CN214295419U - Airplane wheel assembly for nondestructive testing of tire temperature and tire pressure - Google Patents
Airplane wheel assembly for nondestructive testing of tire temperature and tire pressure Download PDFInfo
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- CN214295419U CN214295419U CN202120377686.1U CN202120377686U CN214295419U CN 214295419 U CN214295419 U CN 214295419U CN 202120377686 U CN202120377686 U CN 202120377686U CN 214295419 U CN214295419 U CN 214295419U
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Abstract
The utility model discloses an aircraft wheel assembly for nondestructive testing of tire temperature and tire pressure, which comprises an aircraft wheel, a pressure sensor and a temperature sensor, wherein the aircraft wheel comprises a wheel hub and a movable wheel hub sleeved at one end of the wheel hub, an annular gap is arranged between the wheel hub and the movable wheel hub, and the annular gap is communicated with a tire cavity; the hub is provided with a mounting hole communicated with the annular gap, the mounting hole is respectively provided with the pressure sensor and the temperature sensor in a sealing manner, the pressure sensor and the temperature sensor are respectively and electrically connected with an electric connector, and the electric connector is provided with a data reading interface; the utility model discloses be provided with pressure sensor and temperature sensor on the wheel hub of aircraft wheel to link to each other it with electric connector, obtain pressure and temperature in the tire cavity through connecting and reading electric connector's data, thereby can obtain tire pressure and child temperature under the gaseous condition in the loss-free tire cavity, realize nondestructive test promptly.
Description
Technical Field
The utility model relates to an aircraft wheel technical field especially relates to an aircraft wheel subassembly of nondestructive test child temperature tire pressure.
Background
Aircraft brake wheels generally include a wheel assembly, a brake device. The airplane wheel assembly and the matched tires are used for parking and sliding the airplane on the ground, bearing impact load during landing and the like. When the airplane takes off continuously, the temperature of braking wheels and tires can be reduced by means of forced heat dissipation such as air blowing; when the temperature is unstable, the tire pressure is also unstable. When the forced heat dissipation is not cooled to below the specified temperature, there is a considerable risk of continuous take-off, because after the aircraft lands, the heat of the landing brake before the aircraft lands is not dissipated, and the heat of the subsequent brake is accumulated, which may cause high-temperature tire burst in the aircraft braking process.
The tire pressure is measured as a daily inspection item before the takeoff of the airplane, the inflation pressure generally has a strict range (such as 0-0.05 MPa), and the general detection mode is that the tire pressure is directly measured on the airplane wheel through a pressure gauge, a temperature measuring gun and the like; however, before and after the detection in this way, a small part of gas is inevitably leaked, so that the tire pressure is slightly inconsistent with the tire pressure during measurement. When the tire pressure is inconsistent with the specified tire pressure, the operator must continue to inflate or deflate until the tire pressure meets the specified requirements, which makes the operation cumbersome.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an aircraft wheel subassembly of nondestructive test child temperature tire pressure to solve the problem that above-mentioned prior art exists, be provided with pressure sensor and temperature sensor on the wheel hub of aircraft wheel, and link to each other it with electric connector, obtain pressure and temperature in the tire cavity through connecting and reading electric connector's data, thereby can obtain tire pressure and child temperature under the gaseous condition in the loss tire cavity, realize nondestructive test promptly.
In order to achieve the above object, the utility model provides a following scheme:
the utility model provides an aircraft wheel assembly for nondestructive testing of tire temperature and tire pressure, which comprises an aircraft wheel, a pressure sensor and a temperature sensor, wherein the aircraft wheel comprises a wheel hub and a movable wheel hub sleeved at one end of the wheel hub, an annular gap is arranged between the wheel hub and the movable wheel hub, and the annular gap is communicated with a tire cavity; the hub is provided with a mounting hole communicated with the annular gap, the mounting hole is respectively provided with the pressure sensor and the temperature sensor in a sealing manner, the pressure sensor and the temperature sensor are respectively electrically connected with an electric connector, and the electric connector is provided with a data reading interface.
Preferably, the pressure sensor is in threaded connection with the mounting hole, and the temperature sensor is in threaded connection with the mounting hole.
Preferably, a counter bore is arranged at the opening end of the mounting hole, a pressure sensor annular groove is arranged at the root of the thread of the pressure sensor, and a sealing ring is arranged in a space formed by the counter bore and the pressure sensor annular groove.
Preferably, a counter bore is arranged at the opening end of the mounting hole, a temperature sensor annular groove is arranged at the root of the thread of the temperature sensor, and a sealing ring is arranged in a space formed by the counter bore and the temperature sensor annular groove.
Preferably, the mounting end face of the mounting hole is provided as a flat surface.
Preferably, the electrical connector is mounted on the wheel by screws in a position close to the centre of the wheel.
Preferably, the electrical connector is provided with a dust cap arrangement.
Preferably, the dustproof cap structure comprises a dustproof cap and a dustproof cap fixing part, the dustproof cap and the dustproof cap fixing part are connected through a flexible connecting band, the dustproof cap fixing part is installed on the electric connector, and the dustproof cap is buckled on the data reading interface.
The utility model discloses for prior art gain following technological effect:
(1) the utility model discloses be provided with pressure sensor and temperature sensor on the wheel hub of aircraft wheel to link to each other it with the electric connector, obtain pressure and temperature in the tire cavity through connecting and reading the data of electric connector, thereby can obtain tire pressure and child temperature under the condition of not losing the gas in the tire cavity, realize nondestructive test promptly, do not need frequent aerifing or gassing, easy operation is swift;
(2) the utility model discloses pressure sensor threaded connection is in the mounting hole, and temperature sensor threaded connection is in the mounting hole, through threaded connection, can be with stable the fixing on the wheel hub of wheel of pressure sensor and temperature sensor, can conveniently dismantle and be convenient for change or maintenance when pressure sensor or temperature sensor break down;
(3) the utility model discloses the open end of mounting hole is provided with the counter bore, and pressure sensor's screw thread root is provided with pressure sensor annular groove, is provided with the sealing washer in the space that counter bore and pressure sensor annular groove formed, through the cooperation of pressure sensor annular groove and counter bore, can make the sealing washer block the gap between sealed pressure sensor and the mounting hole to can realize simultaneously axially and radially sealing, and then reach better sealed effect, avoid the gas in the tire cavity to reveal;
(4) the utility model discloses the open end of mounting hole is provided with the counter bore, and temperature sensor's screw thread root is provided with temperature sensor annular groove, is provided with the sealing washer in the space that counter bore and temperature sensor annular groove formed, through the cooperation of temperature sensor annular groove and counter bore, can make the sealing washer block the gap between sealed temperature sensor and the mounting hole to can realize simultaneously axially and radially sealing, and then reach better sealed effect, avoid the gas in the tire cavity to reveal;
(5) the utility model discloses be provided with dustproof block structure, utilize dustproof block structure to realize keeping dustproof to the sealed of electric connector's data reading interface to, dustproof block structure includes dustproof block, dustproof block fixed part and connects the flexonics area between the two, when examining, can avoid the dustproof block to take the back and lose.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive labor.
Fig. 1 is a schematic view of an aircraft wheel assembly of the present invention;
FIG. 2 is a cross-sectional view A-A of FIG. 1;
FIG. 3 is a cross-sectional view B-B of FIG. 1;
FIG. 4 is an enlarged view of section I of FIG. 2;
FIG. 5 is an enlarged view of a portion II of FIG. 3;
FIG. 6 is a schematic view of the wheel configuration;
FIG. 7 is a schematic diagram of a pressure sensor;
FIG. 8 is a schematic diagram of a temperature sensor;
FIG. 9 is a schematic view of an electrical connector;
FIG. 10 is a schematic view of a dust cap;
wherein, 1, a hub; 2. a seal ring; 3. a pressure sensor; 31. a pressure sensor annular groove; 32. a pressure sensor cable; 4. an electrical connector; 41. a data reading interface; 42. a cable hole; 43. screw holes; 5. a dust-proof cap structure; 51. a dust-proof cap; 52. a dust cap fixing portion; 53. a flexible connecting band; 6. a screw; 7. a temperature sensor; 71. a temperature sensor annular groove; 72. a temperature sensor cable; 8. a movable hub; 11. an annular gap; 12. a gas passage hole; 13. mounting holes; 14. a counter bore; 15. mounting an end face; 16. the screw is threaded.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
The utility model aims at providing an aircraft wheel subassembly of nondestructive test child temperature tire pressure to solve the problem that prior art exists, be provided with pressure sensor and temperature sensor on the wheel hub of aircraft wheel, and link to each other it with electric connector, obtain pressure and temperature in the tire cavity through connecting and reading electric connector's data, thereby can obtain tire pressure and child temperature under the condition of the gas in the non-loss tire cavity, realize nondestructive test promptly.
In order to make the above objects, features and advantages of the present invention more comprehensible, the present invention is described in detail with reference to the accompanying drawings and the detailed description.
As shown in fig. 1-10, the utility model provides an aircraft wheel assembly for nondestructive testing of tire temperature tire pressure, including wheel, pressure sensor 3 and temperature sensor 7, wherein, the wheel refers to the aircraft wheel, the wheel includes wheel hub 1 and the movable wheel hub 8 that the cover was established at wheel hub 1 one end, is provided with seal structure between movable wheel hub 8 and wheel hub 1 to fix through half snap ring; an annular gap 11 is arranged between the wheel hub 1 and the movable wheel hub 8 and close to the middle part of the wheel, the annular gap 11 is communicated with a tire cavity, and the tire cavity refers to a gas cavity formed between the tire and the wheel; the hub 1 is provided with a mounting hole 13 communicated with the annular gap 11, and the mounting hole 13 obliquely penetrates through the hub 1 and leads to the annular gap 11 after passing through a section of gas passage hole 12; the mounting holes 13 are respectively provided with the pressure sensor 3 and the temperature sensor 7 in a sealing manner, and it should be noted that the pressure sensor 3 and the temperature sensor 7 can be arranged in the mounting holes 13 in an interference fit manner, can also be connected in the mounting holes 13 through threads, or are provided with bolts at the end parts, and are arranged on the hub 1 by means of the bolts to realize connection; the pressure sensor 3 and the temperature sensor 7 are respectively electrically connected with the electric connector 4, the pressure sensor 3 and the temperature sensor 7 can be connected with the same electric connector 4, and can also be respectively connected with one electric connector 4, the electric connector 4 is provided with a data reading interface 41, the data reading interface 41 comprises pins in plug connection, and the pins connected with the data reading interface 41 through external equipment can realize data transmission to detect the pressure or temperature inside the tire cavity, namely the tire pressure and the tire temperature; the tire pressure and the tire temperature can be obtained under the condition that the gas in the tire cavity is not lost, so that nondestructive detection is realized, frequent inflation or deflation is not needed, and the operation is simple and rapid.
As shown in fig. 2-8, one side of the pressure sensor 3 is provided with a screw thread, the mounting hole 13 is a threaded hole, and the two can be matched with each other, for example, both are M10 × 1, and the pressure sensor 3 can be connected with the mounting hole 13 by the screw thread; one side of the temperature sensor 7 is provided with threads, the temperature sensor 7 can be in threaded connection with the mounting hole 13, and after the temperature sensor is mounted, the probe of the pressure sensor 3 and the probe of the temperature sensor 7 are positioned inside the mounting hole 13 and are communicated with the tire cavity through the gas passage hole 12; through threaded connection, can be with stable the fixing on the wheel hub 1 of wheel of pressure sensor 3 and temperature sensor 7, can conveniently dismantle and be convenient for change or maintenance when pressure sensor 3 or temperature sensor 7 break down.
As shown in fig. 2, 4, and 6-7, a counter bore 14 is provided at an opening end of the mounting hole 13, and a depth of the counter bore 14 may be smaller than or equal to a width of the sealing ring 2, so that the sealing ring 2 can be pressed to a certain extent after the pressure sensor 3 is mounted, and the sealing ring can be attached to a peripheral wall surface more tightly after being deformed, thereby achieving a better sealing effect; the root of the thread of the pressure sensor 3 is provided with a pressure sensor annular groove 31, a seal ring 2 is arranged in a space formed by the counter bore 14 and the pressure sensor annular groove 31, and the seal ring 2 can be an O-shaped seal ring, refer to HB 4-56-1987 circular section rubber seal structure; through the cooperation of the annular groove 31 of the pressure sensor and the counter bore 14, the sealing ring 2 can block a gap between the sealing pressure sensor 3 and the mounting hole 13, and can realize sealing in the axial direction and the radial direction simultaneously, so that a better sealing effect is achieved, and gas leakage in a tire cavity is avoided.
As shown in fig. 3, 4, 6 and 8, a counter bore 14 is arranged at the opening end of the mounting hole 13, and the depth of the counter bore 14 can be smaller than or equal to the width of the sealing ring 2, so that the sealing ring 2 can be extruded to a certain extent after the temperature sensor 7 is mounted, and the sealing ring can be attached to the surrounding wall surface more tightly after being deformed, thereby achieving better sealing effect; the root of the thread of the temperature sensor 7 is provided with a temperature sensor annular groove 71, and a sealing ring 2 is arranged in a space formed by the counter bore 14 and the temperature sensor annular groove 71; through the cooperation of the temperature sensor annular groove 71 and the counter bore 14, the sealing ring 2 can block and seal a gap between the temperature sensor 7 and the mounting hole 13, and can realize sealing in the axial direction and the radial direction simultaneously, so that a better sealing effect is achieved, and gas leakage in a tire cavity is avoided.
As shown in fig. 6, the mounting end face 15 of the mounting hole 13 is provided as a flat surface, the mounting end face 15 may be machined by machining on the hub 1, or may be formed by molding when the hub 1 is cast or forged, and the mounting end face 15 is provided so that the pressure sensor 3 and the temperature sensor 7 are mounted on the flat mounting end face 15, whereby a good seal can be obtained after mounting.
As shown in fig. 1-2 and 9, the electrical connector 4 may be mounted on the wheel by screws 6 at a position close to the center of the wheel, for example, the mounting portion of the electrical connector 4 may be square, four screw holes 43 are provided at four corners of the square, and of course, the mounting portion may also be round or in other shapes, and screw threaded holes 16 need to be correspondingly machined at positions on the hub 1 corresponding to the screw holes 43; the pressure sensor 3 and the temperature sensor 7 are installed at adjacent positions by using the screws 6 through the screw holes 43 and the screw threaded holes 16, and then the pressure sensor 3 and the temperature sensor 7 are connected to the cable hole 42 of the electric connector 4 through the pressure sensor cable 32 and the temperature sensor cable 72 respectively to realize connection; in addition, the electric connector 4 is close to the center of the wheel and is subjected to smaller centrifugal force when the wheel rotates, the electric connector 4 can be protected to be connected and loosened or fall off to a certain extent, the pressure sensor 3 and the temperature sensor 7 are obliquely inserted into the mounting hole 13 in the centrifugal direction and are connected through threads, and the influence on the loosening is smaller after the centrifugal action is carried out, so that the electric connector can be directly arranged at the position, far away from the center of the wheel, of the edge of the hub 1.
As shown in fig. 1-2, the electrical connector 4 may be provided with a dust cap structure 5, because the electrical connector 4 needs to be connected with an external device to read data of the pressure sensor 3 and the temperature sensor 7, and the dust cap structure 5 can prevent dust or rain water from affecting the connection portion after the electrical connector 4 is fastened.
As shown in fig. 9-10, the dust-proof cap structure 5 includes a dust-proof cap 51 and a dust-proof cap fixing portion 52, the dust-proof cap 51 and the dust-proof cap fixing portion 52 are connected by a flexible connecting band 53, the dust-proof cap fixing portion 52 is mounted on the electrical connector 4, specifically, the dust-proof cap fixing portion 52 may be the same as the mounting structure of the electrical connector 4, that is, the same screw hole 43 position is adopted, at this time, the dust-proof cap fixing portion 52 may be fixed on the electrical connector 4, it should be noted that, in order to expose the data reading interface 41 of the electrical connector 4, a circular hole may be formed in the middle of the dust-proof cap fixing portion 52, after the dust-proof cap fixing portion 52 is inserted into the data reading interface 41 of the electrical connector 4, the dust-proof cap fixing portion is matched and fixed with the screw hole 43 on the electrical connector 4, and is connected and fixed by a screw 6; due to the existence of the flexible connecting band 53, the dust cap 51 does not need to be specially stored after being separated from the data reading interface 41, the dust cap 51 can be prevented from being lost, and after detection is finished, the dust cap 51 is buckled on the data reading interface 41 to realize dust prevention protection.
The working principle of the utility model is as follows:
the air in the tire cavity formed between the wheel and the tire is contacted with the temperature sensor 7 and the pressure sensor 3 through the annular gap 11 and the air passage hole 12, and meanwhile, the air leakage is prevented through the sealing ring 2. The temperature sensor 7 and the pressure sensor 3 transmit the sensed pressure and temperature signals of the gas in the tire cavity to the electric connector 4 through the temperature sensor cable 72 and the pressure sensor cable 32 respectively, when the ground measuring equipment is connected with the electric connector 4, the temperature sensor 7 and the pressure sensor 3 are electrified, the ground measuring equipment can read the pressure and temperature signals and convert the pressure and temperature signals into pressure and temperature numerical values, and at the moment, the pressure and temperature of the gas in the tire cavity can be read without loss and are consistent with the real-time temperature and air pressure of the gas in the tire cavity.
Without reading pressure and temperature:
the dust cap 51 of the dust cap structure 5 is covered on the data reading interface 41 of the electric connector 4 to prevent dust from entering;
reading pressure and temperature:
the dust cap 51 of the dust cap structure 5 is opened, an external device is connected to the data reading interface 41 of the electrical connector 4, and pressure and temperature signals are read.
The utility model discloses a concrete example is applied to explain the principle and the implementation mode of the utility model, and the explanation of the above example is only used to help understand the method and the core idea of the utility model; meanwhile, for the general technical personnel in the field, according to the idea of the present invention, there are changes in the concrete implementation and the application scope. In summary, the content of the present specification should not be construed as a limitation of the present invention.
Claims (8)
1. The utility model provides an aircraft wheel subassembly of nondestructive test child temperature tire pressure which characterized in that: the tire wheel comprises a wheel, a pressure sensor and a temperature sensor, wherein the wheel comprises a wheel hub and a movable wheel hub sleeved at one end of the wheel hub, an annular gap is formed between the wheel hub and the movable wheel hub, and the annular gap is communicated with a tire cavity; the hub is provided with a mounting hole communicated with the annular gap, the mounting hole is respectively provided with the pressure sensor and the temperature sensor in a sealing manner, the pressure sensor and the temperature sensor are respectively electrically connected with an electric connector, and the electric connector is provided with a data reading interface.
2. An aircraft wheel assembly for non-destructive testing of warm tire pressure as claimed in claim 1 wherein: the pressure sensor is in threaded connection with the mounting hole, and the temperature sensor is in threaded connection with the mounting hole.
3. An aircraft wheel assembly for non-destructive testing of warm tire pressure as claimed in claim 2, wherein: the opening end of the mounting hole is provided with a counter bore, the thread root of the pressure sensor is provided with a pressure sensor annular groove, and a sealing ring is arranged in a space formed by the counter bore and the pressure sensor annular groove.
4. An aircraft wheel assembly for non-destructive testing of warm tire pressure as claimed in claim 2, wherein: the opening end of the mounting hole is provided with a counter bore, the thread root of the temperature sensor is provided with a temperature sensor annular groove, and a sealing ring is arranged in a space formed by the counter bore and the temperature sensor annular groove.
5. An aircraft wheel assembly for non-destructive testing of warm tire pressure as claimed in any one of claims 1 to 4 wherein: the installation end face of the installation hole is set to be a plane.
6. An aircraft wheel assembly for non-destructive testing of warm tire pressure as in claim 5 wherein: the electric connector is installed on the wheel close to the center of the wheel through screws.
7. An aircraft wheel assembly for non-destructive testing of warm tire pressure as in claim 6 wherein: the electric connector is provided with a dustproof cap structure.
8. An aircraft wheel assembly for non-destructive testing of warm tire pressure as in claim 7 wherein: the dustproof cap structure comprises a dustproof cap and a dustproof cap fixing part, the dustproof cap and the dustproof cap fixing part are connected through a flexible connecting band, the dustproof cap fixing part is installed on the electric connector, and the dustproof cap is buckled on the data reading interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120377686.1U CN214295419U (en) | 2021-02-18 | 2021-02-18 | Airplane wheel assembly for nondestructive testing of tire temperature and tire pressure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120377686.1U CN214295419U (en) | 2021-02-18 | 2021-02-18 | Airplane wheel assembly for nondestructive testing of tire temperature and tire pressure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214295419U true CN214295419U (en) | 2021-09-28 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120377686.1U Active CN214295419U (en) | 2021-02-18 | 2021-02-18 | Airplane wheel assembly for nondestructive testing of tire temperature and tire pressure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214295419U (en) |
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2021
- 2021-02-18 CN CN202120377686.1U patent/CN214295419U/en active Active
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