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Mission design for a halo orbiter of the earthThe International Sun-Earth Explorer (ISEE) scientific satellite to be stationed in 1978 in the vicinity of the sun-earth interior libration point to continuously monitor the space between the sun and the earth, including the distant geomagnetic tail is described. Orbit selection considerations for the ISEE-C are discussed along with stationkeeping requirements and fuel-optimal trajectories. Due to the alignment of the interior libration point with the sun as viewed from the earth, it will be necessary to place the satellite into a 'halo orbit' around the libration point, in order to eliminate solar interference with down-link telemetry. Parametric data for transfer trajectories between an earth parking orbit (altitude about 185 km) and a libration-point orbit are presented. It is shown that the insertion magnitude required for placing a satellite into an acceptable halo orbit is rather modest.
Document ID
19760060159
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Farquhar, R. W.
(Computer Sciences Corp. Silver Spring, MD, United States)
Muhonen, D. P.
(NASA Goddard Space Flight Center Greenbelt, Md., United States)
Richardson, D. L.
(Computer Sciences Corp. Silver Spring, Md., United States)
Date Acquired
August 8, 2013
Publication Date
August 1, 1976
Subject Category
Astronautics (General)
Report/Patent Number
AIAA PAPER 76-810
Meeting Information
Meeting: Astrodynamics Conference
Location: San Diego, CA
Start Date: August 18, 1976
End Date: August 20, 1976
Sponsors: American Institute of Aeronautics and Astronautics and American Astronautical Society
Accession Number
76A43125
Distribution Limits
Public
Copyright
Other

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