CN115773324A - Aircraft brake wear monitoring device - Google Patents

Abstract

An aircraft wheel brake wear monitoring device does not use devices such as ultrasonic sensors or linear displacement sensors, and can reliably remind the replacement of brake disc components when the brake disc reaches a specified amount of wear, thereby reducing manual intervention and improving the reliability of the device. The aircraft wheel brake wear monitoring device includes: a brake cylinder block, which forms a piston chamber; a gas storage chamber, in which the gas that can absorb heat and expand is stored; a piston, which is arranged in the piston chamber; a closed cavity, which A closed cavity is formed between the end of the piston on the side opposite to the side where the brake disc assembly is located and the brake cylinder seat, and communicates with the air storage chamber through a communication conduit; a probe rod, which passes through the piston along the piston chamber The two ends of the two ends; the conductive contact piece, which is arranged in the piston chamber, and can make the conductive contact piece conduct when it is in contact with the piston to send a conduction signal indicating that the brake disc assembly needs to be replaced; and the signal acquisition line, which will conduct The signal is collected to the brake control unit.

Description

Aircraft brake wear monitoring device

technical field

The invention relates to an aircraft wheel brake control technology, and more particularly relates to an aircraft wheel brake wear monitoring device.

Background technique

In the aircraft wheel brake control system, the brake disc is a key component that affects the landing safety of the aircraft. The performance and wear state of the brake disc will directly affect whether the aircraft can land normally and ensure the safety of personnel and aircraft. When the brake disc wears to a certain thickness, the brake disc assembly must be replaced. Therefore, the wear status of the brake disc is an inspection item that the ground crew must carry out after each landing of the aircraft.

However, at present, the vast majority of aircraft wheel disc brake wear indicator devices are in the form of mechanical indicators, and the wear status of the brake discs needs to be checked manually. This manual inspection increases the workload of the ground crew, and it is not easy to obtain For data, it is necessary to manually measure the thickness of the brake disc, and use a certain method for data entry to record the wear data of the brake disc, which causes inconvenience for the analysis of the route use of the brake disc.

For example, it is known that the commonly used solution on existing aircraft is to use a steel needle to pass the worn pointer rod on the piston assembly, and manually insert the pointer into the small hole, and obtain the wear condition through visual inspection, so as to judge whether it needs to be replaced Brake disc assembly.

In addition, other known solutions include detecting the gap between the carbon plate and the piston mounting plate through an ultrasonic sensor installed on the piston assembly, or using a linear displacement sensor to collect the distance between the rod connected to the carbon plate. The displacement is used as the basis for calculating the thickness of the carbon disc.

However, manually inserting the needle and checking for wear would increase the work of the ground crew. In addition, if an ultrasonic sensor is used, the working environment is relatively harsh during the braking process, which affects the detection accuracy of the ultrasonic sensor. In addition, if a tie rod and a linear displacement sensor are used, it is necessary to connect the tie rod and the static plate. Due to the high working temperature of the carbon plate, there are problems in the connection method of the tie rod and the reliability of the sensor.

That is to say, there is an urgent need for an aircraft wheel brake wear monitoring device that can reliably remind the replacement of brake pads when the brake disc reaches a specified amount of wear to address the existing manual inspection problems and sensor reliability problems. , thereby reducing manual intervention.

Contents of the invention

The present invention is made to solve many deficiencies in the existing aircraft wheel disc brake wear indicating device, and its purpose is to provide a new type of aircraft wheel brake wear monitoring device, which does not use ultrasonic sensors or linear displacement sensors to detect For devices whose precision is easily affected, no reminder will be issued when the brake disc does not reach the specified wear amount, but it can reliably remind the replacement of the brake disc assembly when the brake disc reaches the specified wear amount, reducing manual intervention and improving the reliability of the device.

In order to achieve the above object, the present invention provides an aircraft wheel brake wear monitoring device, which is used to monitor the wear of the brake disc assembly of the aircraft wheel. a piston chamber; a gas storage chamber, storing gas capable of absorbing heat and expanding in the gas storage chamber; a piston, the piston being arranged in the piston chamber; a closed cavity, the closed cavity being formed between the piston and A sealed cavity is formed between the piston end on the opposite side of the brake disc assembly and the brake cylinder seat, and communicates with the air storage chamber through a communication conduit; the probe rod is along the The piston chamber passes through the two ends of the piston; the conductive contact piece is arranged in the piston chamber and can make the conductive contact piece conductive to issue an indication when in contact with the piston The conduction signal of the brake disc assembly needs to be replaced; and the signal collection line, the signal collection line collects the conduction signal to the brake control unit.

Preferably, under normal conditions without braking, the gas pressure in the airtight cavity communicated with the air storage chamber is equal to the atmospheric pressure, so that the piston is in a balanced position. In addition, during the braking process, the brake disc assembly generates heat to heat the gas in the air storage chamber, and the gas is heated and expands to make the gas pressure in the cavity higher than the atmospheric pressure, pushing the piston through the closed cavity until The probe rod passing through both ends of the piston bears against the brake disc assembly.

More preferably, before the brake disc assembly is worn to a specified amount of wear, the piston does not contact the conductive contact piece when the probe rod bears against the brake disc assembly; , when the probe rod bears against the brake disc assembly, the piston will move to the conductive contact piece and make contact with it, so that the conductive contact piece conducts.

As an example, the air storage chamber and the piston are separately arranged on the outside of the piston chamber of the brake cylinder block on a side close to the brake disc assembly.

In addition, it is preferable that the probe rod passes through the piston and the piston chamber in an airtight manner.

In addition, the probe rod can be pressed manually until it bears against the brake disc assembly. At this time, the probe rod is preferably provided with a scale, so that it can be judged whether the brake disc assembly needs to be replaced by manually pressing the probe rod and reading the scale on the probe rod.

According to the above structure, the aircraft wheel brake wear monitoring device of the present invention can realize the automatic inspection of the wear state of the aircraft wheel brake disc. In addition, because the heat of the brake disc assembly during the braking process can be used to expand the gas to push the probe rod against the brake disc assembly, instead of testing when the aircraft is stationary, the gap between the discs is eliminated, and it is closer to the brake. The actual thickness of the disc assembly. In addition, the aircraft wheel brake wear monitoring device of the present invention realizes the automatic alarm of the wear state of the aircraft wheel brake disc. At the same time, because the gas storage chamber is separated from the piston, the gas will not be emptied, and manual inspection will not be hindered. Finally, since devices such as ultrasonic sensors and linear displacement sensors that are easily affected by detection accuracy are not used, deterioration of detection accuracy of devices such as sensors in harsh environments can be avoided.

Description of drawings

Fig. 1 is a sectional structure diagram of the aircraft wheel brake wear monitoring device of the present invention.

(Symbol Description)

100 aircraft wheel brake wear monitoring device

110 brake cylinder seat

111 piston chamber

120 gas storage chamber

130 pistons

140 closed cavity

150 connecting conduit

160 probe rod

170 conductive contact piece

180 signal acquisition line

200 brake disc assembly

Detailed ways

Hereinafter, with reference to FIG. 1 , the specific structure of the aircraft wheel brake wear monitoring device 100 of the present invention will be described in detail.

The aircraft wheel brake wear monitoring device 100 of the present invention is used to monitor the wear of the brake carbon disc (also known as "brake disc assembly 200") of the aircraft wheel, including: a brake cylinder block 110, the brake cylinder block 110 forms There is a piston chamber 111; an air storage chamber 120, and the air storage chamber 120 is formed separately from the piston on the outside of the piston chamber 111 of the brake cylinder block 110 near the brake disc assembly 200. The gas that can absorb heat and expand is stored in the gas storage chamber 120; the piston 130, the piston 130 is arranged in the piston chamber 111, and the piston of the piston 130 on the side opposite to the side where the brake disc assembly 200 is located An airtight chamber 140 is formed between the end 131 and the brake cylinder seat 110, and the airtight chamber 140 communicates with the air storage chamber 120 through a communication conduit 150; 111 passes through the two ends of the piston 130; the conductive contact piece 170, the conductive contact piece 170 is arranged in the piston chamber 111, and can make the conductive contact piece 170 conduction when it is in contact with the piston 130 to issue an indication that it needs to be replaced The conduction signal of the brake disc assembly 200; and the signal collection line 180, the signal collection line 180 collects the conduction signal to the brake control unit (not shown).

Under normal conditions without braking, the gas pressure in the airtight cavity 140 communicating with the gas storage chamber 120 is equal to the atmospheric pressure, so that the piston 130 is in a balanced position. During the braking process, since the temperature of the brake carbon disc (brake disc assembly 200) can reach 600-700 degrees Celsius, heat radiation will heat the gas in the gas storage chamber 120, that is, the gas storage chamber 120 absorbs heat, and the gas therein When heated and expanded, the gas pressure in the cavity is higher than the external pressure (atmospheric pressure), and the piston 130 is pushed through the closed cavity 140 until the probe rod 160 passing through the two ends of the piston 130 bears against the brake disc assembly 200 ( static disk).

If the wear of the brake disc assembly 200 is not severe, the piston 130 does not conduct the conductive contact piece 170 when the probe rod 160 bears against (the stationary disc of) the brake disc assembly 200 . On the other hand, when the brake disc assembly 200 wears to a certain extent, the piston 130 will move to the conductive contact piece 170 when the probe rod 160 bears against the brake disc assembly 200 (the static disc), so that the conductive contact piece 170 is turned on to send a conduction signal indicating that the brake disc assembly 200 needs to be replaced. The conduction signal can be collected by the brake control unit through the signal collection line 180, and a reminder will be issued by the aircraft on-board maintenance system (not shown).

In addition, the probe rod 160 passes through the piston 130 and the piston chamber 111 in an airtight manner. Preferably, the probe rod 160 is scaled, so that the ground crew can also manually press the probe rod 160 against the brake disc assembly 200 (the static disc) when performing routine maintenance and testing. , and judge whether the brake disc assembly 200 needs to be replaced through the scale.

Although the embodiments of the present invention have been shown and described, those skilled in the art can understand that various changes, modifications and substitutions can be made to these embodiments without departing from the principle and spirit of the present invention. and modifications, the scope of the invention is defined by the appended claims and their equivalents.

For example, in an embodiment of the present invention, as shown in FIG. 1 , the air storage chamber 120 is disposed separately from the piston on the outside of the piston chamber 111 of the brake cylinder block 110 on the side close to the brake disc assembly 200 , But the present invention is not limited thereto, as long as the air storage chamber 120 is set separately from the piston, it can absorb the heat emitted during the braking process to expand the gas stored therein, and communicate with the air storage chamber 120 through the communication conduit 150 The closed cavity 140 pushes the position of the piston 130.

Claims (7)

1. An aircraft wheel brake wear monitoring device (100) for monitoring wear of a brake disc assembly (200) of an aircraft wheel, comprising:

a brake cylinder block (110), the brake cylinder block (110) forming a piston chamber (111);

a gas storage chamber (120) in which a gas that can absorb heat and expand is stored;

a piston (130), the piston (130) disposed in the piston chamber (111);

a closed cavity (140), the closed cavity (140) being formed between a piston end (131) of the piston (130) on the side opposite to the brake disc assembly (200) and the brake cylinder block (110) to form the closed cavity (140), and being communicated with the air reservoir (120) through a communication conduit (150);

a probe shaft (160), the probe shaft (160) passing through both ends of the piston (130) along the piston chamber (111);

a conductive contact pad (170), said conductive contact pad (170) being disposed within said piston chamber (111) and being capable of rendering said conductive contact pad (170) conductive upon contact with said piston (130) to issue a conductive signal indicating a need to replace said brake disc assembly (200); and

and the signal acquisition line (180) is used for acquiring the conduction signal to the brake control unit.

2. An aircraft wheel brake wear monitoring device (100) as claimed in claim 1,

in the normal condition of non-braking, the gas pressure in the closed cavity (140) communicated with the air storage chamber (120) is equal to the atmospheric pressure, so that the piston (130) is in the balance position,

during braking, the brake disc assembly (200) generates heat to heat the gas in the gas storage chamber (120), the gas expands due to heating to make the gas pressure in the chamber higher than atmospheric pressure, and the piston (130) is pushed through the closed chamber (140) until the probe rods (160) penetrating through the two end parts of the piston (130) are pressed against the brake disc assembly (200).

3. An aircraft wheel brake wear monitoring device (100) as claimed in claim 2,

before the brake disc assembly (200) is worn to a specified wear extent, the piston (130) does not contact with the conductive contact piece (170) when the probe rod (160) abuts against the brake disc assembly (200), and after the specified wear extent is reached, the piston (130) moves to the conductive contact piece (170) to contact with the conductive contact piece (170) when the probe rod (160) abuts against the brake disc assembly (200), so that the conductive contact piece (170) is conducted.

4. An aircraft wheel brake wear monitoring device (100) according to any one of claims 1 to 3,

the air storage chamber (120) is arranged outside the piston chamber (111) of the brake cylinder seat (110) on the side close to the brake disc assembly (200) separately from the piston.

5. An aircraft wheel brake wear monitoring device (100) according to any one of claims 1 to 3,

the probe shaft (160) passes through the piston (130) and the piston chamber (111) in an airtight manner.

6. An aircraft wheel brake wear monitoring device (100) according to claim 5,

the probe rod (160) can be manually depressed until it abuts the brake disc assembly (200).

7. An aircraft wheel brake wear monitoring device (100) as claimed in claim 6,

the probe shaft (160) is graduated,

whether the brake disc assembly (200) needs to be replaced can be judged by manually pressing the probe rod (160) and reading the scale on the probe rod (160).

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