RU2240958C1 - Vertical take-off and landing aircraft - Google Patents

Abstract

FIELD: helicopter manufacturing.

SUBSTANCE: the aircraft has an aerodynamic vertical thrust propulsor, whose body consists of two components: the upper one - conical, and the lower one-disk with a conical flanging entering the upper component with formation of an annular gap, placed in which are curvilinear blades fastening both components of the propulsor body. The flanging of the lower component is rigidly fastened to the base of the thin-walled cone with an angle at the vertex equal to 140 to 150 deg., which is located below on the aircraft vertical axis. The engine is kinematically linked with the propulsor impeller and located inside the cone. The pilot's seat is fastened outside the propulsor body.

EFFECT: enhanced safety in case of a failure of the engine or breakdown of the propulsor at landing.

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Description

The invention relates to the field of helicopter engineering and can be used in small aircraft to improve the safety of aircraft.

A device for moving vehicles in mid-air is known - a helicopter (see, for example, B.N. Yuryev. Aerodynamic calculation of helicopters. - Moscow, Oborongiz, 1956). The main disadvantage of this device is the articulated suspension of the blades, the complexity of the blades themselves, the presence of a swashplate to create a horizontal component of the thrust, a tail rotor to fend off the reactive moment created by the rotor. All this complicates its design and thereby reduces its reliability.

Known aircraft vertical take-off and landing on the application No. 2000131636/28 of the same author, which made a positive decision. It is in its technical essence closest to the proposed (prototype). In this apparatus, a vertical thrust propulsion device is used, the casing of which consists of two parts: the upper-conical and the lower-disk with conical flanging, inserted into the upper one to form an annular gap in which curved blades are placed that fasten both parts of the casing together. A vertical axis with an impeller, the blades of which are located in the upper part of the housing perpendicular to the plane of rotation of the wheel, is rotatably disposed in the lower part of the housing. The axis of the impeller is kinematically connected to the engine.

A hydroaerodynamic propulsion is used here to create horizontal traction. An engine is kinematically connected to it, which can be connected to a thrust propulsion device in case of a failure of the latter engine. This improves flight safety.

The disadvantage of the prototype is that in case of failure of two engines simultaneously, an accident is inevitable. Therefore, further safety improvements are a must.

The aforementioned drawbacks of the analogues and the prototype are eliminated by the fact that the vertical take-off and landing apparatus containing the vertical thrust propulsion device, the body of which consists of two parts: the upper one is conical with two holes in the ends, the upper one has a smaller diameter, and the lower one has a larger one and a lower one a conical flange inserted into the upper with the formation of an annular gap in which curved blades are placed that fasten both parts of the casing to each other; the vertical axis c is rotatably mounted in the lower part of the casing an impeller mounted on it, the blades of which are located in the upper part of the body and are made with a minimum clearance relative to its inner surface, and the working surfaces of the blades are installed perpendicular to the plane of rotation of the impeller, the engine with its units and devices, kinematically connected to the axis of the impeller of the propeller, a pilot's seat with engine and propulsion controls, equipped with a thin-walled cone, the apex of which lies on the vertical axis of the propulsion device at the bottom of the device, a base secured to the bottom - the disk housing portion mover, the engine is mounted inside the cone, and the pilot's seat is installed outside the propulsion unit housing.

This embodiment of the apparatus allows in the event of engine failure or engine breakdown to produce vertical descent of the apparatus with a practically safe speed.

Figure 1 shows the proposed apparatus, a longitudinal section; figure 2 is a top view without a pilot's seat.

The apparatus comprises a vertical thrust propulsion device 1, the casing of which consists of an upper - conical part 2 and a lower - disk part 3 with a conical flange 4, rigidly fastened to each other by curved blades 5, equally spaced around the circumference between the cones 2 and 4. In the disk part 3 is installed with rotary axis 6, on which the impeller 7 of the propeller is fixed. The conical flange 4 is rigidly connected to a thin-walled cone 8, the angle of which at the apex is 140-150 °, with the apex facing down. Cones 2 and 8 are aligned.

Outside of the propulsion cone 2, the pilot's seat 9 is fixed with the engine and propulsion controls. The engine 10 with all units and its servicing devices, the gearbox 11 are fixed inside the cone 8. In this case, the center of gravity of the device, without taking into account the weight of the pilot, must lie on the vertical axis of the device, i.e. the device should be centered. At the same time, the center of gravity should be located below the plane containing the circle of the largest diameter of the apparatus. The device is equipped with a shutter 12, which can be moved in the radial direction, completely or partially blocking part of the annular gap between the cones 2 and 4 of the propulsion, and fixed. The wheels 13 are mounted elastically in the bushings 14, fastened to the housing 3, so that each has the necessary elastic stroke. The device is equipped with rotary arms 15, fastened by loops 16 with curved blades 5 of the propulsion device. Through all the straps 15 passes the cable 17 with the fixation of each strap on the cable. Moving the cable tangentially in one direction or another, we reject the strap 15 from the vertical.

The device operates as follows. Turning on the engine, we begin the ascent. In this case, the pilot creates a weight violation of the centering of the device, so the rise occurs with some deviation from the vertical towards the direction of flight. If the horizontal component of the flight speed is insufficient, then we begin to gradually close the annular gap in the region of the curved blades 5 by the shutter 12, thereby reducing the lifting force at this point of the apparatus, due to which the apparatus tilts even more and acquires the desired horizontal speed. The rotation of the apparatus around the vertical axis is carried out by the deviation of the strips 15 from the vertical. To do this, pull the cable 17 in a direction tangential to it in one direction or another. Then the stream leaving the apparatus will turn the apparatus around a vertical axis, providing the desired direction of flight.

If the engine fails, the device will always start to fall down with the top of the cone 8, as the cone has a stabilizing effect on the position of the apparatus in the air and creates the necessary force Q resistance to fall in accordance with the well-known formula

,

,

where Cx is the drag coefficient of the cone to the flow running from below,

S is the area of the midsection of the cone;

ρ is the air density;

V is the rate of fall.

When falling at a constant speed, the condition Q = G must be met, where G is the weight of the device.

From experience it was found that the model of the apparatus with the diameter of the base of the cone D = 0.6 m and G = 0.25 kg has a fall velocity of V = 1 m / s. If we take the diameter of the base of the cone D = 6 m, and V = 4 m / s, then Q should increase from a change in D - 100 times, and from a change in V - 16 times, total - 1600 times. Therefore, Q = 0.25 kg · 1600 = 400 kg.

Thus, we will have the apparatus D = 6 m; V = 4 m / s; G = 400 kg.

A fall speed of 4 m / s is considered safe if the chassis travel h is at least 0.08 m (see B.N. Yuryev, page 323).

The proposed apparatus is simple in design and easy to put into practice. It provides a higher level of safety for small aircraft.

Claims (1)

A vertical take-off and landing apparatus, comprising a vertical thrust propulsion device, the body of which consists of two parts: a top-conical with two holes in the ends, a smaller diameter on top and a larger diameter below, and a lower-disk conical flange inserted into the upper part to form an annular gap in which curved blades are placed, fastening both parts of the casing to each other, in the lower part of the casing there is a vertical axis rotatably mounted with an impeller fixed to it, the blades of which are located They are wedged in the upper part of the hull and are made with a minimum clearance relative to its inner surface, and the working surfaces of the blades are mounted perpendicular to the plane of rotation of the impeller, the engine with its aggregates and devices, kinematically connected to the axis of the impeller of the propulsion device, the pilot's seat with engine controls and the engine , characterized in that it is equipped with a thin-walled cone, which has a stabilizing effect on the position in the air when falling, the top of which lies on the vert cial propulsion unit below the axis, and the base is secured to the lower housing part-disc mover, the engine is mounted inside the cone, and the pilot's seat is installed outside the propulsion unit housing.

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