CN219115731U - Device for checking tightening moment of wing butt-joint bolt of airplane - Google Patents
Device for checking tightening moment of wing butt-joint bolt of airplane Download PDFInfo
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- CN219115731U CN219115731U CN202320084586.9U CN202320084586U CN219115731U CN 219115731 U CN219115731 U CN 219115731U CN 202320084586 U CN202320084586 U CN 202320084586U CN 219115731 U CN219115731 U CN 219115731U
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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- Y02T50/40—Weight reduction
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Abstract
The utility model provides an airplane wing butt-joint bolt tightening torque checking device, which comprises a base, wherein the top of the base is hinged with a lower screw rod through a ball head structure, an inner telescopic sleeve is arranged on the lower screw rod through screw rod transmission, and an outer telescopic sleeve is arranged outside the inner telescopic sleeve through telescopic fit; the top end of the outer extension sleeve is provided with an upper screw rod through screw rod transmission; a compaction adjusting mechanism is arranged in the upper screw rod; a tool releasing head matched with a wing bolt to be inspected is arranged at the top end of a mandrel of the compaction adjusting mechanism, and a supporting ring structure matched with the outer surface of the lower part of the wing is arranged at the top end of the tool releasing head; and an adapter spanner for connecting the fixed torque spanner is arranged on the mandrel in a matched manner. The whole operation process can be independently completed by one person, so that the labor is saved, the working efficiency is improved, and the device has the advantages of being stable in work, simple to operate, convenient to use, high in working efficiency, safe, reliable and the like.
Description
Technical Field
The utility model belongs to the field of aviation maintenance process equipment, and particularly relates to an airplane wing butt-joint bolt tightening torque checking device.
Background
When an aircraft is overhauled and regularly inspected, the tightening torque of the wing butt-joint bolt is required to be inspected, the tightening torque inspection of the butt-joint bolt of the lower wing surface is required to be completed by at least two persons in a matched mode, one person uses hands to hold the torque wrench and the butt-joint bolt to detach the tool bit, and the other person uses the hands to wrench the wrench rod of the torque wrench and observe the torque reading value on the dial of the torque wrench, but the tightening torque of the butt-joint bolt is larger, the force application is uneven, the process is unstable, the gesture of the detaching tool bit cannot be stably controlled only by hands, deflection is caused to the greatest extent, the detaching tool bit is separated from the groove of the head of the bolt, and even working surface breakage of the detaching tool bit part occurs due to uneven stress and overlarge local load, so that working interruption is caused, and working efficiency is reduced.
Disclosure of Invention
In order to solve the technical problems, the utility model provides an aircraft wing butt-joint bolt tightening torque checking device, which adopts an adjustable supporting device, and can be used for stably pressing a tool loosening head to the head of a butt-joint bolt by taking the table surface of an aircraft maintenance working platform as a supporting surface; the whole operation process can be independently completed by one person, so that the labor is saved, the working efficiency is improved, and the device has the advantages of being stable in work, simple to operate, convenient to use, high in working efficiency, safe, reliable and the like.
In order to achieve the technical characteristics, the aim of the utility model is realized in the following way: the tightening torque checking device for the wing butt bolts of the aircraft comprises a base, wherein the top of the base is hinged with a lower screw rod through a ball head structure, an inner telescopic sleeve is arranged on the lower screw rod through screw rod transmission, and an outer telescopic sleeve is arranged outside the inner telescopic sleeve through telescopic fit; the top end of the outer extension sleeve is provided with an upper screw rod through screw rod transmission; a compaction adjusting mechanism is arranged in the upper screw rod; a tool releasing head matched with a wing bolt to be inspected is arranged at the top end of a mandrel of the compaction adjusting mechanism, and a supporting ring structure matched with the outer surface of the lower part of the wing is arranged at the top end of the tool releasing head; and an adapter spanner for connecting the fixed torque spanner is arranged on the mandrel in a matched manner.
The lower screw rod and the lower nut sleeve form screw rod transmission, the lower nut sleeve is fixed at the bottom end of the inner telescopic sleeve, and the lower screw rod is sleeved with a lower locking nut;
the bottom ball head of the lower screw rod is tightly hinged on the base through a gland.
The upper screw rod and the upper nut sleeve form screw rod transmission, the upper nut sleeve is fixed at the top end of the outer telescopic sleeve, and the upper screw rod is sleeved with an upper locking nut.
Bolt holes are formed in the inner telescopic sleeve and the outer telescopic sleeve at equal intervals; after the relative length adjustment of the inner telescopic sleeve and the outer telescopic sleeve is completed, the inner telescopic sleeve and the outer telescopic sleeve are locked and fixed through a bolt handle inserted between bolt holes.
The compression adjusting mechanism comprises a mandrel which is slidably arranged in the upper screw rod, a spring is sleeved outside the mandrel, the bottom end of the spring is contacted with the top end of the upper screw rod, and the top end of the spring is in tight contact fit with the mandrel through a thrust ball bearing; the inner bottom end of the upper screw rod is matched with a long bolt structure for limiting the mandrel through threaded matching.
The mandrel comprises an optical axis section, the optical axis section and a central hole of an upper screw rod form sliding fit, an internal threaded hole is machined in the central part of the bottom end of the optical axis section, a hexagonal column matched with a transfer spanner is arranged at the top end of the optical axis section, a square column matched with a cutter head is arranged at the top end of the hexagonal column, and a spring positioning sleeve used for installing a thrust ball bearing and positioning a spring is arranged at the bottom end of the hexagonal column.
The long bolt structure comprises a push rod section, wherein a positioning column is arranged at the end part of the push rod section and is matched with an inner threaded hole of the mandrel; the bottom of ejector pin section is provided with the direction section, and the through-hole of direction section and upper portion lead screw bottom constitutes sliding fit, and the bottom of direction section is provided with the hexagon head.
The tool bit comprises a sleeve, a round hole is formed in the sleeve, and a square hole is formed in the bottom end of the round hole; the square hole is matched with a square column of the mandrel and transmits torque; the upper outer wall of the sleeve is provided with a collar, the top end of the sleeve is provided with a threaded ring section, and the center of the top end of the threaded ring section is provided with a knife edge matched with the notch of the wing bolt.
The supporting ring structure comprises a central ring sleeve, wherein a supporting ring is fixed on the outer wall of the top end of the central ring sleeve through a rib plate, and a central hole of the supporting ring is larger than the outer diameter of a nut of the wing bolt; the center ring sleeve and the threaded ring section of the tool bit are in threaded fit, and a gasket is arranged at the contact part of the supporting ring structure and the tool bit.
The utility model has the following beneficial effects:
1. the utility model provides an airplane wing butt-joint bolt tightening torque checking device, which adopts an adjustable supporting device, and can be used for stably pressing a tool loosening head to the head of a butt-joint wing bolt by taking a table top of an airplane maintenance working platform as a supporting surface.
2. The utility model can carry out large-size adjustment of the supporting height through the expansion and contraction of the inner telescopic sleeve and the outer telescopic sleeve, and carries out small-size fine adjustment of the supporting height through the positive and negative thread adjustment of the upper and lower screw rods.
3. The utility model can realize the screw tightening and the pressure maintenance in the moment checking process by the pre-pressure of the compression spring, and ensure that the pressing state of the checking device in the operation process is not loosened.
4. According to the utility model, the bit removing part is contacted with the wing surface area near the outer ring of the head part of the airplane wing butt-joint bolt through the support ring structure, so that the compression contact supporting surface is increased, and the overall stability of the device is improved.
5. The utility model reduces the friction force in the rotating process through the unidirectional thrust ball bearing, and the whole operation process can be independently completed by one person, thereby saving manpower and improving the working efficiency.
6. The utility model has the advantages of stable operation, simple operation, convenient use, high working efficiency, safety, reliability and the like.
Drawings
The utility model is further described below with reference to the drawings and examples.
Fig. 1 is a front view of the present utility model.
Fig. 2 is a right side view of the present utility model.
Fig. 3 is a view A-A of fig. 2 in accordance with the present utility model.
Fig. 4 is a first perspective three-dimensional view of the present utility model.
Fig. 5 is a second perspective three-dimensional view of the present utility model.
Fig. 6 is a three-dimensional view of a third perspective of the present utility model.
Fig. 7 is an enlarged view of part B of fig. 3 in accordance with the present utility model.
Fig. 8 is a partial enlarged view of C in fig. 3 according to the present utility model.
Fig. 9 is an exploded view of the present utility model.
Fig. 10 is a state diagram of the present utility model during a specific use.
Fig. 11 is a first perspective three-dimensional view of the mandrel of the present utility model.
Fig. 12 is a second perspective three-dimensional view of the mandrel of the present utility model.
Fig. 13 is a three-dimensional view of the construction of the long bolt of the present utility model.
Fig. 14 is a first perspective three-dimensional view of a tool tip according to the present utility model.
Fig. 15 is a second perspective three-dimensional view of the tool tip according to the present utility model.
Fig. 16 is a first perspective three-dimensional view of the support ring structure of the present utility model.
Fig. 17 is a second perspective three-dimensional view of the support ring structure of the present utility model.
Fig. 18 is a block diagram of a wing bolt of the present utility model.
In the figure: the device comprises a base 1, a gland 2, a lower screw rod 3, a lower lock nut 4, a lower nut sleeve 5, an inner telescopic sleeve 6, an outer telescopic sleeve 7, a bolt hole 8, a bolt handle 9, an upper nut sleeve 10, an upper lock nut 11, an upper screw rod 12, a spring 13, a mandrel 14, a set screw 15, a tool bit 16, a gasket 17, a support ring structure 18, an adapter wrench 19, a torsion meter 20, a fixed torque wrench 21, a long bolt structure 22, a thrust ball bearing 23 and a wing bolt 24;
an optical axis section 1401, a spring positioning sleeve 1402, a hexagonal column 1403, a square column 1404 and an internal threaded hole 1405;
a hex head 2201, a pilot segment 2202, a ram segment 2203, and a locating post 2204.
Detailed Description
Embodiments of the present utility model will be further described with reference to the accompanying drawings.
Example 1:
referring to fig. 1-18, an aircraft wing butt bolt tightening torque checking device comprises a base 1, wherein the top of the base 1 is hinged with a lower screw rod 3 through a ball head structure, an inner telescopic sleeve 6 is arranged on the lower screw rod 3 through screw rod transmission, and an outer telescopic sleeve 7 is arranged outside the inner telescopic sleeve 6 through telescopic fit; the top end of the outer extension sleeve 7 is provided with an upper screw rod 12 through screw rod transmission; a compaction adjusting mechanism is arranged in the upper screw rod 12; the top end of the mandrel 14 of the compression adjusting mechanism is provided with a cutter head 16 matched with a wing bolt 24 to be inspected, and the top end of the cutter head 16 is provided with a supporting ring structure 18 matched with the outer surface of the lower part of the wing; an adapter wrench 19 for connecting a fixed torque wrench 21 is mounted on the mandrel 14 in a matched manner. The tightening torque checking device can be used for torque detection of the wing bolt 24, the device takes the table surface of an aircraft maintenance working platform as a supporting surface, the tool bit is stably pressed to the head of the wing bolt, the large-size adjustment of the supporting height is carried out through the expansion and contraction of the inner telescopic sleeve 6 and the outer telescopic sleeve 7, the small-size fine adjustment of the supporting height is carried out through the positive and negative thread adjustment of the upper screw rod 12 and the lower screw rod 3, the pre-pressure of the pressing adjusting mechanism is used for realizing the tightening of the wing bolt and the pressure maintenance in the torque checking process, and the pressing state of the checking device in the operation process is ensured not to be released; the tool bit portion is separated through setting up the contact of the airfoil area near supporting ring structure 18 and aircraft wing bolt head outer lane, increases and compresses tightly the contact bearing surface, improves the overall stability of device, and whole operation process can be independently accomplished by a personnel, practices thrift the manpower, improves work efficiency, has job stabilization, easy operation, convenient to use, work efficiency is high, advantages such as safe and reliable.
Further, the lower screw rod 3 and the lower nut sleeve 5 form screw rod transmission, the lower nut sleeve 5 is fixed at the bottom end of the inner telescopic sleeve 6, and the lower locking nut 4 is sleeved on the lower screw rod 3. Through foretell lead screw transmission structure, guaranteed interior telescopic tube 6 rotation in-process, can drive nut cover 5 down in step, and then drive lower part lead screw 3 through nut cover 5 and carry out flexible regulation.
Further, the bottom ball head of the lower screw rod 3 is tightly hinged on the base 1 through the pressing cover 2. Through foretell bulb hinge structure, guaranteed that lower part lead screw 3 can be in the activity of certain within range, the automatic regulation of the device gesture of being convenient for.
Further, the upper screw rod 12 and the upper nut sleeve 10 form screw rod transmission, the upper nut sleeve 10 is fixed at the top end of the outer telescopic sleeve 7, and the upper locking nut 11 is sleeved on the upper screw rod 12. Through foretell lead screw transmission structure, guaranteed outer extension sleeve 7 rotation in-process, can drive nut cover 10 in step, and then drive upper portion lead screw 12 through last nut cover 10 and carry out flexible regulation.
Further, bolt holes 8 are formed in the inner telescopic sleeve 6 and the outer telescopic sleeve 7 at equal intervals; after the relative length adjustment of the inner telescopic sleeve 6 and the outer telescopic sleeve 7 is completed, the locking and fixing are performed by a bolt handle 9 inserted between bolt holes 8. Through foretell bolt hole, can realize supporting high a large scale preliminary adjustment.
Further, the compression adjusting mechanism comprises a mandrel 14 slidably arranged in the upper screw rod 12, a spring 13 is sleeved outside the mandrel 14, the bottom end of the spring 13 is contacted with the top end of the upper screw rod 12, and the top end of the spring 13 is in tight contact fit with the mandrel 14 through a thrust ball bearing 23; the inner bottom end of the upper screw rod 12 is fitted with a long bolt structure 22 for limiting the spindle 14 by screw fitting. The compression force can be adjusted through the compression adjusting mechanism, so that the lower outer wall of the aircraft wing can be stably supported in the detection process. The mandrel 14 inside the spring 13 can move telescopically within the bore of the upper screw 12 to a certain extent to accommodate compression and extension of the spring. The mandrel at the inner side of the spring is provided with a long bolt structure 22 at the lower end of the mandrel after being arranged in the inner hole of the upper screw rod to prevent the mandrel from falling out of the inner hole of the upper screw rod, and the long bolt can also stretch and retract in a certain range in the inner hole of the upper screw rod to adapt to the compression and extension of the spring.
Moreover, the friction force in the rotating process is effectively reduced through the thrust ball bearing 23, so that the accuracy and reliability of the detected moment are ensured.
Further, the mandrel 14 includes an optical axis section 1401, the optical axis section 1401 and a central hole of the upper screw rod 12 form a sliding fit, an internal threaded hole 1405 is machined at a central part of a bottom end of the optical axis section 1401, a hexagonal column 1403 matched with the adapter wrench 19 is arranged at a top end of the optical axis section 1401, a square column 1404 matched with the adapter wrench 16 is arranged at a top end of the hexagonal column 1403, and a spring positioning sleeve 1402 used for installing the thrust ball bearing 23 and positioning the spring 13 is arranged at a bottom end of the hexagonal column 1403. The mandrel 14 can be used to mount and fix the tool tip 16. The hexagonal post 1403 cooperates with the connection wrench 19 and can then be used to transmit torque. Square posts 1404 cooperate with the cutter head 16 to enable torque transfer.
Further, the long bolt structure 22 includes a mandrel segment 2203, a positioning column 2204 is disposed at the end of the mandrel segment 2203, and the positioning column 2204 is matched with the internal threaded hole 1405 of the mandrel 14; the bottom of ejector rod section 2203 is provided with guide section 2202, and guide section 2202 constitutes sliding fit with the through-hole of upper portion lead screw 12 bottom, and the bottom of guide section 2202 is provided with hexagon 2201. The long bolt structure 22 can be used to limit the mandrel 14.
Further, the cutter head 16 includes a sleeve 1601, a circular hole 1605 is machined in the sleeve 1601, and a square hole 1606 is machined at the bottom end of the circular hole 1605; square bore 1606 mates with square post 1404 of mandrel 14 and transmits torque; the upper outer wall of the sleeve 1601 is provided with a collar 1602, the top end of the sleeve 1601 is provided with a threaded ring section 1603, and the center of the top end of the threaded ring section 1603 is provided with a knife edge 1604 for matching with a notch of the wing bolt 24. The tool-tip 16 described above can be used to reliably mate with wing bolts during inspection.
Further, the support ring structure 18 includes a central ring sleeve 1801, a support ring 1803 is fixed on the outer wall of the top end of the central ring sleeve 1801 through a rib plate 1802, and a central hole of the support ring 1803 is larger than the outer diameter of a nut of the wing bolt 24; the central collar 1801 is in threaded engagement with the threaded collar segment 1603 of the cutter head 16, and a washer 17 is provided at the point of contact between the support ring structure 18 and the cutter head 16. The support ring structure 18 is in contact with the airfoil surface area near the outer ring of the head of the aircraft wing butt bolt, so that the compression contact supporting surface is increased, and the overall stability of the device is improved.
The working process and principle of the utility model are as follows:
the method for checking the bolt tightening torque by adopting the device for checking the tightening torque of the docking bolt of the aircraft wing comprises the following steps:
step one, preliminary adjustment of supporting height:
the method comprises the steps of taking a table top of an aircraft maintenance working platform as a supporting surface, supporting a base 1 on the top of the aircraft maintenance working platform, primarily adjusting the lengths of an inner telescopic sleeve 6 and an outer telescopic sleeve 7 according to the height of the lower surface of an aircraft wing from the aircraft maintenance working platform, and locking the relative positions of the inner telescopic sleeve 6 and the outer telescopic sleeve 7 after the primary adjustment of the height is completed;
step two, fine adjustment of the supporting height:
aligning the tool bit 16 with the wing bolt 24 to be inspected, manually rotating the inner telescopic sleeve 6 and the outer telescopic sleeve 7, correspondingly driving the lower screw rod 3 and the upper screw rod 12 at two ends through forward and reverse screw transmission at the moment, compressing the spring 13 through the upper screw rod 12, compressing the mandrel 14 through the spring 13, and propping the tool bit 16 through the mandrel 14, so as to finely adjust the tool bit 16, compressing the tool bit 16 on the wing bolt 24, and ensuring that the compression state of the inspection device is not loosened in the operation process;
third, checking the tightening torque of the bolt:
after the tool bit 16 to be disassembled is reliably pressed and fixed with the wing bolt 24, a fixed torque wrench 21 is arranged on the transfer wrench 19, the fixed torque wrench 21 is pulled, torque is transmitted to the connecting wrench 19 through the fixed torque wrench 21, then the connecting wrench 19 transmits the torque to the mandrel 14, the mandrel 14 transmits the torque to the tool bit 16, the tool bit 16 transmits the torque to the wing bolt 24, and then the torque of the wing bolt 24 is detected;
fourth, adjusting the pressing force:
when the pressing force between the decompression bit 16 and the wing bolt 24 needs to be adjusted, the inner telescopic sleeve 6 and the outer telescopic sleeve 7 are manually rotated, at the moment, the lower screw rod 3 and the upper screw rod 12 at the two ends are correspondingly driven through forward and reverse threaded transmission, the spring 13 is pressed by the upper screw rod 12, the purpose of adjusting the pre-pressing force of the spring 13 is achieved, and the pre-pressing force of the compression spring is used for realizing the screw tightening and the pressure maintenance in the moment inspection process.
Claims (9)
1. An aircraft wing docking bolt tightening torque inspection device which is characterized in that: the device comprises a base (1), wherein the top of the base (1) is hinged with a lower screw rod (3) through a ball head structure, an inner telescopic sleeve (6) is arranged on the lower screw rod (3) through screw rod transmission, and an outer telescopic sleeve (7) is arranged outside the inner telescopic sleeve (6) through telescopic fit; the top end of the outer telescopic sleeve (7) is provided with an upper screw rod (12) through screw rod transmission; a compaction adjusting mechanism is arranged in the upper screw rod (12); a detaching tool bit (16) matched with a wing bolt (24) to be inspected is arranged at the top end of a mandrel (14) of the compaction adjusting mechanism in a matched mode, and a supporting ring structure (18) matched with the outer surface of the lower part of the wing is arranged at the top end of the detaching tool bit (16); an adapter wrench (19) for connecting the fixed torque wrench (21) is arranged on the mandrel (14) in a matching way.
2. The aircraft wing docking bolt tightening torque inspection device of claim 1, wherein: the lower screw rod (3) and the lower nut sleeve (5) form screw rod transmission, the lower nut sleeve (5) is fixed at the bottom end of the inner telescopic sleeve (6), and the lower locking nut (4) is sleeved on the lower screw rod (3);
the bottom ball head of the lower screw rod (3) is tightly hinged on the base (1) through the gland (2).
3. The aircraft wing docking bolt tightening torque inspection device of claim 1, wherein: the upper screw rod (12) and the upper nut sleeve (10) form screw rod transmission, the upper nut sleeve (10) is fixed at the top end of the outer telescopic sleeve (7), and the upper locking nut (11) is sleeved on the upper screw rod (12).
4. The aircraft wing docking bolt tightening torque inspection device of claim 1, wherein: bolt holes (8) are formed in the inner telescopic sleeve (6) and the outer telescopic sleeve (7) at equal intervals; after the relative length adjustment of the inner telescopic sleeve (6) and the outer telescopic sleeve (7) is completed, the inner telescopic sleeve and the outer telescopic sleeve are locked and fixed through a bolt handle (9) inserted between bolt holes (8).
5. The aircraft wing docking bolt tightening torque inspection device of claim 1, wherein: the compression adjusting mechanism comprises a mandrel (14) which is slidably arranged in the upper screw rod (12), a spring (13) is sleeved outside the mandrel (14), the bottom end of the spring (13) is contacted with the top end of the upper screw rod (12), and the top end of the spring (13) is in tight contact fit with the mandrel (14) in a propping way through a thrust ball bearing (23); the inner bottom end of the upper screw rod (12) is provided with a long bolt structure (22) for limiting the mandrel (14) in a threaded fit manner.
6. The aircraft wing docking bolt tightening torque check device of claim 5, wherein: the mandrel (14) comprises an optical axis section (1401), the optical axis section (1401) and a central hole of an upper screw rod (12) form sliding fit, an internal threaded hole (1405) is machined in the central part of the bottom end of the optical axis section (1401), a hexagonal column (1403) used for being matched with an adapter wrench (19) is arranged at the top end of the optical axis section (1401), a square column (1404) used for being matched with a cutter head (16) is arranged at the top end of the hexagonal column (1403), and a spring positioning sleeve (1402) used for installing a thrust ball bearing (23) and positioning a spring (13) is arranged at the bottom end of the hexagonal column (1403).
7. The aircraft wing docking bolt tightening torque check device of claim 5, wherein: the long bolt structure (22) comprises a push rod section (2203), a positioning column (2204) is arranged at the end position of the push rod section (2203), and the positioning column (2204) is matched with an inner threaded hole (1405) of the mandrel (14); the bottom of ejector rod section (2203) is provided with guide section (2202), and guide section (2202) constitutes sliding fit with the through-hole of upper portion lead screw (12) bottom, and the bottom of guide section (2202) is provided with hexagon head (2201).
8. The aircraft wing docking bolt tightening torque inspection device of claim 1, wherein: the tool removing head (16) comprises a sleeve (1601), a round hole (1605) is formed in the sleeve (1601), and a square hole (1606) is formed in the bottom end of the round hole (1605); the square hole (1606) is matched with a square column (1404) of the mandrel (14) and transmits torque; a collar (1602) is machined on the outer wall of the upper part of the sleeve (1601), a threaded ring section (1603) is machined at the top end of the sleeve (1601), and a knife edge (1604) which is used for being matched with a notch of the wing bolt (24) is machined at the center of the top end of the threaded ring section (1603).
9. The aircraft wing docking bolt tightening torque inspection device of claim 1, wherein: the support ring structure (18) comprises a center ring sleeve (1801), a support ring (1803) is fixed on the outer wall of the top end of the center ring sleeve (1801) through a rib plate (1802), and a center hole of the support ring (1803) is larger than the outer diameter of a screw cap of the wing bolt (24); the central ring sleeve (1801) and the threaded ring section (1603) of the tool removing head (16) form threaded fit, and a gasket (17) is arranged at the contact part of the supporting ring structure (18) and the tool removing head (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320084586.9U CN219115731U (en) | 2023-01-29 | 2023-01-29 | Device for checking tightening moment of wing butt-joint bolt of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320084586.9U CN219115731U (en) | 2023-01-29 | 2023-01-29 | Device for checking tightening moment of wing butt-joint bolt of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219115731U true CN219115731U (en) | 2023-06-02 |
Family
ID=86527947
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320084586.9U Active CN219115731U (en) | 2023-01-29 | 2023-01-29 | Device for checking tightening moment of wing butt-joint bolt of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219115731U (en) |
-
2023
- 2023-01-29 CN CN202320084586.9U patent/CN219115731U/en active Active
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