公开(公告)号：US20180244383A1

公开(公告)日：2018-08-30

申请号：US15755187

申请日：2016-08-30

Applicant: UNIVERSITY OF MARYLAND, COLLEGE PARK

Inventor： EVANDRO GURGEL DO AMARAL VALENTE ,  NORMAN M. WERELEY ,  EDUARDO GURGEL DO AMARAL VALENTE

IPC: B64C37/00 ,  B64C39/10 ,  B64C29/00 ,  B64C29/02 ,  B64C15/12 ,  B64C5/02 ,  B64C11/46 ,  B64C19/00

CPC classification number: B64C37/00 ,  B64C5/02 ,  B64C11/46 ,  B64C15/12 ,  B64C17/02 ,  B64C19/00 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/205 ,  B64C2201/208 ,  B64C2211/00 ,  B64D29/00

Abstract: The universal vehicle system is designed with a lifting body which is composed of a plurality of interconnected modules which are configured to form an aerodynamically viable contour of the lifting body which including a front central module, a rear module, and thrust vectoring modules displaceably connected to the front central module and operatively coupled to respective propulsive mechanisms. The thrust vectoring modules are controlled for dynamical displacement relative to the lifting body (in tilting and/or translating fashion) to direct and actuate the propulsive mechanism(s) as needed for safe and stable operation in various modes of operation and transitioning therebetween in air, water and terrain environments.

公开(公告)号：US20180237135A1

公开(公告)日：2018-08-23

申请号：US15896894

申请日：2018-02-14

Applicant: MARTIN UAV, LLC

Inventor： Stephen MORRIS

IPC: B64C29/02 ,  B64C11/00 ,  G05D1/08 ,  G05D1/10 ,  B64C9/00

CPC classification number: B64C29/02 ,  B64C11/001 ,  B64C39/024 ,  B64C2009/005 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/162 ,  G05D1/0858 ,  G05D1/102

Abstract: An aircraft includes a fuselage, a wing, a ducted fan and a controller. The wing and the ducted fan are coupled to the fuselage. The controller is operable to control the aircraft in a vertical flight mode, a horizontal flight mode, and transition the aircraft from the vertical flight mode to the horizontal flight mode.

公开(公告)号：US20180178910A1

公开(公告)日：2018-06-28

申请号：US15852444

申请日：2017-12-22

Applicant: Korea Advanced Institute of Science and Technology

Inventor： Dongsoo HAR ,  Sang Min LEE

IPC: B64C29/00 ,  B64D27/24 ,  B64D41/00

CPC classification number: B64D27/24 ,  B64C3/385 ,  B64C5/02 ,  B64C11/001 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  B64D41/007 ,  F15B15/06 ,  F16H19/001 ,  F16H19/04 ,  F16H21/44 ,  Y02T50/62

Abstract: An aerial vehicle includes: a main body; two main wings arranged to the main body; two main wing tilting control units coupled to the main wings to control the main wings to tilt independently; two main propulsion units arranged to the main wings; tail wings arranged to a rear side of the main body; a rudder arranged to the tail wing; a rudder tilting control unit to control the rudder to tilt; a tail propulsion unit arranged to the rear side of the main body; a tail tilting control unit to control the tail propulsion unit to tilt; a power unit to provide power to the main and tail propulsion units; and a position control unit to control the main wing tilting control units, the main propulsion units, the rudder tilting control unit, the tail propulsion unit, the tail tilting control unit to adjust position of the aerial vehicle.

公开(公告)号：US09994307B2

公开(公告)日：2018-06-12

申请号：US15081163

申请日：2016-03-25

Applicant: The United States of America as represented by the Secretary of the Navy

Inventor： Hoa G. Nguyen ,  Aaron B. Burmeister

IPC: B64C25/28 ,  B64C25/32 ,  B64C25/52 ,  B64C29/00 ,  B64C39/02 ,  B64C25/00

CPC classification number: B64C25/28 ,  B64C25/32 ,  B64C25/52 ,  B64C29/00 ,  B64C39/024 ,  B64C2025/008 ,  B64C2025/325 ,  B64C2201/088 ,  B64C2201/141 ,  B64C2201/18

Abstract: A system for landing, comprising a vertical-take-off-and-landing (VTOL) unmanned air vehicle (UAV) having landing gear, wherein the landing gear is telescopic and comprises a sensor, and wherein the landing gear is compressed upon landing on a surface, and the compression causes a signal to be sent to a system that computes the slope of the ground surface using the length of the compressed landing gear and the attitude of the UAV. If the center of gravity falls within the support area, the legs are locked and the UAV power is turned off. If the center of gravity falls outside the support area, the UAV is forced to take off and find a safer landing spot.

公开(公告)号：US09969491B2

公开(公告)日：2018-05-15

申请号：US14843329

申请日：2015-09-02

Applicant: THE BOEING COMPANY

Inventor： James David Strayer

IPC: B64F1/04 ,  B64C39/02 ,  B64D1/02 ,  B64C5/06

CPC classification number: B64C39/024 ,  B63G3/04 ,  B63G2008/004 ,  B63G2008/008 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/167 ,  B64C2201/201 ,  B64C2201/205

Abstract: A drone launch system includes a canister defining an internal cavity, and a drone positioned within the internal cavity in a stowed state. The drone is configured to be ejected from the canister and transition from the stowed state into a deployed state outside of the canister. A method for launching a drone, the method includes positioning the drone in a stowed state in an internal cavity of a canister, ejecting the drone from the canister, and transitioning the drone into a deployed state after the ejecting operation.

公开(公告)号：US20180127092A1

公开(公告)日：2018-05-10

申请号：US15687936

申请日：2017-08-28

Applicant: Patrick del Castillo ,  Jason Curtis Miller

Inventor： Patrick del Castillo ,  Jason Curtis Miller

IPC: B64C37/00 ,  B60F5/02 ,  B64C39/02 ,  B64D1/22 ,  B64C11/28 ,  B62D57/032

CPC classification number: B64C37/00 ,  B60F5/02 ,  B62D57/032 ,  B64C11/28 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/146 ,  B64C2201/165 ,  B64D1/22

Abstract: The present application discloses an apparatus capable of walking and flight. This apparatus includes a central section supported by a plurality of limbs, wherein a distal end of each of the plurality of limbs defines a contact surface. These limbs are configured to generate a walking-type motion in which the contact surfaces of the limbs cooperate with an environmental surface in a manner sufficient to propel the central section relative the environmental surface. The apparatus further includes a motor operably coupled to at least one limb of the plurality of limbs, wherein the motor is drivingly coupled to a propeller, and wherein the motor and propeller are configured to propel the central section in flight.

公开(公告)号：US09896200B2

公开(公告)日：2018-02-20

申请号：US15332391

申请日：2016-10-24

Applicant: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration

Inventor： William J. Fredericks ,  Mark D. Moore ,  Ronald C. Busan ,  Paul M. Rothhaar ,  David D. North ,  William M. Langford ,  Christopher T. Laws ,  William T. Hodges ,  Zachary R. Johns ,  Sandy R. Webb

IPC: B64C29/00 ,  B64C39/00 ,  B64C11/28 ,  B64C25/52 ,  B64D27/24 ,  B64C3/40 ,  B64C9/14 ,  B64D27/26 ,  B64C11/50 ,  B64C25/32 ,  B64C3/38 ,  B64C39/02 ,  B64C5/02 ,  B64D27/02

CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C3/40 ,  B64C5/02 ,  B64C9/14 ,  B64C11/28 ,  B64C11/50 ,  B64C25/32 ,  B64C25/52 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/24 ,  B64D27/26 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64 ,  Y10S903/903

Abstract: Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.

公开(公告)号：US20170300066A1

公开(公告)日：2017-10-19

申请号：US15131914

申请日：2016-04-18

Applicant: LATITUDE ENGINEERING, LLC

Inventor： Jason Michael K. Douglas ,  Justin Armer ,  Carlos Murphy

IPC: G05D1/08 ,  B64C29/00 ,  B64C39/02

CPC classification number: G05D1/0816 ,  B64C29/0008 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/141 ,  G05D1/0833 ,  G05D1/0858

Abstract: An unmanned aircraft includes a forward propulsion system comprising one or more forward thrust engines and one or more corresponding rotors coupled to the forward thrust engines; a vertical propulsion system comprising one or more vertical thrust engines and one or more corresponding rotors coupled to the vertical thrust engines; a plurality of sensors; and a yaw control system, that includes a processor configured to monitor one or more aircraft parameters received from at least one of the plurality of sensors and to enter a free yaw control mode based on the received aircraft parameters.

公开(公告)号：US20170274988A1

公开(公告)日：2017-09-28

申请号：US15081163

申请日：2016-03-25

Applicant: The United States of America as represented by the

Inventor： Hoa G. Nguyen ,  Aaron B. Burmeister

IPC: B64C25/28 ,  B64C39/02 ,  B64C25/52 ,  B64C29/00 ,  B64C25/32

CPC classification number: B64C25/28 ,  B64C25/32 ,  B64C25/52 ,  B64C29/00 ,  B64C39/024 ,  B64C2025/008 ,  B64C2025/325 ,  B64C2201/088 ,  B64C2201/141 ,  B64C2201/18

Abstract: A system for landing, comprising a vertical-take-off-and-landing (VTOL) unmanned air vehicle (UAV) having landing gear, wherein the landing gear is telescopic and comprises a sensor, and wherein the landing gear is compressed upon landing on a surface, and the compression causes a signal to be sent to a system that computes the slope of the ground surface using the length of the compressed landing gear and the attitude of the UAV. If the center of gravity falls within the support area, the legs are locked and the UAV power is turned off. If the center of gravity falls outside the support area, the UAV is forced to take off and find a safer landing spot.

公开(公告)号：US20170240275A1

公开(公告)日：2017-08-24

申请号：US15456450

申请日：2017-03-10

Applicant: Jetoptera, Inc.

Inventor： Andrei Evulet

IPC: B64C29/04 ,  B64C39/02 ,  B64C11/00 ,  B64C9/00 ,  B64C39/12 ,  B64D27/20

CPC classification number: B64C29/04 ,  B64C9/38 ,  B64C11/001 ,  B64C15/00 ,  B64C21/00 ,  B64C29/02 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/10 ,  B64C2201/104 ,  B64C2201/162 ,  B64D27/10 ,  B64D27/20 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04 ,  B64D2033/0273 ,  Y02T50/166 ,  Y02T50/44

Abstract: A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.