公开(公告)号：US20050133665A1

公开(公告)日：2005-06-23

申请号：US10759545

申请日：2004-01-16

Applicant: Brian Dennis ,  Brian McGeer ,  Cory Roeseler

Inventor： Brian Dennis ,  Brian McGeer ,  Cory Roeseler

IPC: B64C25/68 ,  B64C39/02 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06 ,  B64C25/00

CPC classification number: B64C39/024 ,  B64C25/68 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06

Abstract: Methods and apparatuses for capturing and constraining motion of unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured at an extendable boom. The boom can be extended to deploy a recovery line to retrieve the aircraft in flight. A trigger mechanism coupled to the recovery line can actuate a hoist device to reduce slack in the recovery line. A tension device coupled to the recovery line can absorb forces associated with the impact of the aircraft on the recovery line.

Abstract translation: 描述了用于捕获和约束无人驾驶飞机和其他飞行装置或射弹的运动的方法和装置。 在一个实施例中，飞机可以在可延伸的吊杆上被捕获。 可以扩展繁荣部署恢复线以在飞行中检索飞机。 联接到回收管线的触发机构可以启动提升装置以减少回收管线中的松弛。 耦合到回收管线的张紧装置可以吸收与飞机在回收管线上的冲击相关联的力。

公开(公告)号：US4410151A

公开(公告)日：1983-10-18

申请号：US182021

申请日：1980-08-28

Applicant: Heinz-Jochen Hoppner ,  Ulrich Kramer ,  Hugo Sgarz ,  Herbert Sadowski

Inventor： Heinz-Jochen Hoppner ,  Ulrich Kramer ,  Hugo Sgarz ,  Herbert Sadowski

IPC: B64C39/02 ,  F42B10/14 ,  B64F1/04 ,  F41F3/00

CPC classification number: B64C39/024 ,  F42B10/14 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/208

Abstract: A vehicle or craft is provided for propeller propulsion with start assist by a releasable rocket engine. The craft is launched from a silo of square-shaped cross-section containing the starter motor for the propeller, whose engine is started while the craft is still in the silo. Diagonally opposed corners of the silo are provided with rails, in which run guides on rudder fins of the craft. The wings are pivoted to the fuselage for deployment whereby the wing tips do not move forward. The rocket engine is jettisoned shortly after take-off by simple disengagement. Parts of the wings and/or the rear of the fuselage may be jettisoned shortly before the craft reaches the target area.

Abstract translation: 提供用于螺旋桨推进的车辆或工具，由可释放的火箭发动机开始辅助。 该工艺是从一个方形截面的筒仓中推出的，包含用于螺旋桨的起动电机，当发动机仍然在筒仓中时，发动机起动。 筒仓的对角线相对的角落设有导轨，其中在工艺的方向舵鳍上的行进导轨。 机翼枢转到机身进行部署，由此机翼尖端不向前移动。 火箭发动机在起飞后不久就被简单的分离。 机翼的部分和/或机身的后部可能在飞机到达目标区域之前不久就被抛弃。

公开(公告)号：US20230271700A1

公开(公告)日：2023-08-31

申请号：US17652705

申请日：2022-02-28

Applicant: Matthew W. TOWNSEND

Inventor： Matthew W. TOWNSEND

IPC: B64C29/02 ,  B64C39/02 ,  B64C17/02 ,  B64C3/40

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C17/02 ,  B64C3/40 ,  B64C2201/028 ,  B64C2201/102 ,  B64C2201/088 ,  B64C2201/128

Abstract: A drone can be used to carry a payload. The drone can include at least two wings extending from a fuselage and propellers that allow the drone to fly in a horizontal orientation. The drone can takeoff and land from a vertical orientation via landing rods at the rear of the fuselage. The drone also includes an adjustable center of gravity and/or an adjustable center of lift. The center of gravity can be adjusted by changing the weight of payload located fore and aft of the center of gravity or moving at least a portion of the payload fore or aft along the fuselage. The center of lift can be adjusted by swinging the wings away from or towards the fuselage or sliding the wings fore or aft along the fuselage such that the center of lift is adjacent to the center of gravity.

公开(公告)号：US20230202652A1

公开(公告)日：2023-06-29

申请号：US17645752

申请日：2021-12-23

Applicant: OCTOFAN SAS

Inventor： Pierre Convert

IPC: B64C29/00 ,  B64C3/54 ,  B64C11/00 ,  B64C11/48 ,  B64C39/02 ,  B64C39/08

CPC classification number: B64C29/0033 ,  B64C3/54 ,  B64C11/001 ,  B64C11/48 ,  B64C39/024 ,  B64C39/08 ,  B64C2201/088 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/162

Abstract: The aircraft comprises a fuselage defining a fuselage main axis. The fuselage comprises a docking system for fixing removable nacelles. The aircraft has wings equipped with tilting actuators for rotating wings about rotation axes parallel to the fuselage main axis and at least six propellers mechanically connected to the fuselage. The aircraft also has at least one cryo-hydrogen tank and at least one fuel cell for supplying power to the propellers, and
A capacitor for supplying power to the propellers, charged by at least one fuel cell. This capacitor stores electrical energy greater than the energy needed by all the propellers for ten seconds of hovering flight. Each propeller is equipped with a tilting actuator for rotating the propeller about a rotation axis making an angle of less than 45 degrees with a plane perpendicular to the fuselage main axis. The fuselage having a forward and a rear portion defining a forward to rear order of the propellers, in cruise flight, the two forward propellers are activated to provide vertical thrust, the intermediate propellers between the forward and rearmost propellers are not activated and the two rearmost propellers are activated to provide horizontal thrust.

公开(公告)号：US20190248469A1

公开(公告)日：2019-08-15

申请号：US15895192

申请日：2018-02-13

Applicant: Bell Helicopter Textron Inc.

Inventor： Levi Charles HEFNER ,  Danielle Lynn MOORE ,  Dakota Charles EASLEY

IPC: B64C9/02 ,  B64C5/02 ,  B64C39/02 ,  B64C29/02

CPC classification number: B64C9/02 ,  B64C5/02 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/102 ,  B64C2201/108

Abstract: An example of an aerial vehicle includes a rudder removably connected to the aerial vehicle by a twist lock mechanism. The twist lock mechanism is biased in a locked position by an elastic member.

公开(公告)号：US20190210725A1

公开(公告)日：2019-07-11

申请号：US16352694

申请日：2019-03-13

Applicant: Walmart Apollo, LLC

Inventor： Robert L. Cantrell ,  John P. Thompson ,  David C. Winkle ,  Michael D. Atchley ,  Donald R. High ,  Todd D. Mattingly ,  John J. O'Brien ,  John F. Simon

IPC: B64C39/02 ,  B64C33/02 ,  B64C3/56 ,  B64C3/42

CPC classification number: B64C39/024 ,  B64C3/42 ,  B64C3/56 ,  B64C33/02 ,  B64C2201/021 ,  B64C2201/022 ,  B64C2201/025 ,  B64C2201/027 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/14 ,  B64C2201/162

Abstract: Systems, apparatuses, and methods are provided herein for unmanned flight optimization. A system for unmanned flight comprises a set of motors configured to provide locomotion to an unmanned aerial vehicle, a set of wings coupled to a body of the unmanned aerial vehicle via an actuator and configured to move relative to the body of the unmanned aerial vehicle, a sensor system on the unmanned aerial vehicle, and a control circuit. The control circuit being configured to: control the unmanned aerial vehicle, cause the set of motors to lift the unmanned aerial vehicle, detect condition parameters based on the sensor system, determine a position for the set of wings based on the condition parameters, and cause the actuator to move the set of wings to the wing position while the unmanned aerial vehicle is in flight.

公开(公告)号：US20180257760A1

公开(公告)日：2018-09-13

申请号：US15981623

申请日：2018-05-16

Applicant: The Boeing Company

Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

IPC: B64C3/30 ,  B64C39/02

CPC classification number: B64C3/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/105

Abstract: A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

公开(公告)号：US20180086434A1

公开(公告)日：2018-03-29

申请号：US15567585

申请日：2016-04-20

Applicant: George Michael Cook

Inventor： George Michael Cook ,  Jonathan Edward Cook ,  Michael Kevin Cook

IPC: B64C13/28 ,  B64C3/56 ,  B64C1/06 ,  B64C31/02 ,  B64C39/02

CPC classification number: B64C13/30 ,  B64C1/061 ,  B64C3/56 ,  B64C13/28 ,  B64C31/02 ,  B64C39/024 ,  B64C2001/0054 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2211/00

Abstract: An aircraft for the autonomous aerial delivery of a load to a target location, the aircraft comprising an airframe having at least one adjustable control structure for controlling the flight of the aircraft and a main body adapted to receive a load a self-contained control module releaseably connected to the airframe, the control module containing an actuator for adjusting the control structure and a controller for producing an electrical drive signal for controlling the actuator; and at least one linkage extending from the control module to the at least one adjustable control structure so as to operably connect the control module to the at least one adjustable control structure, wherein the actuator of the control module is adapted to adjust the at least one adjustable control structure using the at least one linkage so as to control the flight of the aircraft and to steer the aircraft to the target location.

公开(公告)号：US20180072414A1

公开(公告)日：2018-03-15

申请号：US15698516

申请日：2017-09-07

Applicant: Wal-Mart Stores, Inc.

Inventor： Robert L. Cantrell ,  John P. Thompson ,  David C. Winkle ,  Michael D. Atchley ,  Donald R. High ,  Todd D. Mattingly ,  John J. O'Brien ,  John F. Simon

IPC: B64C39/02 ,  B64C3/42 ,  B64C33/02 ,  B64C3/56

CPC classification number: B64C39/024 ,  B64C3/42 ,  B64C3/56 ,  B64C33/02 ,  B64C2201/021 ,  B64C2201/022 ,  B64C2201/025 ,  B64C2201/027 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/14 ,  B64C2201/162

Abstract: Systems, apparatuses, and methods are provided herein for unmanned flight optimization. A system for unmanned flight comprises a set of motors configured to provide locomotion to an unmanned aerial vehicle, a set of wings coupled to a body of the unmanned aerial vehicle via an actuator and configured to move relative to the body of the unmanned aerial vehicle, a sensor system on the unmanned aerial vehicle, and a control circuit. The control circuit being configured to: retrieve a task profile for a task assigned to the unmanned aerial vehicle, cause the set of motors to lift the unmanned aerial vehicle, detect condition parameters based on the sensor system, determine a position for the set of wings based on the task profile and the condition parameters, and cause the actuator to move the set of wings to the wing position while the unmanned aerial vehicle is in flight.

公开(公告)号：US20170334542A1

公开(公告)日：2017-11-23

申请号：US15161372

申请日：2016-05-23

Applicant: The Boeing Company

Inventor： Daniel Christopher Stanley ,  John Hershey Fogarty

IPC: B64C3/56 ,  B64C39/02 ,  F42B15/00 ,  F42B10/14 ,  F42B30/14 ,  F42B15/10

CPC classification number: B64C3/56 ,  B64C39/02 ,  B64C2201/102 ,  F42B10/14 ,  F42B15/105

Abstract: A airborne vehicle comprising a fuselage, a folding wing-like structure which is movable from a stowed position to a deployed position, and a hinge mechanism which couples the folding wing-like structure to the fuselage in a manner so that the folding wing-like structure displaces and rotates during movement from the stowed position to the deployed position. The hinge mechanism is housed within an outer mold line of the fuselage and folding wing-like structure to decrease the signature of the airborne vehicle.