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公开(公告)号：US20230356828A1
公开(公告)日：2023-11-09
申请号：US17929127
申请日：2022-09-01
Applicant: Raytheon Company
Inventor： Zachariah A. Seasly , Edgar R. Melkers
Abstract: A control surface restraining system for variably preventing movement of a control surface imparted by a control actuation shaft of a control actuation section of a tactical flight vehicle includes a power take-off shaft operably connected to the control actuation shaft with a power take-off gear train and a control surface restraint. The control surface restraint is configured to variably engage the power take-off shaft, thereby locking the power take-off gear train and preventing the control actuation shaft from imparting the movement of the control surface. The control surface restraint is also configured to variably disengage the power take-off shaft, thereby unlocking power take-off gear train and allowing the control actuation shaft from imparting the movement of the control surface.
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Patent Agency Ranking
公开(公告)号：US12092436B2
公开(公告)日：2024-09-17
申请号：US17466210
申请日：2021-09-03
Applicant: Raytheon Company
Inventor： Edgar R. Melkers , Kenyon Kehl , Andre White , Gregory A. Trainor
Abstract: A control surface restraining system for variably restraining a control surface on a flight vehicle includes a passively triggered and manually movable control surface restraint for keeping the control surface aligned along a longitudinal axis of the flight vehicle, while allowing for temporary control surface rotation during handling and loading. The control surface restraining system allows the control surfaces to be manually rotated out of and back to the “zero position” (i.e., aligned along the longitudinal axis) for loading the flight vehicle with a common load strap, and thereafter maintained in the “zero position” until launch for proper control actuation system initialization. Upon launch, the control surface restraining system is passively actuated for releasing the control surface, requiring no active stimulus from the guidance section, power, or associated wiring, therefore saving critical space and volume within the tactical flight vehicle.
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公开(公告)号：US20230400285A1
公开(公告)日：2023-12-14
申请号：US17829799
申请日：2022-06-14
Applicant: Raytheon Company
Inventor： Jason Allan Dixon , Kenyon Kehl , Edgar R. Melkers , Randall S. Firor
IPC: F42B10/64
CPC classification number: F42B10/64
Abstract: A system for restraining one or more control surfaces of a tactical flight vehicle includes a retaining frame secured at an aft end of the tactical flight vehicle and a cover plate releasably coupled to the retaining frame with a resilient lock ring. The resilient lock ring is disposed between the retaining frame and the cover plate and is deformable between a locking configuration and an unlocking configuration. A control surface restraining ring is releasably coupled to the cover plate and has control surface restraints configured to engage respective control surfaces. The resilient lock ring is configured to deform from the locking configuration to the unlocking configuration upon a launch of the tactical flight vehicle such that the cover plate becomes uncoupled from the retaining frame and may be jettisoned from the tactical flight vehicle after the launch.
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公开(公告)号：US20230072799A1
公开(公告)日：2023-03-09
申请号：US17466210
申请日：2021-09-03
Applicant: Raytheon Company
Inventor： Edgar R. Melkers , Kenyon Kehl , Andre White , Gregory A. Trainor
Abstract: A control surface restraining system for variably restraining a control surface on a flight vehicle includes a passively triggered and manually movable control surface restraint for keeping the control surface aligned along a longitudinal axis of the flight vehicle, while allowing for temporary control surface rotation during handling and loading. The control surface restraining system allows the control surfaces to be manually rotated out of and back to the “zero position” (i.e., aligned along the longitudinal axis) for loading the flight vehicle with a common load strap, and thereafter maintained in the “zero position” until launch for proper control actuation system initialization. Upon launch, the control surface restraining system is passively actuated for releasing the control surface, requiring no active stimulus from the guidance section, power, or associated wiring, therefore saving critical space and volume within the tactical flight vehicle.
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公开(公告)号：US12296942B2
公开(公告)日：2025-05-13
申请号：US17929127
申请日：2022-09-01
Applicant: Raytheon Company
Inventor： Zachariah A. Seasly , Edgar R. Melkers
Abstract: A control surface restraining system for variably preventing movement of a control surface imparted by a control actuation shaft of a control actuation section of a tactical flight vehicle includes a power take-off shaft operably connected to the control actuation shaft with a power take-off gear train and a control surface restraint. The control surface restraint is configured to variably engage the power take-off shaft, thereby locking the power take-off gear train and preventing the control actuation shaft from imparting the movement of the control surface. The control surface restraint is also configured to variably disengage the power take-off shaft, thereby unlocking power take-off gear train and allowing the control actuation shaft from imparting the movement of the control surface.
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公开(公告)号：US12044513B2
公开(公告)日：2024-07-23
申请号：US17829799
申请日：2022-06-14
Applicant: Raytheon Company
Inventor： Jason Allan Dixon , Kenyon Kehl , Edgar R. Melkers , Randall S. Firor
IPC: F42B10/64
CPC classification number: F42B10/64
Abstract: A system for restraining one or more control surfaces of a tactical flight vehicle includes a retaining frame secured at an aft end of the tactical flight vehicle and a cover plate releasably coupled to the retaining frame with a resilient lock ring. The resilient lock ring is disposed between the retaining frame and the cover plate and is deformable between a locking configuration and an unlocking configuration. A control surface restraining ring is releasably coupled to the cover plate and has control surface restraints configured to engage respective control surfaces. The resilient lock ring is configured to deform from the locking configuration to the unlocking configuration upon a launch of the tactical flight vehicle such that the cover plate becomes uncoupled from the retaining frame and may be jettisoned from the tactical flight vehicle after the launch.
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