PRE-PHASE I FOR DESIGN, FABRICATION, AND ORBITAL TESTING OF A SPACE STRUCTURE.
Abstract
This report summarizes the preliminary design and analysis performed by GAC on a large expandable toroidal space structure for orbital testing. The program established preliminary designs, supported by analysis, of two fractional torus concepts, a 138-ft diam elastic recovery materials configuration and a 118-ft diam expandable honeycomb materials configuration. The fractional torus designs comprise 3 identical symmetrically located 8.5-ft diam modules connected together by 3 symmetrically located 4.5-ft diam access tunnels. The torus modules are connected by 5.5-ft diam spokes to a 10-ft diam cylindrical central hub of aluminum honeycomb sandwich construction, which has its 20-ft length perpendicular to the plane of the torus. The expandable components (spokes, modules, and access tunnels) are attached to each other and to the rigid hub with aluminum termination assemblies that provide dual aluminum hatches to compartmentize the structure in the event of depressurization of any component. There is a 7-ft long, 4-ft diam, expandable personnel air lock for EVA at one end of the hub and a docking cone for the Apollo CSM at the other end. The design inflation pressure is 7.5 psia. The structures are designed to maintain attitude control in a 300-nmi circular orbit for one year while spinning about the hub axis at about 3.8 rpm to maintain an artificial gravity level on the module floor of 0.33 g for the 138-ft torus and 0.29 g for the 118-ft torus. With a 60-day resupply cycle for expendables, the structures have sufficient volume to support a 10-man crew in the 138-ft torus and a 6-man crew in the 118-ft torus.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1967
- Accession Number
- AD0815716
Entities
People
- Thomas L. Hoffman
Organizations
- Goodyear Aerospace