An aircraft accelerometer installation error measurement tool

Abstract

This utility model relates to the field of calibrating airborne avionics products for aircraft, specifically disclosing a fixture for measuring the installation error of an aircraft accelerometer. The fixture includes a docking seat, one side of which is connected to the top side of an extension rod via a lead-out plate. A measuring body is connected to the bottom side of the extension rod, and the measuring body and the docking seat are located on the same side. This solves the problem of difficulty in measuring accelerometer installation errors, enables indirect measurement of the three-dimensional installation angle, and ensures measurement accuracy.

Description

Technical Field

[0001] This utility model relates to a measuring fixture, specifically a fixture for measuring the installation error of an aircraft accelerometer, belonging to the field of calibration of airborne avionics products. Background Technology

[0002] Accelerometers are crucial devices for measuring the triaxial acceleration of aircraft. Natural manufacturing errors exist at the accelerometer mounting point, affecting the accuracy of triaxial measurements. Therefore, it is necessary to measure and calculate the error value and implement error compensation measures to ensure measurement accuracy. Because the accelerometer is installed inside the aircraft, it is obstructed by the surrounding airframe structure and accessories, making it impossible to directly measure the installation error using high-precision measuring equipment such as lidar. Utility Model Content

[0003] To address the problems in the existing technology, this utility model provides a tooling for measuring the installation error of an aircraft accelerometer.

[0004] The objective of this utility model can be achieved through the following technical solutions:

[0005] A fixture for measuring the installation error of an aircraft accelerometer includes a docking seat. One side of the docking seat is connected to the top side of an extension rod via an extension plate. A measuring body is connected to the bottom side of the extension rod, and the measuring body and the docking seat are located on the same side.

[0006] Optionally, the bottom of the docking seat faces the measuring body, and the bottom of the docking seat is rectangular with fixing holes through all four corners.

[0007] Optionally, the fixing hole is used for mounting and fixing the docking seat to the machine body. Below the fixing hole, a boss is integrally connected to the bottom of the docking seat. The fixing hole is set with a 90° countersunk head, and the bottom of the boss is parallel to the top of the measuring body.

[0008] Optionally, both sides of the docking seat are triangular in shape, and both sides are perforated.

[0009] Optionally, the side of the measuring body facing the docking seat is the main measuring surface, and the side that is in contact with the main measuring surface is the auxiliary measuring surface.

[0010] Optionally, the outer walls of both the main measuring surface and the auxiliary measuring surface are provided with a reflective coating.

[0011] Optionally, the measuring body is fitted with a protective cover, and the inner wall of the protective cover is connected with a flexible protective layer.

[0012] Optionally, the lead-out plate is hollow, and the extension rod is an H-shaped aluminum profile.

[0013] The beneficial effects of this utility model are:

[0014] This solves the problem of difficult measurement of accelerometer installation errors, enables indirect measurement of three-dimensional installation angles, and ensures measurement accuracy. Attached Figure Description

[0015] To facilitate understanding by those skilled in the art, the present invention will be further described below with reference to the accompanying drawings.

[0016] Figure 1 This is a schematic diagram of the overall structure of the measuring fixture of this utility model.

[0017] Figure 2 This utility model Figure 1 Axonometric view.

[0018] Figure 3 This is a schematic diagram of the bottom structure of the docking seat of this utility model.

[0019] In the diagram: 1. Connecting seat; 2. Lead-out plate; 3. Fixing hole; 4. Extension rod; 5. Measuring body; 6. Main measuring surface; 7. Auxiliary measuring surface; 8. Protective cover; 9. Boss. Detailed Implementation

[0020] The technical solution of this utility model will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0021] Please see Figure 1-3 As shown, an aircraft accelerometer installation error measurement fixture includes a docking seat 1. One side of the docking seat 1 is connected to the top side of an extension rod 4 via an extension plate 2. A measuring body 5 is connected to the bottom side of the extension rod 4. The measuring body 5 and the docking seat 1 are located on the same side.

[0022] Specifically, the bottom of the docking seat 1 faces the measuring body 5, and the bottom of the docking seat 1 is rectangular with fixing holes 3 through each of the four corners.

[0023] Specifically, the fixing hole 3 is used for mounting and fixing the docking seat 1 to the machine body. Below the fixing hole 3, a boss 9 is integrally connected to the bottom of the docking seat 1. The fixing hole 3 adopts a 90° countersunk setting, and the bottom of the boss 9 is parallel to the top of the measuring body 5. The setting of the boss 9 facilitates a closer fit between the docking seat 1 and the accelerometer mounting reference surface on the machine body, thereby improving the installation accuracy. The 90° countersunk setting improves the repeatability accuracy of the docking seat 1.

[0024] Specifically, both sides of the docking seat 1 are triangular in shape, and both sides are perforated. The triangular shape improves the stability of the docking seat 1, while the perforations help reduce the weight of the docking seat 1.

[0025] Specifically, the side of the measuring body 5 facing the docking seat 1 is the main measuring surface 6, and the side that connects to the main measuring surface 6 is the auxiliary measuring surface 7. The main measuring surface 6 is located on the horizontal plane above the measuring body 5, which facilitates the measurement of the measuring body 5 by the lidar and the implementation of the algorithm. Through calibration, the main measuring surface 6 is parallel to the accelerometer mounting reference plane.

[0026] The auxiliary measurement surface 7 is perpendicular to the main measurement surface 6 and parallel to the aircraft's heading. When necessary, the data measured by the auxiliary measurement surface 7 can be used to assist in verifying the measurement data of the main measurement surface 6.

[0027] Specifically, both the main measuring surface 6 and the auxiliary measuring surface 7 have a reflective coating on their outer walls. The measuring body 5 is made of aluminum and its surface is anodized. After the treatment, the measuring body 5 has a natural aluminum silver-white color and forms a reflective coating. The reflective coating is polished to improve the laser reflection effect, making it easier for the lidar to measure the plane, while also ensuring durability.

[0028] Specifically, the measuring body 5 is fitted with a protective cover 8, and the inner wall of the protective cover 8 is connected with a flexible protective layer. The protective cover 8 prevents the measuring surfaces on the measuring body 5 from being damaged during long-term use, thus affecting the measurement accuracy. The protective cover 8 covers the auxiliary measuring surface 7 and the main measuring surface 6, and is made of hard metal material with a certain strength. The flexible protective layer on the inner surface is made of flexible material such as rubber or sponge to avoid damaging the reflective coating.

[0029] Specifically, the lead-out plate 2 is hollow, and the extension rod 4 is an H-shaped aluminum profile. The hollow lead-out plate 2 and the H-shaped aluminum profile extension rod 4 ensure strength during use while reducing the overall weight.

[0030] In use, the side of the docking seat 1 facing the measuring body 5 is aligned with the accelerometer mounting reference surface on the aircraft body. Due to the protrusion 9, the relative position of the measuring body 5 and the accelerometer mounting reference surface is more precise. The main measuring surface 6 is parallel to the accelerometer mounting reference surface. Bolts are then used to connect and fix the measuring body 5 to the accelerometer mounting reference surface through the fixing hole 3. The extension rod 4 faces outwards from the aircraft body, allowing the measuring body 5 to extend outside the aircraft body for convenient subsequent comprehensive measurements. The protective cover 8 is then removed, extending the three-dimensional angle of the accelerometer mounting reference surface parallel to the measurable area. The main measuring surface 6 and auxiliary measuring surface 7 of the laser radar scanning fixture are used to obtain the three-dimensional angle of the measuring body 5, thereby indirectly acquiring the three-dimensional angle of the accelerometer mounting reference surface. By obtaining the three-dimensional angle through indirect measurement and comparing it with the theoretical value, the installation error is calculated. This error value is then set to the aircraft system to compensate for and correct the accelerometer error, thereby improving the measurement accuracy of the accelerometer.

[0031] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the utility model to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of this utility model, thereby enabling those skilled in the art to better understand and utilize it. This utility model is limited only by the claims and their full scope and equivalents.

Claims

1. An aircraft accelerometer installation error measurement tool comprising a docking station (1) characterised in that, One side of the docking seat (1) is connected to the top side of the extension rod (4) via the lead-out plate (2), and a measuring body (5) is connected to the bottom side of the extension rod (4). The measuring body (5) and the docking seat (1) are located on the same side.

2. The fixture for measuring the installation error of an aircraft accelerometer according to claim 1, characterized in that, The bottom of the docking seat (1) faces the measuring body (5). The bottom of the docking seat (1) is rectangular and has fixing holes (3) through each of the four corners.

3. The fixture for measuring the installation error of an aircraft accelerometer according to claim 2, characterized in that, The fixing hole (3) is used for the installation and fixing of the docking seat (1) and the machine body. Below the fixing hole (3), a boss (9) is integrally connected to the bottom of the docking seat (1). The fixing hole (3) is set with a 90° countersunk head. The bottom of the boss (9) is parallel to the top of the measuring body (5).

4. The fixture for measuring the installation error of an aircraft accelerometer according to claim 3, characterized in that, The two side walls of the docking seat (1) are both triangular in shape, and both side walls are perforated.

5. The fixture for measuring the installation error of an aircraft accelerometer according to claim 1, characterized in that, The side of the measuring body (5) facing the docking seat (1) is the main measuring surface (6), and the side that is in contact with the main measuring surface (6) is the auxiliary measuring surface (7).

6. The fixture for measuring the installation error of an aircraft accelerometer according to claim 5, characterized in that, The outer walls of both the main measuring surface (6) and the auxiliary measuring surface (7) are provided with a reflective coating.

7. The fixture for measuring the installation error of an aircraft accelerometer according to claim 6, characterized in that, The measuring body (5) is fitted with a protective cover (8) on the outside, and the inner wall of the protective cover (8) is connected with a flexible protective layer.

8. The fixture for measuring the installation error of an aircraft accelerometer according to claim 1, characterized in that, The lead-out plate (2) is hollow, and the extension rod (4) is an H-shaped aluminum profile.

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