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公开(公告)号：US11994367B2
公开(公告)日：2024-05-28
申请号：US17728624
申请日：2022-04-25
发明人： James Kolanek , Behshad Baseghi , David Sharpin , Anthony Visco , Falin Shieh
IPC分类号： F41G7/34 , F41G7/00 , F41G7/30 , F41H11/02 , F42B10/66 , F42B15/01 , F42B15/10 , G05D1/00 , G05D1/08 , G06T7/246 , F42B15/00
CPC分类号： F41G7/34 , F41G7/007 , F41G7/303 , F41H11/02 , F42B10/66 , F42B10/661 , F42B15/01 , F42B15/105 , G05D1/0808 , G06T7/246
摘要： Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle.
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公开(公告)号：US20220412694A1
公开(公告)日：2022-12-29
申请号：US17728624
申请日：2022-04-25
发明人： James Kolanek , Behshad Baseghi , David Sharpin , Anthony Visco , Falin Shieh
IPC分类号： F41G7/34 , F41G7/00 , F41G7/30 , F41H11/02 , G06T7/246 , F42B10/66 , F42B15/01 , F42B15/10 , G05D1/08
摘要： Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle.
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公开(公告)号：US20210163145A1
公开(公告)日：2021-06-03
申请号：US16770688
申请日：2018-11-27
申请人： MBDA UK LIMITED
摘要： A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a motive arrangement operable to move from a first configuration in which the cover is lockable to a missile, to a second configuration in which the cover is pushed outwardly from the missile. In the first configuration, the surface of the cover is flush with the surface of the missile and the motive arrangement is located inwardly of the cover surface. A missile provided with such a cover is also disclosed.
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公开(公告)号：US10962990B2
公开(公告)日：2021-03-30
申请号：US16534040
申请日：2019-08-07
摘要： The system and method of attitude determination by pulse beacon and extremely low cost inertial measuring unit. A pulse beacon is used to generate a plurality of pulses detected by a detector or receiver located on the rear of a projectile such that direction of arrival can be determined. A synchronized clock proved for velocity and range information. Altitude can also be determined and may use an altimeter or the like. The use of a low cost IMU is possible with internal calibration by the system. Real-time attitude information provides for correction for crosswind and other drift enabling the system to have less down range dispersion.
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公开(公告)号：US10852112B2
公开(公告)日：2020-12-01
申请号：US15525225
申请日：2014-11-07
发明人： Arnstein Solberg , Jens A. Gjestvang , Trond Henning Sleveland , Kristian Jensrud , Ivar Thomle Hoelsæter
摘要： A cover 10 and method for protecting a missile 15 with stowed wings 20 and connected to a vessel carrying it. The cover 10 includes a spoiler shaped front part 25 for covering a gap between the wings 20 of the missile 15 and the fuselage of the missile 15 for minimizing aerodynamic forces.
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公开(公告)号：US10571227B2
公开(公告)日：2020-02-25
申请号：US15646059
申请日：2017-07-10
申请人： Jahangir S Rastegar , Richard T Murray , Gretel Raibeck , Jay Poret , Brandon Andreola , Andrew Zimmer
发明人： Jahangir S Rastegar , Richard T Murray , Gretel Raibeck , Jay Poret , Brandon Andreola , Andrew Zimmer
摘要： A flare including: a casing; and a grain assembly, at least a portion of the grain assembly being slidably disposed in the casing, the grain assembly including: a shell structure; and a grain component at least partially disposed in the shell structure, the grain component including at least one combustible material and at least one reactive material positioned relative to the combustible material and configured to ignite combustion of the at least one combustible material; wherein the shell structure includes one or more fins at an aft end of the shell structure, the one or more fins being restrained into a first shape in the casing and configured to have a second shape, different from the first shape, when the restraint is removed.
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公开(公告)号：US10378483B2
公开(公告)日：2019-08-13
申请号：US14938952
申请日：2015-11-12
申请人： Raytheon Company
IPC分类号： F02K9/97 , F02K9/90 , F02K9/10 , F02K9/34 , F02K9/24 , F02K9/36 , F42B30/08 , F42B30/12 , F42B30/10 , F02K9/95 , F42B15/01 , F42B15/10 , F42B15/36 , F02K9/18 , F41A1/00 , F42B15/00 , F41F3/04
摘要： A motor assembly is provided for use with projectiles, such as munitions, having relatively low length to diameter ratios. The motor assembly has an aerospike nozzle and a casing disposed about the aerospike nozzle, where interior aerospike volume contains propellant and where walls of both the cowl of the casing and of the aerospike nozzle jointly define a combustion chamber.
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公开(公告)号：US10345087B2
公开(公告)日：2019-07-09
申请号：US15665656
申请日：2017-08-01
摘要： A mid-body which a cylindrical housing which defines a longitudinal axis and has an interior compartment. A guidance controller is housed within the mid-body for controlling flight. A plurality of wings are connected to the housing and each of the wings is movable into a deployed position to provide guidance during flight. The mid-body has an access window which facilitates communication between the interior compartment of the housing and an external environment. A normally door covers the access window, but when the door is moved, relative to the access window, into an open position, communication between the interior compartment and the external environment is established. An optical sensor is accommodated within the interior compartment and the optical sensor, once the door is moved relative to the access window, can view the external environment and supply data to the guidance controller for controlling operation of the plurality of wings during flight.
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公开(公告)号：US10109939B2
公开(公告)日：2018-10-23
申请号：US15071745
申请日：2016-03-16
发明人： Neal R. Whatcott
摘要： An electronic system includes first and second circuit boards and a flexible circuit connector. The flexible circuit connector is configured to electrically connect the first and second circuit boards. The flexible circuit connector includes first and second connectors and a spiral portion. The first connector is configured to connect to the first circuit board. The second connector is configured to connect to the second circuit board. The spiral portion is connected between the first and second circuit boards and includes a circumferential portion that extends around the second connector.
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公开(公告)号：US10094646B2
公开(公告)日：2018-10-09
申请号：US14685585
申请日：2015-04-13
申请人： The Boeing Company
摘要： A rocket comprises at least one propulsion unit including a pivotable rocket motor, a spring-assisted one-time deployment mechanism, and a release mechanism. The pivotable rocket motor is pivotable between a stowed position and a deployed position. The spring-assisted one-time deployment mechanism moves the rocket motor from the stowed position to the deployed position when the deployment mechanism is released by the release mechanism. Outer geometry of the rocket is changed as the rocket motor is moved to the deployed position.
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