AU675906B2

AU675906B2 - Vertical take-off aircraft

Info

Publication number: AU675906B2
Application number: AU37940/95A
Authority: AU
Inventors: Tom Kusic
Original assignee: Individual
Current assignee: Individual
Priority date: 1994-11-24
Filing date: 1995-11-20
Publication date: 1997-02-20
Anticipated expiration: 2015-11-20
Also published as: CA2258311A1; WO1997044240A1; CA2258311C; AU3794095A

Description

VERTICAL TAKE-OFF AIRCRAFT This invention relates to the vertical take-off field of aviation.

There are many helipcopters and gyrocopters in existence today. However, helicopters rely on variable pitch rotor blades to maintain control and provide vertical lift, while aircraft commonly referred to as gyrocopters are pushed in a forward direction on take-off due to the backward thrust of air caused by the propeller located to the rear of ooo: the engine assembly.

.e The present invention overcomes the need for varying the pitch of rotor blades while at the same time i: allowing vertical lift on take-off and directional 15 control by providing a vertical take-off aircraft using an assembly of blades and a rotor mechanism at the top of the craft, which rotor blade assembly is connected to the main body of the craft in such a way that the said rotor blade assembly can be tilted as a whole unit in various directions and angles and thus allow changes in horizontal directional travel of the craft by tilting the upper rotor blade assembly in the chosen direction of travel, without the need to change blade pitch angle. Vertical lift is obtained by the rotation of the upper rotor blade assembly thereby forcing air in a downward direction by way of the angle of pitch of the blades. Rotation of the upper rotor blade assembly is achieved using an engine assembly located between the main body of the craft and the upper rotor blade assembly which engine assembly is attached to the main body of the craft in such a way that the *engine assembly and the upper rotor blade assembly can be titled together as a unity relative to the main body of the craft and such that the rate of revolution of the upper rotor blade assembly can be controlled. During flight, rotational stability of the main body of the craft is maintained by means of an additional engine assembly attached to the main body of the aircraft which 20 rotates an assembly of rotor blades at a controlled rate of revolution pushing air 4 primarily in a horizontal direction to counter the rotational force exerted on the the main body of the craft by the rotation of the upper rotor blade assembly.

In one form attached to controlling of the invention variable pitch fins are the main body of the craft to assist in in flight manouvering of the craft.

In one form attached to of the fins of the invention the main body of is controlled by r r where variable pitch fins are the craft, the pitch angle using cables.

where variable pitch fins are the craft, the pitch angle using a gearing meachanism.

In another form of the craft attached to the main body of of the fins is controlled by In another form of the craft where variable pitch fins are attached to the main body of the craft, the pitch 15 angle of the fins is controlled by using combination of gears and cables.

In another form of the invention the main body of the craft exists without variable pitch fins being attached to such main body such that tilting of the upper rotor blade assembly is used to manouvre the craft while in flight.

In one form of the invention, the tilt enabling joint for the upper rotor blade assembly is achieved by means of a double hinged type assembly, consisting of two hinging units joined in the middle at right angles to each other, so that they form a cross, and situated between the upper engine assembly and main body of the craft. Each of the individual hinges would be similar in principle of operation to those commonly found on doors in older style houses.

The hinge mechanism can be achieved by using sections of 10 hollow tube, kept together by rods inserted within the tubes, such that one hinge unit is attached to the lower section of the upper rotor blade and engine assembly, while the other hing unit is connected to the main body of the craft.

In another form of the invention, the tilt enabling joint .".for the upper rotor blade assembly could be achieved by means of a ball and socket type assembly, whereby a ball housed in and retained within the socket, allowing freedom of movement within the socket, with a stem protruding from the ball, which stem is rigidly fixed to the ball and which stem also protrudes from the socket in which the ball is housed, with the ball and socket assembly being fixed to the aircraft between the upper rotor blade and engine assembly and the main body of the craft.

In another form of the invention, the tilt enabling joint is achieved by means of U-shaped bolts connected to each other in a similar manner to which chain linkages are connected, with the open ends of the U-shaped bolts being connected to the aircraft in such a way that the ends :10 on one bolt are connected to upper rotor blade and engine assembly, while the ends of the othei U-shaped bolt are connected to the main body of the aircraft.

In another form of the invention the tilt enabling joint is achieved by means of universal joint which 15 would consist of a rigid cross shaped section with *cylindrically shaped ends, to which ends are fitted circular caps which can swivle on the ends of the cross shaped section relative to the cross shaped section, with two opposing end caps being secured to the upper rotor blade and engine assembly, and the other two opposing end caps being secured to the upper section of the main body of the craft. This tilt enabling joint would be similar in operation to that of universal joints found on automobiles, between differential and transmission assemblies.

In one form of the invention the direction and angle of tilt of the upper rotor blade and engine assembly is controlled by handles attached to the upper rotor blade and engine assembly with the handles attached in 10 such a way that they can be reached from the main body of the craft.

In another form of the invention the direction and angle of tilt of the upper rotor blade assembly is controlled by a plurality of hydraulic 15 activated push rods located in positions between the upper rotor blade assembly and the main body of the craft such that as hydraulic pressure is applied to selected one or more push rods to force expansion of the selected rods, pressure on the rod or rods located directly on the opposite side of the tilt enabling joint to the selected expanding rod or rods is released.

8 In another form of the invention the direction and angle of tilt of the upper rotor blade assembly is controlled by a combination of springs and hydraulic activated push rods located in positions between the upper rotor blade assembly and the main body of the craft, so that as hydraulic pressure is applied to expand selected push rods, the selected rods act as a counter force to the springs, and conversly, as 1" 0 the hydraulic pressure to selected push rods is released, the springs act to compress the push rods.

In another form of the invention the direction and angle of tilt of the upper rotor blade assembly is controlled by a combination of gas 15 pressurised struts and hydraulic activated push rods located in positions between the upper rotor blade assembly and the main body of the craft, so that as hydraulic pressure is applied to expand selected push rods, the selected rods act as a counter force to the gas pressurised struts, and conversly, as the hydraulic pressure to selected push rods is released, the gas pressurised struts act to compress the push rods.

9 In another form of the invention the direction and angle of tilt of the upper rotor blade assembly is controlled by a plurality of air pressure expandable push rods located in positions between the upper rotor blade assembly and the main body of the craft such that as air pressure is applied to selected one or more push rods to force expansion of the selected rods, pressure on the rod or rods located directly on the opposite side of the tilt enabling joint to the selected expanding rod or rods, is released.

In another form of the invention the direction and angle of tilt of the upper rotor blade 15 assembly is controlled by a combination of springs and air pressure expandable push rods located in positions between the upper rotor blade assembly and the main body of the craft, :o mi so that as air pressure is applied to expand selected push rods, the selected rods act as a counter force to the springs, and conversly, as the air pressure to selected push rods is released, the springs act to compress the push rods.

In another form of the invention the direction and angle of tilt of the upper rotor blade assembly is controlled by a combination of gas pressurised struts and air pressure expandable push rods located in positions between the upper rotor blade assembly and the main body of the craft, so that as air pressure is applied to expand selected push rods, the selected rods act as a counter force to the gas 10 pressurised struts, and conversly, as the air pressure to selected push rods is released, the gas pressurised struts act to compress the push rods.

Si. In one form of the invention the distance between the tilt enabling joint and the main body of the craft is 15 constant.

In another form of the invention the distance between the main body of the craft and the lower section section of the tilt enabling joint is able to be varied by straight tubes being able to slide vertically inward and outward of tubes of relatively larger widths, in a telescopic manner, such that the length of the slide is p 11 limited by attachments to the ends of the tubes, with the upper most sections of the telescoping tube assemblies being rigidly joined to the bottom of the tilt enabling joint and with the lower most section of the telescoping tube assemblies being rigidly joined to the main body of the craft.

In another form of the invention where the distance between the main body of the crate and the lower section section of the tilt enabling joint is able to be varied 10 by straight tubes being able to slide vertically inward and outward of tubes of relatively larger widths, in a telescopic manner, valves are attched to the tubes so as to provide control on the amount of slide of the tubes.

15 In one form of the invention the upper engine assembly consists of a single engine.

In another form of the invention, the upper engine .ol.oi assembly consists of a plurality of engines.

In one form of the invention, the engine assembly attached to the main body of the craft which rotates the rotor blade assembly pushing air in a primarily horizontal direction consists of a single engine.

In another form of the invention, the engine assembly attached to the main body of the craft which rotates the rotor blade assembly pushing air in a primarily horizontal direction consists of a plurality of engines.

In one form cf the invention the blades in the upper rotor blade assembly are of fixed pitch with reference to each other.

In another form of the invention the blades in the upper rotor blade assembly are of fixed pitch with reference to each other except for being able to move to a limited extent in an upward and downward flapping motion.

In another form of the invention the blades in the upper rotor blade assembly are of fixed pitch with reference to each other except for .:go being able to move to a limited extent such that the distances o. between the outer tips of the blades in the upper rotor b £de 15 assembly are able to vary.

In another form of the invention the blades in the upper rotor blade assembly are of fixed pitch with reference to each other except for being able to move to a limited extent in an upward and downward flapping motion and also being able to move to a limited extent such 20 that the distances between the outer tips of the blades in the upper rotor blade assembly are able to vary.

In another form of the invention the blades in the rotor blade assembly forcing air in a primarily horizontal direction are of fixed pitch, To assist in understanding the invention, reference will now be made to the accompanying drawings which show two examples of the invention.

13 In the drawings: Figures 1, 2, and 3 show the rear, front, and side, respectively, of one example of the vertical take-off aircraft according to this invention, while figures 4, 5, and 6 show the side, rear, and front, respectively, of another example of the vertical take-off aircraft according to this invention.

Referring to Figure 1 it can be seen this vertical take-off aircraft consists of an assembly of rotor blades 1 at the top of the craft which assembly is rotated by a engine assembly 2 situated below the 10 rotor blade assembly 1. Tilting of the upper rotor blade assembly 1

O

and engine assembly 2 is achieved by way of a double hinged type 0000 assembly 3. The tilting operation is controlled by the use of Sm handles 4 and 5 extending from the upper engine assembly 2. The *0 SO upper engine assembly 2 and rotor blade 1 assembly is connected to the main body 6 by the hinge assembly 3. The outer sections 7 and 8 of the upper component of the hinge assemlby is fixed to the upper engine assembly 2. The middle section of the upper component of the hinge assembly is fixed to the middle section of the lower component of the hinge assembly 9. Rotational stability of the main body of i 20 the aircraft is maintained by adjusting the speed of rotation of the rear rotor blade assembly 10 which is attached to the rear engine 11.

The rate of rotation generated by the upper and rear engines is controlled by throttle controls 12 and 13 located on the handles 4 and 5. In the example a seat 14 is rigidly fixed within the main body of the aircraft.

Claims

1. A vertical take-off aircraft, comprising an assembly of blades and rotor mechanism at the top of the craft, which rotor blade assembly is above the main body of the craft, with vertical lift being achieved by an engine assembly rotating the said upper rotor blade assembly thereby forcing air in a downward direction by way of the rotor blades, which engine assembly is the upper engine assembly of the craft, and which said upper engine assembly is connected to the main body of the "craft by use of a tilt enabling joint, such that the upper engine assembly is attached to the upper section of the tilt enabling joint and such that the upper rotor blade assembly and upper engine assembly can be 0 OV* 15 titled together as a unity in a plurality of directions I and angles relative to the main body of the craft, in a S.controlled manner, such that the direction of travel of e the craft is altered by altering the direction or angle of tilt of the upper engine assembly relative to the main body of the craft with the base of the tilt enabling joint securely fixed to the upper section of the main body of the craft such that the distance between the main body of the craft and the base of the tilt enabling joint is constant, with an additional assembly of blades and rotor mechanism connected to the main body of the craft which forces air in a primarily horizontal direction relative to the main body of the craft, for which rotor blade assembly rotation is achieved by means of an engine assembly which is seperate to the engine assembly which rotates the upper rotor blade assembly, such that by forcing air in a horizontal direction, relative o..to the main body of the craft, the rotational force 10 exerted on the main body of the craft by the rotation of the upper rotor blade assembly can be countered.

2. A vertical take-off aircraft, comprising an assembly of blades and rotor mechanism, at the top of the craft, which rotor blade 15 assembly is connected to the main body of the craft by use of a tilt enabling joint such that the said rotor blade assembly is above the main oe mi S"body of the craft and such that the connection enables the said upper rotor blade assembly to be tilted as a whole unit in a plurality of directions and angles, relative to the main body of the aircraft, in a controlled manner, with the base of the tilt enabling joint connected to the main body of the craft in such a way that the distance between the base of the tilt enabling joint and the main body of the craft can be varied, with vertical lift being achieved by an engine assembly rotating the upper rotor blade ooeo assembly thereby forcing air in a downward directioih by way of the rotor blades, with such engine S. assembly being attached to the upper section of the said tilt enabling joint such that the upper rotor blade assembly and engine assembly can be tilted as a unity relative to the main body of the craft, with an additional assembly of blades and rotor mechanism connected to the main body of the craft which forces air in a primarily horizontal direction relative to the main body of the craft, for which rotor blade assembly rotation is achieved by means of an engine assembly which is seperate to the engine assembly which rotates the upper rotor blade assembly, such that by forcing air in a horizontal direction, relative to the main body of the craft, the rotational force exerted on the main body of the craft by the rotation of the upper rotor blade assembly can be countered. 17

3. A vertical take-off aircraft, comprising an assembly of blades and rotor mechanism at the top of the craft, which rotor blade assembly is above the main body of the craft, with vertical lift being achieved by an engine assembly rotating the said upper rotor blade assembly thereby forcing air in a downward direction by way of the rotor blades, which engine assembly is the upper goo engine assembly of the craft, and which said upper engine assembly is connected to the main body of the craft by use of a tilt enabling joint, such that the upper engine assembly is attached to the upper section of the tilt enabling joint and such that the upper rotor blade assembly and upper engine assembly can be titled together as a unity in a plurality of directions 15 and angles relative to the main body of the craft, in a controlled manner, such that the direction of travel of the craft is altered by altering the direction or angle of tilt of the upper engine assembly relative to the main body of the craft with the base of the tilt enabling joint securely fixed to the upper section of the main body of the craft such that the distance between the main body of the craft and the base of the tilt enabling joint is constant, with an 18 additional assembly of blades and rotor mechanism connected to the main body of the craft which forces air in a primarily horizontal direction relative to the main body of the craft, for which rotor blade assembly rotation is achieved by means of an engine assembly which is seperate to the engine assembly which rotates the upper rotor blade assembly, such that by forcing air in a horizontal direction, relative to the main body of the craft, the rotational force exerted on the main body of 10 the craft by the rotation of the upper rotor blade .assembly can be countered, and to the main body of the craft are attached variable pitch fins. S.

4. A vertical take-off aircraft, comprising an assembly of blades and rotor mechanism, at the top of the craft, which rotor blade assembly is connected to the main body of the craft by use of a tilt enabling joint such that the said rotor blade assembly is above the main body of the 20 craft and such that the connection enables the 19 said upper rotor blade assembly to be tilted as a whole unit in plurality of directions and angles, relative to the main body of the aircraft, in a controlled manner, with the base of the tilt enabling joint connected to the main body of the craft in such a way that the distance between the base of the tilt enabling joint and the main body of the craft can be varied, with vertical lift being achieved by an engine assembly rotating the upper 10 rotor blade assembly thereby forcing air in a downward direction by way of the rotor blades, with such engine assembly being attached to the upper section of the said tilt enabling joint such So that the upper rotor blade assembly and engine 15 assembly can be tilted as a unity relative to the main body of the craft, with an additional of assembly of blades and rotor mechanism connected to the main body of the craft which forces air in a primarily S"horizontal direction relative to the main body of the craft, for which rotor blade assembly rotation is achieved by means of an engine assembly which is seperate to the engine assembly which rotates the upper rotor blade assembly, such that by forcing air in a horizontal 9 direction, relative to the main body of the craft, the rotational force exerted on the main body of the craft by the rotation of the upper rotor blade assembly can be countered, and to the main body of the craft are attached variable pitch fins.

The vertical take off aircraft of any one of claims 3 or 4 wherein the variable pitch fins are controlled from the main body of the craft by cables. ooo*

6. The vertical take off aircraft of any one of claims 3 10 or 4 wherein the variable pitch fins are controlled from I the main body of the craft by a system of gears.

7. The vertical take off aircraft of any one of claims 3 or 4 wherein the variable pitch fins are controlled from the main body of the craft by a combination of cables and gears.

8. The vertical take-off aircraft of any ong of claims 4 to 7 wherein the the distance between the base of the tilt enabling joint and the main body of the craft is able to be varied by straight tubes being able to slide vertically inward and outward of tubes of relatively larger widths, in a telescopic manner, such p 21 that the length of slide is limited by attachments to the ends of the tubes, with the upper most sections of the telescoping tube assemblies being rigidly joined to the bottom of the tilt enabling joint and with lower most sections of the telescoping tube assemblies being rigidly joined to the main body of the aircraft.

9. The vertical take-off aircraft of claim 8 where in valves are connected to the telescopic sliding tubes such that by closing valves the telescopic I 10 sliding movement can be restricted.

The vertical take-off aircraft of claim 2 wherein the distance between the base of the tilt enabling joint and the main body of the craft is able to be S" varied by straight tubes being able to slide 15 vertically inward and outward of tubes of relatively em f S"larger widths, in a telescopic manner, such that the length of slide is limited by attachments to the ends of the tubes, with the upper most sections of the telescoping tube assemblies being rigidly joined to the bottom of the tilt enabling joint and with lower most sections of the telescoping tube assemblies being rigidly joined to the main body of the aircraft. 9 22

11. The vertical take-off aircraft of claim 10 where in valves are connected to the telescopic sliding tubes such that by closing valves the telescopic sliding movement can be restricted.

12. The vertical take-off aircraft of any one of claims 1 to 11 wherein the direction and angle of tilt of the upper rotor blade assembly relative to the main body of the craft is controlled by handles attached to the smoo upper rotor blade and engine assembly where such handles 10 can be reached from the main body of the craft.

13. The vertical take-off aircraft of any one of claims 1 to 11 wherein the direction and angle of tilt of the upper rotor blade assembly relative to the main body of the craft is controlled by a plurality of hydraulic 15 activated push rods located in positions between the upper rotor blade assembly and the main body *0 of the craft such that as hydraulic pressure is applied to selected one or more push rods to force expansion of the selected rod or rods, the pressure on the rod or rods located directly on the oppossite side of the tilt enabling joint to the selected expanding rod or rods, is released. U 23

14. The vertical take-off aircraft of any one of claims 1 to 11 wherein the direction and angle of tilt of the upper rotor blade assembly relative to the main body of the craft is controlled by a combination of springs and hydraulic activated push rods located in positions between the upper rotor blade assembly and the main body of the craft such that ooze as hydraulic pressure is applied to expand selected push rods, the selected rods act as a counter force to 10 the springs, and conversely, as the hydraulic pressure o: to selected push rods is released, the springs act to compress the push rods.

15. The vertical take-off aircraft of any one of claims Ito 11 wherein the direction and angle of tilt of the 15 upper rotor blade assembly relative to the main body me.o•i of the craft is controlled by a combination gas pressurised struts and hydraulic activated push rods located in poistions between the upper rotor blade assembly and the main body of the craft such that as hydraulic pressure is applied to expand selected push rods, the selected rods act as a counter force to the gas pressurised struts, and conversely, as the hydraulic pressure to selected push 24 rods is released, the gas pressurised struts act to compress the push rods.

16. The vertical take-off aircraft of any one of claims 1 to 11 wherein the direction and angle of tilt of the upper rotor blade assembly relative to the main body of the craft is controlled by a plurality of air pressure expandable push rods located in a positions between the upper rotor blade assembly and the main body of the craft such that as air pressure is increased to selected one or more push rods S: to force expansion of the selected rod or rods, the pressure on the rod or rods located directly on the opposite side of the tilt enabling joint to the selected expanding rod or rods, is released.

17. The vertical take-off aircraft of any one of claims 1 to 11 wherein the direction and angle of tilt of the .i upper rotor blade assembly relative to the main body of the craft is controlled by a combination springs and air pressure expandable push rods located in poistions between the upper rotor blade assembly aad the main body of the craft such that as air pressure is increased to expand selected push rods, the selected rods act as a counter force to the springs, and conversely, as the air pressure to selected push rods is released, the springs act to compress the push rods.

18. The vertical take-off aircraft of any one of claims 1 to 11 wherein the direction and angle of tilt of the upper rotor blade assembly relative to the main ~body of the craft is controlled by a combination gas pressurised struts and air pressure expandable push rods located in positions between thp 10 upper rotor blade assembly and the main body of the craft such that as air pressure is applied to expand selected push rods, the selected rods act as a counter force to the gas pressurised struts, and conversely, as the air pressure to selected push rods is released, the gas pressurised struts act to compress the push rods. a

19. The vertical take-off aircraft of any one of claims 1 to 18 wherein the tilt enabling joint for the upper rotor blade assembly is achieved by means of a double hinged type assembly, consisting of hinging units joined in the middle at 90 degree angles to each other, so that they form a cross, and situated between the upper engine assembly and main body of the craft, such that one hinge joint is also connected to the lower section of the upper rotor blade and engine assembly, while the other hinge joint is connected to the main body of the craft, with the hinge mechanisms being made by using sections of hollow tube, and having rods inserted within the tubes.

The vertical take-off aircraft of any one of claims 1 to 18 wherein the tilt enabling joint is achieved by means of U-shaped bolts connected to each other in a similar manner to which chain linkages are connected, with the open ends of the U-shaped bolts being connected to the aircraft in such a way that the ends on one bolt are connected to the upper rotor blade and engine assembly, while the ends of the other U-shaped bolt are connected to the main body of the aircraft. 0

21. The vertical take-off aircraft of any one of claims 1 to 18 wherein the tilt enabling joint is achieved by means of a ball m and socket type assembly, whereby a ball is housed and retained in a socket with a stem protruding from the ball, which stem is rigidly fixed to the ball, and which stem 20 also protrudes from the socket in which the ball is housed, with ball and socket assembly being fixed to the aircraft between the upper rotor blade and engine assembly and the main body of the craft.

22. The vertical take-off aircraft of any one of claims 1 to 18 wherein the tilt enabling joint is achieved by means of universal joint which would consist of a rigid cross shaped -4 .4 27 section with cylindrycally shaped ends, to which ends are fitted circular caps which can swivel on the ends of the cross shaped section relative to the cross shaped sectio, with two opposing end caps being secured to the upper rotor blade and engine assembly, and the other two opposing end caps being secured to the main body of the craft.

23. The vertical take off aircraft of any one of the claims 1 to 22 wherein the upper engine assembly consists of a single engine.

24. The vertical take off aircraft of any one of the claims 1 to 22 *o* 10 wherein the upper engine assembly consists of a pluraity of engines.

The vertical take off aircraft of any one of the claims 1 to 24 wherein the engine assembly attached to the main body of the craft which rotates the rotor blade assembly pushing air in a primarily 15 horizontal direction consists of a single engine. .i

26. The vertical take off aircraft of any one of the claims 1 to 24 wherein the engine assembly attached to the main body of the craft which rotates the rotor blade assembly pushing air in a primarily horizontal direction consists of a pluraity of engines.

27. The vertical take-off aircraft of any one of the claims 1 to 26 wherein the upper rotor blade assembly can be to be tilted as a whole unit in a plurality of directions and angles, relative to the main body of the craft, in a controlled manner, including an ability to be in tilted, in a controlled manner, relative to 28 the main body of the craft, in directions leading away form either side of the main body of the craft, and including an ability to be tilted in a forward direction leading away from the front of the main body of the craft.

28. A vertical take-off aircraft of any one of the claims of 1 to 27 wherein the blades in the upper rotor blade assembly are of fixed pitch with reference to each other.

29. A vertical take-off aircraft of any one of the claims of 1 to 27 wherein the blades in the upper rotor blade assembly 10 are of fixed pitch with reference to each other but are 04 e 0:9. able to move to a limited extent in an upward and fee: Pipe o downward f'apping motion within the assembly. .0

30. A vertical take-off aircraft of any one of the claims of I to 27 wherein the blades in the upper rotor blade assembly 15 are of fixed pitch with reference to each other but are i able to move to a limited extent within the assembly such that the distances between the outer tips of the blades in the rotor blade assembly are able to vary.

31. A vertcial take-off aircraft of claims 1 to 30 wherein the blades in the rotor blade assembly forcing air in a primarily horizontal direction are of fixed pitch with refence to each other.

32. A vertical Takeoff aircraft substantially as herein described with refernce to the accompanying drawings. TOM KUSIC 20 NOVEMBER 1995 (Name of Applicant) (Date) Abstract A vertical take-off aircraft is disclosed. The aircraft has an assembly of votor blades at the top of the craft which assembly can be tilted in a plurality of of angles and directions by way of a tilt enabling joint and which assembly of rotor blades is rotated by way of an engine assembly located S below the assembly of rotor blades The degree *so and direction of tilt is controlled by use of handles Rotational stability of the body of the aircraft is maintained by way of a seperate assembly of rotor blades which assembly of rotor blades o is rotated by the rear engine assembly (11). S S.