CN104316280B - The rolling of the plug-in auxiliary fuel tank of aircraft is shaken test fixture - Google Patents
The rolling of the plug-in auxiliary fuel tank of aircraft is shaken test fixture Download PDFInfo
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- CN104316280B CN104316280B CN201310683373.9A CN201310683373A CN104316280B CN 104316280 B CN104316280 B CN 104316280B CN 201310683373 A CN201310683373 A CN 201310683373A CN 104316280 B CN104316280 B CN 104316280B
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- suspension hook
- section steel
- fuel tank
- scotch
- stop
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Abstract
The invention belongs to environmental test technology, relate to the rolling of the plug-in auxiliary fuel tank of aircraft and shake test fixture.It is characterized in that: it is made up of longeron (1), two fuel tank stop blocks (2), two suspension hook unit (3) and two suspension hook stop blocks (4).The present invention propose a kind of for the plug-in auxiliary fuel tank of aircraft shake shake test fixture, it is ensured that this plug-in auxiliary fuel tank of type aircraft shake shake test be normally carried out.
Description
Technical field
The invention belongs to environmental test technology, relate to the rolling of the plug-in auxiliary fuel tank of aircraft and shake test fixture.
Background technology
The upper surface front and rear of the plug-in auxiliary fuel tank of aircraft wing is respectively arranged with hanger, mounts aircraft machine
Time on the wing, the front hanger front suspension hook on wing is combined, and rear hanger rear hanger on wing is combined.?
The wing retainer that on wing, restricted auxiliary fuel tank rocks.This type aircraft requirements auxiliary fuel tank plug-in to wing enters
Row rolling is shaken test, does not retrieves the most relevant plug-in auxiliary fuel tank of wing and carries out shaking the test clamp that shakes
Open source literature.
Summary of the invention
It is an object of the invention to: propose the folder of a kind of test of shaking for the rolling of aircraft wing plug-in auxiliary fuel tank
Tool, in order to ensure this plug-in auxiliary fuel tank of type aircraft wing shake shake test be normally carried out.
The technical scheme is that the rolling of the plug-in auxiliary fuel tank of aircraft is shaken test fixture, its feature exists
In: it is by longeron 2, two suspension hook unit 3 of 1, two fuel tank stop blocks and two suspension hook stop blocks
4 compositions；Two fuel tank stop blocks 2 are positioned at the two ends of longeron 1, and two suspension hook unit 3 are positioned at two oil
Between case stop block 2, two suspension hook stop blocks 4 between two suspension hook unit 3, two oil
2, two suspension hook unit 3 of case stop block and two suspension hook stop block 4 opposing side rails 1 vertical in point
Line is symmetrical；Longeron 1 is made up of right channel-section steel 1a, left channel-section steel 1b, two cushion block 1c and connecting bolt secondary 1d；
Right channel-section steel 1a is parallel with left channel-section steel 1b, and their bottom land outer surface is relative, and two cushion block 1c are positioned at longeron
Between the two ends of 1, right channel-section steel 1a and the bottom land of left channel-section steel 1b, by connecting bolt adjutant right channel-section steel 1a,
Cushion block 1c and left channel-section steel 1b is connected as entirety, and longeron 1 upper surface has two row's bolt through-holes that interval is equal
1e；Fuel tank stop block 2 by crossbeam 2a, two scotch 2b, two band movable ram bolt 2c and
Two locking nut 2d compositions；Crossbeam 2a and longeron 1 vertical welding be entirety, by a scotch 2b,
An one band movable ram bolt 2c and locking nut 2d forms a stop assembly, and scotch 2b is
One cuboid being welded on crossbeam 2a one end, has the screwed hole of a up/down perforation on scotch 2b,
Band movable ram bolt 2c is screwed in above-mentioned screwed hole, by locking nut 2d by band movable ram bolt
2c locks, and two stop assemblies are positioned at the two ends of crossbeam 2a, band movable ram bolt in two stop assemblies
The angle α of the axis of 2c hangs the stop angles of wing retainer after on wing equal to plug-in auxiliary fuel tank；
Suspension hook unit 3 is made up of suspension hook 3a, suspension hook axle 3b and split pin 3c, and suspension hook 3a is positioned at right channel-section steel 1a
And between the bottom land of left channel-section steel 1b, one end of suspension hook axle 3b with convex shoulder, the other end with cotter-pin hold,
Suspension hook axle 3b is through in the axis hole of suspension hook 3a, and the two ends of suspension hook axle 3b are through right channel-section steel 1a and a left side respectively
In suspension hook axis hole on channel-section steel 1b bottom land, by split pin 3c by suspension hook axle 3b with the one of cotter-pin hold
End location；Suspension hook stop block 4 is by suspension hook scotch 4a, suspension hook scotch connecting bolt secondary 4b, stop
Bolt 4c and dogbolt locking nut 4d composition；Suspension hook scotch 4a is a cuboid, by hanging
Suspension hook scotch 4a is fixed on the lower surface of longeron 1, at suspension hook by hook scotch connecting bolt secondary 4b
Having the screwed hole of a through front and rear surfaces on scotch connecting bolt secondary 4b, dogbolt 4c is threaded on
State in screwed hole, by dogbolt locking nut 4d, dogbolt 4c is locked.
The invention have the advantage that propose a kind of for the plug-in auxiliary fuel tank of aircraft wing shake shake test
Fixture, it is ensured that this plug-in auxiliary fuel tank of type aircraft wing shake shake test be normally carried out.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention.In figure, left is front, and right is rear, direction in paper
For right, the outer direction of paper is left, and above-below direction is constant.
Fig. 2 is the top view of longeron 1 in the present invention.
Fig. 3 is the A-A sectional view of Fig. 1.
Fig. 4 is the B-B sectional view of Fig. 1.
Detailed description of the invention
Below the present invention is described in further details.See Fig. 1 to Fig. 4, the plug-in auxiliary fuel tank of aircraft
Rolling shake test fixture, it is characterised in that: it is by longeron 2, two suspension hooks of 1, two fuel tank stop blocks
Unit 3 and two suspension hook stop blocks 4 form；Two fuel tank stop blocks 2 are positioned at the two ends of longeron 1,
Two suspension hook unit 3 are between two fuel tank stop blocks 2, and two suspension hook stop blocks 4 are positioned at two
Between individual suspension hook unit 3,2, two suspension hook unit 3 of two fuel tank stop blocks and two suspension hook stop lists
The vertical middle separated time of unit's 4 opposing side rails 1 is symmetrical；Longeron 1 is by right channel-section steel 1a, left channel-section steel 1b, two pads
Block 1c and connecting bolt secondary 1d composition；Right channel-section steel 1a is parallel with left channel-section steel 1b, their bottom land appearance
Face is relative, two cushion block 1c between the two ends of longeron 1, right channel-section steel 1a and the bottom land of left channel-section steel 1b,
It is connected as entirety, table on longeron 1 by connecting bolt adjutant right channel-section steel 1a, cushion block 1c and left channel-section steel 1b
There are the two row bolt through-hole 1e that interval is equal in face；Fuel tank stop block 2 by crossbeam 2a, two scotch 2b,
Two band movable ram bolt 2c and two locking nut 2d compositions；Crossbeam 2a and longeron 1 vertical welding
For entirety, it is made up of a scotch 2b, an a band movable ram bolt 2c and locking nut 2d
One stop assembly, scotch 2b is a cuboid being welded on crossbeam 2a one end, at scotch 2b
On have the screwed hole of a up/down perforation, band movable ram bolt 2c is screwed in above-mentioned screwed hole, by lock
Band movable ram bolt 2c is locked by jack panel 2d, and two stop assemblies are positioned at the two ends of crossbeam 2a, and two
In individual stop assembly, the angle α of the axis of band movable ram bolt 2c hangs wing equal to plug-in auxiliary fuel tank
The stop angles of wing retainer after upper；Suspension hook unit 3 is by suspension hook 3a, suspension hook axle 3b and split pin 3c
Composition, suspension hook 3a between the bottom land of right channel-section steel 1a and left channel-section steel 1b, one end band of suspension hook axle 3b
Having convex shoulder, the other end is through in the axis hole of suspension hook 3a with cotter-pin hold, suspension hook axle 3b, suspension hook axle 3b
Two ends be through respectively in the suspension hook axis hole on right channel-section steel 1a and left channel-section steel 1b bottom land, by split pin 3c
Suspension hook axle 3b is positioned with one end of cotter-pin hold；Suspension hook stop block 4 by suspension hook scotch 4a, hang
Hook scotch connecting bolt secondary 4b, dogbolt 4c and dogbolt locking nut 4d composition；Suspension hook is only
Motion block 4a is a cuboid, is fixed by suspension hook scotch 4a by suspension hook scotch connecting bolt secondary 4b
On the lower surface of longeron 1, suspension hook scotch connecting bolt secondary 4b there is a through front and rear surfaces
Screwed hole, dogbolt 4c is screwed in above-mentioned screwed hole, by dogbolt locking nut 4d by stop
Bolt 4c locks.
The using method of the present invention is: by the bolt through-hole 1e of the upper surface of longeron 1 by longeron 1 and rolling
The testing stand that shakes connects, and two hangers of the plug-in auxiliary fuel tank of underproof aircraft are combined with suspension hook unit 3,
Two fuel tank stop blocks 2 are pressed on fuel tank, and suspension hook stop block 4 connects spiral shell by suspension hook scotch
Bolt secondary 4b holds out against at the suspension hook back side, can proceed by rolling and shake test.
One embodiment of the present of invention, has fully met the rolling of the plug-in auxiliary fuel tank of aircraft and has shaken the wanting of test
Ask.
Claims (1)
1. the rolling of the plug-in auxiliary fuel tank of aircraft is shaken test fixture, it is characterised in that: it by longeron (1),
Two fuel tank stop blocks (2), two suspension hook unit (3) and two suspension hook stop block (4) compositions；Two
Fuel tank stop block (2) is positioned at the two ends of longeron (1), and two suspension hook unit (3) are positioned at two fuel tank stop lists
Between unit (2), two suspension hook stop blocks (4) are positioned between two suspension hook unit (3), two fuel tank stop
Unit (2), two suspension hook unit (3) and two suspension hook stop blocks (4) opposing side rails (1) vertical in point
Line is symmetrical；Longeron (1) is secondary (1d) by right channel-section steel (1a), left channel-section steel (1b), two cushion blocks (1c) and connecting bolt
Composition；Right channel-section steel (1a) is parallel with left channel-section steel (1b), and their bottom land outer surface is relative, two cushion blocks (1c)
It is positioned between the two ends of longeron (1), right channel-section steel (1a) and the bottom land of left channel-section steel (1b), secondary by connecting bolt
Right channel-section steel (1a), cushion block (1c) and left channel-section steel (1b) are connected as entirety, and longeron (1) upper surface has interval phase
Deng two row's bolt through-holes (1e)；Fuel tank stop block (2) by crossbeam (2a), two scotch (2b), two
Individual band movable ram bolt (2c) and two locking nut (2d) compositions；Crossbeam (2a) and longeron (1) vertical welding
Connect as entirety, by a scotch (2b), band movable ram bolt (2c) and a locking nut (2d)
Forming a stop assembly, scotch (2b) is a cuboid being welded on crossbeam (2a) one end, only
The screwed hole of a up/down perforation, band movable ram bolt (2c) is had to be screwed in above-mentioned screwed hole on motion block (2b)
In, by locking nut (2d), band movable ram bolt (2c) to be locked, two stop assemblies are positioned at crossbeam
(2a) two ends, in two stop assemblies, the angle α of the axis of band movable ram bolt (2c) is equal to plug-in
The stop angles of wing retainer after on wing hung by auxiliary fuel tank；Suspension hook unit (3) by suspension hook (3a), hang
Hook axle (3b) and split pin (3c) composition, suspension hook (3a) is positioned at right channel-section steel (1a) and the bottom land of left channel-section steel (1b)
Between, one end of suspension hook axle (3b) is through with cotter-pin hold, suspension hook axle (3b) with convex shoulder, the other end
In the axis hole of suspension hook (3a), the two ends of suspension hook axle (3b) are through right channel-section steel (1a) and left channel-section steel (1b) groove respectively
In suspension hook axis hole at the end, by split pin (3c), suspension hook axle (3b) is positioned with one end of cotter-pin hold；
Suspension hook stop block (4) is by suspension hook scotch (4a), suspension hook scotch connecting bolt secondary (4b), dogbolt
(4c) form with dogbolt locking nut (4d)；Suspension hook scotch (4a) is a cuboid, by hanging
Suspension hook scotch (4a) is fixed on the lower surface of longeron (1) by hook scotch connecting bolt secondary (4b), is hanging
Having the screwed hole of a through front and rear surfaces on hook scotch connecting bolt secondary (4b), dogbolt (4c) is twisted
In above-mentioned screwed hole, by dogbolt locking nut (4d), dogbolt (4c) is locked.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310683373.9A CN104316280B (en) | 2014-11-17 | 2014-11-17 | The rolling of the plug-in auxiliary fuel tank of aircraft is shaken test fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310683373.9A CN104316280B (en) | 2014-11-17 | 2014-11-17 | The rolling of the plug-in auxiliary fuel tank of aircraft is shaken test fixture |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104316280A CN104316280A (en) | 2015-01-28 |
| CN104316280B true CN104316280B (en) | 2016-10-26 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310683373.9A Active CN104316280B (en) | 2014-11-17 | 2014-11-17 | The rolling of the plug-in auxiliary fuel tank of aircraft is shaken test fixture |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106840560A (en) * | 2015-12-04 | 2017-06-13 | 中航通飞研究院有限公司 | A kind of Novel fuel tank shakes pilot system of shaking |
| CN107192526B (en) * | 2016-03-15 | 2020-07-17 | 北京航天希尔测试技术有限公司 | Horizontal vibration test device capable of directly hanging test piece |
| CN107167293B (en) * | 2017-05-26 | 2023-03-17 | 西安捷盛电子技术有限责任公司 | Shaking and vibrating test equipment and shaking and vibrating test method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US4445674A (en) * | 1982-04-29 | 1984-05-01 | Clayton Jr Donald H | Shock absorber for an oil well pumping unit |
| NO334024B1 (en) * | 2008-12-02 | 2013-11-18 | Tool Tech As | Nedihull's pressure and vibration measuring device integrated in a pipe section as part of a production pipe |
| CN103659671B (en) * | 2013-12-13 | 2016-01-20 | 合肥江航飞机装备有限公司 | Fuel tank random vibration test cramp in aircraft machine |
| CN103742483B (en) * | 2013-12-20 | 2016-01-20 | 东北大学 | A kind of aeroengine hydraulic plumbing system coupled vibrations simulated experiment platform |
| CN103894953B (en) * | 2014-04-03 | 2015-11-18 | 合肥江航飞机装备有限公司 | The plug-in auxiliary fuel tank of aircraft wing shakes the test fixture that shakes |
| CN104019950B (en) * | 2014-05-20 | 2016-03-30 | 北京航空航天大学 | A kind of pilot system of testing airplane tank vibrating fatigue performance |
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| CN104316280A (en) | 2015-01-28 |
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Address after: 230051 No. 35 Yan'an Road, Baohe Industrial Zone, Hefei City, Anhui Province Patentee after: Hefei Jianghang Aircraft Equipment Co., Ltd. Address before: 230051 Anhui Province, Hefei City Industrial Park Yanan Baohe Road No. 35 Patentee before: Hefei Jianghang Aircraft Equipment Co., Ltd. |
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