Airplane aileron steering wheel angle measuring device
By installing an angle measuring device with graduated lines on the aircraft aileron control panel, the problems of low efficiency and poor accuracy of traditional methods are solved, enabling fast and accurate angle measurement and improving the efficiency and quality of aircraft debugging.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2023-03-29
- Publication Date
- 2026-03-06
AI Technical Summary
During the commissioning of existing aircraft ailerons, it is impossible to quickly and accurately determine the steering wheel rotation angle, resulting in low measurement efficiency and poor accuracy, which affects the aircraft delivery schedule and quality.
Design an aircraft aileron control disc angle measuring device, including an angle measuring ruler, a bushing, and a fastening assembly. By mounting an angle measuring ruler with scale lines on the outer wall of the aileron, combined with the zero mark on the control disc and the aileron, the rotation angle can be determined intuitively and quickly.
This improved measurement efficiency and accuracy, reduced rework rates, and increased aircraft delivery efficiency.
Smart Images
Figure CN223976612U_ABST
Abstract
Description
Technical Field
[0001] This utility model belongs to the field of aviation equipment debugging technology, specifically relating to an aircraft aileron control disc angle measuring device. Background Technology
[0002] Ailerons, located at the left and right ends of the wing, are used to control the aircraft's turning, also known as roll. When turning, one aileron rises to increase drag and lower the wing, while the other aileron lowers to reduce lift and increase power, thus guiding the aircraft to turn.
[0003] During the adjustment of the aircraft ailerons, it is necessary to ensure that the angle of rotation of the control wheel to the left and right is consistent, that is, to ensure that the left and right wings deflect upward or downward at the same angle. If the aileron control wheel angle is not adjusted properly, it will cause malfunctions when the aircraft rolls to the left or right during actual flight.
[0004] When adjusting the aileron control wheel angle of a conventional aircraft, a conversion angle method is used. The specific method is as follows: First, a thin string is wrapped around the neck of the control wheel, marked, and then the length of the wrap is measured to calculate the length of the string corresponding to each degree. Then, the string is wrapped around the neck of the control wheel in the original position, and the control wheel is rotated to a certain angle. Markings are made on the control wheel where the markings correspond to the string, the string is unfolded, and the distance from the marked point to the end of the string is measured. Combining this with the length of the string corresponding to each degree, the angle of rotation of the control wheel is calculated. This method is time-consuming and labor-intensive, cannot quickly and accurately obtain the rotation angle of the control wheel, and has low measurement accuracy and efficiency, often resulting in rework and affecting the aircraft delivery schedule and quality. Utility Model Content
[0005] To address the problem of not being able to quickly and accurately determine the rotation angle of the aileron control disc during existing aircraft aileron commissioning processes, this invention provides an aircraft aileron control disc angle measuring device.
[0006] The technical solution of this utility model is:
[0007] An aircraft aileron control disc angle measuring device is disclosed, wherein the aircraft aileron control disc 1 is coaxially connected to one end of the neck 2 with clearance fit, and the other end of the neck is fixedly connected to the control column 3; the angle measuring device includes an angle measuring ruler 4, a bushing 6, and a fastening assembly; the angle measuring ruler 4 is an open ring shape, with two perforated lugs symmetrically arranged at the open end, the bushing 6 is clamped between the two lugs, and the fastening assembly fixes the angle measuring ruler and the bushing 6 to the neck 2, with the inner wall of the angle measuring ruler tightly fitted to the outer wall of the neck; graduation lines are opened circumferentially on the outer wall of the angle measuring ruler 4, and the zero graduation line of the angle measuring ruler is marked in the middle of the bushing 6; zero graduation lines are provided on the outer wall of the middle part of the control disc 1 and the outer wall of the neck 2, and the zero graduation line in the middle of the bushing 6 is on the same straight line as the zero graduation line on the neck. When the control disc is in the reference position, the zero graduation line on the outer wall of the middle part of the control disc 1 is aligned with the zero graduation line on the neck.
[0008] Furthermore, the fastening assembly includes a fastening bolt 5 and a wing nut 8; the fastening bolt 5 passes through the trunnion mounting hole of the bushing 6 and the angle measuring ruler 4 to fix the bushing 6 and the angle measuring ruler 4.
[0009] Furthermore, the liner 6 is in the shape of a rotating body, with a protrusion in the middle of its outer wall, and the protrusion is collinear with the zero mark line on the neck 2.
[0010] Furthermore, the protrusion is an annular protrusion.
[0011] The beneficial effects of this utility model are as follows:
[0012] This utility model provides an aircraft aileron control disc angle measuring device. By installing a graduated angle measuring ruler on the outer wall of the control disc, the rotation angle of the control disc can be determined intuitively and quickly by using the zero mark on the control disc to correspond to the specific graduation line on the angle measuring ruler. This solves the problems of low efficiency and poor accuracy of the traditional straight-line angle conversion method, reduces the rework rate of aircraft test flights, and improves aircraft delivery efficiency. Attached Figure Description
[0013] Figure 1 This is a schematic diagram of the assembly of the aircraft aileron control disc angle measuring device of this utility model;
[0014] Figure 2 The diagram shows the fixing of the angle measuring ruler for the fixed ring.
[0015] In the diagram, 1-Drive steering wheel, 2-Neck, 3-Drive pillar, 4-Angle measuring ruler, 5-Fastening bolt, 6-Rack block, 7-Annular protrusion, 8-Wing nut, 9-First zero mark, 10-Second zero mark. Detailed Implementation
[0016] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.
[0017] Reference Figures 1-2 The aileron control disc 1 is connected to one end of the neck 2 with a clearance fit, while the other end of the neck 2 is fixedly connected to the control column 3. During aileron adjustments, the rotation angle of the control disc is often measured using a linear conversion method, which is time-consuming, labor-intensive, and prone to large errors.
[0018] To quickly and accurately determine the rotation angle of the aileron control wheel, this utility model provides an aircraft aileron control wheel angle measuring device. The angle measuring device includes an angle measuring ruler 4, a bushing 6, and a fastening assembly. The angle measuring ruler 4 is an open ring with two perforated lugs symmetrically arranged at the open end. The bushing 6 is clamped between the two lugs. The fastening assembly fixes the angle measuring ruler and the bushing 6 to the neck 2. The inner wall of the angle measuring ruler is in close contact with the outer wall of the neck. Circumferential graduation lines are opened on the outer wall of the angle measuring ruler 4, and the zero graduation line of the angle measuring ruler is marked in the middle of the bushing 6. Zero graduation lines are provided on the outer wall of the middle part of the control wheel 1 and the outer wall of the neck 2. The zero graduation line in the middle of the bushing 6 and the zero graduation line on the neck are on the same straight line. When the control wheel is in the reference position, the zero graduation line on the outer wall of the middle part of the control wheel 1 is aligned with the zero graduation line on the neck.
[0019] By rotating the steering wheel, the operator can directly determine the rotation angle of the steering wheel by measuring the scale line on the ruler 4 corresponding to the zero mark on the steering wheel 1, which improves measurement efficiency and accuracy.
[0020] Reference Figure 1 The angle measuring ruler 4 has an open ring structure with symmetrically arranged perforated lugs at the open end for mounting fastening bolts 5. The angle measuring ruler is fitted onto the outer wall of the neck 2 and connected by a fastening assembly. The outer wall of the angle measuring ruler 4 has circumferential graduations.
[0021] Reference Figure 2 The fastening assembly includes fastening bolts 5 and wing nuts 8. The bushing 6 is located between the plate-like structures at the opening of the angle measuring ruler 4 and is fastened to the angle measuring ruler 4 by fastening bolts 5 and wing nuts 8. The wing nuts 8 ensure that the angle measuring ruler 4 fits tightly against the neck 2.
[0022] The liner 6 is cylindrical with a central hole along its axis for mounting the fastening bolt 5. A protrusion 7 is located in the middle of the outer wall of the liner, positioned at the zero mark on the angle measuring scale, facilitating quick alignment with the zero mark on the neck. Furthermore, the protrusion is annular. A second zero mark 10 is engraved on the outer wall of the neck 2, and a first zero mark 9 is engraved on the outer wall of the center of the steering wheel 1. The protrusion 7 is aligned with the first zero mark 9 and the second zero mark 10.
[0023] During testing, first, place the angle measuring ruler 4 on the neck 2, place the liner 6 in the middle of the angle measuring ruler 4, and fasten the angle measuring ruler and the liner to the neck 2 with the fastening bolt 5 and the wing nut 8, and align the protrusion 7 on the liner 6 with the first zero mark line 10 of the neck 2.
[0024] Align the first zero mark 9 on the steering wheel 1 with the second zero mark 10 on the neck 2, rotate the steering wheel 1 to any angle, and observe the specific scale on the angle measuring ruler corresponding to the first zero mark 9. You can then directly and accurately read the steering wheel rotation angle.
[0025] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Any changes, modifications, substitutions and alterations made by those skilled in the art to the above embodiments without departing from the principles and spirit of the present invention are all covered within the protection scope of the present invention.
Claims
1. An aircraft aileron control disc angle measuring device, wherein the aircraft aileron control disc (1) is coaxially connected to one end of a neck (2) with clearance fit, and the other end of the neck is fixedly connected to a control column (3), characterized in that, The angle measuring device comprises an angle measuring scale (4), a block (6) and a fastening assembly; The angle measuring scale is sleeved on the outer wall of the neck, and the inner wall of the angle measuring scale is tightly attached to the outer wall of the neck; The angle measuring scale (4) is an open ring, and the two ends of the opening are symmetrically provided with hole lugs, the block (6) is clamped between the lugs, and the block is fixed by the fastening assembly; The outer wall of the angle measuring scale (4) is provided with scale lines in the circumferential direction, and the zero scale line of the angle measuring scale is marked on the middle part of the block (6); The outer wall of the middle part of the aileron control wheel (1) and the outer wall of the neck (2) are both provided with zero scale lines, the zero scale line of the middle part of the block (6) is located on the same line as the zero scale line on the neck, and when the control wheel is in the reference position, the zero scale line of the outer wall of the middle part of the control wheel (1) is aligned with the zero scale line on the neck.
2. An aircraft aileron stick angle measuring device as claimed in claim 1, characterised in that, The fastening assembly comprises a fastening bolt (5) and a wing nut (8), the fastening bolt (5) passes through the center hole of the block (6) and is installed in the trunnion mounting hole of the angle measuring scale (4), so as to fix the block and the angle measuring scale.
3. An aircraft aileron stick angle measuring device as claimed in claim 2, wherein, The block (6) is a column, and the middle part of the outer wall is provided with a protrusion, the protrusion is located on the same line as the zero scale line on the neck (2).
4. An aircraft aileron control wheel angle measuring device as claimed in claim 3 wherein, The protrusion is an annular protrusion.