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    POWER SAFETY INSTRUMENT SYSTEM
    81.
    发明申请
    POWER SAFETY INSTRUMENT SYSTEM 有权
    电力安全仪表系统

    公开(公告)号：US20160272342A1

    公开(公告)日：2016-09-22

    申请号：US15168356

    申请日：2016-05-31

    Applicant: TEXTRON INNOVATIONS INC.

    Inventor： James M. McCollough ,  Erik Oltheten ,  Nicholas Lappos

    IPC: B64D45/00 ,  B64C27/04 ,  B64D43/00

    CPC classification number: G01C23/00 ,  B60Q1/00 ,  B64C27/00 ,  B64C27/006 ,  B64C27/04 ,  B64C27/52 ,  B64C29/00 ,  B64C39/024 ,  B64C2201/108 ,  B64C2201/121 ,  B64D43/00 ,  B64D45/00 ,  G01C21/00 ,  G01D7/02 ,  G05D17/02

    Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.

    Abstract translation: 电力安全系统被配置为在飞行器中提供电力信息。 电力安全系统包括具有电力需求指示器和功率可用指示器的电力安全仪器，每个都位于显示器上。 所需电源指示灯和电源指示灯的位置表示执行悬停飞行操作所需的电力和功率。 电力安全系统可以在飞行计划模式或当前飞行模式下操作。 电力安全系统使用至少一个传感器来测量对所需功率和可用功率有影响的变量。

    SYSTEMS AND METHODS COUNTERING AN UNMANNED AIR VEHICLE
    84.
    发明申请
    SYSTEMS AND METHODS COUNTERING AN UNMANNED AIR VEHICLE 审中-公开
    对无人空中车辆的系统和方法

    公开(公告)号：US20160023760A1

    公开(公告)日：2016-01-28

    申请号：US14801479

    申请日：2015-07-16

    Applicant: Insitu, Inc.

    Inventor： Wayne Goodrich

    IPC: B64C39/02 ,  G05D1/12 ,  B64C11/00

    CPC classification number: B64C39/024 ,  B64C5/06 ,  B64C11/48 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/141 ,  B64C2201/162 ,  F41H11/02 ,  F41H13/0006 ,  G05D1/12

    Abstract: Systems and methods for countering an unmanned air vehicle are disclosed. Representative methods include directing an interceptor UAV toward a target UAV, and directing the interceptor UAV back to ground along a controlled flight path, for example, in response to an instruction not to engage with the target UAV, and/or in response to an unsuccessful engagement. Another representative method includes disabling the target UAV by deploying a disabling element (e.g., a net) from the interceptor UAV to contact the target UAV. Representative systems include a target acquisition system, a launch control system, and an engagement system carried by the interceptor UAV. In particular embodiments, the interceptor UAV can have a generally cylindrical fuselage, one or more fins carried by the fuselage, counter-rotating propellers carried by the fuselage, and a disabling system that is configured to disable the target UAV.

    Abstract translation: 公开了用于对抗无人驾驶飞行器的系统和方法。 代表性的方法包括将拦截器无人机指向目标无人机，并且将拦截器无人机沿着受控飞行路径引导回地面，例如响应于不与目标无人机接合的指令和/或响应于不成功 订婚。 另一个代表性的方法包括通过从拦截器UAV部署禁用元件（例如网）来禁用目标UAV以接触目标UAV。 代表性系统包括目标采集系统，发射控制系统和拦截机无人机所承载的接合系统。 在特定实施例中，拦截器UAV可以具有大致圆柱形的机身，由机身承载的一个或多个翅片，由机身携带的反向旋转螺旋桨，以及被配置为禁用目标UAV的禁用系统。

    Auto-injector countermeasure for unmanned aerial vehicles
    85.
    发明授权
    Auto-injector countermeasure for unmanned aerial vehicles 有权
    无人驾驶飞行器的自动注射器对策

    公开(公告)号：US09175934B1

    公开(公告)日：2015-11-03

    申请号：US13680597

    申请日：2012-11-19

    Applicant: Lockheed Martin Corporation

    Inventor： James C Kilian

    IPC: F41G9/00 ,  F41H13/00 ,  G05D1/12 ,  B64D47/08

    CPC classification number: F41H13/00 ,  B64C2201/121 ,  B64D47/08 ,  F41H11/02 ,  G05D1/12

    Abstract: An injector device configured to mount to a predatory unmanned aerial vehicle (UAV) for non-destructively disabling and controlling a threat UAV comprises a rigid housing having a hollow interior. A controllable mount structure attaches the rigid housing to the predatory UAV and aligns the housing opening with the fuselage or payload of the threat UAV. A rigid penetrator rod disposed in the interior of the housing is configured to pierce the fuselage and hence payload of the threat UAV. A conduit coupled to the penetrator rod enables a disabling substance to be conveyed through the penetrator rod and into the payload of the threat UAV. An ejector propels the penetrator rod from the housing and into the payload of the threat UAV in response to a trigger when the threat UAV is within a predetermined range.

    Abstract translation: 配置成安装到掠夺式无人驾驶飞行器（UAV）用于非破坏性地禁用和控制威胁无人机的喷射器装置包括具有中空内部的刚性壳体。 可控制的安装结构将刚性壳体连接到掠夺式无人机，并将壳体开口与威胁无人机的机身或有效载荷对准。 设置在壳体内部的刚性穿透杆配置成刺穿机身并因此穿过威胁无人机的有效载荷。 连接到穿透杆的导管使得能够将致残物质输送通过穿透杆并进入威胁无人机的有效载荷。 当威胁UAV在预定范围内时，喷射器响应于触发器将穿透杆从壳体推进到威胁无人机的有效载荷中。

    Power safety instrument system
    86.
    发明授权
    Power safety instrument system 有权
    电力安全仪表系统

    公开(公告)号：US09035802B2

    公开(公告)日：2015-05-19

    申请号：US13641325

    申请日：2010-12-22

    Applicant: James M. McCollough ,  Erik Oltheten ,  Nicholas Lappos

    Inventor： James M. McCollough ,  Erik Oltheten ,  Nicholas Lappos

    IPC: G08B21/00 ,  B60Q1/00 ,  B64C27/04 ,  B64D43/00

    CPC classification number: G01C23/00 ,  B60Q1/00 ,  B64C27/00 ,  B64C27/006 ,  B64C27/04 ,  B64C27/52 ,  B64C29/00 ,  B64C39/024 ,  B64C2201/108 ,  B64C2201/121 ,  B64D43/00 ,  B64D45/00 ,  G01C21/00 ,  G01D7/02 ,  G05D17/02

    Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.

    Abstract translation: 电力安全系统被配置为在飞行器中提供电力信息。 电力安全系统包括具有电力需求指示器和功率可用指示器的电力安全仪器，每个指示器位于显示器上。 所需电源指示灯和电源指示灯的位置表示执行悬停飞行操作所需的电力和功率。 电力安全系统可以在飞行计划模式或当前飞行模式下操作。 电力安全系统使用至少一个传感器来测量对所需功率和可用功率有影响的变量。

    Weapons platform construction
    89.
    发明授权
    Weapons platform construction 有权
    武器平台建设

    公开(公告)号：US07207256B2

    公开(公告)日：2007-04-24

    申请号：US10495131

    申请日：2002-10-24

    Applicant: James Michael O'Dwyer

    Inventor： James Michael O'Dwyer

    IPC: F41A23/02

    CPC classification number: B64D7/00 ,  B64C2201/121 ,  B64D7/04 ,  B64D7/08 ,  F41A21/48 ,  F41A23/00 ,  F42B5/035

    Abstract: A vehicular weapons platform (30) including a plurality of barrel assemblies (10), wherein each barrel assembly includes a barrel (11), a plurality of projectiles (14) axially disposed within the barrel for operative sealing engagement with the bore of the barrel (11) and discrete propellant charges (15) for propelling respective projectiles sequentially through the muzzle of the barrel; and at least one of said plurality of barrel assemblies (10) includes a barrel which also forms a structural member of the weapons platform. In one preferred form, the weapons platform takes the form of a small combat aerial vehicle (SCAV) (30), wherein the barrel assemblies (10) form the airframe. A method of constructing a weapons platform from the barrel assemblies is also described.

    Abstract translation: 一种包括多个筒体组件（10）的车辆武器平台（30），其中每个筒体组件包括筒体（11），多个射出件（14），其轴向设置在所述筒体内，用于与所述筒体 （11）和离散的推进剂装料（15），用于依次通过枪管的枪口推动各射弹; 并且所述多个筒组件（10）中的至少一个包括还形成武器平台的结构构件的筒体。 在一种优选形式中，武器平台采取小作战飞行器（SCAV）（30）的形式，其中枪管组件（10）形成机身。 还描述了从筒组件构造武器平台的方法。

    Immersible unmanned air vehicle and system for launch, recovery, and re-launch at sea
    90.
    发明授权
    Immersible unmanned air vehicle and system for launch, recovery, and re-launch at sea 失效
    潜艇无人机和发射，恢复和重新发射的系统

    公开(公告)号：US07097136B2

    公开(公告)日：2006-08-29

    申请号：US10823434

    申请日：2004-04-13

    Applicant: Robert A. Ruszkowski, Jr.

    Inventor： Robert A. Ruszkowski, Jr.

    IPC: B64C35/00

    CPC classification number: B64C1/062 ,  B63G8/28 ,  B63G8/30 ,  B63G13/00 ,  B64C35/00 ,  B64C37/00 ,  B64C39/024 ,  B64C2001/0045 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/205 ,  F41F3/07 ,  F42B15/20

    Abstract: A sea-launched and recovered unmanned aircraft is disclosed. The aircraft is jet-powered and has features and systems to maintain watertight integrity such that it may be released from a submerged submarine or dropped into a body of water by a ship or an aircraft. The aircraft is buoyant and remains at or near the water surface before its rockets are ignited. The rockets propel the air vehicle out of the sea and accelerate it to flying speed at which time a jet engine is started and the rockets are jettisoned. The air vehicle performs its mission independently or in conjunction with other ones of the air vehicles. The air vehicle then returns to an assigned splashdown point at sea via, for example, an engine-off “whip-stall” maneuver. A submarine or ship may retrieve the air vehicle and readies it for another mission.

    Abstract translation: 披露了一架海上发射和回收的无人机。 飞机是喷气式动力的，并具有保持水密完整性的特征和系统，使得其可以从潜水艇释放或由船或飞机落入水体。 这架飞机是浮力的，并且在其火箭点火之前保持在水面或附近。 火箭将空中车辆推出海面，并将其加速到飞行速度，此时起飞喷气发动机，火箭被抛弃。 机动车辆独立地或与其他机动车辆一起执行任务。 然后，空中飞行器通过例如发动机关闭“鞭炮”操纵返回到海上指定的飞溅点。 潜艇或船只可以检索空中飞行器并准备进行另一个飞行任务。

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