Patent ID: 6135393
Filing Date: 2000-10-24
Classification: B64G,F02K

Abstract:
An attitude and velocity control propulsion system for a space craft comprising:monopropellent thruster means, said monopropellant thruster means, including a fuel inlet, for producing thrust in response to fuel supplied at said fuel inlet;bipropellant secondary combustion augmented thruster means, said bipropellant secondary combustion augmented thruster means including a fuel inlet and an oxidizer inlet for producing a thrust responsive to both fuel supplied at said inlet and oxidizer supplied simultaneously at said oxidizer inlet and for producing a lesser thrust responsive to fuel supplied at said fuel inlet;fuel tank means for storing propellant fuel in liquid form;oxidizer tank means for storing propellant oxidizer in liquid form;first valve means for coupling said fuel from said fuel tank means to said monopropellent thruster means;second valve means for coupling fuel from said fuel tank means to said bipropellant secondary combustion augmented thruster means;third valve means for coupling oxidizer from said oxidizer tank means to said oxidizer inlet of said bipropellant secondary combustion augmented thruster means;controller means for selectively operating said second and third valve means, wherein said secondary combustion augmented thruster means produces a thrust to change the velocity of said space craft, and for selectively operating said first valve means, wherein said monopropellant thruster means produces a thrust to change the attitude of said space craft.