Vertical takeoff and landing aircraft (Project No. 1)

Claims

1. An aircraft with vertical takeoff and landing, comprising an aircraft body with a cabin, two lifting arms located at the front and rear of the cabin, two propellers with electric drives installed in diffusers with the ability to change the angle of inclination of the propeller relative to the walls of the diffuser, an engine with a power transmission, two arched wings, two skirts, two front and one rear wheel with a control mechanism.

2. An aircraft according to paragraph 1, characterized in that, in order to create lifting and thrust forces of different directions, rotors are installed in the cavities of the diffusers, each containing two blades forming a hemisphere with the hump facing upwards and divided along the diametrical plane into two different parts, the blades are covered with a dense durable material and are secured on the inside to load-bearing arcs, stiffening arcs and additional transverse arcs, the diametrical load-bearing arcs are installed at a minimum distance from each other and are hingedly fastened by their middle parts to the axes of the head of the load-bearing shaft, the circumferential ends of the load-bearing and transverse arcs are rigidly connected to the circumferential stiffening arcs, the load-bearing arcs are connected by means of rods and hinges with a swash plate.

3. An aircraft according to paragraph 2, characterized in that in order to obtain different angles of inclination of the rotors, a cardan shaft is used, the driving part of the cardan shaft is secured to the cover of the gearbox housing and is held by a radial-thrust bearing installed in a socket made on the inside of the cover, at the end of the cardan shaft a gear wheel is installed, which is in constant engagement with another gear wheel secured on another shaft held by a radial-thrust bearing installed in a socket made in the side wall of the gearbox; the gearbox is rigidly attached to the walls of the diffuser by means of rods and stretchers;the driven yoke of the cardan shaft with the crosspiece are installed in a spherical cavity enclosed in the walls of two spheres superimposed on each other, the inner fixed sphere with a cut-off top is provided in its lower part with a flange by means of which it is rigidly attached to the cover of the gearbox housing, the upper movable sphere consists of two parts with flanges made along the circumferential surface of the hemispheres, rigidly connected to each other with bolts, the plane of the parting of the flanges is installed at the level of the center of the cardan shaft crosspiece, the flanges on four sides are provided with spherical sockets that are pivotally connected to the ball ends of the rods of the actuator cylinders, which, in turn, are pivotally attached to the wall of the gearbox, the cylinders are communicated by means of pipelines with two injection pumps used to control the apparatus "Forward" or "Backward", "Right" or "Left", "Up" or "Down", or for hovering in airspace.

4. An aircraft according to paragraph 2, characterized in that, in order to create a reliable mechanism for the angle of rotation of the blades, an automatic method is used that operates on the principle of centrifugal forces of weights; the weights are suspended at one end, by means of rods and hinges, to the blade, and at the other end they are suspended by means of rods and hinges to the ends of the sector.

5. An aircraft according to paragraph 1, characterized in that in order to increase the reliability and operability of the apparatus, a gas turbine engine with coupled turbines is used as the prime mover, comprising a split casing, two coupled turbines mounted on parallel shafts, each turbine is made in the form of a set of flat-walled disks rigidly fixed to the shafts, radial depressions are made along the circumference of the disks, the turbine disks mutually enter the gaps between each other's disks and are mated with their circumferential surfaces with the circumferential surfaces of the bushings, each turbine is equipped with removable shutters installed between the outlet window and the combustion chamber, the shutters are made detachable and consist of a pack of plates with gaps between them, fixed on common bases to the casing, the profiles of the shutters are made with the reverse configuration of the profiles of the disks and gaps of the turbines and freely enter between the disks,the inner circumferential surfaces of both valves are mated with the circumferential surfaces of the inter-disc bushings, the circumferential surfaces of the projections are mated with the circumferential surfaces of the spaces between the plates, removable dividing walls are installed on the front and rear sides of the mating turbines, blade wheels are mounted on the turbine shafts in the cavities formed between the casing walls and the dividing walls, on the front side of the casing the blade wheels take in air through channels made in the circumferential walls of the casing, on the rear side of the engine, the blade wheels take in air through channels made in the circumferential walls of the casing on the front and rear sides of the casing the turbine shafts are mounted on bearings in seats made in the casing walls, at the outgoing ends of the turbine shafts, gear wheels are installed on both sides of the casing, which are in constant engagement with each other, the gear wheels on both sides of the casing are closed by covers (walls),Fuel product supply: supplied to both turbines in two ways: a) through different windows made on the left and right sides of the body and b) through a nozzle installed next to the spark plug, communicating with the cavity of the working chamber.