CN219008141U - Front nose wheel steering angle measuring device for airplane for load testing vehicle - Google Patents
Front nose wheel steering angle measuring device for airplane for load testing vehicle Download PDFInfo
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- CN219008141U CN219008141U CN202223216360.4U CN202223216360U CN219008141U CN 219008141 U CN219008141 U CN 219008141U CN 202223216360 U CN202223216360 U CN 202223216360U CN 219008141 U CN219008141 U CN 219008141U
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Abstract
The utility model provides a nose wheel steering angle measuring device of an airplane for a test load vehicle, which relates to the technical field of test load vehicles, and comprises a shaft sleeve, a transmission device and an angle sensor, wherein the shaft sleeve is sleeved on a main shaft of a nose landing gear of a real airplane of the test load vehicle and synchronously rotates with the main shaft; according to the utility model, the shaft sleeve is matched with the transmission device, so that the detection shaft of the angle sensor and the main shaft of the real aircraft nose landing gear synchronously rotate, the rotation angle of the real aircraft nose landing gear can be measured accurately in real time, the accuracy of measuring the rotation angle of the aircraft nose wheel is ensured, the aircraft nose landing gear can be effectively protected from being damaged due to overlarge rotation angle, and reliable data support is provided for the design and research and development of the wheel-holding aircraft tractor.
Description
Technical Field
The utility model relates to the technical field of test load vehicles, in particular to a front nose wheel turning angle measuring device of an airplane for a test load vehicle.
Background
The aircraft tractor is a guarantee device for towing an aircraft on the airport ground, can be used for moving large aircraft parts or aircraft in the aircraft manufacturing process, and generally comprises a rod type tractor and a rodless type tractor, wherein the rodless type tractor is of a wheel-holding type structure, and does not need to use a traction rod for traction operation, so that the need of the aircraft on the traction rod is eliminated, the labor intensity of staff is relieved, the working efficiency of aircraft traction is greatly improved, and meanwhile, the risk hidden danger when the tractor is in butt joint with the traction rod can be effectively avoided, so that the aircraft tractor is widely used. Since a wheel-holding type rodless tractor usually directly contacts the nose landing gear of an aircraft when the aircraft is towed, the reliability and the safety of the wheel-holding type rodless tractor are important.
The test load vehicle for testing the rodless aircraft tractor is provided with a bearing platform, a cab, a power control system, a hydraulic control system and an electrical control system are arranged on the bearing platform, the front end of the bearing platform is provided with a nose wheel device, the nose wheel device comprises a simulated landing gear, an aircraft test wheel, a rotating shaft core, a positioning shaft sleeve, a rotating torque measuring bracket, a rotating positioning pin shaft, an overstretching positioning bracket, an overstretching positioning pin, a traction force sensor, a torque sensor and an angle sensor, wherein the angle sensor is connected with the upper end of the rotating torque measuring bracket, the angle sensor can measure the rotation angle of the simulated landing gear so as to avoid over-rotation, but the front landing gear of the aircraft of the test vehicle does not adopt a real aircraft landing gear, the simulation effect is effective, the corresponding rotation angle measured data is not accurate enough, and the corresponding rotation angle parameter of the front landing gear of the aircraft can not be truly reflected when the tractor pulls the front landing gear of the aircraft, although the real aircraft landing gear can be directly applied to the test vehicle, so that the test vehicle has good simulation effect, but because the structure of the front landing gear of the real aircraft is complex, the original angle measuring sensor is used by an avionics system and can not be directly compatible with the electrical system of the test load vehicle, and therefore, the original angle measuring sensor can not realize the measurement of the rotation angle of the front landing gear of the real aircraft, namely the rotation angle of the front nose wheel of the aircraft.
Disclosure of Invention
The utility model aims to provide an aircraft nose wheel steering angle measuring device for a test load vehicle, which aims to solve the technical problem that the test load vehicle in the prior art cannot accurately measure the aircraft nose wheel steering angle; the preferred technical scheme of the technical schemes provided by the utility model has a plurality of technical effects; details are set forth below.
In order to achieve the above purpose, the present utility model provides the following technical solutions:
the utility model provides an aircraft nose wheel steering angle measuring device for a test load vehicle, which comprises a shaft sleeve, a transmission device and an angle sensor, wherein: the shaft sleeve is sleeved on a main shaft of a nose landing gear of a real airplane of the test load car and rotates synchronously with the main shaft; the detection shaft of the angle sensor is in transmission connection with the shaft sleeve through the transmission device, and the detection shaft synchronously rotates with the shaft sleeve through the transmission device.
Preferably, the transmission device comprises a gear transmission mechanism, a rotary gear ring is fixedly arranged on the top side of the shaft sleeve, a detection gear is fixedly sleeved on the detection shaft, and the detection gear is arranged on the detection shaft, wherein:
the detection gear is in transmission connection with the rotary gear ring through the gear transmission mechanism;
the rotation speed of the detection gear is the same as that of the rotary gear ring.
Preferably, the gear transmission mechanism comprises an input gear mechanism and an output gear mechanism which are arranged in a meshed manner, wherein: the input gear mechanism is meshed with the rotary gear ring; the output gear mechanism is meshed with the detection gear.
Preferably, the input gear mechanism comprises an input gear and an input shaft, wherein: the input gear is sleeved on the input shaft; the input gear is meshed with the rotary ring gear.
Preferably, the output gear mechanism comprises a transition gear, an output shaft and an output gear, wherein: the transition gear is sleeved on the output shaft and meshed with the input gear; the output gear is sleeved on the output shaft, and the output gear is meshed with the detection gear.
Preferably, the gear assembly comprises a gearbox, and the gear assembly is disposed within the gearbox.
Preferably, the gearbox comprises a first box and a second box, wherein: the input gear mechanism is arranged in the first box body; the output gear mechanism is arranged in the second box body; the first box body is detachably connected with the second box body.
Preferably, the first tank and the second tank are detachably connected by a transition flange.
Preferably, the detection gear is disposed in the second case.
Preferably, a first connecting hole is formed in the second box body, and a second connecting hole is formed in the position, corresponding to the first connecting hole, of the shell of the angle sensor; threaded fasteners pass through the corresponding first and second connection holes to connect the angle sensor to the second housing.
The device for measuring the nose wheel steering angle of the airplane for testing the load vehicle has the following advantages:
the device for measuring the nose wheel angle of the airplane for the test load vehicle comprises a shaft sleeve, a transmission device and an angle sensor, wherein the shaft sleeve is sleeved on a main shaft of a nose landing gear of the real airplane of the test load vehicle, and in the working process, the shaft sleeve synchronously rotates along with the main shaft, so that the shaft sleeve can effectively transfer the action of the nose landing gear of the real airplane.
The detection shaft of the angle sensor is in transmission connection with the shaft sleeve through the transmission device, the detection shaft is in synchronous rotation with the shaft sleeve through the transmission device, the transmission device can effectively transmit the rotation motion of the shaft sleeve to the detection shaft of the angle sensor, and the detection shaft and the main shaft of the nose wheel of a real aircraft synchronously move, so that the rotation angle of the nose wheel of the aircraft can be measured truly, accurately and in real time, the nose wheel of the aircraft can be protected from being damaged due to overlarge rotation angle, and reliable data support is provided for the design and research and development of the wheel-holding type tractor.
Drawings
In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the structure of the present utility model as shown in FIG. 2;
fig. 3 is a schematic diagram of the transmission structure of the detection gear, the gear transmission mechanism and the rotary gear ring of the present utility model.
Reference numerals
1. A shaft sleeve; 11. rotating the gear ring; 2. a transmission device; 21. an input gear mechanism; 211. an input shaft; 212. an input gear; 22. an output gear mechanism; 221. a transition gear; 222. an output shaft; 223. an output gear; 23. a gear box; 231. a first case; 232. a second case; 233. a transition flange; 3. an angle sensor; 31. a detection shaft; 32. detecting a gear; 33. a housing.
Detailed Description
In order to make the objects, technical solutions and advantages of the present utility model more apparent, the technical solutions of the present utility model will be described in detail below. It will be apparent that the described embodiments are only some, but not all, embodiments of the utility model. All other embodiments, based on the examples herein, which are within the scope of the utility model as defined by the claims, will be within the scope of the utility model as defined by the claims.
Example 1:
the utility model provides an aircraft nose wheel turning angle measuring device for a test load vehicle, which is shown by referring to fig. 1, and comprises a shaft sleeve 1, a transmission device 2 and an angle sensor 3.
The shaft sleeve 1 is sleeved on a main shaft of a nose landing gear of a real airplane of the test load car and rotates synchronously with the main shaft.
The detection shaft 31 of the angle sensor 3 is in transmission connection with the shaft sleeve 1 through the transmission device 2, and the detection shaft 31 rotates synchronously with the shaft sleeve 1 through the transmission device 2.
When the test load vehicle is used for testing the whole vehicle performance of the wheel-holding type aircraft tractor, the main shaft of the nose landing gear of the real aircraft of the test load vehicle rotates, the shaft sleeve 1 synchronously rotates, and at the moment, the detection shaft 31 of the angle sensor 3 synchronously rotates along with the rotation through the transmission device 2.
In the process, the shaft sleeve 1 and the transmission device 2 are matched with each other, so that the detection shaft 31 of the angle sensor 3 and the main shaft of the real aircraft nose landing gear synchronously rotate, the angle value of the real aircraft nose landing gear can be measured accurately in real time, the accuracy of measuring the angle of the nose wheel of the aircraft can be further ensured, the nose landing gear of the aircraft can be effectively protected from being damaged due to overlarge angle, and reliable data support is provided for the design and research and development of the wheel-holding type aircraft tractor.
Example 2:
example 2 is based on example 1:
as shown in fig. 1 and 3, the transmission device 2 includes a gear transmission mechanism, a rotary gear ring 11 is fixedly arranged on the top side of the shaft sleeve 1, and a detection gear 32 is fixedly sleeved on the end portion of the detection shaft 31.
The detection gear 32 is in transmission connection with the rotary gear ring 11 through the gear transmission mechanism, and the rotation speed of the detection gear 32 is the same as that of the rotary gear ring 11, so that the rotation angle of the detection gear 32 is ensured to be the same as that of the rotary gear ring 11.
Adopt gear drive, compact structure, transmission efficiency is high, and the reliability is good, can effectively with aircraft nose wheel's corner one to one transfer to angle sensor 3.
As an alternative embodiment, as shown in fig. 3, the gear transmission mechanism includes an input gear mechanism 21 and an output gear mechanism 22 which are disposed in engagement.
The input gear mechanism 21 meshes with the rotary ring gear 11 for input of power.
The output gear mechanism 22 meshes with the detection gear 32 for output of power.
As an alternative embodiment, as shown in fig. 3, the input gear mechanism 21 includes an input gear 212 and an input shaft 211, the input gear 212 is fitted over the input shaft 211, and the input gear 212 is meshed with the rotary ring gear 11.
Because the main shaft specification of the nose landing gear of the real aircraft is larger, the diameter of the rotary gear ring 11 of the corresponding shaft sleeve 1 is larger, and the angle sensor 3 is smaller, the input gear 212 adopts a pinion, and the diameter of the pinion is smaller than that of the rotary gear ring 11, so that the structure is more compact on the basis of ensuring an effective transmission rotation angle.
As an alternative embodiment, as shown in fig. 3, the output gear mechanism 22 includes a transition gear 221, an output shaft 222, and an output gear 223.
The transition gear 221 is sleeved on the output shaft 222, the transition gear 221 is meshed with the input gear 212, the output gear 223 is sleeved on the output shaft 222, and the output gear 223 is meshed with the detection gear 32.
Since the input gear 212 adopts a pinion gear, in order to effectively restore the nose wheel rotation angle, the transition gear 221 adopts a large gear, and specifically, the specific specifications of the input gear 212, the transition gear 221, the output gear 223 and the detection gear 32 can be set according to actual requirements, so that the rotation speeds of the rotary gear ring 11 and the detection shaft 31 need to be the same.
The rotational speeds described above are the same, and the rotational speeds do not include directions, and in actual setting, it is only necessary to ensure that the angular speeds of the rotary ring gear 11 and the detection shaft 31 are the same.
As an alternative embodiment, as shown in fig. 2, the gear assembly 2 comprises a gear box 23, said gear assembly being arranged within the gear box 23, the gear box 23 being used for installation and protection of said gear assembly.
As an alternative embodiment, as shown in fig. 2, the gear box 23 includes a first box 231 and a second box 232.
The input gear mechanism 21 is disposed in a first housing 231, and a first opening is provided in a side of the first housing 231 near the rotary ring gear 11, through which the input gear 212 is meshed with the rotary ring gear 11.
The output gear mechanism 22 is disposed in the second casing 232, and the first casing 231 is detachably connected to the second casing 232.
Adopt two box detachable structures, be convenient for its internal part's later maintenance.
As an alternative embodiment, as shown in fig. 2, the first tank 231 and the second tank 232 are detachably connected by a transition flange 233.
The first case 231 and the second case 232 are firmly connected by a flange connection structure.
As an alternative embodiment, as shown in fig. 2, the detection gear 32 is disposed in the second case 232, the second case 232 is provided with a second opening through which the end of the detection shaft 31 is inserted into the second case 232 and connected with the detection gear 32, so that the structure is more compact.
As an alternative embodiment, as shown in fig. 2, a first connection hole is provided on the second case 232, a second connection hole is provided on the housing 33 of the angle sensor 3 at a position corresponding to the first connection hole, and the number of the first connection hole and the second connection hole is set to be plural.
When the angle sensor 3 is assembled, the threaded fastener is inserted through the corresponding first connecting hole and the corresponding second connecting hole, so that the angle sensor 3 is connected to the second box 232, and the structure is firm.
When the utility model is actually used, a transitional steering alarm value can be set, and when the steering angle is too large in an experiment, the test load vehicle gives an alarm to prompt a tractor operator, so that the transitional steering is prevented from damaging the front landing gear of the airplane.
In the actual installation process, the mechanical structure of the real aircraft landing gear is not damaged, and the structural strength of the real aircraft landing gear is not affected on the premise of ensuring the accuracy of measuring the rotation angle.
In the description of the present application, it should be understood that the terms "upper," "lower," "inner," "outer," "top," "bottom," and the like indicate an orientation or a positional relationship based on that shown in the drawings, and are merely for convenience of description and simplicity of description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present application, the meaning of "a plurality", "a number" or "a plurality" is at least two, such as two, three, etc., unless explicitly defined otherwise.
In this application, unless specifically stated and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art as the case may be.
The foregoing is merely illustrative of the present utility model, and the present utility model is not limited thereto, and any person skilled in the art will readily recognize that variations or substitutions are within the scope of the present utility model. Therefore, the protection scope of the present utility model shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides a test load is automobile-used aircraft nose wheel angle measuring device which characterized in that, including axle sleeve, transmission and angle sensor, wherein:
the shaft sleeve is sleeved on a main shaft of a nose landing gear of a real airplane of the test load car and rotates synchronously with the main shaft;
the detection shaft of the angle sensor is in transmission connection with the shaft sleeve through the transmission device, and the detection shaft synchronously rotates with the shaft sleeve through the transmission device.
2. The device for measuring nose wheel turning angle of an aircraft for testing load vehicle according to claim 1, wherein the transmission device comprises a gear transmission mechanism, a rotary gear ring is fixedly arranged on the top side of the shaft sleeve, a detection gear is fixedly sleeved on the detection shaft, and the detection gear is arranged on the detection shaft, wherein:
the detection gear is in transmission connection with the rotary gear ring through the gear transmission mechanism;
the rotation speed of the detection gear is the same as that of the rotary gear ring.
3. The aircraft nose wheel angle measurement device for a test load vehicle of claim 2, wherein the gear train comprises an input gear mechanism and an output gear mechanism in meshed arrangement, wherein:
the input gear mechanism is meshed with the rotary gear ring;
the output gear mechanism is meshed with the detection gear.
4. The aircraft nose wheel angle measurement device for a test load vehicle of claim 3, wherein the input gear mechanism comprises an input gear and an input shaft, wherein:
the input gear is sleeved on the input shaft;
the input gear is meshed with the rotary ring gear.
5. The aircraft nose wheel angle measurement device for a test load vehicle of claim 4, wherein the output gear mechanism comprises a transition gear, an output shaft, and an output gear, wherein:
the transition gear is sleeved on the output shaft and meshed with the input gear;
the output gear is sleeved on the output shaft, and the output gear is meshed with the detection gear.
6. An aircraft nose wheel angle measurement device for a test load vehicle according to claim 3, wherein the transmission comprises a gearbox, the gear transmission being disposed within the gearbox.
7. The aircraft nose wheel angle measurement device for a test load vehicle of claim 6, wherein the gearbox comprises a first housing and a second housing, wherein:
the input gear mechanism is arranged in the first box body;
the output gear mechanism is arranged in the second box body;
the first box body is detachably connected with the second box body.
8. The device for measuring nose wheel angle of an aircraft for a test load vehicle of claim 7, wherein the first and second tanks are detachably connected by a transition flange.
9. The device for measuring nose wheel angle of an aircraft for a test load vehicle according to claim 7, wherein the detection gear is provided in the second case.
10. The device for measuring the nose wheel steering angle of the airplane for the test load car according to claim 7, wherein a first connecting hole is formed in the second box body, and a second connecting hole is formed in a position, corresponding to the first connecting hole, of the shell of the angle sensor;
threaded fasteners pass through the corresponding first and second connection holes to connect the angle sensor to the second housing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223216360.4U CN219008141U (en) | 2022-11-30 | 2022-11-30 | Front nose wheel steering angle measuring device for airplane for load testing vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223216360.4U CN219008141U (en) | 2022-11-30 | 2022-11-30 | Front nose wheel steering angle measuring device for airplane for load testing vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219008141U true CN219008141U (en) | 2023-05-12 |
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ID=86247972
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223216360.4U Active CN219008141U (en) | 2022-11-30 | 2022-11-30 | Front nose wheel steering angle measuring device for airplane for load testing vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219008141U (en) |
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2022
- 2022-11-30 CN CN202223216360.4U patent/CN219008141U/en active Active
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