公开(公告)号：US11994367B2

公开(公告)日：2024-05-28

申请号：US17728624

申请日：2022-04-25

Applicant: Northrop Grumman Systems Corporation

Inventor： James Kolanek ,  Behshad Baseghi ,  David Sharpin ,  Anthony Visco ,  Falin Shieh

IPC: F41G7/34 ,  F41G7/00 ,  F41G7/30 ,  F41H11/02 ,  F42B10/66 ,  F42B15/01 ,  F42B15/10 ,  G05D1/00 ,  G05D1/08 ,  G06T7/246 ,  F42B15/00

CPC classification number: F41G7/34 ,  F41G7/007 ,  F41G7/303 ,  F41H11/02 ,  F42B10/66 ,  F42B10/661 ,  F42B15/01 ,  F42B15/105 ,  G05D1/0808 ,  G06T7/246

Abstract: 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.

公开(公告)号：US20170153097A1

公开(公告)日：2017-06-01

申请号：US15359295

申请日：2016-11-22

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： Alon Kahana

IPC: F42B15/01 ,  B64C15/14 ,  B64C5/06 ,  B64C39/02

CPC classification number: F42B15/36 ,  F42B10/661

Abstract: A reaction control system (RCS) is provided for use with an air vehicle having a nose portion and a center of gravity aft of the nose portion. The RCS includes a belt element configured for selectively securing the RCS to the nose portion, and also includes a plurality of micro-rocket modules affixed to the belt element, each micro-rocket module being configured for being selectively activated to provide corresponding control moments to the air vehicle when secured to the nose portion thereof. A corresponding air vehicle, and a method for modifying an air vehicle, are also provided.

公开(公告)号：US09170070B2

公开(公告)日：2015-10-27

申请号：US13455831

申请日：2012-04-25

Applicant: David Sharpin ,  Jim Kolanek ,  Mark A. Cvetnic ,  Mike Hutchings ,  James Tennison ,  Kent Carl Nelson ,  Harold Kregg Hunsberger ,  Behshad Baseghi

Inventor： David Sharpin ,  Jim Kolanek ,  Mark A. Cvetnic ,  Mike Hutchings ,  James Tennison ,  Kent Carl Nelson ,  Harold Kregg Hunsberger ,  Behshad Baseghi

IPC: F42B10/60 ,  F42B10/66 ,  F41H11/02 ,  F41G7/00 ,  F42B10/00 ,  F41H11/00

CPC classification number: F41H11/02 ,  F41G7/00 ,  F42B10/14 ,  F42B10/26 ,  F42B10/661 ,  F42B15/01 ,  G06T7/246

Abstract: Embodiments include active protection systems and methods for an aerial platform. An onboard system includes one or more radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the plurality of 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 a rocket motor to accelerate the eject vehicle along an intercept vector, alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, and divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector. The eject vehicle activates at least one of the alignment thrusters responsive to the intercept vector.

Abstract translation: 实施例包括用于空中平台的主动保护系统和方法。 车载系统包括一个或多个雷达模块，检测空中平台的威胁范围内的飞行器，并且确定多个空中飞行器中的任何一个是空中威胁。 车载系统还确定到空中威胁的拦截矢量，将拦截矢量传达到弹出车辆，并使弹出车辆从空中平台弹出以拦截空中威胁。 喷射车辆包括火箭发动机，用于沿着拦截矢量加速喷射车辆，对准推进器以使喷射车辆的纵向轴线旋转以与拦截矢量基本对齐，并且使推进器转向以使喷射车辆沿大致垂直于 截距矢量。 排出车辆响应于拦截矢量激活对准推进器中的至少一个。

公开(公告)号：US20140137539A1

公开(公告)日：2014-05-22

申请号：US13680564

申请日：2012-11-19

Applicant: RAYTHEON COMPANY

Inventor： Jeremy C. Danforth ,  Gavin Buttigieg ,  Brian J. Lukow ,  Henri Y. Kim

IPC: F42B10/66

CPC classification number: F42B10/661 ,  F02K7/02 ,  F02K9/08 ,  F42B3/04

Abstract: A detonation thrust-producing device includes an explosive located in a recess in an external surface of a body. Detonation of the explosive expels material out of the recess, providing thrust to the body in an opposite direction. A mass, such as a metal disk, may be placed blocking or covering the external opening. The body may be a part of a vehicle, such as an airborne projectile. The thrust-producing device may include multiple detonation motors arrayed around the body, capable of being individually or multiply detonated. Such thrust-producing devices may be used for attitude adjustment, steering, or other control of the flight of the projectile or other air vehicle. The detonation thrust-producing devices have the advantage of a faster-response time than propellant-based devices, and do not need the nozzles that are used with many propellant-based devices.

Abstract translation: 爆炸推力产生装置包括位于身体的外表面的凹部中的炸药。 爆炸物的爆炸将材料排出凹槽，向相反方向的身体提供推力。 可以将诸如金属盘的质量块放置成阻挡或覆盖外部开口。 身体可能是车辆的一部分，例如机载抛射体。 推力产生装置可以包括围绕身体排列的多个爆震电动机，能够单独或多次引爆。 这种推力产生装置可以用于姿态调节，转向或其他控制飞弹或其他空中飞行器的飞行。 爆炸推力产生装置具有比基于推进剂的装置更快的响应时间的优点，并且不需要与许多基于推进剂的装置一起使用的喷嘴。

公开(公告)号：US08716640B2

公开(公告)日：2014-05-06

申请号：US12659405

申请日：2010-03-08

Applicant: Christian Baras ,  Denis Spitzer ,  Marc Comet ,  Fabrice Ciszek ,  Frederic Sourgen

Inventor： Christian Baras ,  Denis Spitzer ,  Marc Comet ,  Fabrice Ciszek ,  Frederic Sourgen

IPC: F42B10/00 ,  F42B15/01

CPC classification number: F42B10/661

Abstract: The invention concerns the field of devices for improving the piloting of projectiles More specifically, the object of the invention is a piloting device for a missile or a projectile, for example, of small caliber, especially on the order of 40 mm, which has a lateral main surface with a nose at the level of one of its extremities, whereby said device includes at least one cavity consisting of a combustion chamber and filled, at least partially, by an explosive powder, and means of initiation of this explosive powder, and thereby the explosive powder includes nanothermites or gas-generating nanothermites.

Abstract translation: 本发明涉及用于改进射弹导弹的装置领域更具体地，本发明的目的是用于导弹或射弹的引导装置，例如小口径，特别是大约40mm的导弹或射弹，其具有 侧面主表面在其四肢之一处具有鼻子，由此所述装置包括至少一个由燃烧室组成的空腔，至少部分地由爆炸性粉末填充，以及该爆炸性粉末的引发装置，以及 因此爆炸性粉末包括纳米薄层或产生气体的纳米层。

公开(公告)号：US08546736B2

公开(公告)日：2013-10-01

申请号：US13109706

申请日：2011-05-17

Applicant: Richard Dryer

Inventor： Richard Dryer

IPC: F41G7/00

CPC classification number: F42B15/01 ,  F42B10/661

Abstract: A modular artillery projectile and method of engaging a target. A modular artillery projectile may include a payload module, a guidance module coupled to the payload module and a rear module coupled to the guidance module. The payload module may be selected from a plurality of interchangeable payload modules containing different payloads. The guidance module may include a transverse propulsion system to propel the modular artillery projectile transversely to a longitudinal axis of the modular artillery projectile, a global positioning system receiver, and a control system to control the transverse propulsion system responsive to the global positioning system receiver to guide the modular artillery projectile to a predetermined target position.

Abstract translation: 一种模块化的炮弹和一个目标接合的方法。 模块化炮弹可以包括有效载荷模块，耦合到有效载荷模块的引导模块和耦合到引导模块的后模块。 可以从包含不同有效载荷的多个可互换有效载荷模块中选择有效载荷模块。 引导模块可以包括横向推进系统以横向推动模块化炮弹射入模块化射弹的纵向轴线，全球定位系统接收器和控制系统，以响应全球定位系统接收器控制横向推进系统 将模块化炮弹引导到预定的目标位置。

公开(公告)号：US08119958B2

公开(公告)日：2012-02-21

申请号：US12389271

申请日：2009-02-19

Applicant: Christian Adams ,  Kenneth S. Gurley ,  Tara Y. Rohter ,  Patrick A. Nelson

Inventor： Christian Adams ,  Kenneth S. Gurley ,  Tara Y. Rohter ,  Patrick A. Nelson

IPC: F42B15/01 ,  H01H37/76 ,  F42B15/00

CPC classification number: F42B10/661 ,  F41G7/30

Abstract: A matrix of explosive cells can include plural explosive cells formed in an array in a common substrate. Each cell can be formed as a recess filled with explosive material. An ignition device has an addressable ignition source for each cell. This matrix can be used in combination with a projectile guidance system. The projectile guidance system includes an antenna, a transceiver and a control processor. A method of guiding a projectile can include firing a projectile at a target, tracking the projectile and the target, determining a desired change in a flight path of the projectile, transmitting guidance commands to effect the desired change in the projectile's flight path to the projectile, receiving the guidance commands onboard the projectile and selectively igniting an explosive cell in a matrix of addressable explosive cells contained in a common substrate using the guidance commands.

Abstract translation: 爆炸性细胞的基质可以包括在共同的基底中以阵列形成的多个爆炸细胞。 每个电池可以形成为充满爆炸性材料的凹槽。 点火装置具有用于每个电池的可寻址点火源。 该矩阵可与射弹引导系统结合使用。 射弹引导系统包括天线，收发器和控制处理器。 引导射弹的方法可以包括在目标射击射弹，跟踪射弹和目标，确定射弹飞行路径中所需的变化，传递指导命令，以实现弹丸对射弹飞行路径的期望变化 接收射弹的引导命令，并使用引导命令选择性地点燃容纳在共同的基底中的可寻址的爆炸性细胞的矩阵中的爆炸性细胞。

公开(公告)号：US20110179964A1

公开(公告)日：2011-07-28

申请号：US12870843

申请日：2010-08-29

Applicant: Jahangir S. Rastegar ,  Thomas Spinelli

Inventor： Jahangir S. Rastegar ,  Thomas Spinelli

IPC: F42B15/00

CPC classification number: F42B10/661 ,  F42B10/668

Abstract: A ring portion including: a ring body; and one or more actuators formed therein for providing thrust to a projectile and configured for fastening to a shell of an airborne device to form a portion of the shell. The airborne device can be a projectile.

Abstract translation: 环形部分，包括：环体; 以及形成在其中的一个或多个致动器，用于向射弹提供推力并且构造成用于紧固到机载装置的壳体以形成壳体的一部分。 机载装置可以是射弹。

公开(公告)号：US07973270B1

公开(公告)日：2011-07-05

申请号：US12870842

申请日：2010-08-29

Applicant: Jahangir S. Rastegar ,  Thomas Spinelli

Inventor： Jahangir S. Rastegar ,  Thomas Spinelli

IPC: F42B10/20

CPC classification number: F42B10/661

Abstract: A projectile including: a shell; and a movable exterior surface of the shell, the movable exterior surface having one or more actuators for providing thrust to move the movable exterior surface from a first position to a second position.

Abstract translation: 射弹包括：壳; 以及所述外壳的可移动的外表面，所述可移动外表面具有一个或多个致动器，用于提供将所述可移动外表面从第一位置移动到第二位置的推力。

公开(公告)号：US20090072076A1

公开(公告)日：2009-03-19

申请号：US11470900

申请日：2006-09-07

Applicant: ROBERT BRINKERHOFF ,  Michael Mahnken ,  Richard Loehr ,  James Cook

Inventor： ROBERT BRINKERHOFF ,  Michael Mahnken ,  Richard Loehr ,  James Cook

IPC: F42B15/01

CPC classification number: F42B10/661 ,  G05D1/0883

Abstract: A reliable and inexpensive attitude control system uses a plurality of pitch-over thrusters to perform rapid and precise attitude maneuvers for a flight vehicle. The pitch-over thrusters create rotational moments that directly pitch and yaw the flight vehicle. The use of very simple thrusters and control techniques provides for a reliable and cost effective solution. The ability to perform overlapping pitch and yaw maneuvers with single-shot fixed-impulse thrusters provides for high-speed maneuverability.

Abstract translation: 可靠和廉价的姿态控制系统使用多个俯仰推进器来为飞行器执行快速和精确的姿态操纵。 俯仰推进器产生直接俯仰和偏航飞行器的旋转力矩。 使用非常简单的推进器和控制技术提供了可靠且具有成本效益的解决方案。 使用单次固定脉冲推进器执行重叠俯仰和偏航操作的能力提供高速机动性。