DAF/SPK LRO_IGG_SM_10_10.5d_DT_130218.BSP aS LTL-IEEE FTPSTR: : : : :::ENDFTP Lunar Reconnaissance Orbiter SPK file, University of Bonn ************************************************************************************** Author: Anno Loecher Institute of Geodesy and Geoinformation Nussallee 17 D-53115 Bonn Production date: 21 August 2017 Content and usage -------------------------------------------------------------------------------------- This file contains orbit data for the Lunar Reconnaissance Orbiter (LRO) for use with the Spice software system (https://naif.jpl.nasa.gov/naif/). The Spice ID for LRO is -85. This orbit should be used together with the lunar ephemeris from DE421. Time coverage -------------------------------------------------------------------------------------- The LRO orbit in this file covers the following intervals: Start of interval (UTC) End of interval (UTC) ----------------------- --------------------- 20 May 2011 19:55:13 02 Jun 2011 17:34:03 02 Jun 2011 17:58:40 13 Jun 2011 23:44:59 Short description -------------------------------------------------------------------------------------- The orbit contained in this file was produced from Doppler and range data from the LRO ground network retrieved from the Planetary Data System (http://pds-geosciences. wustl.edu/). The orbit determination was performed using an independent software which applies the variational equations approach. The dynamical modelling is based on the GRAIL gravity field model GL0900D truncated at degree 400. The solar radiation pressure was modelled using a spacecraft 3-D model accounting for the effects of self-shadowing and a model for the lunar albedo force. The parameter set estimated for each arc included a scale factor for solar radiation and a piecewise linear acceleration in along-track direction. For the details of data processing see the publication in the "Reference" section. F or the orbit computation, the data were processed in overlapping arcs with a nominal length of 10.5 days. The orbit in this file is assembled from several such arcs with linear transitions in the overlap periods. The state vectors from the orbit integration were converted to the SPK data type 9 (Lagrange interpolation, unequal time steps, polynomial degree 9). Reference -------------------------------------------------------------------------------------- When using this orbit please cite: A Loecher, J Kusche (2017): Precise orbits of the Lunar Reconnaissance Orbiter from radiometric tracking data. Submitted to Journal of Geodesy Acknowledgement -------------------------------------------------------------------------------------- The orbits in this directory were computed at the University of Bonn in the framework of the research unit FOR 1503 "Space-Time Reference Systems for Monitoring Global Change and for Precise Navigation in Space" funded by th e German Research Foundation (DFG). 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