A measuring device and a measuring method for tire compression under static load of an aircraft

Abstract

The application discloses a kind of measuring device and measuring method for tire compression under the static load of aircraft, belong to aircraft maintenance guarantee technical field, including main ruler and vice ruler, front wheel measuring mechanism and main wheel measuring mechanism are respectively provided on main ruler, vice ruler is inserted in main ruler, vice ruler is provided with pointer, the other end of vice ruler is connected with horizontal ruler, horizontal ruler and vice ruler are 90 degrees angle.The application uses the above-mentioned measuring device and measuring method for tire compression under the static load of aircraft, the measurement requirement of all tires of aircraft is respectively corresponded by independently arranged front wheel gauge and main wheel gauge, without replacing measuring device, the compression detection of all tires can be completed;Each gauge independently slides and is locked by corresponding limiting screw, avoid the confusion of parameters when measuring different tires, single device can cover the measurement task of full tire of single aircraft, greatly reduce the equipment carrying amount and operation complexity of aircraft maintenance personnel.

Description

Technical Field

[0001] This invention relates to the field of aircraft maintenance and support technology, and in particular to a device and method for measuring tire compression under static load on an aircraft. Background Technology

[0002] The safety of an aircraft's takeoff and landing system is directly related to the safety of every taxiing, takeoff, and landing, as well as passenger safety. The landing gear and its tire system are the core of this critical link. Aircraft tires are the direct components that come into contact with the runway, and they are subjected to extreme loads, impacts, and thermal environments during every landing, taxiing, and braking process. Tire pressure is a commonly used tire condition monitoring parameter for civil aircraft. Many aircraft models measure tire pressure using sensors embedded in the tires. However, for aircraft without tire pressure sensors, tire compression becomes an effective parameter for maintaining the tires of that aircraft model. Tire compression (tire deflection), that is, the radial deformation of a tire under static load, is a comprehensive physical indicator reflecting the tire's inflation status, tire cushioning performance, and aircraft load balance.

[0003] In routine aircraft maintenance and flight support, measuring tire compression before and after flights allows aircraft maintenance personnel to accurately assess tire condition, predict potential malfunctions, optimize maintenance cycles, and reduce maintenance costs. However, traditional pre- and post-flight tire compression checks typically rely on visual inspection or touch to assess tire deformation, judging tire safety and usability based on experience. The results depend heavily on the individual maintenance experience and subjective judgment of the personnel. Factors such as low light at night, glare from rain, or dirty tire surfaces further reduce the accuracy of these judgments, impacting the quality of aircraft inspections. Summary of the Invention

[0004] The purpose of this invention is to provide a device and method for measuring tire compression under static load on an aircraft. By using independently set front wheel gauges and main wheel gauges to meet the measurement requirements of all tires on the aircraft, the compression of all tires can be measured without changing the measuring device. Each gauge slides independently and is locked by corresponding limit screws, avoiding parameter confusion when measuring different tires. A single device can cover the measurement task of all tires on a single aircraft, greatly reducing the amount of equipment carried and the complexity of operation for maintenance personnel.

[0005] To achieve the above objectives, the present invention provides a measuring device for tire compression under static load of an aircraft, including a main scale and a secondary scale. The main scale is respectively provided with a front wheel measuring mechanism and a main wheel measuring mechanism. The secondary scale is inserted into the main scale and slides along the main scale. One end of the secondary scale is provided with a pointer for indicating the scale. The other end of the secondary scale is connected to a horizontal ruler, which forms a 90-degree angle with the secondary scale. The front wheel measuring mechanism includes a front wheel gauge and a front wheel docking assembly. Two front wheel gauges are respectively fitted on both sides of the front end of the main gauge and slide along the main gauge. The left front wheel gauge is used to measure the tire compression of the left front wheel, and the right front wheel gauge is used to measure the tire compression of the right front wheel. The front wheel gauge is provided with scale lines, and the scale lines are provided with red areas for displaying the compression threshold. The side wall of the front wheel gauge is provided with a first limiting screw, which passes through the side wall of the front wheel gauge and contacts the side wall of the main gauge. The front wheel docking assembly is provided on the left side wall of the front end of the main gauge. The main wheel measuring mechanism includes a main wheel measuring scale and a main wheel docking assembly. Two main wheel measuring scales are respectively fitted on both sides of the rear end of the main scale and slide along the main scale. The main wheel measuring scale on the left is used to measure the tire compression of the left main wheel, and the main wheel measuring scale on the right is used to measure the tire compression of the right main wheel. The main wheel measuring scale is provided with scale lines, and the scale lines are provided with red areas for displaying the compression threshold. The main wheel measuring scale is provided with a second limit screw on its side wall. The main wheel docking assembly is located on the right side wall of the front end of the main scale.

[0006] Preferably, the front wheel docking assembly includes a right front wheel aligning claw and a left front wheel aligning claw. A sleeve is provided on the side wall of the right front wheel aligning claw. The left front wheel aligning claw is sleeved on the sleeve and its front end penetrates the side wall of the right front wheel aligning claw. The sleeve is sleeved on the docking shaft and its front end penetrates the side wall of the right front wheel aligning claw. A retaining ring is engaged at the front end of the docking shaft and contacts the side wall of the right front wheel aligning claw.

[0007] Preferably, the main wheel docking assembly is a main wheel mandrel for docking with the main wheel shaft, with one end of the main wheel mandrel connected to the right side wall of the front end of the main scale.

[0008] Preferably, a universal level is provided at the top of the main scale for adjusting the level of the device, a brake block is inserted at the front of the end of the main scale to prevent the auxiliary scale, the front wheel measuring scale and the main wheel measuring scale from slipping off the main scale, and a first fastening screw is inserted at the rear of the end of the main scale, the first fastening screw passing through the main scale and contacting the auxiliary scale.

[0009] Preferably, the end of the auxiliary ruler is provided with an insert block, which is inserted into the inside of the horizontal ruler. A second fastening screw is inserted into the side wall of the horizontal ruler, and the second fastening screw passes through the horizontal ruler and contacts the insert block.

[0010] A method for measuring tire compression under static load on an aircraft includes the following steps: S1: Secure the horizontal ruler to the end of the auxiliary ruler through the insert block and the second fastening screw, and tighten the first fastening screw, the first limit screw and the second limit screw to the movable state; S2: Use a jack to lift the aircraft's test wheel so that the replaced test tire is in a stress-free state for the first calibration; S3: Use the front wheel docking assembly to dock the main ruler with the axle of the front wheel to be tested, pull the auxiliary ruler to make the cross ruler contact the outer edge of the top of the tire to be tested, adjust the main ruler to a vertical state by observing the universal level, and tighten the first fastening screw. S4: Slide the front wheel gauge to align its zero mark with the pointer, tighten the first limit screw, and record the scale of the front wheel gauge on the main scale as the calibration reference value of the front wheel tire to be tested. S5: Loosen the second fastening screw to remove the cross ruler, loosen the first fastening screw to retract the auxiliary ruler, use a jack to lower the aircraft wheel to be tested until the tire under test fully bears the static load, and measure the compression of the front tire under test. S6: Use the front wheel docking assembly to dock the main scale with the axle of the front wheel to be tested. Adjust the main scale to a vertical position by observing the universal level. Pull the auxiliary scale so that the bottom surface of its insert contacts the ground. Tighten the first fastening screw and read the scale value indicated by the pointer on the front wheel gauge. This is the compression of the front tire to be tested. If the compression value enters the red scale area, it indicates that the compression exceeds the standard. The maintenance measures specified in the technical manual should be taken until the measured compression meets the standard. S7: Use the main wheel docking assembly to dock the main ruler with the axle of the main wheel to be tested, pull the auxiliary ruler to make the cross ruler contact the outer edge of the top of the tire to be tested, adjust the main ruler to a vertical state by observing the universal level, and tighten the first fastening screw. S8: Slide the main wheel measuring scale to align its zero mark with the pointer, tighten the second limit screw, and record the scale reading on the main wheel measuring scale as the calibration reference value of the tire to be tested on the main wheel. S9: Loosen the second fastening screw to remove the cross ruler, loosen the first fastening screw to retract the auxiliary ruler, use a jack to lower the aircraft wheel to be tested until the tire under test fully bears the static load, and measure the compression of the main wheel of the tire under test. S10: Use the main wheel docking assembly to dock the main scale with the axle of the main wheel to be tested. Adjust the main scale to a vertical position by observing the universal level. Pull the auxiliary scale so that the bottom surface of its insert contacts the ground. Tighten the first fastening screw and read the scale value indicated by the pointer on the main wheel scale. This is the compression of the tire to be tested on the main wheel. If the compression value enters the red scale area, it indicates that the compression exceeds the standard. The maintenance measures specified in the technical manual should be taken until the measured compression meets the standard. S11: The measuring personnel can choose to perform S3-S6 or S7-S10 depending on the type of tire to be tested; S12: For multiple tires of the same aircraft, complete the initial calibration and record their respective reference values. In subsequent pre-flight and post-flight routine measurements, directly adjust the position of the front wheel gauge or main wheel gauge according to the corresponding reference values, and then measure the tire compression under the current condition according to S6 or S10.

[0011] Preferably, in S3, the left front wheel alignment claw is pushed to extend out of the side wall of the right front wheel alignment claw or retract, thereby switching between the right front wheel alignment mode and the left front wheel alignment mode.

[0012] Therefore, the present invention adopts the above-mentioned device and method for measuring tire compression under static load of aircraft. By independently setting the front wheel gauge and the main wheel gauge respectively to meet the measurement requirements of all tires of the aircraft, the compression of all tires can be detected without changing the measuring device. Each gauge slides independently and is locked by the corresponding limit screw, avoiding parameter confusion when measuring different tires. A single device can cover the measurement task of all tires of a single aircraft, which greatly reduces the equipment carrying volume and operation complexity of maintenance personnel.

[0013] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the overall structure of the tire compression measuring device for aircraft under static load in this invention. Figure 2 This is an exploded view of the specific structure of the tire compression measuring device for aircraft under static load in this invention. Figure 3 This is an exploded view of the main scale in this invention; Figure 4 This is an exploded view of the specific structure of the secondary ruler and the horizontal ruler in this invention.

[0015] Figure Labels 1. Main scale; 2. Secondary scale; 3. Pointer; 4. Horizontal ruler; 5. Front wheel measuring tape; 6. First limit screw; 7. Connecting shaft; 8. Main wheel measuring tape; 9. Second limit screw; 10. Right front wheel alignment claw; 11. Left front wheel alignment claw; 12. Sleeve; 13. Retaining ring; 14. Main wheel alignment shaft; 15. Universal level; 16. Brake block; 17. First fastening screw; 18. Insert block; 19. Second fastening screw. Detailed Implementation

[0016] The technical solution of the present invention will be further described below with reference to the accompanying drawings and embodiments.

[0017] Unless otherwise defined, the technical or scientific terms used in this invention shall have the ordinary meaning understood by one of ordinary skill in the art to which this invention pertains. The terms "first," "second," and similar terms used in this invention do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Terms such as "comprising" or "including" mean that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, without excluding other elements or objects. Terms such as "connected" or "linked" are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. Terms such as "upper," "lower," "left," and "right" are used only to indicate relative positional relationships; when the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0018] Example 1 like Figures 1-4 As shown, a measuring device for tire compression under static load on an aircraft includes a main scale 1, a secondary scale 2, a front wheel measuring mechanism, and a main wheel measuring mechanism.

[0019] A graduated universal level 15 with an accuracy of 0.5 degrees is fixedly mounted at the top of the main scale 1. This level is used to adjust the main scale 1 to a vertical position in real time during measurement, ensuring that the measurement reference is consistent with the radial direction of the tire. The interior of the main scale 1 has a dovetail groove and two parallel sliding grooves machined along its length. The dovetail groove is located in the middle of the main scale 1, and the sliding grooves are located on the left and right sides of the main scale 1. Two square holes are formed at the front end of the main scale 1. Brake blocks 16 are installed through these square holes via interference fit, limiting the sliding stroke of the auxiliary scale 2, the front wheel measuring scale 5, and the main wheel measuring scale 8, preventing them from slipping out of the main scale 1. A threaded hole is formed at the rear end of the main scale 1, into which a first fastening screw 17 is screwed. The end of the first fastening screw 17 abuts against the surface of the auxiliary scale 2, locking the sliding position of the auxiliary scale 2. Graduation lines with an accuracy of 1 mm are printed on both the left and right side walls of the main scale 1, used to record the calibration reference values ​​of the measuring scales.

[0020] The auxiliary ruler 2 slides into the dovetail groove of the main ruler 1. A red pointer 3 is provided at the upper end of the auxiliary ruler 2 for precise scale indication. A rectangular insert 18 is integrally formed at the end of the auxiliary ruler 2 for connection with the horizontal ruler 4. One end of the horizontal ruler 4 has a slot that mates with the insert 18. A threaded hole is provided on the side wall of the horizontal ruler 4, which is connected to the inside of the slot. A second fastening screw 19 is screwed into the threaded hole. After the insert 18 is inserted into the slot, the end of the second fastening screw 19 abuts against the side wall of the insert 18 to achieve a rigid connection. After connection, the bottom surface of the horizontal ruler 4 is flush with the bottom surface of the auxiliary ruler 2 and forms a 90-degree angle with the auxiliary ruler 2.

[0021] The front wheel measuring mechanism includes a front wheel gauge 5 and a front wheel docking assembly. Two front wheel gauges 5 are respectively fitted onto the front ends of the slide grooves on both sides of the main scale 1 and slide along the slide grooves. The front wheel gauge 5 inside the left slide groove is used to measure the tire compression of the left front wheel, and the front wheel gauge 5 inside the right slide groove is used to measure the tire compression of the right front wheel. The surface of the front wheel gauge 5 is printed with scale lines with an accuracy of 1 mm. The scale lines that exceed the allowable range in the tire technical manual are red. A threaded hole is opened on the lower part of the side wall of the front wheel gauge 5. A first limiting screw 6 is screwed into the threaded hole. The end of the first limiting screw 6 can abut against the side wall of the main scale 1 to lock the position of the front wheel gauge 5.

[0022] A docking shaft 7 is integrally formed on the front end of the left side wall of the main scale 1, and the front wheel docking assembly is fitted onto the docking shaft 7. The front wheel docking assembly includes a right front wheel alignment jaw 10 and a left front wheel alignment jaw 11. The front ends of both the right front wheel alignment jaw 10 and the left front wheel alignment jaw 11 are machined with jaw portions that match the front wheel fixing bolts, for precise docking with the front wheel axle. The side wall of the right front wheel alignment jaw 10 is integrally formed with a sleeve 12, which is fitted onto the docking shaft 7. The rear end of the left front wheel alignment jaw 11 has a mounting hole that matches the outer diameter of the sleeve 12. The left front wheel alignment jaw 11 is fitted onto the sleeve 12 through the mounting hole, and the front jaw portion of the left front wheel alignment jaw 11 penetrates the side wall of the right front wheel alignment jaw 10. The right front wheel alignment claw 10 has a groove on its side wall. The end of the docking shaft 7 away from the main scale 1 passes through the sleeve 12 and enters the groove. The front end of the docking shaft 7 has an annular groove. A retaining ring 13 is engaged in the groove. The end face of the retaining ring 13 contacts the inner wall of the groove of the right front wheel alignment claw 10 to prevent the front wheel docking assembly from coming off the docking shaft 7.

[0023] The main wheel measuring mechanism includes a main wheel measuring scale 8 and a main wheel docking assembly. The two main wheel measuring scales 8 are respectively fitted onto the rear end of the slide grooves on both sides of the main scale 1 and slide along the slide grooves. The main wheel measuring scale 8 inside the left slide groove is used to measure the tire compression of the left main wheel, and the main wheel measuring scale 8 inside the right slide groove is used to measure the tire compression of the right main wheel. The surface of the main wheel measuring scale 8 is printed with scale lines with an accuracy of 1 mm. The scale lines that exceed the allowable range in the tire technical manual are red. A threaded hole is opened in the middle of the side wall of the main wheel measuring scale 8. A second limit screw 9 is screwed into the threaded hole. The end of the second limit screw 9 can abut against the side wall of the main scale 1 to lock the position of the main wheel measuring scale 8.

[0024] The main wheel docking assembly is a main wheel mandrel 14, which is integrally formed with the main scale 1. The other end of the main wheel mandrel 14 is used to dock with the center hole of the main wheel axle to achieve precise docking with the main wheel axle.

[0025] Based on the aforementioned measuring device, taking the left main wheel of an aircraft as an example, this invention provides a method for measuring tire compression under static load on an aircraft, comprising the following steps: S1: Take out the measuring device, insert the insert block 18 at the end of the auxiliary ruler 2 into the slot of the horizontal ruler 4, and tighten the second fastening screw 19 to make the horizontal ruler 4 and the auxiliary ruler 2 rigidly connected and at a 90-degree angle. Loosen the first fastening screw 17 and the second limit screw 9 to make the auxiliary ruler 2 and the main wheel measuring scale 8 in a freely sliding state.

[0026] S2: Use a jack to lift the left main wheel of the aircraft, so that the replaced test tire is in a stress-free state, and perform the first calibration.

[0027] S3: Insert the main wheel axle 14 into the center hole of the left main wheel axle, ensuring that the main wheel axle 14 coincides with the center line of the left main wheel. Pull the auxiliary ruler 2 so that the bottom surface of the horizontal ruler 4 is in close contact with the top outer edge of the left main wheel tire. Adjust the main ruler 1 to a vertical position by observing the universal level 15, and tighten the first fastening screw 17 to lock the auxiliary ruler 2.

[0028] S4: Slide the main wheel measuring scale 8 upward along the left slide groove of the main scale 1 until its zero mark is aligned with the red pointer 3. Tighten the corresponding second limit screw 9 and record the scale value of the main wheel measuring scale 8 on the main scale 1 as the calibration reference value of the left main wheel tire.

[0029] S5: Loosen the second fastening screw 19 to remove the cross ruler 4, loosen the first fastening screw 17 to retract the auxiliary ruler 2, use a jack to lower the left main wheel of the aircraft until the tire under test is fully subjected to static load, and measure the compression of the left main wheel tire.

[0030] S6: Insert the main wheel mandrel 14 into the center hole of the left main wheel axle, ensuring that the main wheel mandrel 14 coincides with the center line of the left main wheel. Adjust the main scale 1 to a vertical position by observing the universal level 15. Pull the auxiliary scale 2 so that the bottom surface of its insert 18 contacts the ground. Tighten the first fastening screw 17. Read the scale value indicated by the pointer 3 on the main wheel measuring scale 8, which is the compression of the left main wheel tire. If the compression value enters the red scale area, it indicates that the compression exceeds the standard. The maintenance measures specified in the technical manual should be taken until the measured compression meets the standard.

[0031] S7: In subsequent pre- and post-flight routine measurements, directly adjust the position of the left main wheel measuring tape 8 on the main scale 1 based on the reference value of the left main wheel, and then follow the measurement steps in S6 to measure the tire compression of the left main wheel at that time.

[0032] Example 2 Based on the measurement method in Embodiment 1, taking the right main wheel of an aircraft as an example, this invention provides a method for measuring tire compression under static load on an aircraft, comprising the following steps: S1: Take out the measuring device, insert the insert block 18 at the end of the auxiliary ruler 2 into the slot of the horizontal ruler 4, and tighten the second fastening screw 19 to make the horizontal ruler 4 and the auxiliary ruler 2 rigidly connected and at a 90-degree angle. Loosen the first fastening screw 17 and the second limit screw 9 to make the auxiliary ruler 2 and the main wheel measuring scale 8 in a freely sliding state.

[0033] S2: Use a jack to lift the right main wheel of the aircraft, so that the replaced test tire is in a stress-free state, and perform the first calibration.

[0034] S3: Insert the main wheel axle 14 into the center hole of the right main wheel axle, ensuring that the main wheel axle 14 coincides with the center line of the right main wheel. Pull the auxiliary ruler 2 so that the bottom surface of the horizontal ruler 4 is in close contact with the top outer edge of the right main wheel tire. Adjust the main ruler 1 to a vertical position by observing the universal level 15, and tighten the first fastening screw 17 to lock the auxiliary ruler 2.

[0035] S4: Slide the main wheel measuring scale 8 upward along the right slide groove of the main scale 1 until its zero mark is aligned with the red pointer 3. Tighten the corresponding second limit screw 9 and record the scale value of the main wheel measuring scale 8 on the main scale 1 as the calibration reference value of the right main wheel tire.

[0036] S5: Loosen the second fastening screw 19 to remove the cross ruler 4, loosen the first fastening screw 17 to retract the auxiliary ruler 2, use a jack to lower the right main wheel of the aircraft until the tire under test is fully subjected to static load, and measure the compression of the right main wheel tire.

[0037] S6: Insert the main wheel mandrel 14 into the center hole of the right main wheel axle, ensuring that the main wheel mandrel 14 coincides with the center line of the right main wheel. Adjust the main scale 1 to a vertical position by observing the universal level 15. Pull the auxiliary scale 2 so that the bottom surface of its insert 18 contacts the ground. Tighten the first fastening screw 17. Read the scale value indicated by the pointer 3 on the main wheel measuring scale 8, which is the compression of the right main wheel tire. If the compression value enters the red scale area, it indicates that the compression exceeds the standard. The maintenance measures specified in the technical manual should be taken until the measured compression meets the standard.

[0038] S7: In subsequent pre- and post-flight routine measurements, directly adjust the position of the right main wheel measuring scale 8 on the main scale 1 based on the reference value of the right main wheel, and then follow the measurement steps in S6 to measure the tire compression of the right main wheel at that time.

[0039] Example 3 Based on the measuring device of Embodiment 1, taking the left front wheel of an aircraft as an example, this invention provides a method for measuring tire compression under static load on an aircraft, comprising the following steps: S1: Take out the measuring device, insert the insert block 18 at the end of the auxiliary ruler 2 into the slot of the horizontal ruler 4, and tighten the second fastening screw 19 to make the horizontal ruler 4 and the auxiliary ruler 2 rigidly connected and at a 90-degree angle. Loosen the first fastening screw 17 and the first limit screw 6 to make the auxiliary ruler 2 and the front wheel measuring scale 5 in a free sliding state.

[0040] S2: Use a jack to lift the left front wheel of the aircraft, so that the replaced test tire is in a stress-free state, and perform the first calibration.

[0041] S3: Switch the left front wheel docking mode: Push the left front wheel alignment claw 11 so that its front end protrudes from the side wall of the right front wheel alignment claw 10, exposing the protruding part of the left front wheel alignment claw 11. Engage the protruding part of the left front wheel alignment claw 11 onto the fixing bolt of the left front wheel, ensuring that the docking shaft 7 coincides with the center line of the left front wheel axle. Pull the auxiliary ruler 2 so that the bottom surface of the horizontal ruler 4 is in close contact with the top outer edge of the left front tire. Adjust the main ruler 1 to a vertical position by observing the universal level 15, and tighten the first fastening screw 17 to lock the auxiliary ruler 2.

[0042] S4: Slide the front wheel gauge 5 upward along the left slide groove of the main scale 1 until its zero mark is aligned with the red pointer 3. Tighten the corresponding first limit screw 6 and record the scale value of the front wheel gauge 5 on the main scale 1 as the calibration reference value of the left front tire.

[0043] S5: Loosen the second fastening screw 19 to remove the cross ruler 4, loosen the first fastening screw 17 to retract the auxiliary ruler 2, use the jack to lower the left front wheel of the aircraft until the tire under test is fully subjected to static load, and measure the compression of the left front wheel tire.

[0044] S6: Engage the pawl of the left front wheel alignment pawl 11 onto the fixing bolt of the left front wheel, ensuring that the center line of the mating shaft 7 coincides with the center line of the left front wheel axle. Adjust the main scale 1 to a vertical position by observing the universal level 15, pull the auxiliary scale 2 so that the bottom surface of its insert 18 contacts the ground, tighten the first fastening screw 17, and read the scale value indicated by the pointer 3 on the front wheel measuring scale 5, which is the compression of the left front tire. If the compression value enters the red scale area, it indicates that the compression exceeds the standard, and maintenance measures specified in the technical manual should be taken until the measured compression meets the standard.

[0045] S7: In subsequent pre- and post-flight routine measurements, directly adjust the position of the left front wheel measuring tape 5 on the main scale 1 based on the reference value of the left front wheel, and then follow the measurement steps in S6 to measure the tire compression of the left front wheel at that time.

[0046] Example 4 Based on the measurement method in Embodiment 3, taking the right front wheel of an aircraft as an example, this invention provides a method for measuring tire compression under static load on an aircraft, comprising the following steps: S1: Take out the measuring device, insert the insert block 18 at the end of the auxiliary ruler 2 into the slot of the horizontal ruler 4, and tighten the second fastening screw 19 to make the horizontal ruler 4 and the auxiliary ruler 2 rigidly connected and at a 90-degree angle. Loosen the first fastening screw 17 and the first limit screw 6 to make the auxiliary ruler 2 and the front wheel measuring scale 5 in a free sliding state.

[0047] S2: Use a jack to lift the right front wheel of the aircraft, so that the replaced test tire is in a stress-free state, and perform the first calibration.

[0048] S3: Engage the pawl of the right front wheel alignment pawl 10 onto the fixing bolt of the right front wheel, ensuring that the center line of the alignment shaft 7 coincides with the center line of the right front wheel axle. Pull the auxiliary ruler 2 to make the bottom surface of the horizontal ruler 4 in close contact with the top outer edge of the right front tire. Adjust the main ruler 1 to a vertical position by observing the universal level 15, and tighten the first fastening screw 17 to lock the auxiliary ruler 2.

[0049] S4: Slide the front wheel gauge 5 upward along the right slide groove of the main scale 1 until its zero mark is aligned with the red pointer 3. Tighten the corresponding first limit screw 6 and record the scale value of the front wheel gauge 5 on the main scale 1 as the calibration reference value of the right front tire.

[0050] S5: Loosen the second fastening screw 19 to remove the cross ruler 4, loosen the first fastening screw 17 to retract the auxiliary ruler 2, use a jack to lower the right front wheel of the aircraft until the tire under test is fully subjected to static load, and measure the compression of the right front wheel tire.

[0051] S6: Engage the pawl of the right front wheel alignment pawl 10 onto the fixing bolt of the right front wheel, ensuring that the center line of the mating shaft 7 coincides with the center line of the right front wheel axle. Adjust the main scale 1 to a vertical position by observing the universal level 15, pull the auxiliary scale 2 so that the bottom surface of its insert 18 contacts the ground, tighten the first fastening screw 17, and read the scale value indicated by the pointer 3 on the front wheel measuring scale 5, which is the compression of the right front tire. If the compression value enters the red scale area, it indicates that the compression exceeds the standard, and maintenance measures specified in the technical manual should be taken until the measured compression meets the standard.

[0052] S7: In subsequent pre- and post-flight routine measurements, directly adjust the position of the right front wheel measuring tape 5 on the main scale 1 based on the reference value of the right front wheel, and then follow the measurement steps in S6 to measure the tire compression of the right front wheel at that time.

[0053] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the technical solutions of the present invention, and these modifications or equivalent substitutions cannot cause the modified technical solutions to deviate from the spirit and scope of the technical solutions of the present invention.

Claims

1. A device for measuring tire compression under static load on an aircraft, characterized in that: It includes a main scale and a secondary scale. The main scale is equipped with a front wheel measuring mechanism and a main wheel measuring mechanism. The secondary scale is inserted into the main scale and slides along the main scale. One end of the secondary scale is equipped with a pointer for indicating the scale. The other end of the secondary scale is connected to a horizontal ruler. The horizontal ruler and the secondary scale form a 90-degree angle. The front wheel measuring mechanism includes a front wheel gauge and a front wheel docking assembly. The two front wheel gauges are respectively sleeved on both sides of the front end of the main gauge and slide along the main gauge. The left front wheel gauge is used to measure the tire compression of the left front wheel, and the right front wheel gauge is used to measure the tire compression of the right front wheel. The front wheel gauge is provided with scale lines, and the scale lines are provided with red areas for displaying compression thresholds. The side wall of the front wheel gauge is provided with a first limiting screw, which passes through the side wall of the front wheel gauge and contacts the side wall of the main gauge. The left side wall of the front end of the main gauge is provided with a docking shaft, and the front wheel docking assembly is disposed on the docking shaft. The main wheel measuring mechanism includes a main wheel measuring scale and a main wheel docking assembly. The two main wheel measuring scales are respectively sleeved on both sides of the rear end of the main scale and slide along the main scale. The main wheel measuring scale on the left is used to measure the tire compression of the left main wheel, and the main wheel measuring scale on the right is used to measure the tire compression of the right main wheel. The main wheel measuring scale is provided with scale lines, and the scale lines are provided with red areas for displaying the compression threshold. The side wall of the main wheel measuring scale is provided with a second limiting screw. The main wheel docking assembly is located on the right side wall of the front end of the main scale.

2. The device for measuring tire compression under static load on an aircraft according to claim 1, characterized in that: The front wheel docking assembly includes a right front wheel aligning claw and a left front wheel aligning claw. A sleeve is provided on the side wall of the right front wheel aligning claw. The left front wheel aligning claw is sleeved on the sleeve, and the front end of the left front wheel aligning claw penetrates the side wall of the right front wheel aligning claw. The sleeve is sleeved on the docking shaft, and the front end of the docking shaft penetrates the side wall of the right front wheel aligning claw. A retaining ring is engaged at the front end of the docking shaft, and the retaining ring contacts the side wall of the right front wheel aligning claw.

3. The device for measuring tire compression under static load on an aircraft according to claim 2, characterized in that: The main wheel docking assembly is a main wheel mandrel for docking with the main wheel shaft, and one end of the main wheel mandrel is connected to the right side wall of the front end of the main scale.

4. The device for measuring tire compression under static load on an aircraft according to claim 3, characterized in that: The top of the main scale is equipped with a universal level for adjusting the level of the device. A brake block is inserted at the front end of the main scale to prevent the auxiliary scale, the front wheel measuring scale and the main wheel measuring scale from slipping off the main scale. A first fastening screw is inserted at the rear end of the main scale, and the first fastening screw passes through the main scale and contacts the auxiliary scale.

5. The device for measuring tire compression under static load on an aircraft according to claim 4, characterized in that: The end of the auxiliary ruler is provided with an insert block, which is inserted into the inside of the horizontal ruler. A second fastening screw is inserted into the side wall of the horizontal ruler, and the second fastening screw passes through the horizontal ruler and contacts the insert block.

6. A method for measuring tire compression under static load on an aircraft, based on the measuring device according to any one of claims 1-5, characterized in that, Includes the following steps: S1: Secure the horizontal ruler to the end of the auxiliary ruler through the insert block and the second fastening screw, and tighten the first fastening screw, the first limit screw and the second limit screw to the movable state. S2: Use a jack to lift the aircraft so that the replaced test tire is in a stress-free state for the first calibration; S3: Use the front wheel docking assembly to dock the main ruler with the axle of the front wheel to be tested, pull the auxiliary ruler to make the cross ruler contact the outer edge of the top of the tire to be tested, adjust the main ruler to a vertical state by observing the universal level, and tighten the first fastening screw. S4: Slide the front wheel gauge to align its zero mark with the pointer, tighten the first limit screw, and record the scale of the front wheel gauge on the main scale as the calibration reference value of the front wheel tire to be tested. S5: Loosen the second fastening screw to remove the cross ruler, loosen the first fastening screw to retract the auxiliary ruler, use a jack to lower the aircraft wheel to be tested until the tire under test fully bears the static load, and measure the compression of the front tire under test. S6: Use the front wheel docking assembly to dock the main scale with the axle of the front wheel to be tested. Adjust the main scale to a vertical position by observing the universal level. Pull the auxiliary scale so that the bottom surface of its insert contacts the ground. Tighten the first fastening screw and read the scale value indicated by the pointer on the front wheel gauge. This is the compression of the front tire to be tested. If the compression value enters the red scale area, it indicates that the compression exceeds the standard. The maintenance measures specified in the technical manual should be taken until the measured compression meets the standard. S7: Use the main wheel docking assembly to dock the main ruler with the axle of the main wheel to be tested, pull the auxiliary ruler to make the cross ruler contact the outer edge of the top of the tire to be tested, adjust the main ruler to a vertical state by observing the universal level, and tighten the first fastening screw. S8: Slide the main wheel measuring scale to align its zero mark with the pointer, tighten the second limit screw, and record the scale reading on the main wheel measuring scale as the calibration reference value of the tire to be tested on the main wheel. S9: Loosen the second fastening screw to remove the cross ruler, loosen the first fastening screw to retract the auxiliary ruler, use a jack to lower the aircraft wheel to be tested until the tire under test fully bears the static load, and measure the compression of the main wheel of the tire under test. S10: Use the main wheel docking assembly to dock the main scale with the axle of the main wheel to be tested. Adjust the main scale to a vertical position by observing the universal level. Pull the auxiliary scale so that the bottom surface of its insert contacts the ground. Tighten the first fastening screw and read the scale value indicated by the pointer on the main wheel scale. This is the compression of the tire to be tested on the main wheel. If the compression value enters the red scale area, it indicates that the compression exceeds the standard. The maintenance measures specified in the technical manual should be taken until the measured compression meets the standard. S11: The measuring personnel can choose to perform S3-S6 or S7-S10 depending on the type of tire to be tested; S12: For multiple tires of the same aircraft, complete the initial calibration and record their respective reference values. In subsequent pre-flight and post-flight routine measurements, directly adjust the position of the front wheel gauge or main wheel gauge according to the corresponding reference values, and then measure the tire compression under the current condition according to S6 or S10.

7. The method for measuring tire compression under static load on an aircraft according to claim 6, characterized in that: In step S3, the left front wheel alignment claw is pushed to extend out of the side wall of the right front wheel alignment claw or retract, thereby switching between the right front wheel docking mode and the left front wheel docking mode.

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