CN210133301U - Aircraft ventral fin supports frock - Google Patents
Aircraft ventral fin supports frock Download PDFInfo
- Publication number
- CN210133301U CN210133301U CN201920418036.XU CN201920418036U CN210133301U CN 210133301 U CN210133301 U CN 210133301U CN 201920418036 U CN201920418036 U CN 201920418036U CN 210133301 U CN210133301 U CN 210133301U
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- Prior art keywords
- nut
- pole setting
- barrel
- tray
- rod
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- Expired - Fee Related
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- 239000003381 stabilizer Substances 0.000 claims abstract description 8
- 239000000203 mixture Substances 0.000 claims abstract description 4
- 238000003466 welding Methods 0.000 claims description 5
- 230000001105 regulatory effect Effects 0.000 abstract 2
- 238000012423 maintenance Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000001934 delay Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Abstract
The utility model discloses an aircraft ventral fin supports frock, the on-line screen storage device comprises a tray, the tray is the U type, and the tray both sides all are equipped with the through-hole, still include altitude mixture control spare, stabilizer blade regulating part and pole setting, the top of pole setting is provided with the slot, be provided with external screw thread two on the pole setting lateral wall in the slot outside, the pole setting lateral wall of two below external screw threads is provided with external screw thread one, the stabilizer blade regulating part sets up the bottom in the pole setting. The utility model discloses during the application, rotate first nut of going up and make first nut in the pole setting lapse, can promote hinge ring lapse through barrel one, because branch is close to one side articulated connecting rod of pole setting, the one end that branch was kept away from to the connecting rod is articulated with the pole setting bottom, so can make 4 branch outwards expand, it is more stable to make the support, when not using, rotate first nut of going up and make first nut in the pole setting lapse, can promote hinge ring lapse through barrel, make 4 branch inwards shrink, and the reduction area is convenient for deposit.
Description
Technical Field
The utility model relates to a support the frock field, specificly relate to an aircraft abdomenal fin supports frock.
Background
With the gradual release of low-altitude airspace and the intensive departure of relevant interest and good policies of navigation in China, the navigation industry in China has sudden development, the aircraft assembly is a technical work which has high technical difficulty, wide subject and high comprehensive integration level, the final quality, the manufacturing cost and the period of the aircraft are determined, the aircraft assembly is a huge barrier which restricts the rapid development of the aircraft in China, and the bottleneck which restricts the technical development of the aircraft assembly is the development of various tools. Also, maintenance of the general purpose aircraft is also affected by delays in tooling development.
In the field of aircraft manufacturing and maintenance, a tool for supporting the tail of an aircraft is needed. The aircraft is the bikini at three undercarriage overall arrangement under normal condition, and the focus of aircraft also just in time falls between the projection of three point on ground, and the aircraft can stably park, and when the aircraft has not assembled yet and finishes or need dismantle great spare part in the maintenance process, makes the focus of aircraft surpass the three point range easily, causes the aircraft to empty, consequently, need provide one kind and can carry out the frock that supports to the aircraft afterbody to improve the aircraft assembly and the stability in the maintenance process.
SUMMERY OF THE UTILITY MODEL
1. Technical problem to be solved
An object of the utility model is to provide an aircraft ventral fin supports frock to solve the problem that proposes in the above-mentioned background art.
2. Technical scheme
In order to solve the above problem, the utility model adopts the following technical scheme:
an aircraft ventral fin supports frock, includes the tray, the tray is the U type, and the tray both sides all are equipped with the through-hole, still includes height adjusting part, stabilizer blade adjusting part and pole setting, the top of pole setting is provided with the slot, be provided with external screw thread two on the pole setting lateral wall in the slot outside, the pole setting lateral wall below external screw thread two is provided with external screw thread one, stabilizer blade adjusting part sets up in the bottom of pole setting, stabilizer blade adjusting part includes hinge ring, barrel one, pole setting, bearing one, branch, connecting rod and universal wheel, and nut one sets up the outside at external screw thread one, barrel one welds the bottom at nut one, the hinge ring slides and sets up in the pole setting below external screw thread one, and barrel one keeps away from the one end of nut one and is connected with the top of hinge ring through bearing one, the bottom of hinge ring evenly articulates along the circumferencial direction has 4 branches, the one end that pole setting was kept away from to branch is provided with the universal wheel, one side that pole setting was close to branch articulates there is the connecting rod, the one end that pole setting was kept away from to the connecting rod is articulated with the pole setting bottom, altitude mixture control spare sets up on the top of pole setting, and altitude mixture control spare is including adjusting pole, spacing ring, nut two, barrel two and bearing two, it establishes inside the slot to adjust the pole to insert, and the one end of adjusting the pole extends to the top fixedly connected with tray of pole setting, the spacing ring sets up on the regulation pole lateral wall of pole setting top, nut two sets up the outside at external screw thread two, the welding of barrel two is at the top of nut two, the one end that nut two was kept away from.
Preferably, the first nut and the first external thread are matched with each other, and the radius of the first nut is equal to that of the first cylinder.
Preferably, the second nut is matched with the second external thread, and the radius of the second nut is equal to that of the second cylinder.
Preferably, 4 pull rods are arranged on the outer sides of the second nut and the first nut at equal intervals.
Preferably, the universal wheel is provided with a brake pad.
3. Advantageous effects
The utility model discloses a nut one sets up in the outside of external screw thread one, and the bottom welding barrel one of nut one, the setting of sliding is at the hinge ring on the pole setting below the external screw thread one, and the barrel one is kept away from the one end of nut one and is connected with the top of hinge ring through bearing one, the bottom of hinge ring evenly articulates 4 spinal branch along the circumferencial direction, the pole branch is kept away from the one end of pole setting and is provided with the universal wheel, when using, rotate nut one and make nut one move down in the pole setting, can promote the hinge ring to move down through barrel one, because the side hinge connecting rod that the spinal branch is close to the pole setting, the connecting rod is kept away from the one end of spinal branch and is articulated with the pole setting bottom, so can make 4 spinal branch expand outward, make the support more stable, when not using, rotate nut one and make nut one move up in the pole setting, can promote, reduce area, be convenient for deposit, establish the regulation pole through inserting inside the slot, and the one end of adjusting the pole extends to the top fixed connection tray of pole setting, set up the spacing ring on the regulation pole lateral wall of pole setting top, the outside at external thread two sets up nut two, two welding of barrel are at the top of nut two, the one end that nut two was kept away from to barrel two is passed through bearing two and is connected with the spacing ring, when the height of tray is adjusted to needs, rotatable nut two makes nut two move in the pole setting, nut two moves accessible barrel two in the pole setting and drives the regulation pole and reciprocate in the slot of pole setting, thereby to the height adjustment of tray, and convenient for operation is simple, and is efficient, auto-lock between nut two and the pole setting, can ensure the bracket and keep the position department after the regulation, ensure the reliability of support.
Drawings
Fig. 1 is a schematic structural view of the present invention;
fig. 2 is a schematic front view of the structure of the present invention.
Reference numerals: 1-universal wheel, 2-strut, 3-bearing I, 4-cylinder I, 5-external thread I, 6-nut I, 7-slot, 8-nut II, 9-cylinder II, 10-limit ring, 11-tray, 12-adjusting rod, 13-bearing II, 14-external thread II, 15-hinged ring, 16-connecting rod and 17-vertical rod.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
Examples
As shown in fig. 1-2, the aircraft ventral fin supporting tool comprises a tray 11, wherein the tray 11 is U-shaped, through holes 111 are formed in two sides of the tray 11, the aircraft ventral fin supporting tool further comprises a height adjusting piece, a support leg adjusting piece and an upright rod 17, a slot 7 is formed in the top of the upright rod 17, an external thread two 14 is arranged on the side wall of the upright rod 17 outside the slot 7, an external thread one 5 is arranged on the side wall of the upright rod 17 below the external thread two 14, the support leg adjusting piece is arranged at the bottom end of the upright rod 17, the support leg adjusting piece comprises a hinge ring 15, a cylinder body one 4, an upright rod 17, a bearing one 3, a support rod 2, a connecting rod 16 and a universal wheel 1, a nut one 6 is arranged outside the external thread one 5, the cylinder body one 4 is welded at the bottom of the nut one 6, the hinge ring 15 is arranged on the upright rod 17 below the external thread one 5 in, the nut I6 is matched with the external thread I5, the radius of the nut I6 is equal to that of the cylinder I4, the bottom of the hinged ring 15 is uniformly hinged with 4 support rods 2 along the circumferential direction, one end of each support rod 2, far away from the upright rod 17, is provided with a universal wheel 1, the universal wheel 1 is provided with a brake pad, one side of each support rod 2, close to the upright rod 17, is hinged with a connecting rod 16, one end of each connecting rod 16, far away from the corresponding support rod 2, is hinged with the bottom end of the upright rod 17, the height adjusting piece is arranged at the top end of the upright rod 17 and comprises an adjusting rod 12, a limiting ring 10, a nut II 8, a cylinder II 9 and a bearing II 13, the adjusting rod 12 is inserted into the slot 7, one end of the adjusting rod 12 extends to the top of the upright rod 17 and is fixedly connected with a tray 11, the limiting ring 10 is arranged on the outer side wall, the second nut 8 is matched with the second external thread 14, the radius of the second nut 8 is equal to that of the second cylinder 9, one end, far away from the second nut 8, of the second cylinder 9 is connected with the limiting ring 10 through the second bearing 13, and 4 pull rods are arranged on the outer sides of the second nut 8 and the first nut 6 at equal intervals.
The specific application process comprises the following steps: before application, the upper nut I6 is rotated to enable the nut I6 to move downwards on the vertical rod 17, the hinge ring 15 can be pushed to move downwards through the cylinder I4, the connecting rod 16 is hinged to one side, close to the vertical rod 17, of the support rod 2, one end, far away from the support rod 2, of the connecting rod 13 is hinged to the bottom end of the vertical rod 17, the bottom ends of the 4 support rods 2 are expanded outwards through the universal wheel 1, so that the support is more stable, when the device is not used, the upper nut I6 is rotated to enable the nut I6 to move upwards on the vertical rod 17, the hinge ring 15 can be pulled to move upwards through the cylinder I4, the bottom ends of the 4 support rods 2 are contracted inwards through the universal wheel 1, the occupied area is reduced, the device is convenient to store, when the device is used, the ventral fin of an airplane is clamped into the inner side of the tray 11, then a pin shaft is inserted into the two through holes, after the rotational degree of freedom of aircraft ventral fin restriction bracket 11, rotatable nut two 8 makes two 8 of nuts remove in pole setting 17, and two 8 of nuts remove accessible barrel two 9 on pole setting 17 and drive regulation pole 12 and reciprocate in slot 7 of pole setting 17 to make tray 11 be located suitable height, and can be according to tray 11's height, rotate the size that 4 branch 2 expanded is adjusted to nut 6, ensure the utility model discloses a stability.
It will be appreciated by those skilled in the art that the above embodiments are only for illustrating the present invention and are not to be used as limitations of the present invention, and that changes and modifications to the above described embodiments will fall within the scope of the claims of the present invention as long as they are within the spirit and scope of the present invention.
Claims (5)
1. The utility model provides an aircraft ventral fin supports frock, includes tray (11), tray (11) are the U type, and tray (11) both sides all are equipped with through-hole (111), its characterized in that still includes altitude mixture control spare, stabilizer blade adjusting part and pole setting (17), the top of pole setting (17) is provided with slot (7), be provided with external screw thread two (14) on the pole setting (17) lateral wall in the slot (7) outside, pole setting (17) lateral wall below external screw thread two (14) is provided with external screw thread one (5), the stabilizer blade adjusting part sets up in the bottom of pole setting (17), the stabilizer blade adjusting part includes articulated ring (15), barrel (4), pole setting (17), bearing (3), branch (2), connecting rod (16) and universal wheel (1), nut (6) set up the outside of external screw thread one (5), barrel (4) welding is in the bottom of nut (6), the hinge ring (15) is arranged on a vertical rod (17) below the outer thread I (5) in a sliding mode, one end, far away from the nut I (6), of the barrel I (4) is connected with the top of the hinge ring (15) through a bearing I (3), 4 supporting rods (2) are evenly hinged to the bottom of the hinge ring (15) along the circumferential direction, a universal wheel (1) is arranged at one end, far away from the vertical rod (17), of each supporting rod (2), a connecting rod (16) is hinged to one side, close to the vertical rod (17), of each supporting rod (2), one end, far away from the supporting rods (2), of each connecting rod (16) is hinged to the bottom end of the vertical rod (17), the height adjusting piece is arranged at the top end of the vertical rod (17) and comprises an adjusting rod (12), a limiting ring (10), a nut II (8), a barrel II (9) and a bearing II (13), the adjusting rod (, and the one end of adjusting pole (12) extends to top fixedly connected with tray (11) of pole setting (17), spacing ring (10) set up on pole setting (12) lateral wall above pole setting (17), nut two (8) set up the outside at external thread two (14), barrel two (9) welding is at the top of nut two (8), the one end that nut two (8) were kept away from in barrel two (9) is passed through bearing two (13) and is connected with spacing ring (10).
2. The aircraft ventral fin support tool according to claim 1, wherein the first nut (6) and the first external thread (5) are matched with each other, and the radius of the first nut (6) is equal to that of the first cylinder (4).
3. The aircraft ventral fin support tool according to claim 1, wherein the second nut (8) and the second external thread (14) are matched with each other, and the radius of the second nut (8) is equal to that of the second cylinder (9).
4. The aircraft ventral fin support tool according to claim 1, wherein 4 pull rods are arranged on the outer sides of the second nut (8) and the first nut (6) at equal intervals.
5. The aircraft ventral fin support tool according to claim 1, wherein a brake pad is arranged on the universal wheel (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920418036.XU CN210133301U (en) | 2019-03-29 | 2019-03-29 | Aircraft ventral fin supports frock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920418036.XU CN210133301U (en) | 2019-03-29 | 2019-03-29 | Aircraft ventral fin supports frock |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210133301U true CN210133301U (en) | 2020-03-10 |
Family
ID=69702992
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920418036.XU Expired - Fee Related CN210133301U (en) | 2019-03-29 | 2019-03-29 | Aircraft ventral fin supports frock |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210133301U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112078820A (en) * | 2020-09-04 | 2020-12-15 | 江西昌河航空工业有限公司 | Adjustable supporting device of small airplane assembly tool and pose adjusting method |
| CN112407319A (en) * | 2020-12-15 | 2021-02-26 | 芜湖中科飞机制造有限公司 | Tail support frame of small-size training machine |
-
2019
- 2019-03-29 CN CN201920418036.XU patent/CN210133301U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112078820A (en) * | 2020-09-04 | 2020-12-15 | 江西昌河航空工业有限公司 | Adjustable supporting device of small airplane assembly tool and pose adjusting method |
| CN112407319A (en) * | 2020-12-15 | 2021-02-26 | 芜湖中科飞机制造有限公司 | Tail support frame of small-size training machine |
| CN112407319B (en) * | 2020-12-15 | 2023-08-18 | 芜湖中科飞机制造有限公司 | Tail support frame of small training machine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200310 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |