performance analysis of the ngst “yardstick” concept performance analysis of the ngst...
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Performance Analysis of the NGST “Yardstick”Concept via Integrated Modeling
Gary Mosier, Keith Parrish, Michael FemianoNASA Goddard Space Flight Center
David Redding, Andrew Kissil, Miltiadis PapalexandrisJet Propulsion Laboratory
Larry Craig, Tim Page, Richard ShunkNASA Marshall Space Flight Center
August 2000
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NGST “Yardstick” Concept
“Open” telescope (no external baffling) allows passive cooling to 50K
Deployable secondarymirror
Berylliumprimary mirror
Space support module (attitude control, communications, power, data handling) is on warm side
ScienceInstruments
Large (200m2) deployable sunshield protects from sun, earth and moon
Isolation truss
3
X
Y Z
sunshield long booms
sunshield short booms
Integrated Science Instrument Module
spacecraft module
isolation truss
OTA
Observatory FEM
Model contains ~5400 DOF
4
IMOS Environment
DESIGNPARAMETERS
MODELINGTOOLS
SYSTEM MODEL
THERMALDISTURBANCES
MECHANICALDISTURBANCES
ControlDesign
StructureDesign
OpticsDesign
MATLABIMOS FEMNASTRAN
STRUCTURE
CONTROLS
OPTICS
SCIENCEMETRICS
TRASYS /SINDA
SYSTEM PERFORMANCE
MATLAB
ENVIRONMENT
OPTICALERRORS
∫
MACOS
Integrated model was applied to investigate three “focus” problems during concept development phase:
• thermal-elastic deformation of OTA
• line-of-sight stability (jitter)
• wavefront sensing and control (not really addressed here)
5
System Error Budget Overview
System imaging performance
Straylight
Wide-anglescatter
Detectioneffects
Jitter
Post-WFS&Coptical aberrations
OTA figure& alignment
IM figure& alignment
OTA actuatorperformance
Imagingperformance
OTA structure OTA optics IM structure IM opticsOTA mechanical
Encircled Energy
WF error
WFS&C
WF C subsystemWFE budget
SystemEE , SR budget
Non-WF C subsystem s WFE budget s
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Thermal-Elastic Analysis
• Linear Systems Model
• Optics Model
• Thermal Model
• OTA FEM
• Results for launch-to-orbit cooldown
• Results for transient (attitude re-orientation)
• Results for transient with active thermal control
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Linear Error Model for Thermal Analysis
Linear optical model
w0 = Cx x + Cu u0
WF sensing
west = w0 + dwest
Control
u1 = -G west + du
G = Cu+ = [Cu
TCu] -1 Cu
w
xrb
xfig
udm
useg x =
xsegrot
xsegtrans
xIMrot
xIMtrans
xfig
u =
usegrot
usegtrans
uSM
udm
w =
w1
w2
wN
Alignment and figure states
Wavefront sampled atN discrete points in theexit pupil
Optical controls
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X
Y
Z
OTA FEM
• 2.00mm thick face sheet by 4cm deep core orthogridberyllium mirror shell
•cells are 14.5 cm on a side equilateral triangles,cell wall are 1.00 mm thick
• RBE2s used to attach SIkinematically to center main ring instead of CELAS
• Three OTA to S/C I/F points instead of four
•The petal reaction structure is a beryllium frame-work of I-beams
• The center segment reaction structure is a flat Beryllium frame with a 1.3M dia inner ring. The frame is composed of a 152 mm deep I-beam inner ring and 152mm by 100mm wide box section outer ring and spokes.
• recover 1044 DOFs (344 nodes on PM, translation only, plus SM and SI)
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Steady State Temps Mapped on OTA FEM
X
Y
Z
52.84
49.54
46.24
42.93
39.63
36.33
33.03
29.72
26.42
23.12
19.82
16.51
13.21
9.908
6.605
3.303
0.
V1L100C50
Output Set: temperaturesContour: Table Output Vector 1
Mapping made possible by one-to-one nodalization !!!
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Computing the Transformation from Nodal Temperatures to Displacements
λ Net Force Balance: {rnet} = 0 = -Ku + {rTemp}
Where {rTemp} = ∫ BT E {ε 0} dV = Ku
B = standard strain-displacement matrix{ε0}= temperature induced strain vector, f (α,temp)
λ We can factor out nodal temperatures, generating a temp to load transformation matrix
– {rTemp} = {rg} = [Agg] {tg}
Where {tg} = nodal temperature (and/or gradient) vector (g-size)
{rg} = nodal force (and/or moment) vector (g-size)λ Reduce [Agg] to f-set size and transform to Local (NASTRAN global) system
– [Afg] = [Tfg] [Agg]
λ Premultipy by the flexibility matrix [Kff]-1 to get the temperature to displacement transformation matrix G
– [Gfg] = [Kff]-1 [Afg]
λ Expand to g-set, and transform back to the basic coordinate system
– [Ggg] = [Tfg]T [Gfg] or
– [Ggg] = [Tfg]T [Kff]-1 [Tfg] [Agg]
λ So we have the temperature to displacement transformation matrix
– {ug} = [Ggg] {tg}
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Steady State Wavefront Error with Control
On-Orbit Thermal
Wav
efro
nt
WFE=4.6271e-0520 40 60 80 100
20
40
60
80
100
Ima
ge
Strehl=0.006111120 40 60 80 100 120
20
40
60
80
100
120
After Segment Control
WFE=2.3886e-0720 40 60 80 100
20
40
60
80
100
Strehl=0.6055520 40 60 80 100 120
20
40
60
80
100
120
After DM Control
WFE=2.4702e-0820 40 60 80 100
20
40
60
80
100
Strehl=1.011720 40 60 80 100 120
20
40
60
80
100
120
Limited DM Control
WFE=7.7059e-0820 40 60 80 100
20
40
60
80
100
Strehl=0.9647220 40 60 80 100 120
20
40
60
80
100
120
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Thermal Transient following 22.5 degree slew
4 8 . 8
4 9 . 0
4 9 . 2
4 9 . 4
4 9 . 6
4 9 . 8
5 0 . 0
5 0 . 2
0 1 0 2 0 3 0 4 0 5 0 6 0 7 0 8 0
D u r a t i o n ( h r s )
Tem
pera
ture
(K
)
2 9 . 5
2 9 . 6
2 9 . 7
2 9 . 8
2 9 . 9
3 0 . 0
3 0 . 1
3 0 . 2
3 0 . 3
0 2 0 40 6 0 8 0 1 0 0 1 2 0 1 4 0 1 6 0
D u r a t i o n ( h r s )
Tem
pera
ture
(K)
Cold Petal(space-side)
Hot Petal(sun-side)
∆T = -0.8 K
∆T = -1.3 K
• Initial attitude has sun normal to sunshield• Final attitude is 22.5 degree pitch away from sun• Thermal equilibrium takes DAYS to reach
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Thermal Transient Wavefront Error – no Control
0 5 10 15 20 25 300
1
2
3
4x 10
-7 Wavefront Error vs. Time
Time (hr)
WF
E R
MS
(m
)
0 5 10 15 20 25 300.7
0.8
0.9
1Strehl Ratio vs. Time
Time (hr)
Str
eh
l
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Jitter Analysis
• Pointing Control Architecture
• Linear Systems Model
• Disturbance Model
• Compensation Model
• Results for parametric studies
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The CSI Challenge for NGST
frequency
ACS 0.025 Hz BW
Disturbances >400 Hz
FSM 2 Hz BW
Structure
sunshieldmodes
isolation truss andSM support modes
higher ordermodes
• Lightweight, flexible structure with very low damping limits ACS bandwidth• FSM bandwidth limited due to guiding sensor noise• Thermal environment presents challenges to “smart structures” solutions for active damping and vibration suppression
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System Level Block Diagram
Optics
Wavefront
LOS Control
ExternalTorque
Dynamics
Centroid
ACSCommands
ACS
6 4
3
74
74
2
72
72
72
6
6
3
3
2
VibrationIsolation
ACS uses wheels,gyros & trackers
ImageStabilizationloop usesNIR & FSM
Vibration Isolationhas not beendesigned in detail;model is a LP filterapproximation
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State-Space Model
111
11111
XCY
UBXAX
=
+=&
222
22222
XCY
UBXAX
=
+=&
333
33333
XCY
UBXAX
=
+=&
444
44444
XCY
UBXAX
=
+=&
1U
KFη++
+
GSη
RWℑ
W
C
2U
3U
4U2Y
1Y
3Y
4Y
+
+
4K
11K
12K
22K
21K
3K
+
+
+
++
CXYBUAXX
=+=&
ℑ
=
RW
KF
GS
U ηη
=
4
3
2
1
X
XX
X
X
=
CW
Y
+
=
4000000
00
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3143
222221212
411
ACBACKB
CKBACKBCBA
A
=
4
3
2
0000
00000
BB
BB
=
0000
222121
212111
CKCKCKCK
C
rays
T
W NWW
=σ CCTC =σ
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Dynamics Model Sensor & Actuator Locations
ACS (10291)
ISIM (825)
SM (829)
PM (900-908)
These grid points are locatedat the center of the primary andin a circle with radius 2.8 meters,connected to mirror grid pointsby RBE2 elements
ST, IRU, RWAare co-located
FSM, DM, otheroptics are co-located
Model size is~ 5400 DOF;only 71 DOFare requiredfor jitter model
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Optomechanical Analysis
Structural dynamics(mode shapes) andthe associatedoptical distortionsare displayed asanimations forqualitative analysis
Image (log stretch) Wavefront Error
Deformed FEM
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Reaction Wheels are Dominant Disturbances
Static Imbalance Dynamic Imbalance
ω
F
F
d
r
m
mω
F
r
m
Us = mrF = U sω2
Ud = mrdT = Udω2
YZ
X X
Y
Z
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Wheel Disturbances - Discrete Speed vs Swept Speed
0 1 2 3 4 5 6 7 8 9 10-1
-0.5
0
0.5
1
sec
Forc
e, N
0 50 100 150 200 2500
0.01
0.02
0.03
Freq, Hz
For
ce P
SD
, N2 /
Hz
0 500 1000 1500 2000 2500 3000 3500 4000 4500 50000
2000
4000
6000
Time, sec
Spe
ed, R
PM
0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000-10
0
10
20
Time, sec
Forc
e, N
0 100 200 300 400 500 600 700 800 900 10000
2
4x 10
-3
Freq, Hz
For
ce P
SD
, N2 /
Hz
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Reaction Wheel Isolation
1 0-2
1 0-1
100
101
1 02
-200
-150
-100
-50
0
5 0
d B
H z
Magn i tude Response
1 Hz Hybr id Dev ice
10 Hz Pass ive Device
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FSM Response Functions
10-4
10-2
100
102
104
-60
-50
-40
-30
-20
-10
0
10
Hz
dB
Acts as a high-passfilter to base-motion
Acts as a low-passfilter to guide star noise
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Linear Analysis - Nominal Response, Effect of Isolation, Effect of Wheel Imbalance Amplitude
10-1
100
101
102
10-6
10-4
10-2
100
102
104
Wheel Speed (Hz)
Poi
ntin
g E
rror
(mas
)
LOS Pointing Error vs. Wheel Speed
Nominal1/10th scale wheels1 Hz isolation3s requirement3s GS noise floor
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How Much Isolation Is Required?
10-2
10-1
100
101
102
10-4
10-3
10-2
10-1
100
101
102
103
Isolation Corner Frequency (Hz)
RM
S P
oint
ing
Err
or (m
as)
LOS Pointing Error vs. Isolation Corner Frequency
O - linear analysis
3-σ requirement
X - simulation
GS noise floor
nominal FEM, 0.001 damping,nominal wheel disturbances
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Conclusions
• Development of end-to-end models using the IMOS environment was relatively painless, owing to the following factors:
• translation from NASTRAN and SINDA was possible for FEM and TMM, as was output to FEMAP neutral format
• geometric and material properties were easily parameterized, as were all other significant entities in the models
• ray-trace code (MACOS) was open-source, so it could be integrated via Mex-function API
• Matlab™ is a matrix-oriented language/tool, with integrated graphics and visualization
• Questions remain about the ability to handle realistically-sized models within Matlab™ (eigenvalues, matrix inversion)
• None of these models have been validated, of course…