RU2612554C1 - Multi-disc cylindrical electromechanical aircraft brake - Google Patents

Abstract

FIELD: transportation.

SUBSTANCE: multi-disc cylindrical electromechanical aircraft brake contains rotating and non-rotating brake disс

s. On the rotating and non-rotating brake discs made of a magnetic material, alternating and arranged relative to each other with the minimum working air gap, the poles are made, oriented radially in the brake discs plane. On the main landing gear axis the axial electromagnet is fixed, the poles of which are perpendicular to the brake discs plane and are arranged with the minimum air gap to the working cylinder of a magnetic material. In a plane parallel to the rotating brake disc, the position sensors of the rotating brake disc poles are located, connected by their outputs to the inputs of the control device connected by its output to the switching device input. The brake force control device output is connected to the other input of the control device.

EFFECT: increasing the reliability of multi-disc brakes and reducing the maintenance costs.

17 dwg

Description

The invention relates to multi-disc braking devices of an airplane landing gear.

A multi-disc brake of an aircraft is known, comprising a brake torque transmission device in the form of an arm including a brake lever and a brake housing made with it, on which a drive is mounted in the form of a cylinder block with pistons, a package of friction rotating and non-rotating disks, and a cylinder. To fix the cylinder block from axial displacement, an annular bead is provided on the brake housing (see RF patent No. 2143381, IPC VC 25/42, publ. 12/27/1999). The disadvantages of such a multi-disc brake include low reliability and high wear of the friction surfaces of the friction elements of the brake.

The closest analogue is the well-known invention related to the field of aerospace engineering, in particular to brake wheels with multi-disc brakes, which can be used in aircraft wheels. The aviation brake wheel contains a movable part with a disk and a rim located on a fixed axis, a multi-disc brake including a housing, a cylinder block with pistons, rotating and non-rotating brake discs made of carbon material, and a fan (see RF patent 2476350, IPC ВСС 25 / 42, F16D 55/24, publ. 02.27.2013).

The disadvantages of the analogue and the prototype multi-disc brakes include low reliability and a high degree of wear of the friction surfaces of the friction elements of the brake, brake pads or brake linings and brake discs. In addition, significant costs are spent on frequent maintenance and non-destructive testing of parts of a tribocouple disc brake, including brake linings and brake discs. In addition, the use of a cylinder block with pistons that uses a hydraulic brake system to supply hydraulic fluid pressure to the cylinder block can lead to leakage of hydraulic fluid, and, as a consequence, to its ignition.

The aim of the invention is to increase the reliability of multi-disc brakes, reduce maintenance costs and non-destructive testing of parts of disc brakes.

This goal is achieved by eliminating the friction elements of the brake actuator with brake discs in a multi-disc brake and the introduction of a movable disk lock. For this, on rotating and non-rotating brake discs, poles made of magnetic material are made, oriented radially in the plane of each brake disc and perpendicular to the axis of rotation of the disc. Rotating and non-rotating brake discs are arranged alternating with a minimum working air gap between them. Instead of a support with working cylinders, an axial electromagnet is introduced, which is fixed on the axis of the main landing gear of the aircraft. The poles of the axial electromagnet are perpendicular to the plane of the brake discs and are located with a minimum working air gap to the cylinder of magnetic material attached to the rotating brake disc. Around the circumference, in a plane parallel to the rotating brake disk, are placed the position sensors of the poles of the rotating brake disk, connected by their outputs to the inputs of the control device, connected by its output to the input of the switching device, which connects the electromagnet winding to the power source, the device output is connected to the other input of the control device brake force regulation. A disk lock device comprising a disk lock pin is attached to an axis of a wheel of a main landing gear of an aircraft adjacent to a rotating brake disk.

The accompanying drawings depict:

FIG. 1 - Multi-disc cylindrical electromechanical brake of an airplane;

FIG. 2 - Front view of the non-rotating brake disc 3;

FIG. 3 - Side view of a non-rotating brake disc 3;

FIG. 4 - View BB in FIG. 3 non-rotating brake disc;

FIG. 5 - Front view of the washer non-rotating brake disc 3;

FIG. 6 - Side view of a washer of a non-rotating brake disc 3;

FIG. 7 - Front view of a rotating brake disc 1;

FIG. 8 - Side view of a rotating brake disc 1;

FIG. 9 - Front view of the electromagnet 15;

FIG. 10 - Electromagnet 15 side view;

FIG. 11 - Front view of cylinder 16;

FIG. 12 - Side view of the cylinder 16;

FIG. 13 - View BB in FIG. 10 electromagnets 15;

FIG. 14 - View GG on. FIG. 12 cylinder 16;

FIG. 15 - View AA in FIG. 1 multi-disc cylindrical electromechanical brake of the aircraft when the poles of 2 rotating brake discs 1 outside the poles of 4 non-rotating discs 3;

FIG. 16 - View AA in FIG. 1 multi-disc cylindrical electromechanical brakes of the aircraft with the position of the poles 2 of the movable brake discs 1 between the poles 4 of the stationary brake discs 3;

FIG. 17 is an electrical diagram: sensors 6, 7, 8, and 9, a control device 10, a switching device 12, an electromagnet winding 5, a power supply 13, and a brake force control device 11.

The list of elements in the attached drawings:

1 - rotating brake disc;

2 - pole of a rotating brake disc;

3 - non-rotating brake disc;

4 - pole non-rotating brake disc;

5 - winding of an electromagnet;

6, 7, 8, 9 - position sensors of the poles of the brake disc;

10 - control device;

11 - device for regulating the braking force;

12 - switching device;

13 - power source;

14 - axis of the main landing gear of the aircraft;

15 - electromagnet;

16 - cylinder;

17 - digital signal processor (DSP);

18 - digital signal processor (DSP);

19 - element 2 OR;

20 - element 2OR;

21 - trigger RS;

22 - element 2I;

23 - a device for fixing a rotating brake disc;

24 - a pin of a clamp of a rotating brake disc;

25 - coupler of rotating brake discs 1;

26 - a washer for a rotating brake disk 1;

27 - a washer for a non-rotating brake disk 3.

A multi-disc cylindrical electromechanical brake of an airplane consists of: rotating brake discs 1 (see FIG. 1, FIG. 7 and FIG. 8) with poles 2; non-rotating brake discs 3 (see Fig. 1, Fig. 2, Fig. 3 and Fig. 4) with poles 4; axial electromagnet 15 (see Fig. 1, Fig. 9, Fig. 10 and Fig. 13) with poles perpendicular to the plane of the cylinder 16 (see Fig. 1, Fig. 11, Fig. 12 and Fig. 14) and with the minimum working air gap to the cylinder 16. Rotating brake discs 1 and non-rotating brake discs 3 are alternating with a minimum working air gap between them (see Fig. 1). In FIG. 5 and FIG. 6 is a view of washers 27 through which non-rotating brake discs 3 are placed on the axis 14 of the main landing gear of the aircraft. FIG. 1 shows the fastening through washers 26 with a coupler 25 of rotating brake discs 1. FIG. 15 is a view of a multi-disc cylindrical electromechanical brake of an airplane when the poles 2 of the rotating brake discs 1 are positioned outside the poles of 4 non-rotating brake discs 3.

In FIG. 16 is a view of a multi-disc cylindrical electromechanical brake of an aircraft when the poles 2 of the rotating brake discs 1 between the poles of 4 non-rotating brake discs 3 are positioned, which is the initial position for fixing the rotating brake disc 1. In the case when the winding of the electromagnet 5 through the switching device 12 is connected to a power source 13 (see Fig. 17), the magnetic field generated by the winding of the electromagnet 5 closes through the pole of the electromagnet 15, through the working air gap, cylinder 16, the pole 2 rotates Xia brake disc 1, the working air gap, the pole 4 non-rotating brake disc 3, the main axis of the landing gear of the aircraft 14 and the other pole of the electromagnet 5. In this way the magnetic field creates a force holding the rotating brake disc 1. FIG. 17 shows an electric diagram of a multi-disc cylindrical electromechanical brake of an airplane: sensors 6, 7, 8, and 9, a control device 10, a switching device 12, an electromagnet winding 5, a power supply 13, and a brake force control device 11.

A multi-disc cylindrical electromechanical brake operates as follows. During landing, when landing, the aircraft wheel starts to rotate with the rotating brake discs 1 mounted on it. At the same time, the control device 10 and the switching device 12 (see Fig. 17) remain constantly on. The locking device 23 does not fix the pin 24 of the rotating brake disc 1.

During the rotation of the rotating brake disk 1 clockwise (see Fig. 15), its poles 2 are periodically placed opposite the sensors 6, 7, 8 and 9 of the position of the poles 2 of the rotating brake disk 1.

At the moment of position of the pole 2 of the rotating brake disc 1 opposite the sensor 6, an electric signal of a positive level corresponding to a logical unit appears at its output. This signal from the output of the sensor 6 is fed to the input X1 of the digital signal processor 17. Then, pole 2, continuing its movement, occupies the position opposite the sensor 7, as a result of which a positive level electric signal corresponding to a logical unit appears at its output. This signal is fed to the input X2 of the digital signal processor 17. According to the algorithm of the digital signal processor 17, if at the beginning the signal of the logical unit appears at its input X1, and then the signal of the logical unit appears at its input X2, then after the transition of both signals to the voltage level is close to zero, which corresponds to a logical zero at these inputs of the signal processor 17, a rectangular electric signal of positive polarity corresponding to the logical unit is formed at its output V1 Nice. This signal is input to the element 19, which performs the logical function 2OR. From the output of element 19, a signal of a positive level corresponding to a logical unit is fed to input S of trigger 21, which performs the logical function of trigger RS. In this case, the trigger 21 goes into a state in which at its output Q appears an electrical signal of a positive level corresponding to a logical unit. This signal is input to the element 22, which performs the logical function 2I. If it is necessary to turn on the braking mode from the output of the brake force control device 11 (see Fig. 17), a frequency-modulated or pulse-width modulated electrical signal of positive polarity is supplied to the other input of element 22 of control device 10. In this case, from the output of the element 22 to the input of the switching device 12 receives a pulse-width modulated electrical signal of positive polarity. As a result, the switching device 12 connects one end of the winding of the electromagnet 5 to the power supply 13, the other output of which is connected directly to the other end of the winding of the electromagnet 5. At this time (see Fig. 16), the poles 2 of the rotating brake disk 1 occupy a position opposite the poles 4 of non-rotating 3 discs with a minimum working air gap. The magnetic field generated by the winding of the electromagnet 5 passes through the core of the electromagnet 15 through its pole, through the working air gap, through the cylinder 16, the pole 2 of the rotating brake disc 1, through the working air gap, the pole 4 of the non-rotating brake disc 3, the axis of the main landing gear of the aircraft 14 and closes on the core of the electromagnet 15 through its other pole. Thus, the magnetic field holds the rotating brake discs 1, transmitting the braking force to the aircraft wheel. As a result of the rotation of the aircraft wheel further, overcoming the brake impulse created by the magnetic field, the rotating brake discs 1 continue to rotate and their poles 2 begin to exit from under the poles 4 of the non-rotating brake discs 3. In this case, the pole 2 of the rotating brake disc 1 initially occupies a position opposite to the sensor 8 at the output of which appears an electrical signal of a positive level corresponding to a logical unit. This signal is fed to the input X2 of the digital signal processor 18. Then, the pole 2 of the rotating brake disk 1, continuing its movement, occupies the position and opposite the sensor 9, the output of which appears an electrical signal of a positive level corresponding to a logical unit. This signal is fed to the input X1 of the digital signal processor 18. According to the algorithm of the digital signal processor 18, if at first a signal of a positive level corresponding to a logical unit appears at its input X2, and then a signal of a positive level corresponding to a logical unit at an input X1, then in the future, after the transition of both signals to a voltage level close to zero, which corresponds to a logical zero at these inputs of the signal processor 18, a rectangular electric is formed at its output V2 Igna positive polarity corresponding to the logical unit. This signal is input to an element 20 that performs a logical function 2OR. From the output of element 20, a signal of a positive level corresponding to a logical unit is fed to input R of trigger 21, which performs the logical function of trigger RS. In this case, the trigger 21 goes into a state in which at its output Q a signal of a positive voltage level corresponding to a logical unit passes to a voltage level close to zero, which corresponds to a logical zero. This logical zero signal is fed to the input of the element 22, which performs the logical function 2I. As a result, the output of the element 22 at the input of the switching device 12 no longer receives a pulse-frequency modulated or pulse-width modulated electric signal of a positive voltage level from the brake force control device 11. Therefore, the switching device 12 disconnects the winding 5 from the power source 13. When moving the poles 2 of the rotating brake disk 1 again opposite the poles 4 of the non-rotating brake disk 3, the cycle of operation of the braking process is repeated.

A frequency-modulated or pulse-width modulated electric signal from the output of the brake force control device 11 controls the average value of the voltage across the load by changing the duty cycle of the pulses controlling the switching device 12 for regulating the braking force acting on the aircraft wheel.

This mode continues until, if it is necessary to turn off the braking mode from the output of the device 11 (see Fig. 17), the supply of an electric signal of positive polarity stops, which is fed to the other input of the element 22 of the control device 10. In this case, from the output of the element 22 the input of the switching device 12 will no longer receive an electric signal of positive polarity and braking will stop, since the coil 5 will no longer be connected to a power source 13.

When the rotation of the aircraft wheel and the rotating brake discs 1 counterclockwise (see Fig. 15), a multi-disc cylindrical electromechanical brake of the aircraft operates as follows. During the rotation of the rotating brake disc 1 (see Fig. 15) counterclockwise, its pole 2 initially occupies a position opposite the sensor 9, as a result of which a positive level electric signal corresponding to a logical unit appears at its output. This signal from the output of the sensor 9 is fed to the input X1 of the digital signal processor 18. Then, the pole 2 of the rotating brake disc 1 takes a position opposite the sensor 8, as a result of which a positive level electric signal corresponding to a logical unit appears at its output. This signal is fed to the input X2 of the digital signal processor 18. According to the algorithm of the digital signal processor 18, if at the beginning the signal of the logical unit appears at its input X1, and then the signal of the logical unit appears at its input X2, then after the transition of both signals to the voltage level is close to zero, which corresponds to a logical zero at these inputs of the signal processor 18, a rectangular electric signal of positive polarity corresponding to the logical unit is formed at its output V1 Nice. This signal is input to the element 19, which performs the logical function 2OR. From the output of element 19, a signal of a positive level corresponding to a logical unit is fed to input S of trigger 21, which performs the logical function of trigger RS. In this case, the trigger 21 goes into a state in which at its output Q appears an electrical signal of a positive level corresponding to a logical unit. This signal is input to the element 22, which performs the logical function 2I. If it is necessary to turn on the braking mode from the output of the brake force control device 11 (see Fig. 17), a pulse-frequency modulated or pulse-width modulated electric signal of positive polarity corresponding to a logical unit is supplied to the other input of element 22 of control device 10. V in this case, the output of the element 22 to the input of the switching device 12 receives an electrical signal of positive polarity. The switching device 12 connects the winding of the electromagnet 5 to the power source 13. At this time, the poles 2 of the rotating brake discs 1 are opposite the poles 4 of the non-rotating brake discs 3. The magnetic field created by the winding of the electromagnet 5 passes through the core of the electromagnet 15 through its poles, through the working air clearance, through cylinder 16, poles 2 of rotating brake discs 1, through the working air gap, poles 4 of non-rotating brake discs 3, the axis of the main landing gear of the aircraft 14 and closes with The core of the electromagnet 15 through its other pole. Thus, the magnetic field holds the rotating brake disc 1, which transfers the braking force to the aircraft wheel. As a result of the movement of the aircraft’s wheel further, overcoming the brake impulse created by the magnetic field, the rotating brake disk 1 continues to rotate and its poles 2 begin to exit from under the poles 4 of the non-rotating brake disk 3. In this case, the pole 2 initially occupies a position opposite to the sensor 7, at the output of which , an electrical signal of a positive level corresponding to a logical unit appears. This signal is fed to the input X2 of the digital signal processor 17. Then, pole 2 occupies a position opposite the sensor 6, at the output of which an electrical signal of a positive level corresponding to a logical unit appears. This signal is fed to the input X1 of the digital signal processor 17. According to the algorithm of the digital signal processor 17, if at first a signal of a positive level corresponding to a logical unit appears at its input X2, and then a signal of a positive level corresponding to a logical unit at an input X1, then in the future, after the transition of both signals to a voltage level close to zero, which corresponds to a logical zero, a rectangular electric one appears on its inputs V2 at its output V2 ignal positive polarity corresponding to a logical unit. This signal is input to an element 20 that performs a logical function 2OR. From the output of element 20, a signal of a positive level corresponding to a logical unit is fed to input R of trigger 21, which performs the logical function of trigger RS. In this case, the trigger 21 goes into a state in which at its output Q a signal of a positive voltage level corresponding to a logical unit passes to a voltage level close to zero, which corresponds to a logical zero. This logical zero signal is fed to the input of the element 22, which performs the logical function 2I. As a result, the pulse-width modulated electrical signal of a positive level no longer comes from the output of element 22 to the input of the switching device 12 and it disconnects the winding of the electromagnet 5 from the power supply 13. With further movement of the poles of 2 rotating brake discs 1 opposite the poles of 4 non-rotating brake discs 3 cycle the operation of the braking process is repeated. This mode continues until, if it is necessary to turn off the braking mode from the output of the brake force control device 11 (see Fig. 17), the supply of an electric signal of positive polarity, which was fed to the other input of the element 22 of the control device 10, ceases. the output of element 22 to the input of the switching device 12 will no longer receive a pulse-frequency modulated or pulse-width modulated electrical signal of positive polarity and braking will stop, since bmotka 5 will no longer be connected to a power source 13 through the switching device 12.

The device of the disk lock 23 (see Fig. 1) after the rotation of the rotating brake disk 1 is completely stopped, pushes the pin 24 into the space between the poles 2 of the rotating brake disk 1 and thereby prevents the rotation of the rotating brake disk 1. After this, the multi-plate cylindrical electromechanical brake of the aircraft can be de-energized .

Claims (1)

A multi-disc cylindrical electromechanical brake of an aircraft, comprising rotating brake discs connected by splines to the wheel housing and rotating with it, and non-rotating brake discs attached to the axis of the main landing gear, characterized in that on alternating rotational disks arranged with respect to one another with a minimum working air gap and non-rotating brake discs of magnetic material made poles oriented radially in the plane of the brake discs and perpendicular to the axis of rotation of the discs, an axial electromagnet is fixed on the axis of the main chassis support, the poles of which are perpendicular to the plane of the brake discs and are located with a minimum working air gap to the cylinder of magnetic material attached to the rotating brake disc, and pole position sensors are arranged around the circumference in a plane parallel to the rotating brake disc a rotating brake disc, connected by its outputs to the inputs of a control device, connected by its output to the input of a switching device, which It connects the winding of the electromagnet to a power source, the output of the brake force control device is connected to the other input of the control device, the disk lock device containing the disk lock pin is attached to the wheel axis of the main landing gear of the aircraft next to the rotating brake disk.

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