Structural design concepts for a multi-megawatt Solar Electric Propulsion (SEP) spacecraft

Technical Report · Thu Aug 01 04:00:00 EDT 1991

OSTI ID:5138894

Lawrence, C; Hickman, J M

As a part of the Space Exploratory Initiative (SEI), NASA-Lewis is studying Solar Electric Propulsion (SEP) spacecraft to be used as a cargo transport vehicle to Mars. Two preliminary structural design concepts are offered for SEP spacecraft: a split blanket array configuration, and a ring structure. The split blanket configuration is an expansion of the photovoltaic solar array design proposed for Space Station Freedom and consists of eight independent solar blankets stretched and supported from a central mast. The ring structural concept is a circular design with the solar blanket stretched inside a ring. This concept uses a central mast with guy wires to provide additional support to the ring. The two design concepts are presented, then compared by performing stability, normal modes, and forced response analyses for varying levels of blanket and guy wire preloads. The ring structure configuration is shown to be advantageous because it is much stiffer, more stable, and deflects less under loading than the split blanket concept.

• Research Organization: National Aeronautics and Space Administration, Cleveland, OH (United States). Lewis Research Center
• OSTI ID: 5138894
• Report Number(s): N-91-30565; NASA-TM--105148; NAS--1.15:105148
• Country of Publication: United States
• Language: English

Related Subjects

14 SOLAR ENERGY
140600* -- Solar Energy-- Photovoltaic Power Systems
COMPARATIVE EVALUATIONS
DESIGN
EQUIPMENT
EVALUATION
PERFORMANCE TESTING
PROPULSION
SOLAR CELL ARRAYS
SOLAR ELECTRIC PROPULSION
SOLAR EQUIPMENT
SPACE VEHICLES
STABILITY
TESTING
VEHICLES