Lunar Reconnaissance Orbiter Overview: The Instrument Suite and Mission

Chin, G.; Brylow, S.; Foote, M. C.; Garvin, J. B.; Kasper, J. C.; Keller, John W.; Litvak, M. L.; Митрофанов, И. Г.; Paige, D. A.; Raney, Keith; Robinson, M. S.; Санин, А. Б.; Smith, David E.; Spence, Harlan E.; Spudis, P. D.; Stern, S. A.; Zuber, M. T.

doi:10.1007/s11214-007-9153-y

Cited by 337 publications

(158 citation statements)

References 13 publications

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“…The Lunar Reconnaissance Orbiter (LRO; Chin et al, 2007) has a suite of science instruments, two of which will be especially useful for investigating geologic structures. The Lunar Reconnaissance Orbiter Camera (LROC) is acquiring images with resolutions as high as 0.5 m/pixel, with image footprints of typically 5 Â 25 km at an altitude of 50 km.…”

Section: Moonmentioning

confidence: 99%

Interpretation and analysis of planetary structures

Schultz

Hauber

Kattenhorn

et al. 2010

Journal of Structural Geology

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Section: Moonmentioning

confidence: 99%

Interpretation and analysis of planetary structures

Schultz

Hauber

Kattenhorn

et al. 2010

Journal of Structural Geology

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“…The focus of future work will be the POD of the Lunar Reconnaissance Orbiter [17,18]. The required knowledge of the spacecraft position is 50 m, which is a challenge given the S-band tracking and the lack of any tracking data over the lunar far side.…”

Section: Current Development and Future Workmentioning

confidence: 99%

Effects of Self-Shadowing on Nonconservative Force Modeling for Mars-Orbiting Spacecraft

Mazarico¹,

Zuber²,

Lemoine³

et al. 2009

Journal of Spacecraft and Rockets

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Modeling improvements of nonconservative forces affecting Mars-orbiting spacecraft are presented in this study. Recent high-resolution gravity fields enable the recovery of smaller signals in the radio tracking data, previously obscured by mismodeled gravitational anomalies. In particular, the estimation of the atmospheric drag experienced by the spacecraft benefits from the new force models. More precise calculations of the spacecraft cross-sectional areas entering the equations for the atmospheric drag and direct solar radiation pressure are possible by accounting for the interplate self-shadowing of the spacecraft physical model. The relevant surface areas can change by as much as 20% on average, and the effects can be very variable within one orbit (10%). The benefits of these updated models are assessed with two spacecraft, the Mars Odyssey and the Mars Reconnaissance Orbiter. The changes in the nonconservative forces can significantly impact the reconstructed spacecraft trajectory and the estimated model parameters depend on the spacecraft geometry and orbit. The atmospheric density estimated by the Mars Odyssey is much improved with self-shadowing applied to the solar radiation, but improvements to both the drag force and the solar radiation are important in this case of the Mars Reconnaissance Orbiter.

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“…Additional measurements with a less complex experimental set-up and additional beam ions would be helpful, but are unlikely to occur given the closure of the AGS. It will be instructive to compare the results of the tests presented here to results returned by the CRaTER instrument [13] aboard the Lunar Reconnaissance Orbiter, to be launched into lunar orbit in 2008. The instrument contains silicon detectors separated by significant depths of tissueequivalent plastic (similar to polyethylene) and will be exposed to the full GCR environment.…”

Section: Discussionmentioning

confidence: 99%