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Rapid Design of Gravity Assist TrajectoriesSeveral International Solar Terrestrial Physics (ISTP) missions require the design of complex gravity assisted trajectories in order to investigate the interaction of the solar wind with the Earth's magnetic field. These trajectories present a formidable trajectory design and optimization problem. The philosophy and methodology that enable an analyst to design and analyse such trajectories are discussed. The so called 'floating end point' targeting, which allows the inherently nonlinear multiple body problem to be solved with simple linear techniques, is described. The combination of floating end point targeting with analytic approximations with a Newton method targeter to achieve trajectory design goals quickly, even for the very sensitive double lunar swingby trajectories used by the ISTP missions, is demonstrated. A multiconic orbit integration scheme allows fast and accurate orbit propagation. A prototype software tool, Swingby, built for trajectory design and launch window analysis, is described.
Document ID
19920015535
Document Type
Conference Paper
Authors
Carrico, J.
(Computer Sciences Corp. Arlington, VA., United States)
Hooper, H. L.
(Computer Sciences Corp. Arlington, VA., United States)
Roszman, L.
(Computer Sciences Corp. Lanham, MD., United States)
Gramling, C.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1991
Publication Information
Publication: ESA, Spacecraft Flight Dynamics
Subject Category
Astronautics (General)
Funding Number(s)
CONTRACT_GRANT: NAS5-31500
Distribution Limits
Public
Copyright
Public Use Permitted.

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NameType 19920015535.pdf STI