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    AIR VEHICLE
    2.
    发明申请
    AIR VEHICLE 审中-公开
    空中车辆

    公开(公告)号：WO2010137016A3

    公开(公告)日：2011-10-20

    申请号：PCT/IL2010000416

    申请日：2010-05-26

    Applicant: ISRAEL AEROSPACE IND LTD ,  WOLFF AMIT ,  DEKEL GUY ,  ZIVAN LIOR

    Inventor： WOLFF AMIT ,  DEKEL GUY ,  ZIVAN LIOR

    IPC: B64C29/00 ,  B64C39/02

    CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/126 ,  B64C2201/165 ,  B64C2211/00

    Abstract: According to one aspect of the invention there is provided a system and method for providing propulsion and control to an air vehicle, and for operating the vehicle, in which at least three propulsion units provide vertical thrust for vectored thrust flight, and in which at least one or two of the propulsion units also provide thrust for vectored thrust cruising or aerodynamic flight by suitably tilting the respective propulsion units for changing the thrust vector thereof. At the same time, the three or more propulsion units are operated to generate controlling moments to the air vehicle about three orthogonal axes, pitch, roll and yaw, during vectored thrust flight (hover, cruising, etc.) or during aerodynamic flight for controlling the vehicle. The control moments are generated by selectively varying the thrust generated by each of the propulsion units independently of one another, and: by selectively vectoring the thrust of one propulsion unit with respect to each of two independent tilt axes independently of one another, or by selectively vectoring the thrust of each of two propulsion units with respect to a respective tilt axis, independently of one another.

    Abstract translation: 根据本发明的一个方面，提供了一种用于向空中交通工具提供推进和控制以及用于操作车辆的系统和方法，其中至少三个推进单元为向量推力飞行提供垂直推力，并且其中至少 一个或两个推进单元还通过适当地倾斜相应的推进单元来改变其推力矢量，来为向量推力巡航或空气动力学飞行提供推力。 同时，三个或更多个推进单元被操作以在向量推力飞行（悬停，巡航等）期间或在用于控制的空气动力学飞行期间在三个正交轴线（俯仰，滚动和偏航）周围产生对空中飞行器的控制力矩 机动车。 通过选择性地改变每个推进单元彼此独立地产生的推力而产生控制力矩，并且：通过相对于彼此独立的两个独立倾斜轴中的每一个选择性地向量化一个推进单元的推力，或者通过选择性地 两个推进单元中的每一个的推力相对于相应的倾斜轴线彼此独立地对齐。

    A SYSTEM, A METHOD AND A COMPUTER PROGRAM PRODUCT FOR MANEUVERING OF AN AIR VEHICLE
    6.
    发明专利
    A SYSTEM, A METHOD AND A COMPUTER PROGRAM PRODUCT FOR MANEUVERING OF AN AIR VEHICLE 未知

    公开(公告)号：SG11201500170XA

    公开(公告)日：2015-03-30

    申请号：SG11201500170X

    申请日：2013-09-12

    Applicant: ISRAEL AEROSPACE IND LTD

    Inventor： DEKEL GUY ,  ZIVAN LIOR ,  EFRATY YOAV ,  WOLFF AMIT ,  VOLOVICK AVNER

    IPC: B64C29/00

    Abstract: A control system configured to control an acceleration of an air vehicle which comprises a tiltable propulsion unit that is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle, the control system comprising: (a) an input interface for receiving information indicative of a monitored airspeed of the air vehicle; and (b) a control unit, configured to issue controlling commands to a controller of the tiltable propulsion unit for controlling the acceleration of the air vehicle.

    AIR VEHICLE
    8.
    发明专利
    AIR VEHICLE 未知

    公开(公告)号：SG176139A1

    公开(公告)日：2011-12-29

    申请号：SG2011084993

    申请日：2010-05-26

    Applicant: ISRAEL AEROSPACE IND LTD

    Inventor： WOLFF AMIT ,  DEKEL GUY ,  ZIVAN LIOR

    Abstract: According to one aspect of the invention there is provided a system and method for providing propulsion and control to an air vehicle, and for operating the vehicle, in which at least three propulsion units provide vertical thrust for vectored thrust flight, and in which at least one or two of the propulsion units also provide thrust for vectored thrust cruising or aerodynamic flight by suitably tilting the respective propulsion units for changing the thrust vector thereof. At the same time, the three or more propulsion units are operated to generate controlling moments to the air vehicle about three orthogonal axes, pitch, roll and yaw, during vectored thrust flight (hover, cruising, etc.) or during aerodynamic flight for controlling the vehicle. The control moments are generated by selectively varying the thrust generated by each of the propulsion units independently of one another, and: by selectively vectoring the thrust of one propulsion unit with respect to each of two independent tilt axes independently of one another, or by selectively vectoring the thrust of each of two propulsion units with respect to a respective tilt axis, independently of one another.

    Un sistema, un procedimiento y un producto de programa informático para maniobrar un vehículo aéreo
    9.
    发明专利
    Un sistema, un procedimiento y un producto de programa informático para maniobrar un vehículo aéreo 未知

    公开(公告)号：ES2859644T3

    公开(公告)日：2021-10-04

    申请号：ES13838658

    申请日：2013-09-12

    Applicant: ISRAEL AEROSPACE IND LTD

    Inventor： DEKEL GUY ,  ZIVAN LIOR ,  EFRATY YOAV ,  WOLFF AMIT ,  VOLOVICK AVNER

    IPC: B64C29/00

    Abstract: Un sistema de control (1201) configurado para controlar una aceleración de un vehículo aéreo (100) que comprende una unidad de propulsión inclinable (420) que puede inclinarse para proporcionar un empuje cuya dirección es variable al menos entre una dirección general del vector de empuje vertical y una dirección general del vector de empuje longitudinal con respecto al vehículo aéreo, comprendiendo el sistema de control: una interfaz de entrada para recibir información indicativa de una velocidad aerodinámica supervisada del vehículo aéreo; y una unidad de control (1290), configurada para emitir comandos de control a un controlador (1410) de la unidad de propulsión inclinable para controlar la aceleración del vehículo aéreo, en la que el control de la aceleración comprende: en una primera parte de la aceleración, en la que la unidad de propulsión inclinable proporciona empuje en la dirección general del vector de empuje vertical: (a) controlar la operación de la al menos una unidad de propulsión inclinable para proporcionar sustentación al vehículo aéreo, y (b) controlar una modificación de un ángulo de inclinación de la unidad de propulsión inclinable con respecto al fuselaje del vehículo aéreo, en función de: (i) la velocidad aerodinámica supervisada y (ii) un comando de velocidad aerodinámica; y después de una inclinación de la al menos una unidad de propulsión inclinable, controlar en una segunda parte de la aceleración una operación de la unidad de propulsión inclinable para proporcionar empuje en la dirección general del vector de empuje longitudinal para impulsar el vehículo aéreo, en la que la unidad de control comprende un módulo de control de cabeceo que está configurado para emitir un comando de cabeceo en función de la velocidad aerodinámica supervisada y el comando de velocidad aerodinámica y para controlar en la primera parte de la aceleración una modificación de un ángulo de cabeceo del vehículo aéreo en función del comando de cabeceo, en la que el control de la modificación del ángulo de inclinación se basa, además, en el comando de cabeceo.

    AIR VEHICLE
    10.
    发明专利
    AIR VEHICLE 未知

    公开(公告)号：SG10201810476RA

    公开(公告)日：2018-12-28

    申请号：SG10201810476R

    申请日：2010-05-26

    Applicant: ISRAEL AEROSPACE IND LTD

    Inventor： WOLFF AMIT ,  DEKEL GUY ,  ZIVAN LIOR

    Abstract: AIR VEHICLE : According to one aspect of the invention there is provided a system and method for providing propulsion and control to an air vehicle, and for operating the vehicle, in which at least three propulsion units provide vertical thrust for vectored thrust flight, and in which at least one or two of the propulsion units also provide thrust for vectored thrust cruising or aerodynamic flight by suitably tilting the respective propulsion units for changing the thrust vector thereof. At the same time, the three or more propulsion units are operated to generate controlling moments to the air vehicle about three orthogonal axes, pitch, roll and yaw, during vectored thrust flight (hover, cruising, etc.) or during aerodynamic flight for controlling the vehicle. The control moments are generated by selectively varying the thrust generated by each of the propulsion units independently of one another, and: by selectively vectoring the thrust of one propulsion unit with respect to each of two independent tilt axes independently of one another, or by selectively vectoring the thrust of each of two propulsion units with respect to a respective tilt axis, independently of one another. Fig. 1

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