RU2385267C1 - Method to convert disk wing - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Disk wing 1 is converted in landing or take-off into rotor due to extending blades 5 through nozzles 2, said blades being fastened by ropes 4 to drum 3 fitted on rotor (wing) shaft 7. Said blades are withdrawn into disk 1 on braking drum 3. Nozzle 5 is jointed to hub 8 of rotor shaft 7 by torsions 9 that take up crosswise load of blade 2. Nozzle 5 is fitted in wing 1 in elastomer bearings 6 that transmit crosswise load of blade 2 to skin of disk-wing 1 and form horizontal and vertical hinges. Position of nozzle 5 governed by control tie rod 11 controls angle of attack of blade 2. Extension of tie rod 11 from nozzle plane limits flapping. Blades 2 are drawn by ropes 4 into wing 1. Wing 1 rotation along frame rails 12 over, wing panels 15 are pulled out via supports 13 and carriages 14.

EFFECT: improved aerodynamic properties.

6 cl, 1 dwg

Description

The invention relates to the field of aviation and space technology, in particular to aircraft and helicopter engineering, and can be used to create a wing of a convertible aircraft (LA) with vertical take-off and landing, as well as vertical landing systems for spaceships and rocket stages on a disk wing.

There are various ways of creating high-speed aircraft with the possibility of vertical take-off and landing, and, consequently, the rotor conversion system when switching to horizontal flight modes and vice versa (Aviation: Encyclopedia, M .: Big Russian Encyclopedia, 1994 - 736 p.) [ p. 466].

Closest to the proposed invention, taken as a prototype, may be the “Pavlov Aircraft Wing”, RF patent No. 2101215, which is a disk-shaped shell from which helicopter-type blades are pulled out for take-off and landing, turning the wing-disk into a rotary rotor jet gases from wing nozzles or from the propeller shaft. The system for cleaning the blades into the wing is a drum for winding cables located on the axis of rotation of the wing-disk, to which blades are attached by these cables, which are extended by inertial forces into the air flow through the dies in the wing and turn the wing into a main rotor, and retract into the wing after take-off or landing of the aircraft due to braking of the drum and winding the cables on it with a rotating wing, which in this case has an angular velocity greater than that of the drum.

The main disadvantage of the system for cleaning and releasing the blades of this wing is their fastening with the help of cables that are capable of perceiving only tension, do not have damping either in the vertical and especially in the horizontal plane. In addition, the cable in the areas of its attachment to the drum and to the blade has curvature limitations, while it must withstand multiple loads from the inertia of the blade during take-off and landing at high wing revolutions, creating transonic speeds at the ends of the blades, although it can serve as a tool cleaning and release of the blades occurring at low speeds of the rotor.

Judging by the drawing of the prototype, the axis of the “cable-blade” has a kink in the die, due to the fact that the axis of the blades in helicopter mode move along the conical surface. This kink creates a large lateral load, loading the wing almost on its perimeter. To create the necessary strength of the wing, it is necessary to increase its mass, which, in turn, increases the centrifugal forces that also load the wing.

And finally, the small wing disc wing has low quality in subsonic flight, on which fuel consumption directly depends.

The present invention is a method of converting a disc wing into a rotor, free from these disadvantages of the prototype. For this, in addition to the drum onto which the cable is folded during the cleaning of the blades, a rotor hub is installed on the wing axis with torsion beams connected to it connecting the hub with the dies. At the final stage of extension from the wing, the blades are connected with the dies with their butt portion, after which the torsion-blade system is a single rod that perceives the tensile load of the blade. In this case, the flywheel movements of the blade cause bending of the two-bearing torsion, control of the angle of attack - its twisting. To make these movements possible, the spinnerets are connected to the wing by spherical elastomeric bearings having a center of rotation in the center of the spinneret and capable of transmitting the lateral load of the blade to the wing. To limit the swing of the blade, the thrust control angle of attack is offset from the plane of the die by a distance h (drawing).

In subsonic flight, when the rotation is stopped, wing consoles extend from the spars attached to the shaft and the wing support to turn the disk into a wing of medium or even large elongation. The consoles extend from the wing through the supports, with which you can control the angle of attack of both consoles symmetrically to change their lifting force in order to reduce the angle of attack and drag of the disk, or inverse symmetrically to control the roll. The location of the wing consoles directly in the disk is due to the fact that after extension they are in an undisturbed flow, forming a single wing, and the weighting of the disk associated with this increases its kinetic energy and improves the characteristics of the rotor in autorotation mode.

It is proposed that the rotor hub be positioned below the diametrical plane of the wing-disk so that the taper angle described by the torsion bars is equal to the taper angle of the surface swept by the blades during take-off and landing overload, so that in these modes the constant component of the transverse load in the die is perceived by tensile torsion.

If the disk wing is designed for flight or maneuver in the main rotor mode with overloads greater than take-off, the position of the main rotor hub can be adjusted in height.

The torsion bar of the blade attachment can be made telescopically entering the blade when cleaning it into the disk.

The blades can also serve as wing consoles if they have the corresponding bending stiffness and lenticular profile with the same flow characteristics from the bow and tail.

The drawing shows one of the variants of the invention with blades partially removed in the disk.

Here:

1 - wing disc;

2 - blade;

3 - drum;

4 - cable;

5 - die;

6 - elastomeric bearing;

7 - a shaft of the screw (wing);

8 - rotor sleeve;

9 - torsion bar;

10 - a brake;

11 - control rod;

12 - spar;

13 - wing support;

14 - carriage;

15 - wing console.

Claims (6)

1. A method of converting a disk wing, which consists in extending by inertial forces through the dies on the perimeter of the rotating disk wing of the blades attached by cables to the drum located on the axis of the wing, and in cleaning them into the cavity of the disk when braking the drum and screwing the cables on it with a rotating disk wing, characterized in that the blades in the final stage of extension from the wing with their butt part are rigidly fixed with torsions connecting the rotor hub with dies mounted in the wing on a spherical x elastomeric bearings generating horizontal and vertical joints blades to control their angles of attack and limiting the strokes and in horizontal flight, when the blades are removed, and the disk rotation is stopped therefrom nominated wing console. 2. The method according to claim 1, characterized in that the rotor hub is located below the diametrical plane of the disk wing so that the taper angle described by the torsion bars is equal to the taper angle of the surface swept by the blades during overload take-off and landing, thereby reducing the constant transverse force the action of the blades on the wing to almost zero. 3. The method according to claim 1 or 2, characterized in that, if necessary, the flight on the main rotor with large overloads, the position of the main rotor hub in height is adjustable. 4. The method according to claim 1, or 2, or 3, characterized in that the torsion bar when cleaning the blade telescopically enters it. 5. The method according to claim 1, characterized in that as the wing console can serve and the blade, which have a lenticular profile with the same nose and tail edges and the corresponding bending stiffness. 6. The method according to claim 1 or 5, characterized in that the wing consoles are controlled in angle of attack to change the lift of the aircraft and perform the function of ailerons.