公开(公告)号：US12214875B2

公开(公告)日：2025-02-04

申请号：US17797808

申请日：2021-02-05

Applicant: AEROVIRONMENT, INC.

Inventor： Greg T. Kendall

IPC: B64C3/18 ,  B64C3/10 ,  B64C3/26 ,  B64C39/02 ,  B64U10/25 ,  B64U30/10

Abstract: Systems, devices, and methods including a leading edge tubular member; an upper tubular member; a lower tubular member; one or more upper rib members connected between the leading edge tubular member and the upper tubular member; one or more lower rib members connected between the leading edge tubular member and the lower tubular member; a rigid sandwich shell disposed between the upper tubular member and the leading edge tubular member; and a sandwich shear web disposed between the upper tubular member and the lower tubular member; where the rigid sandwich shell and the sandwich shear web form a D-shape.

公开(公告)号：US12210346B2

公开(公告)日：2025-01-28

申请号：US18516038

申请日：2023-11-21

Applicant: AeroVironment, Inc.

Inventor： Quentin Lindsey ,  Henry Thome Won

IPC: G05D1/00 ,  B64C29/00 ,  G08G5/00 ,  B64U10/20 ,  B64U30/295 ,  B64U101/32

Abstract: Systems, devices, and methods for receiving, by a processor having addressable memory, data representing a geographical area for imaging by one or more sensors of an aerial vehicle; determining one or more straight-line segments covering the geographical area; determining one or more waypoints located at an end of each determined straight-line segment, where each waypoint comprises a geographical location, an altitude, and a direction of travel; determining one or more turnarounds connecting each of the straight-line segments, where each turnaround comprises one or more connecting segments; and generating, by the processor, a flight plan for the aerial vehicle comprising: the determined one or more straight-line segments and the determined one or more turnarounds connecting each straight-line segment.

公开(公告)号：US20250013239A1

公开(公告)日：2025-01-09

申请号：US18895055

申请日：2024-09-24

Applicant: AEROVIRONMENT, INC.

Inventor： Derek Lisoski ,  Bart Dean Hibbs

IPC: G05D1/00 ,  B64U101/20

Abstract: Systems, devices, and methods for a fleet of three or more unmanned aerial vehicles (UAVs), where each UAV of the fleet of UAVs comprise a respective flight control computer (FCC); at least one computing device at a ground control station, where each computing device is in communication with each FCC, and where each computing device is associated with at least one operator; where the fleet of UAVs above the threshold altitude are in communication with the first computing device monitored by at least one operator such that a ratio of operators to UAVs above the threshold altitude exceeds a 1:1 ratio; and where the first UAV below the threshold altitude is in communication with the second computing device monitored by at least one operator such that a ratio of operators to UAVs below the threshold altitude does not exceed the 1:1 ratio.

公开(公告)号：US20240400225A1

公开(公告)日：2024-12-05

申请号：US18797853

申请日：2024-08-08

Applicant: AeroVironment, Inc.

Inventor： Gaemus Collins ,  Allan Matthew ,  David Twining

IPC: B64U10/60 ,  B64F3/02 ,  B64U50/34 ,  B64U70/93 ,  G01L5/04 ,  H04W4/40 ,  B64U101/31

Abstract: Disclosed herein are system and method for controlling an unmanned aerial vehicle (UAV) tethered from a mobile platform, the UAV system comprising: a UAV comprising one or more sensors, and one or more propellers; a tether attached to the UAV and to the mobile platform; a digital processing device comprising an operating system configured to perform executable instructions and a memory; and a computer program including instructions executable by the digital processing device to automatically control the UAV relative to the mobile platform comprising: a software module identifying the mobile platform; a software module estimating a real-time state of the mobile platform; and a software module automatically controlling three-dimensional real-time motion of the UAV based on the real-time state estimation of the mobile platform and data collected from the one or more sensors, such that the UAV is maintained at a predetermined position relative to the mobile platform.

公开(公告)号：US12139274B2

公开(公告)日：2024-11-12

申请号：US18210418

申请日：2023-06-15

Applicant: AEROVIRONMENT, INC.

Inventor： Carlos Thomas Miralles ,  Guan H Su ,  Alexander Andryukov ,  John McNeil

IPC: B64F1/04 ,  B64C39/02 ,  B64F1/06 ,  F41A21/02 ,  F41F1/00 ,  F41F3/042 ,  F42B39/14 ,  B64U30/12 ,  B64U70/00 ,  B64U80/70

Abstract: An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.

公开(公告)号：US12130644B2

公开(公告)日：2024-10-29

申请号：US18564534

申请日：2022-05-27

Applicant: AEROVIRONMENT, INC.

Inventor： Scott David Davis ,  Drew David Mitchner

IPC: G05D1/48 ,  G05D1/49 ,  G05D109/20 ,  G05D111/10

CPC classification number: G05D1/484 ,  G05D1/49 ,  G05D2109/20 ,  G05D2111/10

Abstract: Systems, devices, and methods for an aircraft autopilot guidance control system for guiding an aircraft having a body, the system comprising: a processor configured to determine if a yaw angle difference and a pitch angle difference meet corresponding angle thresholds; a skid-to-turn module configured to generate a skid-to-turn signal if the corresponding angle thresholds are met; a bank-to-turn module configured to generate a bank-to-turn signal having a lower bandwidth than the generated skid-to-turn signal; a rudder integrator module configured to add a rudder integrator feedback signal to the bank-to-turn signal, where the rudder integrator feedback signal is proportional to a rudder integrator; and a filter module configured to filter the generated bank-to-turn signal, wherein the filter module comprises a low-pass filter configured by a set of gains to pass the bank-to-turn signal if a side force on the body meets a side force threshold.

公开(公告)号：US11981429B2

公开(公告)日：2024-05-14

申请号：US17979647

申请日：2022-11-02

Applicant: AEROVIRONMENT, INC.

Inventor： Derek Lisoski ,  William Stuart Sechrist

IPC: B64C39/02 ,  B26F3/12 ,  B64D17/34 ,  B64D17/62 ,  B64D17/80 ,  B64U70/83 ,  B64U10/25

CPC classification number: B64C39/024 ,  B26F3/12 ,  B64D17/34 ,  B64D17/62 ,  B64D17/80 ,  B64U10/25 ,  B64U70/83

Abstract: Systems, devices, and methods including: a latching mechanism comprising: a first latch configured to attach to a door of an unmanned aerial vehicle (UAV); a second latch configured to attach to a portion of the UAV distal from the first latch; a string connected between the first and second latch, where the string secures the door shut; at least two radio modules in communication with a ground control station; and at least two burn wires in contact with a portion of the string between the first latch and the second latch; where current from a backup battery passes to at least one burn wire when the burn signal is received, where the burn wire causes the connection between the first latch and the second latch to be broken and the door of the UAV is separated from the UAV, and where the parachute is deployed when the door of the UAV is separated from a rest of the UAV.

公开(公告)号：US20240124124A1

公开(公告)日：2024-04-18

申请号：US18533458

申请日：2023-12-08

Applicant: AeroVironment, Inc.

Inventor： Emil Ghapgharan ,  Lane Dalan ,  Pavel Belik ,  Christopher Eugene Fisher ,  Austin Craig Gunder

IPC: B64C11/02 ,  A63H27/00 ,  F01D5/30 ,  F04D29/38 ,  H02K7/00 ,  H02K7/14

CPC classification number: B64C11/02 ,  A63H27/02 ,  F01D5/3007 ,  F01D5/3023 ,  F04D29/382 ,  H02K7/003 ,  H02K7/14 ,  B64C2203/00 ,  B64U50/19

Abstract: A motor assembly that includes a motor having a motor casing, a rotatable shaft extending from said motor casing to a shaft length and a hub coupled to said rotatable shaft, the hub having a circumferential skid surface disposed immediately proximal to the motor casing and having a channel configured to seat a propeller, when a propeller is present, wherein a bending moment applied to the shaft through the hub results in the circumferential skid surface contacting said motor casing.

公开(公告)号：US20240096225A1

公开(公告)日：2024-03-21

申请号：US18512863

申请日：2023-11-17

Applicant: AeroVironment, Inc.

Inventor： Christopher E. Fisher ,  Thomas Robert Szarek ,  Justin B. McAllister ,  Pavel Belik

IPC: G08G5/02 ,  B64C39/02 ,  B64D31/00 ,  G05D1/00 ,  G05D1/06

CPC classification number: G08G5/02 ,  B64C39/024 ,  B64D31/00 ,  G05D1/0011 ,  G05D1/0676 ,  B64U10/25

Abstract: An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation.

公开(公告)号：US20240093966A1

公开(公告)日：2024-03-21

申请号：US18521357

申请日：2023-11-28

Applicant: AeroVironment, Inc.

Inventor： John C. McNeil ,  Earl Clyde Cox ,  Makoto Ueno ,  Jon Andrew Ross

IPC: F41G5/14 ,  F41G3/02 ,  F41G3/14 ,  F41G3/16

CPC classification number: F41G5/14 ,  F41G3/02 ,  F41G3/142 ,  F41G3/165

Abstract: Systems, devices, and methods for determining a predicted impact point of a selected weapon and associated round based on stored ballistic information, provided elevation data, provided azimuth data, and provided position data.