Aircraft ground arresting cable force measuring sensor

Abstract

The utility model relates to the technical field of aircraft ground arresting cable force measurement, specifically relates to a kind of aircraft ground arresting cable force measurement sensor, including elastomer, sealing assembly and strain gauge unit;The elastomer includes measurement section, strain section and lead section, the strain section is between measurement section and lead section, the strain gauge unit is arranged on strain section, the sealing assembly is sleeved in the outside of strain section and is sealingly connected with strain section;Cable is provided on the lead section, and the end of the cable extends to strain section and is connected with strain gauge unit;Utilize measurement section and arresting cable joint to drive strain section to occur microstrain, then utilize the strain gauge set on strain section, the elastomer bearing pressure can be obtained, the force measurement of arresting cable is completed;Through six-column structure, both the upper limit of its bearing can be increased, and the accuracy of more than 0.05%FS can be realized, the force value is more accurate in the process of measuring force, and the performance is more excellent.

Description

Technical Field

[0001] This utility model relates to the field of aircraft ground arresting cable force measurement technology, specifically to an aircraft ground arresting cable force measurement sensor. Background Technology

[0002] Aircraft arresting cables are key devices used to shorten the landing taxi distance of aircraft, and the accurate measurement of their arresting tension directly affects aircraft safety and equipment lifespan.

[0003] For example, Chinese utility model patent application CN120397280A discloses an aircraft arresting system, an energy-absorbing device, and a method for testing mechanical performance. The aircraft arresting system includes: an energy-absorbing system comprising an energy-absorbing component, which includes multiple energy-absorbing devices connected end-to-end. Each energy-absorbing device includes a slider with a pawl, a ratchet groove, a force transmission rod, and an elastic buffer. The force transmission rod is connected to the slider with the pawl, and the slider with the pawl is disposed in the ratchet groove and cooperates with the ratchet groove to form a sliding pair. The elastic buffer is used to connect the force transmission rod and the ratchet groove respectively; a pulley assembly, on which one energy-absorbing system is mounted; and an arresting cable, one end of which is connected to one energy-absorbing system via the pulley assembly. On the force transmission rod, the other end is used to connect to the force transmission rod of the first energy absorption device of another energy absorption system after passing through another set of pulley assemblies; the mechanical performance test method of the energy absorption device is to conduct a static loading experiment on the above-mentioned energy absorption device, obtain the force-displacement curves generated by different loading methods and calculate the energy absorption performance; use the numerical simulation software ABAQUS to perform numerical simulation of the static loading experiment, and at the same time complete the finite element numerical simulation of the impact and obtain the structure that undergoes the main deformation, and on this basis, perform simulation analysis on the structure that undergoes the main deformation; perform theoretical analysis on the structural components that undergo the main deformation, and on this basis, combine the finite element numerical simulation results to calculate the force-displacement curve of the energy absorption metamaterial unit and compare it with the static loading experiment results.

[0004] Measuring arresting force is usually quite complex, which increases the difficulty of measurement. It also requires modification of the aircraft's arresting system, which is costly and cannot meet the actual needs of use. Utility Model Content

[0005] The purpose of this invention is to provide a ground-based arresting cable force measurement sensor for aircraft, thereby solving the technical problem of the difficulty in measuring arresting cable force.

[0006] The solution of this utility model to the above-mentioned technical problems is as follows: An aircraft ground arresting cable force measurement sensor includes an elastomer, a sealing assembly, and a strain gauge unit; The elastomer includes a measuring section, a strain section, and a lead wire section. The strain section is located between the measuring section and the lead wire section. The strain gauge unit is disposed on the strain section. The sealing assembly is sleeved on the outside of the strain section and is sealed to the strain section. A cable is disposed on the lead wire section, and the end of the cable extends to the strain section and is connected to the strain gauge unit.

[0007] Further, the measuring section is provided with a snap-fit ​​groove, and a measuring protrusion is provided in the snap-fit ​​groove, with the measuring protrusion arranged along the inner wall of the snap-fit ​​groove.

[0008] Further defined, the strain section includes a sealing section, a connecting section, and multiple strain columns. The array of multiple strain columns is disposed between the sealing section and the connecting section. The strain gauge unit is disposed on the strain columns. The sealing assembly is sleeved on the outside of the multiple strain columns. The sealing assembly and the connecting section are connected by screws, and the sealing assembly and the sealing section are sealed together. The sealing section is located between the strain columns and the measuring section, and the connecting section is located between the strain columns and the lead wire section.

[0009] Further specified, the sealing assembly includes a U-shaped outer shell and a cover plate. Connecting platforms are provided on both sides of the inner wall of the U-shaped outer shell. The connecting platforms are close to the opening of the U-shaped outer shell. The cover plate is located at the opening of the U-shaped outer shell and is connected to the U-shaped outer shell through the connecting platforms. A first sealing groove is provided on the corresponding side of the connecting platforms and the U-shaped outer shell. A conductive rubber strip is provided in the first sealing groove. A second sealing groove is provided on the sealing section, and a conductive rubber strip is provided in the second sealing groove. The U-shaped outer shell is sealed to the U-shaped outer shell through the conductive rubber strip.

[0010] Further specifying, the strain gauge unit includes two transverse strain gauges and two vertical strain gauges, with the two transverse strain gauges and the two vertical strain gauges arranged on opposite sides of the strain column, and the transverse strain gauges and vertical strain gauges arranged adjacent to each other.

[0011] Further specified, the number of strain columns is six, the array of six strain columns is arranged between the sealing section and the connecting section, the number of strain gauge units is six, and the strain gauge units are arranged in a one-to-one correspondence with the strain columns.

[0012] Further specified, the lead segment is provided with a connector, a conductive rubber strip and a washer, the conductive rubber strip is located between the connector and the washer, and the end of the cable passes through the connector, the conductive rubber strip and the washer in sequence to extend to the strain section and connect with the strain gauge unit.

[0013] Further defined, the two transverse strain gauges in the first strain gauge unit, the two transverse strain gauges in the second strain gauge unit, the two transverse strain gauges in the third strain gauge unit, the two vertical strain gauges in the third strain gauge unit, the two vertical strain gauges in the second strain gauge unit, the two vertical strain gauges in the first strain gauge unit, the two transverse strain gauges in the sixth strain gauge unit, the two transverse strain gauges in the fifth strain gauge unit, the two transverse strain gauges in the fourth strain gauge unit, the two vertical strain gauges in the fourth strain gauge unit, the two vertical strain gauges in the fifth strain gauge unit, and the two vertical strain gauges in the sixth strain gauge unit constitute four bridge circuits; The transverse strain gauge in the first strain gauge unit and the vertical strain gauge in the sixth strain gauge unit are both connected to the negative output terminal. The vertical strain gauge in the first strain gauge unit and the transverse strain gauge in the sixth strain gauge unit are connected to the positive output terminal. The positive input power supply is connected between the transverse strain gauge and the vertical strain gauge in the third strain gauge unit, and the negative input power supply is connected between the transverse strain gauge and the vertical strain gauge in the fourth strain gauge unit.

[0014] Further specified, the transverse strain gauge in the first strain gauge unit is connected to the negative output terminal via a zero-point compensation wire, and the vertical strain gauge in the sixth strain gauge unit is connected to the negative output terminal via a temperature drift compensation wire; Further specifying, in the third strain gauge unit, the transverse strain gauge and the vertical strain gauge are connected to the positive terminal of the input power supply through a compensation resistor and a reduced output resistor; in the fourth strain gauge unit, the transverse strain gauge and the vertical strain gauge are connected to the negative terminal of the input power supply through a compensation resistor and a reduced output resistor.

[0015] The beneficial effects of this utility model are as follows: This invention utilizes the connection between the measuring section and the arresting cable to induce micro-strain in the strain section. The strain gauge installed on the strain section can then be used to obtain the bearing pressure of the elastic body, thus completing the force measurement of the arresting cable. The six-column structure not only increases its upper limit of bearing capacity but also achieves an accuracy of over 0.05%FS, resulting in more accurate force values ​​and superior performance during force measurement. Attached Figure Description

[0016] Figure 1 This is a structural diagram of the aircraft ground arresting cable force measurement sensor of this utility model; Figure 2 This is a structural diagram of the elastomer of this utility model; Figure 3 This is a cross-sectional view of the elastomer of this utility model; Figure 4 This is a structural diagram of the U-shaped outer shell of this utility model; Figure 5This is a schematic diagram showing the arrangement of the strain gauge unit of this utility model on the four end faces of the strain column; Figure 6 This invention relates to a bridge circuit for measuring the force of aircraft ground arresting cables.

[0017] In the diagram, 100-elastic body; 110-measuring section; 111-snap groove; 112-measuring protrusion; 120-strain section; 121-sealing section; 122-connecting section; 123-strain column; 124-second sealing groove; 130-lead section; 131-connecting nozzle; 200-sealing assembly; 210-U-shaped housing; 211-connecting platform; 212-first sealing groove; 220-cover plate; 300-cable; 401-zero point compensation wire; 402-temperature drift compensation wire; 403-compensation resistor; 404-output resistance reduction. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. The components of the embodiments of this utility model described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0019] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0020] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0021] In the description of the embodiments of this utility model, it should be noted that if terms such as "upper," "lower," "horizontal," or "inner" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the utility model product is in use, they are only for the convenience of describing the 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 be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the utility model. Furthermore, terms such as "first" and "second" are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0022] Example 1 refer to Figures 1-4 This utility model provides a ground-based arresting cable force measurement sensor for aircraft, including an elastic body 100, a sealing assembly 200, and a strain gauge unit. The elastic body 100 includes a measuring section 110, a strain section 120, and a lead wire section 130. The strain section 120 is located between the measuring section 110 and the lead wire section 130, and the strain gauge unit is mounted on the strain section 120. During measurement, the lead wire end 130 is threadedly connected to the ground arresting trolley, and the measuring section 110 is used to clamp and support the arresting cable, thereby generating micro-strain in the strain section 120. The strain gauge unit enables real-time measurement of the arresting cable force.

[0023] The sealing assembly 200 is sleeved on the outside of the strain section 120 and sealed to the strain section 120 to ensure the working environment of the strain section 120. A cable 300 is provided on the lead section 130. One end of the cable 300 extends to the strain section 120 and is connected to the strain gauge unit. The cable 300 can be a four-core shielded cable. The other end of the cable 300 is connected to the analog signal port of the force signal acquisition device to convert the analog signal output by the strain gauge unit into a digital signal, so as to realize online and offline force signal acquisition.

[0024] To ensure a reliable connection between the cable 300 and the lead segment 130, a threaded hole is made at the end of the lead segment 130. A washer and a conductive rubber strip are filled into the threaded hole before the connector 131 is connected. The connector 131 is used to reliably connect the cable 300.

[0025] Specifically, a snap-fit ​​groove 111 is provided on the measuring section 110. In order to ensure reliable contact between the snap-fit ​​groove 111 and the barrier cable, reduce the contact area between the snap-fit ​​groove 111 and the barrier cable, and ensure stress concentration, a measuring protrusion 112 is provided in the snap-fit ​​groove 111. The measuring protrusion 112 is provided along the inner wall of the snap-fit ​​groove 111.

[0026] Further explanation: the strain section 120 includes a sealing section 121, a connecting section 122, and multiple strain columns 123. The sealing section 121 is located between the strain columns 123 and the measuring section 110, and the connecting section 122 is located between the strain columns 123 and the lead wire section 130. The array of multiple strain columns 123 is arranged between the sealing section 121 and the connecting section 122. By setting multiple strain columns 123, the load-bearing capacity of the elastic body 100 can be increased, and the measurement accuracy can be improved. Preferably, the number of strain columns 123 is six, and the six strain columns 123 are arranged in a 2×3 manner, with three strain columns 123 spaced apart along the length direction of the elastic body 100.

[0027] At this time, a strain gauge unit is provided on each strain column 123. The sealing assembly 200 is sleeved on the outside of all strain columns 123 to protect the strain section 120. The sealing assembly 200 and the connecting section 122 are connected by M4 countersunk screws to ensure a stable and reliable connection. At the same time, the sealing assembly 200 and the sealing section 121 need to maintain a sealed connection.

[0028] To further explain, the sealing assembly 200 includes a U-shaped housing 210 and a cover plate 220. The U-shaped housing 210 is fitted around the periphery of the strain section 120. One end of the U-shaped housing 210 covers the outside of the sealing section 121, and the other end of the U-shaped housing 210 covers the outside of the connecting section 122. At this time, a second sealing groove 124 is opened on the periphery of the sealing section 121. A conductive rubber strip is provided in the second sealing groove 124. When connecting, the U-shaped housing 210 is sealed to the U-shaped housing 210 by squeezing the conductive rubber strip. The second sealing groove 124 is connected to the connecting section 122 by an M4 countersunk screw.

[0029] The U-shaped opening of the U-shaped housing 210 is connected to the cover plate 220, and the connection position needs to be sealed. At this time, a connecting platform 211 is set on both sides of the inner wall of the U-shaped housing 210. The connecting platform 211 is close to the opening of the U-shaped housing 210. The cover plate 220 is located at the opening of the U-shaped housing 210 and is connected to the U-shaped housing 210 through the connecting platform 211. The corresponding side ends of the connecting platform 211 and the U-shaped housing 210 are provided with a first sealing groove 212. A conductive rubber strip is set in the first sealing groove 212. When the cover plate 220 is connected to the U-shaped housing 210, the corresponding conductive rubber strip is squeezed to achieve a sealed connection. This achieves a sealed protection between the U-shaped housing 210 and the cover plate 220 while ensuring continuous conductivity, thus forming an effective electromagnetic shield.

[0030] When connecting the cover plate 220 to the connecting platform 211, four M3 countersunk screws are used. An appropriate amount of Loctite 243 thread fastening adhesive can be applied to the threaded joint to make the threaded connection secure and reliable.

[0031] To further explain, the strain gauge unit includes two transverse strain gauges and two vertical strain gauges. The two transverse strain gauges and the two vertical strain gauges are all arranged on opposite sides of the strain column 123, with the transverse strain gauges and the vertical strain gauges arranged adjacent to each other.

[0032] For ease of explanation, the b-th strain gauge on the a-th strain column 123 will be denoted as ab. (Refer to...) Figure 5 The second strain gauge 123 consists of a transverse strain gauge 2-1, a vertical strain gauge 2-2, a transverse strain gauge 2-3, and a vertical strain gauge 2-4.

[0033] refer to Figure 6 The specific circuit of the aircraft ground arresting cable force measurement sensor bridge is as follows: Transverse strain gauge 3-1, Transverse strain gauge 1-1, Transverse strain gauge 2-1, Transverse strain gauge 2-3, Transverse strain gauge 3-1, Transverse strain gauge 3-3, Vertical strain gauge 3-2, Vertical strain gauge 3-4, Vertical strain gauge 2-2, Vertical strain gauge 2-4, Vertical strain gauge 1-2, Vertical strain gauge 1-4, Transverse strain gauge 6-1, Transverse strain gauge 6-3, Transverse strain gauge 5-1, Transverse strain gauge 5-3, Transverse strain gauge 4-3, Transverse strain gauge 4-1, Vertical strain gauge 4-2, Vertical strain gauge 4-4, Vertical strain gauge 5-2, Vertical strain gauge 5-4, Vertical strain gauge The strain gauge 6-2 and the vertical strain gauge 6-4 are connected in sequence. The transverse strain gauge 3-1 is connected to the negative output terminal S- through the zero-point compensation wire 401. The vertical strain gauge 6-4 is also connected to the negative output terminal S- through the temperature drift compensation wire 402. The positive output terminal S+ is connected between the vertical strain gauge 1-4 and the transverse strain gauge 6-1. The positive input power supply terminal E+ is connected between the transverse strain gauge 3-3 and the vertical strain gauge 3-2 through the compensation resistor 403 and the output reduction resistor 404. The negative input power supply terminal E- is connected between the transverse strain gauge 4-1 and the vertical strain gauge 4-2 through the compensation resistor 403 and the output reduction resistor 404.

[0034] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. It will be apparent to those skilled in the art that this utility model is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or basic characteristics of this utility model. Therefore, the embodiments should be considered exemplary and non-limiting in all respects. The scope of this utility model is defined by the appended claims rather than the foregoing description, and thus all variations falling within the meaning and scope of equivalents of the claims are intended to be included within this utility model. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0035] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can be appropriately combined to form other embodiments that can be understood by those skilled in the art. The above content is only for illustrating the technical concept of this utility model and should not be used to limit the scope of protection of this utility model. Any modifications made to the technical solutions based on the technical concept proposed by this utility model shall fall within the scope of protection of the claims of this utility model.

[0036] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this utility model.

Claims

1. A ground-based arresting cable force measurement sensor for aircraft, characterized in that, It includes an elastomer (100), a sealing assembly (200), and a strain gauge unit; The elastomer (100) includes a measuring section (110), a strain section (120), and a lead section (130). The strain section (120) is located between the measuring section (110) and the lead section (130). The strain gauge unit is disposed on the strain section (120). The sealing assembly (200) is sleeved on the outside of the strain section (120) and sealed to the strain section (120). A cable (300) is disposed on the lead section (130). The end of the cable (300) extends to the strain section (120) and is connected to the strain gauge unit.

2. The aircraft ground arresting cable force measurement sensor according to claim 1, characterized in that, The measuring section (110) is provided with a snap-fit ​​groove (111), and a measuring protrusion (112) is provided in the snap-fit ​​groove (111), and the measuring protrusion (112) is provided along the inner wall of the snap-fit ​​groove (111).

3. The aircraft ground arresting cable force measurement sensor according to claim 2, characterized in that, The strain section (120) includes a sealing section (121), a connecting section (122), and multiple strain columns (123). The array of multiple strain columns (123) is arranged between the sealing section (121) and the connecting section (122). The strain gauge unit is arranged on the strain column (123). The sealing assembly (200) is sleeved on the outside of the multiple strain columns (123). The sealing assembly (200) and the connecting section (122) are connected by screws. The sealing assembly (200) and the sealing section (121) are sealed together. The sealing section (121) is located between the strain column (123) and the measuring section (110). The connecting section (122) is located between the strain column (123) and the lead wire section (130).

4. The aircraft ground arresting cable force measurement sensor according to claim 3, characterized in that, The sealing assembly (200) includes a U-shaped outer shell (210) and a cover plate (220). Connecting platforms (211) are provided on both sides of the inner wall of the U-shaped outer shell (210). The connecting platforms (211) are close to the opening of the U-shaped outer shell (210). The cover plate (220) is located at the opening of the U-shaped outer shell (210) and is connected to the U-shaped outer shell (210) through the connecting platforms (211). The connecting platforms (211) and the corresponding side ends of the U-shaped outer shell (210) are provided with first sealing grooves (212). Conductive rubber strips are provided in the first sealing grooves (212). The sealing section (121) is provided with a second sealing groove (124), and a conductive rubber strip is provided in the second sealing groove (124). The U-shaped outer shell (210) is sealed to the U-shaped outer shell (210) through the conductive rubber strip.

5. The aircraft ground arresting cable force measurement sensor according to claim 4, characterized in that, The strain gauge unit includes two transverse strain gauges and two vertical strain gauges. The two transverse strain gauges and the two vertical strain gauges are arranged on opposite sides of the strain column (123), with the transverse strain gauges and the vertical strain gauges arranged adjacent to each other.

6. The aircraft ground arresting cable force measurement sensor according to claim 5, characterized in that, The number of strain columns (123) is six, and the array of six strain columns (123) is arranged between the sealing section (121) and the connecting section (122). The number of strain gauge units is six, and the strain gauge units are arranged in a one-to-one correspondence with the strain columns (123).

7. The aircraft ground arresting cable force measurement sensor according to claim 6, characterized in that, The lead segment (130) is provided with a connector (131), a conductive rubber strip and a washer. The conductive rubber strip is located between the connector (131) and the washer. The end of the cable (300) passes through the connector (131), the conductive rubber strip and the washer in sequence to extend to the strain segment (120) and is connected to the strain gauge unit.

8. The aircraft ground arresting cable force measurement sensor according to claim 6, characterized in that, The two transverse strain gauges in the first strain gauge unit, the two transverse strain gauges in the second strain gauge unit, the two transverse strain gauges in the third strain gauge unit, the two vertical strain gauges in the third strain gauge unit, the two vertical strain gauges in the second strain gauge unit, the two vertical strain gauges in the first strain gauge unit, the two transverse strain gauges in the sixth strain gauge unit, the two transverse strain gauges in the fifth strain gauge unit, the two transverse strain gauges in the fourth strain gauge unit, the two vertical strain gauges in the fourth strain gauge unit, the two vertical strain gauges in the fifth strain gauge unit, and the two vertical strain gauges in the sixth strain gauge unit constitute four bridge circuits; The transverse strain gauge in the first strain gauge unit and the vertical strain gauge in the sixth strain gauge unit are both connected to the negative output terminal. The vertical strain gauge in the first strain gauge unit and the transverse strain gauge in the sixth strain gauge unit are connected to the positive output terminal. The positive input power supply is connected between the transverse strain gauge and the vertical strain gauge in the third strain gauge unit, and the negative input power supply is connected between the transverse strain gauge and the vertical strain gauge in the fourth strain gauge unit.

9. The aircraft ground arresting cable force measurement sensor according to claim 8, characterized in that, The transverse strain gauge in the first strain gauge unit is connected to the negative output terminal via a zero-point compensation wire (401), and the vertical strain gauge in the sixth strain gauge unit is connected to the negative output terminal via a temperature drift compensation wire (402).

10. The aircraft ground arresting cable force measurement sensor according to claim 9, characterized in that, In the third strain gauge unit, the transverse strain gauge and the vertical strain gauge are connected to the positive terminal of the input power supply through a compensation resistor (403) and a drop output resistor (404); in the fourth strain gauge unit, the transverse strain gauge and the vertical strain gauge are connected to the negative terminal of the input power supply through a compensation resistor (403) and a drop output resistor (404).

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