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1. 发明授权

US4730793A Ordnance delivery system and method including remotely piloted or programmable aircraft with yaw-to-turn guidance system 失效
标题翻译：兵器交付系统和方法包括遥控或可编程飞机与偏航转弯导向系统
公开(公告)号：US4730793A
公开(公告)日：1988-03-15
申请号：US566163
申请日：1984-01-26
申请人： Charles H. Thurber, Jr. , Frederick A. Behrens , John H. Hunton
发明人： Charles H. Thurber, Jr. , Frederick A. Behrens , John H. Hunton
IPC分类号： B64C39/02 , B64F1/10 , F41G7/00 , F41G7/22 , F42B15/053
CPC分类号： B64C39/024 , B64F1/10 , F41G7/007 , F41G7/22 , B64C2201/044 , B64C2201/046 , B64C2201/084 , B64C2201/102 , B64C2201/128 , B64C2201/141 , B64C2201/146 , B64C2201/165 , B64C2201/201 , B64C2201/208
摘要： A method and system for delivery ordnance to a target via a remotely piloted or programmable aircraft including a yaw-to-turn guidance system, a deployment and launching system and packaging for the aircraft are disclosed.
摘要翻译：公开了一种用于通过远程驾驶或可编程的飞行器对目标进行运送的方法和系统，包括偏航转向引导系统，用于飞机的部署和发射系统以及包装。

2. 发明授权

US4660786A Pivot bearing arrangement for the control surface of a missile 失效
标题翻译：导弹的控制面枢轴轴承布置
公开(公告)号：US4660786A
公开(公告)日：1987-04-28
申请号：US792459
申请日：1985-10-29
申请人： Bernd Brieseck , Josef Nagler
发明人： Bernd Brieseck , Josef Nagler
IPC分类号： B64C9/02 , F42B10/64 , F42B12/00 , F42B13/32 , F16J15/16 , F42B15/027 , F42B15/053
CPC分类号： F42B10/64 , B64C9/02
摘要： A pivot or bearing arrangement for the pivotable control surface of a guidable missile, especially a projectile which can be fired through the intermediary of the gas pressure generated by a propellant charge. The pivot bearing includes a control surface support guided by a radial ball bearing, including a circular shoulder which axially contacts against a sealing ring which lies on a shoulder of the supportive tail end structure of the projectile and which is constituted of a resiliently deformable or compressible material.
摘要翻译：用于可导弹的导弹的枢转或轴承装置，特别是可以通过推进剂装料产生的气体压力的中间燃烧的射弹。枢轴轴承包括由径向球轴承引导的控制表面支撑件，包括圆形肩部，该圆形肩部与位于弹丸的支撑尾端结构的肩部上的密封环轴向接触，并且由可弹性变形或可压缩材料。

3. 发明授权

US4809929A Splitter plates for alleviation of missile hook drag 失效
标题翻译：分离板用于减轻导弹钩阻力
公开(公告)号：US4809929A
公开(公告)日：1989-03-07
申请号：US66449
申请日：1987-06-26
申请人： Henry August
发明人： Henry August
IPC分类号： F42B10/42 , F42B15/053
CPC分类号： F42B10/42
摘要： The overall drag upon a missile body after launch can be reduced and hence the range and average speed of the missile increased by reducing the aerodynamic drag at supersonic velocities attributable to missile hooks which are normally used to attach and launch the missile body from a launcher assembly. After launch a pair of splitter plates are popped up into position next to each missile hook. One splitter plate is positioned in front of the missile hook and a second splitter plate positioned behind the missile hook. The splitter plates are generally planar and arranged so that their planar surfaces are approximately parallel to the fore and aft direction of the missile body. In the illustrated embodiment, the splitter plates are erected into an operative configuration with respect to their missile hooks by rotating each splitter plate about a hinge line. The splitter plate is biased to assume the erect configuration by means of a torsion spring. An electromechanical latch maintains the splitter plates in a folded configuration against the missile body until the missile body has cleared the launch assembly. Thereafter the latch releases the splitter plates allowing the torsional spring to rotate each splitter plate into an operative configuration. Upon full erection of each splitter plate, each splitter plate is mechanically locked into the erect configuration. In one embodiment a fifty percent reduction in the drag coefficient is realized at supersonic velocities as a result of the splitter plates.

4. 发明授权

US4752052A Projectile 失效
标题翻译：射弹
公开(公告)号：US4752052A
公开(公告)日：1988-06-21
申请号：US942724
申请日：1986-12-17
申请人： Mark W. Galvin
发明人： Mark W. Galvin
IPC分类号： F42B10/16 , F42B15/053
CPC分类号： F42B10/16
摘要： The projectile includes a preferably cylindrical body, with an outer preferably generally cylindrical shell disposed over a portion thereof, having a fixed end secured to the body and a rotatable opposite end. The shell bears a number of spaced fins simultaneously moveable between a closed low-profile position and a deployed flight-stabilizing position by rotating the rotatable shell end. Each fin has a pair of elongated plates hinged together at one end, and the fin plates are also hinged to the shell at opposite ends thereof. The plates are aligned in a direction diagonal to the longitudinal axis of the body, while the hinges are parallel to that axis. The projectile includes an impeller connected to the rotatable end of the shell for rotation thereof around the body's longitudinal axis. In the deployed position the fins are preferably dome-shaped with central air passageways, with the main plane of the plates parallel to the body longitudinal axis for minimum air drag and with the fins at about the same transverse position. The impeller may include a return spring, a releasable lock and/or a cowling keyed to a rotor and to the rotatable shell end.
摘要翻译：抛射体包括优选圆柱形主体，其外部优选地大致圆柱形的壳体设置在其一部分上，具有固定到主体的固定端和可旋转的相对端。通过旋转可旋转的外壳端部，壳体具有多个间隔开的翅片，同时可在闭合的低轮廓位置和展开的飞行稳定位置之间移动。每个翅片具有一对在一端铰接在一起的细长板，翅片板也在其相对端处铰接到壳体。这些板在与主体的纵向轴线对角的方向上对齐，而铰链平行于该轴线。抛射体包括连接到壳体的可旋转端部的叶轮，用于围绕身体的纵向轴线旋转。在展开位置，翅片优选地是具有中心空气通道的圆顶形状，其中板的主平面平行于主体纵向轴线，用于最小的空气阻力，并且翅片处于大致相同的横向位置。叶轮可以包括复位弹簧，可释放的锁和/或键合到转子和可转动的壳端的整流罩。

5. 发明授权

US4756492A High velocity aerodynamic body having telescopic pivotal tip 失效
标题翻译：具有伸缩式枢转尖端的高速气动体
公开(公告)号：US4756492A
公开(公告)日：1988-07-12
申请号：US32747
申请日：1987-03-31
申请人： Walter Kranz
发明人： Walter Kranz
IPC分类号： F42B10/46 , F42B10/62 , F42B15/053
CPC分类号： F42B10/46 , F42B10/62
摘要： A high velocity aerodynamic body, particularly a shell flying at supersonic velocity, having a device for stabilizing the aerodynamic body and for reducing its oscillation. The aerodynamic body has in the vicinity of its tip, a rotation symmetrical tip enclosure which is supported, with balanced mass, about a support point located on the longitudinal axis of the aerodynamic body, freely tiltably on all sides.
摘要翻译：高速空气动力体，特别是以超音速飞行的壳体，具有用于稳定气动体并减少其振动的装置。空气动力体在其尖端附近，旋转对称的尖端外壳，其平衡质量被支撑，位于空气动力体的纵向轴线上的支撑点，在所有侧面上可自由倾斜。

6. 发明授权

US4728058A Airborne body with over-caliber sized guidance mechanism 失效
标题翻译：机身尺寸超大的导向机构
公开(公告)号：US4728058A
公开(公告)日：1988-03-01
申请号：US899547
申请日：1986-08-22
申请人： Bernd Brieseck , Josef Nagler
发明人： Bernd Brieseck , Josef Nagler
IPC分类号： F42B10/14 , F42B10/16 , F42B10/64 , F42B15/053
CPC分类号： F42B10/14 , F42B10/64
摘要： An airborne body with an over-caliber sized guidance mechanism, especially a projectile with control surfaces, whose surfaces are retracted against a projectile tail structure prior to launching or firing of the projectile from a weapon barrel or tube, and are generally radially extended subsequent to exiting from the barrel. A securing or latching pin arrangement is provided between the tail end structure of the projectile and each control surface for maintaining the latter is a retracted position, and is released upon acceleration of the projectile after firing to allow for the outward extension of the control surfaces into their operative positions. In this connection, there is especially contemplated a projectile which is fireable from a mortar tube or other kind of weapon barrel, and which possesses guidance control surfaces in order to enable influencing a flight trajectory (such as, for instance, final flight-phase guidance). The airborne body can also relate to a projectile equipped with a rocket propulsion arrangement, and in which the guidance mechanism can pertain to aerodynamic stabilizer fins.
摘要翻译：具有超大口径大小的引导机构的机载物体，特别是具有控制表面的射弹，其表面在从武器枪管或管子发射或射击射弹之前抵抗抛射体尾部结构缩回，并且通常在从桶出来。在弹丸的尾端结构和每个控制表面之间提供固定或闩锁销布置，用于保持弹射器的缩回位置是缩回位置，并且在射出加速之后被释放以允许控制表面向外延伸他们的职位。在这方面，特别考虑了一种可从迫击炮管或其他类型的武器炮发射的射弹，其具有引导控制表面，以便能够影响飞行轨迹（例如，最终的飞行相位指导）。机载体还可以涉及配备有火箭推进装置的射弹，其中引导机构可以涉及空气动力学稳定翼。

7. 发明授权

US4659037A Wing deploying system comprising an airbag 失效
标题翻译：翼展展系统包括气囊
公开(公告)号：US4659037A
公开(公告)日：1987-04-21
申请号：US769178
申请日：1985-08-26
申请人： Klaus Unterstein
发明人： Klaus Unterstein
IPC分类号： F42B10/20 , F42B15/053
CPC分类号： F42B10/20
摘要： The invention concerns a missile body having a first flight guide and stabilization means mounted on the missile body and a second guide and stabilization means mounted on the missile body in front of the first guide and stabilization means with respect to the direction of flight. The second guide and stabilization means comprise a plurality of wings which are folded inwardly (collapsed inwardly, pivoted inwardly) into the missile body when in their inoperative position. These wings can be pivoted or slid outwardly when in their operative position by means of a collapsed expandable body which is expanded by means of pressurized gas. The pressurized gas is stored in a pressurized gas cylinder mounted within the missile body. The expandable body expands in a radial direction and thereby exerts a force on the wings which causes them to either pivot about a rotatable axis or to move in a radial direction outwardly of the missile body.
摘要翻译：本发明涉及一种具有第一飞行引导件和安装在导弹体上的稳定装置的导弹体，以及相对于飞行方向安装在第一引导件和稳定装置前面的导弹体上的第二引导件和稳定装置。第二引导和稳定装置包括多个翼片，当处于其不工作位置时，其向内折叠（向内折叠，向内枢转）到导弹体中。当通过借助于加压气体膨胀的塌缩的膨胀体在其操作位置时，这些翼可以枢转或向外滑动。加压气体储存在安装在导弹体内的加压气瓶中。可膨胀体在径向方向上膨胀，从而在翼上施加力，这使得它们绕可旋转的轴线枢转或者沿导弹本体的径向方向移动。

8. 发明授权

US4641802A Projectile stabilization system 失效
标题翻译：射弹稳定系统
公开(公告)号：US4641802A
公开(公告)日：1987-02-10
申请号：US638769
申请日：1984-08-08
申请人： Seev W. Zalmon , Shlomo Engel , Joseph Eyal
发明人： Seev W. Zalmon , Shlomo Engel , Joseph Eyal
IPC分类号： F42B10/14 , F42B13/32 , F42B15/053
CPC分类号： F42B10/14
摘要： A stabilization system for a projectile includes both fixed fins which exd outwardly from a core and folding fins. Each fixed fin has a pocket wherein a folding fin is pivotably supported. Each folding fin is in the folded state while the projectile is in the bore of the gun from which the projectile is to be fired and the fin unfolds after exiting the bore of the gun. Once the gun is fired to propel the projectile, the folding fins are retained in the folded state due to a moment which is a function of acceleration setback. Shortly after the projectile exits the bore, when the gas velocity Vg exceeds the projectile velocity Vp a moment, due to a pressure difference in the pocket and outside the pocket, is applied to each folding fin to urge it to its unfolded state.
摘要翻译：用于抛射体的稳定系统包括从芯部向外延伸的固定翅片和折叠翅片。每个固定翅片具有凹口，其中折叠翅片可枢转地支撑。每个折叠翅片处于折叠状态，而抛射体位于枪的孔中，射弹将从该孔射出，并且在离开枪孔之后翼片展开。一旦枪被射击以推动射弹，折叠翅片由于加速挫折的一个时刻而保持在折叠状态。在弹丸离开孔后不久，当气体速度Vg超过射出速度Vp时，由于口袋中的压力差和口袋外的压力而被施加到每个折叠翅片以促使其处于展开状态。

9. 发明授权

US4583703A One fin orientation and stabilization device 失效
标题翻译：一个鳍定位和稳定装置
公开(公告)号：US4583703A
公开(公告)日：1986-04-22
申请号：US653570
申请日：1984-09-24
申请人： Roy W. Kline
发明人： Roy W. Kline
IPC分类号： F42B10/14 , F42B10/26 , F42B13/32 , F42B15/053 , F42B25/20
CPC分类号： F42B10/14 , F42B10/26
摘要： An orientation and stabilization device for a submunition is disclosed. A w profile cylindrical submunition body has a single fin attached thereto at an asymmetrically located position with respect to the central axis of the cylindrical body. The fin is tip weighted in such a way that, when the submunition falls through the air, a constant spin and vertical velocity is established, with the major axis of the cylindrical body disposed at an angle to the descent path.
摘要翻译：公开了一种用于子弹药的取向和稳定装置。低角圆柱形子弹药体具有相对于圆柱体的中心轴线位于非对称位置处的单个翅片。翅片以尖端加权，使得当子弹药通过空气流动时，建立恒定的旋转和垂直速度，其中圆柱体的长轴设置成与下降路径成一定角度。

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