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公开(公告)号：US11644287B2
公开(公告)日：2023-05-09
申请号：US16440248
申请日：2019-06-13
Applicant: Raytheon Company
Inventor： Robert D. Travis
Abstract: A deployment system, such as for deploying wings, includes a pair of hub assemblies that transmit linear motion provided by an actuator into a combination of rotational and axial motion. The actuator works on both hub assemblies, rotating (for each wing) a slew ring that is coupled to a lift bar that acts as a follower, following a pair of cam slots, to allow the wings to follow their desired course. In one embodiment the wings move axially away from a fuselage at the beginning of the deployment movement, followed by a primarily rotational movement, with the wings pulling in toward the fuselage at the end of the deployment process. The actuator includes a pair of threaded shafts (threaded in opposite directions) that rotate along with a pinion gear, driven by a motor, to translate a pair of retractor links that are coupled to the slew rings.
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公开(公告)号：US12173740B2
公开(公告)日：2024-12-24
申请号：US16930233
申请日：2020-07-15
Applicant: Raytheon Company
Inventor： Robert D. Travis , Justin Powell
Abstract: A frangible detent pin comprising a base a pin head and an elastic member. The base is configured to be secured within a bore. The pin head and the base are interconnected through a frangible connection. The elastic member is configured to bias the pin head away from the base. The frangible detent pin has a rigid stage in which the pin head is rigidly positioned relative to the base and a spring-loaded stage in which the pin head is moveable relative to the base under a compression load between pin head and the base. The frangible detent pin is configured to transition from the rigid stage to the spring-loaded stage in response to the compression load exceeding a predetermined threshold sufficient to cause the frangible connection to fail.
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公开(公告)号：US20170356558A1
公开(公告)日：2017-12-14
申请号：US15665254
申请日：2017-07-31
Applicant: Raytheon Company
Inventor： Robert D. Travis
IPC: F16K17/40
CPC classification number: F16K17/403 , Y10T137/0379 , Y10T137/1632
Abstract: A frangible valve is disclosed. The frangible valve can include an outer portion operable to form a pressure boundary for a pressure vessel. The frangible valve can also include an inner portion integrally formed with the outer portion and having a central region and a separation region about a perimeter of the central region proximate the outer portion. The separation region can have a thickness less than a thickness of the central region and can be configured to break at a predetermined fluid pressure inside the pressure vessel to vent pressure from the pressure vessel.
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公开(公告)号：US10514241B1
公开(公告)日：2019-12-24
申请号：US16258819
申请日：2019-01-28
Applicant: Raytheon Company
Inventor： Daniel D. Reimann , Jeffrey R. Richards , Charles M. Hoke , Robert D. Travis
IPC: F42B15/36
Abstract: A missile or other flight vehicle has a stage separation mechanism for separating a downstream stage from an upstream portion of the missile. The mechanism includes one or more holes in fluid communication with a cavity between the upstream and downstream portions of the missile. The holes are located downstream of one or more shocks produced by one or more local variations in the outer surface shape of the missile. The one or more local variations in outer surface shapes produce the one or more shocks as the missile is flown at supersonic speeds. These shock(s) produce downstream pressure rises, and these pressure increases are communicated to the cavity by the hole(s). The increased pressure in the cavity provides a mechanism for separating the downstream stage from the upstream portion of the missile, after release of a mechanical coupling between the upstream portion and downstream stage.
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公开(公告)号：US20180023933A1
公开(公告)日：2018-01-25
申请号：US15217491
申请日：2016-07-22
Applicant: Raytheon Company
Inventor： Daniel D. Reimann , Jeffery R. Richards , Charles M. Hoke , Robert D. Travis
IPC: F42B15/36
CPC classification number: F42B15/36
Abstract: A missile or other flight vehicle has a stage separation mechanism for separating a downstream stage from an upstream portion of the missile. The mechanism includes one or more holes in fluid communication with a cavity between the upstream and downstream portions of the missile. The holes are located downstream of one or more shocks produced by one or more local variations in the outer surface shape of the missile. The one or more local variations in outer surface shapes produce the one or more shocks as the missile is flown at supersonic speeds. These shock(s) produce downstream pressure rises, and these pressure increases are communicated to the cavity by the hole(s). The increased pressure in the cavity provides a mechanism for separating the downstream stage from the upstream portion of the missile, after release of a mechanical coupling between the upstream portion and downstream stage.
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Patent Agency Ranking
公开(公告)号：US10222189B2
公开(公告)日：2019-03-05
申请号：US15217491
申请日：2016-07-22
Applicant: Raytheon Company
Inventor： Daniel D. Reimann , Jeffery R. Richards , Charles M. Hoke , Robert D. Travis
IPC: F42B15/36
Abstract: A missile or other flight vehicle has a stage separation mechanism for separating a downstream stage from an upstream portion of the missile. The mechanism includes one or more holes in fluid communication with a cavity between the upstream and downstream portions of the missile. The holes are located downstream of one or more shocks produced by one or more local variations in the outer surface shape of the missile. The one or more local variations in outer surface shapes produce the one or more shocks as the missile is flown at supersonic speeds. These shock(s) produce downstream pressure rises, and these pressure increases are communicated to the cavity by the hole(s). The increased pressure in the cavity provides a mechanism for separating the downstream stage from the upstream portion of the missile, after release of a mechanical coupling between the upstream portion and downstream stage.
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公开(公告)号：US10145482B2
公开(公告)日：2018-12-04
申请号：US15665254
申请日：2017-07-31
Applicant: Raytheon Company
Inventor： Robert D. Travis
IPC: F16K17/40
Abstract: A frangible valve is disclosed. The frangible valve can include an outer portion operable to form a pressure boundary for a pressure vessel. The frangible valve can also include an inner portion integrally formed with the outer portion and having a central region and a separation region about a perimeter of the central region proximate the outer portion. The separation region can have a thickness less than a thickness of the central region and can be configured to break at a predetermined fluid pressure inside the pressure vessel to vent pressure from the pressure vessel.
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公开(公告)号：US20220018377A1
公开(公告)日：2022-01-20
申请号：US16930233
申请日：2020-07-15
Applicant: Raytheon Company
Inventor： Robert D. Travis , Justin Powell
Abstract: A frangible detent pin comprising a base a pin head and an elastic member. The base is configured to be secured within a bore. The pin head and the base are interconnected through a frangible connection. The elastic member is configured to bias the pin head away from the base. The frangible detent pin has a rigid stage in which the pin head is rigidly positioned relative to the base and a spring-loaded stage in which the pin head is moveable relative to the base under a compression load between pin head and the base. The frangible detent pin is configured to transition from the rigid stage to the spring-loaded stage in response to the compression load exceeding a predetermined threshold sufficient to cause the frangible connection to fail.
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公开(公告)号：US11009326B2
公开(公告)日：2021-05-18
申请号：US16747465
申请日：2020-01-20
Applicant: Raytheon Company
Inventor： Robert D. Travis
IPC: F42B15/36
Abstract: An internally coupleable joint is disclosed. The joint can include a first component and a second component configured to mate with one another in an end-to-end relationship. An axially extending protrusion of the first component can interface with a corresponding recess of the second component. In addition, the first component and the second component can each have an internal coupling feature extending at least partially about an inner circumference of the respective component. The joint can also include a securing member having external coupling features configured to engage the internal coupling features of the first and second components to prevent separation of the first and second components.
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公开(公告)号：US20200149850A1
公开(公告)日：2020-05-14
申请号：US16747465
申请日：2020-01-20
Applicant: Raytheon Company
Inventor： Robert D. Travis
IPC: F42B15/36
Abstract: An internally coupleable joint is disclosed. The joint can include a first component and a second component configured to mate with one another in an end-to-end relationship. An axially extending protrusion of the first component can interface with a corresponding recess of the second component. In addition, the first component and the second component can each have an internal coupling feature extending at least partially about an inner circumference of the respective component. The joint can also include a securing member having external coupling features configured to engage the internal coupling features of the first and second components to prevent separation of the first and second components.
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