-
公开(公告)号：US12146454B2
公开(公告)日：2024-11-19
申请号：US18540064
申请日：2023-12-14
Applicant: Blue Origin, LLC
Inventor： Owen Stewart Graham , Stephen Wuest , Nicholas James Keleshian , Warren Godwin Lamont
Abstract: A modular damper plug forming a multi-volume acoustic resonator in an acoustic liner of a rocket engine is provided. In one aspect, the damper plug includes a main body including a top surface spaced from a bottom surface by a first height, a left surface spaced from a right surface by a width, and an exterior surface spaced from an interior surface by a length. A chamber within the main body extends along a part of the height, a part of the width, and a part of the length, and communicates with the top surface through an opening. The chamber also communicates with the interior surface through one or more ducts. The main body is sized and shaped to be received in any one of a plurality of cavities in the acoustic liner. The chamber includes an upstream volume of the acoustic resonator, and the one or more ducts communicate with a downstream volume of the acoustic resonator when the damper plug is received in any one of the plurality of cavities.
-
公开(公告)号：US20240375798A1
公开(公告)日：2024-11-14
申请号：US18315765
申请日：2023-05-11
Applicant: Blue Origin, LLC
Inventor： Jonathan Glen Metts , Alice Clare Watts
Abstract: Systems and methods for high performance, professional-grade photography and filmmaking in a spacecraft during space flights are provided. The systems may include an imaging studio, which is a partially enclosed volume within a spacecraft. The imaging studio may enable photography during microgravity coast phases of space flight while allowing astronauts to tend to non-photographic activities. The imaging studio may allow for commercially-valuable imagery that includes a background of an illuminated, curved Earth horizon. Imagery may also involve, among other things, a unique microgravity environment. Such imagery, without use of an imaging studio as described herein, may otherwise require artificial visual effects that may appear less realistic. Additionally, the novelty of capturing images during an actual space flight may itself be valuable.
-
公开(公告)号：US12129052B1
公开(公告)日：2024-10-29
申请号：US17661023
申请日：2022-04-27
Applicant: Blue Origin, LLC
Inventor： David Degenhardt , Kyle Patrick Doyle , David Aaron Kornuta , Zachary Reid Tolley
Abstract: Systems and methods for achieving pristine microgravity in low earth orbit (LEO) using electric propulsion. Long-duration, low thrust, electric thrusters provide a constant thrust force for a pristine microgravity environment within a given volume of a space vehicle experiencing drag forces in LEO. Large space vehicles in LEO configured to be pressurized for human habitation, for instance having a mass of at least 40,000 kg and an internal volume of at least 400 m3, can use the electric propulsion systems and methods to achieve a quasi-steady acceleration less than or equal to 1.0 μg for durations of 180 consecutive days or longer.
-
公开(公告)号：US20240328373A1
公开(公告)日：2024-10-03
申请号：US18193005
申请日：2023-03-30
Applicant: Blue Origin, LLC
Inventor： Weidong Song , Kutter Kupke , Alexander Twaites
IPC: F02K9/97
Abstract: Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.
-
公开(公告)号：US20240300676A1
公开(公告)日：2024-09-12
申请号：US18669991
申请日：2024-05-21
Applicant: Blue Origin, LLC
Inventor： David Harper , Jeramy Kimball , Logan Sailer , Curtis Wen
CPC classification number: B64G1/58 , B64G1/4021 , F28F3/02
Abstract: Rocket components having internal heat fins are described herein. The disclosed components have internal heat fins that mitigate buckling and uneven force application by adding thermal capacity to the component without adding component stiffness. This reduces a thermal force fight (i.e., tension versus compression between cold and hot areas, respectively), which inhibits the buckling loads on the propellant tank. The internal heats fins also provide for a reduced mass of the propellant tank wall relative to a propellant tank wall without internal heat fins. By reducing the thermal force fight, as discussed above, less material can be used which further allows for thinner welds to be used (i.e., less welding material).
-
Patent Agency Ranking
公开(公告)号：US20240253824A1
公开(公告)日：2024-08-01
申请号：US18433097
申请日：2024-02-05
Applicant: Blue Origin, LLC
Inventor： Emmanuel John Grillos, II , Richard Donovan Jones
Abstract: Systems and methods for receiving a descending rocket, which may be at sea. The rocket may descend vertically with the nose higher than the nozzle. The rocket body may be angled as it descends. A boom arm with hooks may extend at an angle to the rocket body to engage a cable suspended by a semisubmersible platform at sea. The platform may include a dampened cable and lateral straps for securing and rotating the rocket into a horizontal orientation. The platform may receive a ship and purge water to elevate the platform for placing the horizontal rocket onto the ship.
-
公开(公告)号：US20240246491A1
公开(公告)日：2024-07-25
申请号：US18589037
申请日：2024-02-27
Applicant: BLUE ORIGIN, LLC
Inventor： Michael David Johnson
Abstract: A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module. The cargo module of the cargo spacecraft is positioned along the launch vehicle axis in a direction distal from the support structure, and at least a portion of the service module of the cargo spacecraft positioned within an annulus of the support structure.
-
公开(公告)号：US20240191676A1
公开(公告)日：2024-06-13
申请号：US18540064
申请日：2023-12-14
Applicant: Blue Origin, LLC
Inventor： Owen Stewart Graham , Stephen Wuest , Nicholas James Keleshian , Warren Godwin Lamont
CPC classification number: F02K9/62 , F23R3/002 , F23R2900/00014
Abstract: A modular damper plug forming a multi-volume acoustic resonator in an acoustic liner of a rocket engine is provided. In one aspect, the damper plug includes a main body including a top surface spaced from a bottom surface by a first height, a left surface spaced from a right surface by a width, and an exterior surface spaced from an interior surface by a length. A chamber within the main body extends along a part of the height, a part of the width, and a part of the length, and communicates with the top surface through an opening. The chamber also communicates with the interior surface through one or more ducts. The main body is sized and shaped to be received in any one of a plurality of cavities in the acoustic liner. The chamber includes an upstream volume of the acoustic resonator, and the one or more ducts communicate with a downstream volume of the acoustic resonator when the damper plug is received in any one of the plurality of cavities.
-
公开(公告)号：US20240173791A1
公开(公告)日：2024-05-30
申请号：US18438369
申请日：2024-02-09
Applicant: Blue Origin, LLC
Inventor： Michael S. Brendel , Ilana K. Lu , Roger Conant Carter, IV
IPC: B23K20/12 , B23K103/10
CPC classification number: B23K20/1225 , B23K20/1245 , B23K2103/10
Abstract: A friction stir welding system can reduce the likelihood of oxide formation in the work pieces being friction stir welded by forming an inert gas atmosphere in which the friction stir welding process is performed. The friction stir welding system includes one or more inert purge gas sources that direct inert purge gas towards the forming friction stir weld. The inert purge gas can be directed towards the forming weld from both an upper and a lower side, which further reduces the likelihood of oxide formation. Additionally, the friction stir welding system can include one or more housings that contains the inert purge gas about the forming friction stir weld, such as about an upper and lower side of the friction stir weld.
-
公开(公告)号：US11987395B2
公开(公告)日：2024-05-21
申请号：US17341256
申请日：2021-06-07
Applicant: Blue Origin, LLC
Inventor： Scott D. Patty , Park O. Cover, Jr. , Mathew John Theis , Robert E. McMullen
IPC: B64G1/64
CPC classification number: B64G1/645
Abstract: 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.
-
-
-
-
-
-
-
-
-
Search Results
162
records
(took 0.026 seconds)
