CN211810305U - Assembly tool device for vertical tail of airplane - Google Patents
Assembly tool device for vertical tail of airplane Download PDFInfo
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- CN211810305U CN211810305U CN201922484997.3U CN201922484997U CN211810305U CN 211810305 U CN211810305 U CN 211810305U CN 201922484997 U CN201922484997 U CN 201922484997U CN 211810305 U CN211810305 U CN 211810305U
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- vertical tail
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- 230000007246 mechanism Effects 0.000 claims abstract description 24
- 230000008878 coupling Effects 0.000 claims 1
- 238000010168 coupling process Methods 0.000 claims 1
- 238000005859 coupling reaction Methods 0.000 claims 1
- 238000000034 method Methods 0.000 description 16
- 125000006850 spacer group Chemical group 0.000 description 9
- 230000008569 process Effects 0.000 description 8
- 238000005553 drilling Methods 0.000 description 7
- 238000003754 machining Methods 0.000 description 5
- 238000011112 process operation Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
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Abstract
The utility model provides an assembly fixture device of perpendicular fin of aircraft relates to the assembly technical field of the perpendicular fin of aircraft. The device includes: the support is provided with a plurality of positioning and fixing mechanisms, and the plurality of positioning and fixing mechanisms are connected with the vertical tail wing of the airplane; the angle seat is fixed with the bracket; the joint positioning arm is fixed with the angle seat, the joint positioning arm is arranged at a fork-shaped lug of the vertical tail wing of the airplane, and the first through hole, the second through hole and the third through hole are coaxially arranged; the two fork-shaped lugs are arranged in parallel relatively, one fork-shaped lug is arranged between the first transverse plate and the second transverse plate, the other fork-shaped lug is arranged between the second transverse plate and the third transverse plate, and the two second through holes are covered by the two fork-shaped lugs; a gasket is arranged between each fork-shaped lug and the second transverse plate, and the gasket is simultaneously contacted with the fork-shaped lugs and the second transverse plate.
Description
Technical Field
The utility model relates to an assembly technical field of the perpendicular fin of aircraft particularly, relates to an assembly fixture device of the perpendicular fin of aircraft.
Background
The vertical tail of the airplane is usually connected with the airplane body in a butt joint mode of fork-shaped lugs. Since the vertical tail of an aircraft is an important component of the aircraft, the assembly requirements for the vertical tail of the aircraft are high, and accordingly, the positioning accuracy of the fork-shaped tabs becomes particularly important. The connection between the fork-shaped lugs and the airplane body is positioned and installed through positioning through holes formed in the fork-shaped lugs, and the number of the fork-shaped lugs is usually two. Each fork-shaped lug is provided with a positioning through hole, so the consistency between the positioning through holes of the two fork-shaped lugs becomes very important, for example, whether the coaxiality and the position degree of the positioning through holes of the two fork-shaped lugs are consistent or not is ensured.
However, the existing assembling method of the vertical tail of the airplane cannot ensure the consistency between the positioning through holes of the two fork-shaped lugs, and after the assembling is completed, the corresponding precision requirement can be met only by auxiliary adjustment and repair of a bench worker, so that the adjustment of the vertical tail of the airplane after the assembling is very complicated.
SUMMERY OF THE UTILITY MODEL
The utility model discloses aim at solving the problem that the current assembly methods of the perpendicular fin of aircraft can not guarantee the uniformity between the positioning hole of two Y-shaped auricles to a certain extent.
In order to solve the above problem, the utility model provides an assembly fixture device of perpendicular fin of aircraft, include:
the support is provided with a plurality of positioning and fixing mechanisms, and the plurality of positioning and fixing mechanisms are connected with the vertical tail wing of the airplane;
the angle seat is fixed with the bracket;
a joint positioning arm fixed with the corner seat, the joint positioning arm is arranged at the fork lug of the vertical tail wing of the airplane, the joint positioning arm comprises a first transverse plate, a second transverse plate, a third transverse plate and a vertical plate, the vertical plate is connected with the body of the joint positioning arm, the vertical plates are vertically arranged, the first transverse plate, the second transverse plate and the third transverse plate are sequentially arranged in parallel from top to bottom, the first transverse plate, the second transverse plate and the third transverse plate are all horizontally arranged, two first through holes are arranged on the plate surface of the first transverse plate, the plate surface of the second transverse plate is provided with two second through holes, the plate surface of the third transverse plate is provided with two third through holes, one first through hole, one second through hole and one third through hole are coaxially arranged along a first axis, and the other first through hole, the other second through hole and the other third through hole are coaxially arranged along a second axis;
the two fork-shaped lugs are arranged in parallel relatively, one fork-shaped lug is arranged between the first transverse plate and the second transverse plate, the other fork-shaped lug is arranged between the second transverse plate and the third transverse plate, and the two second through holes are covered by the two fork-shaped lugs;
a gasket is arranged between each fork-shaped lug and the second transverse plate, and the gasket is simultaneously contacted with the fork-shaped lugs and the second transverse plate.
Further, a drill sleeve is arranged at each first through hole.
Further, a guide bushing is arranged at each third through hole.
Further, the gasket is of a rectangular sheet structure, a groove is formed in one end of the length of the gasket, the groove is formed in the thickness direction of the gasket, and the long edge of the gasket is bent into a v shape.
Furthermore, each fork-shaped lug is provided with two positioning through holes, and the two positioning through holes and the two second through holes of each fork-shaped lug are coaxially arranged;
the assembling tool device for the vertical empennage of the airplane further comprises two bolts, and one bolt is sequentially inserted into one first through hole, one second through hole, one third through hole and one positioning through hole of each fork-shaped lug plate along the first axis;
the other pin is inserted into the other first through hole, the other second through hole, the other third through hole and the other positioning through hole of each fork-shaped lug plate along the second axis in sequence.
Further, the apertures of the first through-hole to the third through-hole are sequentially reduced.
Further, the pin shaft of the bolt is a stepped shaft.
Further, the support of assembly fixture device of perpendicular fin of aircraft include crossbeam, sloping, first stand, second stand, first base and second base, first stand is fixed on the first base, the second stand is fixed on the second base, the both ends of sloping respectively with first stand with the second stand is fixed, the crossbeam set up in the sloping top, the both ends of crossbeam respectively with first stand with the second stand is fixed, the sloping is installed a plurality ofly location fixed establishment, the crossbeam is installed a plurality ofly location fixed establishment, the aircraft fin set up perpendicularly in the crossbeam with between the sloping.
Furthermore, an auxiliary support seat is fixed at the bottom of the oblique beam and is arranged between the first upright post and the second upright post.
Furthermore, the first upright post is connected with a first supporting arm, the top end of the first supporting arm is connected with the first upright post, and the bottom end of the first supporting arm is connected with the first base;
the second upright post is connected with a second supporting arm, the top end of the second supporting arm is connected with the second upright post, and the bottom end of the second supporting arm is connected with the second base.
The positioning fixing mechanisms are connected with the vertical tail wing of the airplane, so that the first positioning procedure operation, namely the coarse positioning operation, is carried out on the vertical tail wing of the airplane. Then, one fork-shaped lug is placed between the first transverse plate and the second transverse plate, the other fork-shaped lug is placed between the second transverse plate and the third transverse plate, and the two second through holes are covered by the two fork-shaped lugs; thereby ensuring that the positioning through holes can be drilled on the surface of the fork-shaped lug. Meanwhile, in order to ensure that the two fork-shaped lugs and the second transverse plate are firmly fixed, a gasket is arranged between each fork-shaped lug and the second transverse plate, and the gasket is simultaneously contacted with the fork-shaped lugs and the second transverse plate. Thereby using the gasket to plug between the second cross plate and the fork-shaped lug plate and preventing the fork-shaped lug plate from moving relative to the second cross plate.
And then, the drill is guided to drill towards the fork-shaped lug plate by using the first through hole and the third through hole as guide holes. The processing of the positioning through holes of the two fork-shaped lugs is realized in one drilling process, so that the coaxiality, the aperture size and the position degree of the two fork-shaped lugs are ensured. Thereby ensuring the consistency between the positioning through holes of the two fork-shaped lugs.
Drawings
Fig. 1 is a schematic perspective view of an assembly fixture device for a vertical tail of an airplane according to an embodiment of the present invention;
FIG. 2 is an enlarged view taken at P in FIG. 1;
fig. 3 is a schematic perspective view of a forked tab of an aircraft vertical tail according to an embodiment of the present invention;
fig. 4 is a schematic perspective view of the joint locator arm and the fork tab of an embodiment of the present invention assembled together;
fig. 5 is a schematic cross-sectional view of a joint locator arm and a fork tab of an embodiment of the present invention assembled together;
fig. 6 is a schematic perspective view of a joint positioning arm according to an embodiment of the present invention;
fig. 7 is a schematic perspective view of a gasket according to an embodiment of the present invention;
fig. 8 is a schematic front view of a latch according to an embodiment of the present invention.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention more comprehensible, embodiments accompanied with figures are described in detail below.
In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "rear", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention.
Also, in the drawings, the Z-axis represents a vertical, i.e., up-down position, and a positive direction of the Z-axis (i.e., an arrow direction of the Z-axis) represents up, and a negative direction of the Z-axis (i.e., a direction opposite to the positive direction of the Z-axis) represents down;
also, the X-axis in the drawings indicates the horizontal direction;
it should also be noted that the foregoing Z-axis and X-axis are meant only to facilitate the description of the invention and to simplify the description, and are not intended to indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the invention.
The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature.
Referring to fig. 1 to 8, the present embodiment provides an assembly fixture device for an aircraft vertical tail 200, including:
a bracket 100 on which a plurality of positioning and fixing mechanisms 110 are mounted, the plurality of positioning and fixing mechanisms 110 being connected to a vertical tail 200 of an aircraft;
a corner seat 120 fixed to the bracket 100;
the joint positioning arm 300 is fixed with the corner seat 120, the joint positioning arm 300 is arranged at the fork lug 210 of the vertical tail wing 200 of the airplane, the joint positioning arm 300 comprises a first transverse plate 310, a second transverse plate 320, a third transverse plate 330 and a vertical plate 340, the vertical plate 340 is connected with the body of the joint positioning arm 300, the vertical plate 340 is vertically arranged, the first transverse plate 310, the second transverse plate 320 and the third transverse plate 330 are sequentially arranged in parallel from top to bottom, the first transverse plate 310, the second transverse plate 320 and the third transverse plate 330 are both horizontally arranged, the plate surface of the first transverse plate 310 is provided with two first through holes 311, the plate surface of the second transverse plate 320 is provided with two second through holes 321, the plate surface of the third transverse plate 330 is provided with two third through holes 331, one first through hole 311, one second through hole 321 and one third through hole 331 are coaxially arranged along a first axis 381, and the other first through hole 311, the other second through hole 321 and the other third through hole 331 are coaxially arranged along a second axis 382;
it should be noted that the first axis 381 and the second axis 382 are only used for convenience of describing the structure, and are used for explanation, and do not affect the protection scope of the claims.
The two fork-shaped lugs 210 are arranged in parallel, one fork-shaped lug 210 is arranged between the first transverse plate 310 and the second transverse plate 320, the other fork-shaped lug 210 is arranged between the second transverse plate 320 and the third transverse plate 330, and the two fork-shaped lugs 210 cover the two second through holes 321;
a spacer 350 is disposed between each fork tab 210 and the second cross plate 320, the spacer 350 simultaneously contacting the fork tabs 210 and the second cross plate 320.
When the positioning and fixing mechanism is used, the positioning and fixing mechanism is connected with the vertical tail wing 200 through the plurality of positioning and fixing mechanisms 110, so that the first positioning procedure operation is carried out on the vertical tail wing 200, and the positioning, namely the coarse positioning operation, is carried out by taking the plurality of positioning and fixing mechanisms 110 as a reference. Next, one fork-shaped tab 210 is placed between the first horizontal plate 310 and the second horizontal plate 320, another fork-shaped tab 210 is placed between the second horizontal plate 320 and the third horizontal plate 330, and the two second through holes 321 are covered by the two fork-shaped tabs 210; thereby ensuring that the positioning through-holes 211 can be drilled in the surface of the fork-shaped tabs 210. Meanwhile, in order to ensure that the two fork-shaped lugs 210 are firmly fixed with the second transverse plate 320, a gasket 350 is arranged between each fork-shaped lug 210 and the second transverse plate 320, and the gasket 350 is simultaneously contacted with the fork-shaped lugs 210 and the second transverse plate 320. Thereby jamming the fork tab 210 between the second cross plate 320 and the fork tab 210 using the spacer 350 to prevent the fork tab 210 from moving relative to the second cross plate 320.
Next, the drill is guided to drill the fork tab 210 using the first through hole 311 and the third through hole 331 as guide holes. The positioning through holes 211 of the two fork-shaped lugs 210 are machined in one drilling process, so that the coaxiality, the aperture size and the position degree of the two fork-shaped lugs 210 are ensured. Thereby ensuring consistency between the positioning through holes 211 of the two fork-shaped tabs 210.
Referring to fig. 1 to 8, preferably, a drill bushing 312 is disposed at each first through hole 311.
Referring to fig. 1-8, preferably, the drill sleeve 312 is a quick drill sleeve.
The drill sleeve 312 is arranged at the first through hole 311, so that the axis of the drill is ensured to be coaxial with the axis of the first through hole 311, and the first through hole 311, the second through hole 321 and the third through hole 331 are all arranged coaxially, so that the drilling and positioning accuracy of the drill on the positioning through hole 211 is ensured by using the drill sleeve 312.
In addition, after drilling, the positioning through hole 211 needs to be reamed and reamed. So that the drill sleeve 312 may still be used as a reference for reaming and reaming. Thereby ensuring the coaxiality of subsequent drilling and reaming.
Referring to fig. 1 to 8, preferably, a guide bushing 332 is disposed at each third through hole 331.
The guide bush 332 is matched with the drill sleeve 312 to guide the drill bit to continue moving downwards along the set direction after the drill bit drills the positioning through hole 211, so that the accuracy of the position accuracy of the positioning through hole 211 is ensured.
Meanwhile, the guide bush 332 can guide the reamer to continuously move downwards along the set direction in the subsequent reaming and reaming process, so that the correct reaming and reaming direction is ensured.
Referring to fig. 1 to 8, preferably, the gasket 350 has a rectangular sheet structure, a groove 351 is formed at one end of the length of the gasket 350, the groove 351 is opened along the thickness direction of the gasket 350, and the long side of the gasket 350 is bent in a v shape.
Bending the long side of the spacer 350 to v can facilitate the spacer 350 to be inserted into the gap between the fork-shaped lug 210 and the second cross plate 320, especially in the case that the gap is small, the spacer 350 is thin, which may easily scratch the hand of the operator, and the insertion effect is not ideal. The v-shaped gasket 350 is bent, so that the operator can conveniently hold the bent gasket, and the bent gasket can prevent the fingers of the operator from moving relative to the gasket 350.
When the positioning through hole 211 is machined and the insert pin 400 is inserted into the positioning through hole 211, the sidewall of the insert pin 400 may be placed in the groove 351 when the spacer 350 is inserted into the gap, so that the insert pin 400 is positioned by the groove 351 and the spacer 350 is prevented from moving relative to the insert pin 400 during the insertion process.
Referring to fig. 1 to 8, preferably, each fork-shaped lug 210 is provided with two positioning through holes 211, and the two positioning through holes 211 of each fork-shaped lug 210 are coaxially arranged with the two second through holes 321;
the assembly tooling device of the vertical empennage 200 of the airplane further comprises two bolts 400, wherein one bolt 400 is sequentially inserted into one first through hole 311, one second through hole 321, one third through hole 331 and one positioning through hole 211 of each fork-shaped lug plate along a first axis 381;
the other pin 400 is inserted into the other first through hole 311, the other second through hole 321, the other third through hole 331, and the other positioning through hole 211 of each fork tab in sequence along the second axis 382.
After the positioning through-holes 211 are processed, the vertical rear wing 200 is assembled with reference to the positioning through-holes 211 by inserting the pins 400 into the positioning through-holes 211. Since the positioning through holes 211 are already used as a reference, the assembling accuracy of the entire vertical rear wing 200 to the aircraft and the uniformity of the assembly of the vertical rear wing 200 are ensured, thereby ensuring good uniformity of the vertical rear wing to the fuselage. Meanwhile, in this process, the previous positioning, i.e., coarse positioning, based on the plurality of positioning and fixing mechanisms 110 may be gradually eliminated, so that the positions of the plurality of positioning and fixing mechanisms with respect to the vertical rear wing of the aircraft may be adjusted. Thereby ensuring that the entire vertical rear wing 200 is accurately positioned with respect to the positioning through-hole 211.
Of course, in this process, the connection positions of the plurality of positioning and fixing mechanisms 110 and the vertical tail 200 of the airplane need to be adjusted, so as to adjust the positioning state of the entire vertical tail 200 based on the positioning through holes 211.
Referring to fig. 1 to 8, preferably, the apertures of the first to third through holes 311 to 331 are sequentially reduced.
Referring to fig. 1 to 8, preferably, the pin shaft of the latch 400 is a stepped shaft.
The diameters of the through holes 311 to 331 are sequentially reduced, and the pin shaft of the plug 400 is a stepped shaft. Ensures that the vertical tail 200 does not move or shake relative to the joint positioning arm 300 during the assembly process of the entire vertical tail 200 based on the positioning through hole 211, and particularly prevents the plug 400 from moving axially.
In addition, the present embodiment also provides a method for positioning the forked tab 210 of the vertical tail 200 of the aircraft, wherein the method for positioning the forked tab 210 of the vertical tail 200 of the aircraft for mounting the vertical tail 200 of the aircraft using the assembly fixture device of the vertical tail 200 of the aircraft comprises:
s100, placing a second transverse plate 320 between the two fork-shaped lugs 210;
s200. using a plurality of spacers 350 to be inserted into the gap between the fork-shaped lug 210 and the second cross plate 320 to prevent the fork-shaped lug 210 from moving relative to the second cross plate 320;
s300, drilling positioning through holes 211 by taking the first through holes 311 as a reference, so that the positioning through holes 211 of the two fork-shaped lugs 210 are coaxially arranged;
s400, inserting the plug 400 into the first through hole 311, the second through hole 321, the third through hole 331 and the positioning through hole 211 which are coaxially arranged, and assembling the vertical tail wing 200 of the airplane by taking the positioning through hole 211 as a reference.
The technical effect of the positioning method of the fork-shaped lug 210 of the vertical tail 200 of the airplane is the same as that of the assembling tool device, so the explanation is omitted here.
Referring to fig. 1 to 8, preferably, after the positioning through-hole 211 is drilled with reference to the first through-hole 311;
the positioning through hole 211 is reamed;
the positioning through-hole 211 is then reamed.
Then, the plug 400 is inserted into the first through hole 311, the second through hole 321, the third through hole 331 and the positioning through hole 211, which are coaxially disposed, and the vertical rear wing 200 of the airplane is assembled with reference to the positioning through hole 211.
In this embodiment, the drilling is only rough machining, and the positioning through hole 211 is subjected to deep machining by reaming and reaming. Through the cooperation of rough machining and finish machining, the positioning through holes 211 are ensured to meet the machining requirements.
Referring to fig. 1-8, preferably, before the second cross plate 320 is placed between the two fork tabs 210;
performing a first positioning process operation, namely performing coarse positioning, on the vertical tail 200 of the airplane through the plurality of positioning and fixing mechanisms 110, thereby forming a coarse positioning reference;
after the bolts 400 are inserted into the first through holes 311, the second through holes 321, the third through holes 331 and the positioning through holes 211 which are coaxially arranged, a second positioning procedure operation is performed, so that a fine positioning reference is formed, namely, the vertical tail wing 200 is finely positioned by taking the first positioning through holes 211 as a reference, so as to adjust the positions of the plurality of positioning and fixing mechanisms 110 relative to the vertical tail wing 200 of the airplane;
the positioning accuracy of the second positioning process operation is higher than that of the first positioning process operation.
The joint positioning arm 300 is matched with the positioning and fixing mechanism 110, so that the mutual conversion of the rough positioning reference and the fine positioning reference is realized, and the accurate positioning is ensured.
In addition, it should be noted that the bracket 100 of the assembly fixture device for the vertical tail 200 of the aircraft includes a cross beam 131, an oblique beam 132, a first upright post 133, a second upright post 134, a first base 135 and a second base 136, the first upright post 133 is fixed on the first base 135, the second upright post 134 is fixed on the second base 136, two ends of the oblique beam 132 are respectively fixed with the first upright post 133 and the second upright post 134, the cross beam 131 is disposed above the oblique beam 132, two ends of the cross beam 131 are respectively fixed with the first upright post 133 and the second upright post 134, the oblique beam 132 is mounted with a plurality of positioning and fixing mechanisms 110, the cross beam 131 is mounted with a plurality of positioning and fixing mechanisms 110, and the vertical tail 200 of the aircraft is disposed between the cross beam 131 and the oblique beam 132.
Referring to fig. 1 to 8, preferably, an auxiliary support 137 is fixed to the bottom of the inclined beam 132, and the auxiliary support 137 is disposed between the first upright post 133 and the second upright post 134.
The auxiliary support seat 137 is arranged between the first upright post 133 and the second upright post 134, so that the middle part of the oblique beam 132 is prevented from collapsing to influence the assembly accuracy of the vertical tail fin 200.
Referring to fig. 1 to 8, preferably, the first upright post 133 is connected with a first support arm 138, the top end of the first support arm 138 is connected with the first upright post 133, and the bottom end of the first support arm 138 is connected with the first base 135;
the second upright 134 is connected with a second supporting arm 139, the top end of the second supporting arm 139 is connected with the second upright 134, and the bottom end of the second supporting arm 139 is connected with the second base 136.
The first upright 133 and the first base 135 are reinforced by the first support arm 138, and the second upright 134 and the second base 136 are reinforced by the second support arm 139, so that the vertical rear wing 200 is prevented from wobbling during the assembly process.
The joint positioning arms 300 are plural, the plurality of corner seats 120 are respectively fixed at the first upright post 133 and the second upright post 134, and the plurality of joint positioning arms 300 are respectively disposed at the first upright post 133 and the second upright post 134.
Although the present disclosure has been described above, the scope of the present disclosure is not limited thereto. Without departing from the spirit and scope of the present disclosure, those skilled in the art can make various changes and modifications, which will fall into the scope of the present disclosure.
Claims (10)
1. The utility model provides an assembly fixture device of perpendicular fin of aircraft which characterized in that includes:
the device comprises a bracket, a positioning and fixing mechanism and a control mechanism, wherein the bracket is provided with a plurality of positioning and fixing mechanisms which are used for being connected with a vertical tail wing of an airplane;
the angle seat is fixed with the bracket;
connect the locating arm, with the corner seat is fixed, connect the locating arm be used for set up in the forked auricle department of the perpendicular fin of aircraft, connect the locating arm including first diaphragm, second diaphragm, third diaphragm and riser, the riser with this body coupling of connecting the locating arm, the riser is erect and is set up, first diaphragm, the second diaphragm reaches the third diaphragm from top to bottom parallels the setting in proper order, first diaphragm, the second diaphragm reaches the third diaphragm is the level setting, two first through-holes have been seted up to the face of first diaphragm, two second through-holes have been seted up to the face of second diaphragm, two third through-holes have been seted up to the face of third diaphragm, one first through-hole, one second through-hole and one the third through-hole is along the coaxial setting of primary axis, another first through-hole, first through-hole, The other second through hole and the other third through hole are coaxially arranged along a second axis;
the two fork-shaped lugs are arranged in parallel relatively, one fork-shaped lug is arranged between the first transverse plate and the second transverse plate, the other fork-shaped lug is arranged between the second transverse plate and the third transverse plate, and the two second through holes are covered by the two fork-shaped lugs;
a gasket is arranged between each fork-shaped lug and the second transverse plate, and the gasket is simultaneously contacted with the fork-shaped lugs and the second transverse plate.
2. The assembly tool device for the vertical tail of the airplane as claimed in claim 1, wherein a drill bushing is arranged at each first through hole.
3. The assembly tooling device for the vertical tail of the airplane as claimed in claim 2, wherein a guide bushing is arranged at each third through hole.
4. The assembly fixture device for the vertical tail of the airplane as claimed in claim 3, wherein the gasket is of a rectangular sheet structure, a groove is formed in one end of the length of the gasket, the groove is formed in the thickness direction of the gasket, and the long edge of the gasket is bent into a v shape.
5. The assembly tooling device for the vertical tail of the airplane according to claim 3, wherein each fork-shaped lug is provided with two positioning through holes, and the two positioning through holes of each fork-shaped lug are respectively and coaxially arranged with the two second through holes;
the assembling tool device for the vertical empennage of the airplane further comprises two bolts, and one bolt is sequentially inserted into one first through hole, one second through hole, one third through hole and one positioning through hole of each fork-shaped lug plate along the first axis;
the other pin is inserted into the other first through hole, the other second through hole, the other third through hole and the other positioning through hole of each fork-shaped lug plate along the second axis in sequence.
6. The assembly fixture device for the vertical tail of the aircraft as recited in claim 5, wherein the diameters of the first through hole to the third through hole are sequentially reduced.
7. The assembly tooling device for the vertical tail of the airplane as claimed in claim 6, wherein the pin shaft of the pin is a stepped shaft.
8. The assembly fixture device of the vertical tail of the airplane as claimed in any one of claims 1 to 7, wherein the support of the assembly fixture device of the vertical tail of the airplane comprises a cross beam, an oblique beam, a first upright, a second upright, a first base and a second base, the first upright is fixed on the first base, the second upright is fixed on the second base, two ends of the oblique beam are respectively fixed with the first upright and the second upright, the cross beam is arranged above the oblique beam, two ends of the cross beam are respectively fixed with the first upright and the second upright, the oblique beam is provided with a plurality of positioning and fixing mechanisms, the cross beam is provided with a plurality of positioning and fixing mechanisms, and the vertical tail of the airplane is arranged between the cross beam and the oblique beam.
9. The assembly tool device for the vertical tail of the airplane as claimed in claim 8, wherein an auxiliary support seat is fixed to the bottom of the oblique beam and is arranged between the first upright post and the second upright post.
10. The assembly tool device for the vertical tail of the airplane as claimed in claim 9, wherein the first upright is connected with a first support arm, the top end of the first support arm is connected with the first upright, and the bottom end of the first support arm is connected with the first base;
the second upright post is connected with a second supporting arm, the top end of the second supporting arm is connected with the second upright post, and the bottom end of the second supporting arm is connected with the second base.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922484997.3U CN211810305U (en) | 2019-12-31 | 2019-12-31 | Assembly tool device for vertical tail of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922484997.3U CN211810305U (en) | 2019-12-31 | 2019-12-31 | Assembly tool device for vertical tail of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211810305U true CN211810305U (en) | 2020-10-30 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922484997.3U Withdrawn - After Issue CN211810305U (en) | 2019-12-31 | 2019-12-31 | Assembly tool device for vertical tail of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211810305U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979724A (en) * | 2019-12-31 | 2020-04-10 | 哈尔滨安宇迪航空工业有限公司 | Assembly tool device and positioning method for vertical empennage of airplane |
-
2019
- 2019-12-31 CN CN201922484997.3U patent/CN211810305U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979724A (en) * | 2019-12-31 | 2020-04-10 | 哈尔滨安宇迪航空工业有限公司 | Assembly tool device and positioning method for vertical empennage of airplane |
| CN110979724B (en) * | 2019-12-31 | 2024-02-27 | 哈尔滨安宇迪航空工业有限公司 | Assembly fixture device and positioning method for vertical tail wing of airplane |
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Address after: No. 15 Xinghai Road, Pingfang District, Harbin City, Heilongjiang Province, 150066 Patentee after: Harbin Anyudi Aviation Industry Co.,Ltd. Address before: 150000 Xinghai Road, Pingfang District, Harbin, Heilongjiang Patentee before: Harbin anyudi Aviation Industry Co.,Ltd. |
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| CP03 | Change of name, title or address | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20201030 Effective date of abandoning: 20240227 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20201030 Effective date of abandoning: 20240227 |
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| AV01 | Patent right actively abandoned |