/backplane.
Mirror/backplanes thickest in center ring, thinnest at edge ring
Mirror/Backplane segments may be removed (from the back) for servicing
Metering Truss bay frames and beams stored at intermediate site until
backplane hub assembled.
Metering truss built from backplane hub
Kit 8 Backplane Edge Panels &
Cables
• Panels closeout edges of backplane
• Allow backplane to maintain stiffness if
mirror/backplane pieces removed for servicing
• Cable rigging assemblies allow agents to run tiedown cables from backplane to metering truss
Kit 9 Backplane Edge Short Panels
& Secondary Mirror Assembly
• Delta IV Medium Fairing
• Brings remaining Short Edge Closeout panels
– first short panels brought in kit 2
• Integrated secondary mirror assembly placed at end of metering
truss
Kit 10 Aft Optics & Science
Instrument
• Aft Optics, Focal Plane, Guider Optics, Science
Instruments
• Agent serviceable
IDC Concept
• EELV or notional large launch vehicles
• Develop observatory bus concept (IMDC)
• Further detail the OTA (ISAL)
Gregorian 7
0.012-mm pixels, f/2 Primary; BFD=3000-mm
932554 GREGORIAN 60000
Optimized by ZEMAX
System Focal Length: 932554
Primary Focal Length: 60000
Primary Vertex Radius: 120000
cc=k = -1 for paraboloid: ¯1
-0.9994331
Back Focal Distance: 3000
Focal Plane Conic Constant: -1.1152303
Secondary Magnification: 15.5425666666667
Secondary Focal Length: 4332.1101043603
Ellipsoid Focus Distance: 31500
Ellipsoid Major Axis: 35832.1101043603
cc = k = -Eccentricity*2: ¯0.772816417814355
Ellipsoid eccentricity : 0.879099776939088
eccentricity: 0.879099776939088
origin to focus (c): 31500
focus to focus dist (2c): 63000
conic constant (k=-e*2): ¯0.772816417814355
major axis (a): 35832.1101043603
vertex to vertex dist (2a): 71664.2202087206
focus to vertex (a-c): 4332.11010436031
minor axis (b): 17078.9377459782
|
Vertex Radius| (R): 8140.46713077902
Vertex to Second Focus: 67332.1101043603
Focal Plane Radius: 4315.9622861
-0.7793285
Optimized Gregorian 7
0.012-mm pixels, f/2 Primary;
BFD=3000-mm
Field
10
0
40
70
50
80
30
20
60
90
Angle
arc-sec
Strehl
Ratio
0
1.000
10
1.000
20
0.999
30
0.996
40
0.987
50
0.968
-90 ARC-SEC 60
0.935
70
0.883
80
0.809
90
0.711
Circles in Radially Uniform Rings
Segmented 35.0 m
Monolithic 30 m
Overview
• 32.2m effective diameter
– 15% surplus collecting area
over 30m
• 37m actual diameter
• 60m primary to secondary
spacing
• ~44m Dia Hexagonal
Sunshield
– Tension preload provided by
outrigger cables
– Sunshield & outriggers
achored aft of isolation stage
• Core metering ring
– ISIM attached to ring
• .86m optical backplane truss
• 3.5m Support Truss
– 2 Layers
• Truss members composite with
aluminum end fittings/nodes
• Isolation stage
– Active thermal and mechanical
isolator
– LM DFP or similar active
isolation
• ISIM
– Accommodates 4 axial
instruments
– Integral install / remove slides,
similar to drawers to simplify
change out operations
– Requires interface truss to
allow ISIM drawers to slide aft
TMST Initial Instrument Suite
• 4-6 instruments reside in a JWAT/ISIM-like instrument
bay, analogous to HST axial instrument bay.
– Instruments designed for robotic changeout
• Conjectural 5 instrument suite considered:
1)
2)
3)
4)
Full Nyquist Sampled High Resolution Camera
Multi-Filter High Resolution Camera
Wide Field Half-Nyquist Sampled Camera
High Resolution Spectrograph
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STIS-like Instrument
Echelle Component
5) Multi-Object Spectrograph
Isolation Structure
OTA Details
Secondary &
Baffle
Interface Truss
Backplane
Truss
3 Spider
Vanes
Metering Tower
42.8m
ISIM &
Metering
Ring
2 layer
support
Truss
OTA Structure
Secondary &
Baffle
Isolation Structure
Interface Truss
Mirror
Segments
ISIM &
Metering
Ring
3 Spider
Vanes
Metering Tower
42.8m
Backplane
Truss
2 layer
support
Truss
Alternating Rings of
Spacers (purple) and
Mirror Truss (white)
Backplane
cable anchor
1st OTA mode = 7.1 Hz (without
cables)
Outrigger Booms
Sunshield
Tension cables
Rigid Aperture Frame & Masts
support a blanket sunshield…
Similar to a tent
Shield anchors aft
of isolation
structure
OA dimensions w/ sunshield
80 m
92 m
140 m
Mirror Segment
• 1037 1m Segments
• 15% can be non-op
• 15 Rings, 10mm min
gap, 73% FF
ring
radius
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
3.51
4.52
5.53
6.54
7.55
8.56
9.57
10.58
11.59
12.6
13.61
14.62
15.63
16.64
17.65
total
Deployed height, 148mm
Stowed height, 115mm
num
25
31
38
44
50
57
63
69
75
82
88
94
101
107
113
1037
Mirror Truss
6 DOF Segment Detail
XY Actuator
Mirror Tripod
Leg with flexural
interfaces
1m Dia Mirror
x 50mm thick
Ebox
Composite Tray
locks into
triangular truss
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30 mm pallet mounts 8 mirrors &
backplane truss elements
– All supporting hardware for backplane
truss assembly to mount the mirrors
on
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4.5 x 0.18 m (can fit 67 into a D4
heavy fairing)
Stackable
– Requires external edge support
beams
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Mass TBD
All primary mirror segments &
complete backplane truss (1st layer)
can fit in 2 EELV 22.4m fairings
Harnessed for survival heaters, data
Pallet acts as parts caddy when destacked and attached to assembly
robot
Backplane truss
elements of various
lengths
Mirror/Backplane
Pallet
1m mirror w/ cover
Assembly
Robot
Builder Bot
4 7DOF arms
3x2.5m arms
1x4m arm
2 Pallets attach to
opposing turntables
mounted on the arms,
allowing the bot to
access either pallet from
any wrist orientation.
18m Walking Crane
7 DOF = 2x3DOF wrists + 1DOF elbow
Identical end effectors at both ends
4m arm grabs parts from
pallet and continuously
feeds them to 2.5m arms
for installation
Crane end-effector interface
on face allows crane to
translate without removal of
builder bot
Tools &
interchangeable end
effectors stowage on
rear body
4 pan/tilt
camera/light/sensor
groups with
>hemispherical
coverage
OTA build phase
Dual pallets allows robot
to continue building after it
empties a single pallet; a
support robot would
exchange the empty pallet
for a new one. This allows
the “working” robot to
continuously build
independent of pallet
count until translation to a
new worksite is required
OTA final build phase
D4 Heavy-sized build
kits at temporary
stowage locations
Robot installing the
last of the mirror
segments
Partially-used build kit
at ready stowage
location
Bus Details
Summary
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IMDC bus elements incorporated with the ISAL design
– Assembly to take place within sunshield/baffle
– Modification of IMDC bus layout to facilitate launch packing AND early assembly
stages
•
Preliminary launch packaging concept developed for “LV27.3” vehicle based
on December 2005 ESAS report
– TMST can be packaged into a single launch element Ø7.5m x 32.2 m, ~200mT
– TMST cannot be packaged into a single LV27.3
• PL bay Ø7.5m x 12.5m
• 2 LV23 LAUNCHES MAY BE ABLE TO LIFT TMST
– TMST could be lifted to LEO in a single launch of a 27.3 “+” vehicle IF:
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Payload bay was stretched to 33m
Further optimization of OTA structure results in considerable OTA mass reduction
Addition of an extra pair of 5 segment ESRB’s to LV27.3, increasing the total to 4
Launch to LEO instead of L1 or Lunar orbit; with delivery to L2 via tug or enhanced
capability propulsion module(s)
POST-IDC Concept
• VSE ESAS LV 27.3+ class packaging
• “All-up” single launch in stretched fairing
Post-IDC TMST
IMDC TMST
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Overall Picture of IMDC bus W/ ISAL
OTA & LV27.3 bus modifications
Highlight changes to BUS component
layouts for packaging & assembly
considerations
Temp stow of component stack &
robots INSIDE the sunshield
POST-IMDC TMST
ISS-Style
Deployable
Solar Arrays
Deployable
HGA’s
TMST “All Up” Single Launch
Package
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In-Line Shell Carriers with connecting longerons
OTA Stacked on top of bus components
Sunshield boxes surround central ISIM, Isolation ring, and MWA’s;
Propulsion modules are at the base of the stack.
Stack Dimensions Ø24.5’/7.5m, 105’/32.2m long
Carrier-Longerons
Individual Carriere Shells
Component Stacking
Truss beams
on Truss
Carrier Shell
2X Main and 2X RCS Prop
Modules on Propulsion Carrier
Base Shell
5X 215 Mirror
Trays on
Optics Carrier
Shell
12X Sunshade Boxes
radially stowed
boxes, 2 removed for
clarity
6X RCS Modules on
Propulsion Carrier
Shell
ISIM With 4
instruments
Isolation Ring & ACS
Cluster MWA’s
Main Carrier
Shell
2X Assembly
bots
Bus with deployable
HGA’s and Solar
arrays
LV27.3 Fairing Size Issues
39m
128’
22m
72.2’
12.5m
39.4’
TMST Fairing
ESAS Fairing
• Fairing as described in ESAS
report are for 39.4’ payload
cylindrical section only and
does not include conical
volume
• TMST cannot fit within
standard fairing but could
possibly be packaged to fit
within 2 launches
• TMST could fit within a fairing
of ~30m/105ft cylindrical
length, total length 39m/128 ft
based on ESAS report fairing
scaling
ESAS LV27.3/27.3+
• LV27.3
• LV27.3+
– 39.4’ fairing
– 2X 5-Segment
ESRB
– 92.2’ fairing
– 4X 5-Segment
ESRB
Earth
Departure
Stage
4X 5-Segment
ESRB
357.6’
415’
Scale Comparison
TMST OBSERVATORY
FULLY ASSEMBLED
TMST LAUNCH
PACKAGE
Early Assembly Stage
•
Partial bus deployment provides
power, communication, attitude
control PRIOR to robot
deployments
EML1 to SEL2 and back again
Tug Transfer Trajectory
Rendezvous Area
RenDV1 = 580m/s
RenDV2 = 653 m/s
L2
Earth
Moon
L1
LV Transfer Trajectory
Earth- Moon Rotating Coordinate System
SPIE Concept
• ESAS LV27.2 packaging
• No special modifications
Current “SPIE” Version of TMST
Packaging of TMST into three
heavy lift Cargo launch vehicles
ISIM, Isolation Ring,
and Secondary ACS
Cluster
Secondary Mirror
Assembly
Sunshade
Canister
Elements
7.5m fairing Outline
Tray holds
196 segments
Bus, Sunshade, and
OTA Truss Elements
Carrier
Structure
OTA Truss
Elements
Propulsion Units
Bus with 4 Robots, 4m
HGA’s, Deployable
Solar Arrays,
radiators, and Primary
ACS cluster
Mirror
Segment
Trays
FLIGHT 1
FLIGHT 2
FLIGHT 3
3 Flight Build Up
Flight 2
Flight 1
Flight 3