jeff wang lmco lat thermal engineer jeff.wang@lmco

LAT-PR-01967 Section 8.3 Thermal Design 1

GLAST LAT Project

CDR/CD3 Review, May 12-16 2003

Jeff Wang

LMCO

LAT Thermal Engineer

[email protected]

Gamma-ray Large Gamma-ray Large Area Space Area Space TelescopeTelescope

LAT Thermal Systems LAT Thermal Systems AnalysisAnalysis


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003 AgendaAgenda

• Introduction• Design trade analyses performed and results• Thermal systems overview• Thermal parameters

– Requirements and interfaces– Analysis parameters, environments, and case definitions

• Analysis update– Hot- and cold-cases analyses– Survival-case analysis– Other non-design case analyses– Failure-case analyses

• Thermal Control System Design• Summary and Further Work


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003LAT Thermal Systems OverviewLAT Thermal Systems Overview

• Radiators

– Two panels, parallel to the LAT XZ-plane

– Size per panel: 1.82 m x 1.56 m = 2.84 m2

– Aluminum honeycomb structure

• Heat Pipe design

– Constant-conductance heat pipes on Grid Box

– Ammonia working fluid

– Extruded aluminum, with axial groove casings

• Heat pipes

– Variable-conductance Heat Pipes• 6 VCHP’s per Radiator panel• Provides feedback control of grid temperature

– Top Flange Heat Pipes (not shown)• Isothermalize grid structure

– X-LAT Heat Pipes• Remove waste heat from electronics• Connect radiators for load-sharing

– Downspout Heat Pipes• Transport waste heat from grid to Radiators

On-Orbit Thermal Environment and LAT Process Power

Survival Cold Hot Units

Earth IR 208 208 265 W/m2

Earth Albedo 0.25 0.25 0.40

Solar Flux 1286 1286 1419 W/m2

LAT Process Power 0 535 612 W

MLI thermal shielding surrounding ACD, Grid Box, Electronics

X-LAT Heat Pipes shunt electronics power to Radiators

LAT Thermal OverviewLAT Thermal Overview

Active VCHP control allows for variable Radiator area to maintain constant interface temp to LAT

Down Spout Heat Pipes connect Grid to Radiators


GLAST LAT Project


• 3-D ISO OF RADIATOR, X-LAT, DSHP’S FROM RADIATOR TALK


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003LAT Thermal System Schematic DiagramLAT Thermal System Schematic Diagram

Rad

iato

rRad

iato

r

Grid Base Ass’y

CAL

TKR

ACD

X-LAT Plate

EM

I S

kir

tRadMntBkt

Electronics

Htr SwBox

Spacecraft

LV Payload Attach Fitting

EM

I Skirt

RadMntBkt

Htr SwBox

SolarArray

SolarArray

Thermal

Accommodation

Direction of arrow signifiesdirection of heat flow

LAT Thermal Schematic DiagramLAT Thermal Schematic Diagram


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Internal Thermal Design Changes Since Delta-PDRInternal Thermal Design Changes Since Delta-PDR

The following design changes have been incorporated in the CDR thermal model• Added high emissivity black paint to TKR sidewalls

– Lowers peak TKR temperature by radiatively coupling modules together

– Raises ACD survival temperature and lowers TKR hot-case peak temperature by improving radiative coupling between the two

• Connected TKR to Grid with 4 heat straps/module

– Increases temperature gradient across the thermal joint

– Improves thermal joint reliability compared to Delta-PDR thermal gasket design

• Replaced outer ACD MLI blanket layer with germanium black kapton (FOSR before)

– Preferred by subsystem, since MLI is unsupported

– Marginally raises survival case temperatures

• Increased total LAT power (w/o reservoirs) to 612 W (was 602W)

– Total is still within the 650 W allocation• CAL and TKR power increased 26 W• Electronics power dropped 18 W• ACD power increased 3 W

– Net effect is to raise hot-case peak temperatures for the TKR and CAL

• Added S-bend to VCHP transport section

– Results in net drop in survival heater power needs • Reduces survival-case heat leak out of Grid• Increases anti-freeze radiator heater power

– Improves flexibility for better compliance at integration

– Increases transport capacity requirement on VCHP’s


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003LAT Thermal Interface Design Changes Since Delta-PDRLAT Thermal Interface Design Changes Since Delta-PDR

The following interface changes have been incorporated in the CDR thermal model

• Increased Radiator area to 2.78 m2 but decreased efficiency by shortening it– Modified Radiator aspect ratio at request of Spectrum to

accommodate solar arrays

– This change results in slightly higher LAT hot-case temperatures

• Finalized Radiator cut-outs– Added cut-outs for solar array launch locks

– Increased size of cut-out for solar array mast

– This change results in slightly higher LAT hot-case temperatures


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Trade Studies Since Delta-PDRTrade Studies Since Delta-PDR

• Solar Array interface for survival/cold cases– Delta-PDR total survival grid + anti freeze heater power calculated to

be 171 watts (28.0 watts reservoirs) 191 W Total

– Using the Spectrum PDR Solar Array, survival heater power increased to 244 W (28 W for reservoirs)

– With no solar array, total survival heater power increased to 330 watts

– Conclusion: using the Spectrum Astro PDR solar array in the LAT cold- and survival-case models was agreed as reasonable

• Reservoir size reduction– Desire to maximize radiator area and temperature margins

– Used Delta-PDR model to assure that smaller reservoir could totally close heat pipes for survival and provide adequate cold case control

– Reduced size provides more condenser length

– Conclusion: reduce reservoir size from Delta PDR volume of 288 cc to 75 cc. This produces a net gain of 100 mm in condenser length


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Thermal Systems Peer Review RFA StatusThermal Systems Peer Review RFA Status

RFA 13-Stowed Case

Limiting LAT component –VCHP Reservoirs if heaters not activated


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Thermal Systems Peer Review RFA StatusThermal Systems Peer Review RFA Status

• RFA-14 Heater Flight sizing

• RFA-15 With all YS-90 Tracker sidewalls, peak tracker temperature is

• RFA-16 ACD limits

• RFA-21Backup flight heater for anti-freezeheaters: not necessary

• RFA-22 Maximum Tracker temperature with .03 MLI e* is

• RFA-25 Correlation of flight thermistors at unit level

• RFA-30 AO Effects on Germanium Black Kapton-See paper on AO from International SAMPE Technical conference, November 1996.

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Driving Thermal Design RequirementsDriving Thermal Design Requirements

Parameter Requirement Design Margin ComplyVer.

MethodDriving

ReqMax Radiator area (#) < 5.88 m2 5.57 m2 0.31 m2 Y I

Max process power indefinite dissipation 612 W @

T(max)612 W LAT + 38 W Rad @ 24 C

5 C calc + 1 C Operating

Y T, A

Peak process power dissipated for 10 min (#)720 W for 10 min @ T(max)

720 W for 20 min @ <T(max)

10 min, 7 C Y T, A

Min process power indefinite dissipation497 W @

T(min)497 W @ -10 C

50% Rad control auth.

Y T, A

Capable of normal operation when loaded by 75 W/Rad of heat from SC solar arrays

75 W/Rad 73.4 W 0 W/Rad Y T, A

Orbit range of 450 km min to 575 km max 450 - 575 km450 km hot-case 575 km cold-case

OK Y A

Capable of maintaining thermal control during exposure to IR, Albedo, Solar fluxes

OK Y T, A

Provide thermal control with LAT pointed 2pi/24/7/365 during any normal LAT mode

OK Y A

LAT max.min operating temp +30 C / -15 C +24 C / -3 C + 6 C / 12 C Y T, AStability of LAT Control Temp point (3) +/- 3 C < +/- 3 C Y T, AVCHP heater power when LAT is on (at Vmin) < 38 W 13 W @ 27 V 25 W Y DVCHP heater power when LAT is off (at Vmin) < 50 W 42 W @ 27 V 8 W Y DWhen off, orbit-average survival heater power at 27 V min (not incl control auth margin)

< 220 W 152 W 68 W Y D

When off, peak survival heater power < 560 W387 W (incl 30%

control auth)173 W (45%) Y D

During Obs t-vac, TCS capable of full functionality "lying on its side"

OK Y T, A

(1): Total Power = Process Power + VCHP Reservoir Heater Power = 612 + 38 = 650W

(2): Margin on heater power keeps minimum LAT temperature above AT limits

(3): LCT defined as the Grid side of the Grid--DSHP interface point

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Thermal Model Details: LAT Dissipated PowerThermal Model Details: LAT Dissipated Power

• Dissipated power values are pulled directly from the LAT power budget held by the LAT System Engineer

• All power allocations and geographical distribution is under CCB control

Special Status Normal Operations

Surv.Tran-sition

Cold Case

Alloc.Hot

Case10 Min Peak

Unit Comments

Total 50.0 95.3 534.8 590.0 650.0 719.8 WTotal on Grid 0.0 0.0 210.6 234.0 252.1 291.2 W

TKR 139.5 155.0 162.8 192.9 W Evenly distributed up 4 sides of TKR moduleCAL 60.3 67.0 75.8 83.4 W Evenly distributed up 4 sides of CALACD 10.8 12.0 13.6 14.9 W Evenly distributed around 4 sides of BEA

Total on X-LAT 0.0 45.3 286.2 318.0 359.9 390.5 WTEM 43.2 48.0 54.3 58.1 W 1 board/bayTPS 148.5 165.0 186.7 203.2 W 1 P.S. board/bay for TEMGASU 19.8 22.0 24.9 27.8 W 1 lg board spanning 4 center baysSIU 27.2 21.6 24.0 27.2 29.7 W 2 bds in 2 bays (1 hot, 1 cold)EPU 38.7 43.0 48.7 53.0 W 2 bds in 2 bays, both hot (+ 1 cold spare)PDU 18.1 14.4 16.0 18.1 18.6 W 2 bds in 2 bays (1 hot, 1 cold)

Radiators 50.0 50.0 38.0 38.0 38.0 38.0 W Bottom of Radiator panels at VCHP's

LAT Dissipated Power ValuesLAT Dissipated Power Values

Source: LAT-TD-00225-04 “A Summary of LAT Dissipated Power for Use in Thermal Design”, 13 Mar 2003

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Thermal Model Details: Electronics Box Dissipated PowerThermal Model Details: Electronics Box Dissipated Power

Source: LAT-TD-00225-04 “A Summary of LAT Dissipated Power for Use in Thermal Design”, 13 Mar 2003

Cold Case Power Dissipation Hot Case Power Dissipation

Bay 12EPU-B

Bay 13Empty

Bay 14Empty

Bay 15Empty

Bay 12EPU-B

Bay 13Empty

Bay 14Empty

Bay 15Empty

0 0 0 0 0 0 0 0

Bay 8PDU-B

Bay 9GASU

Bay 10GASU

Bay 11SIU-B

Bay 8PDU-B

Bay 9GASU

Bay 10GASU

Bay 11SIU-B

0 9.9 0 0 0 12.4 0-X Side

Bay 4PDU-A

Bay 5GASU

Bay 6GASU

Bay 7SIU-A

+X SideSun Side

-X SideBay 4PDU-A

Bay 5GASU

Bay 6GASU

Bay 7SIU-A

+X SideSun Side

14.4 9.9 21.6 18.11 0 12.4 27.2

Bay 0EPU-A

Bay 1Empty

Bay 2Empty

Bay 3EPU-A

Bay 0EPU-A

Bay 1Empty

Bay 2Empty

Bay 3EPU-A

19.4 0 0 19.4 24.3 0 0 24.3

Boxes 94.5 Boxes 118.8TEM/TPS: 191.7 TEM/TPS: 241.0X-LAT Tot 286.2 X-LAT Tot 359.9

Legend: Notes:GASU Global trigger, ACD, and Switching Unit 1. All power is in wattsSIU Spacecraft Interface UnitPDU Power Distribution BoxEPU LAT Event Processor-A A-side, powered box-B B-side, unpowered cold spare

LAT Top View

-Y SideLAT Radiator

+Y SideLAT Radiator

+Y SideLAT Radiator

-Y SideLAT Radiator

LAT Top View

LAT +X

LAT +Y

LAT +X

LAT +Y

LAT Dissipated Power Distribution in Special Electronics BoxesLAT Dissipated Power Distribution in Special Electronics Boxes

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Environmental Temperature LimitsEnvironmental Temperature Limits

Component Low Temp Limits High Temp Limits SurvivalQual AT Oper. Oper. AT Qual Low High

Tracker Module @ SSD -30 -20 -15 30 35 50 -30 50Calorimeter Module -30 -20 -15 25 40 50 -30 50TEM Box (1) -40 -35 -30 45 50 55 -40 60EPU Box (1) -40 -35 -30 45 50 55 -40 60SIU Box (1, +) -40 -35 -30 45 50 55 -40 60PDU Box (1, +) -40 -35 -30 45 50 55 -40 60GASU Box (1, +) -40 -35 -30 45 50 55 -40 60ACD, BEA Sub-Ass'y (2, +) -25 -20 -15 30 35 40 -40 45TSA Sub-Ass'y (+) -40* -35 -30 35 40 45 -50 45Grid Box Sub-Ass'y (+) -40* -15 -10 30 35 40 -40 40CCHP Components -40* -15 -10 30 35 40 -67 60VCHP Components -40* -15 -10 30 35 40 -67 60Radiator Sub-Ass'y (+) -40 -35 -30 20 25 30 -67 60Notes:All temperatures are in degrees C; see acronym list for an explanation of acronyms usedTemperatures shown are for the hottest/coldest extremity of the subsytem, except as indicated(+) Protoflight units only. Qual temps shown are for proto-flight qual testing(*) Not all performance requirements will be met at EOL for this test. See Appendix A for a full explanation(1) Temperatures shown are for the box interface to its heat sink(2) BEA temperature limits apply to the full ACD assembly as well


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Verification Test TemperaturesVerification Test Temperatures

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003LAT Thermal Math Model and StatusLAT Thermal Math Model and Status

• TSS Model-Calculates radks and heat rates– XXX Surfaces– YYY Active Nodes

• Sinda Model– Submodels

• ACD CDR model • Detailed TKR model• Reduced Cal model• Detailed Grid model• X-LAT and Electronics model updated• Bus model includes solar arrays and SV

– IRD array for hot case– Cold case/survival uses Spectrum Astro PDR

solar array• Detailed radiator and heat pipes • ZZZ nodes total

– Heat pipe logic in VCHPs to predict gas front

– Added VCHP heater control logic• Logic will be part of SIU control of thermal system

Model status: the model is mature, and interfaces understood. The electronics thermal model interface is the one deficiency, and is being worked on.


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Thermal Model Details: Thermal InterfacesThermal Model Details: Thermal Interfaces

• Thermal interfaces to the Spacecraft– All specified in LAT IRD (433-IRD-0001) except cold-/survival-case

solar array definition, which has been arrived at by mutual agreement between Spectrum, LAT, and the GLAST PO

• Environmental parameters– PDR and Delta-PDR analysis shows that Beta = 0, pointed-mode is

the LAT hot-case

– Solar loading is per the LAT IRD

– Sky-survey attitude and “noon roll” is based on an assumed slew rate of 9 degrees/min, max

• Thermal design case parameters are tabulated on the following chart

Parameter HotSurv/Cold

Unit

SC interface temperature 50 -10 CLAT MLI effective emittance 0.01 0.03SC MLI surface emissivity 0.05 0.05Conductive leak: SC bus to Grid 5 0 WConductive leak: SC to each Rad 5 0 WOptical Properties EOL BOLMaterial/Interface Properties Hot Cold

SC-LAT Thermal Interface ParametersSC-LAT Thermal Interface Parameters


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Thermal Model Details: Design Case DetailsThermal Model Details: Design Case DetailsThermal Case: Survival Cold Nominal Hot Rocking Transition Unit

Orbit Definition and EnvironmentLAT Operational Mode Safe-Hold [1] Pointed [2] Sky-Survey [3] Pointed [4] Sky-Survey [3] Re-Point [6]LAT Orientation +X on sun line, +Y

90 deg out of orbital plane

-Z on sun line, +Y 90 deg out of orbital

plane

-Z on nadir line, sun line in +XZ

plane

+Z 90 deg out of orbital plane, +X

on sun line

-Z on nadir line, sun line in +XZ

plane

Change from Pointed[2] to

Pointed[4]Altitude 575 575 450 450 450 450 kmBeta Angle 0 0 0 0 0 0 degOrbit inclination 28.5 28.5 28.5 28.5 28.5 28.5 degOrbit eccentricity 0 0 < 0.01 0.01 < 0.01 0.01 ---Earth IR 208 208 265 265 265 265 W/m2Earth Albedo 0.25 0.25 0.4 0.4 0.4 0.4Solar Flux 1286 1286 1419 1419 1419 1419 W/m2Orbit-averaged solar flux due to re-pointing 0 0 noon flip* 0 noon flip*+27 27 WSolar flux from Radiators mis-alignment 6 6 6 6 W/m2Tolerances (not included in thermal model) +X-axis on sun line

to < +/-15 deg Sun line in +XZ-

plane to < +/- 1 degSun line in +XZ-plane to < +/- 1

deg

Sun line in +XZ-plane to < +/- 1

deg

Sun line in +XZ-plane to < +/- 1

degInstrument Status and Control

LAT process power mode Survival Minimum Maximum Maximum Maximum MaximumVCHP status/reservoir heater power 100% closed/100% TBD% closed/<60% Fully open/0 Fully open/0 Fully open/0 Fully open/0Material/Interface Properties cold-case cold-case hot-case hot-case hot-case hot-case

Solar Array Survival SA Cold SA Hot Real SA Design Hot SA Hot Real SA Hot Real SATotal Array Size (2 wings-3 panels/Wing) 4.7m X 1.54 m, 3

panels with 1" gaps4.7m X 1.54 m, 3

panels with 1" gaps4.7m X 1.54 m, 3 panels with 1"

gaps

4.7m X 1.54 m, 3 panels with 1"

gaps


gaps


gapsDistance from radiator 1.3 1.3 1.3 0.52 1.3 1.3 mBoom size cross-sectional area 0.127 0.127 0.127 0.0254 0.127 0.127 m 2̂Panel Front alpha 0.92 0.92 0.92 0.9 0.92 0.92Solar cell Efficiency 26% 26% 17% NA 17% 17% %Effective Front Panel Alpha 0.68 0.68 0.75 0.9 0.75 0.75Panel front emissivity 0.86 0.86 0.84 0.85 0.84 0.84Panel back alpha 0.18 0.18 0.4 0.5 0.4 0.4Panel back emissivity 0.91 0.91 0.87 0.88 0.87 0.87Boom alpha 0.39 0.39 0.45 0.8 0.45 0.45Boom emissivity 0.75 0.75 0.72 0.9 0.72 0.72Thru conductance (front-back, per panel) 56.2 56.2 56.2 74.3 56.2 56.2 W/KTotal Thermal Capacitance (per panel) 6135 6135 6135 4665 6135 6135 J/K

Source: LAT-TD-00224-04 “LAT Thermal Design Parameters Summary”, 19 Mar 2003

LAT Thermal Case DescriptionLAT Thermal Case Description


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003 Results SummaryResults Summary

Temperature Predicts for LAT SubsystemsTemperature Predicts for LAT Subsystems

• Hot-Case peak temperatures predicts

– Tracker• Predict: 24 oC max• Operating Limit: 30 oC

– Calorimeter:• Predict: 16 oC max• Operating Limit: 25 oC

– Electronics• Predict: 28 oC max• Operating Limit: 45 oC

• These are “raw predicts” and do not include 5 oC uncertainty Survival Cold Ops Hot Design

Component Min Max Min Max Min Max

TKR (worst-case SSD) -23.8 -17.1 -2.8 9.2 13.3 24.0CAL (base plate) -18.9 -17.8 0.8 3.1 12.4 15.8TEM* -19.7 -19.1 4.9 12.4 17.6 27.8TPS* -19.7 -19.1 4.7 12.4 17.2 27.7EPU* -19.7 -19.1 0.0 4.9 0.0 17.5SIU* -19.2 -19.1 2.4 10.2 12.9 24.1PDU* -19.2 -19.1 2.3 7.6 12.6 20.8GASU* -19.7 -19.5 8.8 9.0 21.2 22.0ACD, BEA (worst-case extremity) -19.1 -16.2 3.0 3.8 14.8 18.0TSA (worst-case extremity) -25.6 -13.3 -5.5 -1.9 15.1 20.2Notes:All temperatures are in degrees CTemperatures shown are for the hottest/coldest extremity of the subsytem, except as indicatedTemperature predicts do not include 5 C analysis uncertainty margin

(*) Temperatures shown are for the box interface to its heat sink

UPDATE

quote all predicts

including 5C margin


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Temperature Predicts and Margins to Operating LimitTemperature Predicts and Margins to Operating Limit

Survival Cold Ops Hot DesignComponent Predict Limit Margin Predict Limit Margin Predict Limit Margin

TKR (worst-case SSD) -23.8 -30.0 6.2 -2.8 -15.0 12.2 24.0 30.0 6.0CAL (base plate) -18.9 -30.0 11.1 0.8 -15.0 15.8 15.8 25.0 9.2TEM* -19.7 -40.0 20.3 4.9 -30.0 34.9 27.8 45.0 17.2TPS* -19.7 -40.0 20.3 4.7 -30.0 34.7 27.7 45.0 17.3EPU* -19.7 -40.0 20.3 0.0 -30.0 30.0 17.5 45.0 27.5SIU* -19.2 -40.0 20.9 2.4 -30.0 32.4 24.1 45.0 20.9PDU* -19.2 -40.0 20.8 2.3 -30.0 32.3 20.8 45.0 24.2GASU* -19.7 -40.0 20.3 8.8 -15.0 23.8 22.0 45.0 23.0ACD, BEA (worst-case extremity) -19.1 -40.0 20.9 3.0 -15.0 18.0 18.0 30.0 12.0TSA (worst-case extremity) -25.6 -50.0 24.4 -5.5 -30.0 24.5 25.0 35.0 10.0All temperatures are in degrees CTemperatures shown are for the hottest/coldest extremity of the subsytem, except as indicatedTemperature predicts do not include 5 C analysis uncertainty margin(*) Temperatures shown are for the box interface to its heat sink

Temperature Predicts for LAT SubsystemsTemperature Predicts for LAT Subsystems

• Temperature predicts show that all subsystem components carry greater than 5 oC margin to their operating limit

• Minimum margin of 6 oC is for the center TKR module

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Hot Case TKR Peak Temperature GradientHot Case TKR Peak Temperature Gradient

Location Temp (degC)

Top tray 17.60Wall at top tray 23.00Closeout at top of st'd tray 24.00Bottom of regular tray wall 18.80Top of Cu strap interface 18.30Top of grid 14.30

-Y Rad +Y RadDSHP-4 top row, Rad 6.80 6.50DSHP-4, at VCHP 5.10 4.80Top of Radiator by VCHP4 -3.30 -4.10Maximum temp gradient 27.30 28.10

• Peak temperature gradient is along the heat transfer path to the top of a center TKR module

• Key temperature gradients– Up TKR wall: 5.7 deg C– TKR—Grid thermal joint: 4.0 deg C– Top of Grid—DSHP at VCHP: ~7.6 deg C

TKR Maximum Temperature Gradient in the LATTKR Maximum Temperature Gradient in the LAT

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Hot Case Environmental Orbit LoadsHot Case Environmental Orbit Loads

Hot Case Orbit: Beta 0, +Z Zenith, +X Sun Pointing

sun

Environmental Load on Radiators for Hot-Case OrbitEnvironmental Load on Radiators for Hot-Case Orbit

Solar Constant =1419 W/m 2

Planet Power=265W/m2

Albedo=0.4

0

100

200

300

400

500

600

0

467.1

7

934.3

4

1401

.517

2717

28

1868

.7

2335

.828

03

3270

.2

3737

.338

7838

79

4204

.5

4671

.7

5138

.956

06

Time(seconds)

Ab

sorb

ed F

lux

(W)

Total-Rad1

Total-Rad2

UPDATE


GLAST LAT Project


2008 W orbital heating



83.5 W solar array heating 84 W solar array heating

652 W to space 648 W to space

2072 W to space Instrument Power

612 W

24 W from bus

46 W solar array heating

Y

Z

30 W from bus

3.9 W to space 3.9 W to space

Hot Case QMAPHot Case QMAP

Orbital heatingRadiated to spaceBus heatingBus heatingVCHP reservoir


91 W to space

Hot Case QMAPHot Case QMAP

Hot Operational Orbit Average QmapHot Operational Orbit Average Qmap

30 W from bus

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003 Hot Case TemperaturesHot Case Temperatures

Predicted LAT Temperatures for Hot-Case OrbitPredicted LAT Temperatures for Hot-Case Orbit

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Hot Case Tracker TemperatureHot Case Tracker Temperature

Predicted TKR Temperature Showing Analysis Predicted TKR Temperature Showing Analysis Predict is Stabilizing Toward an AymptotePredict is Stabilizing Toward an Aymptote

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Hot Case Radiator TemperaturesHot Case Radiator Temperatures

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Hot Case with “Real” PDR Solar ArraysHot Case with “Real” PDR Solar Arrays

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003 Survival Case OrbitSurvival Case Orbit

sun

Survival Orientation: +X Sun Pointing

Environmental Load on Radiators for Survival-Case OrbitEnvironmental Load on Radiators for Survival-Case Orbit

Solar Constant =1286 W/m2

Planet Power = 208 W/m2

Albedo = 0.25

0

20

40

60

80

100

120

140

160

0 960 1816 1920 2880 3841 3945 4801 5761Time(seconds)

Ab

so

rbe

d F

lux

(W)

Total-Rad1

Total-Rad2

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003 Survival Case QMAPSurvival Case QMAP




258 W to space

1569 W to space Make-up Heaters

61W

13 W from bus


12 W from bus

9.9 W to space

45.5 W heater power

45.5 W heater power

63 W to space


22 W heater power

Survival Case QMAPSurvival Case QMAP

Y

Z

Survival Orbit Average QmapSurvival Orbit Average Qmap

Orbital heatingRadiated to spaceBus heatingBus heatingVCHP reservoir Anti-freeze heatersVCHP reservoir heaters



259 W to space

10.0 W to space

23 W heater power

12 W from bus

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003 Survival TemperaturesSurvival Temperatures

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003 Survival Case TemperaturesSurvival Case Temperatures

Predicted LAT Temperatures for Survival-Case OrbitPredicted LAT Temperatures for Survival-Case Orbit

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Survival Case Radiator TemperaturesSurvival Case Radiator Temperatures

Predicted Radiator Temperatures for Survival-Case OrbitPredicted Radiator Temperatures for Survival-Case Orbit

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003 Survival Heater PowerSurvival Heater Power

• Survival heater power (orbit average)• Grid make-up heaters 61 W• VCHP anti-freeze heaters 91 W• X-LAT Plate heaters 0 W• Total heater power 152 W

• Allocation: 220 Watts• Heater power margin: +68 W (45% margin)

Parameter Requirement Design Margin ComplyVer.

MethodWhen off, orbit-average survival heater power at 27 V min (not incl control auth margin)

< 220 W 152 W 68 W (45%) Y D

When off, peak survival heater power < 560 W387 W @ 35 V (incl 30% control auth)

173 W (45%) Y D

Control margin on heater power > 30% 88% 55% Y D

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003 VCHP Reservoir Heater PowerVCHP Reservoir Heater Power

• Reservoir Heater Size– 3.5 W/Reservoir @ 27V = 42 W for 12 (100% duty cycle)– Survival minimum required power = 1.5 W/reservoir– Heaters sized at > 200% of required minimum

• Reservoir Duty Cycles– Hot Case: 0% and 0 W– Cold Case: ~ 30% 13 W orbit-averaged power– Survival: 100% 42 W orbit-averaged power (heaters locked on

while LAT is off)

Parameter Requirement Design Margin Comply

VCHP heater power when on (at Vmin) < 38 W 13 W @ 27 V 25 W Y

VCHP heater power when off (at Vmin) < 50 W 42 W @ 27 V 8 W YControl margin on heater power > 30% 200% 170% Y

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003 Cold Case TemperaturesCold Case Temperatures

Predicted Temperatures for Cold-Case OrbitPredicted Temperatures for Cold-Case Orbit

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Cold Case Radiator TemperaturesCold Case Radiator Temperatures

Predicted Radiator Temperatures for Cold-Case OrbitPredicted Radiator Temperatures for Cold-Case Orbit

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003LAT Failure Analyses—Hot-CaseLAT Failure Analyses—Hot-Case

Case #

Orbit Parameters

Solar ArrayRadiator

TempNCG

Heat Pipe Failure

Heater Failure

0ther

9 Hot Case Design Hot Calculated 5 yr VCHP # 2 None None10 Hot Case Design Hot Calculated 5 yr VCHP # 0 None None11 Hot Case Design Hot Calculated 5 yr XLAT # 2 None None12 Hot Case Design Hot Calculated 5 yr XLAT # 0 None None13 Hot Case Design Hot Calculated 5 yr DSHP #2 None None14 Hot Case Design Hot Calculated 5 yr DSHP #0 None None15 Hot Case Design Hot Calculated 5 yr Grid HP # 2 None None16 Hot Case Design Hot Calculated 5 yr Grid HP # 3 None None17 Hot Case Design Hot Calculated 5 yr Grid HP # 0 None None

18 Hot Case Design Hot Calculated 5 yr None1 Grid Htr

ClosedNone

19 Hot Case Design Hot Calculated 5 yr None1 Rsvr Htr

ClosedNone

20 Hot Case Design Hot Calculated 5 yr None NoneTKR-grid

conduction lost (1 Bay)

Summary of Hot-Case Failure AnalysesSummary of Hot-Case Failure Analyses


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003LAT Failure Analyses—Cold/Survival CasesLAT Failure Analyses—Cold/Survival Cases

Case #

Orbit Parameters

Solar ArrayRadiator

TempNCG

Heat Pipe Failure

Heater Failure

1 Cold Case Real Cold Calculated None None None

2 Cold Case Real Cold Calculated None None1 VCHP

Reservoir 3 Survival Case Real Cold Calculated None None None

4 Survival Case Real Cold Calculated None None1 VCHP

Reservoir Heater Open

5 Survival Case Real Cold Calculated None None1Grid Heater

Open

6 Survival Case Real Cold Calculated None NonePri & BU VCHP

Reservoir Heaters on

7 Survival Case Real Cold Calculated None None1 Anti-freeze Heater Circuit

on

Summary of Cold-/Survival-Case Failure AnalysesSummary of Cold-/Survival-Case Failure Analyses


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Thermal Failure Analysis Results SummaryThermal Failure Analysis Results Summary

• TABLE OF PEAK TEMPS AND TEMP CHANGES FOR FAILURE CASES RUN

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003Thermal Failure Analysis Results SummaryThermal Failure Analysis Results Summary

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003LAT Thermal Analysis SummaryLAT Thermal Analysis Summary

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003 Integration and Test FlowIntegration and Test Flow

ObservatoryIntegration

Sine Vibe

TowerIntegration

LATIntegration

LAT Test ObservatoryIntegration

TKR

CAL

TEM/TPS

Grid

Radiators

EPU

SIU

GASU

PDU

ACD

IntegrateE-Boxesw/ Grid

Htr Box

Delivery

AlivenessTests

LimitedPerformance

X-LAT Plate

C

CLE A

A

MassProperties

EMI/EMC

L

InstallRadiators

Acoustic

L

C

Thermal Vac

ThermalBalance

C L

C

Final MassProperties

Pre-ShipSurvey

L

A

Ship toSA

F

F

F

EMI SHIELD

Survey Survey

M

O M

L

M

O Optical M Muon

IntegrateTKR/CAL &TEM's with

Grid

SurveyO

Integrate ACD

SurveyO

Integrate EMISkirt, Htr Switch

Boxes

Mech Fit-Check

SurveyM

Modalsurvey

E

L

FunctionalTests

Survey:

L

ElectricalInterfaceTests

ComprehensivePerformance

Environmental Tests

E

M

C

v CDR 3/14/03

Integrate X-LAT

LAT Integration and Test FlowLAT Integration and Test Flow

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003LAT Thermal Balance/Thermal-Vacuum TestsLAT Thermal Balance/Thermal-Vacuum Tests

• Test goals– Thermal-Balance

• Verify that the LAT thermal control system is properly sized to keep maximum temperatures within mission limits, while demonstrating at least 30% control margin

• Validate the LAT thermal control system control algorithms• Verify that the VCHP control effectively closes the radiator to when the LAT is off• Validate the LAT thermal model by correlating predicted and measured temperatures

– Thermal-Vacuum• Verify the LAT’s ability to survive proto-qualification temperature levels at both the high and low

end• Test for workmanship on hardware such as wiring harnesses, MLI, and cable support and strain-

reliefs which will not have been fully verified at the subsystem level• Demonstrate that the LAT meets performance goals at temperature• Provide stable test environment to complete LAT surveys, as detailed in LAT-MD-00895, “LAT

Instrument Survey Plan”

• Configuration– The LAT instrument will be fully integrated but the SC solar arrays will not be installed

– The LAT will be powered on and off during testing per the test procedure

– The LAT will be oriented with the Z-axis parallel to the ground to allow all heat pipes to operate and the +X axis facing up

– All MLI blanketing will be in its flight configuration for the duration of the 2 tests– The LAT will NOT be reconfigured after the thermal-balance test


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003LAT Thermal Balance/Thermal-Vacuum Tests (cont)LAT Thermal Balance/Thermal-Vacuum Tests (cont)

• Instrumentation

– Thermocouples and RTD’s will be used to instrument the LAT and test chamber

– LAT flight housekeeping instrumentation includes many thermistors and RTD’s. These will also be used for monitoring temperatures within the LAT

• Specialized test equipment requirements

– Chamber pressure of < 1 x 10-5 Torr

– Chamber cold wall temperature of –180 oC to provide a cold sink for accumulation of contaminants

– Thermally controlled surfaces in the chamber• 5 plates for ACD surfaces, each individually controlled• 2 plates for the radiators(one for each side), each individually controlled• 1 plate to simulate the bus, controlling the environment to the X-LAT Plate and the back of each

radiator

– Heat exchangers mounted on the +/– X sides of the LAT Grid, to increase ramp rate during transitions

– LAT heat pipes will be leveled to within 0.2 degrees

– 20 oC/hr max ramp rate

– Facility capable of holding LAT stable to < 2 oC/hr rate of change (TBR)

• Test profile

– Dwell at high and low temps for 12 hours, min

– Comprehensive Performance Tests conducted at select plateaus• Perform at ambient, during cold and hot soaks, and at return to ambient

– Limited Performance Tests during transitions and plateaus• Check operating modes and monitor units for problems or intermittent operation


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003LAT Thermal Balance/Thermal-Vacuum Test ProfileLAT Thermal Balance/Thermal-Vacuum Test Profile

LAT Thermal-Vacuum Test ProfileLAT Thermal-Vacuum Test Profile

Source: LAT-MD-01600-01, “LAT Thermal-Vacuum Test Plan,” March 2003

T-Vac Cycles

1 2 3 4

Bake OutHot T- Bal

Cold T-Bal

Cold SurvT-Bal

Ambient Pressure, Temp Pressure < 1x 10-5 Torr

T-Bal

Pump-Down Repress

Warm-up

Hot QT

ColdQT

LAT Off

CPT

Cold Start

CPT

CPT CPT

LAT Off

Muon Survey

Muon Survey

Muon Survey

LPT LPT CPT

LPT LPT CPT

LAT On

LAT On

Hot QT


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003 Thermal Test LevelsThermal Test Levels

• Test strategy

– Drive components to PFQ limit for LAT, defined in the MAR as Operating limit +/- 10 oC, min

• Minimum test margins

– 5 C margin from Operating to AT level

– 5 C margin from AT to LAT PFQ level

LAT Thermal Verification Test TemperaturesLAT Thermal Verification Test Temperatures

Component Low Temp Limits High Temp Limits SurvivalQual AT Oper. Oper. AT Qual Low High

Tracker Module -30 -20 -15 30 35 50 -30 50Calorimeter Module -30 -20 -15 25 40 50 -30 50TEM Box (1) -40 -35 -30 45 50 55 -40 60EPU Box (1) -40 -35 -30 45 50 55 -40 60SIU Box (1, +) -40 -35 -30 45 50 55 -40 60PDU Box (1, +) -40 -35 -30 45 50 55 -40 60GASU Box (1, +) -40 -35 -30 45 50 55 -40 60ACD, BEA Sub-Ass'y (2, +) -25 -20 -15 30 35 40 -40 45TSA Sub-Ass'y (+) -40* -35 -30 35 40 45 -50 45Grid Box Sub-Ass'y (+) -40* -15 -10 30 35 40 -40 40CCHP Components -40* -15 -10 30 35 40 -67 60VCHP Components -40* -15 -10 30 35 40 -67 60Radiator Sub-Ass'y (+) -40 -35 -30 20 25 30 -67 60Notes:All temperatures are in degrees C; see acronym lis t for an explanation of acronyms usedTemperatures shown are for the hottes t/coldest extremity of the subsytem, except as indicated(+) Protoflight units only. Qual temps shown are for proto-flight qual tes ting(*) Not all performance requirements will be met at EOL for this tes t. See Appendix A for a full explanation(1) Temperatures shown are for the box interface to its heat s ink(2) BEA temperature limits apply to the full ACD assembly as well

Source: LAT-SS-00778-01 “LAT Environmental Specification,” March 2003

UPDATE


GLAST LAT Project

CDR/CD3 Review, May 12-16 2003 SummarySummary

• Summary– We are working towards completing and using a fully integrated

thermal model of the CDR design for generating temperature predicts for CDR

– The Radiator thermal design has been changed to incorporate modifications to the spacecraft interface

– Predicts show that we meet all operating limits, with adequate margin, when using the IRD solar arrays

UPDATE

jeff wang lmco lat thermal engineer jeff.wang@lmco

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