Design development of graphite primary structures enables SSTO success

Journal Article · Tue Dec 31 23:00:00 EST 1996 · 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--
• Journal Information: AIP Conference Proceedings, Journal Name: AIP Conference Proceedings Journal Issue: 1 Vol. 387; ISSN APCPCS; ISSN 0094-243X
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
CARGO
COMPOSITE MATERIALS
DESIGN
FINITE ELEMENT METHOD
GRAPHITE
HEAT RESISTANT MATERIALS
NASA
SPACE VEHICLES