DEPLOYMENT OF A TETHERED ORBITING INTERFEROMETER.
Abstract
Among the candidate configurations for future Radio Astronomy Explorer satellites is a tethered orbiting interferometer, consisting of two end bodies joined by a flexible lightweight cable several kilometers long. One version has a 15-meter dipole antenna on each end body, mounted colinearly with the tether, the entire structure being gravitationally stabilized with its long axis geocentrically aligned. The system is Delta-launched into earth orbit as a single payload. A particularly simple two-stage method of in-orbit deployment is described. The first stage is an impulsive separation of the initially joined end bodies to a predetermined tether length, resulting in librating gravitational capture. The second stage removes libration by a further 3deadbeat3 extension to the intended final length. Some limits of utility are defined parametrically using a point mass dynamical simulation; engineering and operational aspects are discussed; and possible refinements and adaptations of the concept to other missions are explored. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1969
- Accession Number
- AD0707327
Entities
People
- C. J. Swet
- J. M. Whisnant
Organizations
- Johns Hopkins University Applied Physics Laboratory