A personal flight apparatus with vertical take-off and landing is conceived as a biplane apparatus constituted by two distinct parts articulated there between, the first distinct part consists of thecockpit (1) which is hinged to the second part of the latter which is formed of the wings assembly (6), and the cockpit 1 is attached to the wings assembly (6) by two hinges (3) fixed in the upright central vertical supports (7) of the wings, so that the cockpit has a limited swing possibility inside of the wing support structure. The wing support structure is provided with four propellers (9) ofducted type and driven by electric engines (20), wherein two propellers are arranged on the top wing, and two propellers are on the bottom wing, thus forming a kind of quadcopter. The duct (10) of each propeller is provided on the inlet lip with an annular ejection slit (11), and the electrical energy required to operate the apparatus is provided by the batteries (14) placed under the pilot's seatwhich through the speed regulators transmit the electric energy to the engines. The entire operation of the apparatus is managed by means of a flight computer (17) disposed in the central part of theupper wing of the biplane, and the taking off is made with the wings and the engines vertically oriented. The flight apparatus is laid on the ground by means of a landing gear (15) fixed in the wingextremities, the flight apparatus takes off as a quadcopter, and the transition to the cruise flight is made by reducing the angle of incidence of the wings. The angle decreases naturally due to the increased resistance to advancement of the wings concurrently with the speed of translation of the flight apparatus, and at the same time, the cockpit (1) remains in a vertical position due to its lower center of gravity and due to the joints (3) which allow it to rotate relative to the wings assembly (6), and the landing is made similarly to a quadcopter, slowing down the speed leading to increasing the incidence angle of the wings until they return to the vertical plane required for landing.
一种垂直起飞和着陆的个人飞行设备,该飞行设备被认为是由在其间铰接的两个独立部分构成的双翼机设备,第一独立部分包括驾驶员座舱(1),驾驶员座舱铰接到第二部分,第二部分由机翼组件(6)形成,驾驶员座舱1通过两个铰接件(3)附接到机翼组件(6),铰接件固定在机翼的直立的中央竖直支撑件(7)中,并且以这种方式,驾驶员座舱在机翼支撑结构内部具有有限的摆动可能性,机翼支撑结构进而设置有四个导管类型的螺旋桨(9),所述螺旋桨由电发动机(20)驱动,其中两个螺旋桨设置在顶部机翼上,两个螺旋桨设置在底部机翼上,从而形成一种四轴飞行器,在每个螺旋桨的导管(10)的入口边缘上设置有环形喷射狭缝(11),并且操作设备所需的电能由放置在飞行员座椅下方的电池(14)提供,电池通过速度调节器将电能传输到发动机,设备的整个操作借助于设置在双翼机的上机翼的中央部分中的飞行计算机(17)来管理,并且用机翼和发动机来完成垂直定向的起飞,飞行设备借助于固定在机翼末端中的起落架(15)降落到地面上,飞行设备如四轴飞行器一样起飞,并且通过减小机翼的倾角来完成到巡航飞行的过渡,由于机翼前进时的阻力增加同时飞行设备的平移速度增加,倾角自然地减小,并且同时,由于驾驶员座舱(1)的低重心并由于允许驾驶员座舱相对于机翼组件(6)旋转的接合点(3),驾驶员座舱保持在竖直位置,并且着陆以类似于四轴飞行器的方式实现,降低速度导致机翼的倾角增大,直到机翼返回到着陆需要的垂直面。
PERSONAL FLIGHT APPARATUS WITH VERTICAL TAKE-OFF AND LANDING
垂直起飞和着陆的个人飞行设备
2021-02-05
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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