An in-depth analysis and mechanical design of the solar array stowage and deployment arrangements for use in Small Applications Technology Satellite spacecraft is presented. Alternate approaches for the major elements of work are developed and evaluated. Elements include array stowage and deployment arrangements, the spacecraft and array behavior in the spacecraft despin mode, and the design of the main hinge and segment hinge assemblies. Feasibility calculations are performed and the preferred approach is identified.
Engineering design, stress and thermal analysis, and documentation for SATS program
1973-07-24
Report
No indication
English
Online Contents | 2015
|Online Contents | 2015
|SATS Link Independent Data Concepts
British Library Conference Proceedings | 2005
|Small Applications Technology Satellite (SATS)
NTRS | 1970