Accession Number:

AD0260758

Title:

THEORY AND DESIGN CURVES FOR A YO-YO DE-SPIN MECHANISM FOR SATELLITES

Descriptive Note:

Technical note

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION GREENBELT MD GODDARD SPACE FLIGHT CENTER

Personal Author(s):

Report Date:

1961-08-01

Pagination or Media Count:

18.0

Abstract:

The yo-yo de-spin mechanism is essentially two pieces of wire with weights on the ends. These wires are symmetrically wrapped around the equator of the satellite and the weights are secured by a release mechanism. At a preselected time after satellite spin-up and separation from the launching vehicle, the weights are released, thus discarding enough momentum to reduce the spin of the satellite to the desired value. Equations are developed for the yo-yo de-spin mechanism. Under conditions usually met in a de-spin application, the equations can be greatly simplified. A computation sheet is presented based on the simplified equations. The design of a de-spin mechanism is thus reduced to reference to a chart and a few simple calculations.

Subject Categories:

  • Unmanned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE