Airplane sensor mounting device

Abstract

The utility model discloses an aircraft sensor mounting device, which belongs to the technical field of aviation mounting and fitting and comprises a base plate, two pressing plates, a guide plate, a threaded rod and a product fixing plate, + / -30-degree angle scales are arranged on the base plate, and an arc bottom hole is formed in the center of the base plate, so that the product fixing plate provided with a product can rotate around the center. The guide plate is clamped between the two pressing plates, one end is inserted into the top of the product, and the other end is provided with a hole to read angle scale values. According to the utility model, plug-and-play is realized, self-rotation zeroing and up-down zeroing can be realized, the angle is visual, the structure is simple and practical, and the efficiency of repairing accessories after the aircraft sensor is disassembled can be improved.

Description

Technical Field

[0001] This utility model belongs to the field of aviation installation and maintenance technology, and relates to an aircraft sensor installation device, specifically a device for adjusting the parameters of the electronic control system after the ±30 degree measurement of an aircraft sensor is fixed. Background Technology

[0002] A certain type of single aircraft has eight sensors. When measuring left and right offset angles (±30 degrees), angle fixing is required to adjust the sensor's internal parameters and thus repair the sensor. Current technology employs a multi-person, collaborative installation method: one person fixes the sensor, another manually adjusts the angle, and another adjusts the electronic control parameters. There is no dedicated sensor installation device, and the process is inherently unstable (personnel cannot leave the site midway), easily leading to inaccurate fixing positions and inaccurate angle readings, which in turn affects the adjustment of electronic control system parameters. The low efficiency of sensor installation and fixing affects the overall parameter adjustment of the electronic control system, causing delays in the overall thermal support cycle, impacting work efficiency, and consequently affecting the overall combat readiness cycle. Utility Model Content

[0003] Based on the characteristics of sensor shape, usage requirements, and operational difficulties, this utility model provides a dedicated aircraft sensor mounting device with insert-type bolt positioning. It enables installation and fixation, sensor alignment (the bottom is double-arc, allowing for fine-tuning of the angle to ensure the sensor is zero in its free state), measurement of offset angle (±30 degrees), and vertical leveling (threaded post). This utility model has a simple structure, is safe to use, and is easy to operate. Furthermore, due to the versatility of related sensors, this utility model can be extended to the installation and commissioning of similar sensors in automotive, marine, and other applications.

[0004] The present invention adopts the following technical solution:

[0005] An aircraft sensor mounting device includes a chassis 1, a pressure plate 2, a guide plate 3, a threaded rod 4, and a product fixing plate 5.

[0006] The chassis 1 is a graduated dial with an angle scale of ±30° engraved on one edge of its upper surface, with an accuracy of 1°. Two arc-shaped bottom holes are made at the center of the chassis 1, which are symmetrically arranged on the same circumference along the axis of the 0° scale. Two mounting holes are also made on the chassis 1 near the angle scale, which are also symmetrical along the axis of the 0° scale. Four bolt holes are also made on the chassis 1, which are evenly distributed along the circumference. Washers are fixed to the bottom of the bolt holes. The washers are used to raise the chassis 1 as a whole, and it is fixed to the repair platform with fully threaded hexagonal head bolts, which serves as a fixing and protection function.

[0007] The product fixing plate 5 is a vertically placed square plate with holes on its upper part for installing the product to be debugged. Two mounting holes are symmetrically made on its lower surface. Two fully threaded hexagonal bolts pass through the two arc-shaped bottom holes on the chassis 1 from the bottom side and are screwed into the two mounting holes on the lower surface of the product fixing plate 5, so that the product fixing plate 5 is coaxial with the chassis 1 and can rotate around the axis along the arc-shaped bottom holes.

[0008] The pressure plate 2 is a strip plate with through holes at both ends, and two plates with the same structure are made.

[0009] The threaded rods 4 are designed with full threads, and there are two of them. The lower ends of the two rods are fixedly installed in the two mounting holes of the chassis 1 by hexagonal nuts. The two pressure plates 2 are stacked one on top of the other, and the two threaded rods 4 are inserted through the holes at both ends from the top. After insertion, the position is fixed by four hexagonal nuts.

[0010] The guide plate 3 is a long strip that passes between the two pressure plates 2. The height of the guide plate 3 is controlled by adjusting the position of the pressure plates 2 on the threaded rod 4. One end of the guide plate 3 extends above the product fixing plate 5 and is inserted into the top groove of the product to be adjusted. The other end extends above the angle scale of the chassis 1. An observation hole is made on the guide plate 3 at the position corresponding to the position above the angle scale of the chassis 1 for visual reading. After tightening the four hexagonal nuts at the upper end of the threaded rod 4, the two pressure plates 2 press and fix the guide plate 3, and the reading is visually read through the observation hole.

[0011] In use, fix the product to be debugged on the product fixing plate 5, rotate the product fixing plate 5 along the two arc-shaped bottom holes on the chassis 1 to achieve zeroing adjustment of the product's rotation in a free state, ensuring that the rotation is zeroed; after zeroing, align the guide plate 3 with the top groove of the product to be debugged and insert it, tighten the four hexagonal nuts at the upper end of the threaded rod 4, so that the two pressure plates 2 press and fix the guide plate 3. Visually read the value through the observation hole, and adjust and repair the electrical control system according to the reading and the fixed parameters; after adjustment, use the installation device again for inspection.

[0012] The beneficial effects of this utility model are as follows: This utility model provides a special sensor installation device with insert-type bolt positioning, which is ready to use immediately upon insertion. It can be zeroed by rotation and vertical positioning, and the angle is intuitively visible (±30 degrees). The structure is simple and practical, and it has high practicality, speed, operability and safety. At the same time, it can also improve the efficiency of repairing accessories after aircraft sensor disassembly (the special sensor installation device with insert-type bolt positioning can be directly inserted into the slot on the sensor), and reduce the impact on repair efficiency due to improper selection of tools by the worker, which makes it difficult to fix the sensor, and reduce the probability of sensor scrapping. Attached Figure Description

[0013] Figure 1 This is a front view of the overall structure of this utility model.

[0014] Figure 2 This is a left view of the overall structure of this utility model.

[0015] Figure 3 This is a top view of the overall structure of this utility model.

[0016] Figure 4 This is a schematic diagram of the chassis structure, where (a) is the front view and (b) is the side view.

[0017] Figure 5 The diagram shows the structure of the pressure plate, where (a) is the front view and (b) is the top view.

[0018] Figure 6 The diagram shows the structure of the guide plate, where (a) is the front view and (b) is the top view.

[0019] Figure 7 This is a schematic diagram of a threaded rod structure.

[0020] Figure 8 This is a schematic diagram of the product fixing plate structure, where (a) is the front view and (b) is the side view.

[0021] The components include: 1. chassis, 2. pressure plate, 3. guide plate, 4. threaded rod, and 5. product fixing plate. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of this utility model clearer, the specific embodiments of this utility model will be described in detail below.

[0023] An aircraft sensor mounting device includes a chassis 1, a pressure plate 2, a guide plate 3, a threaded rod 4, and a product fixing plate 5. Figures 1 to 3 .

[0024] like Figure 4 The chassis 1 is a graduated dial with an angle scale of ±30° engraved on one edge of its upper surface, with an accuracy of 1°. Two arc-shaped bottom holes are made at the center of the chassis 1, which are symmetrically arranged on the same circumference along the axis of the 0° scale. Two mounting holes are also made on the chassis 1 near the angle scale, which are also symmetrical along the axis of the 0° scale. Four bolt holes are also made on the chassis 1, which are evenly distributed along the circumference. Washers are fixed at the bottom of the bolt holes. The washers are used to raise the chassis 1 by 12mm and fix it to the repair platform with fully threaded hexagonal head bolts, which serves as a fixing and protection function.

[0025] like Figure 8The product fixing plate 5 is a vertically placed square plate with holes on its upper part for mounting the product to be debugged using fully threaded hexagonal head bolts and wing nuts. Two mounting holes are symmetrically made on its lower surface. Two fully threaded hexagonal bolts, together with elastic washers and flat washers, pass through the two arc-shaped bottom holes on the chassis 1 from the bottom side and are screwed into the two mounting holes on the lower surface of the product fixing plate 5, so that the product fixing plate 5 is coaxial with the chassis 1 and can rotate around the axis along the arc-shaped bottom holes.

[0026] like Figure 5 The pressure plate 2 is a strip plate with through holes at both ends, and two plates with the same structure are made.

[0027] like Figure 7 The threaded rods 4 are designed with full threads, and there are two of them. The lower ends of the two rods are fixedly installed in the two mounting holes of the chassis 1 by hexagonal nuts. The two pressure plates 2 are stacked on top of each other, and the two threaded rods 4 are inserted from the top through the holes at both ends and fixed in position by four hexagonal nuts.

[0028] like Figure 6 The guide plate 3 is a long strip that passes between the two pressure plates 2. The height of the guide plate 3 is controlled by adjusting the position of the pressure plates 2 on the threaded rod 4. One end of the guide plate 3 extends above the product fixing plate 5 and is inserted into the top groove of the product to be debugged. The other end extends above the angle scale of the chassis 1. An observation hole is made on the guide plate 3 at the position corresponding to the position above the angle scale of the chassis 1 for visual reading. After tightening the four hexagonal nuts at the upper end of the threaded rod 4, the two pressure plates 2 press and fix the guide plate 3, and the reading is visually read through the observation hole.

[0029] In use, fix the product to be debugged on the product fixing plate 5, rotate the product fixing plate 5 along the two arc-shaped bottom holes on the chassis 1 to achieve zeroing adjustment of the product's rotation in a free state, ensuring that the rotation is zeroed; after zeroing, align the guide plate 3 with the top groove of the product to be debugged and insert it, tighten the four hexagonal nuts at the upper end of the threaded rod 4, so that the two pressure plates 2 press and fix the guide plate 3. Visually read the value through the observation hole, and adjust and repair the electrical control system according to the reading and the fixed parameters; after adjustment, use the installation device again for inspection.

[0030] In summary, the above are merely preferred embodiments of this utility model and are not intended to limit the scope of protection of this utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the scope of protection of this utility model.

Claims

1. An aircraft sensor mounting device, characterized in that, The installation device includes a chassis (1), a pressure plate (2), a guide plate (3), a threaded rod (4), and a product fixing plate (5); The upper surface of the chassis (1) is engraved with an angle scale of ±30° on one side edge. Two arc-shaped bottom holes are made at the center of the chassis (1). The two holes are symmetrically arranged on the same circumference along the axis where the 0° scale is located. The chassis (1) is fixed on the repair platform. The product fixing plate (5) is placed vertically, and the product to be debugged is installed on its upper part. It is installed in two arc-shaped bottom holes on the chassis (1). The product fixing plate (5) is coaxial with the chassis (1) and can rotate around the axis along the arc-shaped bottom holes. The pressure plate (2) is a strip plate with through holes at both ends, and two plates with the same structure are made. There are two threaded rods (4) in total. They are symmetrically installed on the chassis (1) near the angle scale along the axis where the 0° scale is located. The two pressure plates (2) are stacked one on top of the other. The two threaded rods (4) are inserted through the holes at both ends from the top and then fixed in position by four hexagonal nuts. The guide plate (3) is a long strip plate that passes between two pressure plates (2). The height of the guide plate (3) is controlled by adjusting the position of the pressure plate (2) on the threaded rod (4). One end of the guide plate (3) extends above the product fixing plate (5) and is inserted into the top groove of the product to be debugged. The other end extends above the angle scale of the chassis (1).

2. The aircraft sensor mounting device according to claim 1, characterized in that, The chassis (1) has an angle scale accuracy of 1°.

3. The aircraft sensor mounting device according to claim 1, characterized in that, The chassis (1) has multiple pad rings fixed at its bottom for raising the chassis (1).

4. The aircraft sensor mounting device according to claim 1, characterized in that, An observation hole is made on the guide plate (3) at a position above the angle scale of the chassis (1) for visual reading.

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