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公开(公告)号：US11835319B2
公开(公告)日：2023-12-05
申请号：US17664679
申请日：2022-05-24
Applicant: The Boeing Company
Inventor： Brian Edward Est , Leslie Leon Palmer
Abstract: A guided projectile including a projectile housing, a first sensor, and an air brake detachably coupled to the projectile housing. The air brake is deployable from a flight configuration to a braking configuration. A processor is configured to monitor, based on data received from the first sensor, a proximity of the at least one intercepting object relative to the guided projectile, wherein the guided projectile is configured to advance towards a target location on a first target trajectory. The processor is also configured to deploy the air brake to cause the guided projectile to veer from the first target trajectory to evade the at least one intercepting object, and detach the air brake from the guided projectile to enable the guided projectile to advance on a second target trajectory that is offset from the first target trajectory, wherein the first target trajectory and the second target trajectory have the same target location.
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公开(公告)号：US20230045482A1
公开(公告)日：2023-02-09
申请号：US17664679
申请日：2022-05-24
Applicant: The Boeing Company
Inventor： Brian Edward Est , Leslie Leon Palmer
Abstract: A guided projectile including a projectile housing, a first sensor, and an air brake detachably coupled to the projectile housing. The air brake is deployable from a flight configuration to a braking configuration. A processor is configured to monitor, based on data received from the first sensor, a proximity of the at least one intercepting object relative to the guided projectile, wherein the guided projectile is configured to advance towards a target location on a first target trajectory. The processor is also configured to deploy the air brake to cause the guided projectile to veer from the first target trajectory to evade the at least one intercepting object, and detach the air brake from the guided projectile to enable the guided projectile to advance on a second target trajectory that is offset from the first target trajectory, wherein the first target trajectory and the second target trajectory have the same target location.
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公开(公告)号：US20230003494A1
公开(公告)日：2023-01-05
申请号：US17781799
申请日：2020-12-01
Applicant: BAE SYSTEMS BOFORS AB
Inventor： Anders HAGBERG , Thomas PETTERSSON
IPC: F42B10/50
Abstract: In a brake for detachable arrangement on projectiles, the brake is configured with a surface which is situated in the direction of travel of the projectile, where the surface is larger than a surface given by πR2-πr2, where R is the outer radius of the brake and r is the inner radius of the brake. A method for braking projectiles is also provided.
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公开(公告)号：US11220324B2
公开(公告)日：2022-01-11
申请号：US16478221
申请日：2018-02-01
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Shahar Bar Hillel , Saar Shragai
Abstract: Apparatuses for a projectile are provided, the projectile configured for weapons band launching, examples of the apparatus comprising a body, an inflation system and external walls. The body is inflatable by the inflation system, from a deflated configuration having a first volume to an inflated configuration having a second volume, greater than the first volume. The external walls are deployable from an undeployed configuration to a deployed configuration responsive to the body being inflated. In the undeployed configuration and at an operating airspeed, the center of pressure is located at a first position with respect to the projectile. In the deployed configuration the external walls provide a deployed external surface geometry exposed to an airflow corresponding to the operating airspeed, such that the center of pressure is located at a second position with respect to the projectile, different from the first position.
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公开(公告)号：US10408586B1
公开(公告)日：2019-09-10
申请号：US15718262
申请日：2017-09-28
Inventor： Mario E. DeAngelis
Abstract: A non-lethal projectile comprises a carrier with a deployable payload to allow for effective performance at both long and short ranges. The non-lethal projectile is fired from a launcher. At a predetermined range, the carrier opens thereby deploying the payload. The payload may further comprise a drogue chute to reduce the kinetic energy of the payload to a non-lethal level. Alternatively, the inherent drag coefficient of the payload may enable sufficient reduction of kinetic energy without the need for a drogue chute. The deployed petals of the carrier serve as drag surfaces for the carrier, thereby reducing the kinetic energy of the carrier to a non-lethal level.
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Patent Agency Ranking
公开(公告)号：US5153371A
公开(公告)日：1992-10-06
申请号：US833258
申请日：1992-02-10
Applicant: John C. Grau , William G. Kuhnle , Arthur J. Fiorellini
Inventor： John C. Grau , William G. Kuhnle , Arthur J. Fiorellini
IPC: F42B10/50
CPC classification number: F42B10/50
Abstract: A weapon arranged to travel in a given orientation when in flight, has a body and a ribbon. The body has a payload casing and a spindle rotatably mounted at the rear of the payload casing. The ribbon is formed into a flexible loop for trailing behind the body in flight. This ribbon is attached to the spindle. The ribbon has an impelling surface shaped to apply a torque to the spindle when in flight.
Abstract translation: 在飞行中布置成以特定方向行进的武器，具有身体和丝带。 主体具有有效负载外壳和可转动地安装在有效负载外壳后部的主轴。 丝带形成一个柔性环，用于在飞行中后跟身体。 该色带连接到主轴。 带状物具有推力表面，其形状可在飞行时向主轴施加扭矩。
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公开(公告)号：US5088414A
公开(公告)日：1992-02-18
申请号：US599852
申请日：1990-10-19
Applicant: Reijo Vesa
Inventor： Reijo Vesa
IPC: F42B10/50
CPC classification number: F42B10/50
Abstract: A subwarhead adapted for separation from a missile, for example a carrier shell or the like, over a target area comprises an active part, a target detector and an arrangement which imparts a rotation to the subwarhead for scanning of the target area in a helical pattern during the descent of the subwarhead towards the target area, the target detector being arranged displaceably in order to allow a free view at the side of the active part. Two diametrically situated aerofoils are pivotable, each on its own shaft situated in a plane which is at right angles to the axis of symmetry of the active part, from a folded position, in which the aerofoils connect with the outer surface of the subwarhead, to a position folded out by 90.degree., in which the two aerofoils form a braking area for controlling the rate of descent of the subwarhead.
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公开(公告)号：US5063849A
公开(公告)日：1991-11-12
申请号：US599851
申请日：1990-10-19
Applicant: Jan Axinger
Inventor： Jan Axinger
CPC classification number: F42B30/006 , F42B10/50
Abstract: A subwarhead which is adapted to be separated from a missile over a target area comprises an active part, a target detector and an aerofoil, the target detector and the aerofoil being pivotably mounted each on its own bearing shaft parallel with the line of symmetry of the active part in order to allow pivoting out of the target detector and of the aerofoil from a folded position to an unfolded position at the side of the active part in order to allow a controlled movement of scanning of the target area. Both the target detector and the aerofoil are provided with one or more displaceably arranged additional aerofoils for the purpose of increasing the braking area of the subwarhead in order to reduce the descent rate.
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公开(公告)号：US4958565A
公开(公告)日：1990-09-25
申请号：US198512
申请日：1988-05-25
Applicant: Mark A. Koch
Inventor： Mark A. Koch
IPC: F42B10/50
CPC classification number: F42B10/50
Abstract: A decelerator structure for attachment to a munition to be deployed formed of a first triangular section of cloth with apexes and straight sides to provide a back wall and a second equally shaped and sized section of material to form a front wall with the sections joined and having scoops at the apexes on the front wall with openings inside the scoops with a central anchor on the front wall so that the walls expand equally due to inner air pressure to form a rounded rear wall and a rounded forward wall with straight sides.
Abstract translation: 一种用于附接到待部署的弹药的减速器结构，由具有顶点和直边的第一三角形布料形成，以提供后壁和第二等同形状和尺寸的材料部分，以形成前壁，所述部分连接并具有 在前壁顶部的勺子上，勺内有开口，前壁上有一个中心锚杆，因此由于内部空气压力，这些壁面均匀膨胀，形成一个圆形后壁和一个带有直边的圆形前壁。
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公开(公告)号：US4856737A
公开(公告)日：1989-08-15
申请号：US101330
申请日：1987-09-25
Applicant: Alexey T. Zacharin
Inventor： Alexey T. Zacharin
Abstract: The present invention relates to a new and unique structure in a collapsible decelerator for aerial bodies launched from a high velocity vehicle and designed to provide a high drag stabilizer capable of withstanding release in air stream velocities from subsonic to supersonic. The decelerator preferably includes a hollow inflatable star, the outermost points of which have hooded valve openings through which regulated airflow enters and inflates the star to decelerate the body to which it is attached. The new and unique capability comprises an angular offset of each air scoop to create desired rotational speed in the selected direction.The amount of angular offset and protrusion into the air stream controls the magnitude of spin rate, the direction of angular offset controls the direction of spin.
Abstract translation: 本发明涉及一种用于从高速车辆发射的天体的可折叠减速器中的新颖且独特的结构，并且设计用于提供能够承受从亚音速到超音速的空气流速度释放的高阻力稳定器。 减速器优选地包括中空的可充气星，其最外点具有连接的阀开口，经调节的气流通过该孔开口并使星形体膨胀，以使其附接到的身体减速。 新的和独特的能力包括每个空气勺的角度偏移以在所选方向上产生期望的转速。 角度偏移和向空气流中突出的量控制旋转速率的大小，角度偏移的方向控制旋转方向。
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