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公开(公告)号：US20060207465A1
公开(公告)日：2006-09-21
申请号：US11178750
申请日：2005-07-11
申请人： Jahangir Rastegar , Richard Pelz
发明人： Jahangir Rastegar , Richard Pelz
IPC分类号： F42B14/06
CPC分类号： F42B10/146 , F42B10/38 , F42B10/40 , F42B10/42 , F42B10/44
摘要： A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.
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公开(公告)号：US07097133B2
公开(公告)日：2006-08-29
申请号：US10922047
申请日：2004-08-19
申请人： Daryl B. Elam
发明人： Daryl B. Elam
IPC分类号： F42B15/01
CPC分类号： F42B10/146 , B64C39/024 , B64C2201/102
摘要： An articulated wing (20) is readily deployable from a stowed configuration that occupies minimal volume to an extended configuration for flight. The wing (20) includes a frame (24) having a pair of beams (30) spaced by one or more ribs (36), and a flexible covering material (26) over the frame (24) that defines the surface of the wing (20). Each beam (30) typically has multiple segments (40), and each segment (40) is pivotally connected to an adjacent segment (40) at a joint (42). A flexible actuation line (52) extends past each joint (42) and is attached to a portion of the beam beyond the joint. The beam (30) also includes portions that act as stops (46). The stops (46) limit the range of angular motion through which the respective segments (40) can rotate relative to one another. Consequently, when tension is applied to the line (52), the segments (40) rotate until respective stops (46) prevent further rotation. Tension in each line (52) keeps the wing (20) in its extended configuration.
摘要翻译： 铰接翼（20）可以从占有最小体积的收起构型展开到用于飞行的延伸构型。 机翼（20）包括具有由一个或多个肋（36）间隔开的一对梁（30）的框架（24）以及限定翼的表面的框架（24）上方的柔性覆盖材料（26） （20）。 每个梁（30）通常具有多个段（40），并且每个段（40）在接头（42）处枢转地连接到相邻段（40）。 柔性致动线（52）延伸穿过每个接头（42）并且被附接到梁的超过接头的一部分。 梁（30）还包括用作挡块（46）的部分。 止动件（46）限制角运动的范围，相应的段（40）可以相对于彼此旋转。 因此，当向线（52）施加张力时，片段（40）旋转直到相应的挡块（46）阻止进一步旋转。 每条线（52）中的张力保持机翼（20）处于其延伸构型。
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3.发明授权公开(公告)号：US06923123B2
公开(公告)日：2005-08-02
申请号：US10833476
申请日：2004-04-26
CPC分类号： F42B10/146 , F42B10/38 , F42B10/40 , F42B10/42 , F42B10/44
摘要： A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.
摘要翻译： 一种提高无人射弹空气动力学性能的方法。 该方法至少包括以下之一：（a）在发射后变形射弹的横截面形状; （b）在发射后变形射弹的纵向形状; （c）在其飞行期间在射弹的基部处流出液体：（d）作为其速度的函数改变射弹的基底锥角; （e）在发射之后，从射弹的身体部署至少一个翼; 和（f）在发射之后从射弹的身体部署翅片。
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公开(公告)号：US20050133661A1
公开(公告)日：2005-06-23
申请号：US10833477
申请日：2004-04-26
申请人： Jahangir Rastegar , Richard Pelz
发明人： Jahangir Rastegar , Richard Pelz
CPC分类号： F42B10/146 , F42B10/38 , F42B10/40 , F42B10/42 , F42B10/44
摘要： A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.
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公开(公告)号：US4756253A
公开(公告)日：1988-07-12
申请号：US895244
申请日：1986-08-11
申请人： Dana C. Herring , Elbert W. Duvall
发明人： Dana C. Herring , Elbert W. Duvall
CPC分类号： F42B10/146
摘要： Apparatus is disclosed which provides for the controlled deployment of a flexible samara blade used to orient and decelerate a submunition cannister which is dispensed at altitude and allowed to free fall to earth. Spin pins are anchored in and extend outwardly from the downstream end of the cannister. Placement of the pins is such that the flexible samara blade can be wrapped around the pins to place the blade in a stowed condition within the periphery of the cannister end prior to launch of the submunition. Caps on the pins are used to inhibit the stowed blade from slipping off the pins. The blade is wrapped around the pins in a direction opposite to the direction of rotation of the submunition during launch. Launching the submunition in a spinning state creates a centrifugal force in the weighted tip of the samara blade causing the wing to unwrap from the stowed to the deployed state. The pins keep tension in the unfolding wing and preclude erroneous twist-up of the flexible blade.
摘要翻译： 公开了一种设备，用于控制部署用于定向和减速子弹药罐的柔性samara刀片，所述子弹药罐在高度被分配并被允许自由落体。 旋转销被锚固并从罐的下游端向外延伸。 销的放置使得柔性samara刀片可以缠绕在销上，以在发射子弹药之前将刀片放置在罐末端的周边内的收纳状态。 引脚上的盖子用于禁止收起的刀片从引脚上滑落。 在发射期间，刀片沿着与子弹药旋转方向相反的方向缠绕在销上。 在旋转状态下启动子弹药在萨马拉叶片的加重尖端产生离心力，导致机翼从收起的展开状态展开。 针脚在展开的机翼中保持张力，并防止柔性叶片的错误扭曲。
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公开(公告)号：US4664338A
公开(公告)日：1987-05-12
申请号：US772247
申请日：1985-09-03
申请人： Raimar Steuer , Bernd Brieseck
发明人： Raimar Steuer , Bernd Brieseck
CPC分类号： F42B10/146
摘要： A projectile possessing extendable wings or fins which are adapted to be pivoted radially outwardly of the projectile. The wing or fin includes a flexible covering and a tensioning device; for example, a strut arrangement, and with the wing or fin being displaceable from a retracted position prior to launch of the projectile to an outwardly extended position in which the applicable covering portion is tensioned by the tensioning device so as to thereby provide a stable, predetermined aerodynamically defined wing or fin configuration.
摘要翻译： 具有可伸缩翼或翼片的射弹，其适于在射弹的径向向外枢转。 翼或翅片包括柔性覆盖物和张紧装置; 例如，支柱装置，并且在发射抛射体之前，机翼或翼片可从缩回位置移位到向外延伸的位置，在该向外延伸位置中，应用覆盖部分由张紧装置张紧，从而提供稳定的， 预定的空气动力学定义的翼或翅片配置。
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公开(公告)号：US4411398A
公开(公告)日：1983-10-25
申请号：US255413
申请日：1981-04-20
CPC分类号： F42B10/146
摘要： A simple, retractable, self-erecting wing for a low speed missile having a fabric wing cover affixed to a leading edge structure that is the only erected structural member in the wing operative position. The wing cover forms a pocket that contains air. The leading edge structure is hinged and folds, along with the wing cover, into a compact slotted space adjacent the outer wall of a missile body. In the folded position the leading edge structure forms a cover for the slot and the cover coincides with the outer shape of the missile body. A large fabric wing can be completely stored within the missile body for minimum drag during any high speed portion of the missile flight, the wing being released to the operative position by a simple mechanism.
摘要翻译： 一种用于低速导弹的简单的，可伸缩的自立式机翼，其具有固定到作为机翼操作位置中唯一竖立的结构构件的前缘结构的织物翼罩。 机翼盖形成一个包含空气的口袋。 前缘结构与翼盖一起铰接并折叠成与导弹体外壁相邻的紧凑的狭槽空间。 在折叠位置，前缘结构形成用于槽的盖，并且盖与导弹体的外形重合。 在导弹飞行的任何高速部分期间，可以将大型织物翼片完全储存在导弹体内，以达到最小的阻力，机翼通过简单的机构释放到操作位置。
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8.发明申请公开(公告)号：US20100282906A1
公开(公告)日：2010-11-11
申请号：US12463400
申请日：2009-05-10
CPC分类号： B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/201 , F42B10/14 , F42B10/146 , F42B10/16 , F42B10/20
摘要： 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.
摘要翻译： 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。
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公开(公告)号：US07090163B2
公开(公告)日：2006-08-15
申请号：US10833477
申请日：2004-04-26
IPC分类号： F42B10/16
CPC分类号： F42B10/146 , F42B10/38 , F42B10/40 , F42B10/42 , F42B10/44
摘要： A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.
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公开(公告)号：US06935242B2
公开(公告)日：2005-08-30
申请号：US10833475
申请日：2004-04-26
CPC分类号： F42B10/146 , F42B10/38 , F42B10/40 , F42B10/42 , F42B10/44
摘要： A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.
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