Process for Case Bonding Cast Composite Propellant Grains
It is an object of the present invention to provide a method for case bonding a propellant grain directly into a rocket motor tube using a double liner system which will withstand temperature cycling and mechanical vibration and so that they can be reliably fired at temperatures as low as -20F. The objects are accomplished by first coating the inside of a rocket motor chamber or casing with a thermosetting polyurethane composition and then applying a silicone tape to this polyurethane surface. The motor casing is now ready for casting a composite propellant mixture.It is an object of the present invention to provide a method for case bonding a propellant grain directly into a rocket motor tube using a double liner system which will withstand temperature cycling and mechanical vibration and so that ...
| Title | : | Process for Case Bonding Cast Composite Propellant Grains |
| Author | : | Henry T. Sampson, DEPARTMENT OF THE NAVY WASHINGTON D C. |
| Publisher | : | - 1973 |
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