CN108910013A - A kind of fast disassembly type fuselage wing attachment structure - Google Patents
A kind of fast disassembly type fuselage wing attachment structure Download PDFInfo
- Publication number
- CN108910013A CN108910013A CN201810967623.4A CN201810967623A CN108910013A CN 108910013 A CN108910013 A CN 108910013A CN 201810967623 A CN201810967623 A CN 201810967623A CN 108910013 A CN108910013 A CN 108910013A
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- Prior art keywords
- wing
- framework
- connecting plate
- fuselage
- spar
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- 238000000465 moulding Methods 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 18
- 238000003780 insertion Methods 0.000 description 5
- 230000037431 insertion Effects 0.000 description 5
- 238000012423 maintenance Methods 0.000 description 4
- 238000004026 adhesive bonding Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007937 lozenge Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
Abstract
The present invention relates to a kind of fast disassembly type fuselage wing attachment structures, detachable between fuselage body and wing-body to be fixedly connected including fuselage body and two wing-bodies for being symmetrically disposed on fuselage body two sides；Fuselage body includes fuselage framework, and fuselage framework is interior, its cross-sectional direction is provided with preceding connecting plate and rear connecting plate, and the protrusion square box of a both ends open is fixedly installed in the plate face of preceding connecting plate, two angle boxes are symmetrically set in the plate face of rear connecting plate；Wing-body includes wing components and Wedge-shape connector, and Wedge-shape connector is fixed on the end face that wing components are connect with fuselage body；Fuselage body and wing-body are designed as mutually independent component, and by being mutually inserted, are then realized and fixed with fast bolt axle, realize the Quick-dismantling structure of fuselage and wing by fuselage wing attachment structure of the invention, structurally reasonable, convenient and practical.
Description
Technical field
The invention belongs to unmanned vehicle technical fields, and in particular to a kind of fast disassembly type fuselage wing attachment structure.
Background technique
Unmanned vehicle be using electrical remote control equipment and provide for oneself presetting apparatus manipulation unmanned aerial vehicle, fixed-wing without
People's aircraft may be implemented to influence to implement transmission, high-risk areas detecting function, be widely used by carrying multiple sensors
In every field.
The unmanned vehicle of fixed-wing at this stage is that wing and body are integrally formed, this integrally formed unmanned flight
Device, which exists, to be difficult to dismount, and stores very difficult disadvantage, and body occupies biggish space when placing, the manufacture of body mold is complicated, system
Make the disadvantages of difficulty is big, and processing cost is high.And after wing damage, maintenance cost is big, and maintenance difficulty increases.Simultaneously as machine
The wing cannot be dismantled, and need large-scale haulage vehicle in transport, increase transportation cost, can't guarantee transportation safety.
Summary of the invention
It is integrally formed to solve wing existing in the prior art and body, dismounting is inconvenient, is not easy to store and transport
And the technical issues of inconvenient maintenance, the present invention provides following technical schemes：
A kind of fast disassembly type fuselage wing attachment structure including fuselage body and is symmetrically disposed on two of the fuselage body two sides
Wing-body, it is detachable between the fuselage body and wing-body to be fixedly connected；
The fuselage body includes fuselage framework, be provided in the fuselage framework, along its cross-sectional direction preceding connecting plate and after
Connecting plate, is fixedly installed the protrusion square box of a both ends open in the plate face of the preceding connecting plate, it is described after connecting plate plate face
On be symmetrically set with two angle boxes；
The wing-body includes wing components and Wedge-shape connector, and the Wedge-shape connector is fixed on the wing components and machine
On the end face of body ontology connection；
The Wedge-shape connector on two wing-bodies passes through institute respectively from the opening insertion at the protrusion square box both ends
The pin being arranged on protrusion square box is stated to fix；The angle box is bonded with the end face of corresponding wing components respectively, and passes through institute
The pin being arranged on the box of angle is stated to fix；It detachable is fixedly connected with realize between the fuselage body and wing-body.
As a further explanation of the present invention, the wing components include Front wing spar and wing rear spar, before the wing
It is connected between beam and wing rear spar by multiple connection ribs；
The Wedge-shape connector is fixed on the Front wing spar adjacent to one end of fuselage body, the angle box and the neighbouring fuselage
The connection rib of ontology is bonded.
As a further explanation of the present invention, the connection rib includes the wing root positioned at Front wing spar and wing rear spar both ends
Rib and the wing slightly rib, and the intermediate rib in the middle part of Front wing spar and wing rear spar；
The angle box is bonded with the wing root rib, is fixed by pin.
As a further explanation of the present invention, the Wedge-shape connector is an integral molding structure with the Front wing spar.
As a further explanation of the present invention, aileron structure is provided on the wing rear spar.
As a further explanation of the present invention, casing backboard, institute are provided on the top and bottom of the protrusion square box
The fixed plate that casing backboard is arranged in a mutually vertical manner by two pieces is stated to form, two pieces of orthogonal fixed plates respectively with the protrusion side
The top surface or bottom surface of box and the preceding connecting board surface post and fix connection.
As a further explanation of the present invention, a triangular aslant is fixedly installed in the middle part of the two fixed plates of the casing backboard
Beam.
As a further explanation of the present invention, casing is carried on the back there are two being respectively provided on the top and bottom of the protrusion square box
Plate, and it is located at the both ends of the protrusion square box top and bottom.
As a further explanation of the present invention, the fuselage framework includes mutually flat with the preceding connecting plate and rear connecting plate
Preceding framework, middle part framework and the rear framework of row setting, the preceding connecting plate and rear connecting plate be set to the middle part framework and
Afterwards between framework；
It is uniformly distributed circumferentially between the preceding framework, middle part framework, preceding connecting plate, rear connecting plate and rear framework by more
Attachment beam is fixedly connected.
As a further explanation of the present invention, the attachment beam include through central sill, preceding underbeam, rear underbeam and it is rear on
Beam；
It is described to be set in the preceding framework, middle part framework, preceding connecting plate, rear connecting plate and rear framework two sides through central sill
Portion, and be successively fixedly connected with the preceding framework, middle part framework, preceding connecting plate, rear connecting plate and rear framework；
The preceding underbeam is set to two side lower part of the preceding framework and middle part framework, and fixes with the preceding framework and middle part framework
Connection；
Underbeam is set to the rear connecting plate and rear framework two sides lower part after described, and fixes with the rear connecting plate and rear framework
Connection；
It is described after upper beam be set to the middle part framework, preceding connecting plate, rear connecting plate and rear framework two sides top, and successively with
The middle part framework, preceding connecting plate, rear connecting plate and rear framework are fixedly connected.
Compared with prior art, what the present invention obtained has the beneficial effect that：
Fuselage body and wing-body are designed as mutually independent component, and led to by fuselage wing attachment structure of the invention
Cross and be mutually inserted, then with fast bolt axle realize fix, realize the Quick-dismantling structure of fuselage and wing, and do not need by
Dismounting can be completed in professional tool, structurally reasonable, convenient and practical.
The present invention is described in further details below with reference to accompanying drawings and embodiments.
Detailed description of the invention
Fig. 1 is fuselage wing attachment structure general structure schematic diagram.
Fig. 2 is fuselage body structural schematic diagram.
Fig. 3 is wing-body structural schematic diagram.
Fig. 4 is Front wing spar structural schematic diagram.
Fig. 5 is wing rear spar structural schematic diagram.
Fig. 6 is wing root rib structure schematic diagram.
Fig. 7 is intermediate rib structural schematic diagram.
Fig. 8 is the wing slightly rib structure schematic diagram.
When Fig. 9 is that wing-body is connect with fuselage body, the Wedge-shape connector attachment structure schematic diagram of two Front wing spars.
When Figure 10 is that wing-body is connect with fuselage body, the connection structure of angle box, wing root rib and wing rear spar is illustrated
Figure.
Figure 11 is casing back board structure schematic diagram.
Figure 12 is angle box structure schematic diagram.
Figure 13 is fast bolt standard component structural schematic diagram.
Figure 14 is through center sill structure schematic diagram.
Figure 15 is preceding framework structural schematic diagram.
Figure 16 is middle part frame structure schematic diagram.
Figure 17 is preceding connecting plate and protrusion square box structure schematic diagram.
Figure 18 is rear connecting board structure schematic diagram.
Figure 19 is rear framework structural schematic diagram.
In figure：1, preceding framework；2, middle part framework；3, preceding connecting plate；4, rear connecting plate；5, rear framework；6, run through central sill；7,
Preceding underbeam；8, rear underbeam；9, rear upper beam；10, card slot；11, casing backboard；12, angle box；13, Front wing spar；14, wing rear spar；
15, wing root rib；16, intermediate rib；17, the wing slightly rib；18, aileron structure；19, Wedge-shape connector；20, fixed plate；21, triangular aslant
Beam；22, square box is protruded.
Specific embodiment
Reach the technical means and efficacy that predetermined purpose is taken for the present invention is further explained, below in conjunction with attached drawing and reality
Example is applied to a specific embodiment of the invention, structure feature and its effect, detailed description are as follows.
In the description of the invention, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "upper", "lower",
The orientation or positional relationship of the instructions such as "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is
It is based on the orientation or positional relationship shown in the drawings, is merely for convenience of description the invention and simplifies description, rather than indicate
Or imply that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore cannot understand
For the limitation to the invention.
In addition, term " first ", " second ", " third " etc. are used for description purposes only, it is not understood to indicate or imply
Relative importance or the quantity for implicitly indicating indicated technical characteristic.The feature of " first ", " second " etc. is defined as a result,
It can explicitly or implicitly include one or more of the features.In the description of the invention, unless otherwise indicated,
The meaning of " plurality " is two or more.
Term " installation ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, be also possible to removable
Connection is unloaded, or is integrally connected；It can be mechanical connection, be also possible to be electrically connected；It can be directly connected, it can also be in
Between medium be indirectly connected, can be the connection inside two elements.For the ordinary skill in the art, can pass through
Concrete condition understands concrete meaning of the above-mentioned term in the invention.
It being integrally formed to solve fixed-wing unmanned vehicle wing and body existing in the prior art, dismounting is inconvenient,
It is not easy to store and transport and the technical issues of inconvenient maintenance, the present embodiment provides a kind of fast disassembly type fuselage wing attachment structure,
As shown in Figure 1, including fuselage body and two wing-bodies for being symmetrically disposed on fuselage body two sides, fuselage body and wing sheet
It is detachable between body to be fixedly connected；Fuselage body is as shown in Fig. 2, including fuselage framework, in fuselage framework, along its cross section side
To preceding connecting plate 3 and rear connecting plate 4 is provided with, the protrusion square box of a both ends open is fixedly installed in the plate face of preceding connecting plate 3
22, two angle boxes 12 are symmetrically set in the plate face of rear connecting plate 4；Wing-body as shown in figure 3, include wing components and
Wedge-shape connector 19, Wedge-shape connector 19 are fixed on the end face that wing components are connect with fuselage body；On two wing-bodies
Wedge-shape connector 19 respectively from the opening insertion at protrusion 22 both ends of square box, and it is solid by the pin that is arranged on protrusion square box 22
It is fixed；Angle box 12 is bonded with the end face of corresponding wing components respectively, and the pin by being arranged on angle box 12 is fixed；To realize
Detachable between fuselage body and wing-body is fixedly connected.
Above-mentioned wing components include Front wing spar 13 and wing rear spar 14, are passed through between Front wing spar 13 and wing rear spar 14
Multiple connection rib connections；Wedge-shape connector 19 is fixed on Front wing spar 13 adjacent to one end of fuselage body, angle box 12 and neighbouring machine
The connection rib of body ontology is bonded.
Above-mentioned connection rib includes the wing root rib 15 and the wing slightly rib 17 positioned at 14 both ends of Front wing spar 13 and wing rear spar, and
Intermediate rib 16 positioned at 14 middle part of Front wing spar 13 and wing rear spar；Angle box 12 is bonded with wing root rib 15, is fixed by pin.
Preferably, Wedge-shape connector 19 is an integral molding structure with Front wing spar 13, i.e., wing-body is by two beams and three
Root rib is constituted, respectively Front wing spar 13 and wing rear spar 14, wing root rib 15, intermediate rib 16 and the wing slightly rib 17, above-mentioned wing
Aileron structure 18 is installed close to the wing slightly place on the back rest 14, the aileron structure 18 is using the prior art often having, Gu it does not retouch in detail
State its structure.
Preferably, Front wing spar 13 have certain camber, as shown in figure 4, camber size with it is curved on wing span direction
Degree is consistent, and there are two pin holes for setting on the Wedge-shape connector 19 of end, and two wing-bodies are inserted into protrusion square box 22 respectively
Afterwards, the lozenges of two Wedge-shape connectors 19 is bonded to each other, and relatively fixed by protrusion 22 pin of square box realization, such as Fig. 9
It is shown；Front wing spar 13 is square thin rod shape, and end face is " mouth " shape at wing root, and end face is " Contraband " shape at middle part to tip location,
To facilitate the connection of the connection rib of wing-body.
Preferably, wing rear spar 14 have certain camber, as shown in figure 5, camber size with it is curved on wing span direction
Degree is consistent, and its thin rod shape that is also square, the slightly entire end face of wing root to the wing are " Contraband " shape, convenient for connection rib connection.
Preferably, 15 structure of wing root rib is as shown in fig. 6, entirety is made of, head and tail in mouse-like independent two parts
Portion, head and tail portion are hollow type structure, and for Front wing spar 13 between head and tail portion, tail is inserted into 14 end of wing rear spar
In the cavity in portion, angle box 12 and the lateral tail face paste are closed and are fixed by pin, as shown in Figure 10, each section contact surface it
Between connected by way of strength gluing, tail portion offers pin hole on the side adjacent with fuselage body, be used for and angle box 12
On pin be connected and fixed.
Preferably, 16 structure of intermediate rib is as described in Figure 7, and whole is in mouse-like, is made of independent three parts, head, middle part and
Tail portion, Front wing spar 13 is between head and middle part, and wing rear spar 14 between middle part and tail portion, insert respectively by middle part both ends
In " Contraband " the shape groove for entering Front wing spar 13 and wing rear spar 14, connected by way of strength gluing between each contact surface.
Preferably, the wing slightly 17 structure of rib has independent two parts to constitute, head and tail as shown in figure 8, whole is in mouse-like
Portion, head and tail portion are hollow type structure, and for Front wing spar 13 between head and tail portion, the insertion of 14 end of wing rear spar should
In the cavity of tail portion, tail portion it is adjacent with head one end insertion Front wing spar 13 " Contraband " shape groove in, each section contact surface it
Between connected by way of strength gluing.
Casing backboard 11 is provided on the top and bottom of above-mentioned protrusion square box 22, casing backboard 11 is mutually hung down by two pieces
The fixed plate 20 that is directly arranged forms, two pieces of orthogonal fixed plates 20 respectively with the top surface of protrusion square box 22 or bottom surface and preceding
3 plate face of connecting plate posts and fixes connection.Above-mentioned casing backboard 11 as shown in figure 11, two fixed plates 20 in the middle part of be fixedly installed
There is a triangle cant beam 21, that is, be provided with a reinforcing rib, further promotes the stability of Integral connection structure.
Above-mentioned angle box 12 is fixed by bolts on rear connecting plate 4, and left and right side opens up pin hole, due to insertion pin with
Wing root rib 15 connects, and on its side for contact with wing root rib 15, four apertures are uniformly distributed around pin hole, pass through setting pad
The mode of piece, the movement of limitation pin in the circumferential, as shown in figure 12.
Preferably, casing backboard 11 there are two being respectively provided on the top and bottom of above-mentioned protrusion square box 22, and be located at
Protrude the both ends of 22 top and bottom of square box.
This connection structure provided in this embodiment, practical pin use fast bolt, which uses standard component, tail
There is the aperture radially opened up in portion, after pin is inserted into pin hole, is inserted into a thin stick of circle, in the aperture with banking pin
The axial limiting of nail, as shown in figure 13；The fast bolt realizes the fast assembling-disassembling of unmanned vehicle entirety, does not need dismounting work
Tool, can be completed the fast insert-pull between fuselage and wing.
Above-mentioned fuselage framework includes the preceding framework 1 arranged in parallel with preceding connecting plate 3 and rear connecting plate 4, middle part framework 2
And rear framework 5, preceding connecting plate 3 and rear connecting plate 4 are set between middle part framework 2 and rear framework 5；Preceding framework 1, middle part framework
2, the attachment beam being uniformly distributed circumferentially between preceding connecting plate 3, rear connecting plate 4 and rear framework 5 by more is fixedly connected.
Above-mentioned attachment beam includes through central sill 6, preceding underbeam 7, rear underbeam 8 and rear upper beam 9；Before being set to through central sill 6
Framework 1, middle part framework 2, preceding connecting plate 3, rear connecting plate 4 and rear 5 liang of middle side parts of framework, and successively with preceding framework 1, middle part frame
Body 2, preceding connecting plate 3, rear connecting plate 4 and rear framework 5 are fixedly connected；Preceding underbeam 7 is set to preceding framework 1 and 2 liang of middle part framework
Side lower part, and be fixedly connected with preceding framework 1 and middle part framework 2；Underbeam 8 is set under 5 two sides of rear connecting plate 4 and rear framework afterwards
Portion, and be fixedly connected with rear connecting plate 4 and rear framework 5；Upper beam 9 is set to middle part framework 2, preceding connecting plate 3, rear connecting plate 4 afterwards
And 5 liang of upper lateral parts of rear framework, and be successively fixedly connected with middle part framework 2, preceding connecting plate 3, rear connecting plate 4 and rear framework 5.
Preferably, two are provided with through central sill 6, preceding underbeam 7, rear underbeam 8 and rear upper beam 9, respectively at fuselage sheet
The two sides of body are symmetrical arranged.
Preferably, whole through central sill 6 is in beam type mechanism, as shown in figure 14, has a certain radian, radian size and its
The size and location of the preceding framework 1, middle part framework 2, preceding connecting plate 3, rear connecting plate 4 and the rear framework 5 that connect match；Run through
6 cross section of central sill is in the shape of a " convex ", with preceding framework 1, middle part framework 2, preceding connecting plate 3, rear connecting plate 4 and rear framework 5
It is correspondingly connected with place, sentence is extended with auricle to upper and lower two sides, facilitates the connection of itself and each framework and connecting plate.
Above-mentioned preceding underbeam 7, rear underbeam 8 and rear upper beam 9 are whole similar with through 6 structure of central sill, distinguish be its length with
And the component being attached thereto is adjusted, admittedly it is not described in detail.
Preferably, above-mentioned preceding framework 1, middle part framework 2, preceding connecting plate 3, rear connecting plate 4 and rear framework 5 and each connection
The junction of beam is provided with card slot 10, as shown in Figure 15, Figure 16, Figure 17, Figure 18 and Figure 19, with " convex " of mating connection beam
Font cross-sectional structure, realizes the connection structure of male-female engagement, and is subject to the fixation of bolt or other forms, to constitute knot
The stable fuselage body structure of structure.
The above content is a further detailed description of the present invention in conjunction with specific preferred embodiments, and it cannot be said that
Specific implementation of the invention is only limited to these instructions.For those of ordinary skill in the art to which the present invention belongs, exist
Under the premise of not departing from present inventive concept, a number of simple deductions or replacements can also be made, all shall be regarded as belonging to of the invention
Protection scope.
Claims (10)
1. a kind of fast disassembly type fuselage wing attachment structure including fuselage body and is symmetrically disposed on the two of the fuselage body two sides
A wing-body, it is characterised in that：It is detachable between the fuselage body and wing-body to be fixedly connected；
The fuselage body includes fuselage framework, is provided with preceding connecting plate in the fuselage framework, along its cross-sectional direction（3）With
Connecting plate afterwards（4）, the preceding connecting plate（3）Plate face on be fixedly installed the protrusion square box of a both ends open（22）, after described
Connecting plate（4）Plate face on be symmetrically set with two angle boxes（12）；
The wing-body includes wing components and Wedge-shape connector（19）, the Wedge-shape connector（19）It is fixed on the wing
On the end face that component is connect with fuselage body；
The Wedge-shape connector on two wing-bodies（19）Respectively from the protrusion square box（22）The opening at both ends is inserted into, and
And pass through the protrusion square box（22）The pin of upper setting is fixed；The angle box（12）Respectively with the end face of corresponding wing components
Fitting, and pass through the angle box（12）The pin of upper setting is fixed；To realize between the fuselage body and wing-body
It is detachable to be fixedly connected.
2. fuselage wing attachment structure according to claim 1, it is characterised in that：The wing components include Front wing spar
（13）And wing rear spar（14）, the Front wing spar（13）And wing rear spar（14）Between by multiple connection ribs connection；
The Wedge-shape connector（19）It is fixed on the Front wing spar（13）One end of neighbouring fuselage body, the angle box（12）With
The connection rib of the neighbouring fuselage body is bonded.
3. fuselage wing attachment structure according to claim 2, it is characterised in that：The connection rib includes before being located at wing
Beam（13）And wing rear spar（14）The wing root rib at both ends（15）With the wing slightly rib（17）, and it is located at Front wing spar（13）After wing
Beam（14）The intermediate rib at middle part（16）；
The angle box（12）With the wing root rib（15）Fitting, is fixed by pin.
4. fuselage wing attachment structure according to claim 2, it is characterised in that：The Wedge-shape connector（19）With it is described
Front wing spar（13）It is an integral molding structure.
5. fuselage wing attachment structure according to claim 4, it is characterised in that：The wing rear spar（14）On be provided with
Aileron structure（18）.
6. fuselage wing attachment structure according to claim 1, it is characterised in that：The protrusion square box（22）Top surface and
Casing backboard is provided on bottom surface（11）, the casing backboard（11）The fixed plate being arranged in a mutually vertical manner by two pieces（20）Group
At two pieces of orthogonal fixed plates（20）Respectively with the protrusion square box（22）Top surface or bottom surface and the preceding connecting plate
（3）Plate face posts and fixes connection.
7. fuselage wing attachment structure according to claim 6, it is characterised in that：The casing backboard（11）Two pieces it is solid
Fixed board（20）Middle part is fixedly installed a triangle cant beam（21）.
8. fuselage wing attachment structure according to claim 7, it is characterised in that：The protrusion square box（22）Top surface and
Casing backboard there are two being respectively provided on bottom surface（11）, and it is located at the protrusion square box（22）The both ends of top and bottom.
9. fuselage wing attachment structure according to claim 1-8, it is characterised in that：The fuselage framework includes
With the preceding connecting plate（3）With rear connecting plate（4）Preceding framework arranged in parallel（1）, middle part framework（2）And rear framework
（5）, the preceding connecting plate（3）With rear connecting plate（4）It is set to the middle part framework（2）With rear framework（5）Between；
The preceding framework（1）, middle part framework（2）, preceding connecting plate（3）, rear connecting plate（4）And rear framework（5）Between by more
The attachment beam being uniformly distributed circumferentially is fixedly connected.
10. according to right want 9 described in fuselage wing attachment structure, it is characterised in that：The attachment beam includes running through central sill
（6）, preceding underbeam（7）, rear underbeam（8）And rear upper beam（9）；
It is described to run through central sill（6）It is set to the preceding framework（1）, middle part framework（2）, preceding connecting plate（3）, rear connecting plate（4）With
And rear framework（5）Two middle side parts, and successively with the preceding framework（1）, middle part framework（2）, preceding connecting plate（3）, rear connecting plate（4）
And rear framework（5）It is fixedly connected；
The preceding underbeam（7）It is set to the preceding framework（1）With middle part framework（2）Two side lower parts, and with the preceding framework（1）With
Middle part framework（2）It is fixedly connected；
Underbeam after described（8）It is set to the rear connecting plate（4）With rear framework（5）Two side lower parts, and with it is described after connecting plate（4）
With rear framework（5）It is fixedly connected；
Upper beam after described（9）It is set to the middle part framework（2）, preceding connecting plate（3）, rear connecting plate（4）And rear framework（5）Two
Upper lateral part, and successively with the middle part framework（2）, preceding connecting plate（3）, rear connecting plate（4）And rear framework（5）It is fixedly connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810967623.4A CN108910013A (en) | 2018-08-23 | 2018-08-23 | A kind of fast disassembly type fuselage wing attachment structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810967623.4A CN108910013A (en) | 2018-08-23 | 2018-08-23 | A kind of fast disassembly type fuselage wing attachment structure |
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| CN108910013A true CN108910013A (en) | 2018-11-30 |
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| CN201810967623.4A Pending CN108910013A (en) | 2018-08-23 | 2018-08-23 | A kind of fast disassembly type fuselage wing attachment structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110282113A (en) * | 2019-06-25 | 2019-09-27 | 西安爱生技术集团公司 | A kind of fast assembly and disassembly mechanism of unmanned plane Wing-fuselage |
| CN110884642A (en) * | 2019-12-07 | 2020-03-17 | 湖南浩天翼航空技术有限公司 | Wing quick assembly disassembly structure based on square roof beam |
| CN110920884A (en) * | 2019-12-05 | 2020-03-27 | 中国特种飞行器研究所 | Ground effect aircraft wing structure that can dismantle fast |
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| CN110282113A (en) * | 2019-06-25 | 2019-09-27 | 西安爱生技术集团公司 | A kind of fast assembly and disassembly mechanism of unmanned plane Wing-fuselage |
| CN110920884A (en) * | 2019-12-05 | 2020-03-27 | 中国特种飞行器研究所 | Ground effect aircraft wing structure that can dismantle fast |
| CN110920884B (en) * | 2019-12-05 | 2024-01-12 | 中国特种飞行器研究所 | Quick detachable ground effect aircraft wing structure |
| CN110884642A (en) * | 2019-12-07 | 2020-03-17 | 湖南浩天翼航空技术有限公司 | Wing quick assembly disassembly structure based on square roof beam |
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