公开(公告)号：US12196158B2

公开(公告)日：2025-01-14

申请号：US18497442

申请日：2023-10-30

Applicant: PHASE FOUR, INC.

Inventor： Jesse Sidhu ,  Mohammed Umair Siddiqui ,  Derek Thompson ,  Jason Jackson Wallace

IPC: F02K9/44 ,  B64G1/40 ,  F02K9/42 ,  F02K9/58 ,  F02K9/60 ,  F02K9/68 ,  F02K9/76

Abstract: Systems and methods for a multimode propulsion system (MMPS) are presented. The MMPS includes a chemical thruster, an electric thruster, and a shared propellant tank. The MMPS further includes a propellant decomposition chamber that transforms, via a catalytic and/or electrolytic process, the propellant from the tank into vapor form for use as gas propellant by the electric thruster. The electric thruster can be configured for targeted ionization of one or more constituent species present in the vapor form of the propellant. Flow activation/control from the tank to the chemical and electric thrusters is provided by a fluidic feed system. The branches include a check valve and a pressure regulator in series connection. A normally closed squib valve prevents propellant flows/leaks from the tank to either the chemical or the electric thrusters when the MMPS is not in operation.

公开(公告)号：US12173671B2

公开(公告)日：2024-12-24

申请号：US18681099

申请日：2022-07-19

Applicant: Atharva Undire

Inventor： Atharva Undire

IPC: F02K9/97 ,  B64G1/40 ,  F02K7/08 ,  F02K7/10 ,  F02K7/12 ,  F02K9/42 ,  F02K9/44 ,  F02K9/52 ,  F02K9/62 ,  F02K9/64 ,  F02K9/66 ,  F02K9/78 ,  F02K9/90

Abstract: An aerial vehicle engine is proposed which may be powered an adjustable, vortex-based virtual aerospike engine. The vehicle may also include a combustion chamber which may be coupled to the exit nozzle. The combustion chamber may include one or more gas inlets, one or more blanket inlets and one or more main inlets. The gas inlet may be configured to let in a column of gases into the combustion chamber in a direction parallel to the direction of the rocket with minimal angular velocity to prevent the column of gases from mixing with a vortex of propellants or gases. The one or more main inlets may be configured to spray fuel or oxidizer at a specific angle, where the angle may be adjustable for forming the vortex of propellants or gases. The one or more blanket inlets may be configured to spray fuel/oxidizer/(inert) coolant at a specific angle, where the angle may be adjustable and may or may form a vortex, a stagnant pocket of gases (acting as a blanket) or a stream of gases that exits through the exit nozzle. Further, the column of gases inside the combustion chamber leading up to the exit nozzle may form a virtual aerospike nozzle, the virtual aerospike nozzle may exit the gases to propel the vehicle, wherein the virtual aerospike nozzle may not require cooling.

公开(公告)号：US12065270B1

公开(公告)日：2024-08-20

申请号：US18501983

申请日：2023-11-03

Applicant: Government of the United States as represented by the Secretary of the Air Force

Inventor： Jonathan Allison

IPC: B64G1/40 ,  F02K9/42 ,  F02K9/44 ,  F02K9/48 ,  F02K9/50 ,  F02K9/56 ,  F02K9/58

CPC classification number: B64G1/4021 ,  B64G1/401 ,  B64G1/402 ,  B64G1/4024 ,  F02K9/42 ,  F02K9/44 ,  F02K9/48 ,  F02K9/50 ,  F02K9/56 ,  F02K9/566 ,  F02K9/58

Abstract: A system for managing propellant and pressurant for in-space propulsion of a spacecraft is provided. The system includes a conformal fuel tank having an ullage operatively connected for pressurization and a propellant management device (PMD) to wick propellant to a liquid port of the conformal fuel tank. The system further includes a pneumatic circuit including a tank pressurant vent valve for adjustment of operating pressure prior to refueling operations; a vent to release excess pressurant; a pressurant metering vent valve to provide control and safety relief for the pressurant; a check valve to prevent backflow; a pressurant cat bed for decomposing propellant into pressurant; a repressurizing valve to release pressurant once cooled; a burst disk to provide overpressure safety relief; a series of propellant extraction valves to intake a predetermined quantity of propellant for decomposition; and a pressure regulator that delivers proper pressure to a series of thrusters.

公开(公告)号：US12037963B1

公开(公告)日：2024-07-16

申请号：US18133111

申请日：2023-04-11

Applicant: United Launch Alliance, L.L.C.

Inventor： Frank Charles Zegler

IPC: F02K9/58 ,  B64G1/40 ,  B64G1/42 ,  F02K9/42 ,  F02K9/44 ,  F02K9/50 ,  F02K9/60

CPC classification number: F02K9/58 ,  B64G1/402 ,  B64G1/421 ,  F02K9/42 ,  F02K9/44 ,  F02K9/50 ,  F02K9/60 ,  B64G1/401 ,  F02K9/425

Abstract: A system and methods are disclosed for an upper stage space launch vehicle that uses gases from the propellant tanks to power an internal combustion engine that produces mechanical power for driving other components including a generator for generation of electrical current for operating compressors and fluid pumps and for charging batteries. These components and others comprise a thermodynamic system from which system enthalpy may be leveraged by extracting and moving heat to increase the efficient use of propellant and the longevity and performance of the launch vehicle.

公开(公告)号：US20240218844A1

公开(公告)日：2024-07-04

申请号：US18396488

申请日：2023-12-26

Applicant: VAYA SPACE, INC.

Inventor： Kineo WALLACE

IPC: F02K9/44 ,  F02K9/42

CPC classification number: F02K9/44 ,  F02K9/425

Abstract: A rocket engine is provided with a propellant valve controlling the output of a propellant tank. The valve is configured to induce a vortex in the propellant as it passes the propellant valve. Plural rocket engines may be supplied by a single valve, the valve inducing a vortex in the propellant which is then supplied to plural propellant lines configured to enhance the vortex induced by the valve.

公开(公告)号：US12025078B2

公开(公告)日：2024-07-02

申请号：US17813312

申请日：2022-07-18

Applicant: Trans Astronautica Corporation

Inventor： Joel C. Sercel ,  Philip J. Wahl ,  Conrad T. Jensen ,  James G. Small ,  Benjamin G. Workinger ,  Samuel Daugherty-Saunders

IPC: F02K9/64 ,  B64G1/40 ,  B64G1/44 ,  F02K9/42 ,  F02K9/44 ,  F02K9/60 ,  F03H99/00 ,  F24S20/20 ,  F24S23/30 ,  F24S23/70 ,  F24S70/16

CPC classification number: F02K9/64 ,  B64G1/401 ,  B64G1/409 ,  B64G1/446 ,  F02K9/42 ,  F02K9/44 ,  F02K9/60 ,  F03H99/00 ,  F24S20/20 ,  F24S23/30 ,  F24S23/70 ,  F24S70/16 ,  F24S2023/832

Abstract: Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.

公开(公告)号：US11976614B1

公开(公告)日：2024-05-07

申请号：US18457301

申请日：2023-08-28

Applicant: Pivotal Space, Inc.

Inventor： Lloyd J Droppers

IPC: F02K9/82 ,  F02K9/44 ,  F02K9/46 ,  F02K9/56 ,  F02K9/64 ,  F02K9/97

CPC classification number: F02K9/82 ,  F02K9/44 ,  F02K9/46 ,  F02K9/56 ,  F02K9/64 ,  F02K9/972

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.

公开(公告)号：US20230131644A1

公开(公告)日：2023-04-27

申请号：US17970376

申请日：2022-10-20

Applicant: Viridian Space Corporation

Inventor： Matthew S. FELDMAN ,  Rostislav SPEKTOR

IPC: F02K9/44 ,  B64G1/40 ,  B64G1/44 ,  F03H1/00

Abstract: In one embodiment, an air-scoop includes an air inlet that air molecules enter the air-scoop through at an orbital speed when the air-scoop is moving through an atmosphere at the orbital speed. The air-scoop also includes a rotor that is rotated by a motor at a rotational speed, and the rotor includes multiple rotatable blade stages. A first one of the rotatable blade stages has a blade configuration that maximizes transparency of the first one of the rotatable blade stages to air molecules entering the air-scoop through the air inlet at the orbital speed when the rotor is rotating at the rotational speed. A last one of the rotatable blade stages has a blade configuration that maximizes opacity of the last one of the rotatable blade stages to air molecules in the air-scoop flowing directionally toward the air inlet when the rotor is rotating at the rotational speed.

公开(公告)号：US20230130545A1

公开(公告)日：2023-04-27

申请号：US17813312

申请日：2022-07-18

Applicant: Trans Astronautica Corporation

Inventor： Joel C. Sercel ,  Philip J. Wahl ,  Conrad T. Jensen ,  James G. Small ,  Benjamin G. Workinger ,  Samuel Daugherty-Saunders

IPC: F02K9/64 ,  F02K9/60 ,  B64G1/40 ,  F24S20/20 ,  F02K9/42 ,  F02K9/44 ,  F24S23/30 ,  F24S23/70 ,  F03H99/00 ,  B64G1/44 ,  F24S70/16

Abstract: Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.

公开(公告)号：US11542926B2

公开(公告)日：2023-01-03

申请号：US16897193

申请日：2020-06-09

Applicant: The Aerospace Corporation

Inventor： Horatiu C. Dragnea ,  Henry Helvajian ,  Kushal Patel

IPC: F03H1/00 ,  F02K9/08 ,  F02K9/32 ,  F02K9/36 ,  F02K9/44 ,  F02K9/42

Abstract: A vehicle comprising a structure, a plurality of heating sources, and a transport mechanism. The structure is comprised of multiple materials, a composite such that some of the material constituents can be extracted leaving behind others via application of energy (such as de-alloying). The extracted material or materials are configured to be re-purposed into a propellant. The plurality of heating elements surrounds or is embedded within the structure configured to convert the material into the propellant. The transport mechanism is configured to transport the propellant from the structure to a reservoir or to the propulsion system.