Honeycomb rocket propellant grain

Claim 1

IN COMBINATION WITH A COMBUSTION CHAMBER OF A ROCKET, A HIGH IMPULSE SOLID PROPELLANT GRAIN COMPRISING A MULTI-CELLULAR HONEYCOMB FUEL COMPONENT FORMED OF RELATIVELY THIN MIL GAUGE COMBUSTIBLE METAL FOIL HAVING BOTH SUBSTANTIALLY GREATER STRUCTURAL STRENGTH THAN, AND A SUBSTANTIALLY HIGHER RATE OF HEAT CONDUCTIVITY THAN, THE AMORPHOUS MASS OF PROPELLANT AGENT HEREINAFTER SPECIFIED; SAID HONEYCOMB FUEL COMPONENT DEFINING A PLURALITY OF SUBSTANTIALLY UNIDIRECTIONALLY EXTENDING GEOMETRIC CELL OPENINGS; A SUBSTANTIALLY SOLID AMORPHOUS MASS OF FUEL AND OXIDANT PROPELLANT AGENT FILLING SAID CELL OPENINGS; SAID PROPELLANT MASS IN EACH CELL OPENING BEING IN SUFFICIENTLY INTIMATE CONTACT WITH THE SURROUNDING WALLS OF SAID CELL TO PREVENT FLAME PROPAGATION DOWN THE INTERFACE BETWEEN THE PROPELLANT AND CELL WALLS; SAID PROPELLANT MASS INCLUDING OXIDIZER SUFFICIENT TO REACT WITH BOTH THE FUEL CONTAINED IN THE MASS AND THE COMBUSTIBLE METAL FOIL HONEYCOMB FUEL COMPONENTS.