The Lunar Prospector attitude data set consists of values for the spacecraft spin rate and spin axis orientation (attitude) as a function of time. These values are determined from spacecraft attitude data (sun and limb crossing sensors) and ephemeris data. Spacecraft orientations are given as right ascension and declination of the spacecraft spin axis in the Mean-of-J2000 Ecliptic reference frame. The attitude data set consists of a single, cumulative file for the entire mission. Records are added to this file following each significant change in either the spin rate or spin axis orientation. The spacecraft spin rates and attitudes in this data set are orbit averages. The instantaneous spin rate can be determined from the sun pulse data set. The instantaneous spin rate varies as the spacecraft passes into and out of the Moon's shadow and after each spacecraft maneuver. Generally, an attitude record is included for times immediately before and after each maneuver.

The Lunar Prospector spacecraft position data set consists of spacecraft position determinations in selenographic latitude, longitude, and altitude coordinates in one minute intervals. The data set also contains spacecraft velocity and distance from the center of the Moon as a function of time. The coordinate system is selenographic with east longitude positive. The data set is generated by the Goddard Flight Dynamics Analysis Branch.

The Lunar Prospector spacecraft position data set consists of spacecraft position determinations in selenographic latitude, longitude, and altitude coordinates in one minute intervals. The data set also contains spacecraft velocity and distance from the center of the Moon as a function of time. The coordinate system is selenographic with east longitude positive. The data set is generated by the Goddard Flight Dynamics Analysis Branch.

The Lunar Prospector ephemeris data set consists of spacecraft position and velocity determinations as a function of time in Moon-centered, Earth equator, mean of J2000 coordinates. Tracking data collected by ground stations are used by the Goddard Flight Dynamics Analysis Branch (FDAB) to compute the Lunar Prospector orbit ephemeris. The Level 0 Data archive contains the ephemeris type known as the 'definitive ephemeris', which is based on an updated lunar gravity model [FDAB1997].

The sun pulse data set is a record of times that the Lunar Prospector sun sensor detects the Sun. These sun pulse times are derived from ground processing of the sun sensor data, earth-moon limb sensor data, and the spacecraft ephemeris. This data set is part of the Lunar Prospector Level 0 data archive. The sun pulse times are used in determining the spacecraft spin rate and orientation as a function of time. Because the Lunar Prospector spacecraft is sometimes in eclipse with the Sun, the sun pulse data set is generated on the ground to include both actual sun pulse times based on the sun sensor measurements and estimated sun pulse times based on the history of spin rate change during all prior eclipses.

The sun pulse data set is a record of times that the Lunar Prospector sun sensor detects the Sun. These sun pulse times are derived from ground processing of the sun sensor data, earth-moon limb sensor data, and the spacecraft ephemeris. This data set is part of the Lunar Prospector Level 0 data archive. The sun pulse times are used in determining the spacecraft spin rate and orientation as a function of time. Because the Lunar Prospector spacecraft is sometimes in eclipse with the Sun, the sun pulse data set is generated on the ground to include both actual sun pulse times based on the sun sensor measurements and estimated sun pulse times based on the history of spin rate change during all prior eclipses.

Line of Sight Acceleration Profile Data Records (LOSAPDR) consist of data from Doppler tracking of the orbiting spacecraft. The relative motion of the spacecraft and the earth-based radio receiver is measured very precisely, and known motions are removed a priori (i.e. earth rotation, planetary motions, spacecraft orbital motion, solar pressure, drag), leaving small velocity changes caused by variations in the mass distribution of the planet. The residual Doppler frequency shifts are linearly proportional to the component of velocity in the Earth direction. Numerical differentiation of these velocity residuals with respect to time produces line-of-sight (LOS) gravity. These measures are accelerations at spacecraft altitude which can be modeled for geophysical interpretation. For information on Lunar Prospector (LP) gravity investigations see [KONOPLIVETAL1998 CARRANZAETAL1999].

Line of Sight Acceleration Profile Data Records (LOSAPDR) consist of data from Doppler tracking of the orbiting spacecraft. The relative motion of the spacecraft and the earth-based radio receiver is measured very precisely, and known motions are removed a priori (i.e. earth rotation, planetary motions, spacecraft orbital motion, solar pressure, drag), leaving small velocity changes caused by variations in the mass distribution of the planet. The residual Doppler frequency shifts are linearly proportional to the component of velocity in the Earth direction. Numerical differentiation of these velocity residuals with respect to time produces line-of-sight (LOS) gravity. These measures are accelerations at spacecraft altitude which can be modeled for geophysical interpretation. For information on Lunar Prospector (LP) gravity investigations see [KONOPLIVETAL1998 CARRANZAETAL1999].

Trajectory data for the Lunar Prospector spacecraft in Selenographic, SSE, GSE, and GSM coordinates. Dataset covers dates 1998-01-16 to 1999-07-29.

This data set contains gridded data products from the Lunar Orbiter Laser Altimeter instrument [SMITHETAL2009].