Abstract

A hybrid rocket engine system has: an oxidizer tank containing a liquid oxidizer; a rocket engine having a combustion chamber operatively connected to the oxidizer tank; a solid propellant fuel within the combustion chamber; a nozzle fluidly connected to the combustion chamber, the nozzle having a convergent section and a divergent section downstream of the convergent section; and a thrust vector control device operatively connected to the divergent section of the nozzle and operable to inject a fluid through at least one aperture defined through the divergent section for controlling a direction of a thrust generated by the rocket engine.

IPC Classes  ?

• F02K 9/72 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
• B64G 1/40 - Arrangements or adaptations of propulsion systems
• F02K 9/10 - Shape or structure of solid propellant charges
• F02K 9/28 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle
• F02K 9/52 - Injectors
• F02K 9/62 - Combustion or thrust chambers
• F02K 9/82 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by thrust or thrust vector control by injection of a secondary fluid into the rocket exhaust gases
• F02K 9/97 - Rocket nozzles

Abstract

A rocket engine has: a combustion chamber having a chamber inlet for receiving an oxidizer and a chamber outlet for expelling combustion gases in an environment outside the combustion chamber; a manifold having a manifold inlet fluidly connectable to a source of the oxidizer and a manifold outlet; a catalyst having a catalyst inlet fluidly connected to the manifold outlet and a catalyst outlet; and an injector plate having a injector inlet fluidly connected to the catalyst outlet and an injector outlet fluidly connected to the chamber inlet.

IPC Classes  ?

• F02K 9/72 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
• B64G 1/40 - Arrangements or adaptations of propulsion systems
• F02K 9/10 - Shape or structure of solid propellant charges
• F02K 9/28 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle
• F02K 9/52 - Injectors
• F02K 9/62 - Combustion or thrust chambers
• F02K 9/82 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by thrust or thrust vector control by injection of a secondary fluid into the rocket exhaust gases
• F02K 9/97 - Rocket nozzles

Abstract

A rocket engine has a combustion chamber having an inlet and an outlet, the inlet fluidly connectable to a source of oxidizer, the outlet in fluid communication with an environment outside the combustion chamber for expelling combustion gases, a first fuel having a first solid propellant and a second fuel having a second solid propellant, the first and second fuels located within the combustion chamber and configured to be exposed to the oxidizer injected in the combustion chamber via the inlet, the first solid propellant having a regression rate greater than that of the second solid propellant. A hybrid rocket engine with a thrust vector control device is disclosed. A rocket engine with an integrated catalyst in manifold is disclosed.

IPC Classes  ?

• F02K 9/08 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using solid propellants
• F02K 9/28 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle
• F02K 9/32 - Constructional partsDetails not otherwise provided for

Abstract

A rocket engine has a combustion chamber having an inlet and an outlet, the inlet fluidly connectable to a source of oxidizer, the outlet in fluid communication with an environment outside the combustion chamber for expelling combustion gases, a first fuel having a first solid propellant and a second fuel having a second solid propellant, the first and second fuels located within the combustion chamber and configured to be exposed to the oxidizer injected in the combustion chamber via the inlet, the first solid propellant having a regression rate greater than that of the second solid propellant. A hybrid rocket engine with a thrust vector control device is disclosed. A rocket engine with an integrated catalyst in manifold is disclosed.

IPC Classes  ?

• F02K 9/28 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle
• F02K 9/08 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using solid propellants
• F02K 9/32 - Constructional partsDetails not otherwise provided for

Abstract

A rocket engine has a combustion chamber having an inlet and an outlet, the inlet fluidly connectable to a source of oxidizer, the outlet in fluid communication with an environment outside the combustion chamber for expelling combustion gases, a first fuel having a first solid propellant and a second fuel having a second solid propellant, the first and second fuels located within the combustion chamber and configured to be exposed to the oxidizer injected in the combustion chamber via the inlet, the first solid propellant having a regression rate greater than that of the second solid propellant.

IPC Classes  ?

• F02K 9/28 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle
• B64G 1/40 - Arrangements or adaptations of propulsion systems
• F02K 9/10 - Shape or structure of solid propellant charges
• F02K 9/52 - Injectors
• F02K 9/62 - Combustion or thrust chambers
• F02K 9/72 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
• F02K 9/82 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by thrust or thrust vector control by injection of a secondary fluid into the rocket exhaust gases
• F02K 9/97 - Rocket nozzles

Abstract

A hybrid rocket engine system has: an oxidizer tank containing a liquid oxidizer; a rocket engine having a combustion chamber operatively connected to the oxidizer tank; a solid propellant fuel within the combustion chamber; a nozzle fluidly connected to the combustion chamber, the nozzle having a convergent section and a divergent section downstream of the convergent section; and a thrust vector control device operatively connected to the divergent section of the nozzle and operable to inject a fluid through at least one aperture defined through the divergent section for controlling a direction of a thrust generated by the rocket engine.

IPC Classes  ?

• F02K 9/72 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
• B64G 1/40 - Arrangements or adaptations of propulsion systems
• F02K 9/10 - Shape or structure of solid propellant charges
• F02K 9/28 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle
• F02K 9/52 - Injectors
• F02K 9/62 - Combustion or thrust chambers
• F02K 9/82 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by thrust or thrust vector control by injection of a secondary fluid into the rocket exhaust gases
• F02K 9/97 - Rocket nozzles