CN103803078A

CN103803078A - Flying saucer type helicopter utilizing active airflow to generate lifting power

Info

Publication number: CN103803078A
Application number: CN201210447085.9A
Authority: CN
Inventors: 余彦武; 刘志军
Original assignee: Individual
Current assignee: Individual
Priority date: 2012-11-12
Filing date: 2012-11-12
Publication date: 2014-05-21

Abstract

The invention relates to a flying saucer type helicopter utilizing active airflow to generate lifting power. As everyone knows, the asymmetric airflow on the upper surfaces and lower surfaces of wings can generate lifting power, however for both a fixed wing aircraft and a propeller-driven aircraft, the wings move, the air is motionless, and airflow is passively generated. According to the invention, an opposite approach is chosen. Specifically, the wings are fixed, actively generated airflow flows through the upper surfaces of the wings, an air pressure difference is manufactured between the upper surfaces and lower surfaces of the wings so as to generate the lifting power, thus realizing a safe and simple aircraft that can achieve vertical take-off and landing, hovering, level flight and pivot steering. The appearance of the aircraft is similar to a flying saucer. By adjusting the angle between the airflow direction of the aircraft's upper surface and the radial direction, spin of the fuselage can be controlled, and by adjusting the flow velocity distribution of the front, back, left and right directions, the inclination direction of the aircraft body can be changed to realize level flight and direction control. The novel aircraft not only has all the advantages of traditional helicopters, but also has the characteristics of simplicity, compactness, safety, stability and the like, and is an ideal solution to one-man aircrafts and unmanned reconnaissance aerial vehicles.

Description

A kind of flying disc type helicopter that utilizes active flow to produce lift

Technical field

The invention belongs to aviation aircraft field, especially there is helicopter or the flying saucer type aircraft of vertical takeoff and landing, the peaceful ability of flying of hovering.

Background technology

Helicopter is compared other vehicle, sharpest edges are that it can vertical takeoff and landing and hovering, this point makes it not need specific highway (automobile relatively), airport (fixed wing aircraft relatively), harbour (steamer relatively), the auxiliary facilities such as track (train relatively), only needing a level land less times greater than fuselage size to realize takes off and lands, that is to say, geographical terrain does not constitute any limitation substantially to the use of helicopter, therefore no matter be the remote mountain areas on high and steep mountains, marsh, unfrequented desert, the rivers,lakes and seas that can only navigate, or built-up city, helicopter can easily be dealt with.From this point, helicopter is the optimal vehicle.

But, if single-rotor helicopter and the twin-rotor helicopter of the Helicopter Main mechanically driver type of practical application are at present wherein maximum with single-rotor helicopter quantity again.First, no matter single rotor, or cross-arranging type, the lap siding bispin wing, no matter be coaxial anti-oar helicopter, or tilt rotor aircraft, they have a common feature, that is exactly huge rotor, and it is all very unsafe being exposed to the outer rotor of High Rotation Speed and the collision of any object, and this structure has increased the requirement of existing helicopter to the open degree in space to a great extent, limit the operation of helicopter at small space, increased the insecurity of helicopter; Secondly, flat the flying of existing helicopter is mainly to become slurry the dependence cycle to realize apart from technology, this mechanical operating principle, and not only complex structure, has also brought the problems such as vibrations are large, noise is large, easy break-down; The 3rd, eliminate spin aspect, yes for coaxial anti-oar technology well, but main flow helicopter majority still adopts the mode of tail-rotor to realize at present, and the topology layout that this has also limited helicopter has increased the size of helicopter.Just because of its complexity and insecurity, helicopter is mainly used at special dimensions such as rescue and relief work, military affairs, police, geology, seas by the personnel with professional skill at present, can not be universal as ordinary traffic instrument.

If go straight up to function design as flying saucer, there is no exposed rotor, there is no tail-rotor, there is no complicated cycle bending moment structure, do not vibrate, do not have noise, with rising with falling, manipulation is stable, is free to come and go, and will greatly expand the Applicable scope of helicopter, improve safety, the traveling comfort of helicopter, even likely as automobile, popularize as ordinary traffic instrument.

Summary of the invention

The present invention is a kind of Novel flying saucer type helicopter that utilizes active flow technology to produce lift, its outer image flying saucer (flat cake) is the same, it does not have exposed rotor,, for the tail-rotor of balance spin, but can as common heligyro, vertical takeoff and landing, hovering, any direction not put down and fly.

This flying disc type helicopter, by initiatively produce the mode of air-flow at flying saucer fuselage upper surface, utilizes flying saucer fuselage upper and lower surface air pressure difference to manufacture lift.By the breather vane reconditioner anglec of rotation of airflow on surface with it, offset the spin of flying saucer or control flying saucer along self center shaft rotation.The same with common heligyro, this flying disc type helicopter is realized the horizontal flight of certain direction by inclination fuselage, it is to be decided by the angle of four rudder sheets that are arranged on flying saucer surrounding that flying saucer fuselage to which direction tilts, in the time that flying saucer fuselage tilts, lift also can correspondingly tilt, and the horizontal component of force of this inclination lift just provides the power of flying saucer horizontal flight.

Accompanying drawing explanation

Fig. 1 is the outside perspective view of the flying disc type helicopter that the present invention relates to, and visual angle is oblique lower 45 °.

Fig. 2 is the external structure birds-eye view of the flying disc type helicopter that the present invention relates to.

Fig. 3 is the inner structure cross-section front view of the flying disc type helicopter that the present invention relates to.

The specific embodiment

Aircraft according to the present invention is not limited to some structures, describes here for aspect, introduces a kind of typical embodiment.

This aircraft has the fuselage 1 of a butterfly, its outer is an octagon, fuselage 1 is actually a frame-covering structure, and its inside is supported by skeleton 2, and duct 3 is in fuselage 1 top, be fixedly connected with skeleton 2, engine installation 5 is arranged on the central authorities of skeleton 2, and engine installation 5 drives propeller fan 4 to rotate, under duct 3 auxiliary, air-flow enters above ducted fan, is then flowed out by middle mind-set surrounding along the upper surface of fuselage 1.Air flow outlet between duct 3 and fuselage 1, eight breather vanes 6 of well-distributed are installed, breather vane 6 can rotate along vertical axes, adjust the angle of these blades, can control the direction that air-flow flows out, utilize the tangential reaction thrust of air-flow to promote fuselage 1 original place and rotate, or offset the spinning moment that propeller fan 4 brings.Periphery below fuselage 1, four sides is separately installed with a rudder sheet 7, and they are used for controlling the fuselage attitude of flying saucer and the direction of horizontal flight.

In the time that ducted fan is worked, because having high velocity air, fuselage 1 upper surface flows, and lower surface does not have air-flow substantially, the atmospheric pressure of fuselage 1 upper surface is lower than lower surface, the bar pressure that fuselage lower surface is subject to will be greater than the bar pressure of upper surface, this difference of pressure is exactly the main source of the lift of aircraft, secondly, the upper lip of duct also can be due to two airflow on surface speed differences, produce certain lift, in addition, due to Coanda effect, air-flow can flow along the curved surface of fuselage surface always, finally flow out with the direction approaching straight down, the recoil of air-flow also can produce certain lift.

In the time that propeller fan 4 is worked, aircraft itself can be subject to one with the moment of torsion of propeller fan direction of rotation, and rotate backward, be called spin, at this time, if adjust the angle of breather vane 6, make their rotation direction contrary with screw propeller hand of rotation, the air-flow of fuselage upper surface outgoing just has certain tangential velocity, and tangential velocity direction is identical with fuselage spin direction, like this, the reaction thrust of air-flow will produce a reaction thrust square contrary with spinning moment, stop fuselage spin, the angle of blade 6 Off-Radials is larger, this reaction thrust square is also larger, when controlling the angle of blade 6 when suitable, just can just offset fuselage spin, certainly, also can realize pivot stud.

Four rudder sheets of aircraft surrounding can rotate along horizontal shaft separately, and in the time that the rudder sheet of certain direction outwards upward deflects, deflection angle is larger, and the obstruction that the air-flow of this direction is subject to is larger, and flow velocity is less, and lift is also less.Like this, by adjusting the angle of these four rudder sheets, control the lift size on correspondence direction, whether just can control the inclination of aircraft fuselage, once fuselage tilts, the poor horizontal component of force that just has a sensing direction of tilt of bar pressure on fuselage, thus realize horizontal flight.Change fuselage direction of tilt, can realize towards different direction flight.Change the degree that fuselage tilts, just can change the size of horizontal component of force, thereby adjust the speed of horizontal flight.

Claims

One kind can vertical takeoff and landing aircraft, the structure of its exemplary embodiments is as follows: the similar flying saucer of fuselage appearance of aircraft, there is ducted fan the top of flying saucer, ducted fan produces swiftly flowing air-flow surfacewise at aircraft fuselage upper surface, the difference of the air-flow velocity of fuselage upper and lower surface can cause the difference of air pressure, this draught head is as the main lift source of aircraft, air-flow finally separates with fuselage, the recoil application force of ejection is another lift source downwards, it is by regulating the angle of flying saucer upper surface along the breather vane of radially installing, control the hand of rotation of air-flow, control the rotation of flying saucer along self center shaft, by fuselage edge four rudder sheets that can rotate along horizontal shaft all around, adjust the direction of tilt of fuselage, utilize the horizontal component of lift that the power of flying saucer horizontal flight is provided.
2. aircraft according to claim 1, its topmost being characterised in that: by manufacture on one's own initiative the mode of air-flow at the static upper surface of the airfoil in relative ground, make upper and lower two the airflow on surface speed differences of wing, form draught head, thereby the in the situation that of static on the relative ground of aircraft wing, also can provide lift, realize vertical takeoff and landing.
3. aircraft according to claim 1, it is characterised in that: it can, with any device that can produce air-flow as propulsion source, include but not limited to ducted fan, screw propeller, air compressor, air compressor, pressure gas, jet engine.
4. aircraft according to claim 1, it is characterised in that: the mode of controlling fuselage rotation is not limited to breather vane, can be also coaxial anti-oar technology.
5. aircraft according to claim 1, it is characterised in that: use fuselage four rudder sheet control headings around.