Title:
ROCKET ASSEMBLY ABLATIVE MATERIALS FORMED FROM SOLVENT-SPUN CELLULOSIC PRECURSORS, AND METHOD OF INSULATING OR THERMALLY PROTECTING A ROCKET ASSEMBLY WITH THE SAME
Document Type and Number:
WIPO Patent Application WO2000014397
Kind Code:
A3
Abstract:
A rocket motor assembly is insulated or thermally protected with a rocket motor ablative material formed from a prepreg. The prepreg contains at least an impregnating resin matrix and, as a precursor prior to carbonization, either carded and yarn-spun solvent-spun staple cellulosic fibers, solvent-spun cellulosic filaments, or a combination thereof. When patterned and carbonized, the rocket motor ablative material can be lined or otherwise placed into a rocket motor assembly, such as between the solid propellant and case, in the bulk area of the exit nozzle liner, or at susceptible portions of a re-entry vehicle, such as the nose cone.
Inventors:
WILSON KENNETH P (US)
SHIGLEY JOHN K (US)
THOMPSON ALLAN P (US)
SHIGLEY JOHN K (US)
THOMPSON ALLAN P (US)
Application Number:
PCT/US1999/018722
Publication Date:
October 17, 2002
Filing Date:
August 19, 1999
Export Citation:
Assignee:
CORDANT TECH INC (US)
WILSON KENNETH P (US)
SHIGLEY JOHN K (US)
THOMPSON ALLAN P (US)
WILSON KENNETH P (US)
SHIGLEY JOHN K (US)
THOMPSON ALLAN P (US)
International Classes:
C06B45/12; C08J5/04; D01F9/16; F02K9/34; F02K9/97; (IPC1-7): F02K9/34; C08J5/04
Foreign References:
| DE2722575A1 | 1977-12-22 | |||
| US4663065A | 1987-05-05 | |||
| GB2295396A | 1996-05-29 | |||
| US4956397A | 1990-09-11 |
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