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公开(公告)号：US12017807B2
公开(公告)日：2024-06-25
申请号：US17405784
申请日：2021-08-18
申请人： Jasem Jamal Alhubail
发明人： Jasem Jamal Alhubail
摘要： A spacecraft capable of re-entry into atmosphere includes an airframe, including a body and one or more wings, and one or more propulsion devices, for example, rocket engines, reaction control thrusters, and jet engines. One or more louver systems are incorporated into the airframe to assist in controlling the aerodynamic profile of the spacecraft. The louver system includes a number of fins rotatable about and axis. An actuator system may rotate the fins in unison or independently of the other fins. A controller may receive information from sensors incorporated into the airframe and send instructions to the actuator system to rotate the fins in response to the sensor information in order to achieve a calculated aerodynamic profile. The spacecraft may also include retractable landing legs. One or more of the wings may be actuated wings.
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公开(公告)号：US12017804B2
公开(公告)日：2024-06-25
申请号：US17362228
申请日：2021-06-29
摘要： A system for launching aerospace payloads includes a wingless, unmanned modified lifting body spacecraft (100), with a payload compartment in the forward section of the spacecraft. The spacecraft is propelled by hybrid rockets clustered in the aft section of the spacecraft. Reaction control system (RCS) modules control the flight path and its associated avionics hardware and software. This system also includes a carrier aircraft (200) configured to air-launch the spacecraft. The carrier aircraft includes a flight operations control system, which monitors the spacecraft's payload and monitors and controls launch and flight operations of the spacecraft. A ground-based mission control system monitors and controls the spacecraft's payload and monitors and controls the launch and flight operations of the spacecraft.
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公开(公告)号：US20240025566A1
公开(公告)日：2024-01-25
申请号：US17872956
申请日：2022-07-25
申请人： Momentus Space LLC
发明人： Joseph Mark Oorebeek , Robert Erik Schwarz , David Robert Buckley Biggs , Charles Jonathan Chase
CPC分类号： B64G1/242 , B64G1/14 , B64G1/1085
摘要： A space vehicle competition management system includes an orbital transfer vehicle (OTV) and a control unit. The OTV is configured to retain space vehicles (SVs) while the OTV transfers the SVs from an initial altitude of a launch vehicle to a desired altitude, and deploy the plurality of SVs at a series of offset locations and respective times representing starting points of the competition. Furthermore, the control unit is configured to receive signals indicative of waypoint arrival times for one or more of the SVs at one or more waypoints along a course of the competition, and compute one or more metrics indicative of relative performance of the plurality of SVs in the competition.
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公开(公告)号：US20230399997A1
公开(公告)日：2023-12-14
申请号：US18129245
申请日：2023-03-31
摘要： Rocket propulsion systems and associated methods are disclosed. A representative system includes a combustion chamber having an inwardly-facing chamber wall enclosing a combustion zone. The chamber has a generally spherical shape and is exposed to the combustion zone. A propellant injector is coupled to the combustion chamber and has at least one fuel injector nozzle positioned to direct a flow of cooling fuel radially outwardly along the inwardly-facing chamber wall. In addition to or in lieu of the foregoing features, the injector can include an oxidizer piston and a fuel piston that deliver oxidizer and fuel, respectively, to the combustion chamber, in a sequenced manner so that the oxidizer is introduced prior to the fuel.
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公开(公告)号：US20230382564A1
公开(公告)日：2023-11-30
申请号：US18133473
申请日：2023-04-11
发明人： Livingston L. Holder , Gary C. Hudson , Bevin C. McKinney , Marshall L. Crenshaw , Daniel Paul Raymer
摘要： Various embodiments of space launch vehicle systems and associated methods of manufacture and use are disclosed herein. In some embodiments, the systems include a reusable, horizontal takeoff/horizontal landing (HTHL), ground-assisted single-stage-to-orbit (SSTO) spaceplane that is capable of providing frequent deliveries of people and/or cargo to Low Earth Orbit (LEO). In some embodiments, the spaceplane can takeoff with the aid of a rocket-powered sled that, in addition to providing additional thrust for takeoff, can also provide propellant for the spaceplane engines during the takeoff run so that the spaceplane launches with full propellant tanks.
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公开(公告)号：US20230211900A1
公开(公告)日：2023-07-06
申请号：US17811408
申请日：2022-07-08
申请人： Blue Origin, LLC
发明人： James R. French , Roger Eugene Ramsey , Adam Wuerl
摘要： Systems and methods for a fully reusable upper stage for a multi-stage launch vehicle are provided. The reusable upper stage uses an aerospike engine for main propulsion and for vertical landing. A heat shield can include a plurality of scarfed nozzles embedded radially around a semi-spherical surface of the heat shield, wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour. The heat shield can be actively cooled to dissipate heat encountered during reentry of the upper stage.
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公开(公告)号：US11649070B2
公开(公告)日：2023-05-16
申请号：US17339382
申请日：2021-06-04
发明人： Livingston L. Holder , Gary C. Hudson , Bevin C. McKinney , Marshall L. Crenshaw , Daniel Paul Raymer
摘要： Various embodiments of space launch vehicle systems and associated methods of manufacture and use are disclosed herein. In some embodiments, the systems include a reusable, horizontal takeoff/horizontal landing (HTHL), ground-assisted single-stage-to-orbit (SSTO) spaceplane that is capable of providing frequent deliveries of people and/or cargo to Low Earth Orbit (LEO). In some embodiments, the spaceplane can takeoff with the aid of a rocket-powered sled that, in addition to providing additional thrust for takeoff, can also provide propellant for the spaceplane engines during the takeoff run so that the spaceplane launches with full propellant tanks.
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公开(公告)号：US20220411108A1
公开(公告)日：2022-12-29
申请号：US17361022
申请日：2021-06-28
申请人： Yang Li
发明人： Yang Li
摘要： The present invention presents an adjustable speed reusable rocket with attachable wings system which is optimized for multiple purpose, such as space travel, high-speed long-distance travel between different addresses on earth, etc. The rocket system comprises an adjustable speed rocket propulsion system (rocket booster), an attachable wings system, a payload or space shuttle and may include slider wings system, etc. Firstly, the rocket system flies at a lift force caused by the attachable wings system at a low speed (e.g., Mach 0.5˜3). While the rocket system reaches relatively high altitude (e.g., 25,000 meters), at this altitude, the air density is extremely low comparing with the surface of earth at zero sea level, and then the attachable wings system may detach from the rocket system and fly to a designated location as a glider or by its engine on a runway, and the rocket system begins to fully initiate propulsion system and exert the payload to forward at a super high speed. Comparing with rocket fully initiate propulsion system from earth surface, the aerodynamic friction and the aerodynamic heat caused by air is extremely small and low.
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公开(公告)号：US20210094704A1
公开(公告)日：2021-04-01
申请号：US17044704
申请日：2019-04-03
申请人： Geoffrey T. Sheerin
发明人： Geoffrey T. Sheerin
摘要： An aerospace vehicle that permits horizontal launch and subsequent orbital deployment of a second stage. The vehicle can be returned to Earth for subsequent re-use. Both land-based and water-based launch is disclosed. A rocket propulsion engine is located at the center of gravity of the vehicle and rotates to provide vertical and horizontal thrust.
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公开(公告)号：US20210070475A1
公开(公告)日：2021-03-11
申请号：US17053066
申请日：2019-02-19
申请人： VIKRANT SHARMA
发明人： VIKRANT SHARMA
摘要： The embodiments herein disclose a retrofitted or in built or add-on kit/device for airborne vehicles to reduce the aerodynamic drag thereby increasing performance parameters/metrics of the vehicles. Drag reduction is achieved through shape/contour optimization, and/or heat/energy/fluid addition to the flow in neighbourhood of the vehicle. The device is designed with an external surface to offers the minimum drag. The device is configured to deposit heat/energy/fluid in neighbourhood of flying vehicle in several ways by generating/injecting hot gases in neighbourhood of vehicle for energy/heat addition, thereby causing maximum drag reduction. Heat/energy/fluid is added through the nozzles in the add-on kit/device.
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