lisa 19-dof drs modelcgwp.gravity.psu.edu/lisa/presentations/maghami.pdf · 2007-11-14 ·...
TRANSCRIPT
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LISA
LISA 19-DOF DRS Model
Peiman Maghami and Tupper Hyde
NASA GSFC
Greenbelt, MD 20771
Fourth International LISA Symposium
July 23, 2002
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LISA
Overview
• LISA dynamics and controls models aredeveloped to:� Evaluate LISA requirements and verify that they can
be met
� Evaluate DRS control architectures and strategies
� Perform trade studies
� Support the integrated modeling effort
• A 19 degrees of freedom model of a LISAspacecraft has been developed
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LISA
LISA 19-DOF Model
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LISA
Model Overview
• Full LISA S/C model: S/C (6 DOF), two ProofMasses (6 DOF each), and telescope articulation
• Nonlinear translational and rotational kinematicsand dynamics
• Preliminary designs for the four main controlsystems: Drag-Free control, Attitude control,Proof Mass suspension control, and telescopearticulation control
• A decentralized approach to control is followed
• Realistic LISA orbits are brought in via ephemerisfile: obtained from orbit design and optimization
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LISA
Model Overview (Cont’d)
• Orbital ephemeris are also used to simulate incoming laserbeam directions for S/C attitude control and telescopearticulation control
• Point-ahead angle dynamics and its compensation are notconsidered
• Measurement and actuation noise models are included
• Approximations to nonlinear electrostatic forces andtorques, as well as, those from self-gravity, are included
• Realistic gravity gradient forces (due to the Sun) and Solarradiation pressure forces/torques (bias and variations) areincluded
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LISA
Coordinate Systems
x
o 1
2
3
OLI frame
1
2
3
SBFframe
1
2
3
TL1 frame
1
2
3
Tl2 frame
1
2
3
1
2
3
PB1 frame
PB2 frame
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LISA
Measurement and Actuation Models
• Model assumes that laser detector measurements provideunit vectors along the paths of the incoming laser beams.
• Detector noise model is included for S/C attitude controland telescope articulation control.
• Relative PM-S/C attitude and translation (GRS):• Noise models for sensing and actuation included.
• Actuation forces and torques are applied in the proof mass housingframe.
• Nonlinear electrostatic forces and torques, as well as, those fromself-gravity, are modeled via a linear time-invariant system.
• Actuation and sensing cross-talk is included.
• µN-thruster noise model is included.
• Actuator quantization for telescope articulation is included
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LISA
Disturbance Reduction System Control
• DRS control comprises five control systems• S/C attitude control system (ACS): to orient the S/C to align the
telescopes with incoming laser beams
• Drag free control system (DFC): to maintain drag free motion ofthe proof masses in LISA measurement directions
• Proof mass (PM) suspension control: to maintain relative attitudeof the proof mass with respect to its housing an to maintain relativeposition of the proof mass with respect to its housing in thetransverse directions
• Telescope articulation (TA) control: to maintain the angle betweenthe telescopes
• Point ahead (PA) and acquisition control: to point the outgoingbeam while sensing the incoming beam using communication fromthe other spacecraft
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LISA
S/C Attitude Control System
• Detectors provide unit vector measurements correspondingto the incoming laser beams: based on instantaneousinertial positions of the telescopes and the other spacecraft
• S/C attitude control must be done in concert with telescopearticulation
• Error distribution logic determines the spacecraft attitudeerror as well as telescope articulation angle error thataligns the telescope axes with the measured unit vectors.
• S/C attitude error is sent to the ACS for attitudeadjustments
• ACS is a digital controller and designed using classicalsingle loop approach
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LISA
Telescope Articulation Control
• Telescope articulation device is assumed to be a torquedevice at the CM of the telescope, i.e., no reactive forcesduring articulations.
• Static or dynamic imbalances are not modeled for thetelescope articulation.
• Model assumes that the articulation axis and the S/C z-axis are parallel
• Error distribution logic determines the telescopearticulation angle error
• This error is sent to the articulation control for angleadjustments
• Articulation control is a SISO digital controller
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LISA
LISA Attitude Control Concept
x
Incoming beam
from S/C 3
Incoming beam
from S/C 2
Observationunit vector
Observation
unit vector
x
Rap1
Rcr1
Center ofArticulation
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LISA
Attitude and Articulation Errors
• Observed unit vectors to the other spacecraft
• The desired direction, in the respective telescope frame, isgiven by
• The telescope articulation angle error is taken as
• The spacecraft attitude error computed from the requiredcoordinate transformation that would align the measuredunit vectors with the desired direction vector.
1 2
2 2 2 21 1 2 2
1 2
1 2
1 1
;m mo o
α β α βα αβ β
− − − − = =
� �
1
0
0do
=
�
1 2α α−
1 1 1 1
2
1 1
2 2
T T T Te m d
T Te m d
A A A A o A A o
A A o A o
α α α=
=
� �
� �
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LISA
Proof Mass Attitude Control
• Uses relative attitude of the proof mass with respect to itshousing from capacitive sensing
• Suspension torques are applied at the housing frame
• The relative attitude error is sent to the suspension controlfor proof mass attitude adjustments
• The attitude suspension controller is a digital controllerdesigned using classical single loop approach
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LISA
Drag Free Control
• The relative position of the center of mass of the proofmass from its housing is measured by capacitive sensing.
• Two strategies are considered for drag free control:
� Both strategies do not allow proof mass translationcontrol in the sensitive (measurement) axes (FTRStrategy 4): S/C translation will have to center the proofmasses in these directions
� First strategy permits commanding of the gravitationalsensors (in the transverse directions) in a centralizedmanner: cross coupling between sensors
� Second strategy does not allow for centralizedcommanding of the gravitational sensors : proof masssimply follows the housing (no coupling)
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LISA
Drag Free Control (cont’d)
• The out-of-plane DOF of the 2nd proof mass is notsuspended in both strategies: S/C translation will take careof it
• Error distribution matrix computes position errors for theS/C and the proof masses (in the transverse direction) toachieve drag-free motion in the measurement axes as wellas to center the proof masses in the transverse directions
• S/C position error is sent to the Drag-free control for S/Ctranslational adjustments
• Proof mass position error is sent to the translationalsuspension control for position adjustments
• Both DFC and suspension controllers are designed basedon digital classical single loop designs.
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LISA
First Drag Free Strategy
• The required S/C and PM translations
• Solution:
• Note: the z component (out-of-plane) of 2nd proof mass isnot suspended.
1 1
2 2
1
2
( ) ( ) ( ) ( ) 0
( ) ( ) 0
s p m
s p m
A t t t e t
A t t e
δ δ
δ δ
− + =
− + =
� �
�
� �
�
2 2
2 1 2 1
2 2
1 2 1 2
( ) ( )T Ts p m
T Tp p m m
t A t A e
A A A A e e
δ δ
δ δ
= −
− = −
� �
�
� �
� �
1
1 2 1
2
(2)0 0 (1,2)
1 0 (2,2) (3)
0 1 (3,2) (2)
p
p m m
p
A
A Ae e
A
δ
δ
δ
− = − −
�
�
� �
�
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LISA
Second Drag Free Strategy
• The required S/C translations are computed to provide drag-free motion in the sensitive axis and one transverse axis
• The proof mass position errors in the transverse direction arecomputed as
1
2
2
1 1
2 2
(1,1) (1) (1, 2) (2) (1) 0
(1,1) (1) (1, 2) (2) (1) 0
(3) (3) 0
s s m
s s m
s m
A A e
A A e
e
δ δ
δ δ
δ
+ + =
+ + =
+ =
� �
�
� �
�
�
�
1 1
1 1
2 2
p m
p m
p m
(2)=e (2)
(3)=e (3)
(2)=e (2)
δ
δ
δ
�
�
�
�
�
�
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LISA
LISA Simulation Model
• Model is developed in SIMULINK environmentwith MATLAB script file driver• Different stiff and non-stiff solvers are available for integration
• Hybrid systems and nonlinearities are fully treated
• Orbital ephemeris (obtained from optimization) areimported
• Realistic initial attitudes and rates (S/C & PMs) obtainedfrom ephemeris data
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LISA
SIMULINK Model
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LISA
DRS Controller
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LISA
Pointing Error: Telescope 1
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LISA
Pointing Error: Telescope 2
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LISA
Rel. Attitude PM1 to Housing
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LISA
Rel. Attitude PM2 to Housing
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LISA
Rel. Position PM1 to Housing
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LISA
Rel. Position PM2 to Housing
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LISA
ASD of PM position in measurement direction
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LISA
ASD of Telescope no. 1 Attitude
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LISA
ASD of Telescope no. 2 Attitude
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LISA
Future Work
• Obtain a linear 19-DOF model• Frequency-domain analysis
• Robustness and stability analysis
• Perform trade studies on DRS control• Control strategies and architecture
• MIMO and robust control designs
• Integrated modeling and analysis• Couple DRS simulation with optics
• Investigate point-ahead and acquisition controls
• Improve model fidelity
• Develop a full 57 DOF LISA formation model
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LISA
Point Ahead Angle
• So far, the 19 DOF model or control does not address pointahead or acquisition.
• Point ahead angle is the difference between outgoing andincoming beams due to speed of light
• From FTR Section 3-3, the PAA (in object space) are…
85 nrad +- 5.75 µradOut of plane
3.3 µrad +- 55 nradIn plane
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LISA
Component Angles
• Object space (30 cm beam)• Compressed space (0.5 cm beam)
• Mtl=60
• Detector space (0.5 mm beam)• Mbc1=10
• PAA= ~6x10-6 rad max (object)• Θtl = telescope rel bench (object)• Θout = outgoing (object)• Θin = Θout - PAA (object)• Θps1 = beamsplitter (comp)• Θpm = proof mass (comp)• Θfa = fiber aligner (comp)
• Includes fiber aligner and collimator
• Θerr= diff WF tilt (detector)
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LISA
Point Ahead Equations
• Output Beam Angle• Θout = (1/Mtl)(Θfa +2Θps1 ) + Θtl
• Wavefront tilt difference on detector• Θerr = Mbc1 { Mtl (Θin + Θtl ) +2Θpm +2Θps1 - Θfa }
• Conditions for lock…Telescope boresights outgoutingbeam
• Θout = 0, Θtl = 0, Θin = -PAA• Θfa = - 2Θps1
• Results in the following condition• Θerr = Mbc1 { Mtl (-PAA) +2Θpm +4Θps1}• Θerr = -600 PAA +20 Θpm +40 Θps1
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LISA
Options for Point Ahead Control
• Use PM (FTR baseline)• Θerr = -600 PAA +20 Θpm +40 Θps1 = 0• When Θpm = 30 PAA =~ 180 µrad max• and Θps1=0
• Use beamsplitter and fiber aligner• Θerr = -600 PAA +20 Θpm +40 Θps1 = 0• When Θps1 = 15 PAA =~ 90 µrad max and• Θfa = - 2Θps1 = -30 PAA = ~ -180 µrad max
• Live with error in tilt• Θerr = -600 PAA +20 Θpm +40 Θps1 = -600 PAA = ~1.8x10-3 rad
• Problem: Loss of fringe visibility at qp1. At beam edge: 1.8x10-3 rad *0.25x10-3 m= 0.45x10-6 m = 0.45 wave > lamda/20
• When Θpm = 0• and Θps1=0
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LISA
Summary
• Conclusion:• Steering proof mass remains baseline for now
• requires ~ 180 microradians max, what are implications forcalibrations at other than “zero”
• To do:• Use real optics math
• Include other downstream optics (cavity, backside, etc.) andbeam walk.
• Look at acquisition and calibration
• Look at mechanisms for beamsplitter and fiber aligner