CN111559493B

CN111559493B - Brake control device for helicopter undercarriage wheel

Info

Publication number: CN111559493B
Application number: CN202010337493.3A
Authority: CN
Inventors: 彼得罗夫·伊万·谢尔盖耶维奇; 特列马斯金·夫拉季米尔·维克托罗维奇; 西特尼科夫·帕韦尔·伊戈列维奇; 布托瓦·安娜·安德列夫娜
Original assignee: Milkamov National Helicopter Center Inc
Current assignee: Milkamov National Helicopter Center Inc
Priority date: 2019-04-26
Filing date: 2020-04-26
Publication date: 2021-10-22
Anticipated expiration: 2040-04-26
Also published as: RU2710993C1; CN111559493A

Abstract

The invention belongs to the aviation technology and relates to a brake control device for a wheel of a helicopter undercarriage. Comprising two control buttons (2,2') and two operating levers (1,1') connected by means of a cable guide (3,4) connected to the wheels of the undercarriage. The cable guide (3,4) is equipped with a tensioning device (15) consisting of a body (16) closed by a plug (17), into which a sleeve (18) with a piston (19) and a cable (5) with a fixed joint (20) are inserted. The cable guide (3,4) is further provided with a reinforcement device (25) comprising a main body (31) of the relief cylinder, in which a rod (33) is arranged, separated from the main body (31) by a spring (34). The cable guide (3,4) furthermore comprises a unit (8) which is fixed to the cockpit plate and which consists of an inner core (10) and a body (9), through which the cable (5) passes and which is fixed by stops on both sides of the body (9).

Description

Brake control device for helicopter undercarriage wheel

Technical Field

The invention belongs to the aviation technology, and particularly relates to a hydraulic brake device for performing double independent control on the wheel brake of a helicopter undercarriage.

Background

Brake devices are known (GB559817 patent, published 3/7.1944B 64C25/48 for a dual control trainer, student and trainer tiller levers pivotally connected at the ends, the teacher joystick being longer and suspended on the fuselage using a dowel pin, the lever of the brake device being equipped with a brake pad and a ratchet device and a panic stop connected to the teacher joystick.

A known hydraulic aircraft brake system (RU 2092389, published 10/1997, B64C 13/36) comprises a control element and is connected via an input port to a hydraulic accumulator of a hydraulic source and via an output port to a respective brake cylinder of a left or right main landing gear leg. The control device of the brake system is made in the form of a handle with hinged push rods on both sides of its plane of symmetry. Each articulated push rod interacts with a respective control element of the pressure reducing valve. The No. 4 lever is equipped with a locking device for parking brake in the form of a spring hook, placing the control lever in a position where the pressure relief valve fully compresses the lever.

The known Mi-8 helicopter brake system (technical description, Mi-8 helicopter 1970, page 102-. The control rod is connected with the rocker through a steel cable in the rocker arm sheath, and when the control rod is pressed, a push rod of the pneumatic control unit is moved, so that pressure change in the wheel brake cylinder is caused, and the brake block is expanded.

The existing devices allow only one pilot to control the braking process, reducing flight safety in the event of an emergency. In response to the technical problems of the prior art, the present application provides a dual control wheel brake assembly that allows control braking to be transferred to a second pilot.

Disclosure of Invention

The invention has the technical effects that:

-implementing dual control of helicopter wheel braking according to aviation regulations;

the operating fluid pressure of the brake cylinders is controlled by using control buttons on the left and right station levers in the cockpit, while the activation of any control button does not affect the control of the second button.

The above technical result is achieved, according to the claimed invention, in a control device for braking the wheels of a helicopter landing gear, comprising two levers with control buttons, connected to the wheels of the chassis by means of a cable guide provided with a tensioning device consisting of a body closed by a plug, in which a piston and a sleeve of a cable of a fixed joint are inserted. The cable guide is also provided with a reinforcing device comprising a relief cylinder, the piston rod being separated from the housing by a spring, and a unit consisting of a main body and a core and fixed to the cockpit plate, the cable being fixed to the body on the two-side restraint by means of the core.

The cable guider is provided with a tension device, the pressure of working fluid supplied by the brake cylinder is controlled by control buttons on left and right station operating levers in the cockpit, and at the moment, the control of the second button cannot be influenced by any triggered control button, so that the double control of the helicopter wheel brake is realized according to aviation rules.

The unit fixed on the cockpit plate is used and comprises a main body and a rope core, and a steel rope penetrates through the unit fixed on the cockpit plate and is fixed in limiters at two sides of the main body, so that the tightness and the reliability of the steel rope are realized.

Drawings

The brake control device for the wheels of the helicopter landing gear is shown as follows:

FIG. 1 is a front view of a landing gear wheel braking device;

figure 2 is a bottom view of the landing gear wheel braking device;

FIG. 3 is a wire rope through cockpit panel seal design;

FIG. 4 is a tensioner design;

fig. 5 is a reinforcement device design.

Detailed Description

The braking control device for the wheels of a helicopter landing gear comprises two activated control buttons 2,2 'and two joysticks 1,1' (fig. 1) for the pilot and copilot of the aircraft, respectively. The control buttons 2,2' are connected to the

cable guides

3, 4. The cable guides (the left cable guide 3 and the right cable guide 4) are built in with a cable 5 that moves relative to the body, has a joint at the end and transmits the stress from the activation of the control buttons 2,2' to the control lever 6 (fig. 2). The cable 5 is moved along a guide rail, which is a cable sheath fixed to the fuselage structure by means of a stop 7, the stop 7 adjusting the total length of the sheath to allow the gap selection of the

cable guides

3, 4.

The

wire rope guides

3,4 comprise units 8 mounted on the cabin floor to ensure tightness and reliability of the wire rope passing through the floor.

The unit 8 (fig. 3) fixed to the cockpit plate comprises a body 9 fixed to the cockpit floor, inside which a rope core 10 is designed, through which the steel cable 5 is operated using lubricating oil, the cable being pressed from both sides by the body 11 and the cover 12. The securing of the

cable guide

3 or 4 is provided by stops 13 secured to the sides of the body 9 and tightened by screws 14 as the cable passes through the body 9. .

The tension device 15 is arranged in a joint in the wire rope 5.

The tensioning device 15 (fig. 4) is a tensioning cylinder consisting of a body 16 closed by a plug 17, inside which a sleeve 18 is inserted, inside which a piston 19 and the cable 5 fixed by a joint 20 are inserted. A spring 21 is mounted between the piston 19 and the plug 17, the cable 5 passing within the spring 21.

The

cable guides

3,4 are connected to a control rod 6 mounted on a bracket 22, this control rod 6 driving a push rod 23, the push rod 23 being an integral part of a pressure reducing valve 24 which reduces the pressure by reducing the amount of movement of the push rod 23, creating a pressure in the conduit of a hydraulic line (not shown) connected to the wheels of the main landing gear.

The control lever 6 (fig. 2) is used to operate the interaction between the left wire guide 3, the right wire guide 4, the pressure relief valve 24 and the reinforcement device 25. The control rod 6 is provided with a pulley 26 through which the push rod 23 is driven. The adjusting bolt 27 is used to adjust the maximum stroke of the push rod 23.

The bracket 22 fixes the pressure reducing valve 24 and the reinforcing device 25 through bolts 28; the control rod 6 is fixed by means of a bolt 29, and the reinforcement means 25 and the control rod 6 are fixed by means of a bolt 30.

The reinforcement means 25 (fig. 5) is a relief cylinder for unloading the force on the control button 2,2' and is mounted on the bracket 22 of the relief valve 24. The relief cylinder consists of a body 31 connected to the atmosphere, and a plug 32 is mounted in the body 33. The tension of the relief cylinder is ensured due to the stress of the spring 34 mounted between the rod 33 and the body 31.

The device works as follows.

In flight, without the control buttons 2,2 'on the levers 1,1' being pressed, the reinforcing means 25 ensure the tension of the

cable guides

3,4 by the compression of the spring 34 and keep the control buttons in a released state. At this time, the springs 21 of the tension device 15, the left wire guide 3 and the right wire guide 4 are maintained in a maximum compression state, and the piston 19 presses the stopper 17.

In the braking mode, when the control button 2 on the left joystick 1 is pressed, the left wire guide 3 moves, pulling the control rod 6, at which point the pulley 26 pressurizes the valve push rod 23 and the hydraulic system begins to supply pressure to the brake cylinders (not shown) of the landing gear wheels. The reinforcement means 25 passing through the a-axis by rotating around the bolt 28 enhances the impact on the valve push rod 23 due to the spring force of the spring 34. In this case, the control lever 6 acts on the right cable guide 4 to release it, and the spring 21 of the tension device 15 releases to secure the tension of the right cable guide 4 and the right control knob 2' in place. A completely similar operation occurs when the control buttons on the right joystick 1' are used.

Thus when the left joystick 1 is used and the control knob 2 of the brake system is pressed, the control knob 2 'on the right joystick 1' remains stationary because the tension device 15 is designed to ensure tension in the right cable guide 4 and a completely similar operation occurs when the control knob 2 'of the brake system on the right joystick 1' is pressed.

Claims

1. A braking control device for the wheels of the landing gear of a helicopter, comprising two control buttons, the control buttons being connected to a pressure-reducing valve of the hydraulic system of the wheels of the landing gear by means of a cable guide, characterized in that the cable guide is provided with a tension device consisting of a body closed by a plug, in which a sleeve with a piston and a cable with a fixed joint and surrounded by a spring is inserted; the cable guide is provided with a reinforcing device, which comprises a main body with a rod, and the main body is isolated from the main body through a spring and fixed by a plug; the cable guide also comprises a unit fixed on the cockpit plate, the unit fixed on the cockpit plate consists of a main body and an inner rope core, the cable fixed by the main body and the cover passes through the rope core, and the rigid fastening of the cable is ensured by a stop piece at two sides of the main body.