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1. 发明申请

WO2022164467A1 AERO-ASSISTED MISSILE FIN OR WING DEPLOYMENT SYSTEM 审中-公开
公开(公告)号：WO2022164467A1
公开(公告)日：2022-08-04
申请号：PCT/US2021/027598
申请日：2021-04-16
申请人： RAYTHEON COMPANY
发明人： BUGGE, John F. , EDGAR, Byron T.
IPC分类号： F42B10/14
摘要： A projectile and method of deploying a projectile includes a wing deployment system for deploying a wing of a projectile. The wing deployment system includes a stored energy release mechanism that is activated to generate an initial range of motion of the wing and a panel arranged on the wing and configured to cause an angular acceleration of the wing during the initial range of motion of the wing.

2. 发明申请

WO2022055766A1 ADDITIVELY MANUFACTURED ELLIPTICAL BIFURCATING TORSION SPRING 审中-公开
公开(公告)号：WO2022055766A1
公开(公告)日：2022-03-17
申请号：PCT/US2021/048629
申请日：2021-09-01
申请人： BAE SYSTEMS INFORMATION AND ELECTRONIC SYSTEMS INTEGRATION INC.
发明人： CAMPBELL, Benjamin K. , CHADBOURNE, Robert , DIPPEL, Ryan , SHAW, Michael J.
IPC分类号： F42B10/14 , F42B10/64 , F42B15/01 , B64C1/30 , B64C5/00 , F42B10/00
摘要： A 3D printed additively manufactured (AM) elliptical bifurcating torsion flexure assembly system includes a base section; elliptical bifurcating torsion springs, each including a bifurcated legs section supported by the base; a bifurcated elliptical torsion spring section contiguous with the bifurcated legs section; and a single upper section contiguous with the elliptical torsion spring section. The single upper section includes a connection component, and the device material includes Hot Isostatic Pressing (HIP) heat-treated Ti6A14V. The elliptical bifurcating torsion flexure assembly is printed as one part by a 3D additive manufacturing process, and the bifurcation maintains consistent balance while being torqued. The stiffness-spring rate of the device is at least partly controlled by varying cross-sectional shape and diameters by the 3D additive manufacturing printing.

3. 发明申请

WO2022005363A1 A WING ARRANGEMENT, A PROJECTILE, A METHOD FOR DEPLOYING A WING BLADE, A USE AND A METHOD FOR ASSEMBLY 审中-公开
公开(公告)号：WO2022005363A1
公开(公告)日：2022-01-06
申请号：PCT/SE2021/050598
申请日：2021-06-17
申请人： SAAB AB
发明人： BERGGREN, Joakim , BROCKER, David
IPC分类号： F42B10/14
摘要： The invention relates to a wing arrangement (10) for a projectile (1). The wing arrangement (10) comprising: a wing shaft (20) extending longitudinally between a proximal end (21) and a distal end (22) along a wing shaft axis (R), the proximal end (21) being configured to be inserted into a wing shaft aperture (6) in a circumferential wall (2) of the projectile (1), the wing shaft (20) being rotatable around the wing shaft axis (R); a wing blade (30) connected to the distal end (22) of the wing shaft (20); a deployment arrangement (40) configured to control a rotational movement of the wing shaft (20) around the wing shaft axis (R), whereby the wing blade (30) is deployed from a folded state to a deployed state. The deployment arrangement (40) comprising a pre- tensioned torsion spring (41) arranged coaxially with the wing shaft (20), wherein a first end (42) of the torsion spring (41) is coupled to the wing shaft (20) and a second end (43) of the torsion spring (41) is configured to be coupled to the circumferential wall (2) of the projectile (1). The invention also relates to a method for deploying a wing blade (30), use of a wing arrangement (10), a projectile (1) and a method for assembly of a wing arrangement (10).

4. 发明申请

WO2021251930A2 A CONTROL ACTUATION ASSEMBLY FOR A MINIATURE, GUIDED MISSILE 审中-公开
公开(公告)号：WO2021251930A2
公开(公告)日：2021-12-16
申请号：PCT/TR2021/050543
申请日：2021-06-07
申请人： ROKETSAN ROKET SANAYİİ TİCARET A. Ş.
发明人： GÜNGÖR, Mahmut Emre , TANIKER, Semih , SİLİK, Yusuf
IPC分类号： F42B10/14 , F42B10/64 , B64C3/56
摘要： The present invention relates to a control actuation assembly for a miniature, guided missile comprising a seat (20) having a support plate (22) that is transversally mounted to an inner chamber limited by a hollow, elongated main body (10); and at least one wing pair (40) having first and second aerodynamic control members (41, 43) that are adjacent to one another such that a distal end (47) thereof is seated into the inner chamber when it is in a folded position, and that are opposite to one another, that are supported by the seat (20) by means of respective pins (44) fixing them on an extension axis from a proximal end (46) thereof such that it extends outward from the main body (10) when in a deployment position. Control actuation system comprises a threaded rod member (65) that is arranged in close proximity of the wing pair (40) and that converts the shaft (64) linear motion of motor (60), which comprises a shaft (64) that extends towards the wing pair (40) inside the inner chamber, to rotational motion on the shaft (64) axis; and a pendulum arm (82) that is adapted on the wing pair (40) such that it rotates on the pin (44) axis on one hand and that it is seated therein so as to rotate a protrusion (66) of the threaded rod member (65), which extends outwards radially on the other hand.

5. 发明申请

WO2020260009A1 GESCHOSS 审中-公开
公开(公告)号：WO2020260009A1
公开(公告)日：2020-12-30
申请号：PCT/EP2020/065949
申请日：2020-06-09
申请人： RHEINMETALL WAFFE MUNITION GMBH
发明人： HEITMANN, Thomas
IPC分类号： F42B10/14 , F42B10/06
摘要： Die Erfindung betrifft ein abstreifbares Leitwerk (4) für ein Geschoss (1), insbesondere für ein Vollkalibergeschoss. Um zu verhindern, dass eine nach hinten gerichtete Wirkung durch das Leitwerk bzw. das Leitwerkteil (4) reduziert wird, wird vorgeschlagen, eine Schnittstelle (21) zum Trennen des Geschosskopfs (2) vom Leitwerkteil (4) vorzusehen. Die Schnittstelle (21) umfasst ein Übergangs- bzw. Übertragungsteil (8). Der Geschosskopf (2) umfasst eine Hülle (3) zur Aufnahme der Wirkmasse (19). Die Hülle (3) und das Übergangsteil (8) bilden ihrerseits die Schnittstelle (21). Dabei sind die Hülle (3) und das Übergangsteil (8) in ihrer gemeinsamen Verbindungszone (9) konische ausgestaltet bzw. geformt (10, 11). Innerhalb der Schnittstelle (21) sind Verriegelungsnuten (12, 13) sowie Einlaufnuten (14, 15) vorgesehen. Die Nuten (12, 13, 14, 15) sind am Außenumfang des Übergangsteils (8) bzw. innenseitig in der Hülle (3) eingebracht. Das Übergangsteil (8) weist ein Gewinde (16) auf, welches mit einem Gewinde des Leitwerkteils (4) verbindbar ist. Die beiden Einlaufnuten (14, 15) bilden übereinander stehend eine gemeinsame Einlaufnut (17). Die Verriegelungsnuten (12, 13) sind ihrerseits deckungsgleich, derart, dass diese einen Verriegelungszylinder (18) gemeinsam aufnehmen können. Mit Durchschlag des Geschosses (1) in einem Ziel bricht der Verriegelungszylinder (18), wodurch der Geschosskopf (2) vom Leitwerkteil (4) getrennt wird. Leitwerkteil (4) und Übergangsteil (8) verbleiben im günstigsten Fall im Ziel hängen, während der Geschosskopf (2) im Ziel seine Wirkung in allen Richtungen entfalten kann.

6. 发明申请

WO2020047367A1 BALLISTIC RANGE ADJUSTMENT USING CONING COMMANDS 审中-公开
公开(公告)号：WO2020047367A1
公开(公告)日：2020-03-05
申请号：PCT/US2019/048984
申请日：2019-08-30
申请人： BAE SYSTEMS INFORMATION AND ELECTRONIC SYSTEMS INTEGRATION INC.
发明人： ZEMANY, Paul, D. , CHROBAK, Matthew, F.
IPC分类号： F42B10/02 , B64C29/00 , B64C39/00 , B64C39/12 , F42B10/00 , F42B10/14
摘要： 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.

7. 发明申请

WO2019084629A1 SITUATIONAL AWARENESS, NAVIGATION AND COMMUNICATION FOR LOW-COST, GUN-LAUNCHED UAVS 审中-公开
公开(公告)号：WO2019084629A1
公开(公告)日：2019-05-09
申请号：PCT/AU2018/051196
申请日：2018-11-05
申请人： DEFENDTEX PTY LTD
发明人： REDDY, Travis , CAHILL, Damien , GHORBANI, Kamran , BAUM, Thomas
IPC分类号： G01S13/89 , G01S13/90 , G01S19/38 , G01S19/48 , B64C3/56 , F42B10/14 , H01Q3/02
摘要： An unmanned aerial vehicle (UAV), comprising: a projectile body; a propulsion system foldably deployable from the projectile body; a synthetic aperture radar (SAR) system comprising a SAR antenna fixedly and non-rotatably arranged on the projectile body; and a control system connected to the propulsion system and the SAR system, wherein the control system is configured to control: orientation of the projectile body and thus orientation of the SAR antenna; and operation of the SAR system so that the SAR system is selectively operable in one or more of: a situational awareness mode; a navigation mode; and a communication mode.

8. 发明申请

WO2018015367A1 PROJECTILE COMPRENANT UN DISPOSITIF DE DÉPLOIEMENT D`UNE VOILURE OU AILETTE 审中-公开
标题翻译：使用设备或部署D`UNE翼翼SHOT
公开(公告)号：WO2018015367A1
公开(公告)日：2018-01-25
申请号：PCT/EP2017/068092
申请日：2017-07-18
申请人： NEXTER MUNITIONS
发明人： PINOTEAU, Sylvain
IPC分类号： F42B10/14 , F42B10/02
摘要： La présente invention concerne un projectile (P) comportant un corps (PO) possédant un axe longitudinal (L) et une portion intermédiaire comprenant un dispositif (1) de déploiement de voilures ou ailettes comportant au moins un nombre N, au moins égal à trois, de voilures (2) ou ailettes aptes à être déployées, le processus de déploiement comprenant au moins deux phases, une première phase de déploiement où chaque voilure ou ailette passe d'une position tangentielle au corps du projectile et parallèle à l'axe longitudinal (L) à une position semi-déployée, et une seconde phase de déploiement avec le passage de chaque voilure de la position semi-déployée, à une position déployée où elle est perpendiculaire au corps du projectile, ledit dispositif de déploiement des voilures est configuré de manière à synchroniser le déploiement des voilures ou ailettes dans la seconde phase.
摘要翻译：
公关é感觉发明涉及一种包括本体（PO）POSSé荷兰国际集团的纵向轴线（L）和部分中间体é日记包括设备的射弹（P）（1）取消部署翅膀或鳍至少有一个数字N，至少＆gal？三，翼（2）或翅膀适合; ＆Ecirc;被去策略éES，DE部署的，其包含至少两个相，一个Premi＆egrave过程;再相Dé部署O＆ugrave; 每个翼或翅片从切线位置到弹丸和主体通过并行＆egrave;所述＆agrave; 纵轴（L）＆alpha; 半-DE位置;策略ée和第二相位Dé部署与半-DE位置的每一个翼的通过;策略éE，＆agrave; 一个开放的位置o＆rd; 它垂直于射弹的主体，所述翼断裂装置被配置; 以...的方式同步第二阶段的机翼或机翼部署。

9. 发明申请

WO2017105586A1 BASE DRAG REDUCTION FAIRING USING SHAPE MEMORY MATERIALS 审中-公开
标题翻译：使用形状记忆材料进行基础减载
公开(公告)号：WO2017105586A1
公开(公告)日：2017-06-22
申请号：PCT/US2016/055229
申请日：2016-10-03
申请人： RAYTHEON COMPANY
发明人： SUMMERS, Matthew H. , KOEHLER, Frederick B. , DANFORTH, Jeremy C. , VILLARREAL, James K.
IPC分类号： F42B10/14 , F42B10/40 , F42B10/44
CPC分类号： F42B10/38 , B63G8/00 , F42B10/14 , F42B10/40 , F42B10/44
摘要： A device (100) is provided. The device includes at least one SMM component (115, 120, 130) fabricated from a shape memory material (SMM). The SMM component is configured to change shape in response to receiving a stimulus. The SMM component is also configured to deploy from a device body (105) of the device allowing the device to change shape in an advantageous way. A method (1000) implemented by a device (100) is also provided. The method includes changing (1010) a shape of an SMM component (115, 120, 130) of the device in response to receiving a stimulus. The SMM component is fabricated from an SMM. The method also includes deploying (1015) the SMM component from a device body (105) of the device allowing the device to change shape in an advantageous way.
摘要翻译：提供了一种设备（100）。该装置包括由形状记忆材料（SMM）制造的至少一个SMM部件（115,120,130）。 SMM组件配置为响应接收刺激而改变形状。 SMM部件还被配置为从装置的装置主体（105）展开，允许装置以有利的方式改变形状。还提供了由设备（100）实现的方法（1000）。该方法包括响应于接收刺激而改变（1010）设备的SMM组件（115,120,130）的形状。 SMM组件是由SMM制造的。该方法还包括从设备的设备主体（105）部署（1015）SMM组件，允许设备以有利的方式改变形状。

10. 发明申请

WO2011002530A3 REINFORCED INFLATABLE WINGS FOR FITMENT-CONSTRAINED AIR VEHICLES 审中-公开
标题翻译：用于配装有限的空气车辆的加强的可充气翼
公开(公告)号：WO2011002530A3
公开(公告)日：2011-02-24
申请号：PCT/US2010024307
申请日：2010-02-16
申请人： RAYTHEON CO , SANDERSON TERRY M , EISENTRAUT RUDY A , HATFIELD DAVID B
发明人： SANDERSON TERRY M , EISENTRAUT RUDY A , HATFIELD DAVID B
IPC分类号： F42B10/14 , F42B10/20
CPC分类号： B64C3/30 , B64C2201/102 , B64C2201/105 , F42B10/14 , F42B10/146 , F42B10/20
摘要： A reinforced inflatable wing improves the tolerance of the OML and reinforces the wing in at least the high load areas. This approach provides fitment constrained air vehicles with wings having increased surface area to improve flight endurance or aerodynamic control. A wing box (20,108, 208, 308, 400) forms a first portion of the wing. A skin having a plurality of rigid plates (40,122, 222, 322, 406) affixed thereto is inflated to form a second portion of the wing to either increase the chord length or lengthen the wing span. The skin is suitably inflated with foam to form a solid wing.
摘要翻译：增强的充气翼改善了OML的公差，并加强了至少在高负载区域中的机翼。这种方法提供具有增加的表面面积的具有翼的装备受限的空中车辆，以改善飞行耐力或空气动力学控制。机翼箱（20,108,208,308,400）形成机翼的第一部分。具有固定到其上的多个刚性板（40,122,222,322,406）的皮肤被充气以形成机翼的第二部分，以增加弦长或延长机翼跨度。皮肤适当地用泡沫充气以形成固体翼。

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