COLLAPSIBLE UNMANNED AERIAL VEHICLE (UAV)
    92.
    发明申请

    公开(公告)号:US20170313400A1

    公开(公告)日:2017-11-02

    申请号:US15497704

    申请日:2017-04-26

    Inventor: Igor Zhydanov

    Abstract: Disclosed is an aerial vehicle such as an unmanned aerial vehicle (UAV). In one implementation, the vehicle includes a base and one or more front-facing arms extending from the base. Each front facing arm includes an inner segment affixed to the base and an outer segment. The vehicle also includes a rear-facing arm affixed to the base. In another implementation, a UAV includes one or more arms mounted to a base. At least one of the arms includes a first segment that is proximate to the base and a second segment that is distant from the base. A first hinge connects the first segment and the second segment. Various dimensions of the UAV are reduced when the arm(s) are folded along the first hinge.

    Multi-Rotor Structure Applied to Unmanned Aerial Vehicle

    公开(公告)号:US20170152035A1

    公开(公告)日:2017-06-01

    申请号:US15364861

    申请日:2016-11-30

    Abstract: The present invention discloses a multi-rotor structure applied to an unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle includes a fuselage, first rotors, second rotors and rotor shafts; and the multi-rotor structure includes first rotary connecting pieces and second rotary connecting pieces. The first rotary connecting piece includes a first motor and a first dismounting thread group, the first rotor is detachably connected with the first motor through the first dismounting thread group to achieve the mounting or dismounting between the first rotor and the first motor by rotating the first rotor; the second rotary connecting piece includes a second motor and a second dismounting thread group, and the second rotor is detachably connected with the second motor through the second dismounting thread group to achieve the mounting or dismounting between the second rotor and the second motor by rotating the second rotor. The present invention has the advantages of being fast, portable and high in working efficiency.

    LAUNCH CANISTER WITH AIR BAG RAM
    96.
    发明申请
    LAUNCH CANISTER WITH AIR BAG RAM 审中-公开
    推出带有空气袋RAM的CANISTER

    公开(公告)号:US20170066543A1

    公开(公告)日:2017-03-09

    申请号:US14845615

    申请日:2015-09-04

    Abstract: A payload launch system that uses an inflatable air bag ram to launch a payload, such as an unmanned aerial vehicle, from a launch chamber of a launch tube. The air bag ram seals with the interior surface of the launch tube to isolate a dump valve that controls the flow of compressed gas from a gas storage chamber into the air bag ram. The air bag ram sealing with the interior surface of the launch tube isolates the dump valve, both pre-launch and post-launch, from any water or debris carried in with water in which the payload launch system is disposed

    Abstract translation: 一种有效载荷发射系统,其使用可充气气囊冲压器从发射管的发射室发射有效载荷,例如无人驾驶飞行器。 气囊柱塞与发射管的内表面密封,以隔离一个排气阀,其将压缩气体从气体储存室流入气囊冲头。 与发射管内表面密封的气囊柱塞将排放阀(预发射和发射后)与运载有有效载荷发射系统的水携带的任何水或碎屑隔离

    UNMANNED AERIAL VEHICLE ARM ADJUSTMENT DEVICE AND UNMANNED AERIAL VEHICLE
    97.
    发明申请
    UNMANNED AERIAL VEHICLE ARM ADJUSTMENT DEVICE AND UNMANNED AERIAL VEHICLE 审中-公开
    无人机营运车辆调整装置和无人驾驶的空中客车

    公开(公告)号:US20170015403A1

    公开(公告)日:2017-01-19

    申请号:US15210521

    申请日:2016-07-14

    Abstract: An unmanned aerial vehicle arm adjustment device for adjusting an unmanned aerial vehicle arm into a folding state or an extracting state with respect to a fuselage of the aerial vehicle includes: left and right curb plates connected to the fuselage; a rocking arm connected to the unmanned aerial vehicle arm, wherein one end of the rocking arm is articulated with the left and right curb plates, and a first engaging part is provided on the rocking arm; and a locking member articulated with the left and right curb plates, wherein the locking member is provided with a second engaging part for engaging with the first engaging part; wherein the locking member is adapted to rotate in a first direction to force the second engaging part to engage with the first engaging part so as to hold the rocking arm such that the unmanned aerial vehicle arm is in the extracting state; and wherein the locking member is adapted to rotate in a second direction opposite to the first direction to force the second engaging part to disengage with the first engaging part so as to release the rocking arm such that the unmanned aerial vehicle arm is able to be rotated into the folding state.

    Abstract translation: 用于将无人驾驶飞行器臂调整成相对于飞行器的机身的折叠状态或提取状态的无人驾驶飞行器臂调节装置包括:连接到机身的左右路缘板; 连接到无人驾驶飞行器臂的摇臂,其中摇臂的一端与左右路缘板铰接,在摇臂上设置有第一接合部; 以及与所述左右路缘板铰接的锁定构件,其中,所述锁定构件设置有用于与所述第一接合部接合的第二接合部; 其中所述锁定构件适于沿第一方向旋转以迫使所述第二接合部与所述第一接合部接合,以便保持所述摇臂,使得所述无人驾驶飞行器臂处于所述提取状态; 并且其中所述锁定构件适于沿与所述第一方向相反的第二方向旋转,以迫使所述第二接合部分与所述第一接合部分脱离,以便释放所述摇臂,使得所述无人驾驶飞行器臂能够旋转 进入折叠状态。

    Vertical Takeoff and Landing Unmanned Aircraft System
    98.
    发明申请
    Vertical Takeoff and Landing Unmanned Aircraft System 审中-公开
    垂直起飞和着陆无人机系统

    公开(公告)号:US20170008625A1

    公开(公告)日:2017-01-12

    申请号:US15164718

    申请日:2016-05-25

    Abstract: A vertical takeoff and landing (VTOL) unmanned aircraft system (UAS) may be uniquely capable of VTOL via a folded wing design while also configured for powered flight as the wings are extended. In a powered flight regime with wings extended, the VTOL UAS may maintain controlled powered flight as a twin pusher canard design. In a zero airspeed (or near zero airspeed) nose up attitude in a VTOL flight regime with the wings folded, the unmanned aircraft system may maintain controlled flight using main engine thrust as well as vectored thrust as a vertical takeoff and landing aircraft. An airborne transition from VTOL flight regime to powered flight and vice versa may allow the VTOL UAS continuous controlled flight in each regime.

    Abstract translation: 垂直起飞和着陆(VTOL)无人驾驶飞机系统(UAS)可以通过折翼设计独特地实现垂直起降,同时还可以在机翼延伸时配置为动力飞行。 在具有扩展翼的动力飞行机构中,VTOL UAS可以保持受控的动力飞行作为双推杆的设计。 无人驾驶飞机系统可以以垂直起降飞行系统以零空速(或近零空速)起飞的姿态折叠起来,使用主发动机推力以及作为垂直起降飞机的向心推力来维持受控飞行。 从空中飞行任务飞行状态到动力飞行的空降过渡,反之亦然,可能使VTOL UAS在每个制度中持续控制飞行。

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