CN111469817B - Multifunctional aircraft brake cooling control device - Google Patents
Multifunctional aircraft brake cooling control device Download PDFInfo
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- CN111469817B CN111469817B CN202010321706.3A CN202010321706A CN111469817B CN 111469817 B CN111469817 B CN 111469817B CN 202010321706 A CN202010321706 A CN 202010321706A CN 111469817 B CN111469817 B CN 111469817B
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- brake cooling
- wheel speed
- pressure sensor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T5/00—Vehicle modifications to facilitate cooling of brakes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60C—VEHICLE TYRES; TYRE INFLATION; TYRE CHANGING; CONNECTING VALVES TO INFLATABLE ELASTIC BODIES IN GENERAL; DEVICES OR ARRANGEMENTS RELATED TO TYRES
- B60C23/00—Devices for measuring, signalling, controlling, or distributing tyre pressure or temperature, specially adapted for mounting on vehicles; Arrangement of tyre inflating devices on vehicles, e.g. of pumps or of tanks; Tyre cooling arrangements
- B60C23/02—Signalling devices actuated by tyre pressure
- B60C23/04—Signalling devices actuated by tyre pressure mounted on the wheel or tyre
- B60C23/0408—Signalling devices actuated by tyre pressure mounted on the wheel or tyre transmitting the signals by non-mechanical means from the wheel or tyre to a vehicle body mounted receiver
- B60C23/0422—Signalling devices actuated by tyre pressure mounted on the wheel or tyre transmitting the signals by non-mechanical means from the wheel or tyre to a vehicle body mounted receiver characterised by the type of signal transmission means
- B60C23/0433—Radio signals
- B60C23/0447—Wheel or tyre mounted circuits
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60C—VEHICLE TYRES; TYRE INFLATION; TYRE CHANGING; CONNECTING VALVES TO INFLATABLE ELASTIC BODIES IN GENERAL; DEVICES OR ARRANGEMENTS RELATED TO TYRES
- B60C23/00—Devices for measuring, signalling, controlling, or distributing tyre pressure or temperature, specially adapted for mounting on vehicles; Arrangement of tyre inflating devices on vehicles, e.g. of pumps or of tanks; Tyre cooling arrangements
- B60C23/02—Signalling devices actuated by tyre pressure
- B60C23/04—Signalling devices actuated by tyre pressure mounted on the wheel or tyre
- B60C23/0486—Signalling devices actuated by tyre pressure mounted on the wheel or tyre comprising additional sensors in the wheel or tyre mounted monitoring device, e.g. movement sensors, microphones or earth magnetic field sensors
- B60C23/0488—Movement sensor, e.g. for sensing angular speed, acceleration or centripetal force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60C—VEHICLE TYRES; TYRE INFLATION; TYRE CHANGING; CONNECTING VALVES TO INFLATABLE ELASTIC BODIES IN GENERAL; DEVICES OR ARRANGEMENTS RELATED TO TYRES
- B60C23/00—Devices for measuring, signalling, controlling, or distributing tyre pressure or temperature, specially adapted for mounting on vehicles; Arrangement of tyre inflating devices on vehicles, e.g. of pumps or of tanks; Tyre cooling arrangements
- B60C23/18—Tyre cooling arrangements, e.g. heat shields
- B60C23/19—Tyre cooling arrangements, e.g. heat shields for dissipating heat
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Regulating Braking Force (AREA)
- Braking Arrangements (AREA)
Abstract
本发明实施例公开了一种多功能飞机刹车冷却控制装置，包括：刹车冷却风扇、胎压传感器、机轮速度传感器和刹车冷却电机；机轮速度传感器的中心轴孔穿过刹车冷却电机的长轴，且固设于刹车冷却电机的一端；机轮速度传感器用于监控飞机轮胎的速度；胎压传感器的中心轴孔穿过刹车冷却电机的长轴，且固设于机轮速度传感器的一端；胎压传感器中设置有与飞机轮胎相连接的压力传感器，用于与飞机轮胎同步转动，从而监控飞机轮胎的压力；刹车冷却风扇安装于刹车冷却电机的长轴的端部，用于通过刹车冷却电机长轴的带动进行旋转，产生对飞机轮胎进行散热冷却的气流。本发明实施例实现了飞机轮胎压力检测、机轮转速检测和刹车冷却降温功能的集成。
The embodiment of the present invention discloses a multifunctional aircraft brake cooling control device, comprising: a brake cooling fan, a tire pressure sensor, a wheel speed sensor and a brake cooling motor; the central shaft hole of the wheel speed sensor passes through the long length of the brake cooling motor The shaft is fixed at one end of the brake cooling motor; the wheel speed sensor is used to monitor the speed of the aircraft tires; the central shaft hole of the tire pressure sensor passes through the long shaft of the brake cooling motor and is fixed at one end of the wheel speed sensor ; The tire pressure sensor is provided with a pressure sensor connected to the aircraft tire, which is used to rotate synchronously with the aircraft tire, so as to monitor the pressure of the aircraft tire; the brake cooling fan is installed at the end of the long shaft of the brake cooling motor to pass the brake The long shaft of the cooling motor is driven to rotate, and the airflow for cooling the aircraft tires is generated. The embodiment of the present invention realizes the integration of aircraft tire pressure detection, wheel speed detection and brake cooling and cooling functions.
Description
Technical Field
The present application relates to but is not limited to the technical field of aircraft brake systems, and in particular, to a multifunctional aircraft brake cooling control device.
Background
In the stages of takeoff, landing, sliding, braking and the like of the airplane, the reliability and the safety of the braking of the airplane are directly influenced by factors such as the speed of the airplane wheel, the pressure of a tire, the braking temperature and the like. When the airplane needs to be braked during taking off and landing, an accurate speed signal is particularly critical, and the braking performance is directly influenced; in the process of airplane taxiing, the tires of individual airplane wheels are insufficient in pressure or burst, and the tires may deviate from a runway to cause potential safety hazards; and the brake can be frequently used in long-distance sliding, so that the temperature of the brake device is overhigh, and the fire of the brake device of the airplane can be caused in severe cases. Therefore, the method is very necessary for detecting the pressure of the airplane tire, detecting the speed of the airplane wheel and cooling the brake.
Disclosure of Invention
In order to ensure the safety of the take-off and landing sliding brake of the airplane and facilitate the daily maintenance of the airplane wheels, the invention provides a multifunctional airplane brake cooling control device, so as to realize the integration of the functions of detecting the pressure of the airplane tires, detecting the rotating speed of the airplane wheels and cooling the brake.
The embodiment of the invention provides a multifunctional aircraft brake cooling control device, which comprises: the device comprises a brake cooling fan, a tire pressure sensor, an airplane wheel speed sensor and a brake cooling motor;
the airplane wheel speed sensor is provided with a central shaft hole, the central shaft hole penetrates through a long shaft of the brake cooling motor and is fixedly arranged at one end of the brake cooling motor, and the airplane wheel speed sensor and the brake cooling motor are positioned in an airplane wheel shaft; the wheel speed sensor configured to monitor the speed of the aircraft tire;
the tire pressure sensor is provided with a central shaft hole, the central shaft hole penetrates through a long shaft of the brake cooling motor and is fixedly arranged at one end of the airplane wheel speed sensor, and the tire pressure sensor is positioned outside the airplane wheel shaft;
the tire pressure sensor is provided with a pressure sensor connected with an aircraft tire, is configured to rotate synchronously with the aircraft tire, and monitors the pressure of the aircraft tire through the pressure sensor;
the brake cooling fan is mounted at the end of the long shaft of the brake cooling motor and is configured to rotate under the driving of the long shaft of the brake cooling motor to generate airflow for cooling and dissipating heat of the aircraft tire.
Optionally, in the multifunctional aircraft brake cooling control device as described above, the tire pressure sensor includes: the brake cooling motor comprises a shell rotating part and a shell static part, wherein one end of the shell static part, which is close to the brake cooling motor, is provided with a tire pressure leading-out cable;
a bearing is installed at one end, close to the brake cooling fan, of the shell rotating part, a long shaft of the brake cooling motor is fixed and supported through the bearing, two shifting fork structures are arranged on the maximum excircle of the shell rotating part, the shifting fork structures are fixed on the airplane tire and rotate synchronously with the airplane tire, and the pressure sensor arranged on the shell rotating part is installed in an outer half hub of the airplane tire and communicated with air pressure in the airplane tire;
the aircraft wheel speed sensor is characterized in that a hollow shaft is arranged in the static part of the shell, the shell of the hollow shaft rotates along with the rotating part of the shell, and a first shifting fork structure is arranged at one end, close to the wheel speed sensor, of the hollow shaft and is configured to transmit the rotation of an aircraft tire to the wheel speed sensor.
Optionally, in the multifunctional aircraft brake cooling control device as described above, one end of the wheel speed sensor close to the tire pressure sensor is provided with a second fork structure fixed in cooperation with the first fork structure, through the second fork structure and the tire pressure sensor fixed connection, one end of the wheel speed sensor close to the brake cooling motor is provided with a wheel speed leading-out cable.
Alternatively, in the multifunctional aircraft brake cooling control device as described above, the housing stationary portions of the brake cooling motor, the wheel speed sensor and the tire pressure sensor are mounted within the axle of the landing gear axle.
Optionally, in the multifunctional aircraft brake cooling control device as described above, the brake cooling motor includes a cylindrical housing, a cooling motor disposed in the cylindrical housing, and the long shaft disposed on the cooling motor;
two wiring grooves are formed in two sides of the cylindrical shell and used for correspondingly arranging leading-out cables of the tire pressure sensors and the wheel speed sensors one by one, and the width and the depth of each wiring groove are larger than those of the leading-out cables.
Optionally, in the multifunctional aircraft brake cooling control device described above, a socket of the brake cooling motor is arranged on the rear end cover of the cylindrical housing, and two wire pressing tables are further arranged on the rear end cover of the cylindrical housing, and are used for fixing the tire pressure sensors and the outgoing cables of the wheel speed sensors in a one-to-one correspondence manner.
Optionally, in the multifunctional aircraft brake cooling control device as described above, flanges are disposed at two ends of the wheel speed sensor, and are fixed to the cylindrical housings of the tire pressure sensor and the brake cooling motor respectively by screws.
Optionally, in the multifunctional aircraft brake cooling control device as described above, further comprising: and the supporting sleeve is arranged outside the airplane wheel speed sensor and the brake cooling motor, the opening end of the supporting sleeve is one end close to the brake cooling motor, and the annular spigot at the round spigot end is clamped in the clamping groove position corresponding to the undercarriage wheel shaft.
Optionally, in the multifunctional aircraft brake cooling control device as described above, the multifunctional aircraft brake cooling control device is mounted in the landing gear axle wheel through a fixed wheel nut, and a threaded surface that is matched with an outer surface of the fixed wheel nut is provided on an inner surface at a port of the landing gear axle; and the convex key on the circumference of the shell of the tire pressure sensor is inserted into the convex key groove on the inner surface of the nut of the fixed airplane wheel and is used for limiting the radial rotation of the multifunctional airplane brake cooling control device.
The embodiment of the invention provides a multifunctional aircraft brake cooling control device, which comprises: the device comprises a brake cooling fan, a tire pressure sensor, an airplane wheel speed sensor and a brake cooling motor; the central shaft hole of the airplane wheel speed sensor penetrates through the long shaft of the brake cooling motor and is fixedly arranged at one end of the brake cooling motor; the airplane wheel speed sensor is used for monitoring the speed of airplane tires; a central shaft hole of the tire pressure sensor penetrates through a long shaft of the brake cooling motor and is fixedly arranged at one end of the airplane wheel speed sensor; the tire pressure sensor is internally provided with a pressure sensor connected with the airplane tire and used for synchronously rotating with the airplane tire so as to monitor the pressure of the airplane tire; the brake cooling fan is arranged at the end part of the long shaft of the brake cooling motor and is used for rotating under the driving of the long shaft of the brake cooling motor to generate airflow for radiating and cooling the tire of the airplane. The multifunctional aircraft brake cooling control device in the embodiment of the invention effectively utilizes the narrow space in the landing gear shaft to realize the integration of the functions of aircraft tire pressure detection, wheel rotation speed detection and brake cooling; based on the existing principle and function technology, the structure design is ingenious and reasonable, the maximum utilization of the internal space of the landing gear shaft is realized, and the integration of multiple functions is realized.
Drawings
The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the example serve to explain the principles of the invention and not to limit the invention.
FIG. 1 is a schematic structural diagram of a multifunctional aircraft brake cooling control device according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a tire pressure sensor in the multifunctional aircraft brake cooling control device according to an embodiment of the present invention;
fig. 3 is a right side view of the tire pressure sensor shown in fig. 2;
fig. 4 is a schematic structural view of a gasket in the tire pressure sensor shown in fig. 2;
FIG. 5 is a cross-sectional view of the gasket shown in FIG. 4;
FIG. 6 is a schematic structural diagram of a wheel speed sensor in the multifunctional aircraft brake cooling control device according to an embodiment of the present invention;
FIG. 7 is a left side view of the wheel speed sensor of FIG. 6;
FIG. 8 is a schematic structural diagram of a brake cooling motor in the multifunctional aircraft brake cooling control device according to the embodiment of the invention;
FIG. 9 is a schematic view of the long shaft end of the brake cooling motor of FIG. 8;
FIG. 10 is a left side elevational view of the brake cooling motor illustrated in FIG. 8;
FIG. 11 is a schematic structural diagram of a support sleeve of the multifunctional aircraft brake cooling control device according to the embodiment of the invention;
FIG. 12 is a cross-sectional view of the support sleeve of FIG. 11;
FIG. 13 is a cross-sectional view of the support sleeve of FIG. 11 taken along line A-A;
FIG. 14 is a schematic structural diagram of a wheel nut of a fixing device in the multifunctional aircraft brake cooling control device according to the embodiment of the invention;
fig. 15 is a left side view of the retainer wheel nut of fig. 14.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
In the prior patent CN105752053A, compressed gas is used for cooling a brake device in an airplane brake cooling system and method, a compressed gas cylinder adopted by the method is suitable for small airplanes with few airplane wheels, and the method has long cooling time and low efficiency in braking. This method is different from the cooling method used in the following examples of the present invention. The embodiment of the invention adopts a mode of braking and cooling the fan to quickly cool the airplane wheel, and has short verified cooling time and high efficiency.
The prior patent CN201821199740.2 "wheel speed sensor" protects the wheel speed sensor alone, and does not describe other devices in the brake device.
In the prior patent CN201811309693.7 brake cooling system for main wheels of multi-wheel-train aircraft, a brake cooling component only comprises a brake cooling motor and a fan and only has the function of brake cooling. The fan blades are consistent with the brake cooling fan; the brake cooling motor is different from the brake cooling motor in structure, and the brake cooling motor adopts a long shaft structure.
The foreign aircraft a320 series aircraft is provided with a tire pressure indicating device and a general brake cooling fan, and the overall structural layout of the foreign aircraft a320 series aircraft is different from the following embodiments of the present application. The space in the A320 series aircraft landing gear shaft is large, the tire pressure indicating device and the brake cooling fan motor are directly connected, the speed sensor is arranged at the tail end in the landing gear shaft, and the speed measuring rod penetrates through the motor to drive the speed sensor, so that the motor is of a hollow structure, and higher requirements are provided for the space of the motor and the landing gear shaft; the invention adopts a brake cooling motor with a long shaft, and an airplane wheel speed sensor and a tire pressure sensor which penetrate through a hollow structure.
The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.
Fig. 1 is a schematic structural diagram of a multifunctional aircraft brake cooling control device according to an embodiment of the present invention. The multifunctional aircraft brake cooling control device provided by the embodiment can comprise: a brake cooling fan 1, a tire pressure sensor 2, a wheel speed sensor 3, and a brake cooling motor 4.
As shown in fig. 1, in the structure of the multifunctional aircraft brake cooling control device, the wheel speed sensor 3 is provided with a central shaft hole, and the central shaft hole penetrates through a long shaft of the brake cooling motor 4 and is fixedly arranged at one end of the brake cooling motor 4. When needing to be explained, in the multifunctional aircraft brake cooling control device, an aircraft wheel speed sensor 3 and a brake cooling motor 4 are positioned inside an aircraft wheel shaft; and a wheel speed sensor 3 configured to monitor the speed of aircraft tires.
The tire pressure sensor 2 in the embodiment of the present invention is also provided with a central shaft hole, which also penetrates through the long shaft of the brake cooling motor 4 and is fixedly disposed at one end of the wheel speed sensor 3. When needing to be explained, in the multifunctional aircraft brake cooling control device, the tire pressure sensor is positioned outside the aircraft wheel shaft.
The tire pressure sensor 2 in the embodiment of the invention is provided with a pressure sensor connected with an airplane tire, and the pressure sensor can rotate synchronously with the airplane tire and monitor the pressure of the airplane tire.
The brake cooling fan 1 in the embodiment of the present invention is installed at an end of a long shaft of the brake cooling motor 4, and is configured to rotate by being driven by the long shaft of the brake cooling motor 4 to generate an air flow for heat dissipation and cooling of an aircraft tire.
As shown in fig. 1, the multifunctional aircraft brake cooling control device in the embodiment of the invention is assembled from the outside to the inside by a brake cooling fan 1, a tire pressure sensor 2, a wheel speed sensor 3 and a brake cooling motor 4. The brake cooling fan 1 is located on the outermost side, is installed at the end of a long shaft of the brake cooling motor 4 and is used for achieving the brake cooling function of the airplane; the tire pressure sensor 2 and the wheel speed sensor 3 are both hollow structures and sequentially penetrate through a long shaft of the brake cooling motor 4, and the diameters of central shaft holes of the tire pressure sensor 2 and the wheel speed sensor 3 are larger than the diameter of the long shaft of the brake cooling motor 4; in addition, flange plates can be arranged on the left side and the right side of the wheel speed sensor 3 and are respectively fixed with the tire pressure sensor 2 and the brake cooling motor 4 through screws. As described above, the brake cooling fan 1, the tire pressure sensor 2, the wheel speed sensor 3, and the brake cooling motor 4 are assembled and integrally mounted in the aircraft landing gear shaft.
Alternatively, fig. 2 is a schematic structural diagram of an air pressure sensor in the multifunctional aircraft brake cooling control device according to an embodiment of the present invention, and fig. 3 is a right side view of the air pressure sensor shown in fig. 2. Referring to the tire air pressure sensor 2 shown in fig. 2 and 3, the tire air pressure sensor 2 in the embodiment of the present invention may include: a shell rotating part and a shell static part, wherein one end of the shell static part close to the brake cooling motor 4 is provided with a tire pressure leading-out cable.
In the tire pressure sensor 2 shown in fig. 2, a bearing 15 is installed at one end of the rotating part of the housing close to the brake cooling fan 1, the long shaft of the brake cooling motor 4 is fixed and supported by the bearing 15, two fork structures 12 are arranged on the maximum outer circle of the rotating part of the housing, and the two fork structures 12 are fixed on the aircraft tire to synchronously rotate with the aircraft tire; in addition, a pressure sensor 11 in the tire pressure sensor 2 is provided in the housing rotating portion, the pressure sensor 11 being mounted in the outer half hub of the aircraft tire in communication with the air pressure inside the aircraft tire.
In the tire pressure sensor 2 shown in fig. 2, a hollow shaft is arranged inside the stationary part of the housing, the housing of the hollow shaft rotates with the rotating part of the housing, and a first fork structure 16 is arranged at one end of the hollow shaft close to the wheel speed sensor 3, and the first fork structure 16 can transmit the rotation of the aircraft tire to the wheel speed sensor 3.
In practical applications, the gasket 13 and the spacer 14 may be installed in the rotating part of the housing of the tire pressure sensor 2 before the bearing 15 is installed, and then the bearing 15 is installed, as shown in fig. 4, which is a schematic structural diagram of the gasket in the tire pressure sensor shown in fig. 2, and fig. 5 is a sectional view of the gasket shown in fig. 4.
Optionally, fig. 6 is a schematic structural diagram of a wheel speed sensor in the multifunctional aircraft brake cooling control device according to an embodiment of the present invention, and fig. 7 is a left side view of the wheel speed sensor shown in fig. 6. Referring to the wheel speed sensor 3 shown in fig. 6 and 7, one end of the wheel speed sensor 3 close to the tire pressure sensor in the embodiment of the present invention is provided with a second fork structure 17 fixed in cooperation with the first fork structure 16, and is fixedly connected to the tire pressure sensor 2 through the second fork structure 17, and one end of the wheel speed sensor 3 close to the brake cooling motor 4 is provided with a wheel speed leading-out cable, such as the right cable in fig. 6.
In actual installation, as shown in fig. 1, the housing stationary portions of the brake cooling motor 4, the wheel speed sensor 3, and the tire pressure sensor 2 are all mounted within the axle of the landing gear axle 7.
Alternatively, fig. 8 is a schematic structural view of a brake cooling motor in the multifunctional aircraft brake cooling control device according to the embodiment of the present invention, fig. 9 is a schematic view of an end portion of a long axis of the brake cooling motor shown in fig. 8, and fig. 10 is a left side view of the brake cooling motor shown in fig. 8. The brake cooling motor in the embodiment of the invention comprises a cylindrical shell, a cooling motor arranged in the cylindrical shell and a long shaft arranged on the cooling motor;
two wiring grooves are formed in two sides of the cylindrical shell and used for correspondingly arranging leading-out cables of the tire pressure sensors and the wheel speed sensors one by one, and the width and the depth of each wiring groove are larger than those of the leading-out cables.
In addition, a socket of the brake cooling motor 4 is arranged on the rear end cover of the cylindrical shell, and two wire pressing tables 18 are further arranged on the rear end cover of the cylindrical shell and used for fixing the lead-out cables of the tire pressure sensors 2 and the wheel speed sensors 3 in a one-to-one correspondence manner.
In practical application, the two ends of the wheel speed sensor 3 according to the embodiment of the present invention are provided with flanges, and the flanges are fixed to the cylindrical housings of the tire pressure sensor 2 and the brake cooling motor 4 respectively by screws.
Optionally, as shown in fig. 1, the multifunctional aircraft brake cooling control device provided in the embodiment of the present invention may further include: and a support sleeve 6 is arranged outside the wheel speed sensor 3 and the brake cooling motor 4, the open end of the support sleeve 6 is close to the brake cooling motor 4, and the annular spigot at the round closed end is clamped in a clamping groove position corresponding to the undercarriage wheel shaft 7. Fig. 11 is a schematic structural view of a support sleeve in the multifunctional aircraft brake cooling control device according to an embodiment of the invention, fig. 12 is a sectional view of the support sleeve shown in fig. 11, and fig. 13 is a sectional view of the support sleeve shown in fig. 11 taken along line a-a.
In practical installation, as shown in fig. 1, the multifunctional aircraft brake cooling control device provided by the embodiment of the invention is installed in the landing gear wheel 7 through the fixed wheel nut 5, and the inner surface at the port of the landing gear wheel 7 is provided with a threaded surface matched with the outer surface of the fixed wheel nut 5; the convex key 10 on the circumference of the shell of the tire pressure sensor 2 is inserted into the convex key groove on the inner surface of the fixed wheel nut 5 and is used for limiting the radial rotation of the multifunctional aircraft brake cooling control device. Fig. 14 is a schematic structural diagram of a wheel nut of a fixed wheel in the multifunctional aircraft brake cooling control device provided by the embodiment of the invention, and fig. 15 is a left side view of the wheel nut of the fixed wheel shown in fig. 14.
According to the multifunctional aircraft brake cooling control device provided by the embodiment of the invention, the tire pressure sensor 11 can measure the air pressure in the tire of the airplane wheel, and simultaneously rotates along with the airplane wheel to transmit the rotation of the airplane wheel to the airplane wheel speed sensor 3, and the airplane wheel speed sensor 3 can be a common excitation type sensor and can output a sinusoidal voltage signal in direct proportion to the rotation speed of the airplane wheel; the brake cooling motor 4 can drive the brake cooling fan 1 to rotate under the action of an on-machine power supply, and air flow is generated to cool the wheel of the brake.
The multifunctional aircraft brake cooling control device provided by the embodiment of the invention can effectively utilize narrow space in the landing gear shaft, and realize integration of functions of aircraft tire pressure detection, wheel rotation speed detection and brake cooling; based on the existing principle and function technology, the structure design is ingenious and reasonable, the maximum utilization of the internal space of the landing gear shaft is realized, and the integration of multiple functions is realized.
The implementation manner of the multifunctional aircraft brake cooling control device provided by the embodiment of the invention is described in detail through an implementation example. The following implementation examples may refer to fig. 1 to 15.
The multifunctional aircraft brake cooling control device in the present embodiment includes a brake cooling fan 1, a tire pressure sensor 2, a wheel speed sensor 3, and a brake cooling motor 4.
Some type of brake cooling control device is the carrier of this implementation. The airplane wheel speed sensor 3 penetrates through a long shaft of the brake cooling motor 4, and after a cable led out from the airplane wheel speed sensor 3 is aligned with a traveling wire groove 19 in a cylindrical shell of the brake cooling motor 4, a mounting flange of the airplane wheel speed sensor 3 is fixed with the shell of the brake cooling motor 4 through 6 screws; the tire pressure sensor 2 penetrates through a long shaft of the brake cooling motor 4, a shifting fork structure 16 of the tire pressure sensor 2 is aligned to a shifting fork structure 17 corresponding to the wheel speed sensor 3, a lead-out cable of the tire pressure sensor 2 is aligned to another wiring groove 19 of a cylindrical shell of the brake cooling motor 4, a gasket 13, a gasket 14 and a bearing 15 are sequentially arranged at a bearing hole position on a shell rotating part of the tire pressure sensor 2, the conical surface of the gasket 13 is in contact with the conical surface of the long shaft end of the brake cooling motor 4, and the gasket 14 with different thicknesses is selected to ensure that the end surface of the bearing 15 is basically flush (plus or minus 1mm) with the bearing 15 of the shell rotating part of the tire pressure sensor 2. Lead-out cables of the tire pressure sensor 2 and the wheel speed sensor 3 are respectively fixed on two wire pressing tables 18 on the rear end cover of the shell of the brake cooling motor 4. To this end, the assembly of the tire pressure sensor 2, the wheel speed sensor 3, and the brake cooling motor 4 is completed.
Before the tire pressure sensor 2, the wheel speed sensor 3 and the brake cooling motor 4 are integrally installed in the landing gear shaft 7, the support sleeve 6 needs to be installed in the landing gear shaft 7, the open end of the support sleeve 6 faces inwards, and the annular spigot at the circular closed end is clamped in the corresponding clamping groove position of the landing gear shaft 7.
The brake cooling control arrangement in this embodiment is placed in the landing gear axle 7 by the fixed wheel nut 5; the inner surface at the port of the undercarriage axle 7 is a threaded surface matched with the outer surface of the fixed wheel nut; a convex key 10 on the circumference of the shell of the tire pressure sensor 2 is inserted into a convex key groove on the inner surface of the wheel nut 5 to limit the radial rotation of the brake cold control assembly; the fixed wheel nut 5 is fixedly connected with the tire pressure sensor 2 through a screw. The outer circumferential surface at the port of the outer end of the shell of the tire pressure sensor 2 is provided with a radially protruding annular seam allowance 8, and after the brake cold control assembly is installed in the undercarriage axle 7, the inner end surface of the annular seam allowance 8 is attached to the outer end surface of the fixed wheel nut 5, so that the axial leap of the brake cold control assembly is limited. The screws are screwed into the threaded holes 9 in the tire pressure sensor 2 through the threaded holes reserved on the circumference of the wheel nut 8. To this end, the fixing of the assembly of the tire pressure sensor 2, the wheel speed sensor 3 and the brake cooling motor 4 to the aircraft landing gear shaft 7 is completed.
The blisk of the brake cooling fan 1 in this embodiment is fixedly mounted on the long axis of the brake cooling motor 5 and is fixed by a lock washer and a nut. The pressure sensor 11 of the tire pressure sensor 2 is screwed onto a corresponding joint on the outer half hub of the wheel of the airplane. The brake cooling fan 1 in the embodiment of the invention can be an airfoil-shaped five-blade fan.
The tire pressure sensor 2 in the present embodiment is a hollow structure, takes the annular spigot 8 as an interface, can randomly rotate at the left side, and is a rotating part of the shell; the right side is arranged in the landing gear shaft 7 and is a static part of the shell; the shell of the rotating part of the shell is provided with a bearing 15 which is used for supporting a long shaft in a high-speed working state after the brake cooling motor 4 is started; a shifting fork structure 12 is arranged on the rotating part of the shell and is matched with the existing structure on the airplane wheel for transmission; a radial convex key 10 is processed on the outer circumferential surface of the static part of the shell, a threaded hole 9 is processed at the symmetrical position of the convex key on the outer circumferential surface, an annular spigot 8 which protrudes in the radial direction is arranged on the outer circumferential surface at the port of the static part of the shell, a hollow shaft is arranged in the static part of the shell, and the hollow shaft end is designed into a shifting fork structure 16; the rotating part rotates together with a hollow shaft in the static part, and the mechanical transmission of the rotating speed of the airplane wheel is realized through the matching transmission of a shifting fork structure 16 and a shifting fork structure 17 of the airplane wheel speed sensor 3; thereby realizing the function of detecting the tire pressure.
The wheel speed sensor 3 in the present embodiment is a hollow structure.
The brake cooling motor 4 in this embodiment may be a three-phase ac motor, with a voltage of 115V, a frequency of 400Hz, and a rotation speed of 11000 r/min. In order to meet the structural layout of the airplane wheel speed sensor 3 and the tire pressure sensor 2, 6 fixed threaded holes are uniformly distributed on the end surface of the shell, which is close to the airplane wheel speed sensor 3; two wire pressing tables 18 are designed at the rear end of the shell; two groups of wiring grooves 19 are designed on the circumferential shell; a long shaft structure is adopted.
The support sleeve 6 in this embodiment may be made of teflon, and has a three-piece opening structure. The round necking end is provided with an annular spigot; the thickness of the three open ends is thickened, and the three open ends can be spread after the brake cooling motor 4 penetrates into the three open ends, so that the inner walls of the brake cooling motor 4, the support sleeve 6 and the lifting frame shaft 7 are tightly attached to play a role in supporting and fixing.
When the multifunctional aircraft brake cooling control device provided by the embodiment works, the pressure sensor 11 of the tire pressure sensor 2 collects the air pressure in the tires of the aircraft, and a tire pressure signal is output through a leading-out cable; the tire pressure sensor 2 rotates along with the airplane wheel, the rotation of the airplane wheel is transmitted to the airplane wheel speed sensor 3, and the airplane wheel speed sensor 3 outputs a sinusoidal voltage signal in direct proportion to the rotation speed of the airplane wheel; the brake cooling motor 4 drives the brake cooling fan 1 to rotate at a high speed under the action of an on-machine power supply, and generates airflow to cool a brake wheel; the integration of the functions of detecting the pressure of the airplane tire, detecting the speed of the airplane wheel and cooling the brake is realized. On the basis of the existing principle function technology, ingenious and reasonable structural design is carried out, the maximum utilization of the internal space of the landing gear shaft is realized, the integration of multiple functions is realized, and the multifunctional aircraft brake cooling control device is designed.
Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (9)
1. A multifunctional aircraft brake cooling control device, characterized by comprising: the device comprises a brake cooling fan, a tire pressure sensor, an airplane wheel speed sensor and a brake cooling motor;
the airplane wheel speed sensor is provided with a central shaft hole, the central shaft hole penetrates through a long shaft of the brake cooling motor, the airplane wheel speed sensor is fixedly arranged at one end of the brake cooling motor, and the airplane wheel speed sensor and the brake cooling motor are positioned in an airplane wheel shaft; the wheel speed sensor configured to monitor the speed of aircraft tires;
the tire pressure sensor is provided with a central shaft hole, the central shaft hole penetrates through a long shaft of the brake cooling motor, the tire pressure sensor is fixedly arranged at one end of the airplane wheel speed sensor, and the tire pressure sensor is positioned outside the airplane wheel shaft;
the tire pressure sensor is provided with a pressure sensor connected with an aircraft tire, is configured to rotate synchronously with the aircraft tire, and monitors the pressure of the aircraft tire through the pressure sensor;
the brake cooling fan is arranged at the end part of a long shaft of the brake cooling motor and is configured to rotate under the driving of the long shaft of the brake cooling motor so as to generate airflow for carrying out heat dissipation and cooling on the airplane tire; the brake cooling fan is an airfoil-shaped five-blade fan.
2. The multifunctional aircraft brake cooling control device of claim 1, wherein the tire pressure sensor comprises: the brake cooling motor comprises a shell rotating part and a shell static part, wherein one end of the shell static part, which is close to the brake cooling motor, is provided with a tire pressure leading-out cable;
a bearing is installed at one end, close to the brake cooling fan, of the shell rotating part, a long shaft of the brake cooling motor is fixed and supported through the bearing, two shifting fork structures are arranged on the maximum excircle of the shell rotating part, the shifting fork structures are fixed on the airplane tire and rotate synchronously with the airplane tire, and the pressure sensor arranged on the shell rotating part is installed in an outer half hub of the airplane tire and communicated with air pressure in the airplane tire;
the aircraft wheel speed sensor is characterized in that a hollow shaft is arranged in the static part of the shell, the shell of the hollow shaft rotates along with the rotating part of the shell, and a first shifting fork structure is arranged at one end, close to the wheel speed sensor, of the hollow shaft and is configured to transmit the rotation of an aircraft tire to the wheel speed sensor.
3. The multifunctional aircraft brake cooling control device of claim 2, wherein a second fork structure is disposed at an end of the wheel speed sensor close to the tire pressure sensor, the second fork structure is fixed to the first fork structure in a matched manner, and a wheel speed leading-out cable is disposed at an end of the wheel speed sensor close to the brake cooling motor through the second fork structure and fixed to the tire pressure sensor.
4. A multi-function aircraft brake cooling control apparatus according to claim 2, wherein the stationary portions of the housings of the brake cooling motor, the wheel speed sensor and the tire pressure sensor are mounted within the axle of the landing gear axle.
5. The multi-function aircraft brake cooling control device of claim 4, wherein said brake cooling motor comprises a cylindrical housing, a cooling motor disposed in said cylindrical housing, and said long shaft disposed on said cooling motor;
two wiring grooves are formed in two sides of the cylindrical shell and used for correspondingly arranging leading-out cables of the tire pressure sensors and the wheel speed sensors one by one, and the width and the depth of each wiring groove are larger than those of the leading-out cables.
6. The multifunctional aircraft brake cooling control device of claim 5, wherein a socket of the brake cooling motor is arranged on the rear end cover of the cylindrical shell, and two wire pressing platforms are further arranged on the rear end cover of the cylindrical shell and used for fixing the leading-out cables of the tire pressure sensor and the wheel speed sensor in a one-to-one correspondence manner.
7. The multifunctional aircraft brake cooling control device of claim 6, wherein flanges are provided at both ends of the wheel speed sensor and are fixed to the cylindrical housings of the tire pressure sensor and the brake cooling motor by screws, respectively.
8. The multifunctional aircraft brake cooling control device of any one of claims 4-7, further comprising: and the supporting sleeve is arranged outside the airplane wheel speed sensor and the brake cooling motor, the opening end of the supporting sleeve is one end close to the brake cooling motor, and the annular spigot at the round spigot end is clamped in the clamping groove position corresponding to the undercarriage wheel shaft.
9. A multifunctional aircraft brake cooling control device according to any one of claims 4-7, characterized in that the multifunctional aircraft brake cooling control device is mounted in the landing gear axle wheel through a fixed wheel nut, and the inner surface at the port of the landing gear axle is provided with a threaded surface which is matched with the outer surface of the fixed wheel nut; and the convex key on the circumference of the shell of the tire pressure sensor is inserted into the convex key groove on the inner surface of the nut of the fixed airplane wheel and is used for limiting the radial rotation of the multifunctional airplane brake cooling control device.
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| CN202010321706.3A CN111469817B (en) | 2020-04-22 | 2020-04-22 | Multifunctional aircraft brake cooling control device |
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| CN202010321706.3A CN111469817B (en) | 2020-04-22 | 2020-04-22 | Multifunctional aircraft brake cooling control device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3231364A1 (en) * | 1982-08-24 | 1984-03-01 | Dr.Ing.H.C. F. Porsche Ag, 7000 Stuttgart | Ventilation device for the brake in a motor vehicle |
| FR2718850B1 (en) * | 1994-04-13 | 1996-05-15 | Messier Bugatti | Aircraft landing gear tachometer. |
| FR2941438B1 (en) * | 2009-01-26 | 2011-03-04 | Technofan | VENTILATED WHEEL ASSEMBLY. |
| CN101774337B (en) * | 2010-01-08 | 2012-05-23 | 西北工业大学 | Real-time monitoring system and method of tire pressure of airplane |
| US9950701B2 (en) * | 2014-11-03 | 2018-04-24 | Goodrich Corporation | Tire pressure sensor with included position sensor |
| JP2016175507A (en) * | 2015-03-19 | 2016-10-06 | いすゞ自動車株式会社 | Tire pressure regulator |
| CN207403715U (en) * | 2017-10-26 | 2018-05-25 | 西安华欧精密机械有限责任公司 | A kind of airplane wheel quickly cooling device |
| CN108843709A (en) * | 2018-09-03 | 2018-11-20 | 夏长江 | A kind of vehicle bridge, brake apparatus and vehicle |
| CN209112157U (en) * | 2018-10-24 | 2019-07-16 | 西安航空制动科技有限公司 | On-board brake air cooling system with automatic control function |
| CN109307025B (en) * | 2018-11-06 | 2023-08-29 | 西安航空制动科技有限公司 | A brake cooling system for main engine wheel of multi-wheel system aircraft |
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