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Proceedings Paper

Solution to the problem of determining the relative 6 DOF state for spacecraft automated rendezvous and docking
Author(s): Phillip C. Calhoun; Richard Dabney
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Paper Abstract

The automated rendezvous and docking of spacecraft requires knowledge of the relative 6 degrees of freedom (6 DOF) between the chase and target spacecraft. A sensor system for estimation of the 6 DOF state is being developed at the Marshall Space Flight Center for the Automated Rendezvous and Capture Project. This sensor employs the use of a charge coupled device camera mounted on the chase spacecraft to image a reflective target located on the target spacecraft. The target is illuminated using an array of laser diodes and the resulting camera image is processed to produce an estimate of the relative 6 DOF state. This paper will contain a brief description of the sensor system, known as the Video Guidance Sensor, and will describe the algorithms necessary to determine the 6 DOF state from the camera image. The solution begins by determining the range to each target reflector. This information is used to determine spacecraft position and to derive vectors used for attitude determination. Two methods of attitude determination using vector measurements are described for a 3 spot and 5 spot target.

Paper Details

Date Published: 12 June 1995
PDF: 10 pages
Proc. SPIE 2466, Space Guidance, Control, and Tracking II, (12 June 1995); doi: 10.1117/12.211505
Show Author Affiliations
Phillip C. Calhoun, NASA Marshall Space Flight Ctr. (United States)
Richard Dabney, NASA Marshall Space Flight Ctr. (United States)

Published in SPIE Proceedings Vol. 2466:
Space Guidance, Control, and Tracking II
Walter J. Fowski; Morris M. Birnbaum, Editor(s)

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