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公开(公告)号：US09745063B2
公开(公告)日：2017-08-29
申请号：US14708197
申请日：2015-05-09
申请人： Ventions, LLC
摘要： A system for air-launching a liquid fueled rocket launch vehicle using a tubular rocket support structure for holding the launch vehicle and for supplying the launch vehicle with make-up cryogenics, electrical power, and control signals, and for providing coupling to a launch-assist aircraft. The tubular rocket support structure contains cryogenic fluids, in addition to fuel and oxidizer, to cool the fuel and oxidizer during the pre-launch phase. The tubular rocket support structure has features that keep the liquid fuel and oxidizer from sloshing away from the tank outlet ports to the launch vehicle's rocket engine after release from the aircraft but before rocket launch. In operation, the aircraft controllably releases the tubular rocket support structure containing the launch vehicle, and the launch vehicle then launches from the rocket support structure.
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公开(公告)号：US20160332738A1
公开(公告)日：2016-11-17
申请号：US15111147
申请日：2015-10-12
申请人： Skycat Oy
发明人： Henri Hiisilä
CPC分类号： B64D17/70 , B64C39/024 , B64C2201/128 , B64C2201/146 , B64C2201/185 , B64D1/04 , B64D1/12 , B64D7/08 , B64D17/64 , B64D25/00 , F41A19/58 , F41B7/00 , F41F1/00
摘要： The object of this invention is a method to shoot an object from a flying apparatus. Into an flying apparatus, into certain part of it, like a container that consists at least of a bottom and a shell a spring will be placed, like a push spring that has been loaded in a tense state and that is locked in this position using a fixing organ and further there will be put as an extension of the spring an object to be shot out from the flying apparatus. The fixing organ is thread, metal cord, bar, strip, rope, line, or some combination of these and tension strength (T) is greater than the tension load of the push force (F) to the mentioned fixing organ. the tension strength (T) of the fixing organ is weakened to be less than the mentioned tension load by heating, burning, or melting the mentioned fixing organ by electric energy when the fixing organ breaks, the spring expands into the direction of the object and the push force (F) pushes the object out of the container and off the flying apparatus. The apparatus that is used in the present method is also an object of the invention.
摘要翻译： 本发明的目的是从飞行装置拍摄物体的方法。 进入飞行装置，进入其某一部分，如至少包括底部和壳体的容器，弹簧将被放置，就像已经加载处于紧张状态并且被锁定在该位置的推动弹簧一样，使用 一个固定器，进一步将弹簧的一个物体从飞行装置中射出。 定影器是螺纹，金属绳，棒，条，绳，线或这些的一些组合，并且拉伸强度（T）大于推动力（F）对所述定影器官的张力负荷。 固定器官的断裂强度（T）通过在定影器官断裂时通过加热，燃烧或熔化所述定影器而被弱化到小于上述的张力负荷，弹簧向物体的方向膨胀， 推动力（F）将物体从容器中推出并离开飞行装置。 本方法中使用的装置也是本发明的目的。
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公开(公告)号：US09272785B2
公开(公告)日：2016-03-01
申请号：US13947869
申请日：2013-07-22
CPC分类号： B64D7/08 , B64D1/02 , B64D7/04 , Y10T29/49826
摘要： A mounting apparatus includes a fixed mounting structure that includes a first fixed fitting including a plurality of first flanges and a second fixed fitting. A rotatable mounting structure has a swivel fitting configured to engage and swivel with respect to the first fixed fitting. The swivel fitting includes a plurality of second flanges, one of which is configured to rest on one of the plurality of first flanges when the swivel fitting and first fixed fitting are engaged. The rotatable mounting structure also has a slide fitting configured to slide with respect to the second fixed fitting based on the swivel fitting being engaged with the first fixed fitting. An adjustment assembly is arranged at an interface between the second fixed fitting and the slide fitting. The adjustment assembly is configured to adjust an angular position of the slide fitting relative to the swivel fitting.
摘要翻译： 一种安装装置，包括固定安装结构，其包括第一固定配件，该第一固定配件包括多个第一凸缘和第二固定配件。 可旋转的安装结构具有被配置为相对于第一固定配件接合和旋转的旋转接头。 旋转接头包括多个第二凸缘，当旋转接头和第一固定接头接合时，其中一个凸缘配置成搁置在多个第一凸缘中的一个上。 可旋转安装结构还具有滑动配件，该滑动配合构造成基于与第一固定配件接合的旋转接头相对于第二固定配件滑动。 调整组件布置在第二固定配件和滑动配件之间的界面处。 调节组件被配置为调节滑动配件相对于旋转接头的角度位置。
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公开(公告)号：US20150021436A1
公开(公告)日：2015-01-22
申请号：US13947869
申请日：2013-07-22
IPC分类号： B64C7/00
CPC分类号： B64D7/08 , B64D1/02 , B64D7/04 , Y10T29/49826
摘要： A mounting apparatus includes a fixed mounting structure that is fixed relative to a vehicle wing, the fixed mounting structure including a first fixed fitting and a second fixed fitting. The mounting apparatus further includes a rotatable mounting structure having a swivel fitting configured to engage the first fixed fitting and to swivel with respect to the first fixed fitting, the rotatable mounting structure also having a slide fitting configured to slide with respect to the second fixed fitting based on the swivel fitting being engaged with the first fixed fitting.
摘要翻译： 安装装置包括相对于车辆翼固定的固定安装结构，所述固定安装结构包括第一固定配件和第二固定配件。 所述安装装置还包括可转动的安装结构，其具有旋转接头，所述旋转接头构造成接合所述第一固定接头并相对于所述第一固定接头旋转，所述可旋转安装结构还具有配置成相对于所述第二固定配件 基于所述旋转接头与所述第一固定配件接合。
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5.发明授权System and method for dispensing of multiple kill vehicles using an integrated multiple kill vehicle payload 有权使用综合多重杀伤车辆有效载荷分配多个杀伤车辆的系统和方法公开(公告)号：US08575526B1
公开(公告)日：2013-11-05
申请号：US12923707
申请日：2010-10-05
申请人： Randy D. Colvin , Adam M. Wuerl , Michael S. Mak
发明人： Randy D. Colvin , Adam M. Wuerl , Michael S. Mak
摘要： An interceptor system and method for dispensing of multiple kill vehicles, including, a carrier vehicle having a central carrier vehicle axis and axial propulsion integrated into the carrier vehicle, a payload adapter associated with the carrier vehicle for connecting a payload to a boost vehicle, the payload adapter being located aft of the carrier vehicle, and multiple kill vehicles mounted to the carrier vehicle radially around a circumference of the carrier vehicle.
摘要翻译： 一种用于分配多个杀伤车辆的拦截器系统和方法，包括具有集成到载体车辆中的中央运载工具车轴线和轴向推进的运载工具，与运载工具相关联的有效载荷适配器，用于将有效载荷连接到升压车辆， 有载体适配器位于运载工具的后方，并且多个杀伤车辆沿着载体车辆的圆周径向地安装到运载工具上。
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6.发明申请公开(公告)号：US20130221158A1
公开(公告)日：2013-08-29
申请号：US13407692
申请日：2012-02-28
申请人： Ryan Binkholder , John K. Foster
发明人： Ryan Binkholder , John K. Foster
摘要： In one embodiment there is provided a radar signature and induced aerodynamic drag minimizing, externally mountable, internally configurable pod structure optimized for internal placement of one or more deployable stores through configuration and optimal kinematic operation of a pod door assembly. The pod structure has an externally mountable pod housing, a predetermined pod housing cross-sectional configuration optimized to provide a configurable interior volume accommodating multiple different store configurations, and a predetermined pod housing configuration having a cross-sectional configuration optimized to minimize a radar signature and an induced aerodynamic drag. The pod structure further has a pod door assembly integral with the pod housing and having a plurality of pod doors and one or more seal door mechanism assemblies. The pod structure is optimized in kinematic operational combination of the pod doors and seal door mechanism assemblies controlling ejection launch envelopes.
摘要翻译： 在一个实施例中，提供了通过配置和荚式门组件的最佳运动学操作优化用于内部放置一个或多个可部署商店的雷达签名和感应空气动力学阻力最小化的可外部安装的内部可配置荚结构。 荚结构具有可外部安装的荚壳体，其经过优化以提供容纳多个不同储存结构的可配置内部容积的预定荚壳体横截面构型，以及具有优化以最小化雷达标记的横截面构型的预定荚壳体构型， 诱发气动阻力。 荚结构还具有与荚壳体一体的荚门组件，并具有多个荚门和一个或多个密封门机构组件。 荚结构在荚果门的运动学操作组合和控制喷射发射信封的密封门机构组件的优化。
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7.发明授权Method for discharging countermeasure means, rocket launcher, and dispenser arrangement 有权排放对策装置，火箭发射器和分配器装置的方法公开(公告)号：US07600477B2
公开(公告)日：2009-10-13
申请号：US10476757
申请日：2002-05-03
申请人： Christer Zätterqvist
发明人： Christer Zätterqvist
IPC分类号： F42B14/06
摘要： A method for discharging countermeasures, a rocket launcher, and a dispenser arrangement. A space for one or more rockets in a rocket launcher is used as a carrier for a dispenser arrangement for countermeasures. The dispenser arrangement is designed with one or more cylindrical sections specially adapted to the rocket space in the rocket launcher. Equipment already adapted to aircraft can be used in supplementing the countermeasure equipment of the aircraft.
摘要翻译： 一种用于排放对策，火箭发射器和分配器装置的方法。 用于火箭发射器中的一个或多个火箭的空间用作用于对策的分配器装置的载体。 分配器装置设计有一个或多个圆柱形部分，特别适用于火箭发射器中的火箭空间。 已经适应飞机的设备可用于补充飞机的对策设备。
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公开(公告)号：US20030121404A1
公开(公告)日：2003-07-03
申请号：US10275549
申请日：2002-11-07
IPC分类号： F41F005/00 , B64D001/04
摘要： Aircraft (10) carries at least two clusters of barrel assemblies. At least one cluster is oriented normal to the longitudinal axis of aircraft (10) and at least one other cluster is oriented parallel to the longitudinal axis of aircraft (10). Each cluster comprises a plurality of barrel assemblies, with each barrel having a plurality of axially disposed projectiles therein. Each projectile is associated with a discrete, sequentially activated propellant charge for propelling it through the muzzle of the barrel. Various methods of deploying a multiplicity of projectiles onto a target from aircraft (10) are also described and claimed. The projectiles deployment might occur at any time whils aircraft (10) is approaching the target, overflying the target, or departing from the target. The projectiles may include smoke canisters, high explosive canisters, flares, electronic and thermal countermeasures, mines, grenades or cameras.
摘要翻译： 飞机（10）携带至少两组筒组件。 至少一个群集平行于飞机（10）的纵向轴线定向，并且至少一个其他群集平行于飞行器（10）的纵向轴线定向。 每个簇包括多个筒组件，每个筒在其中具有多个轴向设置的弹丸。 每个抛射体与不连续的，依次激活的推进剂装药相关联，以将其推进通过枪管的枪口。 还描述和要求保护从飞机（10）将多个弹体部署到目标上的各种方法。 飞机部署可能随时飞机（10）正在接近目标，飞越目标或离开目标。 射弹可能包括烟筒，高爆炸罐，火炬，电子和热对策，矿山，手榴弹或照相机。
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公开(公告)号：US06446906B1
公开(公告)日：2002-09-10
申请号：US09825808
申请日：2001-04-04
IPC分类号： B64C936
摘要： Pyrotechnic actuator cover/fin release system designed for high G forces of gun-launched-systems. As safety feature, system allows the pyrotechnic actuator to be installed as one of the last steps of the final testing sequence and removed safely on disassembly. A first cam action develops initial ejection. Subsequently firing the pyrotechnic pushes both the fins and the covers outward via a second cam surface. The release system both holds covers securely latched until commanded to release and then unlatches covers prior to pushing them open. The cover eject sequence results in the flight forward edge of cover being kicked into air stream. Thereafter the cover is lifted and rotates about its aft release hinge until, at about 30 degrees of rotation, the hinge disengages. The fins then are driven into the fully deployed state by a spring and piston/wedge mechanism on the actuator shaft.
摘要翻译： 烟火执行器盖/散热片释放系统设计用于枪支发射系统的高G力。 作为安全特征，系统允许将烟火执行器安装为最终测试顺序的最后一个步骤，并在拆卸时安全拆除。 第一个凸轮动作开始初始喷射。 随后点燃烟火通过第二凸轮表面向外推动翅片和盖子。 释放系统均将盖子牢固地锁定，直到被释放，然后在将它们打开之前将盖子解开。 盖弹出顺序导致盖的飞行前沿被踢入气流。 此后，盖被提起并绕其后释放铰链旋转，直到约30度的旋转，铰链脱离。 然后，翅片通过致动器轴上的弹簧和活塞/楔形机构被驱动到完全展开状态。
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公开(公告)号：US06296202B1
公开(公告)日：2001-10-02
申请号：US09501289
申请日：2000-02-09
申请人： Michael J. Stanek
发明人： Michael J. Stanek
IPC分类号： B64C138
摘要： An aircraft weapons bay acoustic suppression apparatus is disclosed. The apparatus reduces or eliminates acoustic resonance within an open cavity of an aircraft such as a weapons bay of an aircraft in flight. The apparatus includes an oscillatable spoiler plate which is extended into the airstream. At least one shaker is placed in operative engagement with the spoiler plate in order to oscillate the spoiler plate at high frequencies and high amplitudes to seed the shear layer with frequencies which directly complete with the natural frequency of the shear layer vortices. In this way, the damage arising from natural shear layer vortices can reduced or canceled within the weapons bay.
摘要翻译： 公开了一种飞机武器舱声抑制装置。 该装置减少或消除在诸如飞行中的飞行器的武器舱的飞行器的开放空腔内的声共振。 该装置包括延伸到气流中的可振荡扰流板。 将至少一个振动器放置成与扰流板操作地接合，以便以高频和高振幅振荡扰流板，以使剪切层以剪切层涡旋的固有频率直接完成的频率播种。 以这种方式，在武器舱内可以减少或取消天然剪切层漩涡所造成的破坏。
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