公开(公告)号：US20240201691A1

公开(公告)日：2024-06-20

申请号：US18306258

申请日：2023-04-25

Applicant: AEGIVERSE Co., Ltd.

Inventor： HUNG-PIN CHUNG ,  SHIH-JU FAN

IPC: G05D1/02 ,  G05D1/08

CPC classification number: G05D1/0278 ,  G05D1/0816

Abstract: An auto-alignment laser pointing system is provided. The auto-alignment laser pointing system is used in an aircraft and includes a light source module, a beam control device, a tracking receiving module, and a gyroscope. The light source module is used for generating laser beam. The beam control device corresponds to the light source module, is disposed in a path of the laser beam, and controls the laser beam to form a projection beam based on a set attitude angle. The tracking receiving module is used for tracking the aircraft and receiving the projection beam, so as to know flight information of the aircraft. The gyroscope is electrically connected to the beam control device to detect an actual attitude angle of the beam control device. When a deviation angle is between the actual attitude angle and the set attitude angle, the beam control device is controlled by the gyroscope to rotate for eliminating the deviation angle, so the projection beam is ensured projecting to the tracking receiving module.

公开(公告)号：US11920999B2

公开(公告)日：2024-03-05

申请号：US17605509

申请日：2018-11-29

Applicant: SZ DJI TECHNOLOGY CO., LTD.

Inventor： Kai Wang ,  Xiang Gao

IPC: G05D1/10 ,  B64C39/02 ,  G01M1/12 ,  G05D1/00 ,  B64U101/60

CPC classification number: G01M1/127 ,  B64C39/024 ,  G05D1/0816 ,  G05D1/106 ,  B64U2101/60 ,  B64U2201/20

Abstract: An unmanned aerial vehicle (UAV) control method includes obtaining target flight data and current flight data; determining a control state variable based on the target flight data and the current flight data; and calibrating a center of gravity of the UAV based on the control state variable.

公开(公告)号：US20230182898A1

公开(公告)日：2023-06-15

申请号：US18107191

申请日：2023-02-08

Applicant: AeroVironment, Inc.

Inventor： Quentin Lindsey ,  Henry Thome Won

IPC: B64C29/02 ,  G05D1/08 ,  G05D1/02 ,  G05D1/06

CPC classification number: B64C29/02 ,  G05D1/0808 ,  G05D1/0202 ,  G05D1/0669 ,  G05D1/0816 ,  B64U10/25

Abstract: Systems, devices, and methods that may include: determining one or more take-off variables for a vertical take-off and landing (VTOL) aerial vehicle; increasing an altitude of the VTOL aerial vehicle to a first altitude, where increasing the altitude comprises substantially vertical flight of the VTOL aerial vehicle; performing a first pre-rotation check of the VTOL aerial vehicle; adjusting a pitch of the VTOL aerial vehicle to a first pitch angle via motor control; adjusting the pitch of the VTOL aerial vehicle to a second pitch angle via at least one of: motor control and one or more effectors; and adjusting the pitch of the VTOL aerial vehicle to a third pitch angle via the one or more effectors, where the third pitch angle is substantially perpendicular to a vertical plane.

公开(公告)号：US20190232932A1

公开(公告)日：2019-08-01

申请号：US16378227

申请日：2019-04-08

Applicant: Goodrich Corporation

Inventor： Marc Georgin ,  Efrem E. Ayichew

IPC: B60T8/17 ,  B64C25/42 ,  B60W10/188 ,  B60T8/1761 ,  B64C25/48

CPC classification number: B60T8/1703 ,  B60T8/1701 ,  B60T8/1761 ,  B60T8/17613 ,  B60T8/24 ,  B60T2201/03 ,  B60T2230/02 ,  B60T2250/03 ,  B60W10/184 ,  B60W10/188 ,  B64C25/426 ,  B64C25/48 ,  G05D1/0816

Abstract: A method for controlling brakes includes receiving, by a controller, a first wheel speed from a first wheel speed sensor of a first wheel arrangement, receiving, by the controller, a second wheel speed from a second wheel speed sensor of a second wheel arrangement, calculating, by the controller, a pressure correction, and adjusting, by the controller, a pressure command for at least one of the first wheel arrangement and the second wheel arrangement.

公开(公告)号：US20190212755A1

公开(公告)日：2019-07-11

申请号：US16352982

申请日：2019-03-14

Applicant: Intel Corporation

Inventor： Fabian Oberndorfer ,  Wolfgang Rottner ,  Stefan Klar

IPC: G05D1/08 ,  B64C39/02 ,  B64C7/00

CPC classification number: G05D1/0816 ,  B64C7/00 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/165

Abstract: Methods and devices are presented for controlling or reducing amount of downwash generated by a drone. A drone including a plurality of arms including rotors may be configured to operate and fly with arms in an elevated position with respect to a horizontal plane. The elevated arms may allow a drone to fly with reduced vertical downwash.

公开(公告)号：US20190084675A1

公开(公告)日：2019-03-21

申请号：US16193902

申请日：2018-11-16

Applicant: SZ DJI TECHNOLOGY CO., LTD.

Inventor： Zongyao QU ,  Hideaki MITA

IPC: B64C39/02 ,  B64D47/08 ,  G05D1/08 ,  G05D1/00

CPC classification number: B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/127 ,  B64D47/08 ,  G03B15/006 ,  G05D1/0094 ,  G05D1/0816 ,  G05D1/0858

Abstract: An unmanned aerial vehicle (UAV) apparatus includes an airframe, a propulsion system carried by the airframe and including at least one propulsion device, a movable component carried by the airframe, and a control system. The control system is programmed with instructions that, when executed, cause the control system to receive a first input corresponding to a characteristic of the movable component, receive a second input corresponding to a command to move the movable component, and direct a change in a setting of the at least one propulsion device in response to the first input and the second input.

公开(公告)号：US20180222573A1

公开(公告)日：2018-08-09

申请号：US15426560

申请日：2017-02-07

Applicant: Bell Helicopter Textron Inc.

Inventor： Luke Gillett ,  Sung K. Kim

IPC: B64C13/50 ,  B64C27/06 ,  B64C27/82 ,  G05D1/02 ,  G05D1/00 ,  G05D1/08

CPC classification number: B64C13/503 ,  B64C13/00 ,  B64C27/06 ,  B64C27/82 ,  G05D1/0061 ,  G05D1/0066 ,  G05D1/0077 ,  G05D1/0202 ,  G05D1/0204 ,  G05D1/0816 ,  G05D1/0858

Abstract: In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes operating the rotorcraft in a speed control mode, where a speed of the rotorcraft is proportional to a pilot control command; detecting a high longitudinal acceleration condition; upon detection of the high longitudinal acceleration condition, temporarily disabling the speed control mode and stabilizing the rotorcraft while the speed control mode is disabled; and reestablishing the speed control mode when a measured longitudinal acceleration of the rotorcraft falls below a first threshold.

公开(公告)号：US20180141641A1

公开(公告)日：2018-05-24

申请号：US15788434

申请日：2017-10-19

Applicant: Aurora Flight Sciences Corporation

Inventor： Riley Griffin ,  Edward Scott ,  Sean Humbert

IPC: B64C13/16 ,  B64C3/00 ,  G05D1/08 ,  G01B7/16

CPC classification number: B64C13/16 ,  B64C3/00 ,  B64C39/024 ,  G01B7/16 ,  G01B11/18 ,  G01C19/5698 ,  G01C21/16 ,  G01P15/18 ,  G05D1/0204 ,  G05D1/0816

Abstract: An aerial vehicle comprising an airframe, an aircraft flight controller to provide an output control signal, and a planar printed circuit board positioned on the airframe. The printed circuit board may include coupled thereto a processor, a rate gyroscope, and at least three accelerometers. The processor is configured to generate an actuation signal based at least in part on a feedback signal received from at least one of said rate gyroscope and the at least three accelerometers. The processor communicates the actuation signal to said aircraft flight controller, which is configured to adjust the output control signal based on said actuation signal.

公开(公告)号：US09938018B2

公开(公告)日：2018-04-10

申请号：US15233428

申请日：2016-08-10

Applicant: Aviation Safety Advancements, Inc.

Inventor： David Patrick Welsh ,  Joseph Tobias Kujawski

IPC: B64D43/00 ,  B64D43/02 ,  G05D1/00 ,  G05D1/08

CPC classification number: B64D43/02 ,  G05D1/0061 ,  G05D1/0816

Abstract: Despite pilot training and current safety systems, aircraft accidents continue to occur. It is recognized herein that existing approaches to preventing aircraft accidents lack capabilities. A predictive aircraft recovery control unit can receive flight data from the plurality of data nodes. The flight data can be indicative of at least a speed of the aircraft and a position of the aircraft. In some cases, based on the flight data, the predictive aircraft recovery control unit can determine that the aircraft will enter a stall condition. Furthermore, based on the flight data, the predictive aircraft recovery control unit can determine a time period that will elapse before the aircraft enters the stall condition. In response to determining that the aircraft will enter the stall condition after the time period elapses, the predictive aircraft recovery control until can trigger a recovery sequence before the aircraft enters the stall condition.

公开(公告)号：US09915954B2

公开(公告)日：2018-03-13

申请号：US15146108

申请日：2016-05-04

Applicant: AIRBUS HELICOPTERS

Inventor： Jean-Baptiste Vallart ,  Romeo Byzery

IPC: G06G7/76 ,  G06F19/00 ,  G05D1/08 ,  G05D1/06 ,  B64C13/16

CPC classification number: G05D1/0816 ,  B64C13/16 ,  G05D1/0676 ,  G05D1/0858

Abstract: A control system for a rotorcraft, which system includes at least one control unit allowing a rotor of a rotorcraft to be driven, with the rotorcraft including at least three independent landing-gear units, with each landing-gear unit including means for detecting a ground reaction force F1, F2, F3 exerted on the landing-gear unit when the rotorcraft is in contact with the ground, and with the control system being suitable for receiving information from the detection means. The invention also relates to the rotorcraft and to a control method corresponding to the control system.