Design development of graphite primary structures enables SSTO success

Journal Article · Wed Jan 01 00:00:00 EST 1997 · AIP Conference Proceedings

DOI:https://doi.org/10.1063/1.51909· OSTI ID:627635

Biagiotti, V A; Yahiro, J S ^[1]; Suh, D E ^[1]; Hodges, E R; Prior, D J ^[1]

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1. Northrop Grumman 8900 E. Washington Blvd. Pico Rivera, California90660 (United States)

This paper describes the development of a graphite composite wing and a graphite composite intertank primary structure for application toward Single-Stage to Orbit space vehicles such as those under development in NASA{close_quote}s X-33/Reusable Launch Vehicle (RLV) Program. The trade study and designs are based on a Rockwell vertical take-off and horizontal landing (VTHL) wing-body RLV vehicle. Northrop Grumman{close_quote}s approach using a building block development technique is described. Composite Graphite/Bismaleimide (Gr/BMI) material characterization test results are presented. Unique intertank and wing composite subcomponent test article designs are described and test results to date are presented. Wing and intertank Full Scale Section Test Article (FSTA) objectives and designs are outlined. Trade studies, supporting building block testing, and FSTA demonstrations combine to develop graphite primary structure composite technology that enables developing X-33/RLV design programs to meet critical SSTO structural weight and operations performance criteria. {copyright} {ital 1997 American Institute of Physics.}

• Sponsoring Organization: USDOE
• OSTI ID: 627635
• Report Number(s): CONF-970115-; ISSN 0094-243X; TRN: 9808M0052
• Journal Information: AIP Conference Proceedings, Vol. 387, Issue 1; Conference: Space technology and applications international forum (STAIF - 97), Albuquerque, NM (United States), 26-30 Jan 1997; Other Information: PBD: Jan 1997
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING NOT INCLUDED IN OTHER CATEGORIES
SPACE VEHICLES
DESIGN
COMPOSITE MATERIALS
GRAPHITE
HEAT RESISTANT MATERIALS
CARGO
FINITE ELEMENT METHOD
NASA