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Patched conic approximation
In astrodynamics, the patched conic approximation or patched two-body approximation〔Bate, R. R., D. D. Mueller, and J. E. White (), ''Fundamentals of Astrodynamics.'' Dover, New York.〕 is a method to simplify trajectory calculations for spacecraft in a multiple-body environment.
==Method==
The simplification is achieved by dividing space into various parts by assigning each of the ''n'' bodies (e.g. the Sun, planets, moons) its own sphere of influence. When the spacecraft is within the sphere of influence of a smaller body, only the gravitational force between the spacecraft and that smaller body is considered, otherwise the gravitational force between the spacecraft and the larger body is used. This reduces a complicated n-body problem to multiple two-body problems, for which the solutions are the well-known conic sections of the Kepler orbits.
Although this method gives a good approximation of trajectories for interplanetary spacecraft missions, there are missions for which this approximation does not provide sufficiently accurate results.〔Koon, W.S., Lo, M.W., Marsden, J.E., Ross, S.D. (2008) (''Dynamical Systems, the Three-Body Problem and Space Mission Design'' ). Marsden Books. pp 5. ISBN 978-0-615-24095-4.〕 Notably, it does not model Lagrangian points.
抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』
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