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Perturbed Equations of Motion for Formation Flight Near the Sun-Earth L2 PointThis Memorandum Report consists of a compilation of three individual reports, of increasing complexity, describing investigations of formation flight of spacecraft in the vicinity of the L2 Sun-Earth 1ibration point. The individual reports form the following parts of this compilation: - Introduction to the relative motion of spacecraft about the Sun-Earth L2 Point - Linear and quadratic modelling and solution of the relative motion - Modelling the Perturbations - Elliptical Earth Orbit, Lunar Gravity, Solar Radiation Pressure, Thrusters. The three parts are self-contained, with somewhat, varying notation and terminology. After fair1y significant literature searches: this new work (of Parts 2 and 3) is deemed to be unique because it describes the primary perturbations to the description of relative motion between nearby spacecraft. The effect of the elliptical motion of the Earth about the Sun was verified to be the dominant perturbation to the circular restricted three body problem. Contributions due to lunar gravity and solar radiation pressure are seen to have much smaller effect.
Document ID
20050212415
Acquisition Source
Goddard Space Flight Center
Document Type
Preprint (Draft being sent to journal)
Authors
Segerman, Alan M.
(AT and T Government Solutions United States)
Zedd, Michael F.
(Naval Research Lab. United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2005
Subject Category
Astrodynamics
Meeting Information
Meeting: 2005 AAS/AIAA Astrodynamics Specialist Conference
Location: Lake Tahoe, CA
Country: United States
Start Date: August 7, 2005
End Date: August 11, 2005
Sponsors: American Astronomical Society, American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NNG04CB01I
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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