Practical aspects of transfer from GTO to lunar orbit

Details Practical aspects of transfer from GTO to lunar orbit Practical aspects of transfer from GTO to lunar orbit

Feb 1993

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993fmet.symp..369u&link_type=abstract

In NASA. Goddard Space Flight Center, Flight Mechanics/Estimation Theory Symposium, 1992 p 369-380 (SEE N93-24694 09-13)

Physics

Error Analysis, Geosynchronous Orbits, Launch Windows, Lunar Orbits, Spacecraft Launching, Transfer Orbits, Apsides, Conics, Daytime

Scientific paper

This paper is a presentation of some practical aspects of orbital transfer from Geosynchronous Transfer Orbit (GTO) to close, near-circular orbits of the Moon. The intent is to identify the important parameters affecting the problem and to bound (approximately) the range of required delta V for a spacecraft that has been placed in GTO. The basic geometric relationships are described and the dynamics are simulated by use of the Zero-Sphere-of Influence Patched Conic method. It is found that the inclination of the transfer orbit to the Earth-Moon plane is relatively unimportant while the position of the line of apsides with respect to the Moon's orbit is the main geometric parameter of interest. It is shown that this parameter can be controlled by selecting the time of day for launch and that two launch windows of approximately 45 minutes duration are available each day of the year if use is made of the recommended phasing orbit transfer. The phasing orbit transfer not only provides twice-daily launch windows, but also provides a mechanism for efficacious correction of GTO injection errors. Delta V penalties for out-of-plane transfer and for late launch are evaluated and the method is recommended for use as an affordable means of achieving lunar orbit.

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