Aircraft nose wheel steering calibration device and method

Abstract

This invention provides an aircraft nose wheel steering calibration device and method, relating to the field of aircraft nose wheel steering calibration technology. The device includes: a base with a receiving groove on its upper part, the groove wall having a first notch; a turntable rotatably disposed within the receiving groove, the turntable having a second notch on its edge that engages with the first notch to form a pin hole, a positioning groove at the center of the upper side of the turntable engaging with the aircraft nose wheel; a main scale on the upper side of the base; a vernier scale on the upper side of the base, engaging with the main scale; and a positioning pin that engages with the pin hole to align the vernier zero mark of the vernier scale with the main zero mark of the main scale. This invention addresses the problem of the lack of dedicated aircraft nose wheel steering calibration fixtures and processes in the prior art.

Description

Technical Field

[0001] This invention belongs to the field of aircraft nose wheel steering calibration technology, and more specifically, relates to an aircraft nose wheel steering calibration device and method. Background Technology

[0002] The front wheel steering calibration fixture is mainly used in the field of aircraft debugging, and is usually used for front wheel calibration operations during the aircraft production debugging process.

[0003] Aircraft require the nose wheel for steering and heading correction, and the nose wheel steering angle plays a crucial role in the aircraft control system. Therefore, strict requirements are placed on the accuracy of the nose wheel angle calibration during the commissioning process. Current nose wheel steering angle calibration methods require multiple people to work together, which is time-consuming and labor-intensive. Furthermore, the lack of dedicated tooling leads to inconsistent nose wheel steering angle calibration methods and insufficient calibration accuracy, further increasing the difficulty of nose wheel angle calibration.

[0004] Therefore, this paper proposes a calibration device and method for aircraft nose wheel steering to address this phenomenon. This method is designed to facilitate operation, standardize calibration methods, and improve calibration accuracy. The nose wheel steering calibration device also provides convenience for aircraft production, saves human resources, and improves production efficiency. The design challenge lies in the fact that aircraft products have short overall adjustment, maintenance, and upkeep cycles, involve a large workload, require significant manpower, and demand high levels of operator experience. Therefore, it is necessary to design a calibration device and method that saves time and manpower, greatly simplifies the process, and is easy to operate. Summary of the Invention

[0005] The purpose of this invention is to address the shortcomings of existing technologies by providing an aircraft nose wheel steering calibration device and method, thus solving the problem of the lack of dedicated aircraft nose wheel steering calibration tooling and processes in the prior art.

[0006] To achieve the above objectives, the present invention provides an aircraft nose wheel steering calibration device, the device comprising: The base has a receiving groove on its upper part, and the groove wall has a first notch. A turntable is rotatably mounted in the receiving groove. The edge of the turntable is provided with a second notch, which can cooperate with the first notch to form a pin hole. The upper center of the turntable is provided with a positioning groove, which cooperates with the aircraft's nose wheel. The main scale is located on the upper side of the base; A vernier scale is provided on the upper side of the transfer surface, and the vernier scale mates with the main scale. A positioning pin is inserted into the pin hole to align the vernier zero mark of the vernier scale with the main zero mark of the main scale.

[0007] Optionally, the turntable is rotatably connected to the base via a radial bearing.

[0008] Optionally, the base has a first mounting groove below the receiving groove, the turntable has a first boss at its lower part, and the radial bearing is disposed between the groove wall of the first mounting groove and the outer wall of the first boss.

[0009] Optionally, the turntable is rotatably connected to the base via an axial bearing.

[0010] Optionally, the first boss has an annular second mounting groove inside, and the second mounting groove forms a second boss inside. The base has a third boss inside the first mounting groove. The lower part of the third boss has a third mounting groove, and the upper part of the third boss has a through hole for the second boss to pass through. The axial bearing is disposed in the third mounting groove. The upper side of the axial bearing is connected to the top wall of the third mounting groove, and the lower side of the axial bearing is connected to a baffle fastened to the second boss.

[0011] Optionally, the positioning groove is provided with a textured structure that matches the outer surface of the aircraft's front wheel.

[0012] Optionally, the lower side of the base is provided with a limiting hole, and the upper part of the limiting hole is provided with a connecting hole that communicates with the pin hole. A limiting step structure is formed between the limiting hole and the connecting hole, and the positioning pin is a quick-release pin with an elastic locking part.

[0013] Optionally, the main scale has main scale lines of 0-60° on both sides of the main zero scale line, and the graduation value of the main scale line is 1°. The vernier scale has vernier scale lines of 10 divisions on both sides of the vernier zero scale line, and the angle between the 10-division vernier scale line and the 9-division main scale line is equal.

[0014] Optionally, one end of the base is provided with a ramp structure, both sides of the base are provided with recessed handle structures, and the bottom of the base is provided with an anti-slip pad.

[0015] The present invention also provides a method for calibrating the nose wheel steering of an aircraft, utilizing the aforementioned aircraft nose wheel steering calibration device, the method comprising: Align the vernier zero mark of the vernier scale with the main zero mark of the main scale by inserting the locating pin into the pin hole; Push the aircraft's nose wheel into the positioning slot on the upper side of the turntable; Remove the locating pin; The turntable deflects by steering the aircraft's nose wheel; The aircraft's nose wheel steering angle is read using the vernier scale and the main scale.

[0016] This invention provides an aircraft nose wheel steering calibration device and method, which has the following advantages: The aircraft nose wheel steering calibration device has a base and a turntable rotatably mounted on the base. A positioning groove on the upper side of the turntable can accommodate and position a portion of the aircraft nose wheel. By inserting a positioning pin into the pin hole formed after the first notch and the second notch are aligned, the turntable can be positioned so that the vernier zero mark of the vernier scale is aligned with the main zero mark of the main scale. Before the aircraft nose wheel rotates, the positioning pin is removed. The rotation of the aircraft nose wheel can drive the turntable to rotate relative to the base. Then, through the cooperation between the vernier scale and the main scale, the deflection angle of the aircraft nose wheel can be accurately read, thereby realizing the calibration of the aircraft nose wheel steering. The aircraft nose wheel steering calibration device is small in size, simple to use, and easy to carry. It is a manual mechanical operation device that does not require a power supply, is not limited by the working environment, and has a wide range of applications. The aircraft nose wheel steering calibration method is simple and quick to operate, saves operation time, and simplifies the process.

[0017] Other features and advantages of the present invention will be described in detail in the following detailed description section. Attached Figure Description

[0018] The above and other objects, features and advantages of the present invention will become more apparent from the more detailed description of exemplary embodiments of the invention in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments of the invention.

[0019] Figure 1 A three-dimensional structural schematic diagram of an aircraft front wheel steering calibration device according to an embodiment of the present invention is shown.

[0020] Figure 2 An exploded view of an aircraft front wheel steering calibration device according to an embodiment of the present invention is shown.

[0021] Figure 3 A cross-sectional schematic diagram of an aircraft front wheel steering calibration device according to an embodiment of the present invention is shown.

[0022] Figure 4 A flowchart of an aircraft nose wheel steering calibration method according to an embodiment of the present invention is shown.

[0023] Explanation of reference numerals in the attached figures: 1. Locating pin; 2. Fixing bolt; 3. Turntable; 4. Radial bearing; 5. Base; 6. Axial bearing; 7. Baffle; 8. Fastener; 9. First notch; 10. Second notch; 11. Locating groove; 12. Main scale; 13. Vernier scale; 14. First boss; 15. Second boss; 16. Third boss; 17. Through hole; 18. Anti-loss rope; 19. Sloping structure; 20. Recessed handle. Detailed Implementation

[0024] Preferred embodiments of the invention will now be described in more detail. While preferred embodiments of the invention are described below, it should be understood that the invention can be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that the invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0025] like Figure 1 and Figure 2 As shown, the present invention provides an aircraft nose wheel steering calibration device, the device comprising: The base 5 has a receiving groove on its upper part, and the groove wall has a first notch 9. Turntable 3 is rotatably mounted in the receiving groove. The edge of turntable 3 is provided with a second notch 10, which can cooperate with the first notch 9 to form a pin hole. The upper center of turntable 3 is provided with a positioning groove 11, which cooperates with the aircraft's nose wheel. Main scale 12 is located on the upper side of the base 5; Vernier scale 13 is located on the upper side of the transfer and is matched with the main scale 12; Positioning pin 1 is engaged with the pin hole and is used to align the vernier zero mark of vernier scale 13 with the main zero mark of main scale 12.

[0026] Specifically, to address the lack of dedicated equipment and processes for calibrating aircraft nose wheel steering in existing technologies, this invention provides an aircraft nose wheel steering calibration device. The device comprises a base 5 and a turntable 3 rotatably mounted on the base 5. A positioning groove 11 on the upper side of the turntable 3 accommodates and positions a portion of the aircraft nose wheel. A positioning pin 1 is inserted into a pin hole formed by aligning the first notch 9 and the second notch 10, positioning the turntable 3 so that the vernier zero mark of the vernier scale 13 aligns with the main zero mark of the main scale 12. Before the aircraft nose wheel rotates, the positioning pin 1 is removed, allowing the turntable 3 to rotate relative to the base 5. The cooperation between the vernier scale 13 and the main scale 12 accurately reads the deflection angle of the aircraft nose wheel, thus calibrating the aircraft nose wheel steering. This aircraft nose wheel steering calibration device is small in size, simple to use, and easy to carry. It is a manual mechanical operation device, requiring no power supply, and its working environment is unrestricted, making it widely applicable. The aircraft nose wheel steering calibration method is simple and quick to operate, saves operating time, and simplifies the process.

[0027] Optionally, the turntable 3 is rotatably connected to the base 5 via a radial bearing 4.

[0028] Specifically, the radial axial setting not only makes the rotation of the turntable 3 relative to the base 5 smoother, but also provides a certain radial load-bearing capacity.

[0029] Optionally, the base 5 has a first mounting groove below the receiving groove, the turntable 3 has a first boss 14 at the bottom, and the radial bearing 4 is disposed between the groove wall of the first mounting groove and the outer wall of the first boss 14.

[0030] Specifically, such as Figure 3 As shown, the inner ring of the radial bearing 4 is fitted around the outer circumference of the first boss 14, the outer ring of the radial axial direction is embedded in the inner circumference of the first mounting groove, the turntable 3 is rotatably mounted in the receiving groove, and the upper surface of the turntable 3 is flush with the upper surface of the base 5.

[0031] In this embodiment, the radial bearing 4 is a tapered roller bearing.

[0032] Optionally, the turntable 3 is rotatably connected to the base 5 via an axial bearing 6.

[0033] Specifically, the combined use of axial bearing 6 and radial bearing 4 can further ensure the smooth and silky rotation of turntable 3.

[0034] Optionally, the first boss 14 has an annular second mounting groove inside, and the second mounting groove forms a second boss 15 inside. The base 5 has a third boss 16 inside the first mounting groove. The lower part of the third boss 16 has a third mounting groove. The upper part of the third boss 16 has a through hole 17 for the second boss 15 to pass through. The axial bearing 6 is disposed in the third mounting groove. The upper side of the axial bearing 6 is connected to the top wall of the third mounting groove, and the lower side of the axial bearing 6 is connected to the baffle 7 fastened to the second boss 15.

[0035] Specifically, the annular second mounting groove creates a second boss 15 below the turntable 3. The second boss 15 is rotatably disposed within the through hole 17 and the third mounting groove, and passes through the inner hole of the axial bearing 6. A third boss 16 is provided at the center of the first mounting groove. The third boss 16 is rotatably disposed within the annular second mounting groove, and forms a thin-walled structure through the third mounting groove inside it. The baffle 7 is fastened to the lower side of the second boss 15 by the fastener 8, and provides a fastening force to the axial bearing 6. Under the action of the fastening force, the axial bearing 6 is clamped between the baffle 7 and the top wall of the third mounting groove.

[0036] In this embodiment, the axial bearing 6 is a thrust ball bearing.

[0037] Optionally, the positioning groove 11 is provided with a textured structure that matches the outer surface of the aircraft's nose wheel.

[0038] Specifically, the positioning groove 11 can be provided with a strip-shaped groove that matches the striped tire pattern on the outer surface of the aircraft's nose wheel, so as to better match the installation of the aircraft's nose wheel.

[0039] Optionally, a limiting hole is provided on the lower side of the base 5, and a connecting hole 17 is provided on the upper part of the limiting hole to communicate with the pin hole. A limiting step structure is formed between the limiting hole and the connecting hole 17, and the positioning pin 1 is a quick-release pin with an elastic locking part.

[0040] Specifically, after the quick-release pin is inserted into the pin hole, it can pass through the connecting hole 17, partially enter the limiting hole, and form a limit using the limiting step structure to prevent the positioning pin 1 from accidentally coming out.

[0041] In this embodiment, a quick-release pin with a button and an elastic protrusion is used, and an anti-loss rope 18 is connected to the upper end of the quick-release pin. The anti-loss rope 18 is connected to the base 5 through a fixing bolt 2 to prevent the quick-release pin from being lost.

[0042] Optionally, the main scale 12 has main scale lines of 0-60° on both sides of the main zero scale line, and the graduation value of the main scale line 12 is 1°. The vernier scale 13 has vernier scale lines of 10 divisions on both sides of the vernier zero scale line, and the angle between the 10-division vernier scale line 13 and the 9-division main scale line 12 is equal.

[0043] Specifically, to improve calibration accuracy, the vernier scale 13 and the main scale 12 adopt the degree principle of vernier calipers. The 10 division value of the vernier scale 13 line corresponds to the 9 division value of the main scale 12 line. The angle value with an accuracy of 0.1° is calculated by the difference between the integer degree of the main scale 12 and the alignment line of the vernier scale 13.

[0044] Optionally, one end of the base 5 is provided with a ramp structure 19, both sides of the base 5 are provided with recessed handle structures 20, and the bottom of the base 5 is provided with an anti-slip pad.

[0045] Specifically, the ramp structure 19 facilitates pushing the aircraft's nose wheel into the positioning slot 11 on the turntable 3. The recessed handles 20 on both sides of the base 5 make it easy to pick up and transport the device. The anti-slip pads on the bottom of the base 5 improve the stability of the device when it is placed and prevent it from sliding during use.

[0046] like Figure 4 As shown, the present invention also provides a method for calibrating the nose wheel steering of an aircraft, utilizing the aforementioned aircraft nose wheel steering calibration device. The method includes: By inserting the positioning pin 1 into the pin hole, the vernier zero mark line of the vernier scale 13 is aligned with the main zero mark line of the main scale 12; Push the aircraft's nose wheel into the positioning groove 11 on the upper side of the turntable 3; Remove positioning pin 1; The steering of the aircraft's nose wheel causes turntable 3 to deflect; The nose wheel steering angle of the aircraft is read using vernier scale 13 and main scale 12.

[0047] Specifically, the aircraft nose wheel steering calibration method utilizes the aforementioned aircraft nose wheel steering calibration device. Taking its use in the calibration of a certain model of aircraft nose wheel as an example: the installation qualification standard is: the aircraft nose wheel is in reliable contact with the aircraft nose wheel steering calibration device, and the installation is stable; by inserting the positioning pin 1 into the pin hole, the vernier zero mark of the vernier scale 13 is aligned with the main zero mark of the main scale 12, thus achieving initial positioning of the turntable 3; the aircraft nose wheel is conveniently pushed onto the turntable 3 using the ramp structure 19, and the aircraft nose wheel is embedded in the positioning groove 11, ensuring reliable fit between the outer surface of the aircraft nose wheel and the texture structure of the positioning groove 11; the positioning pin 1 is removed, allowing the turntable 3 to rotate relative to the base 5; the aircraft nose wheel drives the turntable 3 to deflect, and the vernier scale 13 on the turntable 3 cooperates with the main scale 12 on the base 5, enabling accurate reading of the deflection angle of the turntable 3 and the aircraft nose wheel using the reading principle of vernier calipers, thereby measuring the actual steering angle of the aircraft nose wheel and thus achieving aircraft nose wheel steering calibration. The aircraft's nose wheel is pushed off the base 5 via the ramp structure 19, and the positioning pin 1 is inserted to lock the turntable 3 and the base 5, thus completing the calibration operation.

[0048] The various embodiments of the present invention have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. An aircraft nose wheel steering calibration device, characterized in that, The device includes: The base has a receiving groove on its upper part, and the groove wall has a first notch. A turntable is rotatably mounted in the receiving groove. The edge of the turntable is provided with a second notch, which can cooperate with the first notch to form a pin hole. The upper center of the turntable is provided with a positioning groove, which cooperates with the aircraft's nose wheel. The main scale is located on the upper side of the base; A vernier scale is provided on the upper side of the transfer surface, and the vernier scale mates with the main scale. A positioning pin is inserted into the pin hole to align the vernier zero mark of the vernier scale with the main zero mark of the main scale.

2. The aircraft nose wheel steering calibration device according to claim 1, characterized in that, The turntable is rotatably connected to the base via radial bearings.

3. The aircraft nose wheel steering calibration device according to claim 2, characterized in that, The base has a first mounting groove below the receiving groove, the turntable has a first boss at its lower part, and the radial bearing is disposed between the groove wall of the first mounting groove and the outer wall of the first boss.

4. The aircraft nose wheel steering calibration device according to claim 3, characterized in that, The turntable is rotatably connected to the base via an axial bearing.

5. The aircraft nose wheel steering calibration device according to claim 4, characterized in that, The first boss has an annular second mounting groove inside, and a second boss is formed inside the second mounting groove. The base has a third boss inside the first mounting groove. The lower part of the third boss has a third mounting groove. The upper part of the third boss has a through hole to accommodate the passage of the second boss. The axial bearing is disposed in the third mounting groove. The upper side of the axial bearing is connected to the top wall of the third mounting groove. The lower side of the axial bearing is connected to a baffle fastened to the second boss.

6. The aircraft nose wheel steering calibration device according to claim 1, characterized in that, The positioning groove is provided with a textured structure that matches the outer surface of the aircraft's front wheel.

7. The aircraft nose wheel steering calibration device according to claim 1, characterized in that, The base is provided with a limiting hole on its lower side, and a connecting hole is provided on the upper part of the limiting hole to communicate with the pin hole. A limiting step structure is formed between the limiting hole and the connecting hole, and the positioning pin is a quick-release pin with an elastic locking part.

8. The aircraft nose wheel steering calibration device according to claim 1, characterized in that, The main scale has main scale lines of 0-60° on both sides of the main zero scale line, and the division value of the main scale line is 1°. The vernier scale has vernier scale lines of 10 divisions on both sides of the vernier zero scale line, and the angle of the 10 division vernier scale line is equal to that of the 9 division main scale line.

9. The aircraft nose wheel steering calibration device according to claim 1, characterized in that, One end of the base is provided with a ramp structure, the two sides of the base are provided with recessed handle structures, and the bottom of the base is provided with an anti-slip pad.

10. A method for calibrating the nose wheel steering of an aircraft, utilizing the aircraft nose wheel steering calibration device according to any one of claims 1-9, characterized in that, The method includes: Align the vernier zero mark of the vernier scale with the main zero mark of the main scale by inserting the locating pin into the pin hole; Push the aircraft's nose wheel into the positioning slot on the upper side of the turntable; Remove the locating pin; The turntable deflects by steering the aircraft's nose wheel; The aircraft's nose wheel steering angle is read using the vernier scale and the main scale.

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