RU2388653C2 - Device for vtol aircraft - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to VTOL aircraft. Proposed device comprises one or more lifting bearing elements arranged, for example on airframe sides. Every said element comprises support frame with rotary shaft. Said rotary shaft supports two-bearing shaft representing a spider supporting shafts with wings (5). Rotary shaft and shafts with wings carry toothed pulleys and toothed clutches. Said pulleys are enveloped by toothed belts. Clutch throw-in or out locks or starts rotation of shafts with wings about said spider. Spider revolving at angular speed ω, clutch of shaft with wings 5 passing through sectors I and II is thrown out, while that of rotary shaft in thrown in. As a result, wing (5) revolves at ω₁ relative to spider and in opposite direction to it, driven by toothed belt enveloping toothed pulleys in spider shaft and shaft of wing (5). On the contrary, in sectors II and IV, clutch of shaft with wing (5) is thrown in, while spider shaft clutch is thrown out. This is why wing (5) is stationary relative to spider. Aircraft vertical take-off, landing and flight are realised by creating preset wing trajectory in its complex rotation about two parallel axes, aircraft full aerodynamic force comprising wings lift and front aerodynamic drag.

EFFECT: relatively simple and safe design of VTOL aircraft.

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Description

The invention relates to the field of aircraft construction and can be used to increase the scope of practical applications in aircraft in any field of aviation.

There is an aircraft (No. 2003136456 www.fips.ru) containing a frame with a horizontal rudder stabilizer, an engine, control mechanisms, as well as a supporting device made in the form of two structurally identical carrier disks mounted coaxially, the movable sleeve of which is pivotally mounted on the frame and is connected to the glider handle, each of which is simultaneously a pneumatic engine and a vertical propulsion engine, and two deafs are made in the upper part of the carrier disk, opening to the side of B deployed rotation relative to each other by 180 degrees channel.

The disadvantage of this device is the following: the significant size of the diameters of the disks to create a vertical lift, the significant weight of the disks, affecting the capacity of the apparatus, the incomplete use of the expended power, the difficulty in managing.

A device is known (Modeller-Designer, 1987, third edition, pp. 20-24 V. Kondratiev) of creating lift for vertical lift and autorotation used in rotary-wing aircraft.

The device in a simplified form is a vertically mounted hoisting rotor, which is a structure consisting of a hub with blades fixed to it, installed at a certain angle. When the rotor rotates due to the installation angle and the surface area of the blades, a lifting force Y occurs. The geometric parameters of the blades, the installation angle and the rotational speed of the lifting rotor are the main determining parameters of the carrying capacity and dimensions of aircraft with vertical lift.

The disadvantage of this device are:

- strict adherence to the characteristics of the polar and aerodynamic quality of the blade;

- significant dimensions of the diameter of the screw;

- the cantilever arrangement of the blades limits the specific load on their surface;

- incomplete use of power expended;

- the use of an additional tail rotor that extinguishes the reactive moment;

- another.

There is an invention US 5100080 A, containing a method for lifting and moving an aircraft using the maximum efficiency of the expended power, which is carried out using devices in the form of the same type of rotors having wings, the position of which is determined by the control and monitoring system in accordance with real-time flight conditions time. Each rotor has a central shaft rotating from the power plant and mounted on two supports located on the housing. Two flanges are fixed on the central shaft, between which five wings with shafts are symmetrically located, and also a gear wheel, which provides a kinematic connection between the phase shifter and the wing shafts through the mechanisms of five hydraulic drives located on one of the flanges. The phase shifter and hydraulic drives through the system of control and monitoring devices determine the necessary position of the wings for flights.

The disadvantage of this device is the complexity of the control and monitoring systems for the necessary positions of the wings during their flight path, that is, in a system of changing conditions; and since in a simplified form the kinematic diagram of the device for the wing separately is a differential mechanism having two degrees of freedom, since the two links in it are given independently of each other, and to determine any of the three values (differential), two should be set; and in the presence of several rotors, with five wings on each, the complexity of the control and control system increases, and under changing flight conditions several times. In order to ensure reliability, duplication of a number of devices is required due to their operational interconnectedness-dependency. And last, the total weight of the control and monitoring systems, as well as the wing drive mechanisms, will negatively affect the flight qualities of the aircraft.

The objective of the invention is to increase opportunities in the fields of practical application and ensuring the safe operation of aircraft with vertical lift.

The task is achieved by the fact that, creating a given trajectory of the wing - portable and relative movements with complex rotation around two parallel axes - the aircraft is vertically raised and moved with optimal changes in the angles of attack of the wing, depending on their phase angles of the trajectory.

The device is a lifting-bearing element of an aircraft with vertical ascent.

The invention is illustrated by drawings: figure 1 - the trajectory of the wing, figure 2 is a simplified kinematic diagram.

The device, which is a lifting-bearing element installed in the upper part of the sides of the fuselage, consists of two paired structures of the same type.

Each design of the device contains a support frame 1 (Fig. 2), on the axis of rotation of which are placed: clutch couplings 2, which fix or rotate the gear pulleys 3, and a two-support shaft in the form of a cross 4. On the shaft in the form of a cross 4 are: four double-support shaft 5, on each of which a wing is located (the quantity may be different) and gear clutches 6, which fix or rotate the shafts with wings 5 around their own axis. On the shaft of the wing 5 there is a rigidly set gear pulley 7, which together with the gear pulley 3 is covered by a gear belt 8.

The principle of operation (figures 1, 2) is based on figurative and relative movements during complex rotation around two parallel axes in I and II quarters and figurative in III and IV quarters of a circle and consists in the following:

- the power plant of the aircraft (not shown) transmits torque to the shaft in the form of a cross 4;

- the shaft in the form of a cross 4 carries shafts with wings 5 around its own axis (portable movement) at an angular velocity ω;

- being in I and II quarters, shafts with wings 5 rotate around their own axis (relative motion) with an angular velocity ω ₁ equal to the angular velocity ω, a shaft in the form of a cross 4 (ω = ω ₁ ). This rotation is accomplished due to the equality of the diameters of the gear pulleys 3 and 7, covered by the gear belt 8. In this case, the gear pulley 3 is fixed by the clutch gear 2 - the clutch is turned on, and the gear clutch 6 is turned off, providing rotation of the shafts with wings 5 through the gear pulley 7;

- in the third and fourth quarters, the reverse process occurs - the clutch gear 6 fixes the wing 5 (the clutch is engaged) with the gear pulley 7, and the clutch gear 2 is turned off, ensuring the rotation of the gear pulley 3. The whole cycle is repeated.

The presence of four shafts with wings 5 is explained by the total constancy of the values of the angle of attack a, equal to 90 degrees in the I and II circles.

A distinctive feature and the main advantage of the proposed device is:

- trajectories of the shafts with wings, at which the optimal changes in the angles of attack of the wing;

- rational use of power expended;

- two-bearing arrangement of elements increases the specific load, which allows to increase the carrying capacity or reduce the size of the aircraft;

- there is no need for a steering auxiliary screw;

- and more, including operational safety.

Claims (1)

A device for the vertical lifting and movement of aircraft, comprising a lifting-bearing element mounted in the upper part of the sides of the fuselage in the form of two paired structures of the same type, each of which contains a support frame with an axis of rotation, on which a two-bearing shaft in the form of a cross is mounted with shafts with wings having the possibility of rotation and fixing relative to the specified double-shaft, characterized in that on the specified axis of rotation are placed gear pulleys and gear couplings lances that provide fixation or rotation of these gear pulleys together with the specified double-shaft, made in the form of a cross, containing gear clutches for fixing or rotation of these shafts with wings, on each of which a gear pulley is fitted, covered by a gear belt, also covering the specified gear pulley located on the axis of rotation of the support frame.

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