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  • 1
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    Trajectory Design and Orbit Determination for the Lunar CRater Observation and Sensing Satellite (LCROSS) (2007)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: The Lunar CRater Observation and Sensing Satellite (LCROSS) was competitively selected by the National Aeronautical and Space Administration (NASA) Exploration Systems Mission Directorate (ESMD) as a low-cost (〈 $80M) 1000 kg secondary payload to be launched with the Lunar Reconnaissance Orbiter (LRO) in October of 2008. LCROSS is a lunar impactor mission that will investigate the presence or absence of water in a permanently shadowed crater. Following launch, trans-lunar injection (TLI) and separation from LRO, LCROSS will remain attached to the launch vehicle's approximately 2300 kg spent Earth Departure Upper Stage (EDUS) and will guide it toward an impact of a permanently shadowed crater at the lunar South Pole. Hours prior to impact, LCROSS will separate from the EDUS and perform a braking maneuver that will allow the spacecraft to take measurements of the resulting EDUS impact ejecta cloud for several minutes, before impacting the crater as well. As a cost-capped secondary mission that must accommodate specific LRO launch dates, LCROSS faces unique challenges and constraints that must be carefully reconciled in order to satisfy an ambitious set of science observation requirements. This paper examines driving mission requirements and constraints and describes the trajectory design and navigation strategy that shape the LCROSS mission.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Proceedings of the 20th International Symposium on Space Flight Dynamics; NASA/CP-2007-214158
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Resource Prospector Instrumentation for Volatile Analysis (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Resource Prospector Instrumentation for Volatile Analysis, presentation for Exploration Science Forum conference.
    Keywords: Lunar and Planetary Science and Exploration
    Type: KSC-E-DAA-TN44629 , Annual NASA Exploration Science Forum (NESF); Jul 18, 2017 - Jul 20, 2017; Moffett Field, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Challenges of Rover Navigation at the Lunar Poles (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Observations from Lunar Prospector, LCROSS, Lunar Reconnaissance Orbiter (LRO), and other missions have contributed evidence that water and other volatiles exist at the lunar poles in permanently shadowed regions. Combining a surface rover and a volatile prospecting and analysis payload would enable the detection and characterization of volatiles in terms of nature, abundance, and distribution. This knowledge could have impact on planetary science, in-situ resource utilization, and human exploration of space. While Lunar equatorial regions of the Moon have been explored by manned (Apollo) and robotic missions (Lunokhod, Cheng'e), no surface mission has reached the lunar poles.
    Keywords: Lunar and Planetary Science and Exploration; Ground Support Systems and Facilities (Space)
    Type: ARC-E-DAA-TN25257 , Annual NASA Exploration Science Forum (ESF); Jul 21, 2015 - Jul 23, 2015; Moffett Field, CA; United States
    Format: application/pdf
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  • 4
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    Near-Infrared Volatile Spectrometer System (NIRVSS) Spectrometers for NASA's Resource Prospector (RP) Mission (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Lunar and Planetary Science and Exploration; Instrumentation and Photography
    Type: ARC-E-DAA-TN26771 , NASA Ames Instrument Workshop; Sep 16, 2015; Moffett Field, CA; United States
    Format: application/pdf
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  • 5
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    Synchronized Lunar Pole Impact Plume Sample Return Trajectory Design (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The presented trajectory design enables two maneuverable spacecraft launched onto the same trans-lunar injection trajectory to coordinate a steep impact of a lunar pole and subsequent sample return of the ejecta plume to Earth. To demonstrate this concept, the impactor is assumed to use the LCROSS missions trajectory and spacecraft architecture, thus the permanently-shadowed Cabeus crater on the lunar south pole is assumed as the impact site. The sample-return spacecraft is assumed to be a CubeSat that requires a complimentary trajectory design that avoids lunar impact after passing through the ejecta plume to enable sample-return to Earth via atmospheric entry.
    Keywords: Astrodynamics; Lunar and Planetary Science and Exploration
    Type: AAS 16-550 , ARC-E-DAA-TN32698 , AAS/AIAA Space Flight Mechanics Meeting; Feb 15, 2016 - Feb 18, 2016; Napa, CA; United States
    Format: application/pdf
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