公开(公告)号：WO2017052396A1

公开(公告)日：2017-03-30

申请号：PCT/PL2016/000107

申请日：2016-09-21

Applicant: MARGAŃSKI, Edward ,  IZDEBSKI, Andrzej

Inventor： MARGAŃSKI, Edward

IPC: B64C29/02 ,  B64C39/02 ,  B64C39/12

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108

Abstract: The object of the invention is a vertical take-off and landing aircraft in the manned or unmanned version powered by one or more electric motors which rotate two contra-rotating, fixed-pitch or variable-pitch propellers located at the front. To control the aircraft during vertical and horizontal flights auxiliary horizontal and vertical control and trim surfaces (5) and (7), located in the slipstream of contra-rotating propellers (1) in front of the aircraft's centre of gravity are used, whereas the control and trim surfaces (5) and (7) are suspended in relation to the aircraft on axles (6) and (8) that are located in front of the centre of aerodynamic forces created by them, owing to which the aerodynamic surfaces place themselves in the direction of the flowing control air of the aircraft, while the lift force created by them depends directly on the moments exerted on their axes of rotation (6) and (8), created with the use of linear or angular magneto-dynamic hoists (10) or with the aerodynamic method through auxiliary control tabs (12) installed on the control and trim surfaces (5) and (7).

Abstract translation: 本发明的目的是一种垂直起飞和着陆飞机，它是由一个或多个电机驱动的载人或无人驾驶飞行器，它们旋转位于前部的两个反向旋转，固定桨距或可变桨距螺旋桨。 为了在垂直和水平航行期间控制飞机，使用位于飞机重心前面的反转螺旋桨（1）的滑流中的辅助水平和垂直控制和装饰表面（5）和（7），而 控制和装饰表面（5）和（7）相对于位于由它们产生的空气动力中心前面的轴（6）和（8）上的飞机悬挂，由此空气动力学表面放置 在飞行器的流动控制空气的方向上，由它们产生的提升力直接取决于施加在其旋转轴线（6）和（8）上的力矩，其使用线性或角度磁动力提升机 （10）或通过安装在控制和装饰表面（5）和（7）上的辅助控制翼片（12）的空气动力学方法。

公开(公告)号：WO2011056082A2

公开(公告)日：2011-05-12

申请号：PCT/PL2010/000110

申请日：2010-11-05

Applicant: MARGAŃSKI, Edward

Inventor： MARGAŃSKI, Edward

IPC: B64C5/04

CPC classification number: B64C5/04 ,  B64C9/10 ,  B64C39/12

Abstract: The object of the invention is an aircraft provided with a device for creating a constant moment in relation to the axis of rotation of an additional control surface placed at the front of the aircraft at an as large as possible distance from the centre of gravity of the aircraft. The aircraft is characterised in that the control of the aerodynamic vertical force (7) is effected by deflecting control elements (3) pivotably mounted on the rotation axis (4), the deflection of said control elements causing rotation of a balance and control surface (1) mounted rotatably on axis (2), wherein the axis (2) is mounted perpendicularly to the plane of symmetry (5) of aircraft (6) forward of the resultant aerodynamic vertical force (7) generated by the balance and control surface (1).

Abstract translation: 本发明的目的是提供一种装置，该装置用于产生相对于放置在飞行器前部的附加控制表面的旋转轴线的恒定力矩，其距离重心的距离尽可能大 飞机。 飞行器的特征在于，空气动力学垂直力（7）的控制通过使可旋转地安装在旋转轴线（4）上的控制元件（3）偏转来实现，所述控制元件的偏转导致平衡和控制表面的旋转 1），其可旋转地安装在轴线（2）上，其中轴线（2）垂直于飞机（6）的对称平面（5）安装在由平衡和控制表面（...）产生的合成空气动力学垂直力（7） 1）。