Hybrid rocket engine

• US 3,178,885 A
• Filed: 06/12/1961
• Issued: 04/20/1965
• Est. Priority Date: 06/12/1961
• Status: Expired due to Term

• Current Assignee: Robert H. Loughran
• Original Assignee: Robert H. Loughran
• Inventors: Loughran, Robert H.
• Application Number:
  US04/116,416
• Time in Patent Office: 1,408 Days
• US Class Current: 60/251
• CPC Class Codes: F02K 9/72 using liquid and solid propellants, i.e. hybrid rocket-engine plants

Claims

1. A HYBRID ROCKET ENGINE UTILIZING A FUEL COMPONENT AND AN OXIDIZER COMPONENT, ONE OF SAID COMPONENTS BEING SOLID AND THE OTHER BEING LIQUID, SAID ENGINE COMPRISING A MOTOR CASE LOADED WITH SAID SOLID COMPONENT AND HAVING A REARWARDLY DIRECTED NOZZLE THROUGH WHICH COMBUSTION PRODUCTS ARE DISCHARGED, A CONTAINER IN WHICH SAID LIQUID COMPONENT IS CONTAINED, AN AUXILIARY GAS GENERATOR MOUNTED ON THE FRONT END OF THE MOTOR CASE AND HAVING A NOZZLE DISCHARGING INTO SAID MOTOR CASE, MEANS FOR PRESSURIZING SAID CONTAINER WITH GAS GENERATED BY SAID AUXILIARY GAS GENERATOR, MEANS FOR CONVEYING SAID LIQUID COMPONENT UNDER PRESSURE FROM SAID CONTAINER TO SAID LASTNAMED NOZZLE AND MEANS INCLUDING SAID LAST-NAMED NOZZLE FOR MIXING SAID LIQUID COMPONENT WITH THE HOT COMBUSTION GASES DISCHARGED BY SAID AUXILIARY GAS GENERATOR, WHEREBY THE SAID LIQUID COMPONENT IS VAPORIZED AS IT IS DISCHARGING INTO SAID MOTOR CASE FOR REACTION WITH SAID SOLID COMPONENT.