Variable thrust reaction motor with multiple sets injector orifices

Claim 1

A variable thrust fluid propellant rocket motor comprising: a. a source of a fluid fuel, b. a source of a fluid oxidizer, c. a combustion chamber provided with thrust producing nozzle means at the aft end, d. an injector in the forward end of said combustion chamber, said injector being provided with a multiplicity of sets of injector orifices, each set comprising first, second, third and fourth fixed area injector orifices on the face thereof which is exposed to said combustion chamber, said first, second, third and fourth fixed area injector orifices of each said set being directed to cause impingement, at a common point, of fluid emitted from each said orifice, which said point is unique for each said set, e. at least first and second oxidizer supply lines in fluid communicating relationship with said source of oxidizer and said injector, f. at least first and second fuel supply lines in fluid communicating relationship with said source of fuel and said injector, g. variable flow control means associated with each of said fuel and oxidizer supply lines for adjusting the fluid flow in each of said lines independently to any level between full on and full off inclusive, and h. first, second, third and fourth fluid distributing means in said injector providing fluid communication between said first oxidizer supply line and said first injector orifice, said first fuel supply line and said second injector orifice, said second oxidizer supply line and said third injector orifice, and said second fuel supply line and said fourth injector orifice respectively; whereby operation of said rocket motor at varying thrust levels up to a first predetermined maximum may be obtained by flowing fluid only through said first fuel and oxidizer supply lines and operation at varying thrust levels up to a second predetermined maximum may be obtained by flowing fluid through said second fuel and oxidizer supply lines while fluid is flowing through said first fuel and oxidizer supply lines.