RU2842299C1 - Guided missile steering drive actuating mechanism based on cycloidal gear - Google Patents

Abstract

FIELD: astronautics.

SUBSTANCE: invention relates to the field of rocketry, in particular to the guided missiles instrument compartments steering drives, and can be used for creation of actuators for rotation of rudders of aerodynamic surfaces of steering drive of missile or aircraft based on cycloidal gear, operating under action of high aerodynamic loads exerted on them. Controlled missile steering drive aerodynamic surface rudders rotation actuator incorporates motor and reduction gear. Made in the form of an electric machine, separately installed in the steering drive by one common assembly unit, which includes a two-stage reduction gear with a main high-speed cycloidal gear having a gear ratio of 4 to 70, and an auxiliary low-speed screw involute gear having a gear ratio of 1 to 1.5, an electric motor with a flange part and an output shaft, which are the component parts of the cycloidal gear. At that, flange part serves simultaneously as housing and toothed rim of cycloidal gear, and output shaft acts as eccentric shaft.

EFFECT: invention allows to create small-sized high-loaded and high-speed electric machines with cycloidal reduction gear for missiles steering drives, as well as other aircraft with aerodynamic surfaces control surfaces deflection angle of up to 30 degrees; and also, the steering drive design simplification and increase in the rocket manoeuvrability characteristics.

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Description

The invention relates to the field of rocket engineering, in particular to steering drives for instrument compartments of guided missiles, and can be used in the creation of actuators for rotating the rudders of the aerodynamic surfaces of the steering drive of a missile or aircraft based on a cycloidal transmission, functioning under the action of high aerodynamic loads exerted on them.

A steering drive device for controlling aerodynamic surfaces is known (patent RU 121794 U1, B64C 13/34, priority from 19.06.2012). It consists of an electric motor, a multi-stage cylindrical gearbox and a ball screw transmission.

The advantage of the device under consideration is its high load capacity, rigidity and high positioning accuracy of the output link.

The disadvantages are the extremely complex design of the steering drive due to the large number of intermediate elements required to transmit torque from the electric motor to the steering wheel of the aerodynamic surfaces, as a result of which the device has a reduced efficiency, the need for precise processing of the ball screw transmission, which limits the scope of possible application of this device.

The closest to the proposed invention is the steering actuator (patent RU 2265553 C1, B64C 13/28, priority from 29.03.2004). The mechanism includes an electric motor and a three-stage gearbox consisting of a bevel gear and two wave gears.

The main advantages of this mechanism include control of the aerodynamic surfaces without using a ball screw transmission, as in the previously considered device. Also, the possibility of creating large gear ratios.

The main disadvantages of the mechanism are the presence of difficult-to-manufacture mating surfaces and parts of the gearbox wave transmissions, which have many spherical shapes, the lack of the ability to adjust the bevel gear, low rigidity of the output shaft due to the cantilever seal, limited load capacity of the bevel gear, and large overall dimensions of the mechanism due to the existing bevel gear.

The task, which the invention is aimed at solving, is the development of a small-sized, highly loaded and high-speed electric machine with a cycloidal gearbox for use as an actuator for the steering drives of rockets and other aircraft with an angle of deflection of the aerodynamic surface rudders of up to 30 degrees.

An additional technical result is the simplification of the design of the steering drive and the increase in the maneuverability of the rocket or aircraft due to the high load capacity of the cycloidal transmission.

In order to achieve the specified result, in the proposed invention, the actuator mechanism for rotating the rudder of the aerodynamic surfaces of the steering drive of a guided missile is made in the form of an electric machine separately installed in the steering drive by an assembly unit, which includes a two-stage reducer with a main high-speed cycloidal and an auxiliary low-speed helical involute gear, while it includes an electric motor, the flange part and its output shaft of which are integral parts of the cycloidal gear, where the flange part serves as the housing of the cycloidal gear, and the output shaft performs the function of an eccentric shaft. In turn, the housing of the low-speed gear of the helical involute gear is fastened to the flange part with screws, which, when installing the electric machine in the housing of the steering drive of the product, is brought into engagement with the mating toothed sector of the gear of the helical involute gear, which is simultaneously the axis of rotation of the aerodynamic surfaces of the steering drive of the rudder. For ease of engagement, the housing with the low-speed pinion of the helical involute transmission has a special cutout, and the shape of the cutout can be arbitrary, ensuring ease of assembly. In turn, the toothed sector can be made in the form of a solid toothed wheel. The main gear ratio is achieved by means of a cycloidal transmission and can be from 4 to 70, depending on the geometric characteristics of the engagement. An additional gear ratio is selected by the helical involute transmission depending on the required optimal overall dimensions in the range from 1 to 1.5. In this case, the value of the rotation angle of the low-speed pinion of the helical involute transmission is not limited in any way and can be up to 360 degrees, which simplifies the assembly of the steering gear as a whole. The essence of the invention is explained by drawings.

Fig. 1 shows a general view of the steering drive of a guided missile, indicating in its design an electric machine with a cycloidal gearbox, as well as a rudder with aerodynamic surfaces (plates).

Fig. 2 shows the general layout of the electric machine, where it can be seen how the fingers of the parallel crank mechanism of the cycloidal satellite 4, necessary for transmitting torque, are connected through holes with the low-speed gear of the helical involute transmission 6, and section A-A is also shown.

Fig. 3 shows a section A-A, which shows that the pins 3 are placed in special recesses of the cycloidal transmission housing 2, while the cycloidal satellite 4 is offset by the eccentric shaft of the electric motor 5.

Fig. 4 shows a simplified diagram of the engagement of the low-speed gear of the helical involute transmission of an electric machine with the toothed sector of the steering axis of the aerodynamic surfaces of the steering drive.

To describe the drawings Fig. 2 and Fig. 3, the following designations are used:

1 - electric motor;

2 - cycloidal transmission housing;

3 - shanks (rollers);

4 - cycloidal satellite;

5 - eccentric shaft of the electric motor;

6 - low-speed gear of helical involute transmission;

7 - screw that locks against axial movements;

8 - radial thrust bearings;

9 - body;

10 - protective cover;

11 - screws;

The principle of operation is as follows. The eccentric shaft of the electric motor 5, rotating, causes a plane-parallel planetary motion of the cycloidal satellite 4. The cycloidal satellite 4, rolling along the pins 3 located in the housing of the cycloidal part 2, transmits, with the help of the existing fingers of the parallel crank mechanism made as a single part with the satellite, the torque to the low-speed gear of the helical involute transmission 6 through the holes in it. It, in turn, tightened from axial movements by the screw 7, rotating in radial thrust bearings 8 located in the housing 9 transmits the torque to the toothed sector of the mating gear of the helical involute transmission of the rudder of the aerodynamic surfaces of the steering gear. The housing 9 is fastened to the housing of the cycloidal part 2 with screws 11 and is closed with a protective cover 10, and the cycloidal satellite 4 can be fastened to the eccentric shaft of the electric motor 5 from axial movements in any available way that ensures its reliable fixation.

Thus, the proposed invention can be implemented by creating actuator mechanisms consisting of one small-sized, highly loaded and high-speed electric machine with a cycloidal gearbox for controlling the rotation of the rudders of the aerodynamic surfaces of the steering drives of rockets and other aircraft.

Claims (1)

A mechanism for executing the rotation of the rudders of the aerodynamic surfaces of the steering drive of a guided missile, having an electric motor and a gearbox, characterized in that it is made in the form of an electric machine, separately installed in the steering drive with one common assembly unit, including a two-stage gearbox with a main high-speed cycloidal transmission, having a gear ratio from 4 to 70, and an auxiliary low-speed screw involute transmission, having a gear ratio from 1 to 1.5, an electric motor with a flange part and an output shaft, which are integral parts of the cycloidal transmission, where the flange part serves simultaneously as a housing and a toothed ring of the cycloidal transmission, and the output shaft performs the function of an eccentric shaft.

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