The subject of the invention is an enhanced driver unit for circular wing, which can be used for driving structure based on aerodynamic lifting effect having a circular wing embodiment ensuring a better efficiency and a more balanced drive, and also which improves the stability and controlling ability of lifting structures established with circular wing.

According to the state of art the US 2 726 829 patent document makes known circular wing aircraft.

The US 6 450 446 patent document makes known counter rotating circular wing for aircraft.

The US 2008302920 patent document makes known aerial lifting and propulsion device.

The US 2010270420 patent document makes known an aircraft with fixed circular wing.

The US 5503351 patent document makes known the flying structure provided with circular wing. The essential idea of this invention is that the well-known airfoil used in aircraft is arranged as a circular wing to which air is blown from the direction of the circle centre by an air blower device, in the given case by an impeller. The flowing air produces a lift on the aerodynamically suitable airfoil the same way, which is applicable for lifting airborne vehicle mentioned in the invention, for instance a helicopter.

In case of the solution introduced in the invention the air is blown onto the circular ring from the inside by means of suitable device, by a so called impeller, which has blades with arch starting from the centre, and it blows the air perpendicularly to the axis of rotation. The experiments conducted with the solution introduced in the invention verified that the construction is capable of operating, however, the possibilities were limited for practical testing or taking measures and gaining experience. It can be seen from the experiences gained untill now, that the lifting capability depends on the intensity of air flow blown on the circular ring, and can be increased by increasing the airflow.

While developing the solution according to the invention the aim was, and therefore the further improvements aimed in multiple directions.

- One of the aim was to establish alterative embodiments of the already existing construction working with impeller, and to increase its efficiency.

- Finding other solutions for blowing the air, which ensure the efficient air flow.

- Finding the various modes of improving the efficiency of air guiding.

- Considering further aspects, such a balancing the momenst, stability, ability to control. A further aim was to establish equipment for measurement and for obtaining practical experience, which would form basis for the applications in various fields.

During the development of the solution according to the invention we recognized, that the lifting effect could be improved, if the intensity of air blown on the circular wing is increased. We recognized, that the air blowing can be increased, if the air is blown on the impeller by means of a fan, and if we use more than one impellers and corresponding number of fans. According to our recognition, the blowing of air onto the circular wing can be increased according to this invention also by using one or two jets, which use their respective deflectors to direct the air laterally to the circular wing, as a result of which the lifting force occurs the same way, and the set out aim can be achieved.

The invention is an enhanced driver unit for circular wing, which can be used for driving structures based on aerodynamic lifting effect, having a circular wing embodiment, ensuring a better efficiency and a more balanced drive, and also which improves the stability and controlling ability of lifting structures established with circular wing, and in which a circular wing is created with aerodynamically suitable profile for ensuring the lift, with an impeller installed near to it, which rotates at its middle around a drive shaft, which impeller blows the air from central direction laterally towards the circular wing, on which a lifting force is produced thanks to the profile of the airfoil. It is characterized by that, in the driver unit according to the invention a fan is used above the impeller in order to enhance the air blowing effect of the impeller, which blows the air onto the blades of the impeller from above.

In a preferred embodiement of the solution according to the invention the fan is installed above the impeller on the same drive shaft.

In another preferred embodiement of the solution according to the invention in the driver unit according to the invention two impellers rotating in the opposite directions are used in the driver unit according to the invention, and a fan is installed above the upper impeller.

In a further preferred embodiement of the solution according to the invention a closing plate is used for guiding and bordering the airflow below one of the impeller or below the other impeller.

In a further preferred embodiement of the solution according to the invention the air is allowed to flow to the lower impeller through a hole prepared in the middle of the upper impeller.

In a further preferred embodiement of the solution according to the invention in the driver unit the impellers rotating in opposite directions are provided with a fan above the upper impeller and with a fan below the lower impeller.

In a further preferred embodiement of the solution according to the invention the drive shafts ensure the drive of the impellers rotating in opposite directions, so that the upper impeller rotates in the direct rotating direction corresponding to the rotating direction of one of the drive shafts, while the lower impeller rotates in the opposite indirect rotating direction. In a further preferred embodiement of the solution according to the invention within the driver unit a cover is provided at the fan above one of the impeller, and in the given case at the lower fan below the other impeller, the upper and lower parts of which act as air guiding funnels for directing the intake air.

The invention is furthermore enhanced driver unit for circular wing, which ensures a more balanced drive of structures having circular wing and working on the basis of aerodynamic lift, which also improves the stability and controlling ability of lifting structures having circular wings, and in which a circular wing is installed for providing lift by means of aerodynamical ly suitable profile, and an air blowing device is installed at its central location for blowing the air from a central direction laterally to the circular wing, where the shape of the wing profile ensures a lift. It is characterised by that, in the upper part of the driver unit according to the invention there is a vertically aligned jet at the central location of the circular wing, and a deflector is placed in the given case on a closing plate below the jet, which deflects the air flow discharged vertically downwards to the direction of the circular wing laterally, thus the intake air of the jet is discharged from the driver unit in lateral direction as the air to circular wing, and its direction could be influenced by means of suitably adjustable nozzle opening.

In a preferred embodiement of the solution according to the invention there is a jet in the upper part of the driver unit, and there is another jet at the opposite lower location aligned vertically, and two deflectors are installed facing one another between the jets in two directions, and these two deflectors guide the air discharged vertically downwards and upwards from the jets to the direction of the circular wing laterally, thus the intake air of the jets is discharged from the driver unit in lateral direction as the air to circular wing, and its direction could be influenced by means of suitably adjustable nozzle opening.

In a further preferred embodiement of the solution according to the invention a cover is provided above the jet in the upper section of the driver unit, as well as below the other jet located at the opposite lower section in the given case, the upper and lower parts of which act as air guiding funnels for directing the intake air.

In a further preferred embodiement of the solution according to the invention there is an adjustable nozzle opening within the driver unit around its side, from which the air to circular wing is directed from around its inside to the circular wing.

In a further preferred embodiement of the solution according to the invention the adjustable nozzle opening consists of plates that can be moved upwards and downwards, the position of which greatly influences the direction and quantity of air flowing to the circular wing.

In a further preferred embodiement of the solution according to the invention the driver unit is located in the given case above or next to the aircraft preferably in a symmetrical fashion.

The solution according to the invention is furthermore set forth on the base of the enclosed figures as follows:

Fig. 1 shows an aircraft established with circular wing according to the state of art. Fig. 2 shows the detailed embodiment of the circular wing according to the state of art. Fig. 3 shows the air flow conditions in a general case when circular wing is used.

Fig. 4 shows a possible embodiment of the driver unit according to the invention, where a fan is situated above the impeller.

Fig. 5 shows yet another possible embodiment of the driver unit according to the invention in case if using two impellers, where a fan is situated above the upper impeller.

Fig. 6 shows another possible embodiment of the driver unit according to the invention, when two impellers and two fans are used at the top and at the bottom.

Fig. 7 shows the top view of the driver unit according to the invention together with plates of the adjustable nozzle openings arranged laterally in a circle.

Fig. 8 shows the cross section A- A of the arrangement introduced in Fig. 7. Fig. 9 shows a further mode of air blowing onto the circular wing, when a jet is used for this purpose.

Fig. 10 shows a possible embodiment of blowing air onto the circular wing by means of jet from above and from below.

Fig. 1 shows an aircraft established with circular wing 2 according to the state of art. An aircraft 1 and a circular wing 2 was already described in the patent document US 5503351 , the further development of which is the purpose of this invention. Accordingly, as can be seen in Fig. 1 , the circular wing 2 providing the lift is located above the aircraft 1 , the driving unit of which is formed by an impeller 5 rotating above a circularly formed closing plate 6. The impeller 5 rotating around the driving shaft 4 blows the air in central direction above the circularly shaped closing plate 6 from vertical direction towards the circular wing 2 laterally, on which a lifting force FL is produced as a result of the airfoil shape of the wing.

Fig. 2 shows the detailed embodiment of the circular wing 2 according to the state of art. The cross section of the circular wing 2 can be seen in the figure, which has a suitable profile designed in line with the aerodynamic requirements, and the impeller 5 can also be seen here, which rotates above the circularly shaped lower wing plate 6 to blow the air onto the circular wing 2, on which a lifting force FL is produced as a result.

Fig. 3 shows the air flow conditions in a general case when circular wing 2 is used. The figure depicts an aircraft 1 with a driving unit 3 placed on its top designed with circular wing 2. The air intake ΑΓΝ takes place from above in case of driving unit 3, which is ensured by the impeller 5 situated at the top. The impeller 5 delivers the air ACT to the circular wing 2, which ensures the lifting force FL around the circular wing 2. If the impeller 5 blows the air on the circular wing 2 uniformly around, then the lifting force FL is generated also in a uniform fashion, thus producing a balanced lifting force. Fig. 4 shows a possible embodiment of the driver unit 3 according to the invention, where a fan 7 is situated above the impeller 5. In this case the blowing of air by the impeller 5 is improved by the use of the fan 7 used above the impeller 5 on the same drive shaft 4, which blows the air onto the blades of the impeller 5 while rotating together with the impeller 5. I case of this embodiment of the driver unit 3 according to the invention the fan 7 and the impeller 5 are provided with a cover 8 on the top, the upper part of which is shaped as a funnel for guiding the air, while a wing plate 6 is installed at the bottom below the impeller 5. An adjustable nozzle opening 9 is formed with a circular shape in lateral direction. At the bottom of the figure the rotating direction DR of the drive shaft 4 is shown, which is identical to the rotating direction of the impeller 5 and the fan 7.

During the operation of the driver unit 3 the air intake ΑΓΝ takes place from above, and the air to circular wing ACW is directed to the circular wing 2 through the laterally situated adjustable nozzle opening 9. The quantity of intake air is increased by the fan installed above the impeller 5. The direction and rate of air flow to the circular wing 2 can be efficiently influenced by the adjustable nozzle opening 9. The lifting capability of the driver unit 3 is substantially determined by this, and by influencing the lifting force produced at various parts of the circular wing 2 the position of the entire lifting unit, and in turn the aircraft 1 can be adjusted, can be titled or changed in any direction.

Fig. 5 shows yet another possible embodiment of the driver unit 3 according to the invention in case if using two impellers 5,10, where a fan 7 is situated above the upper impeller 5. In case of this embodiment, the two impellers 5, 10 rotate in opposite direction, and these are driven by the drive shaft 4,1 1. The upper impeller 5 rotates in direct rotating direction DR corresponding to the rotating direction of the shaft 4, while the impeller 10 rotates in the opposite indirect rotating direction IDR. The fan 7 is installed above the upper impeller 5 on the same drive shaft 4. The entire driver unit 3 is bordered by the cover 8 at the top and by the wing plate 6 at the bottom. The air intake ΑΓΝ takes place from above, while the delivery of air to circular wing ACW towards the circular wing 2 takes places laterally through the adjustable nozzle opening 9. The air is allowed to flow to the lower impeller 10 by the opening established at the middle of the upper impeller 5.

The stability of the present embodiment is significantly enhanced by the fact, that the lower impeller 10 rotates in the apposite direction relative to the upper impeller 5, thus the stability of the aircraft 1 can be ensured much easier, because the generated moments are balanced. The lateral rotation or turning of the aircraft 1 is possible in a simple manner by suitably changing the moments of the two impellers 5, 10.

Fig. 6 shows another possible embodiment of the driver unit 3 according to the invention, when two impellers 5 and 10 and two fans 7, 12 are used at the top and at the bottom. In case of the present embodiment, the fan 7 is situated above the impeller 5, while the other fan 12 is situated below the lower impeller 10. In the present embodiment the two impellers 5 and 10 rotate in directions opposite to one another, and are driven by the drive shafts 4 and 1 1. The upper impeller 5 rotates in direct rotation direction DR corresponding to the rotating direction of the shaft 4, while the impeller 10 rotates in the opposite indirect rotation direction IDR. The fan 7 is installed above the upper impeller 5 on the same drive shaft 4, while the fan 12 is installed below the lower impeller 10 on the same drive shaft 1 1. The entire driver unit 3 is bordered by the cover 8 at the top and at the bottom, the lower and upper parts of which act as air deflecting funnels for guiding the incoming and intake air ΑΓ . The air intake AIN takes place with fans 7, 12 from above and from below, the air to circular wing ACW is delivered towards the circular wing 2 in lateral direction thought the adjustable nozzle opening 9.

The stability of the present embodiment is greatly improved by the fact that the lower impeller 10 rotates in opposite direction relative to the upper impeller 5, and the air intake ΑΓΝ also takes place from two directions. This improves the stability of the aircraft 1 further, because the aerodynamically effects caused by the air intake AIN are also balanced in addition to the balancing of the generated moments. The lateral rotation or turning of the aircraft 1 is possible in a simple manner by suitably changing the moments of the two impellers 5, 10. Fig. 7 shows the top view of the driver unit 3 according to the invention together with plates of the adjustable nozzle openings 9 arranged laterally in a circle.

Fig. 8 shows the cross section A-A of the arrangement introduced in Fig. 7, which corresponds to the embodiment of the bottom - top air intake ΑΓΝ shown in Fig 6 containing the described two impellers 5, 10, as well as the two fans 7, 12. The adjustable nozzle opening 9 preferably consists of plates that can be moved downwards and upwards, the position of which greatly influences the direction and extent of air flowing onto the circular ring 2. As a result, it directly influences the lifting force FL produced on the circular wing 2.

Fig. 9 shows a further mode of air blowing onto the circular wing, when a jet 13 is used for this purpose. In the figure it is possible to see the driver unit 3, in the upper part of which a jet 13 is installed with vertical alignment. The deflector 14 is placed on the closing plate 6 below the jet 13, which guides the air flow coming vertically downwards from the jet in lateral direction towards the circular wing 2. In this way the intake air AIN of the jet 13 is discharged from the driver unit 3 in lateral direction as the air to circular wing ACW, the direction of which can be influenced by means of the adjustable nozzle opening 9.

Fig. 10 shows a possible embodiment of blowing air onto the circular wing 2 by means of jet 13 and 15 from above and from below.

In the figure it is possible to see the driver unit 3, in which the vertically aligned jet 13 is installed at the upper sectiion, and the jet 15 is installed at the opposite side in the lower section. Two deflectors 14 are installed between the jets 13 and 15 in two directions facing one another. The two deflectors 14 guide the air flowing downwards vertically from the jets 13 and 15 in lateral direction towards the circular wing 2. In this way the intake air AIN of the jets 13, 15 is discharged from the driver unit 3 in lateral direction as the air to circular wing ACW, the direction of which can be influenced by means of the adjustable nozzle opening 9.

The stability of the embodiment using symmetrically arranged jets 13 and 15 as shown in Fig. 10 is greatly enhanced by the fact that the lower jet 15 rotates in opposite direction relative to the jet 13, and the air intake AIN takes place from two directions. This improves the stability of the aircraft 1 further, because the aerodynamic effects caused by the air intake ΑΓΝ are also balanced in addition to the balancing of the generated moments. The lateral rotation or turning of the aircraft 1 is possible in a simple manner by suitably changing the moments of the two impellers 13, 15.

Possible embodiments, versions of the solution according to the invention:

A number of modes and embodiments were considered during the further development.

Version I:

Using a fan as an air mover, an air blower. The effects of this fan are as follows:

1. The funnel-like embodiment on the upper inlet opening produces a lift, and facilitates the flow of air without turbulence.

2. If a ducted fan with large surface is installed upstream to the impeller, then it eliminates the vacuum produced by the impeller, which would otherwise limit the maximum air delivery.

3. Adding a second impeller and fan rotating in the opposite direct, which intakes air from below, thus doubling the air delivery with the same overall dimensions, and eliminating the counterrotation.

4. The lower and upper part of annular guide nozzle of the discharge air can be moved in vertical direction, thus controlling the direction of the discharged air in vertical direction, and influencing the air velocity, because the lifting force and the efficiency could be controlled.

Version II

Application of a further impeller. There is no lower fan, its place is closed. The air is allowed to enter into the further impeller through the opening established at the middle of the upper impeller.

Versions for the joint use of fan and impeller:

The systematic possibilities of the joint application of fan and impeller are as follows: - The fan helps to guide the air and to blow the air onto the impeller, thus increasing the flow rate, which increases the velocity of air discharged from the impeller. As a result, the velocity of air flow is increased, and with this the lift produced on the wing surface is increased.

- In case of another embodiment, the air is blown in from above, which is ensured by the fan located at the top, but there are two impellers below turning in opposite directions, which ensure the balancing of the moments and improving the discharge of air.

- In a further embodiment, the two fans located at the top and at the bottom allows the intake of double quantity of air, as a result of which the upper impeller blows the air delivered by the upper fan, and the lower impeller blows the air delivered by the lower fan to the airfoil. This also influences the double air velocity and quantity.

The fans and impeller rotating in the opposite direction ensure a full balancing of moments.

A further possibility of air blow is the application of "jet", i.e. air turbine. The systematic advantages of the use of jet air blow are as follows:

The jet air blow provides a further possibility of blowing air onto the circular wing, i.e. the application of "jet", which eliminates the necessity of using separate fan.

The use of jet provides a high capacity and eliminates the necessity of separate fan, however, an air deflecting profile has to be uses at the bottom, which guides the air jets in lateral direction.

With the use of suitable deflecting shapes it is possible to use two jets turned face to face. This construction is symmetrical, which fully solves the problem of moment balancing, and it increases the air delivery. Directions, possibilities for further development:

Application of deflectors, controlling the lateral discharge of air.

With the use of deflectors it is possible to control the spatial distribution of discharged air, and to influence the direction and intensity of air flowing to the airfoil.

Advantages of the solution according to the invention:

Advantages:

- Compact embodiment.

- Increased air delivery.

- Balancing the moments because of the impellers or jets rotating in opposite directions.

- The spatial distribution of the air flowing in the direction of circular wing can also be controlled in addition to its velocity by means of deflectors and the impellers rotating in opposite directions.

List of references:

1 - aircraft

2 - circular wing

3 - driver unit

4 - drive shaft

5 - impeller (I)

6 - closing plate

7 - fan (I)

8 - cover

9 - adjustable nozzle opening 10 - impeller (II)

1 1 - drive shaft

12 - fan (II)

13 - jet (I)

14 - deflector

15 -jet (II)

FL -force lifting

ACW -air to circular

ΑΓΝ -air inlet

DR -direct rotation direction IDR - indirect rotation direction