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Latest LRO Geometry Model Design A Concept

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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Latest LRO Geometry Model Design A Concept

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

  2. 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

  3. 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

  4. Thermal Model AssumptionsFor CRaTER Instrument CRaTER Thermal Preliminary Results

  5. Preliminary Results (Steady-state) CRaTER Thermal Preliminary Results

  6. 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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