公开(公告)号：US20130306789A1

公开(公告)日：2013-11-21

申请号：US13475371

申请日：2012-05-18

Applicant: Suneal Guptaa ,  Jeremy Bley

Inventor： Suneal Guptaa ,  Jeremy Bley

IPC: B64C3/56 ,  B65B43/00 ,  B65D6/00 ,  B65B11/00

CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/102 ,  F42B10/16 ,  Y02T50/14

Abstract: An air vehicle, as well as a method for folding an air vehicle for storage, may include a fuselage and a wing connected to the fuselage. The wing may include two ends positioned opposite from each other, and the wing may be substantially perpendicular to the fuselage. At least one of the ends may define a space therebetween the fuselage and the wing. The space may be sized to receive a potion of the wing when the wing is wrapped around the fuselage.

Abstract translation: 一种空中飞行器以及用于折叠用于存储的空中飞行器的方法可以包括机身和连接到机身的机翼。 机翼可以包括彼此相对定位的两个端部，并且机翼可以基本上垂直于机身。 端部中的至少一个可以限定机身和机翼之间的空间。 当机翼围绕机身缠绕时，该空间的大小可以接收机翼的一部分。

公开(公告)号：US08528863B2

公开(公告)日：2013-09-10

申请号：US12463400

申请日：2009-05-10

Applicant: Terry M. Sanderson ,  Brian J. Gowler ,  David R. Sar ,  Thomas P. McCreery

Inventor： Terry M. Sanderson ,  Brian J. Gowler ,  David R. Sar ,  Thomas P. McCreery

IPC: B64C3/20 ,  B64C3/56

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  F42B10/14 ,  F42B10/146 ,  F42B10/16 ,  F42B10/20

Abstract: A laminated wing structure includes at least one layer of metal material and at least one layer of a shape memory polymer (SMP) material. The SMP is heated to a temperature in its glass transition band Tg to roll the wing around the air vehicle into a stored position. The metal layer(s) must be thin enough to remain below its yield point when rolled up. In preparation for launch, the SMP material is thermally activated allowing the strain energy stored in the layer of metal material to return the wing to its deployed position at launch. Once deployed, the SMP cools to its glassy state. The SMP material may be reinforced with fiber to form a polymer matrix composite (PMC). SMP may be used to provide shear strain relief for multiple metal layers. By offloading the motive force required to return the wing to its original deployed position from the SMP to the metal, the polymer does not acquire a permanent set and the wing may be deployed accurately.

Abstract translation: 层压翼结构包括至少一层金属材料和至少一层形状记忆聚合物（SMP）材料。 将SMP加热到其玻璃化转变带Tg的温度，以将机身周围的机翼卷绕成储存位置。 金属层必须足够薄以便在卷起时保持低于其屈服点。 在准备发射时，SMP材料被热激活，允许存储在金属材料层中的应变能在发射时将机翼返回到其展开位置。 一旦部署，SMP冷却到玻璃状态。 SMP材料可以用纤维增强以形成聚合物基质复合材料（PMC）。 SMP可用于为多个金属层提供剪切应变消除。 通过卸载将机翼从SMP返回到金属的原始展开位置所需的动力，聚合物不会获得永久变形，并且可以准确地展开机翼。

公开(公告)号：US20130214085A1

公开(公告)日：2013-08-22

申请号：US13398773

申请日：2012-02-16

Applicant: Michael Gaudette

Inventor： Michael Gaudette

IPC: F42B10/64

CPC classification number: F42B10/64 ,  F42B10/16

Abstract: A system for actuating a control surface of a deployable member is provided. The system includes an actuator disposed within a fuselage structure of a missile; a double joint having a distal end for connecting to the actuator and a proximal end for engaging the control surface, wherein the double joint further includes a first and second pivot; and a mechanical brake configured to controllably prevent rotation of the actuator.

Abstract translation: 提供了用于致动可部署构件的控制表面的系统。 该系统包括设置在导弹的机身结构内的致动器; 具有用于连接到所述致动器的远端的双接头和用于接合所述控制表面的近端，其中所述双接头还包括第一和第二枢轴; 以及构造成可控制地防止致动器的旋转的机械制动器。

公开(公告)号：US20120036779A1

公开(公告)日：2012-02-16

申请号：US13283048

申请日：2011-10-27

Applicant: Arie ASHKENAZI

Inventor： Arie ASHKENAZI

IPC: E06B3/48 ,  E05F15/20 ,  E05F1/12

CPC classification number: F42B10/16

Abstract: A foldable deployable panel device attached to a body of an object is disclosed. The device includes a panel pivotally attached to the body by a first pivot element at first pivot position and a second pivot element at a second pivot position. The first pivot element is disengageable from the first pivot position, when the panel is aligned in a predetermined orientation. The second pivot element is fixed at the second pivot position, when the first pivot element is engaged at the first pivot position. The panel is urged by an energy storing element, when the first pivot element is disengaged from the first pivot position, to move into the deployed position.

Abstract translation: 公开了一种连接到物体的可折叠展开面板装置。 该装置包括通过在第一枢转位置处的第一枢转元件枢转地连接到主体的面板和在第二枢转位置处的第二枢转元件。 当面板以预定取向对准时，第一枢轴元件可脱离第一枢转位置。 当第一枢转元件在第一枢转位置接合时，第二枢转元件被固定在第二枢转位置处。 当第一枢转元件从第一枢转位置脱离时，面板被能量存储元件推动以移动到展开位置。

公开(公告)号：US07728266B2

公开(公告)日：2010-06-01

申请号：US11549223

申请日：2006-10-13

Applicant: Edgar R. Melkers ,  Rudy Eisentraut ,  Doron Strassman

Inventor： Edgar R. Melkers ,  Rudy Eisentraut ,  Doron Strassman

IPC: F42B15/01

CPC classification number: F02K1/78 ,  F02K9/97 ,  F05D2250/31 ,  F42B10/16 ,  F42B10/28 ,  F42B10/665

Abstract: A system, device and method provide an exhaust assembly adapted for use with a mass ejection drive system to produce rotational torque about the principle axis of the drive system. Representative features generally include a vane suitably configured to at least partially engage a mass ejecta stream to apply a net rotational torque about the principal axis of the drive system, and a tailfin coupled to the at least one vane. The tail fin is configured to selectively deploy from an at least partially stowed position in order to decrease the application of net rotational torque about the principal axis of the drive system.

Abstract translation: 一种系统，装置和方法提供了适于与质量喷射驱动系统一起使用的排气组件，以产生围绕驱动系统的主轴的旋转扭矩。 代表性特征通常包括适当地构造成至少部分地接合质量流出物流以围绕驱动系统的主轴施加净旋转扭矩的叶片，以及联接到至少一个叶片的尾鳍。 尾翼构造成从至少部分收起位置选择性地展开，以便减小围绕驱动系统的主轴的净旋转扭矩的应用。

公开(公告)号：US20100102162A1

公开(公告)日：2010-04-29

申请号：US12257699

申请日：2008-10-24

Applicant: Chris E. Geswender ,  Shawn B. Harline ,  Nicholas E. Kosinski

Inventor： Chris E. Geswender ,  Shawn B. Harline ,  Nicholas E. Kosinski

IPC: F42B10/14 ,  B29C65/78

CPC classification number: F42B10/16

Abstract: A projectile has filler material placed between an outer surface of its fuselage, and fins that are hingedly coupled to the fuselage. The filler material fills space that otherwise would be occupied by pressurized gases. Such pressurized gases could cause undesired outward force against the projectile fins during launch of the projectile from a launch tube or gun, such as when pressure outside the fins is suddenly removed, as in when the projectile passes a muzzle brake in the launch tube. The filler material may be any of a variety of lightweight solid materials, such as suitable plastics or closed cell foams. The filler material prevents pressurized gases from entering at least some of the space between the fins and the outer fuselage surface. When the fins deploy after the projectile emerges from the launch tube the filler material pieces fall away harmlessly.

Abstract translation: 抛射体具有放置在其机身的外表面之间的填充材料和铰接到机身的翅片。 填充材料填充否则将被加压气体占据的空间。 这样的加压气体可能在从发射管或喷枪发射抛射物时引起对弹丸的不期望的向外的力，例如当突出部分的翅片外部的压力被突然移除时，如在射弹通过发射管中的枪口制动器时。 填充材料可以是各种轻质固体材料中的任何一种，例如合适的塑料或闭孔泡沫。 填充材料防止加压气体进入翅片和外部机身表面之间的至少一些空间。 当射弹从发射管出来时，翅片部署，填充材料片无害化掉。

公开(公告)号：US20100102161A1

公开(公告)日：2010-04-29

申请号：US12257690

申请日：2008-10-24

Applicant: Chris E. Geswender ,  Shawn B. Harline ,  Nicholas E. Kosinski

Inventor： Chris E. Geswender ,  Shawn B. Harline ,  Nicholas E. Kosinski

IPC: F42B10/16

CPC classification number: F42B10/16

Abstract: A projectile has fins that are hingedly coupled to a fuselage. The fins are configured to wrap around the fuselage, assuming a location as close as possible to the fuselage, when the projectile is in a gun or launch tube. The fins have spiracles, one or more openings in each of the fins that allow pressurized gases to pass therethrough. The spiracles may be always open, or may open only when there is a sufficient pressure differential between the sides (major surfaces) of the fins. The spiracles allow release of pressurized gases that are trapped between the fins and the fuselage during the launch process. This prevents undesired outward movement or bending of the fins when the projectile reaches a muzzle brake during launch, a structure which causes a sudden release of pressure at radially outer locations of the launch tube.

Abstract translation: 射弹具有与机身铰接的翅片。 当飞弹在枪或发射管中时，翅片配置为围绕机身包围，假设尽可能靠近机身的位置。 翅片具有螺旋形，每个翼片中的一个或多个开口允许加压气体通过。 螺旋可以总是打开，或者只有当翅片的侧面（主表面）之间存在足够的压差时才可以打开。 在发射过程中，螺旋体允许释放在翅片和机身之间被捕获的加压气体。 这防止了在发射期间弹丸到达枪口制动器时翅片的不期望的向外运动或弯曲，这是在发射管的径向外部位置处突然释放压力的结构。

公开(公告)号：US20070138335A1

公开(公告)日：2007-06-21

申请号：US11640171

申请日：2006-12-18

Applicant: Christian Trouillot

Inventor： Christian Trouillot

IPC: F42B10/00

CPC classification number: F42B10/16 ,  F42B10/14

Abstract: The invention relates to a locking device for a deployable surface or fin of a projectile characterized in that it incorporates at least one flexible tongue, one end of which protrudes in the groove, a recess to the side of the groove enabling the tongue to bend in a first direction to enable the fin to enter the groove.

Abstract translation: 本发明涉及一种用于可展开的抛射体表面或翅片的锁定装置，其特征在于，其包括至少一个柔性舌片，其一端在凹槽中突出，凹槽到凹槽的侧面，使得舌头能够弯曲 使翅片进入槽的第一方向。

公开(公告)号：US20070084961A1

公开(公告)日：2007-04-19

申请号：US10907301

申请日：2005-03-28

Applicant: Stig Johnsson ,  Ulf Hellman ,  Ulf Holmqvist

Inventor： Stig Johnsson ,  Ulf Hellman ,  Ulf Holmqvist

IPC: F42B10/00

CPC classification number: F42B10/16 ,  F42B10/18 ,  F42B10/20 ,  F42B10/40

Abstract: This disclosure relates to a method and an arrangement for low or non-rotating artillery shells fired from launch weaponry, and which introduces a portion of the barrel pressure built up in the barrel during the launch phase into a chamber arranged in the low or non-rotating artillery shell which is delimited in at least one direction by an element which is movable relative to the rest of the shell when a differential pressure between the chamber and the external environment of the shell is sufficient to move the element. The moveable element may be a protective casing covering fins of the artillery shell.

Abstract translation: 本公开涉及一种用于从发射武器发射的低或非旋转炮弹的方法和装置，并且其将在发射阶段期间在枪管中积累的枪管压力的一部分引入布置在低或非弹性的腔室中， 旋转炮壳，其在至少一个方向上被限定在相对于壳体的其余部分可移动的元件，当壳体与壳体的外部环境之间的压差足以使元件移动时。 可移动元件可以是覆盖炮弹的翅片的保护壳体。

公开(公告)号：US20040108410A1

公开(公告)日：2004-06-10

申请号：US10309828

申请日：2002-12-04

Inventor： Henry August

IPC: B64C037/02 ,  B64D005/00

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/046 ,  B64C2201/104 ,  B64C2201/121 ,  F42B10/16 ,  F42B10/62 ,  F42B12/58 ,  F42B12/62 ,  F42B15/00

Abstract: A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.

Abstract translation: 可重复使用的马赫速度移动平台通过垂直发射，无力滑翔，武器释放和着陆操作阶段提供武器有效载荷。 平台包括具有尾部和前端的大致管状的主体和有效载荷部分。 一个弓翼由身体后端支撑。 拱翼具有通过两个弯曲端板在远端连接的上翼和下翼。 前端组件在前端连接，具有向上定向的固定迎角，以产生前端提升。 安装在车体下方的散热瓦片和下部翼片下侧辐射/消散在高角度攻角平台折返期间产生的热量。 使用雷达吸收或雷达半透明材料。 该平台优选地从尾端排出有效载荷以进行安全分离。 起落架延伸到着陆阶段。