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公开(公告)号：US12209848B1
公开(公告)日：2025-01-28
申请号：US18536527
申请日：2023-12-12
Applicant: Northrop Grumman Systems Corporation
Inventor： Michael J. Wilson
Abstract: A guided projectile having a nose portion, a body portion, a tail portion, and a central axis. In various embodiments the projectile includes a control support portion and a collar assembly pivotally mounted to the control support portion. In various embodiments the collar assembly includes a collar having an exterior sidewall with a plurality of fixed aerodynamic surfaces thereon for spinning the collar and a plurality of variable sweep wings for directional control of the projectile. In various embodiments the plurality of variable sweep wings each have a first end coupled to a wing actuator configured to rotate a second end portion between and including a first position, where the wings are oriented generally parallel to the central axis of the projectile to a second position, where the lengthwise wing axis of the plurality of wings are oriented generally perpendicular to the central axis of the projectile.
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公开(公告)号：US11946727B2
公开(公告)日：2024-04-02
申请号：US17765148
申请日：2020-10-08
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Jacob Rovinsky
CPC classification number: F42B10/668 , F41F3/04 , F41G7/36 , F42B10/26
Abstract: The presently disclosed subject matter includes a system and a method for launching a projectile towards a target, wherein the system comprises a control circuitry, a booster engine, and one or more thrusters adapted to be connected to the projectile and capable of being spun during launch around a longitudinal axis of the projectile, the control circuitry being operatively connected to the one or more thrusters; wherein responsive to ignition of propellant stowed in a combustion chamber of the booster engine, the booster engine causes the projectile to launch from its cell; following launch of the projectile, cause the projectile to turn at a certain rate and a certain azimuth.
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公开(公告)号：US11898827B2
公开(公告)日：2024-02-13
申请号：US17893566
申请日：2022-08-23
Applicant: FSG Enterprises
Inventor： Frederick Scott Gizowski
Abstract: A projectile fired from a weapon which has a bore with inner rifling, having a point and a base which are disposed within a sleeve such that the point and base of the projectile rotate independently of the sleeve when fired from a gun or similar weapon designed to discharge projectiles or similar material.
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公开(公告)号：US20230384068A1
公开(公告)日：2023-11-30
申请号：US18097520
申请日：2023-01-17
Applicant: Jamie George McWilliam
Inventor： Jamie George McWilliam , Charles Edmond McWilliam, SR.
Abstract: The present invention relates to increasing the flight stability of a bullet in subsonic flight. The bullet may incorporate features that impart additional angular momentum during flight. Helical fins may be configured such that laminar airflow over the bullet during flight increases rotational forces, thus increasing the angular momentum of the bullet and stabilizing it during flight. The fins may be self-forming during the use of the bullet or may be formed during manufacturing.
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5.发明公开公开(公告)号：US20230243628A1
公开(公告)日：2023-08-03
申请号：US17972939
申请日：2022-10-25
Inventor： Curtis B. Rath
Abstract: The system and method of mixing pitch and roll commands from a flight control computer to produce fin deflections applied to as few as two fins to simultaneously produce both a rolling moment and a pitching moment. The system may be mechanical or digital where actuators can be linear or rotary, digital or analog. Deflections of the fins are generated which produce pitch and roll moments where addition of pitch and roll commands determines deflection commands to be sent to a first fin and subtraction of pitch and roll commands determines deflection commands to be sent to a second fin.
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Patent Agency Ranking
公开(公告)号：US11598615B1
公开(公告)日：2023-03-07
申请号：US15998269
申请日：2018-07-26
Applicant: Northrop Grumman Systems Corporation
Inventor： Michael J. Wilson
Abstract: A guided projectile having a nose portion, a body portion, a tail portion, and a central axis. In various embodiments the projectile includes a control support portion and a collar assembly pivotally mounted to the control support portion. In various embodiments the collar assembly includes a collar having an exterior sidewall with a plurality of fixed aerodynamic surfaces thereon for spinning the collar and a plurality of variable sweep wings for directional control of the projectile. In various embodiments the plurality of variable sweep wings each have a first end coupled to a wing actuator configured to rotate a second end portion between and including a first position, where the wings are oriented generally parallel to the central axis of the projectile to a second position, where the lengthwise wing axis of the plurality of wings are oriented generally perpendicular to the central axis of the projectile.
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公开(公告)号：US11578957B2
公开(公告)日：2023-02-14
申请号：US16887724
申请日：2020-05-29
Inventor： John T. Willits , Sachin N. Dekate , Gary L. Viviani
Abstract: A method includes determining a rotational position of a rotating projectile as a function of an orientation of a sensor on the rotating projectile. The method also includes actuating a steering mechanism on the rotating projectile at the determined rotational position. The method also includes altering the trajectory of the rotating projectile.
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公开(公告)号：US20210285747A1
公开(公告)日：2021-09-16
申请号：US16887724
申请日：2020-05-29
Inventor： John T. Willits , Sachin N. Dekate , Gary L. Viviani
Abstract: A method includes determining a rotational position of a rotating projectile as a function of an orientation of a sensor on the rotating projectile. The method also includes actuating a steering mechanism on the rotating projectile at the determined rotational position. The method also includes altering the trajectory of the rotating projectile.
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公开(公告)号：US20200340787A1
公开(公告)日：2020-10-29
申请号：US16960971
申请日：2019-08-30
Inventor： Paul D. Zemany , Matthew F. Chrobak
IPC: F42B10/26
Abstract: A guided projectile including a precision guidance munition assembly utilizes angular rate sensors to sample a first angular velocity of the precision guidance munition assembly from the first angular rate sensor at a first time, sample a second angular velocity of the precision guidance munition assembly from the second angular rate sensor at the first time, generate a coning command based, at least in part, on the first angular velocity and the second angular velocity, and apply the coning command to the canard assembly. The range may be decreased or increased based on the coning commands.
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公开(公告)号：US20200056866A1
公开(公告)日：2020-02-20
申请号：US16662677
申请日：2019-10-24
Applicant: James F. Brown
Inventor： James F. Brown , Thomas Ott
IPC: F42B10/28 , F42B10/02 , B22F5/10 , C22C32/00 , B22F5/04 , F42B12/74 , F42B15/00 , F42B10/30 , F42B10/24 , F42B30/02 , B22F5/00 , F42B10/22 , F42B33/00 , B33Y10/00 , B33Y80/00 , F42B10/26 , F42B14/06 , B22F3/10 , B22F3/105
Abstract: A projectile apparatus is provided that includes a projectile, a propellant, and optional components such as a wading, a sabot, and an intermediary device. The projectile can be fired through a barrel having a smooth bore. A sabot is provided that can include molded features, for example, a base portion and a plurality of petal portions defining, in-part, a volume for accommodating a projectile. The sabot and wadding can include molded features that control and direct gases produced by the propellant. The apparatus can convert gas pressure or gas velocity into a high rate of projectile spin. The projectile has long-range accuracy due to a high or sustainable velocity and high rate of spin.
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