-
公开(公告)号:US11909110B2
公开(公告)日:2024-02-20
申请号:US17382288
申请日:2021-07-21
申请人: The Boeing Company
CPC分类号: H01Q13/0283 , B22F10/80 , B33Y50/00 , B33Y80/00 , H01Q21/061
摘要: An antenna device is disclosed, including an additively manufactured tubular body portion having a wall portion with a plurality of holes. The tubular body portion is configured to transmit electromagnetic radiation in a selected operating frequency range, and to have a mass below a maximum mass threshold. The plurality of holes reduce the mass of the tubular body below the maximum mass threshold without significantly adversely affecting electromagnetic radiation transmission capability of the tubular body in the selected operating frequency range.
-
公开(公告)号:US11802606B2
公开(公告)日:2023-10-31
申请号:US16877480
申请日:2020-05-18
申请人: The Boeing Company
CPC分类号: F16F15/08 , B64G1/641 , B64G1/645 , F16M13/02 , B64G2001/228
摘要: A vibration isolation system is disclosed, including a rigid retaining device having an internal space, a first external side, and a second external side. A rigid anchoring device is retained in the internal space of the rigid retaining device. The anchoring device has a linkage member that extends from the internal space to the first external side of the retaining device and is configured for rigid connection to a first apparatus. The second side of the retaining device is configured for attachment to a second apparatus. A damping material is sandwiched between the retaining device and the anchoring device, and is configured to limit transfer of vibration between the retaining device and the anchoring device.
-
3.
公开(公告)号:US11708181B2
公开(公告)日:2023-07-25
申请号:US16903017
申请日:2020-06-16
申请人: The Boeing Company
IPC分类号: B64G1/40 , B64G1/24 , B64G1/00 , B64G1/26 , B64G1/64 , B64G1/10 , B64G1/28 , B64G1/36 , B64G1/42 , B64G1/44 , B64G1/50
CPC分类号: B64G1/242 , B64G1/002 , B64G1/007 , B64G1/10 , B64G1/26 , B64G1/40 , B64G1/402 , B64G1/405 , B64G1/641 , B64G1/283 , B64G1/361 , B64G1/363 , B64G1/365 , B64G1/422 , B64G1/428 , B64G1/44 , B64G1/503 , B64G2001/643
摘要: Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example launch vehicle includes a first space vehicle including a first core structure and a first electric propulsion system, and a second space vehicle including a second core structure and a second electric propulsion system, the second core structure releasably attached to the first space vehicle in a stacked configuration.
-
公开(公告)号:US11542041B2
公开(公告)日:2023-01-03
申请号:US16877477
申请日:2020-05-18
申请人: The Boeing Company
摘要: A satellite is disclosed, including a body having an additively manufactured wall panel and a communication device connected to the body. The wall panel includes a facesheet and a stiffening structure extending from a first side of the facesheet. The communication device is configured to send and receive data while in space.
-
公开(公告)号:US20210362230A1
公开(公告)日:2021-11-25
申请号:US17393342
申请日:2021-08-03
申请人: The Boeing Company
发明人: Richard W. Aston , Martin W. Bieti , Michael John Langmack , Nicole M. Hastings , Nicole Diane Schoenborn
摘要: An additively manufactured antenna device is disclosed, including a base portion and a body portion. The body portion is attached to the base portion and includes a lattice stiffening structure configured to eliminate secondary printing support.
-
公开(公告)号:US20210247140A1
公开(公告)日:2021-08-12
申请号:US17242204
申请日:2021-04-27
申请人: The Boeing Company
发明人: Richard W. Aston , Matthew Joseph Herrmann , Michael John Langmack , Nicole M. Hastings , Sumit K. Purohit
IPC分类号: F28D7/00
摘要: An additively manufactured heat transfer device is disclosed, including an enclosure portion with outer walls. The outer walls contain an inner channel configured to direct a flow of coolant fluid. The heat transfer device further includes a fluid intake port and a fluid outtake port, each connected to the first inner channel. The fluid intake port is configured to direct a flow of coolant fluid through an outer wall of the enclosure portion into the inner channel, and the fluid outtake port is configured to direct a flow of coolant fluid through an outer wall of the enclosure portion out of the inner channel. The inner channel is defined by internal walls, and the enclosure portion and the internal walls form a single additively manufactured unit.
-
公开(公告)号:US11015872B2
公开(公告)日:2021-05-25
申请号:US16024582
申请日:2018-06-29
申请人: The Boeing Company
发明人: Richard W. Aston , Matthew Joseph Herrmann , Michael John Langmack , Nicole M. Hastings , Sumit K. Purohit
摘要: An additively manufactured heat transfer device is disclosed, including an enclosure portion with outer walls. The outer walls contain an inner channel configured to direct a flow of coolant fluid. The heat transfer device further includes a fluid intake port and a fluid outtake port, each connected to the first inner channel. The fluid intake port is configured to direct a flow of coolant fluid through an outer wall of the enclosure portion into the inner channel, and the fluid outtake port is configured to direct a flow of coolant fluid through an outer wall of the enclosure portion out of the inner channel. The inner channel is defined by internal walls, and the enclosure portion and the internal walls form a single additively manufactured unit.
-
公开(公告)号:US20200373642A1
公开(公告)日:2020-11-26
申请号:US16422939
申请日:2019-05-24
申请人: The Boeing Company
摘要: A radio frequency filter apparatus is disclosed, including an elongate hollow body portion having an inner side and an outer side. The apparatus further includes an iris structure on the inner side of the body portion and a stiffening structure on the outer side of the body portion. The stiffening structure is aligned with the iris structure.
-
公开(公告)号:US10457425B2
公开(公告)日:2019-10-29
申请号:US13655224
申请日:2012-10-18
申请人: THE BOEING COMPANY
摘要: A satellite is disclosed comprising an anti-nadir panel having a first side and a second side. In one or more embodiments, the first side of the anti-nadir panel is mounted to an anti-nadir side of the main body of the satellite. The satellite further comprises at least one battery pack mounted to the second side of the anti-nadir panel, where at least one battery pack comprises at least one battery cell.
-
公开(公告)号:US10076899B2
公开(公告)日:2018-09-18
申请号:US14949224
申请日:2015-11-23
申请人: The Boeing Company
IPC分类号: B32B5/12 , B32B38/18 , B32B5/26 , B32B1/00 , B32B3/02 , B64G1/64 , B29C65/02 , B29C65/00 , B32B37/06 , B32B37/18 , B64G1/22 , B29K105/00 , B29L9/00 , B29L31/30
CPC分类号: B32B38/1808 , B29C65/02 , B29C66/432 , B29K2105/256 , B29L2009/00 , B29L2031/3097 , B32B1/00 , B32B3/02 , B32B5/12 , B32B5/26 , B32B37/06 , B32B37/182 , B32B2250/20 , B32B2262/02 , B32B2307/306 , B32B2307/308 , B32B2307/734 , B32B2605/00 , B64G1/22 , B64G1/641 , Y10T156/10 , Y10T428/192
摘要: A method of manufacturing a cone-shaped composite article may include providing unidirectional plies in a continuous arcuate shape in a flat pattern configured to wrap 360 degrees around a cone-shaped mandrel such that opposing ply ends of each unidirectional ply terminate at a ply seam. The method may further include laying up at least one inner sublaminate on the cone-shaped mandrel, the inner sublaminate containing at least four of the unidirectional plies having an inner stacking sequence with fiber angles of −45, 90, 0, +45 degrees such that the inner sublaminate has a quasi-isotropic layup at any location of the inner sublaminate. The method may additionally include laying up at least one outer sublaminate in an outer stacking sequence being a mirror image of the at least one inner stacking sequence.
-
-
-
-
-
-
-
-
-