Accession Number : ADA302718

Title :   Graphite/LARC-160 Technology Demonstration Segment Test Results.

Descriptive Note : Contract rept.,

Corporate Author : ROCKWELL INTERNATIONAL DOWNEY CA

Personal Author(s) : Morita, W. H. ; Graves, S. R.

PDF Url : ADA302718

Report Date : JUN 1983

Pagination or Media Count : 119

Abstract : Early Shuttle orbiter studies identified several structural items for which application of advanced composites could save significant orbiter weight. Several of these structural components were part of the baseline design, including the graphite/epoxy payload bay doors and the boron/epoxy-reinforced titanium main engine thrust structure. Other components, such as the body flap, elevons, and vertical tail, were identified for advanced high-temperature graphite/polyimide (Gr/PI) composite application. A complex Gr/PI technology demonstration segment (TDS) was designed, fabricated, and tested to confirm the structural performance of Celion/LARC-160 Gr/PI. The test results reported herein verified this advanced structure concept. (MM)

Descriptors :   *SPACE SHUTTLES, *GRAPHITE EPOXY COMPOSITES, MANUFACTURING, TAIL ASSEMBLIES, COMPOSITE MATERIALS, HIGH TEMPERATURE, DEFLECTION, GRAPHITE, STRAIN(MECHANICS), FLAPS(CONTROL SURFACES), FATIGUE(MECHANICS), TITANIUM, BORON, THERMAL STRESSES, ELEVONS, STRUCTURAL COMPONENTS, CYCLIC LOADS, HONEYCOMB STRUCTURES, POLYIMIDE PLASTICS, POLYIMIDE RESINS.

Subject Categories : Laminates and Composite Materials
      Manned Spacecraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE