Concentric layer ramjet fuel
AssigneeThe United States of America as represented by the Secretary of the Navy
InventorsGeorge W. Burdette, John P. Francis
Life of this patent
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Abstract
An air-breathing solid fuel rocket motor containing a solid fuel ramjet gn having a plurality of concentric layers of solid fuel which provide a means of controlling the thrust of the motor.
Claims5
A solid fuel ramjet grain comprising a plurality of concentric layers of solid ramjet fuel having a perforation therethrough along the center axis of said grain, said perforation connected to a combustion after-chamber, said solid ramjet fuel layers comprising a pure hydroxyl-terminated polybutadiene hydrocarbon fuel or a mixture of a hydroxyl-terminated polybutadiene hydrocarbon fuel and from about 5 to about 60 percent by weight of an additive to increase the fuel regression rate selected from the group consisting of magnesium, boron carbide, aluminum, and zirconium such that, when burned in the operation of the ramjet, each said fuel layer produces a different level of thrust.
A device for controlling the thrust of a solid fuel ramjet comprising a solid fuel ramjet grain having a plurality of concentric layers of solid ramjet fuel with a perforation therethrough along the center axis of said grain, said solid ramjet fuel layers each consisting essentially of a mixture of a polymeric binder and a fuel so that each concentric layer of fuel has a different rate of regression (RDOT) such that the burn-off of each layer of solid ramjet produces a different thrust than the previous layer.
A method for controlling the thrust of a solid fuel ramjet, said solid fuel ramjet comprising a plurality of concentric layers of solid ramjet fuel having a perforation therethrough along the center axis of said grain, said perforation connected to a combustion after chamber, said solid ramjet fuel layers consisting essentially of a mixture of a polymeric binder and fuel particles, and said grain has a cross section which defines a geometric shape designed for the efficient burn-off of the solid ramjet fuel to produce thrust, said method comprising:
- a. igniting and partially combusting the outermost layer of solid fuel having a particular rate of regression (R DOT), burning at the surface of said fuel layer and in said combustion chamber to produce thrust until the adjacent layer of solid fuel is exposed;
- b. partially combusting the adjacent layer of solid fuel having a different rate of regression (R DOT), burning at the surface of said fuel layer and in said combustion afterchamber to produce thrust;
- and
- c. repeating steps (a) and (b) until the remaining solid fuel layers have been consumed.
Dependencies are inferred from the claim text.