公开(公告)号：EP1144835A2

公开(公告)日：2001-10-17

申请号：EP99963836.4

申请日：1999-08-19

申请人： Cordant Technologies, Inc.

发明人： WILSON, Kenneth, P. ,  SHIGLEY, John, K. ,  THOMPSON, Allan, P.

IPC分类号： F02K9/00

CPC分类号： F02K9/974 ,  C06B45/12 ,  C08J5/04 ,  D01F9/16 ,  F02K9/346 ,  F05D2300/42 ,  Y10T428/24612 ,  Y10T428/24661 ,  Y10T428/24669 ,  Y10T428/24678 ,  Y10T428/2913 ,  Y10T428/2918 ,  Y10T428/30 ,  Y10T442/2926 ,  Y10T442/2975 ,  Y10T442/2984 ,  Y10T442/2992

摘要： 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.

公开(公告)号：EP1105636A1

公开(公告)日：2001-06-13

申请号：EP99942262.9

申请日：1999-08-19

申请人： Cordant Technologies, Inc.

发明人： WILSON, Kenneth, P. ,  SHIGLEY, John, K. ,  THOMPSON, Allan, P.

IPC分类号： F02K9/34 ,  C08J5/04

CPC分类号： C08J5/04 ,  C06B45/12 ,  D01F9/16 ,  F02K9/346 ,  F02K9/974 ,  F05D2300/42 ,  Y10S428/92 ,  Y10T428/1314 ,  Y10T428/1362 ,  Y10T428/24992 ,  Y10T428/2843 ,  Y10T428/2924 ,  Y10T428/2982 ,  Y10T428/30 ,  Y10T442/56 ,  Y10T442/637

摘要： 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, carded and spun staple cellulosic fibers. 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.

公开(公告)号：EP1009623A1

公开(公告)日：2000-06-21

申请号：EP98926235.7

申请日：1998-06-04

申请人： Cordant Technologies, Inc.

发明人： THOMPSON, Allan, P. ,  SHIGLEY, John, K.

IPC分类号： B29C70/44

CPC分类号： B29C70/44 ,  B29K2105/04 ,  B29K2995/0017 ,  B29K2995/0063 ,  B29L2031/3097

摘要： A process for producing low density composite components involves forming a compacted and curable pre-preg into a selected configuration under a selected level of compaction whereby voids are capable of forming in the compacted curable pre-preg; curing the compacted curable pre-preg under a pressure less than about atmospheric pressure to obtain a cured product; and recovering the cured product. The pre-preg is only partially de-bulked in the process. Rocket nozzle components can be produced with reduced densities while still exhibiting satisfactory erosion and other characteristics desired for products subjected to the harsh erosive environment of a rocket motor.