RU2371351C2 - Method to control rotor of rotary wing flying vehicle and device to this end - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Proposed method consists in varying rotor blade angle (5) by servo-flaps connected with swashplate ropes (9) tensioned by centrifugal force. Cyclic control is effected deflecting the axis from position parallel to that of rotor shaft. Note here that servo-flaps are deflected by ropes (9), while general control is performed by turning axle threaded into hinge when it moves along shaft axle. Note that all servo-flaps are deflected simultaneously on all blades (5).by cables (9) and rocking chairs, fixed on blades. Rotor control device comprises swashplate coupled with servo-flaps via ropes (9) and bell cranks fitted on blades. Aforesaid swashplate consists of threaded joint between axle (3) and hinge (2). The latter without opportunity of rotation inside shaft (1) screws, while axle is arranged inside aforesaid hinge in threaded joint. Note here that thread angle is sufficient for axle to turn at preset axial forces. Upper part of the axle is coupled with servo-flaps via ropes and bell cranks, while its lower part is linked up, via bearings (18), with control tie-rods (13) with spherical hinges (14).

EFFECT: higher safety.

2 cl, 3 dwg

Description

The invention relates to aviation, namely to control the rotor of a rotorcraft.

A known method of controlling the rotor implemented on helicopters of the Design Bureau of Bratukhin I.P. Omega I, Omega II, B-4, B-11 and on helicopters of the Design Bureau A. Yakovleva YAK-100 (Isakson A.N., "Soviet Helicopter Engineering", Mechanical Engineering, 1981, p. 162, 251), which consists in changing the angle of installation of the blades using a swashplate type "spider". When controlling the cyclic pitch of the rotor blade, the axis of the swash plate deviates from the vertical position under the action of the control rods, while the traction of the blades move, changing the angle of installation of the blades, while controlling the common step, the axis moves along the axis of the rotor shaft, changing the angle of installation of the blades through the rods.

The method is implemented in the design used on the helicopters of the Design Bureau of Bratukhin I.P. Omega I, Omega II, B-4, B-11 and in the helicopter of the Design Bureau A. Yakovleva YAK-100 (Isakson A.N., “Soviet Helicopter Engineering”, Mechanical Engineering 1981, pp. 162, 251).

The control design consists of control rods and a swash plate, which is made in the form of a shaft moving inside the shaft of the main gearbox, and has an axis swinging inside the shaft on the ball joint of the head located on the upper end of the axis and connected by three levers with leads of the rotor blades. The shaft of the swashplate through an irreversible helical mechanism is connected by a system of rods and rocking chairs with a common pitch lever.

The disadvantages of this method are: large efforts in the control wiring, axle loads, which reduces the flight safety of the aircraft; the need to use rods and rockers connecting the axis with the blades, this leads to a small rigidity of the control wiring, increasing the likelihood of oscillation of the blades, and reduces flight safety.

The disadvantages of this control design are: large loads on the axis and control wiring, this leads to a small stiffness of the axis on bending and a small stiffness of the control wiring in general, the large size and weight of the rods and rockers of the control system; increases the possibility of oscillations of the blades, which reduces flight safety, the features of this design limit the scope of its application on aircraft of large masses, the great effort required to control the rotor, leading to the need to install a heavy hydraulic system.

A known rotor control method implemented on a KAMAN helicopter (Tsaga review, "Design and experimental studies of high-speed helicopters and rotary-wing vehicles", No. 296 for 1969), which consists in changing the blade installation angle by deflecting servo-flaps controlled by the skew automatic dish type. During cyclic control, the ring of the swashplate is deviated from the position perpendicular to the rotor shaft, and the servo-flaps are deflected through the rods and rockers, when controlling the general pitch, the ring of the swashplate is moved along the axis of the rotor shaft, by rejecting the servo-flaps through the rods, the moment arising from the deviation of the servo-flaps, rotates the blades relative to the longitudinal axis by a predetermined installation angle.

The rotor control method is implemented in the control structure installed on the KAMAN helicopter (Tsaga review, "Design and experimental studies of high-speed helicopters and rotary-wing vehicles", No. 296 for 1969).

The rotor control design consists of servo-flaps connected through rods and rockers with a swash plate, which includes: a rotating ring with rods articulated to it and a non-rotating ring with longitudinal and transverse rods articulated to it and connected by a bearing with a rotating ring .

The disadvantages of this method are: the need for a large number of rods and rockers connecting the movable ring of the swash plate with servo flaps, the need for a large number of hinges, which leads to loopholes and the possibility of oscillations in the control wiring, impairing the controllability of the rotor, thereby reducing flight safety rotorcraft.

The disadvantages of this control design are: a large number of rockers, hinges and long rods transmitting movement from the swashplate ring to the servo-flaps, which increases the mass of the control system and reduces its rigidity, which reduces the rotor controllability and flight safety.

The closest in technical essence to the proposed method of controlling the rotor is a method of controlling the rotor of the authors S. Balakirev and Pavlova V.A. Patent 2203835 B643C 11/30 according to the application 200121687 dated 08/14/2000, which consists in changing the angle of installation of the blades using servo-flaps rejected by the swash plate, while controlling the cyclic step by moving the swash ring in a plane parallel to the plane of the rotor hub , these movements are transmitted through the rolling rollers pressed to the ring by centrifugal force to the summing mechanism of the swash plate, and the common step is controlled by moving the slider along the axis of the rotor shaft, for thereby, the cyclic and general control movements are summed up on the lever and, through the cables pulled by centrifugal force, the servo-flaps are deflected, and the aerodynamic moments turn the blades around the longitudinal axes.

Closest in design to the proposed rotor control device is the rotor control device of the authors S. Balakirev and Pavlova V.A. Patent 2203835 B643C 11/30 according to the application 200121687 of 08/14/2000, consisting of a swashplate, servo-flaps and communication between them. The swash plate is made of a non-rotating ring mounted parallel to the rotor hub and pivotally mounted on the rockers of the cyclic pitch, which are mounted on the gear housing, while the non-rotating ring is movable in a plane parallel to the plane of the rotor hub, and a summing mechanism consisting of a rocking chair of the common step pivotally mounted on the rotor hub with the possibility of supporting it on the connecting rod of the common step and the summing rocker fixed on it, on which through the bearing is fixed to a roller, made with the possibility of rolling around in a non-rotating ring, and the swashplate is connected to the servo-flaps using a cable stretched by centrifugal force.

The disadvantages of this method are: the need for the use of rods and rockers, as well as a summing mechanism linking the longitudinal and lateral control, a large number of hinges leads to loopholes and the possibility of fluctuations in the control wiring, impairing the controllability of the rotor, thereby reducing the flight safety of the rotorcraft.

The disadvantages of this control design are: a large number of parts of the swashplate, which complicates the manufacture, and also reduces the reliability of the design. The use of rolling rollers due to their constant wear complicates the operation of the structure, reduces its reliability, which reduces flight safety.

The solved problem of the proposed method and device is to increase the control of the rotor, and therefore, increase the flight safety of the aircraft. Reducing the cost of manufacturing a swashplate, simplifying the design and increasing reliability.

In the method of controlling the rotor of a rotary-wing aircraft, which consists in changing the angle of installation of the blades using servo-flaps connected to the swash plate by cables pulled by centrifugal force, the cyclic step is controlled by deviating the axis from a position parallel to the axis of the rotor shaft, while cyclically deflecting through the servo-flap cables, and the common step is controlled by turning the axis in a threaded connection with a hinge when it moves along the shaft axis, while flaps on all blades at the same time.

In the rotor control device of a rotary-wing aircraft, consisting of a swashplate connected to servo-flaps with ropes and rockers mounted on the blades, the swashplate is made of a threaded connection between the axis and the hinge, and the hinge is fixed without rotation inside the screw shaft, and the axis is installed inside the hinge in a threaded connection with an angle of inclination of the thread sufficient to rotate the axis for given axial forces, while the upper part of the axis is connected to the servo-flaps through cables and rockers, replicated on the rotor blades, and the lower part of the axis through bearings is connected to control rods, spherical joints.

To clarify the essence of the invention, figure 1 shows a General view, figure 2 - rotor blade with a servo-flap, figure 3 is a top view of the rotor, where:

1 - screw shaft;

2 - spherical hinge;

3 - axis;

4 - thrust;

5 - rotor blade;

6 - horizontal hinge;

7 - servo-flap;

8 - rocking chair;

9 - a cable;

10 - thrust;

11 - a rocking chair;

12 - gear housing;

13 - thrust control;

14 - spherical hinge;

15 - a glass of the bearing;

16 - slot;

17 - hinges;

18 - the bearing.

A spherical hinge 2 is fixed inside the rotor shaft 1, from rotation inside the screw shaft the hinge is fixed by a slot 16. Inside the hinge, on the threaded connection with a large angle of inclination of the thread, axis 3 is installed, which is connected to the servo by the upper part through rod 4 and control cables 9, rocking 8 - flaps 7 located on the blades of the rotor 5. On the other hand, the axis 3 through the bearing 18 located inside the glass 15 is connected by a spherical hinge 14 with a thrust of a common pitch of the screw 13 and connected by a thrust 10 with spherical hinges 14, with a rocker 11 oraya on hinges 17 fixed to the body unit 12 and is connected with traction cyclic. The tension of the cables 9 is carried out by centrifugal force.

The device operates as follows.

The cyclic control is carried out by the deviation of the axis 3 under the action of the rods of the cyclic step 10 from a position parallel to the axis of the rotor shaft 1, while through the cables 9, stretched by centrifugal force, and a rocker 8, mounted on the blades 5, the servo-flaps 7 are deflected.

The control of the common step is carried out by turning the axis 3 in a threaded connection with the hinge, under the action of axial force from the rod of the common step 13 through the bearing 18, while the servo-flaps 7 are deflected through the ropes 9 and the rockers 8 mounted on the blades, leading to a change angle of installation of the blade 5. Slot - hinge 16 prevents rotation of the hinge inside the shaft of the rotor.

The advantage of this method is that there is no need to use additional rods and rockers connecting the swashplate with servo-flaps, this increases the rigidity and reliability of the control system, increasing the flight safety of the rotorcraft; the use of a small diameter bearing makes it possible to simplify and facilitate the swashplate; screw control with servo flaps eliminates the need for a heavy hydraulic system.

The advantage of this design of the screw control system is that a small diameter bearing is used in the swash plate, this greatly facilitates the swash plate. The design is simple to manufacture and contains a small number of parts, does not require complex settings and is easy to operate, this design can be used on aircraft models.

Claims (2)

1. The method of controlling the rotor of a rotary-wing aircraft, which consists in changing the angle of installation of the blades using servo-flaps connected to the swash plate with cables pulled by centrifugal force, characterized in that the cyclic control is carried out by deviating the axis from a position parallel to the axis of the rotor shaft, while servo-flaps cyclically deflecting through the cables, and the common pitch is controlled by turning the axis in a threaded connection with a hinge when it moves along the shaft axis, while through s at the same time reject the flaps on all blades. 2. The rotor control device of a rotary-wing aircraft, consisting of a swashplate connected with servo-wings with ropes and rockers mounted on the blades, characterized in that the swashplate is made of a threaded connection of the axis with a hinge, the hinge being fixed without rotation inside the rotor shaft, and the axis is mounted inside the hinge in a threaded connection with an angle of inclination of the thread sufficient to rotate the axis for a given axial force, while the upper part of the axis is connected to servo-flaps through and rocking ropes attached to the rotor blades and the bottom part of the axis through the bearings is connected to the control rods, spherical hinges.

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