CN1269307A

CN1269307A - Flyer with centrifugal fan for launching and landing vertically

Info

Publication number: CN1269307A
Application number: CN 00113206
Authority: CN
Inventors: 王新云
Original assignee: Individual
Current assignee: Individual
Priority date: 2000-01-07
Filing date: 2000-01-07
Publication date: 2000-10-11

Abstract

The present invention discloses a flying vehicle capable of vertically rising and falling, and is characterized by that a centrifugal fan is set over the wing of the flying vehicle or specially-designed lifting platform, and the centrifugal fan is driven by an engine to make high-speed rotation to obtain air working medium with dynamic pressure energy, and the working medium can be horizontally flowed toward wing or over the lifting platform to form a continuous stable artificial laminar flow on the surface of wing or lifting platform, and the dynamic pressure of said working medium can make the laminar flow become a negative pressure zone to produce suction, and at the same time, the static pressure of two wings or under the lifting platform can be increased and become a positive pressure zone so as to utilize the lifting force produced by this pressure difference to realize vertical/short distance rising and falling or hovering of flying vehicle.

Description

The aircraft of band centrifugal fan for launching and landing vertically

The present invention relates to a kind of aircraft, be adapted to all traffic in civilian and military field, transportation, lifting gear, field machine, be adapted to the aircraft of aviation field especially with centrifugal fan for launching and landing vertically.

At present, aircraft such as aircraft are to rely on wing to produce lift, and helicopter is to utilize the rotor rotation and the counteraction of air to produce lift, and all there are some shortcomings in they.As aircraft be rely on wing profile up and down the variation of geometric configuration cause aerofoil up and down the variation of air-flow velocity produce up and down that pressure difference produces lift, this lift will account for about 2/3 of takeoff and landing lift, the generation of this lift not only efficient is low, and its lift becomes a square direct ratio with speed, promptly when flying speed doubled, lift then improved four times.In the landing stage of aircraft, because of lift is not enough, have to improve its landing speed, and this needs the high airfield runway of cost and cause a large amount of aircraft accidents.When aircraft flew with cruising speed, its speed will exceed several times of landing speed to more than ten times, so just made its lift be greater than tens to tens times of its required lift, and this is the problem of a quite complicated contradiction, can only adopt compromise proposal to solve so far.The Harrier of helicopter and Britain, though energy vertical takeoff and landing, but its structure is very complicated, cost is high, vertically/voyage of short take-off and landing (STOL) is too short, as Harrier vertical/voyage of short take-off and landing (STOL) is not as good as 1/10 of run-up landing voyage, operating costs exceeds more than 10 times, therefore, their development is restricted.

Analyze above-mentioned aircraft, they are to utilize the speed of the special-purpose member of aircraft to remove to clash into air or the jet lift that provides, so its efficient is not high, particularly vertical/short take-off and landing (STOL) or when hovering.

According to aerodynamic principle, air and object which with respect to ground motion, no matter be that object is static, and air flows, or non-moving air, object of which movement, as long as the speed of the two relative motion is identical, then the mutual action of object and air is just identical.If our change method is gone motion with respect to object with the motion of air, just can realize vertical/short take-off and landing (STOL) of aircraft or hover.

The purpose of this invention is to provide a kind of aircraft with centrifugal fan for launching and landing vertically, it can be realized the vertical/short take-off and landing (STOL) of aircraft and hover.

The object of the present invention is achieved like this: the lift unit at aircraft is wing or ad hoc bay-lift, the shape of its upper surface can be convex surface, plane or concave surface, top at wing or bay-lift, be provided with centrifugal fan as the centrifugal blower fan blade wheel shape, driving engine directly or by transmission device is connected with centrifugal fan, the top parallel or summary of the following and wing of centrifugal fan air outlet or bay-lift is high, and its axis and wing or the angle above the bay-lift are between 75～90 °.Driving engine drives the air working medium that the centrifugal fan rotation obtains to have dynamic pressure energy, working medium flows to the upper surface of wing or bay-lift with horizontal direction around centrifugal fan or from the air outlet of spiral case, produce the artificial laminar flow of a continous-stable, negative pressure at the upper surface of being close to wing or bay-lift.According to the Bernoulli principle, the hydrodynamic of motion increases, and the just inevitable equivalent simultaneously of its static pressure reduces, and so just forms a zone of negative pressure on the top of wing or lifting table; And in the bottom of wing or lifting table, air is static, static pressure when its top has reduced, and stagnation pressure is constant, the static pressure of its underpart equivalent increase simultaneously becomes zone of positive pressure, just form pressure difference up and down, this in theory pressure difference can reach 100 kPas of every sq ms (10 tons) in the sea level maximum, and centrifugal fan can provide and is several times as much as 100 kPas dynamic pressure.Like this, just utilize wing or bay-lift pressure difference up and down to realize vertical/short take-off and landing (STOL) of aircraft or hover.When the malleation of wing or bay-lift bottom during greater than the deadweight of aircraft, aircraft just rises; When the back malleation that rises equaled the deadweight of aircraft, aircraft just hovered; Malleation is during less than the deadweight of aircraft, and aircraft just descends.Because working medium is to escape into the atmosphere from horizontal direction, therefore its remaining kinetic energy can not have any impact to the lift and the airworthiness of aircraft, here, when blade area one timing, dynamic pressure is high more, and pressure difference is big more up and down, the lift that produces is just big more, but the dynamic pressure loss that escapes into simultaneously in the atmosphere is just many more, and efficient is just low more, otherwise efficient is just high more.

Adopt said method, can reduce the travel deadweight of machinery of needs land or waterborne, improve its traffic potential and moving velocity, this point has the meaning of particular importance on military field and field machine.

According to the above, the invention solves the vertical/short take-off and landing (STOL) of aircraft and the problem of hovering, also can alleviate the deadweight of the machinery that travels land or waterborne simultaneously, improve its traffic potential and moving velocity.Its structure is very simple, volume is little, and is in light weight, and California bearing ratio is big, the efficient height, with low cost, easy and simple to handle, be not subjected to the influence of external condition during use, do not disturb external condition yet, safe and reliable, be adapted to all civil and military fields, aviation aircraft, the machinery that travels, elevator machinery and field machine and other field, field of application is very extensive.

The present invention is further illustrated in conjunction with the accompanying drawings more below:

Fig. 1 is the structural representation of one of embodiment of the invention autogyro.

Fig. 2 is the structural representation of two aircrafts of the embodiment of the invention.

Fig. 3 is the birds-eye view of Fig. 2.

Fig. 4 is the structural representation of three flying saucers of the embodiment of the invention.

Fig. 5 is the structural representation of four carplane of the embodiment of the invention.

Fig. 6 is the structural representation of five HIKOUSENs of the embodiment of the invention.

Fig. 1 is the structural representation of one of embodiment of the invention autogyro, among the figure, top at helicopter hull 1, be provided with one and go up the wing 3 that even up as far as possible on the plane, the middle part of wing 3 is provided with a centrifugal fan 4, and driving engine 2 is located at the bottom of wing 3, directly or by transmission device 5 be connected, drive centrifugal fan 4 rotations with centrifugal fan 4.Making gas obtain dynamic pressure energy during centrifugal fan 4 rotation becomes working medium, and working medium escapes into the atmosphere after flowing to the periphery of wing 3 around the centrifugal fan 4, be close to wing 3 above form the laminar flow of a continous-stable, negative pressure.Because the gas high-speed motion, dynamic pressure increases, and its static pressure just reduces simultaneously, therefore form one and inhale the district, and below wing 3, static pressure just increases simultaneously, and the front was carried, and the speed of air and relative motion of object is identical, and the mutual action of the two is just identical.The present invention adopts mobile gas with respect to object of which movement, is to produce identical effect.For autogyro can be flown to horizontal direction, be provided with thrust (or pulling force) device 6 and promote to fly before the autogyro.When autogyro reached certain speed and makes wing 3 produce enough lift, centrifugal fan 4 quit work, but and the inside of retraction wing 3 and rectification, autogyro changes average flight state over to.When autogyro needs to slow down, hover or land, restart centrifugal fan 4 rotations, can reach the purpose that autogyro vertically descends, hovers.Certainly, windstream can take place when improving for this autogyro flying speed when disturbing the problem of wing forward layer stream and centrifugal fan to stop the rotation lift changes the lift imbalance problem of transition to wing, and this can structurally solve separately.

Fig. 2, the 3rd, the structural representation and the birds-eye view of the embodiment of the invention 2 aircrafts.Among the figure, wing 3 is located at the top of fuselage 1 and evens up as far as possible.In the place ahead of left and right sides wing 3 and the junction of fuselage 1, respectively establish 4, two centrifugal fans of a centrifugal fan and be contrarotation, can be respectively by driving engine 2 independent drive.The working medium that produces during centrifugal fan 4 rotation the top of wing 3 flow to wing above form laminar flow, produce a zone of negative pressure on wing top, the wing bottom then is a zone of positive pressure, pressure difference up and down produces lift rises aircraft, fly before 6 promotion aircrafts of thruster, can realize the short takeoff of aircraft.When aircraft reached certain speed wing 3 and produces enough lift, centrifugal fan 4 quit work and rectification, and aircraft can enter average flight state.When aircraft need land, restart centrifugal fan work, can realize the short range landing.

Fig. 4 is the structural representation of 3 flying saucers of the embodiment of the invention.Among the figure, the bay-lift 8 of flying saucer is circular or microscler, is provided with a centrifugal fan 4 above it, and microscler establishes two or many, and driving engine 2 can directly or by transmission device 5 connect, and thruster 6 is located at the bottom of bay-lift 8.Driving engine 2 drive centrifugal fans 4 rotations produce working medium flow to bay-lift 8 around after escape in the atmosphere, form a continous-stable at the upper surface of being close to bay-lift 8, the laminar flow of negative pressure, bay-lift 8 following then becomes a zone of positive pressure simultaneously, pressure official post bay-lift 8 up and down produces a lift, centrifugal fan 4 rotations are fast more, pressure difference up and down is big more, lift is just big more, before making the flying saucer energy, fly, can set up one or more thruster 6, thruster 6 can be around the horizontal direction rotating certain angle, to offset the deflecting torque that produces when centrifugal fan is worked or flying saucer is turned to.Flying saucer is suitable for doing elevator machinery and uses, and with regard to present technical merit, its load-carrying ability can reach thousands of tons of.It also is suitable for using on small-sized or the minute vehicle.In order to improve aeroperformance, can be higher than the center around the bay-lift, make laminar flow stable and uniform more, and the 1ift-drag ratio that it causes is inappreciable.

Fig. 5 is the structural representation of 4 carplane of the embodiment of the invention, and among the figure, the top of vehicle body 9 is provided with bay-lift 8, and centrifugal fan 4 is located in the middle of it, and long car can be established two or many, by transmission device or directly be connected with driving engine.Produce during centrifugal fan 4 rotation working medium flow to bay-lift 8 around after escape into atmosphere, form the laminar flow of a negative pressure at the upper surface of being close to bay-lift 8, and following air is a zone of positive pressure, the pressure difference that produces produces lift up and down, make carplane leave the stratum, advance by the thruster 6 that is located at vehicle body 9 rear portions again.Heavy goods vehicles or field machine can only be established centrifugal fan device work and alleviate its deadweight, improve its traffic potential and improve moving velocity.

Fig. 6 is the structural representation of 5 HIKOUSENs of the embodiment of the invention, among the figure, the top of hull 10 is provided with a bay-lift 8, be provided with one or more centrifugal fan 4 above the bay-lift 8, driving engine drives centrifugal fans 4 rotations by transmission device 5 and produces working medium, working medium flow to bay-lift 8 around after escape in the atmosphere, produce the laminar flow of a band negative pressure at the upper surface of being close to bay-lift 8, barometric pressure forces the part of HIKOUSEN or major part to carry away the water surface, promotes it by thruster 6 and advances.In order to make HIKOUSEN keep stable, the hull bottom can be made into two bodies.

In above-mentioned aircraft, if the tail gas of driving engine is imported centrifugal fan (can adopt two-sided air inlet), lift unit did not freeze when aircraft was used under the condition of cold, can eliminate infrared radiation fully again, and was militarily significant.

The present invention is adapted to the aircraft of all drives and the vehicle, elevator machinery, military field, field machine etc., and from miniature to huge, range of use is quite extensive.

Claims

1, a kind of aircraft with centrifugal fan for launching and landing vertically, it is characterized in that above the lift unit wing of aircraft or bay-lift, be provided with the centrifugal fan of the impeller shape that is equivalent to centrifugal blower, driving engine directly or by transmission device is connected with centrifugal fan, the rotation of drive centrifugal fan, generation has the air working medium of dynamic pressure energy, working medium around centrifugal fan or air outlet flow to the horizontal direction of wing or bay-lift, produce the artificial laminar flow of a continous-stable, negative pressure at the upper surface of being close to wing or bay-lift.

But 2, band centrifugal blower vertically taking off and landing flyer according to claim 1, the last plane that it is characterized in that the lower plane of centrifugal fan and wing or bay-lift is on same horizon, or the lower plane of centrifugal fan is a little more than the last plane of wing or bay-lift, and the angle on the last plane of its rotation axis and wing or lifting table is between 75～90 °.

3, the aircraft of band centrifugal fan for launching and landing vertically according to claim 1 is characterized in that being provided with centrifugal fan above the helicopter wing, and driving engine directly or by transmission device is connected with centrifugal fan.

4, the aircraft of band centrifugal fan for launching and landing vertically according to claim 1 is characterized in that the position that is connected with fuselage in the front portion of aircraft left and right sides wing respectively being provided with centrifugal fan, and driving engine directly or by transmission device is connected with centrifugal fan.

5, the aircraft of band centrifugal fan for launching and landing vertically according to claim 1, the lift unit that it is characterized in that flying saucer is a bay-lift, and flat-bed top is provided with centrifugal fan, and driving engine directly or by transmission device is connected with centrifugal fan.

6, the aircraft of band centrifugal fan for launching and landing vertically according to claim 1 is characterized in that the top of carplane is provided with a bay-lift, and bay-lift is provided with centrifugal fan, and driving engine directly or by transmission device is connected with centrifugal fan.

7, the aircraft of band centrifugal fan for launching and landing vertically according to claim 1 is characterized in that the top of HIKOUSEN is provided with bay-lift, and bay-lift is provided with centrifugal fan, and driving engine directly or by transmission device is connected with centrifugal fan.