Title:
【発明の名称】ステープルセルロースファイバを先駆物質として形成されたロケットアッセンブリの削摩材、及びロケットアッセンブリをこれによって断熱する即ち熱的に保護する方法
Document Type and Number:
Japanese Patent JP2002523669
Kind Code:
A
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, 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.
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Inventors:
Wilson, Kenneth Pee
John Kaye, Sigourie
Alan Pee, Thompson
John Kaye, Sigourie
Alan Pee, Thompson
Application Number:
JP2000566565A
Publication Date:
July 30, 2002
Filing Date:
August 19, 1999
Export Citation:
Assignee:
Cordant Technologies, Inc.
International Classes:
C06B45/12; C08J5/04; C08J5/24; C08K3/04; C08K7/06; C08L61/06; B64G1/40; D01F9/16; F02K9/34; F02K9/97; (IPC1-7): F02K9/34; B64G1/40; C08J5/24; C08K3/04; C08K7/06; C08L61/06
Attorney, Agent or Firm:
Kazuo Shamoto (5 outside)