Accession Number : AD0707327

Title :   DEPLOYMENT OF A TETHERED ORBITING INTERFEROMETER.

Descriptive Note : Technical memo.,

Corporate Author : JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB

Personal Author(s) : Swet,C. J. ; Whisnant,J. M.

Report Date : AUG 1969

Pagination or Media Count : 34

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)

Descriptors :   (*SCIENTIFIC SATELLITES, RADIO INTERFEROMETERS), (*RADIO INTERFEROMETERS, DEPLOYMENT), NUMERICAL ANALYSIS, EQUATIONS OF MOTION, GRAVITY, SPINNING(MOTION), DIPOLE ANTENNAS, DAMPING, SPIN STABILIZATION

Subject Categories : Unmanned Spacecraft
      Spacecraft Trajectories and Reentry

Distribution Statement : APPROVED FOR PUBLIC RELEASE