NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Material capture by double lunar gravity assistThe equations yielding the performance of a single lunar flyby in removing incoming hyperbolic excess velocity to capture payloads on interplanetary trajectories are briefly derived. The impossibility of using a single lunar flyby to capture a body entering the earth-moon system with a hyperbolic velocity in excess of about 1.9 km/s is discussed, and a method of using a double flyby of the moon to significantly improve this performance is developed. The equations for achieving a double lunar flyby are derived by solving the orbital equations and Lambert's problem both for the incoming trajectory in the plane of the moon's orbit and for arbitrary declination. For the in-plane case it is shown that the maximum removable hyperbolic excess velocity is 2.2687 km/s. For the inclined case, it is shown that the use of a double lunar flyby allows capture for declinations in excess of 54 degrees, and that for declinations less than 38 degrees the double lunar flyby offers better performance than the single lunar flyby.
Document ID
19800062349
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ross, D. J.
(California Institute of Technology, Jet Propulsion Laboratory, Mission Design Section, Pasadena Calif., United States)
Date Acquired
August 10, 2013
Publication Date
August 1, 1980
Subject Category
Astrodynamics
Report/Patent Number
AIAA PAPER 80-1673
Meeting Information
Meeting: Astrodynamics Conference
Location: Danvers, MA
Start Date: August 11, 1980
End Date: August 13, 1980
Sponsors: American Institute of Aeronautics and Astronautics and American Astronautical Society
Accession Number
80A46519
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available