Dual manifold high performance throttleable injector

Claim 1

An injector for uniformly distributing propellant within the combustion chamber of a rocket engine comprising at least four platelets, each of said platelets having planar surfaces and edge surfaces, one of said planar surfaces of each of said platelets containing a plurality of flow passages therein, said flow passages terminating at said edge surface in an opening in said edge surface, said platelets being joined together in a stack to form a unitary structure, the first of said platelets having means therein adapted to receive a predetermined quantity of fuel, the second of said platelets having means therein adapted to receive less than said predetermined quantity of fuel, the third of said platelets having means therein adapted to receive a predetermined quantity of oxidizer, the fourth of said platelets adapted to receive less than said predetermined quantity of oxidizer, each of said first and second platelets having means therein for operatively connecting said fuel receiving means to said flow passages, each of said third and fourth platelets having means therein for operatively connecting said oxidizer receiving means to said flow passages and each of said platelets having flow restrictors therein operatively connected to said flow passages for metering flow of propellant to each of said edge surface openings thereby providing homogeneous, intimately mixed propellants at all thrust levels.