Pivotal Space, Inc.

United States of America

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New (last 4 weeks) 1
2024 3
IPC Class
F02K 9/97 - Rocket nozzles 3
F02K 9/44 - Feeding propellants 2
F02K 9/46 - Feeding propellants using pumps 2
F02K 9/56 - Control 2
F02K 9/64 - Combustion or thrust chambers having cooling arrangements 2
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Found results for  patents

1.

Boost injection turbine exhaust cycle (BITEC)

      
Application Number 18457312
Grant Number 12180914
Status In Force
Filing Date 2023-08-28
First Publication Date 2024-12-31
Grant Date 2024-12-31
Owner Pivotal Space, Inc. (USA)
Inventor
  • Droppers, Lloyd J
  • Luick, Landon

Abstract

A rocket propulsion system that may include a supersonic rocket nozzle with a supersonic divergent section, and a heat transfer system configured to transfer heat from the supersonic rocket nozzle to a propellant where a portion of the propellant may be selectively injected, combusted, and expanded in the supersonic nozzle generating an additional thrust. In examples, the heated propellant may be used to power a pump system to feed the rocket engine.

IPC Classes  ?

2.

Afterburning turbine exhaust cycle (ABTEC)

      
Application Number 18457301
Grant Number 11976614
Status In Force
Filing Date 2023-08-28
First Publication Date 2024-05-07
Grant Date 2024-05-07
Owner Pivotal Space, Inc. (USA)
Inventor Droppers, Lloyd J

Abstract

A rocket propulsion system that may include a supersonic rocket nozzle with a supersonic divergent section, and a heat transfer system configured to transfer heat from the supersonic rocket nozzle to a propellant where a portion of the propellant may be selectively injected, combusted, and expanded in the supersonic nozzle generating an additional thrust. In examples, the heated propellant may be used to power a pump system to feed the rocket engine.

IPC Classes  ?

  • 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 9/44 - Feeding propellants
  • F02K 9/46 - Feeding propellants using pumps
  • F02K 9/56 - Control
  • F02K 9/64 - Combustion or thrust chambers having cooling arrangements
  • F02K 9/97 - Rocket nozzles

3.

Dual mode rocket engine with bipropellant injection in the nozzle

      
Application Number 18457283
Grant Number 11976613
Status In Force
Filing Date 2023-08-28
First Publication Date 2024-05-07
Grant Date 2024-05-07
Owner Pivotal Space, Inc. (USA)
Inventor Droppers, Lloyd J.

Abstract

A rocket propulsion system that may include a supersonic rocket nozzle with a supersonic divergent section, and a heat transfer system configured to transfer heat from the supersonic rocket nozzle to a propellant where a portion of the propellant may be selectively injected, combusted, and expanded in the supersonic nozzle generating an additional thrust. In examples, the heated propellant may be used to power a pump system to feed the rocket engine.

IPC Classes  ?

  • 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 9/44 - Feeding propellants
  • F02K 9/56 - Control
  • F02K 9/80 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by thrust or thrust vector control
  • F02K 9/64 - Combustion or thrust chambers having cooling arrangements
  • F02K 9/97 - Rocket nozzles