CN101992853A

CN101992853A - Coaxial dual-rotor one-seater aircraft

Info

Publication number: CN101992853A
Application number: CN2009100702592A
Authority: CN
Inventors: 于纯德
Original assignee: Individual
Current assignee: Individual
Priority date: 2009-08-28
Filing date: 2009-08-28
Publication date: 2011-03-30

Abstract

The invention relates to a coaxial dual-rotor one-seater aircraft, belonging to an ultra light aircraft, which is characterized in that three single-cylinder engines are utilized as power so as to improve the safety and reliability, and two coaxially arranged rotors are driven by power through a main transmission case and an auxiliary transmission case to rotate oppositely and inversely so as to counteract the autorotation inertial force of the aircraft body along with the rotor caused by the fact that a common helicopter is only provided with one rotor, thus omitting a tail propeller, reducing the size and weight of aircraft body, having small and light overall unit and being flexible, and a unique flight control system is adopted to realize course alternation of the aircraft, such as ascending and descending, advancing and retreating as well as turning. The aircraft in the invention can be used as emergency equipment in national defense and military, aviation shooting, forest fire prevention, traffic guidance and sudden events.

Description

The coaxial double-rotary wing individual lift device

The present invention is a kind of microlight-type aircraft, and particularly a kind of coaxial double-rotary wing is gone straight up to individual lift device.

The purpose of this invention is to provide a kind of novel individual lift device,

The object of the present invention is achieved like this: it passes through power-transfer clutch by three single cylinder engine petroies that are arranged on the main transmission box of frame top, transmission gearbox, the rotor of main shaft a and two pairs of relative retrograde rotations of main shaft b driving, make aircraft obtain flying power, pass through the state of flight of flight control system controlling aircraft simultaneously, rise and descend, move forward and backward, turning is changed course.The present invention is owing to adopt the coaxial inverse double-rotation wing, thereby avoided pure helicopter to use single rotor to make also and then spin of fuselage, in order to overcome this spin have to the be provided with tail slurry of a long-tail crust at the fuselage rear, thereby fuselage is shortened, complete machine size and weight have been reduced, the complete machine deadweight is no more than 116kg, echos the regulation of the relevant microlight-type aircraft of the existing Civil Aviation Law of China.

The present invention provides a kind of flexibly light and handy for people, and the individual lift device of mobility strong can be used for outdoor exercises, national defence, guiding of traffic, the emergency serving unit of accident.

The invention will be further described below in conjunction with embodiment and accompanying drawing thereof.

Fig. 1 is an overall structure scheme drawing of the present invention.

Fig. 2 is the structure cut-away view of main transmission box and secondary transmission case.

Fig. 3 is the main transmission box birds-eye view

Fig. 4 and Fig. 5 are flight control system scheme drawings.

Fig. 6 and Fig. 7 are the rack construction scheme drawings.

1 is to go up rotor among the figure, the 2nd, and driving engine, the 3rd, secondary transmission case, the 4th, main transmission box, the 5th, rotor shakes hinge, and the 6th, control system, the 7th, the chaufeur seat, the 8th, frame, the 9th, yaw rudder, the 46th, following rotor, as shown in Figure 1.

Three driving engines 2 are fixed on the main transmission box upper plate 16 at circumferencial direction interval 120 degree, owing to adopt three simultaneous firings that the safety factor of aircraft is improved, even having one or two driving engine et out of order to also have a driving engine can keep aircraft security lands, when reaching certain rotating speed, driving engine is fixed on automatic centrifugal clutch 15 combinations on the engine shaft 14, power is passed to big belt pulley 13 by cone belt 18, give main shaft 12 transmission of power again, main shaft 12 passes to main shaft a11 to power by spline bevel gear 25 again, connect hinge 10 by last rotor and drive upward rotor 1 rotation, simultaneously, spline bevel gear 25 drives spline bevel gear 22 by planetary bevel gear 23 again, the rectangular teeth of spline bevel gear 22 upper ends and the engagement of main shaft b21 lower end rectangular teeth, power is passed to down rotor again connect hinge 45, drive down that rotor 46 rotate round about, because of two rotor axle drive shafts title of all in same axis, dying coaxial.The upper plate 16 and the lower plate 19 of main transmission box are combined as a whole by 6 connecting columns 17, secondary transmission case 3 is fixed on auxiliary driving casing 24 both sides by the upper end of a pair of connection seat 20, and the lower end is fixed on above the upper plate 16, as Fig. 2, shown in Figure 3, Fig. 3 is the main transmission box birds-eye view.

Flight control system 6 is made up of course control and rise and fall forward-reverse control mechanism, and the course is controlled by the handgrip 28 that is fixed on the frame 8, active drag-line sheave 26, and drag-line 27, driven drag-line sheave 29 and yaw rudder 9 constitute, as shown in Figure 4.Pull handgrip 28 and drive initiatively drag-line sheave 26 front and back rotation forward or backward, the driven drag-line sheave 29 of two drag-lines 27 pulling synchronously fixed thereon rotates, driving the direction rudder face that is fixed as one with it swings around z axis, under the action of high-speed airflow that below rotor, forms, on rudder face, produce lateral thrust, promote the fuselage left rotation and right rotation, thereby reach the purpose of changing course.The control of rise and fall forward-reverse is shaken hinge 5 by the rotor that is fixed on the main transmission box lower plate 19, and handgrip 31, drag-line are 32, and oil door handle 33 is located orifice plate 34 and locating dowel pin 30 constitutes, as shown in Figure 5.Rotor is in horizontal attitude when locating dowel pin 30 is in the position of knock hole b, and aircraft is in and rises or the descending flight state, at this moment as about stir the rotating speed height of oil door handle 33 control driving engines, with regard to the rising and the decline of may command aircraft.When pulling drag-line 32 the time, locating dowel pin 30 is drawn out knock hole b, promoting handle 31 forward drives the head rotors and shakes dumpling 5 around rotor and recede, make rotor and horizontal surface form certain included angle, make rotor produce the component that pulls back aircraft, unclamp drag-line handle 32, locating dowel pin 30 enters under the elastic element effect and retreats flight knock hole a, aircraft regression.When making locating dowel pin enter c or d hole by aforementioned program, rotor leans forward, and can obtain two and keep off flying speed forward, flies before the aircraft.

Frame 8 is by shaking the hinge sleeve 35 that dumpling 5 connects with rotor, yaw rudder connection seat 36, drag-line bearing 37, the blue tie-plate 38 of method, reinforced pull rod 39, girder 40, seat bearing 41, drag-line bearing 42, drag-line handle support base 43, stretcher 44 constitutes, and shown in Figure 7 as Fig. 6, Fig. 7 is the birds-eye view of frame.

Claims

1. a coaxial double-rotary wing individual lift device is characterized in that having improved the safety factor of aircraft with many simultaneous firings.

2. Du Te flight control system turns that to change course be to be swung by a pair of drag-line sheave and two drag-line Synchronous motion control yaw rudders, makes action of high-speed airflow rotor under produce lateral thrust promotion fuselage on the bevelled rudder face and rotates and realize.Rise and descend, advancing with retreating is that handgrip by push-and-pull is installed on the main transmission box makes rotor shake the hinge swing around rotor, changes that rotor and the angle of horizontal surface realize with the acquisition horizontal component of force.