solar orbiter – eus instrument mechanical design
DESCRIPTION
Solar orbiter – EUS instrument mechanical design. Tim Froud and Doug Griffin. Talk outline. Mechanical-thermal-optical considerations for the Primary Mirror Silicon Carbide Testbed Study Structural layout. Primary mirror WFE under Solar IR Loads. - PowerPoint PPT PresentationTRANSCRIPT
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Solar orbiter – EUS instrument mechanical design
Tim Froud and Doug Griffin
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Talk outline
• Mechanical-thermal-optical considerations for the Primary Mirror• Silicon Carbide Testbed Study• Structural layout
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Primary mirror WFE under Solar IR Loads
• The Solar radiation load will introduce thermal gradients in the Primary Mirror
– Thermal stresses
• Internal mirror temperature gradients
• Possibly also from CTE mismatches
• The thermal load will vary by roughly an order of magnitude during each orbit
• Goal is to meet the optical performance during the encounter and during down link phases of the orbit
• Mirror distortions will introduce distortions in the surface of the mirror which will reduce the spectral and spatial resolution of the instrument
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Primary Mirror WFE Tolerance Estimates
RMS Irregularity l/X @ 633nmRMS
IrregularityApprox PTV
IrregChange in RMS
Spot SizeTotal spot
size(in waves at test
wavelength)(in nm)
(with mirror irregularity)
0.5 X = 2 317 nm 448 nm 67.0 um 74.6 um0.2 X = 5 127 nm 179 nm 23.0 um 30.6 um0.1 X = 10 63 nm 90 nm 8.9 um 16.5 um0.05 X = 20 32 nm 45 nm 3.2 um 10.8 um
0.0333 X = 30 21 nm 30 nm 1.7 um 9.3 um0.025 X = 40 16 nm 22 nm 1.1 um 8.7 um
• Calculation based on encircled energy and are to be considered provisional • Given the Spectral and Spatial resolution requirements:
– Derived requirement on PSF ~ 10um:• Mirror rms WFE: ~l/30 i.e. 21nm rms
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NI Primary Mirror Distortion EstimatesModel Geometry
Uniform heat load B/C35kW/m2
Axis of symmetry
5mm
10
mm
5m
m5
mm
25
mm
40
mm
Fixed Temperature
B/C
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NI Primary Mirror Distortion EstimatesMaterial Assumptions
• Assume that the mirror is made from homogeneous Silicon Carbide– E=249GPa– Poission ratio: 0.16– CTE: 2.7x10-6 m/m– Thermal conductivity: 127 W/m/K– Mirror is absorbing in the IR
• Thermal interfaces have identical mechanical properties as Mirror– No interface stresses
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NI Primary Mirror Distortion EstimatesTemperature Distribution
TemperatureT (K)
5.280
4.752
4.224
3.696
3.168
2.640
2.112
1.584
1.056
0.528
-0.000
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NI Primary Mirror Distortion EstimatesThermal distortions
Axial displacement
-800
-700
-600
-500
-400
-300
-200
-100
0
0 5 10 15 20 25 30 35 40 45
Distance from C/L (mm)
Dis
pla
cem
ent
(nm
)
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NI Primary Mirror Distortion EstimatesConclusions
• The analysis has to be considered as a preliminary estimate
– Optical
– Thermal
– Mechanical
– Layout
• Nonetheless: The conclusion is that the thermal control of the Primary Mirror will have to be considered in tandem with the overall instrument optical performance
– It could be one of the largest challenges for the instrument design
– Rastering of the instrument via the Primary mirror could be very difficult with the complexity of the thermal control
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Primary Structure Material SelectionTest Bed Study
• A study was carried out on a SiC based Optical Bench
– Looked at the practical details of designing structural components in SiC
– Very useful in terms of understanding:• Detailed manufacturing processes • Achievable tolerances• Mounting and interface designs• Lightweighting• Non-destructive Testing
– Procurement of test-bed did not proceed due to cost
– Promising outcome for Flight-build
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Primary Structure Material SelectionTest Bed Study
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Components of system
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Components of system
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Optical bench
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Primary mirror
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Slit mechanism
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Grating
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Detectors and electronics
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Enclosure and baffling