Aircraft gun spring force measuring device

Abstract

The invention discloses an aircraft gun spring force measuring device, and belongs to the technical field of aviation equipment testing. A fixed seat is mounted on a sliding table of a guide rail, a sensor assembly is mounted between the fixed seat and a stable seat, a guide seat is inserted into the stable seat, a spring penetrates into a long rod of the stable seat, two fixed plates are fixed at the other end of the guide rail, and a slot is formed between the two fixed plates; the insertion plate with a through hole is inserted into the insertion groove, the long rod of the guide seat is inserted into the through hole of the insertion plate, the sliding table is moved, the spring is compressed through the guide seat and the insertion plate, and the elastic force of the spring is measured. The method has the advantages of practicability, convenience, accuracy and safety, the aircraft gun spring measuring efficiency can be improved, and the situation that the compression is complex due to inaccurate positioning of operators is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation equipment testing and relates to a spring force measuring device for an aircraft cannon. Background Art

[0002] After disassembling a cannon on a certain aircraft, the maintenance process requires repeated testing of the spring tension within the cannon and recording the pressure after multiple compressions as essential parameters for cannon maintenance. Because the cannon spring is long and has a small inner diameter, compression measurement is difficult. Furthermore, spring sizes vary, and conventional measuring equipment has a short travel range, making it incapable of measuring specific cannon springs. Furthermore, it is also unable to quickly swap springs of different specifications for measurement. Consequently, existing equipment is unable to measure the spring tension of this cannon spring. Summary of the Invention

[0003] The present invention provides an aircraft cannon spring force measuring device, which can accurately position the aircraft cannon spring. By replacing a guide seat and an inserting plate, the elastic force of aircraft cannon springs of different specifications can be quickly measured. The spring is compressed by operating a slideway through a crank, and the spring force can be measured easily and labor-savingly, thereby achieving the purposes of accurate positioning and measurement, labor-saving, and convenient operation.

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

[0005] A spring force measuring device for an aircraft cannon comprises a fixing seat 1, a stabilizing seat 2, a guiding seat 3, a slide rail 4, a first fixing plate 5, a second fixing plate 6, an inserting plate 7, and a sensor assembly 8.

[0006] A slide is provided on the slideway of the slide rail 4, and a handwheel is provided at one end of the slide rail 4 for controlling the movement of the slide; the fixed seat 1 is fixedly connected to the slide, and a vertical plate is provided on its upper surface, on which the sensor assembly 8 and the stable seat 2 are fixed in sequence, and a circular groove is made on the end face of the other side of the stable seat 2; the guide seat 3 includes a circular base plate and a long rod, one end of the long rod is fixedly connected to the center of the circular base plate, and the circular base plate is inserted into the circular groove of the stable seat 2 to make its long rod horizontal. The outer diameter of the long rod is designed according to the inner diameter of the spring to be tested, and the spring to be tested is sleeved on the long rod; circular holes are made at corresponding positions on the upper parts of the first fixed plate 5 and the second fixed plate 6, and bosses are made on both sides of the circular hole on one side of the second fixed plate 6, and the bosses fit with the first fixed plate 5 to form a slot between the first fixed plate 5 and the second fixed plate 6. 5 and the bottom of the second fixed plate 6 are fixed to the other end of the slide rail 4, the circular holes of the two are coaxial with the long rod of the guide seat 3, and the diameter of the circular hole is larger than the outer diameter of the long rod; the thickness and width of the inserting plate 7 are set according to the slot between the first fixed plate 5 and the second fixed plate 6, and a through hole is formed in the middle thereof, and the inner diameter of the through hole is set according to the outer diameter of the long rod of the guide seat 3, and bosses are formed on both sides of the upper portion. The inserting plate 7 is inserted into the slot between the first fixed plate 5 and the second fixed plate 6 and positioned by the boss. After insertion, the through hole of the inserting plate 7 is exposed from the circular holes of the first fixed plate 5 and the second fixed plate 6 and is coaxial, which is used to guide the movement of the guide seat 3. The two ends of the spring to be tested are clamped between the bottom plate of the guide seat 3 and the inserting plate 7. The crank of the slide rail 4 is shaken to operate the guide seat 3 to compress the spring to be tested, and the spring elastic force is measured by the sensor assembly 8.

[0007] Furthermore, the sensor assembly 8 adopts a cylindrical force sensor, including a force sensor, a force display instrument, and an electrical control box. It has a compact structure and is easy to install. The force display instrument has upper and lower limit alarm functions and is placed in a small electrical control box for easy storage, retrieval, and viewing of recorded values.

[0008] Furthermore, the long rod of the guide seat 3 is provided with multiple specifications of different outer diameters to accommodate springs of different inner diameters, and the corresponding inserting plate 7 is also provided with multiple specifications of different through hole inner diameters, and the two are used in combination.

[0009] The beneficial effects of the present invention are as follows: the present invention has a simple and practical structure, and is highly practical, convenient, accurate, and safe. It can also improve the measurement efficiency of aircraft cannon springs and reduce the occurrence of complex compression caused by inaccurate positioning of operators. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 It is a three-dimensional schematic diagram of the overall structure of the present invention.

[0011] Figure 2 It is a front view of the overall structure of the present invention.

[0012] Figure 3Schematic diagram of the fixed seat structure, where (a) is the main view, (b) is the side view, and (c) is the top view.

[0013] Figure 4 Schematic diagram of the stabilizing seat structure, where (a) is the main view and (b) is the cross-sectional view.

[0014] Figure 5 This is a schematic diagram of the guide seat structure.

[0015] Figure 6 Schematic diagram of the first fixed plate structure, where (a) is the main view and (b) is the side view.

[0016] Figure 7 Schematic diagram of the second fixed plate structure, where (a) is the main view and (b) is the side view.

[0017] Figure 8 Schematic diagram of the plug-in board structure, where (a) is the main view and (b) is the side view.

[0018] Among them, 1 is a fixed seat, 2 is a stable seat, 3 is a guide seat, 4 is a slide rail, 5 is a first fixed plate, 6 is a second fixed plate, 7 is an inserting plate, and 8 is a sensor assembly. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical solutions and advantages of the present invention more clear, the specific implementation methods of the present invention will be described in detail below based on the technical solutions.

[0020] A spring force measuring device for an aircraft cannon, such as Figure 1 and Figure 2 As shown, it includes a fixing seat 1, a stabilizing seat 2, a guiding seat 3, a slide rail 4, a first fixing plate 5, a second fixing plate 6, an inserting plate 7, and a sensor assembly 8.

[0021] The slide rail 4 is provided with a slide, and a hand wheel is provided at one end of the slide rail 4 for controlling the movement of the slide; Figure 3 As shown, the fixed seat 1 is fixedly connected to the slide, and a vertical plate is provided on its upper surface; the sensor assembly 8 is a cylindrical force sensor, equipped with a force value display instrument, with upper and lower limit alarm functions, and the instrument is placed in a small electric control box; one side of the sensor assembly 8 is fixedly connected to the vertical plate of the fixed seat 1, and the other side is fixedly connected to the stable seat 2, and the other side end surface of the stable seat 2 is made of a circular groove, as shown Figure 4 As shown; Figure 5 As shown, the guide seat 3 includes a circular base plate and a long rod. The center of the circular base plate is formed with a threaded hole, and one end of the long rod is formed with a threaded head, which is threadedly connected to the threaded hole of the circular base plate. The circular base plate is inserted into the circular groove of the stable seat 2 to make the long rod horizontal. The long rod is made of various specifications with different outer diameters, which are selected according to the inner diameter of the spring to be tested. The spring to be tested is sleeved on the long rod; Figure 6and Figure 7 As shown, circular holes are made at corresponding positions on the upper parts of the first fixing plate 5 and the second fixing plate 6, and bosses are made on both sides of the circular hole on one side of the second fixing plate 6. The bosses fit with the first fixing plate 5 to form a slot between the first fixing plate 5 and the second fixing plate 6. The bottoms of the first fixing plate 5 and the second fixing plate 6 are fixed to the other end of the slide rail 4. The circular holes of the two are coaxial with the long rod of the guide seat 3, and the diameter of the circular holes is larger than the outer diameter of the long rod; as shown Figure 8 As shown, the thickness and width of the insert plate 7 are set according to the slot between the first fixed plate 5 and the second fixed plate 6, a through hole is formed in the middle thereof, the inner diameter of the through hole is set according to the outer diameter of the long rod of the guide seat 3, and bosses are formed on both sides of the upper portion. The insert plate 7 is inserted into the slot between the first fixed plate 5 and the second fixed plate 6 and positioned by the bosses. After insertion, the through hole of the insert plate 7 is exposed from the circular holes of the first fixed plate 5 and the second fixed plate 6 and is coaxial, and is used to guide the movement of the guide seat 3. The two ends of the spring to be tested are clamped between the bottom plate of the guide seat 3 and the insert plate 7. The crank of the slide rail 4 is shaken to operate the guide seat 3 to compress the spring to be tested, and the sensor assembly 8 is used to measure the spring force.

[0022] When in use, select the appropriate guide seat 3 according to the inner diameter of the spring to be tested, put the spring to be tested on the long rod of the guide seat 3, select the matching plug-in plate 7 according to the outer diameter of the long rod and insert it into the slot between the first fixed plate 5 and the second fixed plate 6; shake the crank of the slide rail 4, and the guide seat 3 moves with the slide to the through hole of the plug-in plate 7 until the two ends of the spring are respectively fitted with the bottom plate of the guide seat 3 and the plug-in plate 7; continue to shake the crank to compress the aircraft gun spring and measure the elastic force of the aircraft gun spring.

[0023] In summary, the above are only preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. An aircraft cannon spring force measuring device, characterized in that: It comprises a fixed seat (1), a stabilizing seat (2), a guide seat (3), a slide rail (4), a first fixed plate (5), a second fixed plate (6), an inserting plate (7), and a sensor assembly (8); The slideway of the slide rail (4) is provided with a slide, and a hand wheel is provided at one end of the slide rail (4) for controlling the movement of the slide; the fixed seat (1) is fixedly connected to the slide, and a vertical plate is provided on its upper surface, and the sensor assembly (8) and the stable seat (2) are fixed on the vertical plate in sequence, and a circular groove is made on the other end face of the stable seat (2); the guide seat (3) includes a circular base plate and a long rod, one end of the long rod is fixedly connected to the center of the circular base plate, and the circular base plate is inserted into the circular groove of the stable seat (2) to make the long rod horizontal, and the outer diameter of the long rod is designed according to the inner diameter of the spring to be tested, and the spring to be tested is sleeved on the long rod; the corresponding positions of the upper parts of the first fixed plate (5) and the second fixed plate (6) are made with circular holes, and the two sides of the circular hole on one side of the second fixed plate (6) are made with bosses, and the bosses fit with the first fixed plate (5) to form a slot between the first fixed plate (5) and the second fixed plate (6). The bottom of the fixed plate (6) is fixed to the other end of the slide rail (4), and the circular holes of the two are coaxial with the long rod of the guide seat (3), and the diameter of the circular hole is larger than the outer diameter of the long rod; the thickness and width of the inserting plate (7) are set according to the slot between the first fixed plate (5) and the second fixed plate (6), wherein a through hole is formed in the middle thereof, and the inner diameter of the through hole is set according to the outer diameter of the long rod of the guide seat (3), and bosses are formed on both sides of the upper portion thereof, and the inserting plate (7) is inserted into the slot between the first fixed plate (5) and the second fixed plate (6) and positioned by the bosses. After insertion, the through hole of the inserting plate (7) is exposed from the circular holes of the first fixed plate (5) and the second fixed plate (6) and is coaxial, and is used for guiding the movement of the guide seat (3). The two ends of the spring to be measured are clamped between the bottom plate of the guide seat (3) and the inserting plate (7), and the crank of the slide rail (4) is operated to operate the guide seat (3) to compress the spring to be measured, and the spring elastic force is measured by the sensor assembly (8).

2. The aircraft cannon spring force measuring device according to claim 1, characterized in that: The sensor assembly (8) adopts a cylindrical force sensor.

3. The aircraft cannon spring force measuring device according to claim 1, characterized in that: The long rod of the guide seat (3) is provided with multiple specifications of different outer diameters to accommodate springs of different inner diameters, and the corresponding inserting plate (7) is also provided with multiple specifications of different through hole inner diameters, and the two are used in conjunction with each other.

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