公开(公告)号：US20180001990A1

公开(公告)日：2018-01-04

申请号：US15198953

申请日：2016-06-30

Applicant: Insitu, Inc

Inventor： Chad Stuart Kossar ,  Bradley Yeomans ,  Matthew Grubb

IPC: B64C1/36 ,  B64C39/02 ,  F16B31/02

CPC classification number: B64C1/36 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/182 ,  F16B31/021

Abstract: A reusable frangible joint includes a first part having a hemispherical convex surface, and a second part defined by a reversely identical mating hemispherical concave surface. The convex and concave surfaces of the joint are secured and held together in compression until a predetermined applied load causes the joint to fail. The joint includes at least one replaceable fastener that rigidly secures and holds the respective concave and convex surfaces together. The fastener, designed to be the only part of the joint configured to fail, is sheared apart under the predetermined load, which results in separation of the concave and convex parts from one another irrespective of from which direction or to which part the impact load is applied. The failed fastener can then be replaced, wherein the frangible joint becomes immediately reusable, as having incurred no other damage by the impact load.

公开(公告)号：US20170369150A1

公开(公告)日：2017-12-28

申请号：US15608758

申请日：2017-05-30

Applicant: SIERRA NEVADA CORPORATION

Inventor： Ken FINKLEA ,  Carlos MIRALLES

IPC: B64C3/56 ,  B64D17/80 ,  B64C39/02

CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/08 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/201 ,  B64C2201/206 ,  B64C2201/208 ,  B64D17/80

Abstract: In one embodiment, a wing for an unmanned aerial vehicle is described. The unmanned aerial vehicle includes a first body of the wing with a first end proximate a body of the vehicle. A second end is opposite the first end. A first joint is on the first end of the first main body of the wing. The joint rotatably couples the wing to the vehicle. A second joint is on the second end of the vehicle. A second body of the wing is rotatably coupled to the first body via the second joint.

公开(公告)号：US20160355261A1

公开(公告)日：2016-12-08

申请号：US15176250

申请日：2016-06-08

Applicant: Howard Martin Chin ,  Kimberly A. Carraha

Inventor： Howard Martin Chin ,  Kimberly A. Carraha

IPC: B64D5/00 ,  B64C39/02

CPC classification number: B64D5/00 ,  B64C39/024 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/206

Abstract: An airborne drone launch and recovery apparatus for selectively launching drones located on the underside of a carrier aircraft or recovering drones following flight of the drones, the airborne launch and recovery apparatus has an extensible stinger slidable along the length of a stinger sheath between a retracted position proximal the rear portion of the carrier aircraft and an extended position in front of the carrier aircraft, and a catcher shuttle carried on the forward part of the stinger for extending into the non-turbulent air in front of the carrier aircraft when the stinger is in the extended position. The carrier shuttle includes a launch/recovery assembly for selectively either having a locked condition for the recovery guide of a drone prior to the positioning of the catcher shuttle in a selected for the launch of the drone, and having an open condition for receiving the recovery guide of a drone at the termination of the flight of the drone to terminate the flight.

Abstract translation: 一种空中无人机发射和恢复装置，用于选择性地发射位于载体飞行器的下侧上的无人机或在无人机的飞行之后恢复无人机，机载发射和恢复装置具有可伸长的刺针，沿着刺血刺鞘的长度在缩回位置 靠近载体飞行器的后部，并且在载体飞行器的前面延伸的位置，以及在托管架前部延伸到载体飞行器前方的非湍流空气中的捕手穿梭器，当托管架处于 延长的位置。 运输班车包括发射/恢复组件，用于选择性地具有用于无人机的恢复引导件的锁定状态，在捕集器穿梭机定位在被选择用于发射无人机之前，并且具有用于接收恢复的打开状态 在无人驾驶飞机终止时终止飞行的无人机指导。

公开(公告)号：US20160347477A1

公开(公告)日：2016-12-01

申请号：US14999290

申请日：2016-04-20

Applicant: Engineered Arresting Systems Corporation

Inventor： Andrew Tully ,  Dennis Page ,  Robert Withers ,  Kenneth Neeld ,  Richard L. Orner, JR.

IPC: B64F1/04 ,  B64C39/02

CPC classification number: B64F1/08 ,  B64C2201/084

Abstract: Embodiments of the present invention provide improvements to UAV launching systems. The disclosed launching system eliminates the use of hydraulic fluid and compressed nitrogen or air by providing an electric motor-driven tape that causes movement of a shuttle along a launcher rail. The shuttle is detachable from the motor-driven tape, such that stoppage of the tape can be separate from stoppage of the shuttle. Embodiments further provide a secondary arrestment strap. Further embodiments provide an anti-rollback latch system.

Abstract translation: 本发明的实施例提供了对UAV发射系统的改进。 所公开的发射系统通过提供使电动机驱动的带子沿着发射轨运动，从而消除了液压流体和压缩的氮气或空气的使用。 梭子可从马达驱动的带子上拆下，使得带子的停止可以与梭子的停止分开。 实施例进一步提供了次级止动带。 另外的实施例提供了一种防回滚锁存系统。

公开(公告)号：US20160325849A1

公开(公告)日：2016-11-10

申请号：US14707424

申请日：2015-05-08

Applicant: AAI Corporation

Inventor： Stephen W. Miller ,  Zachary J. Smith ,  Peter J. Helman

IPC: B64F1/06 ,  B64F1/02 ,  B64C39/02

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/182 ,  B64F1/02 ,  B64F1/025

Abstract: An unmanned aerial vehicle (UAV) platform includes a stationary base constructed and arranged to reside over a fixed location on a surface (e.g., a ground location, a ship's deck, a trailer or other vehicle, etc.). The UAV platform further includes a set of UAV interfaces constructed and arranged to interface directly with a UAV (e.g., a launcher, a net apparatus, etc.). The UAV platform further includes a turntable assembly which couples to the stationary base. The turntable assembly is constructed and arranged to couple to each UAV interface and control angular direction of that UAV interface over the fixed location. A method of operating a UAV platform includes deploying the UAV platform over a fixed location, preparing a UAV interface on a turntable assembly of the UAV platform, and rotating the turntable to control angular direction of the UAV interface over the fixed location.

Abstract translation: 无人飞行器（UAV）平台包括构造和布置成居住在表面（例如，地面位置，船舶甲板，拖车或其他车辆等）上的固定位置的固定基座。 无人机平台还包括一组UAV接口，其被构造和布置成与UAV（例如，发射器，网络设备等）直接接口。 UAV平台还包括一个转盘组件，它与固定基座相连。 转盘组件被构造和布置成耦合到每个UAV接口并且控制该UAV接口在固定位置上的角度方向。 一种操作无人机平台的方法包括在固定位置部署无人机平台，在无人机平台的转盘组件上准备无人机接口，旋转转盘，以控制无人机接口在固定位置的角度方向。

公开(公告)号：US20150267996A1

公开(公告)日：2015-09-24

申请号：US14281680

申请日：2014-05-19

Applicant: AeroVironment, Inc.

Inventor： Guan H. Su ,  Marcos Henry Rodriguez

IPC: F41F3/00 ,  B64C39/02

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/201 ,  B64F1/06 ,  F41B11/80 ,  F41F3/00 ,  F41F3/042 ,  F41F3/052 ,  F41F3/073

Abstract: An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV (400) having an exterior surface, an aerial vehicle (AV) tab (510) extending from the exterior surface, a tube (440) containing the UAV (400), the tube (440) including a tab stop (515) configured to controllably hinder travel of the AV tab (510) past the tab stop (515), and a pair of opposing tab guides (700, 705) configured to position the AV tab (510) for travel over the tab stop (515).

Abstract translation: 公开了一种无人驾驶飞行器（UAV）发射装置，其包括具有外表面的UAV（400），从外表面延伸的飞行器（AV）突片（510），包含无人机（400）的管（440） ），所述管（440）包括构造成可控制地阻碍所述AV突片（510）经过所述突片止动件（515）的移动的突片止动件（515），以及一对相对的突片引导件（700,705），其被配置为 AV选项卡（510），用于在制表位（515）上移动。

公开(公告)号：US09004393B2

公开(公告)日：2015-04-14

申请号：US13279827

申请日：2011-10-24

Applicant: Ronald M. Barrett-Gonzales

Inventor： Ronald M. Barrett-Gonzales

IPC: B64C27/24 ,  B64C29/02 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C27/24 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/084 ,  B64C2201/102

Abstract: Embodiments of the present invention include an aircraft capable of sustained out-of-ground-effect hover flight and sustained supersonic flight. At least some embodiments includes two wings powered by an engine to counterrotate while hovering, and to not rotate and sweep while flying at transonic and supersonic speeds. Other embodiments include two rotating wings that generate a force per unit area of under 100 lb/ft2 within the rotating wing disk during hover. Still other embodiment include a vehicle with rotating wings that can increase pitch to accelerate the aircraft, align the chord line of the wings with the airstream, and sweep the wings. Still further embodiments include a power plant that powers unducted rotating wings during hover and disengages from the wings to propel the aircraft at supersonic speeds.

Abstract translation: 本发明的实施例包括能够持续地面效应悬停飞行和持续的超音速飞行的飞机。 至少一些实施例包括由发动机驱动的两个翼，以在盘旋时反向旋转，并且在以跨音速和超音速飞行的同时不旋转和扫掠。 其它实施例包括两个旋转翼，其在悬停期间在旋转翼盘内产生每100英寸/ ft 2以下的每单位面积的力。 另外的实施例包括具有旋转翼的车辆，其可以增加俯仰以加速飞行器，将翼的弦线与气流对准，并且扫掠翼。 另外的实施例包括在悬停期间为未被引导的旋转翼提供动力的动力装置，并且与翼分离，以超音速推进飞行器。

公开(公告)号：US08894007B2

公开(公告)日：2014-11-25

申请号：US13558728

申请日：2012-07-26

Applicant: Andrew McComas ,  Jon Clark

Inventor： Andrew McComas ,  Jon Clark

IPC: B64F1/04 ,  B64F1/06

CPC classification number: B64F1/06 ,  B64C2201/084 ,  B64C2201/102

Abstract: A canister system for a folding aircraft may include a canister housing and a launch mechanism powered by one or more compression springs. A hand-operated drive mechanism may rotate a plurality of threaded rods to drive the launch mechanism from a released position to a cocked position, in which mechanical energy is stored in the springs. A latch mechanism may capture the launch mechanism in the cocked position. The canister may include a housing for receiving and storing the aircraft when the launch mechanism is in the cocked position. A trigger mechanism may release the latch mechanism, permitting the energy stored in the compressed springs to drive the launch mechanism toward the released position and propel the aircraft from the housing at launch velocity.

Abstract translation: 用于折叠飞机的罐系统可以包括罐壳体和由一个或多个压缩弹簧驱动的发射机构。 手动驱动机构可以旋转多个螺杆，以将发射机构从释放位置驱动到起动位置，其中机械能存储在弹簧中。 闩锁机构可以捕捉发动机构处于俯视位置。 罐可以包括用于在发射机构处于起动位置时接收和存储飞行器的壳体。 触发机构可以释放闩锁机构，允许存储在压缩弹簧中的能量将发射机构驱动到释放位置，并以发射速度将飞行器从壳体推进。

公开(公告)号：US08894006B2

公开(公告)日：2014-11-25

申请号：US13450887

申请日：2012-04-19

Applicant: John Charles Jones ,  Artem Igorevich Grigoryev ,  Luis Carlos Espinosa

Inventor： John Charles Jones ,  Artem Igorevich Grigoryev ,  Luis Carlos Espinosa

IPC: B64F1/04

CPC classification number: B64F1/06 ,  B64C2201/084

Abstract: A man-portable unmanned aerial system launcher (UAS) launcher includes a rail assembly having an internal track and a carriage assembly having a base configured to translate within the internal track. The carriage assembly also includes a cradle configured to support a UAS and a bracket configured to support the cradle above the base. The UAS launcher includes a launch control system configured to secure the carriage assembly in the launch-ready position until the launch control system receives a launch signal. The UAS launcher also includes one or more elastic members configured to engage the carriage assembly and the rail assembly. Once the carriage assembly is translated to the launch-ready position, strain is applied to the carriage assembly by the one or more elastic members. Release of the carriage assembly enables force generated by strain of the elastic members to propel the carriage assembly toward a launch position.

Abstract translation: 便携式无人机系统发射器（UAS）发射器包括具有内部轨道的轨道组件和具有被配置为在内部轨道内平移的底座的滑架组件。 托架组件还包括支架，其构造成支撑UAS和支架，所述托架被构造成支撑在基座上方的托架。 UAS发射器包括发射控制系统，其配置成将支架组件固定在发射准备位置，直到发射控制系统接收到发射信号。 UAS发射器还包括一个或多个弹性构件，其构造成接合滑架组件和轨道组件。 一旦滑架组件被转换到发射就绪位置，则通过一个或多个弹性构件将应变施加到滑架组件。 托架组件的释放使得由弹性构件的应变产生的力能够将托架组件推向发射位置。

公开(公告)号：US08740142B2

公开(公告)日：2014-06-03

申请号：US13901295

申请日：2013-05-23

Applicant: Aerovel Corporation

Inventor： Brian T. McGeer ,  Andreas H. von Flotow

IPC: B64F1/02

CPC classification number: B64F1/12 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/084 ,  B64C2201/182 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06 ,  B64F1/125 ,  B64F1/28 ,  B64F5/00

Abstract: Various embodiments of the present disclosure provide an apparatus configured to automatically retrieve, service, and launch an aircraft. For retrieval, the aircraft drops a weighted cable, and pulls it at low relative speed into a broad aperture of the apparatus. In certain instances, the cable is dragged along guiding surfaces of the apparatus into and through a slot until its free end is captured. The aircraft becomes anchored to the apparatus, and is pulled downward by the cable into a receptacle. Guiding surfaces of the receptacle adjust the position and orientation of a probe on the aircraft, directing the probe to mate with a docking fixture of the apparatus. Once mated, the aircraft is automatically shut down and serviced. When desired, the aircraft is automatically started and tested in preparation for launch, and then released into free flight. A full ground-handling cycle is thus accomplished with a simple, economical apparatus.