CN102060100B - Aircraft fuselage-wing connecting mechanism - Google Patents
Aircraft fuselage-wing connecting mechanism Download PDFInfo
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- CN102060100B CN102060100B CN 201010586694 CN201010586694A CN102060100B CN 102060100 B CN102060100 B CN 102060100B CN 201010586694 CN201010586694 CN 201010586694 CN 201010586694 A CN201010586694 A CN 201010586694A CN 102060100 B CN102060100 B CN 102060100B
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Abstract
The invention provides an aircraft fuselage-wing connecting mechanism, comprising a pin joint device (100) and a loading and unloading jack (200), wherein the pin joint device (100) comprises a circular pin drum (101) and a dowel (102) which are opposite and parallel; the circular pin drum (101) is connected with a wing (801) by a pin drum lug (103); the dowel (102) is arranged on a fuselage side stiffener (112) by a dowel lug (104); the loading and unloading jack (200) is composed of a loading and unloading stiffener (201) on a fuselage (802) and a spring device (202) which is arranged on the corresponding position on the wing (801); and the loading and unloading stiffener (201) and the spring device (202) are movably connected by a ring-pull frame (301). In the aircraft fuselage-wing connecting mechanism, the structure of the connector joint is simplified, the weight of the connector joint is reduced, and the assembly working strengthen and time at the time of connecting aircraft parts are lowered.
Description
Technical field
The present invention relates to a kind of bindiny mechanism of aircraft fuselage-wing, belong to the aircraft components field.
Background technology
Between the large parts of existing aircraft such as fuselage, wing, interconnect joint and mostly be bolt-auricle joint connection.This traditional link form structure is complicated, and weight is large, work capacity is large when assembling or dismantling, and is inconvenient to use.Especially for the wing of monocoque, covering is main bearing member, and jointing should be multiple spot distributing joint.At this moment, this traditional bolt auricle joint just is difficult to realize at wing root covering.
Summary of the invention
The objective of the invention is:
In order to address the above problem, provide a kind of simply, the bindiny mechanism of aircraft fuselage-wing quickly and easily, to simplify the structure of jointing, alleviate the weight of jointing, finally reduce fitting work intensity and time when connecting between aircraft components.
Purpose of the present invention can be achieved through the following technical solutions:
A kind of aircraft fuselage-wing connecting mechanism, pin joint device and loading and unloading jack have been comprised, described pin joint device has comprised annulus pin cylinder and the pin that the position is corresponding and parallel, annulus pin cylinder links to each other with wing by pin cylinder ear sheet, pin is installed on the fuselage side reinforcement by the pin auricle, the loading and unloading jack is comprised of with the spring installation that is installed in the wing correspondence position the loading and unloading reinforcement that is installed on the fuselage, is flexibly connected by the draw ring frame between loading and unloading reinforcement and the spring installation.
The quantity of described pin joint device is some groups and is parallel to each other, these some groups of pin joint devices distribute and are arranged on the edge of aircraft fuselage-wing docking port, the pin joint device has comprised annulus pin cylinder and the pin that the position is corresponding and parallel, and annulus pin cylinder is horizontally disposed with along the course with pin, open up to setting or along lift direction-vertical setting on the edge.
The quantity of described loading and unloading jack is a pair, and the loading and unloading jack is arranged on the axis of aircraft fuselage-wing docking port and near peripheral.
The cross-sectional plane of described pin cylinder ear sheet is " L " type, and the vertical side of pin cylinder ear sheet is welded mutually with annulus pin cylinder; The cross side of pin cylinder ear sheet has some the first nail holes and embeds in the aviation laminate of wing, and the first rivet penetrates aviation laminate, the first nail hole and wing cover makes aviation laminate, pin cylinder ear sheet rivet mutually with wing cover.
The cross-sectional plane of described pin cylinder ear sheet is " L " type, and its cross side has the band hole and embeds in the aviation laminate of wing, and some glass fibre bands pass band hole incorporating mill wing covering and glued joint.
One side of described pin auricle is provided with key seat, and key seat and pin are affixed; The opposite side of pin auricle is offered some the second nail holes, and the second rivet penetrates the second nail hole, fuselage side reinforcement is riveted pin auricle and fuselage side reinforcement mutually.
Described loading and unloading jack is comprised of with the spring installation that is installed in the wing correspondence position the loading and unloading reinforcement that is installed on the fuselage, be flexibly connected by the draw ring frame between loading and unloading reinforcement and the spring installation, the draw ring frame is a rectangle frame, the middle part of one side vertical edge is provided with the positional punch that leads in the frame, the loading and unloading reinforcement is comprised of bottom block and screens piece, bottom block is riveted on the fuselage, vertically be fixed with the screens piece on the bottom block, the screens piece is provided with detent towards the one side of spring installation, the screens piece dorsad one side of spring installation is provided with the bayonet socket that can fasten with the draw ring frame, and bayonet socket is stuck in the middle part that draw ring frame inside casing does not have a side vertical edge of positional punch; Described spring installation has comprised positioning base, screw rod and pull back spring, the base plate of positioning base is riveted on the wing, vertically draw a locating piece on the base plate, have a through hole with negative thread in the locating piece, the hypomere of screw rod is provided with the outside thread that matches with the through hole negative thread and is screwed onto in the through hole, the epimere of screw rod penetrates in the positional punch of draw ring frame, the hypomere top of screw rod is corresponding with the detent position, the epimere top of screw rod is provided with handle, and is affixed by pull back spring between handle and the positional punch.
Beneficial effect of the present invention:
After the bindiny mechanism of aircraft fuselage-wing of the present invention adopts in groups pin joint, aircraft components assembling (dismounting) is worked become very easy, quick, greatly saved labour and time.Especially for requiring often to load and unload parts so that flight, transportation, the aviette that stores, technology of the present invention has more outstanding preceence.The bindiny mechanism of aircraft fuselage-wing of the present invention can guarantee the interchangeability of aircraft components equally.The bindiny mechanism of aircraft fuselage-wing of the present invention also goes for other mechanical equipment Rapid Combination-dismounting design except aircraft.
Description of drawings
Fig. 1 is pin joint apparatus structure scheme drawing of the present invention;
Fig. 2 is loading and unloading jack structure scheme drawing of the present invention;
Among the figure:
100, pin joint device;
101, annulus pin cylinder; 103, pin cylinder ear sheet; 105, the first nail hole; 107, the first rivet; 109, band hole; 111, glass fibre band;
102, pin; 104, pin auricle; 106, key seat; 108, the second nail hole; 110, the second rivet; 112, fuselage side reinforcement;
200, loading and unloading jack;
201, loading and unloading reinforcement; 203, bottom block; 205, screens piece; 207, detent; 209, bayonet socket
202, spring installation; 204, positioning base; 206, base plate; 208, locating piece; 210, through hole; 212, screw rod; 214, pull back spring; 216, handle
301, draw ring frame; 302, positional punch
801, wing; 803, aviation laminate; 805, wing cover;
802, fuselage
The specific embodiment
The present invention is further illustrated below in conjunction with accompanying drawing and example.
The invention provides a kind of aircraft fuselage-wing connecting mechanism, comprised pin joint device 100 and loading and unloading jack 200.Pin joint device 100 is used for engaging airframe and wing, and loading and unloading jack 200 helps the top to disembark body and wing so that dismounting.
In the aircraft fuselage-wing connecting mechanism of the present invention, comprised that some groups of pin joint devices 100 and its are parallel to each other, some groups of corresponding annulus pin cylinder 101 and pins 102 have namely been comprised, the preferred version that this annulus pin cylinder 101 and pin 102 arrange is to be horizontally disposed with along the course, but these some groups corresponding annulus pin cylinders 101 and pin 102 also can be along exhibitions to arranging or along lift direction-be arranged vertically, principle is identical.These some groups of pin joint devices 100 can distribute according to actual needs and be arranged on the edge of aircraft fuselage-wing docking port.
As shown in Figure 1, pin joint device 100 has comprised some groups of corresponding annulus pin cylinder 101 and pins 102, annulus pin cylinder 101 links to each other with wing 801 by pin cylinder ear sheet 103, pin 102 is installed on the fuselage side reinforcement 112 by pin auricle 104, loading and unloading jack 200 is comprised of with the spring installation 202 that is installed in wing 801 correspondence positions the loading and unloading reinforcement 201 that is installed on the fuselage 802, is flexibly connected by draw ring frame 301 between loading and unloading reinforcement 201 and the spring installation 202.Annulus pin cylinder 101 all is parallel with pin 102, because parallel so can guarantee when having one group of corresponding pin 102 to finish its corresponding annulus pin cylinder 101 of insertion, then each pin 102 of all groups has all inserted respectively each annulus pin cylinder 101 of its correspondence, and fuselage-wing has namely been finished connection; On the contrary, there is a pair of pin 102 from annulus pin cylinder 101, to extract (disengagement), then entirely organizes each pin 102 and just can all from the annulus pin cylinder 101 of correspondence, extract () simultaneously, namely finish separating of fuselage-wing two parts.Therefore say that aircraft fuselage-wing connecting mechanism of the present invention is easy, a fast speed link aircraft components dismounting design.The radical function of pin 102 is to bear shearing force; Shearing, moment of flexure and transfer of torque that pin 102-annulus pin cylinder 101 has in groups been finished between aircraft fuselage-wing.
The cross-sectional plane of described pin cylinder ear sheet 103 is " L " type, and the vertical side of pin cylinder ear sheet 103 is welded mutually with annulus pin cylinder 101; The cross side of pin cylinder ear sheet 103 has some the first nail holes 105 and embeds in the aviation laminate 803 of wing 801, and the first rivet 107 penetrates aviation laminate 803, the first nail hole 105 and wing cover 805 makes aviation laminate 803, pin cylinder ear sheet 103 rivet mutually with wing cover 805.The cross-sectional plane of pin cylinder ear sheet 103 is " L " type, and its cross side has band hole 109 and embeds in the aviation laminate 803 of wing 801, and some glass fibre bands 111 pass band hole 109 incorporating mill wing coverings 805 and glued joint.Pin cylinder ear sheet 103 and wing 801 also glued joint glass fibre band 111 and wing cover 805, strengthen by epoxy glue except being connected by fastener the first rivet 107, thus the transmission of exerting all one's strength with disperse more rationally, reliably.One side of pin auricle 104 is provided with key seat 106, and key seat 106 is affixed with pin 102; The opposite side of pin auricle 104 offers that some the second nail holes 108, the second rivets 110 penetrate the second nail hole 108, fuselage side reinforcement 112 is riveted pin auricle 104 and fuselage side reinforcement 112 mutually.
Because airframe 802 and 801 on wing have adopted some groups of pin joint devices 100, it is many to connect stress point, so the gross load that every pair of pin 102-annulus pin cylinder 101 joint are born than traditional beam type connect bolt-auricle jointing load is just much smaller, this is just so that the technology of the present invention can be on the monocoque wing of wing cover 805 as main stressed member, very easily successfully is able to practical application.
In order to realize that the some groups of pins 102 in the pin joint device 100 can insert (or extracting) annulus pin cylinder 101 abreast simultaneously, the present invention has designed again a secondary loading and unloading jack 200 simultaneously: when component assemble made up, the full group of loading and unloading jack 200 pullings pin 102 inserted corresponding circle battle pin cylinder 101 simultaneously; When the parts dismounting separated, it promoted again entirely to organize pin 102, extracted in the self-corresponding annulus pin cylinder 101 simultaneously.By the loading and unloading jack 200 of this special use, the present invention realize the aircraft fuselage-wing component assemble make up-working strength and work capacity when decomposing greatly reduce and simplify.The position of loading and unloading jack 200 can preferably be arranged on the axis of aircraft fuselage-wing docking port and near peripheral, in order to pin joint device 100 is accepted evenly and made things convenient for the staff to operate.
As shown in Figure 2, loading and unloading jack 200 is comprised of with the spring installation 202 that is installed in wing 801 correspondence positions the loading and unloading reinforcement 201 that is installed on the fuselage 802, is flexibly connected by draw ring frame 301 between loading and unloading reinforcement 201 and the spring installation 202.Described draw ring frame 301 is a rectangle frame, the middle part of one side vertical edge is provided with the positional punch 302 that leads in the frame, loading and unloading reinforcement 201 is comprised of bottom block 203 and screens piece 205, bottom block 203 is riveted on the fuselage 802, vertically be fixed with screens piece 205 on the bottom block 203, screens piece 205 is provided with detent 207 towards the one side of spring installation 202, the screens piece 205 dorsad one side of spring installation 202 is provided with the bayonet socket 209 that can fasten with draw ring frame 301, and bayonet socket 209 is stuck in the middle part that draw ring frame 301 inside casings do not have a side vertical edge of positional punch 302; Described spring installation 202 has comprised positioning base 204, screw rod 212 and pull back spring 214, the base plate 206 of positioning base 204 is riveted on the wing 801, vertically draw a locating piece 208 on the base plate 206, have a through hole 210 with negative thread in the locating piece 208, the hypomere of screw rod 212 is provided with the outside thread that matches with through hole 210 negative threads and is screwed onto in the through hole 210, the epimere of screw rod 212 penetrates in the positional punch 302 of draw ring frame 301, the hypomere top of screw rod 212 is corresponding with detent 207 positions, the epimere top of screw rod 212 is provided with handle 216, and is affixed by pull back spring 214 between handle 216 and the positional punch 302.Screw rod 212 can be in locating piece 208 interior rotations.When screw rod 212 is left-handed, just drives draw ring frame 301 and retreat.Draw ring frame 301 just spurs loading and unloading reinforcement 201 and retreats, thereby makes fuselage 802 and mutually close motion of wing 801.Each corresponding annulus pin cylinder 101 is inserted in all pin 102 translations simultaneously.Until pin 102 roots and annulus pin cylinder 101 ends fit, just finished combination, the assembling of fuselage 802 with 801 liang of parts of wing.When screw rod 212 dextrorotation, the end of screw rod 212 is pushing tow loading and unloading reinforcement 201 just, and fuselage 802 is pushed away wing 801.Whole fuselage 802 is just along pin 102 axis direction translations, and all pin 102 is all thrown off annulus pin cylinder 101 simultaneously, and fuselage 802 has just been finished to throw off with 801 liang of parts of wing and decomposed.
The part that the present invention does not relate to all prior art that maybe can adopt same as the prior art is realized.
Claims (7)
1. aircraft fuselage-wing connecting mechanism, pin joint device (100) and loading and unloading jack (200) have been comprised, it is characterized in that annulus pin cylinder (101) and pin (102) that described pin joint device (100) has comprised that the position is corresponding and parallel, annulus pin cylinder (101) links to each other with wing (801) by pin cylinder ear sheet (103), pin (102) is installed on the fuselage side reinforcement (112) by pin auricle (104), loading and unloading jacks (200) are comprised of the spring installation (202) that is installed in the loading and unloading reinforcement (201) on the fuselage (802) and is installed in wing (801) correspondence position, pass through draw ring frame (301) flexible connection between loading and unloading reinforcement (201) and the spring installation (202).
2. aircraft fuselage-wing connecting mechanism according to claim 1, the quantity that it is characterized in that described pin joint device (100) is some groups and is parallel to each other, these some groups of pin joint devices (100) distribute and are arranged on the edge of aircraft fuselage-wing docking port, pin joint device (100) has comprised annulus pin cylinder (101) and the pin (102) that the position is corresponding and parallel, and annulus pin cylinder (101) is horizontally disposed with along the course with pin (102), open up to setting or along lift direction-vertical setting on the edge.
3. aircraft fuselage-wing connecting mechanism according to claim 1, the quantity that it is characterized in that described loading and unloading jack (200) is a pair, loading and unloading jacks (200) are arranged on the axis of aircraft fuselage-wing docking port and near peripheral.
4. aircraft fuselage-wing connecting mechanism according to claim 1 is characterized in that the cross-sectional plane of described pin cylinder ear sheet (103) is " L " type, and the vertical side of pin cylinder ear sheet (103) is welded mutually with annulus pin cylinder (101); The cross side of pin cylinder ear sheet (103) has some the first nail holes (105) and embeds in the aviation laminate (803) of wing (801), and the first rivet (107) penetrates aviation laminate (803), the first nail hole (105) and wing cover (805) makes aviation laminate (803), pin cylinder ear sheet (103) rivet mutually with wing cover (805).
5. aircraft fuselage-wing connecting mechanism according to claim 1, the cross-sectional plane that it is characterized in that described pin cylinder ear sheet (103) is " L " type, its cross side has band hole (109) and embeds in the aviation laminate (803) of wing (801), and some glass fibre bands (111) pass band hole (109) incorporating mill wing covering (805) and glued joint.
6. aircraft fuselage-wing connecting mechanism according to claim 1 is characterized in that a side of described pin auricle (104) is provided with key seat (106), and key seat (106) is affixed with pin (102); The opposite side of pin auricle (104) is offered some the second nail holes (108), and the second rivet (110) penetrates the second nail hole (108), fuselage side reinforcement (112) is riveted pin auricle (104) and fuselage side reinforcement (112) mutually.
7. aircraft fuselage-wing connecting mechanism according to claim 1, it is characterized in that described loading and unloading jack (200) is comprised of the spring installation (202) that is installed in the loading and unloading reinforcement (201) on the fuselage (802) and is installed in wing (801) correspondence position, be flexibly connected by draw ring frame (301) between loading and unloading reinforcement (201) and the spring installation (202), draw ring frame (301) is a rectangle frame, the middle part of one side vertical edge is provided with the positional punch (302) that leads in the frame, loading and unloading reinforcements (201) are comprised of bottom block (203) and screens piece (205), bottom block (203) is riveted on the fuselage (802), vertically be fixed with screens piece (205) on the bottom block (203), screens piece (205) is provided with detent (207) towards the one side of spring installation (202), screens piece (205) the dorsad one side of spring installation (202) is provided with the card (209) that can fasten with draw ring frame (301), and card (209) is stuck in the middle part that draw ring frame (301) inside casing does not have a side vertical edge of positional punch (302); Described spring installation (202) has comprised positioning base (204), screw rod (212) and pull back spring (214), the base plate (206) of positioning base (204) is riveted on the wing (801), vertically draw a locating piece (208) on the base plate (206), have a through hole (210) with negative thread in the locating piece (208), the hypomere of screw rod (212) is provided with the outside thread that matches with through hole (210) negative thread and is screwed onto in the through hole (210), the epimere of screw rod (212) penetrates in the positional punch (302) of draw ring frame (301), the hypomere top of screw rod (212) is corresponding with detent (207) position, the epimere top of screw rod (212) is provided with handle (216), and is affixed by pull back spring (214) between handle (216) and the positional punch (302).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010586694 CN102060100B (en) | 2010-12-14 | 2010-12-14 | Aircraft fuselage-wing connecting mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010586694 CN102060100B (en) | 2010-12-14 | 2010-12-14 | Aircraft fuselage-wing connecting mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102060100A CN102060100A (en) | 2011-05-18 |
| CN102060100B true CN102060100B (en) | 2013-03-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010586694 Expired - Fee Related CN102060100B (en) | 2010-12-14 | 2010-12-14 | Aircraft fuselage-wing connecting mechanism |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105217017A (en) * | 2015-08-06 | 2016-01-06 | 北京韦加航通科技有限责任公司 | A kind of unmanned plane wing mechanical electric connecting device |
| CN106043661B (en) * | 2016-06-08 | 2018-08-24 | 江西洪都航空工业集团有限责任公司 | A kind of artificial rapid abutting joint method of fuselage wing |
| CN108639308A (en) * | 2018-05-11 | 2018-10-12 | 南京航天猎鹰飞行器技术有限公司 | A kind of wing mechanism for assembling-disassembling for Fixed Wing AirVehicle |
| CN108750070A (en) * | 2018-06-04 | 2018-11-06 | 顺丰科技有限公司 | Locking device and wing body connection structure |
| CN113401329B (en) * | 2020-03-16 | 2023-03-14 | 海鹰航空通用装备有限责任公司 | Unmanned aerial vehicle wing quick assembly disassembly mechanism and have its unmanned aerial vehicle |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1073406A (en) * | 1991-12-14 | 1993-06-23 | 谭喜德 | Small-sized wing aircraft without the airport |
| EP0888201B1 (en) * | 1996-03-22 | 2006-05-31 | The Boeing Company | Determinant spar assembly |
| US7134649B2 (en) * | 2004-05-27 | 2006-11-14 | The Boeing Company | Conformal vacuum cup apparatus and method |
| CN100429119C (en) * | 2007-03-30 | 2008-10-29 | 哈尔滨工业大学 | Aircraft with wing sweepback angle change |
| CN202038449U (en) * | 2010-12-14 | 2011-11-16 | 上海智晟航空科技有限公司 | Plane body-wing connecting mechanism for plane |
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| CN102060100A (en) | 2011-05-18 |
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