VERTICAL TAKE-OFF AND LANDING AIRCRAFT

Abstract

A vertical take-off and landing aircraft comprising two turbines, the lower of which is plate-like, and the upper is flat or plate-like. Each turbine comprises a reactive power plant comprising an air engine and receivers connected to a compressor. The body of each turbine is mounted on a metallic disc connected to a vertical shaft of the aircraft, and is equipped with vanes. The vanes are mounted in a single row along the perimeter of the body or are arranged in a single tier such that the position thereof can be changed. The aircraft can comprise intermediate turbines which are mounted between the upper and lower turbine and are flat or plate-like. The body of each turbine is metallic and comprises two rings, one of which is connected to the disc, and also radial struts mounted along the perimeter of the turbine body and connected to the rings and vanes.

Claims

1. The vertical take-off and landing aircraft is characterized in that it comprises at least two turbines, the lower of which is dish-shaped and the upper is flat or dish-shaped, each turbine comprising a jet propulsion power unit, and the casing of each turbine is mounted on a metallic disk connected to a vertical shaft of the aircraft, and is equipped with blades mounted such that the position thereof can be changed.

2. The vertical take-off and landing aircraft as claimed in claim 1 is characterized in that it comprises at least one intermediate turbine mounted between the upper and lower turbines and made flat or dish-shaped.

3. The vertical take-off and landing aircraft as claimed in claim 1 is characterized in that it is equipped with a cockpit.

4. The vertical take-off and landing aircraft as claimed in claim 1 is characterized in that the jet propulsion power unit of each turbine comprises at least one air engine and receivers connected to a compressor or compressors.

5. The vertical take-off and landing aircraft as claimed in claim 1 is characterized in that to provide lateral-direction motion, the aircraft is equipped with at least one turbine for horizontal motion and air intakes connected to the bypass control valves by means of the internal turbine receivers.

6. The vertical take-off and landing aircraft as claimed in claim 1 is characterized in that the casing of each turbine is metallic and comprises at least two rings, one of which is connected to the disk, and also radial struts mounted along the perimeter of the turbine casing and connected to the rings and blades.

7. The vertical take-off and landing aircraft as claimed in claim 1 is characterized in that to change the position of the blades, the aircraft is equipped with a blade pitch control device and/or blade extension control device.

8. The vertical take-off and landing aircraft as claimed in claim 1 is characterized in that the blades are mounted at least in one row along the perimeter of the casing.

9. The vertical take-off and landing aircraft as claimed in claim 1 is characterized in that the blades are positioned at least in one tier.

10. The vertical take-off and landing aircraft as claimed in claim 1 is characterized in that the blades are mounted with partial overlapping.

11. The vertical take-off and landing aircraft as claimed in claim 1 is characterized in that it comprises additional side blades mounted on the casing of the turbines and configured to change the rotation angle by up to 90.

12. The vertical take-off and landing aircraft as claimed in claim 1 is characterized in that it comprises electric generators.

13. The vertical take-off and landing aircraft as claimed in claim 1 is characterized in that to provide for the flat attitude in the air the aircraft is equipped with a balancing wing mounted on the casing of the upper turbine configured to adjust its rotation.

14. The vertical take-off and landing aircraft as claimed in claim 1 is characterized in that is equipped with supports for the purpose of the aircraft landing and parking.

Description

[0053] The claimed invention is explained in the following drawings.

[0054] FIG. 1 shows the general view of the aircraft with the horizontal moving turbine;

[0055] FIG. 2 shows the cross-sectional view of the aircraft with two intermediate turbines;

[0056] FIG. 3 shows the blades from two adjacent rows (inside view);

[0057] FIG. 4 shows a segment of the turbine casing with two adjacent rows of the blades (top view);

[0058] FIG. 5 shows the aircraft (top view);

[0059] FIG. 6 shows a design variant of the aircraft with upper flat turbine;

[0060] FIG. 7 shows connection of the blades mounted in the tier.

[0061] The aircraft components on the figures stated above are specified under the following reference numbers:

[0062] 1blade of one row of the upper turbine;

[0063] 2blade of the other row of the upper turbine;

[0064] 3blade of one row of the lower turbine;

[0065] 4blade of the other row of the lower turbine;

[0066] 5side blade;

[0067] 6casing of the upper turbine;

[0068] 7casing of the lower turbine;

[0069] 8nozzle of the jet propulsion power unit;

[0070] 9air intake of the horizontal motion turbine;

[0071] 10vertical axis of the aircraft;

[0072] 11small (upper) disk of the upper turbine;

[0073] 12small (lower) disk of the lower turbine;

[0074] 13intermediate turbine;

[0075] 14rod;

[0076] 15blade extension control device;

[0077] 16lever of the blade extension control device;

[0078] 17blade pitch control device;

[0079] 18lever of the blade extension control device;

[0080] 19side blade control device;

[0081] 20lever of the blade pitch control device;

[0082] 21ball joint;

[0083] 22radial strut;

[0084] 23larger ring of the casing;

[0085] 24balancing wing;

[0086] 25ball joint of the balancing wing;

[0087] 26smaller ring of the casing;

[0088] 27intermediate ring of the casing.

[0089] The claimed vertical take-off and landing aircraft operates as follows.

[0090] Air engines of the jet propulsion power units of the aircraft are started. During climbing, the blades 1, 2 of the upper turbine, blades 3, 4 of the lower turbine and side blades 5 of the upper and lower turbines are simultaneously open. The blade tilt control device 17 lifts (inclines) one side of the blades 1, 2 of the upper turbine and blades 3, 4 of the lower turbine by means of the levers 18; the other side of the blades 1, 2 of the upper turbine, blades 3, 4 of the lower turbine moves down automatically so that the air is boosted from the top and directed downwards (inside the aircraft casing). The blade extension control devices 15 lift the rods 14 by means of the levers 16 to extend the blades 1, 2 of the upper turbine and blades 3, 4 of the lower turbine to the required height. The side blade tilt control devices 19 by means of the levers 20 and side blade extension control devices (not shown in the drawings) control the change of the position of the side blades 5 so that the side blades 5 boost the air from the top and direct it downwards.

[0091] If the intermediate turbines 13 are available, the blades of the intermediate turbines 13 are open in climbing, and boost the air from the top and direct it downwards. The upper turbine sucks the air from the top and directs it downwards to the intermediate turbines 13; the latter in their turn direct the air to the lower turbine, which sends the air downwards. The air is exhausted (as exhaust gas) through the vertical RPU (not shown in the drawings) augmenting the aircraft lift. Thanks to the synchronous operation of all turbines, the aircraft easily takes off. After the aircraft has gotten off the ground, the turbines for lateral motion are started. The aircraft is getting off the ground and flying in a specified direction at the same time. The specified direction is adjusted with the help of the bypass valves (not shown in the drawings).

[0092] Having gained altitude in case of the aircraft lateral motion (motion in the horizontal plane), the blades 1, 2 of the upper turbine, blades 3, 4 of the lower turbine and side blades 5 may be shut (lowered) to starting position. In case of moving horizontally with descent the blades 1, 2 of the upper turbine, blades 3, 4 of the lower turbine and side blades 5 are open so that the headwind blowing from the bottom and in the direction of the aircraft motion rotates the turbines, creates resistance for the aircraft descent and generates electric power.

[0093] To maintain the required altitude, the upper turbine sucks the air from the top and directs it downwards keeping the aircraft at the required altitude. The lower turbine and the intermediate turbine (of intermediate turbines in case there are several of them) are involved when necessary; in this case, the turbines switch to the electric generators and generate electricity, which is supplied to the accumulators. The aircraft control center constantly monitors the operation of all turbines and their switching from one function to another (from the electric generators to the engines and vice versa), as well as the blades pitch (and/or extension) on each turbine is controlled.

[0094] The claimed aircraft is able to land in case of emergency even from high altitude, remaining undamaged as each turbine is provided with at least one air engine and separate receiver, which are separately connected to the compressor or several compressors. The air engines are automatically started at a certain speed of descent and maintain required speed when landing; the engines are provided with a separate (emergency) control system.