Auxiliary measuring equipment for aircraft maintenance and detection

Abstract

The invention relates to the technical field of component measurement, in particular to auxiliary measurement equipment for aircraft maintenance and detection, which comprises a measurement table, a measurement positioning part, a detection part and a marking part, and is characterized in that the measurement positioning part is fixedly arranged at the top of the measurement table, the detection part is fixedly arranged at the top of the measurement table, and the marking part is fixedly arranged in the detection part; a PC control electric box is fixedly arranged at the bottom of the measuring table, and supporting legs are fixedly installed at the circle center of the bottom of the measuring table and used for supporting and fixing the auxiliary measuring equipment for aircraft maintenance and detection. The aircraft hub is positioned through the measurement positioning part, the measurement stability is guaranteed, the deformation position of the aircraft hub is accurately measured through the arranged detection part, meanwhile, the deformation of the aircraft hub can be measured through the detection part, and therefore a maintainer can know the deformation of the hub, and the maintenance efficiency of the maintainer is improved. And judging whether the hub meets the standard of maintenance and reuse or not.

Description

Technical Field

[0001] The invention relates to the technical field of component measurement, in particular to auxiliary measurement equipment for aircraft maintenance and detection. Background Art

[0002] The aircraft wheel hub is the part of the wheel center where the axle is installed, which is also commonly known as the wheel rim or steel rim. When the aircraft lands, the wheel hub bears a large weight, and the wheel hub is more likely to deform, resulting in reduced force-bearing effect of the wheel hub. If it is not inspected and repaired for a long time, it may cause damage to the wheel hub when the aircraft lands, resulting in safety hazards;

[0003] According to a Chinese patent with application publication number CN116358382B, an auxiliary measuring device for aircraft maintenance and inspection is disclosed. By setting a contact component, it can be ensured that the auxiliary measuring device can maintain a concentric circle with the aircraft wheel hub when in use, thereby ensuring that the wheel hub can be accurately detected when it is deformed. However, it is still difficult for the auxiliary measuring device for aircraft maintenance and inspection to measure the deformation position and deformation amount of the aircraft wheel hub. In fact, some wheels with large deformation do not meet the standards for repair and reuse. When using the measuring equipment, it is difficult for maintenance personnel to grasp the deformation position and deformation amount of the wheel hub, and it is difficult to remove the wheel hub with large deformation. For this reason, we propose an auxiliary measuring device for aircraft maintenance and inspection to solve the above technical problems. Summary of the invention

[0004] The present invention provides the following technical solution: an auxiliary measurement device for aircraft maintenance and inspection, comprising:

[0005] Measuring table;

[0006] The measuring and positioning part is fixedly arranged on the top of the measuring platform and is used for positioning the aircraft wheel hub;

[0007] The detection part is fixed on the top of the measuring table and is used for measuring the aircraft wheel hub;

[0008] The marking part is fixedly arranged inside the detection part and is used for marking the deformation position of the aircraft wheel hub.

[0009] As a preferred solution of the present invention, the measuring and positioning unit includes:

[0010] Support columns are fixedly mounted on the top of the measuring platform in a circular array;

[0011] A positioning plate, fixedly mounted on the top of the plurality of pillars;

[0012] The positioning rods are fixedly mounted on the top of the positioning plate in a circular array, and the layout and specifications are compatible with the mounting holes of the aircraft wheel hub;

[0013] The rubber gasket is fixedly mounted on the outer wall of the positioning rod.

[0014] As a preferred solution of the present invention, the detection unit includes:

[0015] The translation seat is slidably mounted on the top of the measuring table in the form of a circular array and is located at the periphery of the measuring positioning part;

[0016] The U-shaped bearing seat is fixedly mounted on the top of the translation seat;

[0017] The connecting shaft is rotatably mounted inside the U-shaped bearing seat through the bearing;

[0018] The measuring swing arm is fixedly mounted on the outer wall of the connecting shaft;

[0019] A coupling groove is provided on the top of the measuring swing arm and close to one end of the measuring positioning part;

[0020] Rope rod, fixedly installed at the bottom of the measuring swing arm;

[0021] The elastic rope is fixedly installed at the bottom of the rope rod;

[0022] A pillow platform, which is fixedly mounted on the top of the measuring platform and is located between the plurality of pillars;

[0023] The grating sensor body is movably arranged on the top of the pillow platform, and the outer wall of the grating sensor body is fixedly connected to one end of the elastic rope, and the elastic rope is arranged in a stretched and force-storing state.

[0024] As a preferred solution of the present invention, the detection unit also includes:

[0025] A lifting lug is fixedly mounted on the middle of a side surface of the measuring swing arm close to the measuring positioning portion;

[0026] A cross bar is fixedly installed inside the U-shaped bearing seat and close to a side of the measuring and positioning part;

[0027] The tension spring is fixedly installed between the lifting lug and the cross bar.

[0028] As a preferred solution of the present invention, the detection unit also includes:

[0029] The pneumatic guide rails are fixedly mounted on the top of the measuring table in the form of a circular array and correspond one-to-one to the positions of the translation seats;

[0030] The pneumatic slide is slidably mounted on the periphery of the pneumatic guide rail, and the top of the pneumatic slide is fixedly connected to the bottom of the translation seat at the corresponding position by bolts.

[0031] As a preferred solution of the present invention, the detection unit also includes:

[0032] The signal light is fixedly mounted on the top of the translation seat and is away from one end of the measurement and positioning part. The signal light is electrically connected to the grating sensor body.

[0033] As a preferred solution of the present invention, the marking portion includes:

[0034] A No. 1 sliding hole is provided on the side wall of the coupling groove and passes through the interior of the measuring swing arm;

[0035] A marking rod is slidably mounted inside the No. 1 sliding hole;

[0036] The marking pen tip is fixedly mounted on one end of the marking rod close to the coupling groove, and the marking pen tip is used for marking the deformation position of the wheel hub.

[0037] As a preferred solution of the present invention, the marking portion further includes:

[0038] The second sliding hole is provided at an end of the first sliding hole away from the coupling groove and has a diameter greater than that of the first sliding hole;

[0039] The limiting ring is slidably mounted inside the second sliding hole and is fixedly connected to the end of the marking rod away from the marking pen head;

[0040] The spring is located at the periphery of the marking rod and is fixedly installed between the inner wall of one side of the second sliding hole and the limiting ring;

[0041] The hand push rod is fixedly mounted on a side of the limiting ring away from the marking rod.

[0042] As a preferred solution of the present invention, a PC control electric box is fixedly provided at the bottom of the measuring platform, and the output end of the PC control electric box is electrically connected to the input end of the grating sensor body.

[0043] As a preferred solution of the present invention, a support leg is fixedly installed at the center of the bottom circle of the measuring platform, and the support leg is used to support and fix the auxiliary measuring equipment for aircraft maintenance and inspection.

[0044] Compared with the prior art, the present invention has the following beneficial effects:

[0045] 1. In the present invention, the aircraft wheel hub is positioned by the measuring and positioning part to ensure the stability of the measurement, and the deformation position of the aircraft wheel hub is accurately measured by the arranged detection part. At the same time, the detection part can also measure the deformation amount of the aircraft wheel hub, so that the maintenance personnel know the deformation amount of the wheel hub and judge whether the wheel hub meets the standard of maintenance and reuse.

[0046] 2. In the present invention, by pressing the push rod at the corresponding position, the limit ring, the marking rod and the marking pen tip are further pushed to slide along the inner walls of the No. 1 sliding hole and the No. 2 sliding hole in the direction close to the coupling groove, so that the end of the marking pen tip contacts the rim of the wheel hub, thereby marking the deformation position of the wheel hub, making it convenient for maintenance personnel to quickly find the deformation position of the wheel hub, so as to facilitate maintenance and improve the accuracy and convenience of aircraft wheel hub maintenance.

[0047] 3. In the present invention, the marking rod, the marking pen tip, the limiting ring and the hand push rod are reset by the rebound force of the spring, so that the marking pen tip is separated from the rim of the wheel hub, thereby avoiding repeated marking by the marking pen tip leading to confusion of marking points. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] Figure 1 It is a structural schematic diagram of the present invention;

[0049] Figure 2 is a schematic diagram of the cross-sectional structure of the positioning plate in the present invention;

[0050] Figure 3 For the present invention Figure 2 A schematic diagram of the enlarged structure of part A;

[0051] Figure 4 It is a structural schematic diagram of the measuring and positioning part in the present invention;

[0052] Figure 5 It is a schematic diagram of the structure of the translation seat and the measuring swing arm in the present invention;

[0053] Figure 6 It is a schematic diagram of the cross-sectional structure of the U-shaped bearing seat in the present invention;

[0054] Figure 7 It is a detailed structural diagram of the measuring swing arm in the present invention;

[0055] Figure 8 It is a schematic diagram of the detailed structure of the measuring swing arm and the rope rod in the present invention;

[0056] Fig. 9 It is a partial cross-sectional structural schematic diagram of the measuring swing arm in the present invention;

[0057] Fig.10 For the present invention Fig. 9 Schematic diagram of the enlarged structure of part B.

[0058] In the figure: 100, measuring platform; 200, measuring positioning part; 201, pillar; 202, positioning plate; 203, positioning rod; 204, rubber pad; 300, detection part; 301, translation seat; 302, U-shaped bearing seat; 303, connecting shaft; 304, measuring swing arm; 305, coupling groove; 306, rope rod; 307, elastic rope; 308, pillow platform; 309, grating sensor body; 3010, lifting ear; 3011, cross bar; 3012, tension spring; 3013, pneumatic guide rail; 3014, pneumatic slide; 3015, indicator light; 400, marking part; 401, No. 1 sliding hole; 402, marking rod; 403, marking pen tip; 404, No. 2 sliding hole; 405, limiting ring; 406, spring; 407, push rod; 500, PC control electric box; 600, supporting leg. DETAILED DESCRIPTION

[0059] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0060] See also Figures 1 to 10 The technical solution provided by the present invention specifically includes the following embodiments:

[0061] An auxiliary measuring device for aircraft maintenance and inspection comprises a measuring platform 100, a measuring and positioning part 200, a detecting part 300 and a marking part 400. The measuring and positioning part 200 is fixedly arranged on the top of the measuring platform 100 and is used for positioning the aircraft wheel hub. The detecting part 300 is fixedly arranged on the top of the measuring platform 100 and is used for measuring the aircraft wheel hub. The marking part 400 is fixedly arranged inside the detecting part 300 and is used for marking the deformation position of the aircraft wheel hub. A PC control electric box 500 is fixedly arranged on the bottom of the measuring platform 100. A supporting leg 600 is fixedly installed at the center of the bottom circle of the measuring platform 100. The supporting leg 600 is used for supporting and fixing the auxiliary measuring device for aircraft maintenance and inspection.

[0062] For further details, please refer to Figure 2 , Figure 3 As shown:

[0063] The measuring and positioning part 200 includes pillars 201, positioning plates 202, positioning rods 203 and rubber pads 204. The pillars 201 are fixedly mounted on the top of the measuring platform 100 in a circular array. The positioning plates 202 are fixedly mounted on the tops of multiple pillars 201. The positioning rods 203 are fixedly mounted on the tops of the positioning plates 202 in a circular array, and the layout and specifications are compatible with the aircraft wheel hub mounting holes. The rubber pads 204 are fixedly mounted on the outer walls of the positioning rods 203.

[0064] Specifically, the bolt mounting holes of the aircraft wheel hub are matched to the positioning rods 203 of the device one by one, and the aircraft wheel hub is placed downward so that a plurality of positioning rods 203 are inserted into the bolt mounting holes of the aircraft wheel hub. Thus, the aircraft wheel hub is positioned by utilizing the insertion effect of the plurality of positioning rods 203 and the bolt mounting holes of the aircraft wheel hub, and the rubber pads 204 arranged on the outer walls of the positioning rods 203 can support the aircraft wheel hub to ensure the stability of the aircraft wheel hub.

[0065] For further details, please refer to Figures 4 to 8 As shown:

[0066] The detection unit 300 includes a translation seat 301, a U-shaped bearing seat 302, a connecting shaft 303, a measuring swing arm 304, a coupling slot 305, a rope rod 306, an elastic rope 307, a pillow 308, a grating sensor body 309, a lifting ear 3010, a cross bar 3011, a tension spring 3012, a pneumatic guide rail 3013, a pneumatic slide 3014 and a signal light 3015. The translation seat 301 is slidably mounted on the top of the measuring platform 100 in the form of a circular array and is located at the periphery of the measuring positioning unit 200. The U-shaped bearing seat 302 is fixedly mounted. At the top of the translation seat 301, the connecting shaft 303 is rotatably mounted inside the U-shaped bearing seat 302 through a bearing, the measuring swing arm 304 is fixedly mounted on the outer wall of the connecting shaft 303, the coupling groove 305 is opened at the top of the measuring swing arm 304 and close to one end of the measuring positioning part 200, the rope rod 306 is fixedly mounted at the bottom of the measuring swing arm 304, the elastic rope 307 is fixedly mounted at the bottom of the rope rod 306, the pillow platform 308 is fixedly mounted on the top of the measuring platform 100 and is located between the multiple pillars 201, and the grating sensor body 309 is movable. The grating sensor body 309 is electrically connected to the output end of the PC control box 500, and the outer wall of the grating sensor body 309 is fixedly connected to one end of the elastic rope 307, and the elastic rope 307 is set in a stretched state. The ear 3010 is fixedly installed on the middle of a side of the measuring swing arm 304 close to the measuring positioning part 200, the cross bar 3011 is fixedly installed inside the U-shaped bearing seat 302 and close to the side of the measuring positioning part 200, and the tension spring 3012 is fixedly installed on the ear 301 0 and the cross bar 3011, the pneumatic guide rail 3013 is fixedly installed on the top of the measuring platform 100 in the form of a circular array, and corresponds to the position of the translation seat 301 one by one, the pneumatic slide 3014 is slidably installed on the periphery of the pneumatic guide rail 3013, and the top of the pneumatic slide 3014 is fixedly connected to the bottom of the translation seat 301 at the corresponding position by bolts, the indicator light 3015 is fixedly installed on the top of the translation seat 301, and is away from one end of the measuring positioning part 200, and the indicator light 3015 is electrically connected to the grating sensor body 309.

[0067] Specifically, commands are inputted through the PC control electric box 500, so that the multiple pneumatic slides 3014 move linearly along the multiple pneumatic guide rails 3013 toward the direction close to the measuring and positioning part 200, and further drive the multiple translation seats 301, the U-shaped bearing seat 302, the measuring swing arm 304 and the marking part 400 to move together, until the side surfaces of the multiple translation seats 301 are all in contact with the side surfaces of the adjacent translation seats 301. During this period, the measuring swing arm 304 also drives the coupling groove 305 to move together, so that the surface of the coupling groove 305 abuts against the rim of the aircraft wheel hub. At the same time, the movement of the translation seat 301 causes the measuring swing arm 304 to rotate along the connection between the connecting shaft 303 and the U-shaped bearing seat 302 in the direction away from the measuring and positioning part 200, causing the tension spring 3012 to rotate. Stretching and storing force. At this time, if the aircraft wheel hub is not deformed, that is, the rim of the aircraft wheel hub is a regular circle, then the rotation angles of all translation seats 301 are equal, so that the angles of rotation of the measuring swing arm 304 driving the rope rod 306 during the rotation are also equal. The rotation of the rope rod 306 causes the elastic force of the elastic rope 307 to shrink to the same degree. Therefore, after all the rope rods 306 rotate, the tension applied to the grating sensor body 309 through the elastic rope 307 is equal. Therefore, the tension of multiple elastic ropes 307 on the surface of the grating sensor body 309 cancels each other. Therefore, the grating sensor body 309 is still in the center of the top of the pillow 308, so that the grating signal sensor at the bottom of the grating sensor body 309 will not generate a displacement pulse signal;

[0068] If the wheel hub of the aircraft is deformed, as the multiple measuring swing arms 304 move toward the measuring positioning portion 200, because the curvature of the deformed part of the wheel hub is inconsistent with that of the other undeformed parts, after the surface of the coupling groove 305 contacts the rim of the wheel hub, the rotation angle of the measuring swing arms 304 will also be different. In other words, the rotation angle of the measuring swing arms 304 in contact with the deformed part of the wheel hub is smaller than that of the other measuring swing arms 304. Therefore, the rotation angle of the rope rod 306 of this part is also smaller than that of the other rope rods 306, resulting in differences in the degree of contraction of the elastic force of the elastic rope 307, causing the multiple elastic ropes 307 to apply inconsistent tension to the surface of the grating sensor body 309. The resultant force of the pulling force generated on the surface of the body 309 will deviate from the center position of the pillow 308, that is, the grating sensor body 309 will move along the top of the pillow 308 in the direction of the offset force, that is, in the direction of the wheel hub deformation. At this time, the grating signal sensor at the bottom of the grating sensor body 309 generates a displacement pulse signal and transmits the signal to the PC control electrical box 500. The display of the PC control electrical box 500 displays the displacement distance, so as to know the deformation amount of the wheel hub and judge whether the wheel hub meets the standards for repair and reuse. At the same time, the grating sensor body 309 will also send a current signal to the indicator light 3015 in the direction of the offset, so that the indicator light 3015 at this position will light up, which is convenient for maintenance personnel to accurately know the deformation position of the wheel hub.

[0069] For further details, please refer to Fig. 9 , Fig.10 As shown:

[0070] The marking part 400 includes a first sliding hole 401, a marking rod 402, a marking pen head 403, a second sliding hole 404, a limiting ring 405, a spring 406 and a hand push rod 407. The first sliding hole 401 is opened on the side wall of the coupling groove 305 and passes through the interior of the measuring swing arm 304. The marking rod 402 is slidably installed in the first sliding hole 401. The marking pen head 403 is fixedly installed at one end of the marking rod 402 close to the coupling groove 305. The marking pen head 403 is used to mark the deformation position of the wheel hub. The No. 1 slide hole 404 is opened at the end of the No. 1 slide hole 401 away from the coupling groove 305, and its diameter is larger than the diameter of the No. 1 slide hole 401. The limiting ring 405 is slidably installed inside the No. 2 slide hole 404, and is fixedly connected to the end of the marking rod 402 away from the marking pen head 403. The spring 406 is located on the periphery of the marking rod 402, and is fixedly installed between the inner wall of one side of the No. 2 slide hole 404 and the limiting ring 405. The hand push rod 407 is fixedly installed on the side of the limiting ring 405 away from the marking rod 402.

[0071] Specifically, the maintenance personnel presses the push rod 407 at the corresponding position according to the lighting position of the indicator light 3015, and further pushes the limit ring 405, the marking rod 402 and the marking pen head 403 to slide along the inner wall of the No. 1 slide hole 401 and the No. 2 slide hole 404 in the direction close to the coupling groove 305, so that the end of the marking pen head 403 contacts the rim of the hub, thereby marking the deformation position of the hub. At the same time, the movement of the limit ring 405 causes the spring 406 to compress and accumulate force. Therefore, after the marking is completed After that, the maintenance personnel releases the push rod 407, and the resilience of the spring 406 is released, pushing the marking rod 402, the marking pen head 403, the limiting ring 405 and the push rod 407 to reset, so that the marking pen head 403 is separated from the rim of the hub, avoiding repeated marking by the marking pen head 403 and causing confusion of the marking points. Subsequently, the maintenance personnel can quickly find the deformed position of the hub by searching for the marking points on the hub, so as to facilitate maintenance and improve the accuracy and convenience of aircraft wheel hub maintenance.

[0072] When the auxiliary measuring device for aircraft maintenance and inspection of the present invention is working, the supporting legs 600 are fixedly mounted on the bottom of the measuring platform 100 to provide support for the entire measuring device, thereby ensuring the overall stability of the measuring device. The measuring device includes the following use process during use:

[0073] Fixing of aircraft wheel hub: Align the bolt mounting holes of the aircraft wheel hub with the positioning rods 203 of the device one by one, place the aircraft wheel hub downward, and make multiple positioning rods 203 inserted into the bolt mounting holes of the aircraft wheel hub, so as to position the aircraft wheel hub by using the insertion effect of multiple positioning rods 203 and the bolt mounting holes of the aircraft wheel hub, and the rubber pads 204 arranged on the outer walls of the positioning rods 203 can support the aircraft wheel hub to ensure the stability of the aircraft wheel hub;

[0074] Measurement of the aircraft wheel hub: commands are inputted through the PC control electric box 500, so that the multiple pneumatic slides 3014 move linearly along the multiple pneumatic guide rails 3013 toward the direction close to the measuring positioning part 200, and further drive the multiple translation seats 301, the U-shaped bearing seat 302, the measuring swing arm 304 and the marking part 400 to move together, until the side surfaces of the multiple translation seats 301 are all in contact with the side surfaces of the adjacent translation seats 301. During this period, the measuring swing arm 304 also drives the coupling groove 305 to move together, so that the surface of the coupling groove 305 abuts against the rim of the aircraft wheel hub. At the same time, the movement of the translation seat 301 causes the measuring swing arm 304 to rotate along the connection between the connecting shaft 303 and the U-shaped bearing seat 302 in the direction away from the measuring positioning part 200, causing the tension spring 30 12 stretching and storing force. At this time, if the aircraft wheel hub is not deformed, that is, the rim of the aircraft wheel hub is a regular circle, then the rotation angles of all translation seats 301 are equal, so that the angles of the rope rod 306 driven by the measuring swing arm 304 during the rotation are also equal. The rotation of the rope rod 306 causes the elastic force of the elastic rope 307 to shrink to the same degree. Therefore, after all the rope rods 306 rotate, the tension applied to the grating sensor body 309 through the elastic rope 307 is equal. Therefore, the tensions of multiple elastic ropes 307 on the surface of the grating sensor body 309 offset each other. Therefore, the grating sensor body 309 is still in the center of the top of the pillow 308, so that the grating signal sensor at the bottom of the grating sensor body 309 will not generate a displacement pulse signal;

[0075] If the wheel hub of the aircraft is deformed, as the multiple measuring swing arms 304 move toward the measuring positioning portion 200, because the curvature of the deformed part of the wheel hub is inconsistent with that of the other undeformed parts, after the surface of the coupling groove 305 contacts the rim of the wheel hub, the rotation angle of the measuring swing arms 304 will also be different. In other words, the rotation angle of the measuring swing arms 304 in contact with the deformed part of the wheel hub is smaller than that of the other measuring swing arms 304. Therefore, the rotation angle of the rope rod 306 of this part is also smaller than that of the other rope rods 306, resulting in differences in the degree of contraction of the elastic force of the elastic rope 307, causing the multiple elastic ropes 307 to apply inconsistent tension to the surface of the grating sensor body 309. The resultant force of the pulling force generated on the surface of the body 309 will deviate from the center position of the pillow 308, that is, the grating sensor body 309 will move along the top of the pillow 308 in the direction of the offset force, that is, in the direction of the wheel hub deformation. At this time, the grating signal sensor at the bottom of the grating sensor body 309 generates a displacement pulse signal and transmits the signal to the PC control electric box 500. The display of the PC control electric box 500 displays the displacement distance, so as to know the deformation amount of the wheel hub and judge whether the wheel hub meets the standard for repair and reuse. At the same time, the grating sensor body 309 will also send a current signal to the indicator light 3015 in the offset direction, so that the indicator light 3015 at this position lights up, which is convenient for maintenance personnel to accurately know the deformation position of the wheel hub;

[0076] Marking of the deformation position of the aircraft wheel hub: the maintenance personnel presses the push rod 407 at the corresponding position according to the lighting position of the indicator light 3015, and further pushes the limit ring 405, the marking rod 402 and the marking pen head 403 to slide along the inner wall of the No. 1 slide hole 401 and the No. 2 slide hole 404 in the direction close to the coupling groove 305, so that the end of the marking pen head 403 contacts the rim of the wheel hub, thereby marking the deformation position of the wheel hub. At the same time, the movement of the limit ring 405 causes the spring 406 to compress and accumulate force. Therefore, After the marking is completed, the maintenance personnel release the push rod 407, and the rebound force of the spring 406 is released, pushing the marking rod 402, the marking pen tip 403, the limit ring 405 and the push rod 407 to reset, so that the marking pen tip 403 is separated from the rim of the hub, avoiding repeated marking by the marking pen tip 403 and causing confusion of the marking points. Subsequently, the maintenance personnel can quickly find the deformation position of the hub by searching for the marking points on the hub, so as to facilitate maintenance and improve the accuracy and convenience of aircraft hub maintenance.

[0077] While the embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that many changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the invention.

Claims

1. An auxiliary measuring device for aircraft maintenance and inspection, characterized in that: include: Measuring table (100); A measuring and positioning part (200) is fixedly arranged on the top of the measuring platform (100) and is used for positioning the wheel hub of the aircraft; A detection unit (300) is fixedly arranged on the top of the measuring platform (100) and is used for measuring the aircraft wheel hub; The marking part (400) is fixedly arranged inside the detection part (300) and is used for marking the deformation position of the aircraft wheel hub.

2. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 1, characterized in that: The measuring and positioning unit (200) comprises: Support pillars (201) are fixedly mounted on the top of the measuring platform (100) in a circular array; A positioning plate (202) is fixedly mounted on the top of the plurality of pillars (201); Positioning rods (203) are fixedly mounted on the top of the positioning plate (202) in a circular array, and the layout and specifications are compatible with the aircraft wheel hub mounting holes; The rubber gasket (204) is fixedly mounted on the outer wall of the positioning rod (203).

3. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 2, characterized in that: The detection unit (300) comprises: The translation seat (301) is slidably mounted on the top of the measuring platform (100) in the form of a circular array and is located at the periphery of the measuring positioning portion (200); A U-shaped bearing seat (302) is fixedly mounted on the top of the translation seat (301); The connecting shaft (303) is rotatably mounted inside the U-shaped bearing seat (302) via a bearing; A measuring swing arm (304) is fixedly mounted on the outer wall of the connecting shaft (303); A coupling groove (305) is provided on the top of the measuring swing arm (304) and is close to one end of the measuring positioning portion (200); A rope rod (306) is fixedly mounted on the bottom of the measuring swing arm (304); An elastic rope (307) is fixedly mounted on the bottom of the rope rod (306); A pillow platform (308) is fixedly mounted on the top of the measuring platform (100) and is located between the plurality of pillars (201); The grating sensor body (309) is movably arranged on the top of the pillow platform (308), and the outer wall of the grating sensor body (309) is fixedly connected to one end of the elastic rope (307), and the elastic rope (307) is arranged in a stretched and force-storing state.

4. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 3, characterized in that: The detection unit (300) further includes: A lifting lug (3010) is fixedly mounted on a middle portion of a side surface of the measuring swing arm (304) close to the measuring positioning portion (200); A cross bar (3011) is fixedly mounted inside the U-shaped bearing seat (302) and close to one side of the measuring and positioning portion (200); The tension spring (3012) is fixedly installed between the lifting ear (3010) and the cross bar (3011).

5. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 4, characterized in that: The detection unit (300) further includes: The pneumatic guide rails (3013) are fixedly mounted on the top of the measuring platform (100) in the form of a circular array and correspond one-to-one to the positions of the translation seats (301); The pneumatic slide table (3014) is slidably mounted on the periphery of the pneumatic guide rail (3013), and the top of the pneumatic slide table (3014) is fixedly connected to the bottom of the translation seat (301) at a corresponding position by bolts.

6. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 5, characterized in that: The detection unit (300) further includes: The indicator light (3015) is fixedly mounted on the top of the translation seat (301) and at one end away from the measurement and positioning portion (200), and the indicator light (3015) is electrically connected to the grating sensor body (309).

7. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 6, characterized in that: The marking portion (400) comprises: A first sliding hole (401) is formed on the side wall of the coupling groove (305) and penetrates the interior of the measuring swing arm (304); A marking rod (402) is slidably mounted inside the first sliding hole (401); The marking pen tip (403) is fixedly mounted on one end of the marking rod (402) close to the coupling groove (305), and the marking pen tip (403) is used to mark the deformation position of the wheel hub.

8. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 7, characterized in that: The marking portion (400) further includes: The second sliding hole (404) is formed at an end of the first sliding hole (401) away from the coupling groove (305) and has a diameter greater than that of the first sliding hole (401); A limiting ring (405) is slidably mounted inside the second sliding hole (404) and is fixedly connected to an end of the marking rod (402) away from the marking pen head (403); A spring (406) is located at the periphery of the marking rod (402) and is fixedly mounted between an inner wall of one side of the second sliding hole (404) and the limiting ring (405); The push rod (407) is fixedly mounted on a side of the limiting ring (405) away from the marking rod (402).

9. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 8, characterized in that: A PC control electric box (500) is fixedly provided at the bottom of the measuring platform (100), and an output end of the PC control electric box (500) is electrically connected to an input end of the grating sensor body (309).

10. The auxiliary measurement equipment for aircraft maintenance and inspection according to claim 9, characterized in that: A support leg (600) is fixedly mounted at the center of the bottom circle of the measuring platform (100), and the support leg (600) is used to support and fix the auxiliary measuring equipment for aircraft maintenance and inspection.

Images