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LRO CRaTER Preliminary Temperature Predictions Design A Concept  Old Concept April 12, 2005 Cynthia Simmons/ESS. Latest LRO Geometry Model Design A Concept. CRaTER located on its own bench in old spacecraft concept. Instrument Deck. +X. -Y. Propulsion Module. Beta 0°. Beta 90°.

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LRO CRaTERPreliminary Temperature PredictionsDesign A Concept  Old ConceptApril 12, 2005Cynthia Simmons/ESS


Latest lro geometry model design a concept
Latest LRO Geometry ModelDesign A Concept

CRaTER located on its own bench in old spacecraft concept

Instrument Deck

+X

-Y

Propulsion Module

CRaTER Thermal Preliminary Results


Beta 0°

Beta 90°

LRO Thermal Environment

Orbit Parameters

type lunar circular

altitude 50 +/-20 Km

inclination 90°

orbit period 113. minutes

full sun orbits beta 90.0° to 76.4° (55 days/yr)

eclipsed orbits beta 76.4° to 0.0° (310 days/yr)

max. eclipse 48. minutes (beta 0°)

lunar orbit plane angle to earth 5.15°

Lunar Thermal Environment

solar constant 1420 - 1280 W/m2 (Hot to Cold)

albedo factor 0.13 – 0.06 (0.073 average)

Lunar emittance 1 – albedo factor

infrared emission

sunlit side varies (cosine from sub solar point)

sub solar point 400 K (1335 W/m2)

dark side 100 K (5.22 W/m2)

CRaTER Thermal Preliminary Results


Thermal model assumptions for crater instrument
Thermal Model AssumptionsFor CRaTER Instrument

CRaTER Thermal Preliminary Results


Preliminary results steady state
Preliminary Results (Steady-state)

CRaTER Thermal Preliminary Results


Latest lro geometry model design e concept
Latest LRO Geometry ModelDesign E Concept

CRaTER location in latest spacecraft concept

Instrument Deck

Avionics Module

Propulsion Module

PAF

Solar Array

+X

-Y

NOTE: Star Trackers and solar array will be moved to new location.

CRaTER Thermal Preliminary Results


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