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    Method and an apparatus to shoot an object from a flying apparatus
    81.
    发明申请
    Method and an apparatus to shoot an object from a flying apparatus 有权
    从飞行装置拍摄物体的方法和装置

    公开(公告)号：US20160332738A1

    公开(公告)日：2016-11-17

    申请号：US15111147

    申请日：2015-10-12

    Applicant: Skycat Oy

    Inventor： Henri Hiisilä

    IPC: B64D17/70 ,  B64C39/02 ,  B64D17/64

    CPC classification number: 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

    Abstract: 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.

    Abstract translation: 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。

    Unmanned Aerial Systems
    83.
    发明申请
    Unmanned Aerial Systems 审中-公开
    无人机系统

    公开(公告)号：US20150203200A1

    公开(公告)日：2015-07-23

    申请号：US14421435

    申请日：2013-07-25

    Applicant: George Bye ,  Matt Bickel

    Inventor： George Bye ,  Matt Bickel

    IPC: B64C39/02 ,  B64D41/00 ,  B64D33/00

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/046 ,  B64C2201/066 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2211/00 ,  B64D2211/00 ,  Y02T50/55

    Abstract: The present invention provides an Unmanned Aircraft System, including an integrated unmanned aerial vehicle and all related components and subsystems that can be packaged and transported as a kit, and customized to fit desired mission profiles, and easily repaired by replacement of damaged components or subsystems. The present invention further provides unmanned aircraft system components and subsystems that facilitate low power and low noise operation, and extended flight times.

    Abstract translation: 本发明提供了一种无人驾驶飞行器系统，包括一个综合的无人驾驶飞行器以及所有相关的组件和子系统，可以作为一个工具包进行打包和运输，并进行定制，以适应所需的任务轮廓，并通过更换损坏的组件或子系统进行修理。 本发明还提供了便于低功率和低噪声操作以及延长飞行时间的无人飞行器系统部件和子系统。

    Unmanned aerial vehicle for logistical delivery
    86.
    发明申请
    Unmanned aerial vehicle for logistical delivery 失效
    无人机用于后勤运输

    公开(公告)号：US20050006525A1

    公开(公告)日：2005-01-13

    申请号：US10856360

    申请日：2004-05-27

    Applicant: David Byers ,  Gary Hall ,  Graham Hunter ,  Colen Kennell ,  Aleksander MacAnder ,  Judah Milgram ,  Jason Strickland

    Inventor： David Byers ,  Gary Hall ,  Graham Hunter ,  Colen Kennell ,  Aleksander MacAnder ,  Judah Milgram ,  Jason Strickland

    IPC: B64C1/00 ,  B64C1/06 ,  B64C1/22 ,  B64C3/58 ,  B64C29/02 ,  B64C31/02 ,  B64C39/02 ,  B64D5/00 ,  B64C27/22

    CPC classification number: B64C1/068 ,  B64C1/061 ,  B64C1/22 ,  B64C3/58 ,  B64C29/02 ,  B64C31/02 ,  B64C39/024 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/105 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/187 ,  B64D5/00

    Abstract: A hollow elliptical-cylindrical hull conformingly houses a hollow rectangular-prismatic cabin whereby the four longitudinal parallel outside edges of the latter make contact with the inside surface of the former. The fully constructed aircraft (either non-powered or powered) includes the integral hull-plus-cabin structure along with nose, tail and airfoil structures that are coupled therewith. The cabin conformingly accommodates hollow rectangular-prismatic modules useful for cargo storage. While the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the modules are inserted into the cabin and the cabin is sealed. The aircraft is lifted (e.g., via airplane, helicopter, rocket or balloon) to a particular elevation and released, whereupon the two wings fully emerge and the aircraft effects controlled flight until reaching its destination. After landing, the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the cabin is unsealed, and the modules are removed from the cabin.

    Abstract translation: 中空的椭圆柱形船体适合地容纳中空矩形棱柱舱，由此四个纵向平行的外边缘与前者的内表面接触。 完全构造的飞机（非动力或动力）包括一体的船体加舱结构以及与其结合的鼻，尾和翼型结构。 机舱适合容纳用于货物存储的中空矩形模块。 当鼻部和/或尾部结构与整体的船体 - 舱室结构脱离时，模块被插入到舱室中，舱室被密封。 飞机被提升（例如，通过飞机，直升机，火箭或气球）到特定的高度并被释放，于是两翼完全出现，并且飞机实现控制的飞行直到到达其目的地。 在着陆后，鼻部和/或尾部结构与整体式的船体 - 舱室结构脱离，舱室被开封，模块从舱室中取出。

    Unmanned aircraft with automatic fuel-to-air mixture adjustment
    87.
    发明授权
    Unmanned aircraft with automatic fuel-to-air mixture adjustment 失效
    无人机具有自动燃油对空气混合调节

    公开(公告)号：US06721646B2

    公开(公告)日：2004-04-13

    申请号：US10255184

    申请日：2002-09-26

    Applicant: Ernest A. Carroll

    Inventor： Ernest A. Carroll

    IPC: F02D4100

    CPC classification number: B64D31/06 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  F02B75/34 ,  F02D35/0069 ,  F02D41/2406 ,  F02D2200/0414 ,  F02D2200/703 ,  F02D2400/06 ,  F02D2400/11 ,  Y10S123/03

    Abstract: A miniature unmanned aircraft which uses remotely controlled model aircraft components and technology, and has on-board automatic “on-the-fly” fuel and air mixture adjustment enabling high altitude flight. The aircraft, which may have conventional fuselage, wing, reciprocating piston engine and radio frequency operated controls, also has sensors for sensing atmospheric pressure, atmospheric temperature, engine crankshaft rotational speed, engine temperature, and exhaust temperature. A microprocessor aboard the aircraft receives inputs from the sensors and controls at least one servo to adjust fuel and air mixture according to preprogrammed look-up tables and equations to operate the engine at appropriate fuel-to-air ratios for the altitude and other operating conditions.

    Abstract translation: 一种使用遥控模型飞机部件和技术的微型无人机，并具有机载自动“飞行”燃料和空气混合调节，实现高空飞行。 可以具有常规机身，机翼，往复活塞发动机和射频操作控制器的飞行器还具有用于感测大气压力，大气温度，发动机曲轴转速，发动机温度和排气温度的传感器。 飞机上的微处理器接收来自传感器的输入并控制至少一个伺服器，以根据预编程的查找表和方程来调节燃料和空气混合物，以在适当的燃料与空气比下操作发动机的高度和其他操作条件 。

    Unmanned aircraft with automatic fuel-to-air mixture adjustment
    88.
    发明申请
    Unmanned aircraft with automatic fuel-to-air mixture adjustment 失效
    无人机具有自动燃油对空气混合调节

    公开(公告)号：US20030060962A1

    公开(公告)日：2003-03-27

    申请号：US10255184

    申请日：2002-09-26

    Inventor： Ernest A. Carroll

    IPC: G05D001/00

    CPC classification number: B64D31/06 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  F02B75/34 ,  F02D35/0069 ,  F02D41/2406 ,  F02D2200/0414 ,  F02D2200/703 ,  F02D2400/06 ,  F02D2400/11 ,  Y10S123/03

    Abstract: A miniature unmanned aircraft which uses remotely controlled model aircraft components and technology, and has on-board automatic nullon-the-flynull fuel and air mixture adjustment enabling high altitude flight. The aircraft, which may have conventional fuselage, wing, reciprocating piston engine and radio frequency operated controls, also has sensors for sensing atmospheric pressure, atmospheric temperature, engine crankshaft rotational speed, engine temperature, and exhaust temperature. A microprocessor aboard the aircraft receives inputs from the sensors and controls at least one servo to adjust fuel and air mixture according to preprogrammed look-up tables and equations to operate the engine at appropriate fuel-to-air ratios for the altitude and other operating conditions.

    Abstract translation: 一种使用遥控模型飞机部件和技术的微型无人机，并具有机载自动“飞行”燃料和空气混合调节，实现高空飞行。 可以具有常规机身，机翼，往复活塞发动机和射频操作控制器的飞行器还具有用于感测大气压力，大气温度，发动机曲轴转速，发动机温度和排气温度的传感器。 飞机上的微处理器接收来自传感器的输入并控制至少一个伺服器，以根据预编程的查找表和方程来调节燃料和空气混合物，以在适当的燃料与空气比下操作发动机的高度和其他操作条件 。

    Miniature, unmanned aircraft with automatically deployed parachute
    89.
    发明申请
    Miniature, unmanned aircraft with automatically deployed parachute 失效
    微型无人机，自动部署降落伞

    公开(公告)号：US20030057327A1

    公开(公告)日：2003-03-27

    申请号：US10255185

    申请日：2002-09-26

    Inventor： Ernest A. Carroll

    IPC: B64D017/00 ,  B64D019/00

    CPC classification number: B64C39/028 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64D17/80 ,  F02B75/34 ,  F02D35/0069 ,  F02D41/2406 ,  F02D2200/0414 ,  F02D2200/703 ,  F02D2400/06 ,  F02D2400/11 ,  G05D1/101

    Abstract: A miniature, unmanned aircraft having a parachute which deploys automatically under certain conditions. The aircraft has a flight control system based on remotely generated signals, potentially achieves relatively high altitude flight for a remotely controlled aircraft, and can thus operate well beyond line-of-sight control. For safety, an automatically deployed parachute system is provided. The parachute deployment system includes a folded parachute and a propulsion system for expelling the parachute from the aircraft. Preferably, a microprocessor for flight management sends intermittent inhibitory signals to prevent unintended deployment. A deployment signal is generated, illustratively, when the microprocessor fails, when engine RPM fall below a predetermined threshold, and when the aircraft strays from predetermined altitude and course.

    Abstract translation: 具有降落伞的微型无人机在某些条件下自动部署。 该飞机具有基于远程产生的信号的飞行控制系统，可能为遥控飞机实现相对较高的高空飞行，并且因此可以远远超出视线控制。 为了安全起见，提供了自动部署的降落伞系统。 降落伞部署系统包括折叠的降落伞和用于从降落伞排出飞机的推进系统。 优选地，用于飞行管理的微处理器发送间歇性抑制信号以防止意外部署。 例如，当微处理器发生故障时，当发动机转速低于预定阈值时，以及当飞行器从预定高度和当然时间偏离时，产生部署信号。

    Flyer assembly
    90.
    发明授权
    Flyer assembly 有权
    传单装配

    公开(公告)号：US06392213B1

    公开(公告)日：2002-05-21

    申请号：US09690000

    申请日：2000-10-12

    Applicant: Richard T. Martorana ,  Jamie Anderson ,  Simon Mark Spearing ,  Seth Kessler ,  Brent Appleby ,  Edward Bergmann ,  Sean George ,  Steven Jacobson ,  Donald Fyler ,  Mark Drela ,  Gregory Kirkos ,  William McFarland, Jr.

    Inventor： Richard T. Martorana ,  Jamie Anderson ,  Simon Mark Spearing ,  Seth Kessler ,  Brent Appleby ,  Edward Bergmann ,  Sean George ,  Steven Jacobson ,  Donald Fyler ,  Mark Drela ,  Gregory Kirkos ,  William McFarland, Jr.

    IPC: B64C351

    CPC classification number: F42B15/105 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201

    Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state. The wing assembly is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly is adapted to be launched from a ballistic delivery system such as an artillery cannon, and can thus reach a target quickly, without expending system energy stored within the flyer. During launch, the flyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along the flyer axis resulting from the launch. The flyer assembly is adapted to withstand the high g-load and high temperature environments of a cannon launch, and can tolerate a set-back g load of about 16,000 g.

    Abstract translation: 飞行器组件适用于从具有沿弹道壳轴线延伸的中心空隙区域的炮弹发射，转移和展开。 传单组件包括可喷射的护罩和传单​​。 护罩沿护罩轴线延伸，并且可定位在中心空隙区域内，护罩轴线基本上平行于外壳轴线。 飞行器适于在处于第一状态时承受沿飞行器轴的发射加速力，并且在处于第二状态时实现空气动力学飞行。 当处于第一状态时，传单可定位在护罩内，飞翼轴线平行于护罩轴线和外壳轴线。 传单包括围绕飞翼轴设置的主体部件和安装到主体部件的可折叠翼组件。 翼组件可配置成折叠状态，其特征在于当传单处于第一状态时由多个嵌套翼片段组成。 机翼组件可配置为展开状态，其特征在于当传单处于第二状态时基本上不间断的空气动力学表面。 飞行器组件适于从诸如炮兵炮的弹道传送系统发射，并且因此可以快速到达目标，而不会消耗存储在飞行物内的系统能量。 在发射期间，传单联接到护罩上，以便在飞行物沿着由发射引起的飞翼轴的加速期间，使传单的一部分保持张紧。 飞行器组件适于承受大炮发射的高负载和高温环境，并且可以容忍约16,000g的安装载荷。

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