Aircraft landing gear brake cooling device

Abstract

The utility model relates to an aircraft landing gear brake cooling device, and relates to the field of aircraft ground support equipment. The device comprises a machine base, a centrifugal fan and a fan cover, the centrifugal fan and the fan cover are both installed on the machine base, the two ends of the fan cover are open, one end of the fan cover is connected with an air inlet of the centrifugal fan, and the other end of the fan cover is used for being connected with a hub. A plurality of servo cylinders arranged at equal intervals in the circumferential direction of the axis of the servo cylinders are arranged at the end, facing the hub, of the fan cover, push rods of the servo cylinders are connected with arc-shaped sealing strips, the sealing strips are elastic and can define an annular sealing part, and the inner contour of the sealing part is matched with the outer contour of the fan cover and the outer contour of the hub. Multiple airflows are used for heat dissipation, the brake cooling speed is increased, the brake cooling time is shortened, the brake cooling efficiency is improved, and the possibility of aircraft delay is reduced; and adsorption of carbon powder is realized through the air tap, so that a cleaning effect is achieved.

Description

Technical Field

[0001] This application relates to the field of aircraft ground support equipment, and in particular to an aircraft landing gear brake cooling device. Background Technology

[0002] During taxiing, turning, landing braking, and takeoff aborts, aircraft must use wheel brakes to convert kinetic energy into heat energy in the brake discs. Under continuous and excessive braking, the brake discs absorb a significant amount of braking energy, causing their temperature to exceed specified limits. If braking continues, the wheel's braking capacity will rapidly decrease, potentially leading to complete failure. Because disc brakes are installed inside the wheel's internal cavity, failure to reduce the wheel brake temperature below the specified level can easily cause a fire after the wheels retract into the wheel well. Therefore, effective cooling measures are essential.

[0003] Currently, the cooling measures for civil aircraft brakes generally involve installing cooling fans inside the landing gear axles. A power system supplies electricity to a motor, which in turn drives the fan to rotate. The rotating fan blades create airflow, cooling the brake discs. For the safety of the fan blades, a cover is installed on the outer end face of the axle to prevent external objects from being drawn inside. The cover also has several holes to allow airflow between the inside and outside of the axle.

[0004] Normally, the fans are used 5 minutes after landing or when the aircraft reaches the parking position. However, when the stopover time is short or the brake temperature may exceed 500°C, especially in summer and low-latitude regions, the air temperature is already high, and the tarmac surface temperature can reach 40 or 50 degrees Celsius or even higher, which is very detrimental to the heat dissipation of the brake pads. If only the aircraft's own cooling fans are used for cooling, it will be time-consuming and inefficient, which may increase the cooling time and cause flight delays. Utility Model Content

[0005] In order to improve the problem that the aircraft's built-in cooling fan is time-consuming and inefficient, which may increase the cooling time and cause flight delays, this application provides an aircraft landing gear brake cooling device.

[0006] The aircraft landing gear brake cooling device provided in this application adopts the following technical solution:

[0007] An aircraft landing gear brake cooling device includes a base, a centrifugal fan, and a fan shroud. The centrifugal fan and the fan shroud are both mounted on the base. The fan shroud is open at both ends, with one end connected to the air inlet of the centrifugal fan and the other end connected to the wheel hub.

[0008] The end of the wind shield facing the wheel hub is provided with several servo cylinders equidistantly arranged circumferentially along its own axis. The push rod of each servo cylinder is connected to an arc-shaped sealing strip. The sealing strip is elastic and can form an annular sealing part. The inner contour of the sealing part is adapted to the outer contour of the wind shield and the wheel hub.

[0009] Optionally, the shroud is provided with a bracket, on which a first air pipe is rotatably connected. The end of the first air pipe facing the hub is connected to a diverter box, which can rotate around the axis of the hub. Several air nozzles are installed on the side wall of the diverter box. The end of the first air pipe away from the diverter box is connected to a second air pipe through a rotary joint. The second air pipe extends out of the shroud and is used to communicate with the air extraction equipment. The bracket is provided with a drive assembly for driving the first air pipe to rotate.

[0010] Optionally, the drive assembly includes a servo motor and pulleys. Two pulleys are provided and are respectively connected to the first air pipe and the motor shaft of the servo motor. The two pulleys are connected by a belt.

[0011] Optionally, both pulleys are provided with several through holes.

[0012] Optionally, a telescopic tube connects the first air tube to the diversion box. The diversion box has two studs symmetrically distributed about the first air tube on its side wall. The first air tube has an adjustment plate corresponding to each stud. The studs pass vertically through the adjustment plate and are threaded with adjustment nuts on both sides of the adjustment plate.

[0013] Optionally, when the sealing strips form a sealing portion, adjacent sealing strips are squeezed against each other and undergo elastic deformation.

[0014] Optionally, the centrifugal fan is equipped with a temperature sensor at its outlet.

[0015] Optionally, the base is equipped with several casters.

[0016] The centrifugal fan has a filter cover at its outlet, and a dust collection box is connected to the second air pipe.

[0017] A lifting platform is provided parallel above the base, and an electric cylinder is connected between the base and the lifting platform.

[0018] In summary, this application includes at least one of the following beneficial technical effects:

[0019] 1. The airflow generated by the centrifugal fan quickly removes heat from the brake pads, and the cooling fan works in conjunction with the cooling pads to achieve rapid cooling. At the same time, the second air pipe is connected to the air extraction equipment, and each air nozzle extracts air from the inside of the wheel axle through the holes on the cover. On the one hand, this further increases the airflow speed, allowing internal heat to be carried away. On the other hand, the suction force of the nozzles can adsorb carbon powder adhering to the holes, achieving a cleaning effect. The use of multiple airflows for heat dissipation increases the brake cooling speed, shortens the brake cooling time, and thus improves brake cooling efficiency, reducing the possibility of aircraft delays.

[0020] 2. The sealing part formed by the various sealing strips blocks the gap between the fan cover and the hub, enhancing the centrifugal fan's suction and heat dissipation effect on the inside of the wheel shaft;

[0021] 3. The distance between the diversion box and the first air tube is adjustable. The operator can control the distance between the nozzle and the cover by moving the diversion box to avoid collision between the nozzle and the cover, and at the same time make the nozzle fit as close as possible to the hole on the cover to ensure the adsorption effect. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall structure of an embodiment of this application.

[0023] Figure 2 This is a schematic diagram illustrating the wheel hub and the cover in an embodiment of this application.

[0024] Figure 3 This is a schematic diagram illustrating the internal structure of the windshield in an embodiment of this application.

[0025] Figure 4 This is a schematic diagram illustrating the driving component in an embodiment of this application.

[0026] Figure 5 yes Figure 4 Enlarged view of point A in the middle;

[0027] Figure 6 This is a structural diagram of the lifting platform in an embodiment of this application.

[0028] Explanation of reference numerals in the attached drawings: 1. Base; 11. Centrifugal fan; 111. Temperature sensor; 12. Fan shroud; 13. Servo cylinder; 131. Sealing strip; 14. Caster wheel; 2. Bracket; 21. First air pipe; 211. Adjusting plate; 22. Diverter box; 221. Air nozzle; 222. Telescopic tube; 223. Stud; 224. Adjusting nut; 23. Second air pipe; 3. Drive assembly; 31. Servo motor; 32. Pulley; 321. Through hole; 33. Belt; 4. Hub; 5. Cover; 6. Filter cover; 7. Dust collection box; 8. Lifting platform; 81. Electric cylinder. Detailed Implementation

[0029] The present invention will now be described in further detail with reference to the accompanying drawings and specific preferred embodiments.

[0030] In the description of this utility model, it should be understood that the terms "left side," "right side," "upper part," "lower part," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. "First," "second," etc., do not indicate the importance of the components, and therefore should not be construed as a limitation of this utility model. The specific dimensions used in this embodiment are only for illustrating the technical solution and do not limit the protection scope of this utility model.

[0031] This application discloses an aircraft landing gear brake cooling device. For example... Figure 2 The holes on the cover 5 are divided into several fan-shaped areas that are equidistantly distributed along the circumference of the hub 4 axis, and the number of holes in each fan-shaped area is the same.

[0032] like Figure 1 The aircraft landing gear brake cooling system includes a base 1, a centrifugal fan 11, and a fan shroud 12. Several casters 14 are mounted on the bottom of the base 1. Both the centrifugal fan 11 and the fan shroud 12 are mounted on the base 1. A temperature sensor 111 is installed at the outlet of the centrifugal fan 11 to detect the temperature of the outlet. A filter shroud 6 is also installed at the outlet of the centrifugal fan 11 to filter particulate matter in the airflow.

[0033] The wind cover 12 is open at both ends and has different inner diameters. The end with the smaller inner diameter of the wind cover 12 is connected to the air inlet of the centrifugal fan 11, and the end with the larger inner diameter is used to connect to the hub 4 to cover the outer cover 5 of the axle.

[0034] like Figure 3 The wind shield 12, facing the hub 4, has several servo cylinders 13 arranged equidistantly along its own axis. The axis of the servo cylinders 13 is perpendicular to the axis of the wind shield 12. Each servo cylinder 13's push rod is connected to a sealing strip 131. The sealing strip 131 is elastic and arc-shaped, and the axis of each sealing strip 131 is parallel to the axis of the wind shield 12. When each servo cylinder 13 drives the sealing strip 131 to move and abut against the outer peripheral wall of the wind shield 12, the sealing strips 131 can form an annular sealing part. The sealing part extends outside the wind shield 12, and the inner contour of the sealing part matches the outer contour of the wind shield 12 and the hub 4. At the same time, adjacent sealing strips 131 are squeezed against each other and produce elastic deformation to enhance the sealing effect of the sealing part at the joint. In the initial position, each sealing strip 131 is separated from the wind shield 12, and adjacent sealing strips 131 are spaced apart.

[0035] like Figure 3 , Figure 4and Figure 5 The wind shield 12 is equipped with a bracket 2, and a first air pipe 21 is rotatably connected to the bracket 2. The end of the first air pipe 21 facing the hub 4 is connected to a telescopic pipe 222. The end of the telescopic pipe 222 away from the first air pipe 21 is connected to a diverter box 22. The side wall of the diverter box 22 is vertically provided with two studs 223 symmetrically distributed about the first air pipe 21. The first air pipe 21 is provided with an adjustment plate 211 corresponding to the studs 223. The studs 223 pass vertically through the adjustment plate 211 and the studs 223 are threaded with adjustment nuts 224 on both sides of the adjustment plate 211. The diverter box 22 can rotate around the axis of the hub 4. Several air nozzles 221 are installed on the side wall of the diverter box 22. The number and position of the air nozzles 221 correspond to the holes in any area of ​​the cover 5. The end of the first air pipe 21 away from the diverter box 22 is connected to the second air pipe 23 through a rotary joint. The second air pipe 23 extends out of the wind cover 12 and is used to communicate with the air extraction equipment. The bracket 2 is provided with a drive assembly 3 for driving the first air pipe 21 to rotate.

[0036] A dust collection box 7 is connected to the second air pipe 23. The dust collection box 7 is connected to the second air pipe 23 and has a filter element inside. When the second air pipe 23 draws air, the airflow enters the dust collection box 7 and passes through the filter element, which intercepts carbon powder particles in the airflow. In some other embodiments, a sponge pad can be provided at the air outlet of the air nozzle 221 to prevent the air nozzle 221 from making hard contact with the cover 5.

[0037] like Figure 4 and Figure 5 The drive assembly 3 includes a servo motor 31 and pulleys 32. Two pulleys 32 are respectively connected to the first air tube 21 and the motor shaft of the servo motor 31, and the two pulleys 32 are connected by a belt 33. The servo motor 31 drives the connected pulleys 32 to rotate, causing the first air tube 21 to rotate via belt drive. The operator can move the diverter box 22 by adjusting the nuts 224 and studs 223 to adjust the distance between each air nozzle 221 and the cover 5, so that the air nozzles 221 are as close to the cover 5 as possible, ensuring the adsorption effect of the air nozzles 221.

[0038] Both pulleys 32 are provided with several through holes 321. When the centrifugal fan 11 is started, airflow is generated in the fan cover 12. The through holes 321 allow the airflow to pass through, reducing the obstruction to the airflow.

[0039] In some embodiments, a lifting platform 8 is provided parallel above the base 1, and an electric cylinder 81 is connected between the lifting platform 8 and the base 1. The centrifugal fan 11 and the fan cover 12 are both installed on the lifting platform 8. The operator can adjust the height of the fan cover 12 by using the electric cylinder 81 so that the fan cover 12 can be adapted to the hubs 4 of different sizes, thereby increasing the applicability of the device.

[0040] The principle of this application embodiment: When the aircraft is parked, if the brake temperature reaches above 100 degrees Celsius, the cooling fan will be turned on. If the brake temperature exceeds 300 degrees Celsius, the aircraft system will issue a BRAKE HOT warning. In order to speed up the brake cooling speed, the operator moves the base 1 to the aircraft hub 4 and adjusts the position of the base 1 so that the fan cover 12 is directly facing the hub 4. Each servo cylinder 13 drives the corresponding sealing strip 131 to move and abut against the fan cover 12. Each sealing strip 131 forms a sealing part and covers the gap between the fan cover 12 and the hub 4.

[0041] Centrifugal fan 11 starts, drawing air outward from the shroud 12. This airflow continuously carries away heat from the brake pads. Furthermore, because the sealing strip 131 blocks the gap between the shroud 12 and the wheel hub 4, the airflow within the shroud 12 is enhanced within the limited space, improving brake pad cooling efficiency and ensuring normal flight operations. Temperature sensor 111 detects the temperature at the outlet of centrifugal fan 11 to determine if the brake temperature has reached the normal range, allowing for a decision from the ground whether to continue or interrupt brake cooling.

[0042] Currently, aircraft brake pads are generally made of carbon or carbon composite materials. During the cooling process, the brake pads generate dust due to friction during operation, which is discharged with the cooling fan, releasing harmful substances that may endanger the health of ground personnel. Therefore, the operator can connect the second air pipe 23 to an air extraction device, such as a vacuum pump, and start the servo motor 31 to drive the first air pipe 21 to rotate, aligning the distribution box 22 with one of the fan-shaped areas of the cover 5. Each air nozzle 221 sucks air from the inside of the hub 4 through the holes on the cover 5, which can both accelerate the airflow speed inside the hub 4 and adsorb the carbon powder attached to the holes, reducing the outward diffusion of carbon powder. After the adsorption of one fan-shaped area is completed, the servo motor 31 drives the first air pipe 21 to rotate a certain angle, which will cause the distribution box 22 to rotate to the corresponding position of the next fan-shaped area.

[0043] Operators can combine the exhaust equipment with the dust collector to send the adsorbed carbon powder into the dust collector for collection and then process it uniformly.

[0044] Those skilled in the art will understand that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless defined as herein.

[0045] The meaning of "and / or" as used in this application includes situations where each exists alone or both exist simultaneously.

[0046] The term "connection" as used in this application can mean a direct connection between components or an indirect connection between components through other components.

Claims

1. A cooling device for aircraft landing gear brakes, characterized in that: Includes a base (1), a centrifugal fan (11) and a fan cover (12). The centrifugal fan (11) and the fan cover (12) are both mounted on the base (1). The fan cover (12) is open at both ends, with one end connected to the air inlet of the centrifugal fan (11) and the other end used to connect to the hub (4). The wind shield (12) is provided with a number of servo cylinders (13) arranged equidistantly along its own axis at one end facing the hub (4). The push rod of each servo cylinder (13) is connected to an arc-shaped sealing strip (131). The sealing strip (131) is elastic and each sealing strip (131) can form an annular sealing part. The inner contour of the sealing part is adapted to the outer contour of the wind shield (12) and the hub (4).

2. The aircraft landing gear brake cooling device according to claim 1, characterized in that: The hood (12) is provided with a bracket (2), and a first air pipe (21) is rotatably connected to the bracket (2). The end of the first air pipe (21) facing the hub (4) is connected to a diverter box (22). The diverter box (22) can rotate around the axis of the hub (4). Several air nozzles (221) are installed on the side wall of the diverter box (22). The end of the first air pipe (21) away from the diverter box (22) is connected to a second air pipe (23) through a rotary joint. The second air pipe (23) extends out of the hood (12) and is used to communicate with the air extraction equipment. The bracket (2) is provided with a drive assembly (3) for driving the first air pipe (21) to rotate.

3. The aircraft landing gear brake cooling device according to claim 2, characterized in that: The drive assembly (3) includes a servo motor (31) and pulleys (32). There are two pulleys (32) and they are respectively connected to the first air pipe (21) and the motor shaft of the servo motor (31). The two pulleys (32) are connected by a belt (33).

4. The aircraft landing gear brake cooling device according to claim 3, characterized in that: Both pulleys (32) are provided with several through holes (321).

5. The aircraft landing gear brake cooling device according to claim 2, characterized in that: A telescopic tube (222) is connected between the first air tube (21) and the diversion box (22). The diversion box (22) has two studs (223) vertically arranged about the first air tube (21) symmetrically distributed. The first air tube (21) has an adjusting plate (211) corresponding to the studs (223). The studs (223) pass vertically through the adjusting plate (211) and the studs (223) are threaded with adjusting nuts (224) on both sides of the adjusting plate (211).

6. The aircraft landing gear brake cooling device according to claim 1, characterized in that: When the sealing strips (131) form a sealing portion, adjacent sealing strips (131) are squeezed against each other and undergo elastic deformation.

7. The aircraft landing gear brake cooling device according to claim 1, characterized in that: The centrifugal fan (11) is equipped with a temperature sensor (111) at its air outlet.

8. The aircraft landing gear brake cooling device according to claim 1, characterized in that: The base (1) is equipped with several casters (14) on its bottom surface.

9. The aircraft landing gear brake cooling device according to claim 2, characterized in that: The centrifugal fan (11) has a filter cover (6) at its air outlet, and a dust collection box (7) is connected to the second air pipe (23).

10. The aircraft landing gear brake cooling device according to claim 1, characterized in that: A lifting platform (8) is provided parallel above the base (1), and an electric cylinder (81) is connected between the base (1) and the lifting platform (8).

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