CN109367787A - A kind of synchronization provision for disengagement of vertical shaft type Airplane suspension beam - Google Patents
A kind of synchronization provision for disengagement of vertical shaft type Airplane suspension beam Download PDFInfo
- Publication number
- CN109367787A CN109367787A CN201811205743.7A CN201811205743A CN109367787A CN 109367787 A CN109367787 A CN 109367787A CN 201811205743 A CN201811205743 A CN 201811205743A CN 109367787 A CN109367787 A CN 109367787A
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- China
- Prior art keywords
- connector
- vertical shaft
- disengagement
- top connection
- suspension beam
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
The present invention relates to a kind of provision for disengagement of Airplane suspension beam, the synchronization provision for disengagement of especially a kind of Airplane suspension beam belongs to airplane design technical field.A kind of synchronization provision for disengagement of vertical shaft type Airplane suspension beam, the synchronous provision for disengagement includes connector and mechanism member；Connector includes strut, hand operating parts；Mechanism member includes: threaded rod, left connector, right connector, connecting rod, top connection and lower contact；Described mechanism member at least two.The present invention has the advantage that 1, reduce damage to aircraft.2, clamping stagnation is solved the problems, such as.3, it is common to the drop in beam of different vertical shaft spacing.4, mechanism efficiency is improved.5, structure more simplifies.6, practicability is stronger, application easy to spread.
Description
Technical field
The present invention relates to a kind of provision for disengagement of Airplane suspension beam, the synchronization provision for disengagement of especially a kind of Airplane suspension beam belongs to
In airplane design technical field.
Background technique
The plug-in ability of weapon is aircraft important indicator, how plug-in in order to realize, it will usually store mounting point be arranged on wing, lead to
Drop in beam is crossed to be connected with wing.In order to which structure is simple and lightweight construction, frequently with vertical shaft type drop in beam, as shown in Figure 1, preceding vertical shaft
35, rear vertical shaft 36 is connect with the connector on wing 37, but often be will appear in the disassembly process of this drop in beam and be difficult to dismantle, strikes wound
The problems such as wing cover.In daily maintenance, ground crew, which needs to stand, is little by little connect vertical shaft from preceding vertical shaft with hammer on wing
First 29, it is knocked out on rear vertical shaft connector 30, after knocking out one of vertical shaft, since weight effect drop in beam 38 can be with the formation of wing 37
Inclination angle causes another vertical shaft to be more difficult to dismantle.
Summary of the invention
Present invention aim to address problems of the prior art, and forward and backward vertical shaft disassembly can be guaranteed by providing one kind
Synchronization, easily, and additional disassembly external force is not generated to aircraft, reduces disassembly to the vertical shaft type aircraft of aircraft structural damage
The synchronization provision for disengagement of drop in beam.
To achieve the goals above, the present invention adopts the following technical scheme: a kind of synchronous disassembly of vertical shaft type Airplane suspension beam
Device, the synchronous provision for disengagement includes connector and mechanism member；Connector includes strut, hand operating parts；Mechanism member includes: spiral shell
Rasp bar, left connector, right connector, connecting rod, top connection and lower contact；One end of threaded rod is connect with hand operating parts, and is grasped in hand
It is rotated under the drive of workpiece；Left connector, right connector are bolted in the left and right of threaded rod and left connector, right connector threaded hole direction respectively
On the contrary；Connecting rod includes four, is respectively used to connect left connector and top connection, lower contact, right connector and top connection, lower contact；
One end of top connection is slidably connected with strut, and the other end is provided with through-hole, and through slot is provided in top connection along its length,
Threaded rod passes through through slot, and left connector, right connector are located at the left and right sides of top connection；It is provided in lower contact and is matched with through-hole
Mandril, mandril is pierced by through-hole and realized and the limit of top connection by nut；Described mechanism member at least two.
Preferably, the quantity of the mechanism member is 2, including preceding mechanism and rear mechanism, is connected by hand operating parts.
Preferably, the mechanism member further includes rocker arm, rocking bar；One end of rocker arm and one end of threaded rod are clamped, the other end
It is connect with one end of rocking bar；Rocking bar is linked together by hand operating parts.
Further, rocker arm is in " I " fonts, and one end is provided with the card hole with the pocket matches of screw thread boom end, the other end
It is provided with the mounting hole for accommodating rocking bar end.
Further, the angle that rocker arm and rocking bar are formed is 90 °.
Preferably, the hand operating parts is sleeve, and the other end of rocking bar is inserted into the centre bore of sleeve.
Preferably, the strut is i-shaped beams.
Preferably, it is provided with hinge in the two sides of left connector, right connector, top connection, lower contact, connecting rod passes through hinge
It is attached thereto.
Compared with the prior art, the invention has the following advantages:
1, for the device when extruding vertical shaft, the pulling force of the pressure and socket of pressing vertical shaft is the internal force mutually balanced, will not be to winged
Machine generates additional disassembly load, reduces because external force dismantles the damage to aircraft.
2, the device utilizes sleeve, rotates synchronously front and back rocking bar, threaded rod revolving speed is identical, makes the ejection speed phase of vertical shaft
Together, the synchronous disassembly of front and back vertical shaft is realized, the disassembly of effective solution vertical shaft type Airplane suspension beam is asynchronous to lead to vertical shaft and connector clamping stagnation
The problem of.
3, the through-hole that strut passes through top connection in the device connects preceding mechanism, rear mechanism, and connector can be in strut
Upper sliding allows the device to be common to the drop in beam of different vertical shaft spacing so as to adjust the relative position of preceding mechanism, rear mechanism.
4, screw thread is reversed before and after device screw rod, and two sides generate pulling force realization internal force balance when rotation, and improve
Mechanism efficiency.
5, the device using screw rod and rocker arm these effort-saving mechanisms only need manual operation can provide one it is biggish
Active force completes the disassembly of vertical shaft, it is not necessary to increase other attachment devices, simplify structure more.
6, the apparatus structure is simple, and clear principle is easy to produce, and practicability is stronger, application easy to spread, has biggish
Value.
Detailed description of the invention
Fig. 1 is background of invention attached drawing；
Fig. 2 is structural representation of embodiment of the present invention Fig. 1；
Fig. 3 is structural representation of embodiment of the present invention Fig. 2；
Fig. 4 is preceding thread bar in the embodiment of the present invention, rear thread rod structure schematic diagram；
Fig. 5 is front left connector in the embodiment of the present invention, rear left connector, preceding right connector, rear right connector structural schematic diagram；
Fig. 6 is preceding lower contact in the embodiment of the present invention, rear lower contact structural schematic diagram；
Fig. 7 is preceding top connection in the embodiment of the present invention, rear top connection structural schematic diagram；
Fig. 8 is that the embodiment of the present invention with vertical shaft type Airplane suspension beam connect cross-sectional view；
Fig. 9 is working state schematic representation of the embodiment of the present invention；
In Fig. 2-9,1, preceding thread bar；2, front left connector；3, preceding right connector；4, front left upper boom；5, front left lower beam；6, in front right
Bar；7, front right lower beam；8, preceding top connection；9, preceding lower contact；10, preceding top connection bolt；11, preceding top connection nut；12, preceding to shake
Arm；13, preceding rocking bar；14, rear thread bar；15, rear left connector；16, rear right connector；17, rear left upper boom；18, rear left lower beam；19,
Upper right bar afterwards；20, rear bottom right bar；21, rear top connection；22, rear lower contact；23, rear top connection bolt；24, rear top connection nut；
25, rear arm；26, rear rocking bar；27, sleeve；28, strut；29, preceding vertical shaft connector；30, rear vertical shaft connector；31, it is served as a contrast on preceding vertical shaft
Set；32, rear vertical shaft upper bushing；33, bushing under preceding vertical shaft；34, bushing under rear vertical shaft；35, preceding vertical shaft；36, rear vertical shaft；37, machine
The wing；38, drop in beam.
Specific embodiment
It should be noted that the noun of locality " above and below front and back " in the present embodiment is described according to shown in attached drawing, no
It is construed as limiting the invention.
2-9 is further described the present invention with reference to the accompanying drawing: as shown in Figure 2,3, a kind of vertical shaft type Airplane suspension beam
Synchronous provision for disengagement, including preceding mechanism: preceding thread bar 1, front left connector 2, preceding right connector 3, front left upper boom 4, front left lower beam 5, preceding
Upper right bar 6, front right lower beam 7, preceding top connection 8, preceding lower contact 9, preceding top connection bolt 10, preceding top connection nut 11, front arm 12,
Preceding rocking bar 13；Mechanism afterwards: rear thread bar 14, rear left connector 15, rear right connector 16, rear left upper boom 17, rear left lower beam 18, rear upper right
Bar 19, rear bottom right bar 20, rear top connection 21, rear lower contact 22, rear top connection bolt 23, rear top connection nut 24, rear arm 25,
Rocking bar 26 afterwards；Connector: sleeve 27, strut 28.
As shown in figure 4, be provided with screw thread on preceding thread bar 1, rear thread bar 14, and hand of spiral is on the contrary, be used for and front left
Connector 2, preceding right connector 3, rear left connector 15, rear right connector 16 are spirally connected, and are respectively provided in one end of preceding thread bar 1, rear thread bar 14
There is card slot.
Front left connector 2, preceding right connector 3, rear left connector 15, rear right connector 16 structure as shown in figure 5, center is provided with
Threaded hole, is respectively used to be spirally connected with preceding thread bar 1, rear thread bar 14, and mounting hole is distributed in the surrounding of threaded hole, for it is preceding
Upper left bar 4, front left lower beam 5, front right upper boom 6, front right lower beam are hinged, or for rear left upper boom 17, rear left lower beam 18, after
Upper right bar 19, rear bottom right bar 20 are hinged.
The structure of preceding lower contact 9 and rear lower contact 22 is as shown in fig. 6, T-shaped, including two parts: horizontal component with
Front left connector 2, preceding right connector 3, rear left connector 15, the structure of rear right connector 16 are identical, and vertical portion is across center screw thread
The bolt in hole, it may be assumed that preceding top connection bolt 10, rear top connection bolt 23.
The structure of preceding top connection 8 and rear top connection 21 as shown in fig. 7, upper end is provided with aperture is slidably connected with strut, with
Just the relative position of preceding mechanism, rear mechanism is adjusted, upper, middle, and lower part along its length is provided with through slot, and lower end is set
Be equipped with threaded hole, be pierced by threaded hole for preceding top connection bolt 10, rear top connection bolt 23, by preceding top connection nut 11, after
Top connection nut 24 is fixed respectively therewith.
In preceding mechanism, preceding thread bar 1 is spirally connected by screw thread with front left connector 2, preceding right connector 3, wherein the end of one end
It is connect by card slot with front arm 12,12 other end of front arm is connect by mounting hole with preceding rocking bar 13, preceding 13 other end of rocking bar
It is inserted in the through-hole of sleeve 27；Front left connector 2 is connect by bolt with the hinge of front left upper boom 4,5 side of front left lower beam, front left
4 other end of upper boom is connect by bolt with the hinge of preceding 8 side of top connection, and 5 other end of front left lower beam is connect by bolt with front lower
The hinge of first 9 side connects, and preceding right connector 3 is connect by bolt with the hinge of front right upper boom 6,7 side of front right lower beam, in front right
6 other end of bar is connect by bolt with the hinge of preceding 8 other side of top connection, and 7 other end of front right lower beam is connect by bolt with front lower
The hinge of first 9 other side connects；Preceding 8 lower end of top connection is connect by screw thread with preceding top connection bolt 10, preceding top connection bolt 10
Realized by the connection of preceding top connection nut 11 fixed with preceding top connection 8 in lower end.
Mechanism structure is identical as preceding mechanism afterwards, both: rear screw rod 14 is connected by screw thread and rear left connector 15, rear right connector 16
It connects, wherein one end end is clamped by card slot and rear arm 25, and 25 other end of rear arm is connected by logical mounting hole and rear rocking bar 26
It connects, rear 26 other end of rocking bar is inserted in the through-hole of sleeve 27；Rear left connector 15 passes through bolt and rear left upper boom 17, rear left lower beam 18
The hinge of side connects, and 17 other end of rear left upper boom is connect by bolt with the hinge of rear 21 side of top connection, rear left lower beam 18
The other end is connect by bolt with the hinge of rear 22 side of lower contact；Right connector 16 passes through bolt and rear upper right bar 19, the rear right side afterwards
The hinge of 20 side of lower beam connects, and rear 19 other end of upper right bar is connect by bolt with the hinge of rear 21 other side of top connection, after
Bar 20 other end in bottom right is connect by bolt with the hinge of rear 22 other side of lower contact；21 lower end of top connection is by screw thread with after afterwards
Top connection bolt 23 connects, and rear 23 lower end of top connection bolt is realized solid with rear top connection 21 by the connection of rear top connection nut 24
It is fixed.
Strut 28 is the biggish i-shaped beams of rigidity, by preceding top connection 8, the aperture of 21 upper end of rear top connection, by preceding machine
Structure, rear mechanism connect, and provide support for whole device.
Front and back mechanism structure is identical, and overall structure is similar with rhombic lifting jack.
As Figure 8-9, preceding top connection nut 11 has screw thread to connect with preceding vertical shaft upper bushing 31 in inside below, rear top connection
Inside has screw thread to connect with rear vertical shaft upper bushing 32 to nut 23 below, and preceding lower contact 9 and rear lower contact 22 have mandril extruding below
Vertical shaft upper surface, during extruding vertical shaft, vertical shaft 35 before the pressure that preceding lower contact 9 generates is passed to by mandril, under rear
The pressure that connector 22 generates passes to rear vertical shaft 36 by mandril, and the pulling force that preceding top connection generates is passed by preceding top connection bolt 10
Top connection nut 11 before passing, the pulling force that rear top connection generates pass to rear top connection nut 24 by rear top connection bolt 23,
Bushing 33, rear top connection nut 24 pass to bushing 34 under rear vertical shaft, preceding vertical shaft under vertical shaft before preceding top connection nut 11 passes to
Bushing 34 is delivered separately to vertical shaft connector under lower bushing 33 and rear vertical shaft.Whole process pulling force is the interior of a pair of of balance with pressure
Power will not generate additional additional load (such as striking with a hammer, tapping load will act directly on aircraft) to aircraft in this way, subtract
The damage dismounted to aircaft configuration is lacked.
Preceding rocking bar 13, rear rocking bar 26 are connected by sleeve 27, are had through-hole among sleeve 27, can be slided on rocking bar, from
And adjust the distance of front and back mechanism.Sleeve 27 drives preceding rocking bar 13, rear rocking bar 26 to rotate, and revolving speed is identical, therefore preceding thread
Bar, rear thread bar revolving speed be also it is identical, preceding mechanism, rear mechanism extrude vertical shaft speed distance be also it is identical, thus
It can guarantee the synchronous disassembly of front and back vertical shaft, effectively avoid the feelings that front and back vertical shaft dismantles asynchronous caused vertical shaft and connector clamping stagnation
Condition.
Above-described embodiment is only the preferred embodiment of the present invention, is not construed as limiting the invention, and this field is common
Any amplification, the deformation that technical staff is done on this basis, are within the scope of the invention.
Claims (8)
1. a kind of synchronization provision for disengagement of vertical shaft type Airplane suspension beam, it is characterised in that: the synchronous provision for disengagement includes connector
And mechanism member；Connector includes strut, hand operating parts；Mechanism member include: threaded rod, left connector, right connector, connecting rod, on connect
Head and lower contact；One end of threaded rod is connect with hand operating parts, and is rotated under the drive of hand operating parts；Left connector, right connector
It is bolted in the left and right of threaded rod respectively and left connector, right connector threaded hole are contrary；Connecting rod includes four, the company of being respectively used to
Connect left connector and top connection, lower contact, right connector and top connection, lower contact；One end of top connection is slidably connected with strut, another
End is provided with through-hole, and through slot is provided in top connection along its length, and threaded rod passes through through slot, left connector, right connector point
Not Wei Yu top connection the left and right sides；It is provided in lower contact and is pierced by through-hole with the matched mandril of through-hole, mandril and passes through nut
Realize the limit with top connection；Described mechanism member at least two.
2. the synchronization provision for disengagement of vertical shaft type Airplane suspension beam according to claim 1, it is characterised in that: the mechanism member
Quantity is 2, including preceding mechanism and rear mechanism, is connected by hand operating parts.
3. the synchronization provision for disengagement of vertical shaft type Airplane suspension beam according to claim 2, it is characterised in that: the mechanism member is also
Including rocker arm, rocking bar；One end of rocker arm and one end of threaded rod are clamped, and one end of the other end and rocking bar connects；Rocking bar passes through hand
Operating parts links together.
4. the synchronization provision for disengagement of vertical shaft type Airplane suspension beam according to claim 3, it is characterised in that: rocker arm is in " work " word
Type, one end are provided with the card hole with the pocket matches of screw thread boom end, and the other end is provided with the mounting hole for accommodating rocking bar end.
5. the synchronization provision for disengagement of vertical shaft type Airplane suspension beam according to claim 3 or 4, it is characterised in that: rocker arm with shake
The angle that bar is formed is 90 °.
6. the synchronization provision for disengagement of vertical shaft type Airplane suspension beam according to claim 1, it is characterised in that: the hand operating parts
The other end for sleeve, rocking bar is inserted into the centre bore of sleeve.
7. the synchronization provision for disengagement of vertical shaft type Airplane suspension beam according to claim 1, it is characterised in that: the strut is work
Font beam.
8. the synchronization provision for disengagement of vertical shaft type Airplane suspension beam according to claim 1 or claim 7, it is characterised in that: left connector,
Right connector, top connection, lower contact two sides be provided with hinge, connecting rod is attached thereto by hinge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811205743.7A CN109367787B (en) | 2018-10-17 | 2018-10-17 | Synchronous dismounting device of vertical shaft type aircraft hanging beam |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811205743.7A CN109367787B (en) | 2018-10-17 | 2018-10-17 | Synchronous dismounting device of vertical shaft type aircraft hanging beam |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109367787A true CN109367787A (en) | 2019-02-22 |
| CN109367787B CN109367787B (en) | 2021-12-28 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811205743.7A Active CN109367787B (en) | 2018-10-17 | 2018-10-17 | Synchronous dismounting device of vertical shaft type aircraft hanging beam |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109367787B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109808893A (en) * | 2019-04-11 | 2019-05-28 | 北京航空航天大学 | A kind of aerial recycling of link-type hangs and takes device |
| CN115741522A (en) * | 2022-11-15 | 2023-03-07 | 江西洪都航空工业集团有限责任公司 | Universal vertical shaft type airplane hanging beam clamp |
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| CN102442435A (en) * | 2011-11-04 | 2012-05-09 | 哈尔滨飞机工业集团有限责任公司 | Aeronautic nacelle hanger with retracting guide function |
| CN103995542A (en) * | 2014-05-04 | 2014-08-20 | 江苏大学 | Level adjusting device and method thereof |
| CN104443429A (en) * | 2014-12-06 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Suspended beam type clamping plate structure for central position of movable component of airfoil |
| CN204507278U (en) * | 2014-12-24 | 2015-07-29 | 四川航泰航空装备有限公司 | The general hanging equipment of a kind of aircraft |
| CN205080880U (en) * | 2015-10-15 | 2016-03-09 | 武新洋 | Foldable adjustable and tensioning panel support frame |
| CN207843330U (en) * | 2017-05-23 | 2018-09-11 | 南京工业职业技术学院 | Aircraft back store Combinations support device |
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Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6250195B1 (en) * | 1999-11-09 | 2001-06-26 | Northrop Grumman Corporation | Compact universal ejection/rail launching system |
| CN102442435A (en) * | 2011-11-04 | 2012-05-09 | 哈尔滨飞机工业集团有限责任公司 | Aeronautic nacelle hanger with retracting guide function |
| CN103995542A (en) * | 2014-05-04 | 2014-08-20 | 江苏大学 | Level adjusting device and method thereof |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109808893A (en) * | 2019-04-11 | 2019-05-28 | 北京航空航天大学 | A kind of aerial recycling of link-type hangs and takes device |
| CN115741522A (en) * | 2022-11-15 | 2023-03-07 | 江西洪都航空工业集团有限责任公司 | Universal vertical shaft type airplane hanging beam clamp |
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| Publication number | Publication date |
|---|---|
| CN109367787B (en) | 2021-12-28 |
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