公开(公告)号：US11879416B1

公开(公告)日：2024-01-23

申请号：US17930741

申请日：2022-09-09

Applicant: Raytheon Company

Inventor： Brandon J. Napier ,  Scott R. Wells ,  Derek T. Betts ,  Kevin R. Albrecht

IPC: F02K9/90 ,  F42B10/64 ,  F42B10/66 ,  F02K9/80

CPC classification number: F02K9/90 ,  F02K9/80 ,  F42B10/64 ,  F42B10/66 ,  F42B10/665

Abstract: A method of thrust vectoring a missile utilizing jet tabs is presented. Jet tabs are used to create lateral control moments on a missile by rotating tabs into the rocket exhaust plume and changing the thrust deflection angle. The method includes simultaneously rolling the missile during the thrust vector maneuver in order to reduce the maximum tab exposure to the rocket plume. The method enables aggressive pitchover maneuvers while reducing the risk of tab failure due to excessive exposure.

公开(公告)号：US20230243628A1

公开(公告)日：2023-08-03

申请号：US17972939

申请日：2022-10-25

Applicant: BAE Systems Information and Electronic Systems Integration Inc.

Inventor： Curtis B. Rath

IPC: F42B10/26 ,  F42B10/64

CPC classification number: F42B10/26 ,  F42B10/64

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.

公开(公告)号：US20180328348A1

公开(公告)日：2018-11-15

申请号：US16043500

申请日：2018-07-24

Applicant: Marotta Controls, Inc.

Inventor： John E. Albright

IPC: F03G7/06 ,  F42B10/14 ,  F42B10/64

CPC classification number: F03G7/065 ,  F42B10/14 ,  F42B10/64

Abstract: An actuation mechanism used in, for example, a missile assembly is disclosed, as are methods of its use. The actuation mechanism is locked in a first orientation and is unlocked in a second orientation. Locking and unlocking of the actuation mechanism is achieved by way of a locking mechanism that responds to a certain stimulus. In some embodiments, the actuation mechanism is incorporated into a sub-assembly of a missile to assist in controlling the missile's flight.

公开(公告)号：US09945649B2

公开(公告)日：2018-04-17

申请号：US13216467

申请日：2011-08-24

Applicant: Assaf Malul ,  Ziv Moshkovitz

Inventor： Assaf Malul ,  Ziv Moshkovitz

IPC: F42B10/14 ,  F42B10/64

CPC classification number: F42B10/14 ,  F42B10/64

Abstract: An apparatus and method for guiding a cannon shell accurately are disclosed. The apparatus includes two main parts adapted to be installed on the leading end of the cannon shell. The front main part of the apparatus is equipped with at least one pair of fins and is rotatable with respect to the rear main part. The pair of fins is controlled to hold the front main part substantially stable with respect to an external reference frame when the cannon shell rotates as it flies towards its target. Control system is comprised within the apparatus that receives location signals and is adapted to provide guiding control commands to the cannon shell via the fins so as to guide the shell accurately to its preprogrammed target. The control system is adapted to activate the detonation chain of the shell according to preprogrammed mode.

公开(公告)号：US20170343327A1

公开(公告)日：2017-11-30

申请号：US15131228

申请日：2016-04-18

Applicant: DIEHL DEFENCE GMBH & CO. KG

Inventor： HAGEN KEMPAS

IPC: F42B10/64

CPC classification number: F42B10/64

Abstract: A system of missile control surfaces includes a control surface housing, a control surface shaft which is rotatably mounted in the control surface housing, a control surface secured on the control surface shaft, a control surface drive and a coupling unit. The coupling unit couples the control surface drive to the control surface shaft in such a way that a movement of the control surface drive produces a rotation of the control surface shaft. To enable high forces to be applied reliably to a guided missile control surface, it is proposed that the coupling unit has at least one flexible tension element, which is secured on the control surface drive and is rolled up onto the control surface shaft to a certain extent.

公开(公告)号：US09677861B2

公开(公告)日：2017-06-13

申请号：US14701099

申请日：2015-04-30

Applicant: Raytheon Company

Inventor： Richard Ames

IPC: F42B10/64 ,  F42B12/60

CPC classification number: F42B10/64 ,  F42B12/60

Abstract: A projectile having a leading section and a trailing section coupled together to define a structure for delivering a plurality of flechettes. The trailing section includes aerodynamic control surfaces that are deployable to apply an aerodynamic braking force to the trailing section to separate the trailing section from the leading section. The flechettes surround an explosive charge in the leading section such that initiation of the explosive charge outwardly disperses the flechettes after the leading section and the trailing section have separated. The control surfaces optionally also may impart spin to the projectile to assist in dispersing the flechettes. Thus, aerodynamic force is employed to assist in removing the flechettes from their confining structure in the projectile before dispersing them.

公开(公告)号：US20170146328A1

公开(公告)日：2017-05-25

申请号：US15403008

申请日：2017-01-10

Applicant: Jahangir S Rastegar ,  Jacques Fischer

Inventor： Jahangir S Rastegar ,  Jacques Fischer

IPC: F42B10/18 ,  F42B30/08 ,  F42B15/01

CPC classification number: F42B10/18 ,  C06D5/00 ,  F42B10/64 ,  F42B30/08

Abstract: A munition including: a casing having a first portion and the second portion; and an actuator comprising two or more pistons, each of the pistons being connected at a first end to the first portion of the casing and engaged at a second end to the second portion of the casing, each of the pistons being capable of having an extended and retracted position relative to the first and second ends, the retracted position resulting from an activation of each of the two or more pistons; wherein activation of one or more of the two or more pistons moves the first portion relative to the second portion.

公开(公告)号：US20170115103A1

公开(公告)日：2017-04-27

申请号：US15334818

申请日：2016-10-26

Applicant: Institut franco-allemand de recherches de Saint-Louis

Inventor： Dominique Chargelegue ,  Bastien Martinez ,  Philippe Wernert ,  Cedric Decrocq ,  Spilios Theodoulis

IPC: F42B10/26 ,  F42B10/14

CPC classification number: F42B10/26 ,  F42B10/14 ,  F42B10/38 ,  F42B10/64 ,  F42B15/105

Abstract: An increased range guided projectile includes overcaliber lateral moment reducing wings (10) that can be deployed. The lateral moment reducing wings (10) are designed and arranged behind the center of gravity (S) in the tail direction on the guided projectile (1) so that the pitching moment derivative coefficient (Cmα) of the guided projectile (1) is in the range of ±0.5, if the guided projectile (1) has a speed that is in the speed range of Mach 0.4 to 0.8; the lateral moment reducing wings (10) are in their deployed position; and, the canard guide device (20) does not exert any guiding moments.

公开(公告)号：US09482490B2

公开(公告)日：2016-11-01

申请号：US14747152

申请日：2015-06-23

Applicant: Lone Star IP Holdings, LP

Inventor： Steven D. Roemerman

IPC: F41G7/22 ,  F41G7/26 ,  F42B10/64 ,  F42B12/04 ,  F42B12/36 ,  F42B12/44 ,  F42B25/00 ,  F42C15/00 ,  F42C15/20 ,  F41G7/00

CPC classification number: F41G7/226 ,  F41G7/001 ,  F41G7/2246 ,  F41G7/2293 ,  F41G7/26 ,  F42B10/64 ,  F42B12/04 ,  F42B12/362 ,  F42B12/44 ,  F42B25/00 ,  F42C15/005 ,  F42C15/20

Abstract: A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead including destructive elements and a guidance section with a seeker configured to guide the weapon to a target. The seeker includes a detector configured to receive a distorted signal impinging on an objective lens from the target, memory configured to store target criteria and a correction map, and a processor configured to provide a correction signal based on the distorted signal, the target criteria and the correction map to guide the weapon to the target.

公开(公告)号：US09429402B2

公开(公告)日：2016-08-30

申请号：US13869793

申请日：2013-04-24

Applicant: Simmonds Precision Products, Inc.

Inventor： Matthew Plumer ,  Randy Buker

IPC: F42B10/14 ,  F42B10/64 ,  F16H21/54

CPC classification number: F42B10/14 ,  F16H21/54 ,  F42B10/64 ,  Y10T74/18888 ,  Y10T74/18944

Abstract: A multi-stage drive includes a linear actuator configured for linear movement along an actuation axis, and a control surface. The control surface is operatively connected to the linear actuator for rotation about a deployment axis in a deployment stage, and for rotation in a control stage about a control axis that is different from the deployment axis, so that movement of the linear actuator along the actuation axis drives rotation of the control surface in both the deployment stage and in the control stage.

Abstract translation: 多级驱动器包括线性致动器，其构造成沿着致动轴线线性移动，以及控制表面。 控制表面可操作地连接到线性致动器，用于在展开阶段围绕展开轴线旋转，并且在围绕不同于展开轴线的控制轴线的控制阶段中旋转，使得线性致动器沿着致动 轴在驱动阶段和控制阶段驱动控制面的旋转。