Aircraft sensor mounting device and use method thereof

Abstract

The invention discloses an aircraft sensor installation device and a using method thereof, and belongs to the technical field of aviation installation and decoration, the aircraft sensor installation device comprises a chassis, pressing plates, a guide plate, a threaded rod and a product fixing plate, the chassis is provided with + / -30-degree angle scales, the center is provided with an arc bottom hole, the product fixing plate provided with a product can rotate around the center, and the two pressing plates are installed on the threaded rod. 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] The present invention belongs to the technical field of aviation installation and repair, and relates to an aircraft sensor installation device and a method for using the same, specifically to a device for adjusting the electronic control system parameters after measuring and fixing the aircraft sensor at ±30 degrees. Background Art

[0002] A certain type of single aircraft has 8 sensors. When measuring the left and right offset angles (±30 degrees), the angles need to be fixed to adjust the internal parameters of the sensors, so as to achieve the purpose of repairing the sensors. The existing technology adopts the installation method of multiple people cooperating with each other, that is, one person fixes the sensor, another person adjusts the angle manually, and still another person adjusts the electronic control parameters. There is no special sensor installation device, and there is a certain degree of instability (during the operation process, personnel cannot leave midway), which is likely to cause inaccurate fixing positions and inaccurate angle readings, thereby affecting the adjustment of the electronic control system parameters. The installation and fixing efficiency of the sensors is low, affecting the parameter adjustment of the overall electronic control system, thereby causing a lag in the overall cycle of thermal protection, affecting work efficiency, and further affecting the overall combat readiness cycle. Summary of the Invention

[0003] According to the shape of the sensor, usage requirements, operation difficulties and other characteristics, the present invention provides a special aircraft sensor installation device with plug-in bolt positioning and a method for using the same, which can realize installation and fixing, sensor alignment (the bottom is double-arc-shaped, and the angle can be finely adjusted to ensure zeroing under the free state of the sensor), measure the offset angle (±30 degrees), and adjust the level (threaded column) up and down. The structure of the present invention is simple, safe to use, convenient to operate, and due to the universality of related sensors, the present invention can be popularized for the installation and debugging of the same type of sensors in automobiles, ships, etc.

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

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

[0006] The chassis 1 is a dial, on the upper surface of which there is an angle scale of ±30° engraved at one side edge, with an accuracy of 1°. There are two arc-bottom holes made at the center of the chassis 1, and the two are symmetrically arranged on the same circumference along the axis where the 0° scale is located. There are also two mounting holes made on the chassis 1 near the angle scale, and the two holes are also symmetric along the axis where the 0° scale is located. There are another 4 bolt holes evenly distributed along the circumference on the chassis 1, and a gasket is fixed at the bottom of the bolt holes. The chassis 1 is lifted as a whole by using the gasket and fixed on the repair platform through a full-thread hexagon head bolt, playing a role of fixing and protecting.

[0007] The product fixing plate 5 is a square plate placed vertically. Holes are made in its upper part for installing the product to be debugged. Two mounting holes are symmetrically made on its lower surface. After two fully threaded hexagon bolts respectively pass upward through the two arc-bottom holes on the chassis 1 from the lower side, they 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-bottom holes.

[0008] The pressing plate 2 is a strip-shaped plate, and through holes are made at both ends, and there are two with the same structure in total.

[0009] The threaded rods 4 are designed with a fully threaded outer shape, and there are two in total. Their lower ends are fixedly installed in the two mounting holes on the chassis 1 through hexagon nuts. The two pressing plates 2 are stacked up and down, and the through holes at their two ends are inserted into the two threaded rods 4 from the upper end, and their positions are fixed through four hexagon nuts after insertion.

[0010] The guide plate 3 is a long strip-shaped plate. It passes through between the two pressing plates 2. The height of the guide plate 3 is controlled by adjusting the position of the pressing 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, and the other end extends above the angle scale of the chassis 1. An observation hole is made at the position corresponding to above the angle scale of the chassis 1 on the guide plate 3 for visual reading; after tightening the four hexagon nuts at the upper end of the threaded rod 4 to make the two pressing plates 2 tightly press and fix the guide plate 3, visual reading is carried out through the observation hole.

[0011] A usage method of an aircraft sensor installation device includes: fixing the product to be debugged on the product fixing plate 5, rotating the product fixing plate 5 along the two arc-bottom holes on the chassis 1 to realize the self-rotation zero adjustment of the product to be debugged in a free state and ensure self-rotation zeroing; after zeroing, align the guide plate 3 with the top groove of the product to be debugged and insert it, tighten the four hexagon nuts at the upper end of the threaded rod 4 to make the two pressing plates 2 tightly press and fix the guide plate 3, visually read through the observation hole, and adjust and repair the electronic control system according to the reading in cooperation with the fixed parameters; after adjustment, use the installation device again for inspection.

[0012] The beneficial effects of the present invention: The present invention provides a special sensor installation device with plug-in bolt positioning and its usage method, which can be used immediately after "plugging in", with self-rotation zeroing and up-and-down zeroing, and the angle is visually visible (±30 degrees). The structure is simple and practical, with high practicability, quickness, operability and safety. At the same time, it can also improve the repair efficiency of the accessories after the aircraft sensor is disassembled (the special sensor installation device with plug-in bolt positioning can be directly inserted into the internal slot of the sensor), and reduce the situation that the repair efficiency is affected due to the improper selection of tools by the worker and the difficulty of fixing the sensor, as well as reduce the probability of sensor scrapping. Description of the Drawings

[0013] Figure 1 It is the front view of the overall structure of the present invention.

[0014] Figure 2 This is the left view of the overall structure of the present invention.

[0015] Figure 3 This is the top view of the overall structure of the present invention.

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

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

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

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

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

[0021] Among them, 1 is the chassis, 2 is the pressure plate, 3 is the guide plate, 4 is the threaded rod, and 5 is the product fixing plate. Specific Embodiments

[0022] In order to make the purpose, technical solutions and advantages of the present invention clearer and more understandable, the following will describe the specific embodiments of the present invention in detail according to the technical solutions.

[0023] An aircraft sensor installation device, 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, as Figures 1 to 3 .

[0024] As Figure 4 , the chassis 1 is a dial, on one side edge of its upper surface, there are angle scales of ±30°, with an accuracy of 1°, at the center of the chassis 1, there are two arc-bottom holes, and the two are symmetrically arranged on the same circumference along the axis where the 0° scale is located. There are also two installation holes on the chassis 1 near the angle scale, and the two holes are also symmetric along the axis where the 0° scale is located. There are another 4 bolt holes evenly distributed along the circumference on the chassis 1, and a gasket is fixed at the bottom of the bolt holes. The chassis 1 is lifted as a whole by 12 mm by using the gasket and fixed on the repair platform through a full-thread hexagon head bolt to play a role of fixing and protecting.

[0025] As Figure 8, the product fixing plate 5 is a vertically placed square plate, with holes made in its upper part for installing the product to be debugged by means of fully threaded hexagon head bolts and wing nuts. Two mounting holes are symmetrically made on its lower surface. Two fully threaded hexagon bolts, together with elastic washers and flat washers, respectively pass through the two arc bottom holes on the chassis 1 from the lower side upwards and are then 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 bottom holes.

[0026] As Figure 5 , the pressing plate 2 is a strip-shaped plate, with through holes made at both ends, and there are two with the same structure.

[0027] As Figure 7 , the threaded rods 4 are designed with a fully threaded outer shape, and there are two in total. The lower ends of the two are fixedly installed in the two mounting holes on the chassis 1 through hexagon nuts. The two pressing plates 2 are stacked up and down, and the through holes at both ends are inserted into the two threaded rods 4 from the upper end. After insertion, the positions are fixed by four hexagon nuts.

[0028] As Figure 6 , the guide plate 3 is a long strip-shaped plate, which passes through between the two pressing plates 2. The height of the guide plate 3 is controlled by adjusting the position of the pressing 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, and the other end extends above the angle scale of the chassis 1. An observation hole is made at the position corresponding to the angle scale of the chassis 1 on the guide plate 3 for visual reading; after tightening the four hexagon nuts at the upper end of the threaded rod 4 to make the two pressing plates 2 clamp and fix the guide plate 3, visual reading is carried out through the observation hole.

[0029] A usage method of an aircraft sensor installation device includes: fixing the product to be debugged on the product fixing plate 5, rotating the product fixing plate 5 along the two arc bottom holes on the chassis 1 to realize the self-rotation zero adjustment of the product to be debugged in the free state and ensure the self-rotation zero; after zeroing, align the guide plate 3 with the top groove of the product to be debugged and insert it. Tighten the four hexagon nuts at the upper end of the threaded rod 4 to make the two pressing plates 2 clamp and fix the guide plate 3, and visually read the number through the observation hole. Adjust and repair the electronic control system according to the reading in cooperation with the fixed parameters; after adjustment, use the installation device again for inspection.

[0030] In summary, the above is only a preferred embodiment of the present invention and is not used to limit the protection scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. An aircraft sensor installation device, characterized in that, The described installation device includes a chassis (1), a pressing plate (2), a guide plate (3), a threaded rod (4), and a product fixing plate (5); On one side edge of the upper surface of the chassis (1), an angular scale of ±30° is engraved. At the center of the chassis (1), two arc-bottom holes are made, and the two 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. The product to be debugged is installed on its upper part and placed in the two arc-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-bottom holes; The pressing plate (2) is a strip-shaped plate, and through holes are made at both ends, and there are two with the same structure; There are two threaded rods (4) in total, which are symmetrically installed on the chassis (1) near the angular scale along the axis where the 0° scale is located on the chassis (1). The two pressing plates (2) are stacked up and down, and the through holes at both ends are inserted into the two threaded rods (4) from the upper end. After insertion, their positions are fixed by four hexagon nuts; The guide plate (3) is a long strip-shaped plate. It passes through between the two pressing plates (2). The height of the guide plate (3) is controlled by adjusting the position of the pressing 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, and the other end extends above the angular scale of the chassis (1).

2. The aircraft sensor mounting device according to claim 1, wherein The angular scale accuracy of the chassis (1) is 1°.

3. The aircraft sensor mounting device according to claim 1, wherein, A plurality of spacer rings are fixed at the bottom of the chassis (1) for raising the chassis (1).

4. The aircraft sensor mounting device according to claim 1, characterized in that, Observation holes are made at the position corresponding to above the angular scale of the chassis (1) on the guide plate (3) for visual reading.

5. A method for using the aircraft sensor installation device according to any one of claims 1-4, characterized in that Fix the product to be debugged on the product fixing plate (5), rotate the product fixing plate (5) along the two arc-bottom holes on the chassis (1) to achieve the self-rotation zero adjustment of the product to be debugged in a free state; after zeroing, align the guide plate (3) with the top groove of the product to be debugged and insert it, tighten the two pressing plates (2) to press and fix the guide plate (3), read the angular scale value, and adjust and repair the electronic control system according to the reading in combination with the fixed parameters.

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