themis instrument thermal peer review 1 ucb, february 26, 2004 themis t ime h istory of e vents and...

THEMIS Instrument Thermal Peer Review 1 UCB, February 26, 2004

THEMISTIME HISTORY OF EVENTS AND MACROSCALE INTERACTIONS DURING SUBSTORMS

RESOLVING THE MYSTERY OF WHERE, WHEN AND HOW AURORAL ERUPTIONS START

THEMIS Instrument CDR Peer Review – Thermal MaterialTHEMIS Instrument CDR Peer Review – Thermal MaterialApril 19 - 20, 2004April 19 - 20, 2004University of California, BerkeleyUniversity of California, Berkeley


UCB Thermal Peer Review

THEMIS Instrument CDR - Thermal

Christopher Smith

Thermal Engineer

[email protected]

510-642-2461


Launch

Probe Carrier Assembly (PCA) on Delta 3rd StageProbe Carrier Assembly (PCA) on Delta 3rd Stage

• Five Identical probes launched on a Delta II

• Coordinated but independent probe release

ADAMS Dispense Model Dynamic Simulation Image

ADAMS Dispense Model Dynamic Simulation Image

• Must design for any launch date

• Must design for all solar aspect angles


Probe Design

• Simple Single string design

• Power positive most attitudes with instruments off (launch, safe hold modes)

• Top to sun is slightly power negative

• Passive thermal design tolerant of longest shadows (3 hours)

• Passive spin stability achieved in all nominal and off-nominal conditions

• Monoprop blow down RCS (propulsion) system is self balancing on orbit


THEMIS Instruments

Eight Deployed Instruments

• Two 5m spin axis booms (AXB)

• Four 20m spin plane wire booms (SPB)

• One 1m spin plane boom (SCM)

• One 2m spin plane boom (FGM)

Two Fixed Instruments

• Corner panel mounted SST

• ESA mounted to the IDPU which mounts to bottom deck


Mission Orbits

Probe Orbital Period Orbit Geometry Prior to First Year Tail Season

1 4 d 1.500 x 31.645 Re at 7.0°

2 2 d 1.168 x 19.770 Re at 7.0°

3 1 d 1.200 x 12.019 Re at 9.0°

4 1 d 1.200 x 12.019 Re at 9.0°

5 4 / 5 d 1.350 x 10.042 Re at 9.0°

• Synchronized orbits align in the geotail over North America in winter

• Phase into a long eclipse season approximately 30 days long

• Maximum eclipse < 180 min


Thermal Responsibilities

•Probe Bus and Probe Carrier Assembly thermal design / analysis

- Swales Aerospace

•Instrument thermal design / analysis

- UC Berkeley

•RCS thermal design / analysis

- RCS Contractor

•Integrated Probe Bus and Instrument thermal analysis

- Swales Aerospace

•Integrated Probe Carrier Assembly thermal analysis

- Swales Aerospace

•Instrument and Instrument Suite level thermal testing

- UC Berkeley

•Probe level thermal testing

- Swales Aerospace


Instrument Introduction

• Radial EFI (Electric Field Instrument) or SPB (Spin Plane Boom) deploys EFI sensor and preamp on a wire

• Axial EFI or AXB (AXial Boom) deploys an EFI sensor and preamp on a coiled rigid stacer

• SST - Ion and electron Solid State Telescope

• ESA - ion and electron ElectroStatic Analyzer

• IDPU - Instrument Data Processing Unit

• FGM - FluxGate Magnetometer

• SCM - Search Coil Magnetometer


Design Approach

• THEMIS will use passive thermal control techniques

• Heat dissipating boxes are coupled radiatively and/or conductively to the spacecraft

• Components mounted on the exterior of the spacecraft are isolated and/or use low e finishes or blankets to minimize bus heat loss

– SST emittance tailored to meet ideal science requirements

• Internal box finishes chosen to assist heat transfer between probe top and bottom deck for top deck to sun case

• Heaters designed for 50% or below duty cycle in coldest case


Interfaces

Interface Material

SST to Probe ULTEM Isolators

SPB to Probe ULTEM Isolators

IDPU to Probe ULTEM Isolators

ESA to IDPU Bare Bolted

FGM to boom G10 Isolators

SCM to boom PEEK structure

AXB Tube to top deck ULTEM Isolators

AXB Tube to bottom deck Bare bolted

AXB to AXB Tube Bare bolted

Boom to Probe ULTEM isolators

Boom Release Towers to Probe

ULTEM isolators


Design Margins

•Thermal Analysis results must be 5 degrees inside limits

•Acceptance tests will be 10 degrees outside of predictions

•Qualification tests will be 10 degrees outside of limits

•Heater duty cycle will be 50% or less in coldest case

Max Predict

Op

Lim

it s

Min Predict

>5°C

>5°C

10°C

10°C

10°C

10°C

Qu

alif

ica

ti on

Ac c

ep

t an

c e


MRD REQUIREMENT THERMAL DESIGN

M-26. THEMIS shall survive and performed as designed under worst-case thermal conditions

Compliance. Worst-case hot and cold conditions used in thermal analysis and design.

IN-1. The Instrument Payload shall be designed for at least a two-year lifetime

Compliance. 2-year EOL numbers used in thermal analysis and design.

IN-2. The Instrument Payload shall be designed for a total dose environment of 33 krad/year

Compliance. Radiation environment considered in thermal design.

IN-20, -21, -22. The Instrument Payload shall be compatible per (all) ICDs

Compliance. Thermal limits and interface requirements documented in ICDs…

IN-16 The Instrument Payload shall comply with the Magnetics Cleanliness standard described in the THEMIS Magnetics Cleanliness Plan

Compliance. THM-SYS-002 Magnetics Contamination Control Plan. Heaters will be magnetically clean, power/return wires will be twisted.

IN-17 The Instrument Payload shall comply with the THEMIS Electrostatic Cleanliness Plan

Compliance. THM-SYS-003 Electrostatic Cleanliness Plan signed off. Thermal blankets and all other exposed surfaces will be sufficiently conductive and have sufficiently dense grounding networks.

IN-18 The Instrument Payload shall comply with the THEMIS Contamination Control Plan

Compliance. THM-SYS-004 Contamination Control Plan signed off. Thermal blankets will be baked out.

Thermal Requirements


Analysis Tools

Geometry Model • Thermal Desktop

4.5 / AutoCAD 2000– Same version as

Swales counterpart

Equation Solver • SINDA/FLUINT 4.5

– Same version as Swales counterpart

Simplified Node Analysis• Excel Spreadsheet


Thermal Desktop Models

• UCB node, variable, Thermophysical and optical properties all uniquely named to prevent collisions

• Model definition files transferred to Swales for integration into probe model


Spacecraft Environment

•Solar Flux varies from a high of 1425 W/m2 to a low of 1287 W/m2

•Earth IR varies from a high of 261 W/m2 to a low of 209 W/m2

•Earth Albedo varies from a high of 0.35 to a low of 0.16


Conductors

• A single conductance value or a conductance range is determined through analysis.

• If a range is determined, (mostly for contact cases) this is used for hot and cold cases

• If a single conductance value was determined than it is multiplied by 1.5 and 0.5 to determine the high and low values to use

• Whether to use the high or low conductance is determined by the model and the case, though it is usually the max estimate


Example Conductors


Isolated Joint Conductance


EOL and BOL Values


AO Effects

• Minimum height at perigee = 1.108 Re = 700 km altitude, AO evaluation continuing but expected to be small for ITO-FEP-Ag

• All final material properties will be submitted to GSFC thermal coatings group for approval


• Nodal capacitance is adjusted to match current best estimate of mass

• Blanket effective emittance• SPB Cold case uses 0.05, Hot case uses 0.01

• SCM and FGM, Cold case uses 0.1, Hot case uses 0.03

Thermophysical Properties


Limit Categories

• Science Operation Limit– Limits placed on an operating instrument– Specifies the range of temperatures the instrument will be calibrated to

• Eclipse Operation Limit– Limits placed on an operating instrument– May represent a wider (cooler) range that is acceptable to components– Temperatures beyond Science Op Limit need not be calibrated to

• Survival Limit– Limits placed on a non operating instrument

• Pre-Deployment Limit– Limits placed on a mechanical system before it is actuated

• Deployment Limit– Limits placed on a mechanical system at the time of actuation

• Post-Deployment Limit– Limits placed on a mechanical system after it has executed its one-time

deployment


Science vs. Eclipse Limits

• Science will not be collected during the deepest eclipses

• Science cases currently cut off at 100 min eclipse


Limits


Boundary Condition Case Sets

• Instrument thermal models coupled to the deck temperature boundary conditions provided by Swales


Swales P1 Orbit Cold Case

Longest eclipse occurs in P1 orbit

Top tilted toward the sun 13 Degrees

BOL Optical Properties

Solar Flux = 1287 W/m2

Earth IR = 209 W/m2

Blanket e* = .05

Dissipation 24 W


Swales P4 Orbit Hot Case

No eclipse in the P4 orbit

Top tilted away from the sun 13 Degrees

EOL Optical Properties

Solar Flux = 1425 W/m2

Earth IR = 265 W/m2

Earth Albedo = 0.35

Blanket e* = .01

Dissipation 27.4 W

Transmitter on for 30 min at perigee


Summary of Swales Case Sets


Boundary Temperature Inputs


General UCB Case Sets

• “CBE” is current best estimate

• Actual Case sets differ by instrument any modifications and additional case sets will be discussed in the instrument section


EFI Axial Booms

Thermal

Christopher Smith

Thermal Engineer

[email protected]

510-642-2461


Axial Boom Stowed

Axial Boom (AXB)

• Two units mount inside a carbon fiber tube centrally mounted on the probe

• Tube attached to the top deck through an aluminum flange that is bare bolted

• Bare bolted to lower deck

• Two stacers, one from each unit, deploy out the tube ends

AXB Mounting

Tube

Single AXB unit


AXB / Map

80% Alum Foil Tape

20% Bare Carbon Fiber

Bare Carbon Fiber

Alodined Aluminum

VDA Tape


AXB Model Inputs

• Optical materials– Aluminum Foil Tape– Bare Carbon Fiber– Alodined Aluminum

• Thermophysical materials– Aluminum, 6061– K13D2U Carbon Fiber– T300 Carbon Fiber

• Heaters– None used at this time, though we are prepared to supply deployment heaters

if needed

• Conductors– Bare bolted top flange to deck: 0.612 W/C inc. bolts, flange, and adhesive– Bare bolted bottom flange to deck: 3.3 W/C each, 20 W/C total– Bare bolted AXB to Tube mount: 0.79 W/C each, 0.476 total

• Power Dissipation– 0 Watts

AXB Mounting Tab


AXB Case sets

• Bottom to sun a cold case boundary condition has no eclipse

• All above cases run separately with stowed boom and deployed boom


AXB Mechanical Unit Standard Plots - Deployed

-60

-40

-20

0

20

40

60

50K 100K 150K 200K 250K 300K

AXB Mechanical Unit, Deployed, Standard Case Set - Foil and Bare Carbon Fiber Mix (04/10/04)SAA 103 Hot - SAA 90 Cold - SAA 77 Cold - SAA 77 Cold Low Power

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BOT DECK TOP DECK TUBE TOP TUBE MIDDLE TUBE BOTTOM TOP AXB BOTTOM AXB BOT DECK TOP DECK TUBE TOP

TUBE MIDDLE TUBE BOTTOM TOP AXB BOTTOM AXB BOT DECK TOP DECK TUBE TOP TUBE MIDDLE TUBE BOTTOM TOP AXB

BOTTOM AXB BOT DECK TOP DECK TUBE TOP TUBE MIDDLE TUBE BOTTOM TOP AXB BOTTOM AXB


AXB Mechanical Unit Sunline Plots - Deployed

-60

-40

-20

0

20

40

60

80

100

40K 50K 60K 70K 80K 90K 100K 110K

AXB Mechanical Unit, Deployed, TBSun Case Set - Foil and Bare Carbon Fiber (04/10/04)SAA 0 Hot - SAA 180 Cold

Tem

pera

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Time

BOT DECK TOP DECK TUBE TOP TUBE MIDDLE TUBE BOTTOM TOP AXB BOTTOM AXB



AXB Mechanical Unit Standard Plots - Stowed

-60

-40

-20

0

20

40

60

80

50K 100K 150K 200K 250K 300K

AXB Mechanical Unit, Stowed, Standard Case Set - Foil and Bare Carbon Fiber Mix (04/10/04)SAA 103 Hot - SAA 90 Cold - SAA 77 Cold - SAA 77 Cold Low Power

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BOT DECK TOP DECK TUBE TOP TUBE MIDDLE TUBE BOTTOM TOP AXB BOTTOM AXB BOT DECK TOP DECK TUBE TOP

TUBE MIDDLE TUBE BOTTOM TOP AXB BOTTOM AXB BOT DECK TOP DECK TUBE TOP TUBE MIDDLE TUBE BOTTOM TOP AXB

BOTTOM AXB BOT DECK TOP DECK TUBE TOP TUBE MIDDLE TUBE BOTTOM TOP AXB BOTTOM AXB


AXB Mechanical Unit Sunline Plots - Stowed

-60

-40

-20

0

20

40

60

80

100

40K 50K 60K 70K 80K 90K 100K 110K

AXB Mechanical Unit, Stowed, TBSun Case Set - Foil and Bare Carbon Fiber (04/10/04)SAA 0 Hot - SAA 180 Cold

Tem

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Time




AXB Results Table


AXB Mounting Tube Modifications

• Spacecraft was consuming too much power in the coldest, but nominal, science case ~2.2 W

• To help mitigate this issue two modifications are being considered for the AXB Mounting tube

• Tube construction switched from all T300 ( 5 W/mK) fiber to 4 plys K13D2U (500 W/mK) + 2 plys T300

• Tube exterior changed from blanket to a mix of Foil tape and bare carbon

• Current results show the AXB unit getting too hot and we are currently exploring options to cool it down

• Increase isolation between AXBs and tube

• Isolate tube flange from top deck

• At worst, cool the tube down by reducing the percentage of foil tape

• When the design is complete it will be within limits though new temperatures may require the thermal vac hot deploy test be repeated at a new higher temperature


AXB Temp Map for Hottest Case


AXB Temp Map for Coldest Case


Axial Boom Deployed

AXB “can”

AXB PreAmp

Exposed Bit After Deploy


AXB Geometry Model

Deployed Stacer Model


AXB Deployed Elements / Map

DAG 154Alodined AluminumDAG 213

Bronze


AXB Model Inputs

• Optical materials– Acheson Coloids DAG 213 (2 part)– Acheson Coloids DAG 154– Alodined Aluminum– Bronze

• Thermophysical materials– Aluminum, 6061– Bronze– Elgiloy– PEEK

• Heaters– None

• Conductors– Main Stacer to Tip Piece, 1 rivet and circumferential contact, .3 < G <.9 W/C– Tip Piece To Bronze DDAD Lock, Large threaded interface, 10 W/C– DDAD Lock to PreAmp, large threaded bolt 3.57 W/C– PreAmp to Mini Stacer, 1 rivet and circumferential contact .3< G <.8 W/C– Mini Stacer to Can, 1 rivet, 0.3 W/C

• Power Dissipation– 0.07 Watts Nominal at Preamp

AXB Preamp


AXB Deployed Elements Case Sets

• Top and Bottom to sun cases after deployment are limited to no less than 11 degrees off the sun line

• The Model for the Top and Bottom to Sun cases goes through a 180 min eclipse. A 100 min eclipse is the actual limit and is shown in plots


AXB Boom Elements Standard Plots - Deployed

-150

-100

-50

0

50

50K 100K 150K 200K 250K 300K

AXB Boom Elements, Deployed, Standard Case Set (04/10/04)SAA 103 Hot - SAA 90 Cold - SAA 77 Cold - SAA 77 Cold Low Power

Tem

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Time

AXBROD.T14 AXBCAN.T6 AXBDDAD.T6 AXBPAMP.T10 AXBSTACR.T28 AXBTIP.T7 AXBROD.T14 AXBCAN.T6 AXBDDAD.T6

AXBPAMP.T10 AXBSTACR.T28 AXBTIP.T7 AXBPAMP.Q10 AXBROD.T14 AXBCAN.T6 AXBDDAD.T6 AXBPAMP.T10 AXBSTACR.T28

AXBTIP.T7 AXBROD.T14 AXBCAN.T6 AXBDDAD.T6 AXBPAMP.T10 AXBSTACR.T28 AXBTIP.T7


AXB Boom Elements Sunline Plots - Deployed

-180

-160

-140

-120

-100

-80

-60

-40

-20

20K 30K 40K 50K 60K 70K 80K 90K 100K 110K 120K 130K

AXB Boom Elements, Deployed, TBSun Case Set (04/10/04)SAA 11 Cold - SAA 169 Cold

Tem

pera

ture

Time

AXBROD.T14 AXBCAN.T6 AXBDDAD.T6 AXBPAMP.T10 AXBSTACR.T28 AXBTIP.T7

AXBROD.T14 AXBCAN.T6 AXBDDAD.T6 AXBPAMP.T10 AXBSTACR.T28 AXBTIP.T7


AXB Preamp Results Table

• Science operation limited to a 36 min eclipse

• Current predicts show Preamp falling below the limit on the TO99 can.


AXB Preamp Qualification

• AXB Preamp model is currently a simple lump with the proper radiative surfaces

• Thermal isolation of the TO-99 from the outer shell is complicated and difficult to reliably model

• Thermal Vacuum test planned determine the thermal isolation of the TO-99 from the preamp outer surface (April 12th – April 23rd)

• This thermal isolation determined by test will be input into the thermal model to determine a reliable qualification temperature, still likely to be under the current qualified temp of –65


AXB Preamp Models


EFI Spin Plane Booms

Thermal

Christopher Smith

Thermal Engineer

[email protected]

510-642-2461


SPB

• 4 separate units mounted to the bottom deck

• Snout pokes out the solar panel

• Sphere and Preamp deploy out the snout on a wire (Half Sphere shown in picture)

• Sphere and preamp separate as rotation unwinds a thin wire from a spring loaded wheel


SPB / Map

AZ 2000 IECW Inorganic White Paint

MLI

Alodined Aluminum


SPB Model Inputs

• Optical materials– Germanium Black Kapton (Sheldahl 275XC Black Kapton)– Alodined Aluminum– AZ 2000 IECW Inorganic White Paint– Blanket: .01 < < .05

• Thermophysical materials– Aluminum, 6061– ULTEM

• Heaters– None used at this time, though we are prepared to supply deployment heaters

if needed

• Conductors– 1/8” Ultem isolators for top deck: 0.01 W/C each, 0.04 W/C total

• Power Dissipation– 0 Watts


SPB Case Sets


SPB Mechanical Unit Standard Plots

-40

-30

-20

-10

0

10

20

30

40

50K 100K 150K 200K 250K 300K

SPB - Alodine w/ AZ 2000 IECW (04/12/04)SAA 103 Hot - SAA 90 Cold - SAA 77 Cold - SAA 77 Cold Low Power

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TOP HAT TOP HAT TOP REAR PANEL BOTTOM REAR PANEL BOTDECK





SPB Mechanical Unit Sunline Plots

15

20

25

30

35

40

45

20000 25000 30000 35000 40000 45000 50000 55000 60000 65000

SPB - Alodine w/ AZ 2000 IECW (04/12/04)SAA 0 Hot - SAA 180 Hot

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SPB Results Table


SPB Heat Map for Coldest Case


SPB Heat Map for Hottest Case


SPB Deployed Elements

• Preamp and sphere are connected by a thin wire

• Preamp is connected to SPB deployment unit by another wire

• Preamp is nearly identical to Axial version

• Sphere is only a mechanical element

Titanium Nitride

DAG 213


Preamp and Sphere Analysis


SPB Sphere and Preamp Model

• Nodes 3 and 4 are for the sphere hot and cold cases

• Nodes 5 and 6 are for the preamp hot and cold cases

• As with the axial preamp the SPB preamp falls below its limit by a bit. Qualification plan is in the works


SPB Sphere and Preamp Plot


Flux Gate Magnetometer and Boom

Thermal

Christopher Smith

Thermal Engineer

[email protected]

510-642-2461


FGM

• Two carbon fiber tubes joined by an elbow hinge

• Frangibolt release on the base hinge

• Elbow hinge is capture only, no release


FGM Geometry Model

FGM Model

Deployed

Stowed


FGM / Map

MLI30% AZ2000IECW White Paint

70% VDA Tape

= 0.5 to 0.9

AZ2000IECW White Paint

Alodined Aluminum on Undersides


FGM Model Inputs

• Optical materials– MLI– Vapor Deposited Aluminum Tape– AZ 2000 IECW White Paint– Alodined Aluminum

• Thermophysical materials– Aluminum, 6061– M55J– ULTEM– Dexter Hysol 9349

• Heaters– None in current model though provisions have been made for deployment heaters if needed and it

looks like we will need them.

• Conductors– Deck Hinge ULTEM isolators, 0.0078 < G < .0133 W/C each– Conductance through deck hinge, 0< G <.02 W/C– Conductance through adhesive to boom tube, 6.6 W/C– Conductance through adhesive at elbow hinge, 4.9 W/C– Conductance through elbow hinge, 0< G < 0.04 W/C– Conductance through adhesive to Sensor, 3.3 W/C– G10 Isolation mounts at FGM sensor, 0.01 W/C– Elbow Latch Tower ULTEM isolators, 0.0078 < G < .0133 W/C each

• Power Dissipation– 0 Watts Nominal

Elbow Hinge


FGM Case Sets

• Identical case sets to the SCM

* UCB model eclipse time, boundary conditions do not yet include eclipse


FGM Deployed – Nominal Plot

-100

-80

-60

-40

-20

0

20

50K 100K 150K 200K 250K 300K

FGM - 30% AZ 2000 70% VDA (04/14/04)SAA 103 Hot - SAA 90 Cold - SAA 77 Cold - SAA 77 Cold Low Power

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INNER BOOM OUTER BOOM DECK HINGE ELBOW HINGE SENSOR TOPDECK INNER BOOM OUTER BOOM

DECK HINGE ELBOW HINGE SENSOR TOPDECK INNER BOOM OUTER BOOM DECK HINGE ELBOW HINGE

SENSOR TOPDECK INNER BOOM OUTER BOOM DECK HINGE ELBOW HINGE SENSOR TOPDECK


FGM Deployed – Top and Bottom to Sun Plot

-80

-60

-40

-20

0

20

40

60

80

100

40K 50K 60K 70K 80K 90K 100K 110K

FGM - 30% AZ 2000 70% VDA (04/14/04)SAA 0 Hot - SAA 180 Cold

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TOPDECK INNER BOOM OUTER BOOM DECK HINGE ELBOW HINGE SENSOR

TOPDECK INNER BOOM OUTER BOOM DECK HINGE ELBOW HINGE SENSOR


FGM Stowed – Nominal Plots

-100

-80

-60

-40

-20

0

20

40

60

80

100

20K 40K 60K 80K 100K 120K 140K 160K 180K 200K

FGM Stowed - 30% AZ 2000 70% VDA (04/14/04)SAA 103 Hot - SAA 77 Cold - SAA 0 Hot - SAA 180 Cold

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TOPDECK INNER BOOM OUTER BOOM DECK HINGE ELBOW HINGE SENSOR TOPDECK

INNER BOOM OUTER BOOM DECK HINGE ELBOW HINGE SENSOR TOPDECK INNER BOOM

OUTER BOOM DECK HINGE ELBOW HINGE SENSOR TOPDECK INNER BOOM OUTER BOOM

DECK HINGE ELBOW HINGE SENSOR FGM FRANGIBOLT SCM FRANGIBOLT


FGM Results Table


FGM DeployedColdest Heat Map


FGM DeployedHot Temperature Map


FGM StowedColdest Temperature Map


FGM StowedHottest Temperature Map


Search Coil Magnetometer and Boom

Thermal

Christopher Smith

Thermal Engineer

[email protected]

510-642-2461


SCM Model

• Carbon Fiber boom mounted on the top deck

• Frangibolt activated deployment

• Sensor mounted in PEEK structure


SCM Geometry Model

SCM Model

Deployed

Stowed


SCM / Map

MLI

30% AZ2000IECW White Paint

70% VDA Tape

= 0.5 to 0.9

AZ2000IECW White Paint

Alodined Aluminum on Undersides


SCM Model Inputs

• Optical materials– MLI– Vapor Deposited Aluminum Tape– AZ 2000 IECW White Paint– Alodined Aluminum

• Thermophysical materials– Aluminum, 6061– M55J– ULTEM– Dexter Hysol 9349

• Heaters– None in current model though provisions have been made for deployment heaters if needed and

it looks like we will need them.

• Conductors– Deck Hinge ULTEM isolators, 0.0078 < G < .0133 W/C each– Conductance through deck hinge, 0< G <.02 W/C– Conductance through adhesive to boom tube, 6.6 W/C– Conductance through adhesive to Sensor, 3.3 W/C– PEEK isolation of SCM sensor, 0.01 W/C– Release Tower ULTEM isolators, 0.0078 < G < .0133 W/C each

• Power Dissipation– 0 Watts Nominal

Deck Hinge


SCM Case Sets


SCM Deployed – Nominal Plot

Deployed SCM Plot, Nominal Case Sets

-80

-70

-60

-50

-40

-30

-20

-10

0

10

20

30

50K 100K 150K 200K 250K 300K

SCM - 30% AZ 2000 70% VDA (04/14/04)SAA 103 Hot - SAA 90 Cold - SAA 77 Cold - SAA 77 Cold Low Power

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BOOM INNER BOOM OUTER SENSOR DECK HINGE TOPDECK BOOM INNER BOOM OUTER SENSOR DECK HINGE TOPDECK



SCM Deployed – Top and Bottom to Sun Plot

Deployed SCM Plot, Top and Bottom to Sun

-80

-60

-40

-20

0

20

40

60

80

100

40K 50K 60K 70K 80K 90K 100K 110K

SCM - 30% AZ 2000 70% VDA (04/12/04)SAA 0 Hot - SAA 180 Cold

Tem

pera

ture

Time



SCM Stowed – Nominal Plots

-100

-80

-60

-40

-20

0

20

40

60

80

100

20K 40K 60K 80K 100K 120K 140K 160K 180K 200K

SCM Stowed - 30% AZ 2000 70% VDA (04/14/04)SAA 103 Hot - SAA 77 Cold Low Power - SAA 0 Hot - SAA 180 Cold

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BOOM INNER BOOM OUTER SENSOR DECK HINGE TOPDECK BOOM INNER BOOM OUTER SENSOR

DECK HINGE TOPDECK BOOM INNER BOOM OUTER SENSOR DECK HINGE TOPDECK BOOM INNER

BOOM OUTER SENSOR DECK HINGE TOPDECK FGM FRANGIBOLT SCM FRANGIBOLT


SCM PlotCross Tube Temp Differentials

Cross-Tube Temperature Differentials


SCM Plot Axial Temperature Differentials

Axial Temperature Differentials


SCM Results Table


SCM DeployedColdest Heat Map


SCM DeployedHot Temperature Map


SCM StowedColdest Temperature Map


SCM StowedHottest Temperature Map


Solid State Telescope

Thermal

Christopher Smith

Thermal Engineer

[email protected]

510-642-2461


SST

• Mounts directly to the corner panel on three 1/8 inch isolators

• Has four open apertures that are sometimes obscured by attenuators

• Must operate at 10 Deg C or less


SST Geometry Model

Alodined

Aluminum

AZ 2000 IECW

Ebanol

Black Body /

Alodined Aluminum


SST Model Inputs

• Optical materials– Ebanol– AZ 2000 IECW White Paint– Alodined Aluminum


• Heaters– Two 5 watt heaters per sensor head controlled by redundant thermostats– Set points –50 and -42

• Conductors– 3 ULTEM isolators to corner panel, 0.0078 < G < .0133 W/C each

• Power Dissipation– 0.135 W Watts Nominal per Sensor


SST Case Sets


SST – Nominal Plots

-70

-60

-50

-40

-30

-20

-10

0

10

20

30

40

0 50K 100K 150K 200K 250K 300K

SST - Alodine and AZ 2000 IECW White Paint, 10 W Heater (04/12/04)SAA 103 Hot Aperture Closed - SAA 103 Hot - SAA 90 Cold - SAA 77 Cold - SAA 77 Cold Low Power

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SST1 TOP SST1 COLLIMATOR SST 1 INTERNAL CORNER PANEL SST2 INTERNAL SST1 HEATER SST2 HEATER SST1 TOP

SST1 COLLIMATOR SST1 INTERNAL CORNER PANEL SST2 INTERNAL SST1 HEATER SST2 HEATER SST1 TOP SST1 COLLIMATOR

SST1 INTERNAL CORNER PANEL SST2 INTERNAL SST1 TOP SST1 COLLIMATOR SST1 INTERNAL CORNER PANEL SST2 INTERNAL

SST1 TOP SST1 COLLIMATOR SST1 INTERNAL CORNER PANEL SST2 INTERNAL


SST – Top and Bottom to Sun Plots

-80

-70

-60

-50

-40

-30

-20

-10

0

10

20K 30K 40K 50K 60K 70K 80K 90K 100K 110K 120K 130K

SST - Alodine and AZ 2000 IECW White Paint, 10 W Heater (04/12/04)SAA 0 Cold - SAA 180 Cold

Te

mp

era

ture

Time

SST1 TOP SST1 COLLIMATOR SST1 INTERNAL CORNER PANEL SST2 INTERNAL SST1 HEATER

SST2 HEATER SST1 TOP SST1 COLLIMATOR SST1 INTERNAL CORNER PANEL SST2 INTERNAL


SST Results Table


SST – Coldest Heat Map


SST Hottest Heat Map


ESA – IDPU – SCM Preamp

Thermal

Christopher Smith

Thermal Engineer

[email protected]

510-642-2461


ESA – IDPU – SCM Preamp

ESA

IDPU

SCM Preamp (Mounted on Back)

ESA Support Bracket

• ESA and IDPU mounted together to conserve shielding / weight

• SCM Preamp mounted to IDPU to share heat


ESA-IDPU / Map

Alodined Aluminum

Black Anodized Aluminum


ESA-IDPU Model Inputs

• Optical materials– Black Anodized Aluminum– Alodined Aluminum


• Heaters– Survival Heater

• Conductors– IDPU, 6 ULTEM isolators to bottom deck, 0.0078 < G < .0133 W/C each– Bare Bolted ESA to IDPU,9.8 W/C– ESA Brace to bottom deck, 2 ULTEM isolators, 0.0078 < G < .0133 W/C each– Bare bolted SCM Preamp to IDPU, 5.6 W/C

ESA Brace


ESA-IDPU Model Inputs - Power

Power Dissipation

THM-SYS-009 Rev O, Apr 04


ESA-IDPU Case Sets


ESA-IDPU – Nominal Plots

-40

-30

-20

-10

0

10

20

30

40

50K 100K 150K 200K 250K 300K

IDPU-ESA-SCMPreAmp Alodined / Black Anodized Aluminum (04/12/04)SAA 103 Hot - SAA 90 Cold - SAA 77 Cold - SAA 77 Cold Low Power

Te

mp

era

ture

Time

BOT DECK ESA INTERNAL ESA CYLINDER IDPU BASE IDPU INTERNAL SCMAMP INTERNAL





ESA-IDPU – Top and Bottom to Sun Plots

5

10

15

20

25

30

35

40

45

35000 40000 45000 50000 55000 60000 65000 70000 75000 80000 85000 90000 95000

IDPU-ESA-SCMPreAmp Alodined / Black Anodized Aluminum (04/12/04)SAA 0 Hot - SAA 180 Hot

Te

mp

era

ture

Time




ESA-IDPU Results Table


ESA-IDPU Coldest Temperature map


EAS-IDPU Hottest Temperature Map

themis instrument thermal peer review 1 ucb, february 26, 2004 themis t ime h istory of e vents and...

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