| 摘要 |
An insulation system for use in rocket motors containing solid composite propellants is disclosed. Some composite rocket propellants are based on carboxyl-terminated polybutadiene (CTPB) and others on hydroxyl-terminated polybutadiene (HTPB) 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 CTPB propellants, a sheet insulant comprising chrysotile asbestos fibers and floats dispersed in a CTPB polymeric binder has been successfully employed. However, the use of a similar sheet insulant based on HTPB polymeric binder has not proved to be compatible with HTPB propellants. The present invention provides a composite sheet insulation system which is compatible with HTPB propellants including a first layer of sheet material comprising a CTPB binder having a mixture of asbestos fibers and floats dispersed in it and, bonded to it, a second layer of aluminum foil and an economical and effective method of lining a rocket casing propellant chamber, using the novel system of the present invention. |
| 申请人 |
HER MAJESTY THE QUEEN IN RIGHT OF CANADA AS REPRESENTED BY THE MINISTER OF NATIONAL DEFENCE, OTTAWA, CA |
发明人 |
RATTE, JACQUES;DUCHESNE, GONZAGUE, STE-FOY, QUEBEC, CA;CARIGNAN, PIERRE, CHARLESBOURG, QUEBEC, CA |
