Airplane control surface angle measuring scale
By designing a portable aircraft control surface angle measuring ruler, the problems of poor portability and environmental dependence of traditional laser measuring instruments have been solved, enabling simple measurement in extreme environments and improving ease of operation and portability.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-05-19
- Publication Date
- 2026-04-07
AI Technical Summary
Traditional laser measuring instruments are poorly portable, power-dependent, and susceptible to environmental factors when measuring aircraft control surfaces, making them difficult to use in extreme environments.
Design an aircraft control surface angle measuring ruler, including a measuring ruler body, vertical side, horizontal side, diagonal side and angle ruler, with scale and protrusions, suitable for snapping into the control surface groove, simplifying operation and easy to carry.
It enables simple, power-free measurement of aircraft control surface angles in extreme environments, improving portability and ease of operation.
Smart Images
Figure CN224095081U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aircraft maintenance technology, and in particular to an aircraft control surface angle measuring ruler. Background Technology
[0002] In the field of aircraft maintenance, the deflection angle of control surfaces (such as ailerons, elevators, and rudders) directly affects flight safety and handling performance.
[0003] Traditional measurement methods often use laser measuring instruments. Although they are fast, they are not portable, and the equipment is large and heavy (usually ≥3kg). They need to be transported in special protective cases and are difficult to adapt to confined spaces or high-altitude operations. They rely on electricity and require continuous power supply (battery or external power source). Their battery life is insufficient in extreme environments (such as high altitudes or deserts). They are also susceptible to interference from strong light and vibration, which can cause data fluctuations or calibration failures. Utility Model Content
[0004] To address the issues of poor portability, reliance on power, and susceptibility to environmental factors when maintenance personnel use laser measuring instruments to measure aircraft control surfaces, this application provides an aircraft control surface angle measuring ruler.
[0005] The aircraft control surface angle measuring ruler provided in this application adopts the following technical solution:
[0006] An aircraft control surface angle measuring ruler includes a measuring ruler body, which includes a vertical side, a horizontal side, a first inclined side, and a second inclined side. The vertical side and the second inclined side are located on opposite sides of the measuring ruler body. The horizontal side is located between the vertical side and the second inclined side and at the bottom of the measuring ruler body. The first inclined side is located between the vertical side and the second inclined side and at the top of the measuring ruler body. An angle ruler, which is an arc-shaped plate, is integrally formed on the measuring ruler body and is located between the first inclined side and the second inclined side. The angle ruler has graduations. A protrusion is integrally formed on the measuring ruler body and is located between the vertical side and the second inclined side.
[0007] Preferably, the measuring ruler body has a through groove that extends through both surfaces of the measuring ruler body.
[0008] In summary, this application includes the following beneficial technical effects:
[0009] This utility model provides an aircraft control surface angle measuring ruler. During operation, simply attach the measuring ruler tightly to the elevator so that the protrusion on the measuring ruler body is inserted into the groove of the elevator to measure the deflection angle of the adjustment tab (TAB). The operation is simple and easy to carry, thus improving the problems of poor portability, reliance on power, and environmental influence when maintenance personnel use laser measuring instruments to measure aircraft control surfaces. Attached Figure Description
[0010] Figure 1 This is a schematic diagram of the structure of the aircraft control surface angle measuring ruler in the embodiments of this application.
[0011] Explanation of reference numerals in the attached diagram: 1. Measuring ruler body; 11. Vertical side; 12. Horizontal side; 13. First hypotenuse; 14. Second hypotenuse; 15. Through groove; 2. Angle ruler; 3. Protrusion. Detailed Implementation
[0012] To enable those skilled in the art to better understand the present invention, the solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of the present invention.
[0013] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation or specific orientation structure and operation, and therefore should not be construed as a limitation of this utility model; the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In addition, unless otherwise explicitly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. For those skilled in the art, the specific meaning of the above terms in this utility model can be understood according to the specific circumstances.
[0014] This application discloses an aircraft control surface angle measuring ruler. (Refer to...) Figure 1The aircraft control surface angle measuring ruler includes a measuring ruler body 1, which includes a vertical side 11, a horizontal side 12, a first inclined side 13, and a second inclined side 14. The vertical side 11 and the second inclined side 14 are located on opposite sides of the measuring ruler body 1. The horizontal side 12 is located between the vertical side 11 and the second inclined side 14 and at the bottom of the measuring ruler body 1. The first inclined side 13 is located between the vertical side 11 and the second inclined side 14 and at the top of the measuring ruler body 1. An angle ruler 2 is integrally formed on the measuring ruler body 1. The angle ruler 2 is an arc-shaped plate located between the first inclined side 13 and the second inclined side 14. The angle ruler 2 is provided with a scale. A protrusion 3 is integrally formed on the measuring ruler body 1 and is located between the vertical side 11 and the second inclined side 14.
[0015] The measuring ruler body 1 has a through groove 15 that runs through both surfaces of the measuring ruler body 1. By setting the through groove 15, the weight and material cost of the measuring ruler are reduced on the one hand, and it is also convenient for maintenance personnel to pass through the through groove 15 to hold the measuring ruler on the other hand.
[0016] The implementation principle of the aircraft control surface angle measuring ruler in this application embodiment is as follows: During operation, simply attach the measuring ruler tightly to the elevator so that the protrusion 3 on the measuring ruler body 1 is inserted into the groove of the elevator, and the deflection angle of the adjustment piece TAB can be measured. The operation is simple and easy to carry.
[0017] The angles of the aileron and rudder trim tabs can also be measured.
[0018] Finally, it should be noted that the above description is only a preferred embodiment of this utility model, and the protection scope of this utility model is not limited to the above embodiments. All technical solutions within the scope of this utility model's concept are within the protection scope of this utility model. It should be pointed out that for those skilled in the art, any improvements and modifications made without departing from the principle of this utility model should also be considered within the protection scope of this utility model.
Claims
1. A ruler for measuring the angle of aircraft control surfaces, characterized in that: The measuring ruler includes a measuring ruler body (1), which includes a vertical side (11), a horizontal side (12), a first inclined side (13), and a second inclined side (14). The vertical side (11) and the second inclined side (14) are located on opposite sides of the measuring ruler body (1). The horizontal side (12) is located between the vertical side (11) and the second inclined side (14) and at the bottom of the measuring ruler body (1). The first inclined side (13) is located between the vertical side (11) and the second inclined side (14) and at the top of the measuring ruler body (1). An angle ruler (2) is integrally formed on the measuring ruler body (1). The angle ruler (2) is an arc-shaped plate located between the first inclined side (13) and the second inclined side (14). The angle ruler (2) is provided with a scale. A protrusion (3) is integrally formed on the measuring ruler body (1) located between the vertical side (11) and the second inclined side (14).
2. The aircraft control surface angle measuring ruler according to claim 1, characterized in that: The measuring ruler body (1) has a through groove (15) that passes through both surfaces of the measuring ruler body (1).