Insulation system for rocket motors

Details Insulation system for rocket motors Insulation system for rocket motors

B - Operations, Transporting

32

B

26/109, 60/39, 1

B32B 15/08 (2006.01) F02K 9/34 (2006.01)

Patent

CA 1060330

ABSTRACT OF THE DISCLOSURE The invention relates to an insulation system for use in rocket motors containing solid composite propellants. Some composite rocket propellants are based on carboxyl-terminated polybutadiene (CIPB) and others on hydroxyl-terminated polybutyadiene (HIPB) binders. An important requirement of such systems is the ability of the wall insulation to adhere to the combustion chamber and of the composite propellant to adequately adhere to the insulation system. With CIPB propellants, a sheet insulant comprising chrysotile asbestos fibres and floats dispersed in a CIPB polymeric binder has been successfully employed. However, the use of a similar sheet insulant based on HIPB polymeric binder has not proved to be compatible with HIPB propellants. The present invention provides a composite sheet insulation system which is compatible with HIPB propellants and which comprises a first layer of a sheet material comprising a CIPB binder having a mixture of asbestos fibres and floats dispersed therein and, bonded thereto, a second layer of aluminumfoil. The invention also comprises an economical and effective method of lining a rocket casing propellant chamber, using the novel system of the invention.

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