公开(公告)号：US20160207625A1

公开(公告)日：2016-07-21

申请号：US14915101

申请日：2014-08-29

Applicant: Airbus Defence and Space GmbH ,  STEUBBEUS FLUGZEUG- UND LEICHTBAU GMBH

Inventor： Michael JUDAS ,  Friederike STRATENBERG ,  Jan VAN TOOR ,  Werner SCHOLZ ,  Berthold KARRAIS ,  Wolfgang STANGL

IPC: B64C29/00 ,  B64C27/08 ,  B64C27/473 ,  B64C3/38 ,  B64C5/08 ,  B64D27/02 ,  B64D27/24 ,  B64C39/02 ,  B64C39/08

CPC classification number: B64C29/0025 ,  B64C3/38 ,  B64C5/08 ,  B64C27/08 ,  B64C27/473 ,  B64C39/024 ,  B64C39/08 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/02 ,  B64D27/24 ,  B64D2027/026

Abstract: The invention relates to an aircraft which can both take off and land vertically and can hover and also fly horizontally at a high cruising speed. The aircraft has a support structure, a wing structure, at least three and preferably at least four lifting rotors and at least one thrust drive. The wing structure is designed to generate a lifting force for the aircraft during horizontal motion. To achieve this the wing structure has at least one mainplane provided with a profile that generates dynamic lift. The wing structure is preferably designed as a tandem wing structure. Each of the lifting rotors is fixed to the support structure, has a propeller and is designed to generate a lifting force for the aircraft by means of a rotation of the propeller, said force acting in a vertical direction. The thrust drive is designed to generate a thrust force on the support structure, said force acting in a horizontal direction. The lifting rotors can have a simple construction, i.e. they can have a simple rigid propeller for example, and a vertical take-off or hovering of the aircraft can be controlled, in a similar manner to quadcopters, by a simple control of the speeds of the lifting rotors. High cruising speeds can be achieved as a result of the additional horizontally acting thrust drive.

Abstract translation: 本发明涉及一种能够垂直起飞和着陆的飞机，其可以悬停并且以高巡航速度水平飞行。 飞行器具有支撑结构，翼结构，至少三个，优选至少四个提升转子和至少一个推力驱动。 机翼结构被设计成在水平运动期间为飞机产生提升力。 为了实现这一点，翼结构具有至少一个主平面，其具有产生动态升力的轮廓。 机翼结构优选地被设计为串联翼结构。 每个提升转子固定在支撑结构上，具有螺旋桨，并被设计成通过螺旋桨的旋转而产生用于飞行器的提升力，所述力作用在垂直方向上。 推力驱动器被设计成在支撑结构上产生推力，所述力在水平方向上作用。 提升转子可以具有简单的结构，例如它们可以具有简单的刚性推进器，并且可以通过简单地控制速度来简单地控制飞机的垂直起飞或悬停 提升转子。 由于额外的水平作用推力驱动，可以实现高巡航速度。

公开(公告)号：US20180283292A1

公开(公告)日：2018-10-04

申请号：US15953209

申请日：2018-04-13

Applicant: Airbus Defence and Space GmbH

Inventor： Juergen STEINWANDEL ,  Florian STAGLIANO ,  Jan VAN TOOR

IPC: F02D29/02 ,  B64D31/00

CPC classification number: F02D29/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/066 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/16 ,  B64D27/02 ,  B64D27/24 ,  B64D31/00 ,  B64D41/00 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64

Abstract: An unmanned aircraft includes a propulsion system having a diesel or kerosene internal combustion engine and a charger device for engine charging. The propulsion system can be a hybrid propulsion system or a parallel hybrid propulsion system.