发明名称 |
ROCKET ASSEMBLY ABLATIVE MATERIALS FORMED FROM SOLVENT-SPUN CELLULOSIC PRECURSORS, AND METHOD OF INSULATING OR THERMALLY PROTECTING A ROCKET ASSEMBLY WITH THE SAME |
摘要 |
<p>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.</p> |
申请公布号 |
EP1144835(A2) |
申请公布日期 |
2001.10.17 |
申请号 |
EP19990963836 |
申请日期 |
1999.08.19 |
申请人 |
CORDANT TECHNOLOGIES, INC. |
发明人 |
WILSON, KENNETH, P.;SHIGLEY, JOHN, K.;THOMPSON, ALLAN, P. |
分类号 |
C06B45/12;C08J5/04;D01F9/16;F02K9/34;F02K9/97;(IPC1-7):F02K9/00 |
主分类号 |
C06B45/12 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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