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公开(公告)号：US20240359832A1
公开(公告)日：2024-10-31
申请号：US18767813
申请日：2024-07-09
申请人： BLUE ORIGIN, LLC
发明人： Michael D. Johnson
摘要： A representative spacecraft system includes a connecting device, which in turn includes a housing having a common port opening, a first connecting element carried by the housing and positioned to connect with a corresponding first spacecraft connecting structure having a first configuration, and a second connecting element carried by the housing and positioned to connect with a corresponding second spacecraft connecting structure having a second configuration different than the first configuration. At least one of the first and second connecting elements is moveable relative to the other between an operational position and a non-operational position, and each of the first and second connecting elements, when connected to the corresponding first or second spacecraft connecting structure, is positioned to allow transport through the common port opening.
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公开(公告)号：US12104699B2
公开(公告)日：2024-10-01
申请号：US17715781
申请日：2022-04-07
申请人： Blue Origin, LLC
发明人： Ryan Linderman , Jacob Mills
CPC分类号： F16J15/3432 , F02K9/48 , F16J15/34 , F16J15/3408 , F16J15/3412 , F16J15/346 , F01D11/003 , F01D11/122 , F05D2220/30 , F05D2240/55
摘要： A representative seal system (such as a seal system for a turbopump of a rocket engine) automatically adjusts a balance ratio of a seal. The system can include a ring element encircling an axis. A front side of the ring element contacts a revolving surface to form a seal with the revolving surface. The front side can include a stepped surface having two or more steps. Each step includes a sealing surface configured to contact the revolving surface to form a sealing area that is different from a sealing area of each other sealing surface. Each step is positioned and configured to wear away during operation of the machine to expose an underlying surface to the revolving surface, to change the sealing area and the balance ratio of the seal. A representative method of operating a turbomachinery system includes changing the balance ratio of a seal while rotating a rotor.
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公开(公告)号：US20240300678A1
公开(公告)日：2024-09-12
申请号：US18664115
申请日：2024-05-14
申请人： BLUE ORIGIN, LLC
IPC分类号： B64G1/64
CPC分类号： B64G1/645
摘要： The present technology is directed to thrusting rails for launch vehicles, and associated systems and methods. Certain embodiments of the thrusting rails can include a first rail housing portion having a cavity and a second rail housing portion having a projection positioned at least partially within the cavity. The rails can include a bellows positioned within the cavity and an elongated tube positioned within the bellows. The elongated tube can include a vent opening in a lateral wall of the elongated tube. A shield can be positioned between the vent opening at the bellows and a sleeve can be positioned within the elongated tube. The sleeve can be constructed from a fibrous material and positioned to retain an ordnance within the elongated tube.
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公开(公告)号：US12065991B2
公开(公告)日：2024-08-20
申请号：US17514471
申请日：2021-10-29
申请人： Blue Origin, LLC
CPC分类号： F02K9/974 , B32B5/024 , B32B5/26 , B32B7/027 , B32B7/09 , B32B7/12 , B64G1/226 , B64G1/58 , F02K9/97 , F02K9/972 , B32B2262/103 , B32B2262/105 , B32B2307/304 , B32B2605/00 , B32B2605/18
摘要： A high temperature thermal protection systems for rockets, and associated methods, is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end. The launch vehicle is elongated along a vehicle axis extending between the first and second ends and carries a propulsion system having at least one nozzle positioned at the second end of the launch vehicle. A thermal protection apparatus positioned around the nozzle is used to provide cooling and/or insulation to the nozzle during the flight of the launch vehicle. The thermal protection apparatus can include multiple fabric layers and an insulation layer stacked and stitched together. The fabric layers can include metal alloy fibers. In representative systems, the thermal protection apparatus can further include provisions for water that saturates the insulation layer to provide further insulating and/or cooling effects.
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公开(公告)号：US12037143B2
公开(公告)日：2024-07-16
申请号：US18079819
申请日：2022-12-12
申请人： Blue Origin, LLC
发明人： Michael D. Johnson
摘要： A representative spacecraft system includes a connecting device, which in turn includes a housing having a common port opening, a first connecting element carried by the housing and positioned to connect with a corresponding first spacecraft connecting structure having a first configuration, and a second connecting element carried by the housing and positioned to connect with a corresponding second spacecraft connecting structure having a second configuration different than the first configuration. At least one of the first and second connecting elements is moveable relative to the other between an operational position and a non-operational position, and each of the first and second connecting elements, when connected to the corresponding first or second spacecraft connecting structure, is positioned to allow transport through the common port opening.
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公开(公告)号：US20240218980A1
公开(公告)日：2024-07-04
申请号：US18149589
申请日：2023-01-03
申请人： Blue Origin, LLC
发明人： Joseph C. Levy
IPC分类号： F17C13/00
CPC分类号： F17C13/004 , F17C2201/0109 , F17C2203/0646 , F17C2221/017 , F17C2223/0161 , F17C2227/0339 , F17C2265/033
摘要： A cryogenic tank, or a support structure of a cryogenic tank, is constructed from a number of panels of aluminum extrusion sheets having integrated in-line cooling channels. These channels carry a cooling fluid to absorb heat from the contents of the cryogenic tank, thus cooling the contents. Boil-off vapor from contents of the cryogenic tank or cold helium from another tank may be circulated through the channels to maintain temperatures of the contents in the cryogenic tank, which may be a propellant such as liquid oxygen or liquid hydrogen.
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公开(公告)号：US20240218845A1
公开(公告)日：2024-07-04
申请号：US18510495
申请日：2023-11-15
申请人： Blue Origin, LLC
发明人： Owen Graham , Warren Lamont , James Sisco
摘要： Systems and methods for subscale testing of rocket engine injector stability. The system includes a combustion chamber and a piston within the chamber that is continuously axially moveable via an actuator. An annular gap between the piston and a chamber sidewall provides a minimal cross-sectional flow area. A modular injector plate comprises one or more injector elements configured to inject a fuel and an oxidizer into the chamber. The piston is continuously translated, to thereby continuously vary a combustion volume of the chamber and to create a dynamically tunable downstream boundary. The injector elements are thus exposed to acoustic modes of varying frequency, covering the range of acoustic modes expected in a full scale rocket engine. The injector plate is removably attached to an upstream end of the chamber for replacement of the first injector elements with different, second injector elements for subsequent testing.
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公开(公告)号：US20240200875A1
公开(公告)日：2024-06-20
申请号：US18069080
申请日：2022-12-20
申请人： Blue Origin, LLC
CPC分类号： F28D1/06 , F17C13/001 , F17C13/008 , F17C2201/0128 , F17C2203/0362 , F17C2221/011 , F17C2221/012 , F17C2260/031 , F17C2270/0197 , F28F2240/00 , F28F2275/025 , F28F2275/16
摘要： A heat exchange system includes cooling tubes that carry coolant and are placed on an external surface of a storage tank, which may be spherical, cylindrical, or other shape. The storage tank may be a cryogenic rocket fuel tank. The cooling tubes are bent to particular radius of curvatures that correspond to the varying curvatures of the storage tank. A network of spacers and bridge brackets with adjustable setscrews are used to precisely place the cooling tubes in correct positions on the external surface of the storage tank. Once placed in the desired position, the setscrews are adjusted to maximize the surface area contact between the cooling tubes and the exterior surface of the storage tank, resulting in optimal heat transfer without overstressing the materials of the tubing or the storage tank. The precisely positioned tubes may then be permanently affixed to the exterior surface of the storage tank using a cryogenic adhesive.
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公开(公告)号：US20240125413A1
公开(公告)日：2024-04-18
申请号：US18539033
申请日：2023-12-13
申请人： Blue Origin LLC
发明人： Brock Steffen
摘要： A gimbal assembly for a flexible conduit configured to convey a medium is disclosed herein. The gimbal assembly includes a first component including a first plurality of struts that terminate in a first socket defining a first cavity of a first geometric configuration. The gimbal assembly also includes a second component including a second plurality of struts that terminate in a second socket defining a second cavity of a second geometric configuration. A joint fastener is configured to couple the first socket to the second socket. The joint fastener includes a first portion that geometrically corresponds to the first cavity and a second portion that geometrically corresponds to the second cavity. The first portion is configured to be immovably seated within the first cavity, and the second portion is configured to be movably retained by the second socket such that the first component can rotate relative to the second component.
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公开(公告)号：US11939938B2
公开(公告)日：2024-03-26
申请号：US17805591
申请日：2022-06-06
申请人： Blue Origin, LLC
摘要： Systems and methods for equalizing fluid levels within a vent line and a propellant tank in which the vent line is located are discussed herein. The vent line includes a vent valve and an equalization valve. The vent valve can be included in a vent duct of the vent line. The equalization valve is included in a bottom wall (i.e., a low point) of the vent duct of the vent line. A controller is also included in the system to instruct a vent valve and the equalization valve to open and close.
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