CN107963225A - Aircraft engine hanger and hanging box section thereof - Google Patents
Aircraft engine hanger and hanging box section thereof Download PDFInfo
- Publication number
- CN107963225A CN107963225A CN201711239526.5A CN201711239526A CN107963225A CN 107963225 A CN107963225 A CN 107963225A CN 201711239526 A CN201711239526 A CN 201711239526A CN 107963225 A CN107963225 A CN 107963225A
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- CN
- China
- Prior art keywords
- wainscot
- hanging
- box section
- hanging box
- engine
- Prior art date
- 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; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/04—Aircraft characterised by the type or position of power plants of piston type
- B64D27/06—Aircraft characterised by the type or position of power plants of piston type within, or attached to, wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
- B64D27/402—Arrangements for mounting power plants in aircraft comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
- Pallets (AREA)
Abstract
A tow box section for an aircraft engine tow comprising: a body; the engine of the airplane is connected to the hanging box section through the hanging-engine connecting part, and the hanging box section is connected to the wing or the fuselage of the airplane through the hanging-wing connecting part. Hang the body of box section and include: an upper wall plate; a bottom plate disposed opposite to the upper wall plate; and a side wall panel connected between the upper wall panel and the bottom panel, wherein the upper wall panel is formed by combining at least two panel parts to form a convex structure. Also relates to an aircraft engine hanger comprising the hanger box section. The hanging box section with the structure can bear larger load, the overall structural strength of the hanging box section is improved, and the service life of the hanging box section is prolonged.
Description
Technical field
The present invention relates to field of airplane structure, and in particular to aircraft engine hanging, particularly hanging box therein
The structure design of section.
Background technology
Engine hanging is the connection structure between the engine of aircraft and the wing (or fuselage) of aircraft.Engine is hung
Including hanging box section, to provide the carrying to engine load, and also provide between engine and each system of aircraft
Route profiling, such as fuel pipe, hydraulic fluid pipeline, electric wiring.
Fig. 1 shows a kind of structure of the engine hanging of prior art.As shown in Figure 1, the engine hanging 1 of aircraft is logical
Often include hanging box section 10.In addition, in order to make the overall structure that engine is hung disclosure satisfy that the requirement of certain aerodynamic configuration,
Engine hanging 1 further includes top radome fairing 20, the hanging component such as trailing edge 30 and duct rectifier structure 40, is thus hung for engine
The good aerodynamic configuration of 1 overall offer is hung, as shown in Figure 1.Top radome fairing 20, hanging trailing edge 30, duct rectifier structure 40 etc.
Pneumatic rectification part is generally connected in hanging box section 10, it is acted on mainly carries out rectification to the air-flow flowed through, is not intended as
Main load structure.
In other words, in engine hanging 1, the load transmission of engine and wing control piece is mainly by hanging box section
10 come what is realized, and main be provided in of hanging-wing connection 50 and hanging-engine connecting portion 60 of engine hanging 1 is hung
In extension box section 10.
Fig. 2 and 3 shows the structure of the hanging box section 10 of engine hanging 1, wherein, its knot is shown in order to clearer
Structure, eliminates top radome fairing 20, the hanging rectification part such as trailing edge 30 and duct rectifier structure 40.
As shown in Figures 2 and 3, hang box section 10 include wainscot 11, the bottom plate 13 substantially opposite set with wainscot 11,
And two side walls plate 12, sidewall paneling 12 are connected between wainscot 11 and bottom plate 13.
As shown in Fig. 2, formed with top connection 51 on wainscot 11, in the rear end of hanging box section 10, i.e. relative to aircraft
That one end for being located behind of course on formed with center tap 52, top connection 51 and center tap 52 form hanging-wing connection
50 at least a portion.As shown in figure 3, hanging box section 10 front end, i.e. relative to the course of aircraft be located at front that
End is upper formed with preceding installation section 61, saves 62 compositions formed with rear installation section 62, preceding installation section 61 and rear installation on base 13 and hangs
At least a portion of extension-engine connecting portion 60.
Specifically, in the mounted state, top connection 51 and center tap 52 are connected on wing (or fuselage), preceding installation
Section 61 and rear installation section 62 are connected with the engine of aircraft, and thus, installation section 61 and rear installation save the load of engine in the past
62 bottom plate 13, sidewall paneling 12 and wainscots 11 through hanging box section 10, then aircraft machine is delivered to by top connection 51 and center tap 52
On the wing or fuselage.
Fig. 4 shows the partial cross sectional views of hanging box section 10, the part specifically near the top connection 51 of hanging box section 10
Cut away view.As shown in figure 4, being equipped with reinforcing frame 14 at 10 inside of hanging box section with 51 corresponding position of top connection, should add
Strong frame 14 is connected with wainscot 11, sidewall paneling 12 and bottom plate 13.
Research shows that in the mounted state, wainscot 11, sidewall paneling 12 and bottom plate 13 are in the area being connected with reinforcing frame 14
Most load is carried at domain.In Fig. 4, arrow A represents the course of aircraft, and the course of represented by arrow B and aircraft is mutually hung down
Straight is vertical, and arrow 70 then represents the load being applied in top connection 51.It can be seen that the load 70 being applied on connector 51 with
Course A is at an angle, and can resolve into course load 71 and vertical load 72, and then in wainscot 11, sidewall paneling
12 and bottom plate 13 on be also applied with vertical and course load.In Fig. 4 with the solid load bold arrows show engine
The caused deformation in the various pieces of hanging box section 10.Wherein, course load 71 is entirely in wainscot 11,12 and of sidewall paneling
Along the extending direction transmission of each siding in bottom plate 13, therefore cause tension and compression deformation 21 in face in these sidings.It is and vertical
Load 72 is also the extending direction transmission along sidewall paneling 12 in sidewall paneling 12, therefore also causes tension and compression in the face of sidewall paneling 12
Deformation 21, and for bottom plate 13, which is delivered to bottom plate 13 via reinforcing frame 14, and in bottom plate 13 with strengthening
Dog-ear is provided with the join domain of frame 14, therefore is delivered to the vertical load 72 at bottom plate 13 also by partially along bottom plate 13
Extending direction be passed, so as to also cause tension and compression deformation in face in bottom plate 13.But vertical load 72 is on wainscot 11
It is that edge applies perpendicular to the direction of wainscot 11, therefore siding vertical direction will be caused to deform 22.
Thus, it can be seen that, obvious siding vertical direction deformation 22 is had on wainscot 11 in being analyzed more than, and
It is mainly then tension and compression deformation 21 in face on other sidings.For platy structure, tension and compression deformation 21 is in platy structure in face
In caused stress by far smaller than siding vertical direction deform 22 caused by stress.The present inventor is with 1 meter long, wide
0.3 meter, tablet 0.06 meter thick shown for the result of study of object, under the load of formed objects, caused vertical deformation
It is 1111 times of in-plane deformation, and the maximum stress caused by the vertical deformation is 100 times of the stress caused by in-plane deformation.
Thus, it was found by the inventors of the present invention that in existing engine hanging 1, the stress in wainscot 11 is larger, therefore wainscot
11 destroyed risk biggers, therefore the structure of existing engine hanging 1 stills need further to improve.
The content of the invention
The present invention is found based on above-described research, for the above-mentioned technical problem in the presence of the solution prior art
Make.The object of the present invention is to provide a kind of hanging box section with improved structure, more excellent structure is made it have
Intensity, make hanging box section and including the hanging box section engine hanging it is safer, service life is longer.
Hanging box section includes according to the present invention：Body；Hanging-engine connecting portion, the hanging-engine connecting portion shape
Into on body, and the engine of aircraft is connected to hanging box section by hanging-engine connecting portion；And hanging-wing connects
Socket part, the hanging-wing connection are formed on body, and are hung box section and be connected to aircraft by hanging-wing connection
On wing or fuselage.In the present invention, hanging the body of box section includes：Wainscot；Bottom plate, the bottom plate are relatively set with wainscot
Put；And sidewall paneling, the sidewall paneling are connected between wainscot and bottom plate, wherein, wainscot combined by least two plate portions and
Into being formed as raised construction, also, hanging-wing connection includes the top connection that is arranged on wainscot.
In hanging box section according to the present invention, the raised construction of wainscot is so that the load transmission carried by top connection
Into each plate portion, and transmitted in the face of each plate portion, be tension and compression deformation in face caused by each plate portion thus.Therefore, originally
The hanging box section of invention can carry the load of bigger, its overall construction intensity is improved, and service life is also extended.
According to the size of top connection and installation space, the vertical height of the top connection is preferably in 150~216mm
In the range of.
It is preferred that the course of top connection along aircraft, which is positioned at, is in the position in same perpendicular with the load of engine
Place.The course position of top connection makes the overall load of hanging box section minimum.
In the structure of the present invention, the top of wainscot is provided with platform, top connection is fixedly or detachably installed
On platform.For example, top connection can be installed on the platform by the mode such as welding, being bolted.
A kind of preferably in example, wainscot includes four triangle plate portions being mutually connected to each other, be respectively on
Plate portion, wainscot left plate portion and wainscot right panel portion after siding front panel portion, wainscot.
Further it is preferred that in this four plate portions, plate portion, wainscot left plate portion and wainscot right panel portion shape after wainscot
The component being integrally formed, component of the wainscot front panel portion removably with one are connected.The connection mode of plate portion can be easy to
Carry out maintenance, while the strength character of wainscot can be kept to be maintained in acceptable level again.
In another embodiment, wainscot includes two plate portions, i.e. plate portion after wainscot front panel portion and wainscot, upper wall
Plate portion links together along the course of aircraft after plate front panel portion and wainscot.
It is preferred that wainscot is detachably connected with sidewall paneling, in order to carry out maintenance.
In addition, hanging-engine connecting portion in the hanging box section of the present invention includes：Preceding installation section, preceding installation section are set
In the front end in the course along aircraft of body；And rear installation section, rear section of installing are arranged on bottom plate；And/or
Hanging-wing connection further includes center tap, and center tap is arranged on the rear end in the course along aircraft of body.
The invention further relates to a kind of hanging of aircraft engine, it includes hanging box section as described above and being connected to this hanging
At least one pneumatic rectification part in extension box section.
Brief description of the drawings
Fig. 1 shows a kind of stereogram of the engine hanging of prior art.
Fig. 2 shows the stereogram of the hanging box section of the hanging of engine shown in Fig. 1.
Fig. 3 shows another stereogram of the hanging box section shown in Fig. 2.
Fig. 4 shows the partial cross sectional views of hanging box section shown in Fig. 2, and which schematically illustrates each portion of hanging box section
Load distribution on point.
Fig. 5 shows the stereogram of hanging box section according to the present invention.
Fig. 6 shows the load in plate portion after top connection, wainscot front panel portion and the wainscot of hanging box section shown in Fig. 5
Schematic diagram.
Fig. 7 schematically shows the different vertical height that the top connection of hanging box section can be taken.
Fig. 8 is to show to close between the ratio for reflecting different connector height and positions and siding load-top connection load
The curve map of system.
Fig. 9 schematically shows the cantilever beam structure of hanging box section.
The diverse location in the course along aircraft that the top connection that Figure 10 schematically shows hanging box section can be taken.
Figure 11 is illustrated that the radar drawn to the load at the diverse location along the course of aircraft shown in Figure 10
Figure.
Figure 12 schematically shows the connection mode of each plate portion of the wainscot of hanging box section according to the present invention.
Figure 13 shows the partial enlarged view of the wainscot of hanging box section according to the present invention, is connect wherein having been shown in particular
The mounting structure of head.
Figure 14 is the schematic plan for the wainscot for including three plate portions and seven plate portions.
Figure 15 is the stereogram of another example of the hanging box section of the present invention, and wherein wainscot includes two plate portions.
Figure 16 is the stereogram of another example again of the hanging box section of the present invention, and wherein wainscot includes six plate portions.
Embodiment
It is described below in conjunction with Fig. 5~16 pair specific embodiment of the invention.
Fig. 5 shows the top perspective view of the hanging box section 100 in engine hanging according to the present invention.The hanging box section
100 include wainscot 120, bottom plate (not shown in FIG. 5) and the side plate being connected between wainscot 120 and bottom plate
130.Top connection 110 is provided with wainscot 120, installation 140 Hes of section before being also respectively provided with the both ends of hanging box section 100
Center tap 150.Although in addition, not shown in FIG. 5, identically with existing hanging box section, in the bottom plate of hanging box section 100
On be also equipped with after install section.
In the present invention, wainscot 120 is combined by multiple plate portions, so as to form the construction of protrusion.In Figure 5
In shown specific example, wainscot 120 includes the plate portion of four triangles, respectively after wainscot front panel portion 121, wainscot
Plate portion 122, wainscot left plate portion 123 and wainscot right panel portion 124, top connection 110 is then positioned at the position that these plate portions mutually intersect
Put place.
Fig. 6 schematically shows by taking plate portion 122 after wainscot front panel portion 121 and wainscot as an example and acts on top connection
Transmission of the load on wainscot 120 on 110.As shown in fig. 6, act on top connection load 200 and the water in top connection 110
Square at an angle.Analysis shows, the front panel portion sharing part of the load of the top connection load 200 on wainscot front panel portion 121
Extending direction of 211 direction along wainscot front panel portion 121, and top connection load 200 after wainscot in plate portion 122 after
Extending direction of the direction of the plate portion sharing part of the load 212 along plate portion after wainscot 122.After wainscot front panel portion 121 and wainscot
Plate portion 122 carries most of top connection load 200, and reinforcement is then played in wainscot left plate portion 123 and wainscot right panel portion 124
Effect, it is basic without or only carry a small amount of load.For being held in wainscot left plate portion 123 and wainscot right panel portion 124
For a small amount of load carried, its direction is also the extension side respectively along wainscot left plate portion 123 and wainscot right panel portion 124
To.
Therefore, in the hanging box section 100 of the present invention, wainscot 120 is by multiple plate portions (such as four three shown in figure
Angular plate portion) form raised construction so that by the load transmission that top connection 110 carries into each plate portion, and in each plate portion
Face in transmit, thus, in each plate portion caused by is tension and compression deformation in face.In this way, the knot of the hanging box section 100 in the present invention
In structure, the load of bigger can be carried so that the overall construction intensity of hanging box section 100 is improved, and hanging box section 100 makes
Also extended with the service life.
Below by further specifically describe to hang box section 100 wainscot 120 design details：
<The vertical height of top connection>
The wainscot 120 of the hanging box section 100 of the present invention is formed the construction of protrusion by multiple plate portions, and top connection 110 is then
It is positioned at the position that each plate portion mutually intersects, therefore relative to existing hanging box section 10 is in horizontal wainscot 11 substantially
For, top connection 110 of the invention is in elevated height and position, which is the vertical of top connection 110
Highly.
Fig. 7 schematically shows the top connection 110 in different vertical height and positions, wherein, represent existing with solid line
The wainscot 11 of technology, is represented by dotted lines plate portion 122 after the wainscot front panel portion 121 and wainscot of wainscot 120 of the invention,
Filled arrows then represent the load 200 being applied in top connection 110, which has along wainscot front panel portion
The 121 front panel portion sharing parts of the load 211 transmitted and the rear plate portion sharing part of the load 212 transmitted along plate portion after wainscot 122.From figure
It can be seen that the rise of the vertical height with top connection 110, the front panel portion sharing part of the load 211 and the rear plate portion sharing part of the load 212 are all
Correspondingly reduce.When hang box section 100 vertical height reach connector ideal height Hu when, the direction of top connection load 200 with
The extending direction of wainscot front panel portion 121 is parallel, and top connection load 200 is all transmitted in wainscot front panel portion 121 at this time, and
Component after wainscot in plate portion 122 is zero.In a kind of conventional hanging box section 100, connector ideal height Hu is substantially
1147mm。
But in actual structure, due to hanging the size limitation of box section 10, top connection 110 is unable to reach connector reason
Think height Hu, and can only achieve at the radome fairing upper level Hl of top radome fairing.In the hanging box section 100 of stock size
In, radome fairing upper level Hl is typically at around 216mm.
Fig. 8 shows relation between the ratio for reflecting different connector height and positions and siding load-top connection load
Curve map.It can see from the curve map shown in Fig. 8, with the rise of top connection 110,211 He of the front panel portion sharing part of the load
The plate portion sharing part of the load 212 all gradually reduces afterwards, and when reaching connector ideal height Hu, the front panel portion sharing part of the load 211, which is equal to, above to be connect
Head load 200, then the plate portion sharing part of the load 212 is zero.And the radome fairing upper level that can actually reach in top connection 110
At Hl, 1.89 times of the substantially top connection load 200 of the front panel portion sharing part of the load 211, then the plate portion sharing part of the load 212 substantially on
1.122 times of joint load 200.But, since the front panel portion sharing part of the load 211 and the rear plate portion sharing part of the load 212 are all in upper wall
Transmitted after plate front panel portion 121 and wainscot in the face of plate portion 122, caused is tension and compression deformation in face, therefore compared to existing
For hanging the vertical load on the wainscot 11 of box section 10, its caused internal stress is still much lower.
Further, consider that the height and position of top connection 110 should not be low from the size and installation space of top connection 110
In connector height lower limit Hd, in the hanging box section 100 of stock size, connector height lower limit Hd substantially 150mm.Such as Fig. 8
It is shown, at connector height lower limit Hd, 2.134 times of the substantially top connection load 200 of the front panel portion sharing part of the load 211, back plate
1.36 times of the substantially top connection load 200 of portion's sharing part of the load 212.
In conclusion in the present invention, the preferable height and position of the top connection 110 in hanging box section 100 is in radome fairing
Between upper level Hl (about 216mm) and connector height lower limit Hd (about 150mm).
<The position along course of top connection>
Top connection 110 sets the load performance to hanging box section 100 on wainscot 120 along the position in the course of aircraft
Have a significant impact.
Carried as shown in figure 9, engine saves 160 by preceding installation section 140 and rear installation, its position of centre of gravity installs section preceding
140 save the point of intersection of the respective extending direction of the load at 160 with rear installation, represent the load of engine with arrow 221 in fig.9
Lotus.And on the other hand, hanging box section 100 is then by top connection 110, center tap 150 and hound 170 by the load of engine
221 are delivered on wing or fuselage.Therefore, entirely hanging box section 100 can similarly be considered a cantilever beam, wherein in hair
Part in the same perpendicular of the load 221 of motivation is equivalent to the free end 231 of cantilever beam, and top connection 110, center tap
150 and hound 170 combination equivalent to cantilever beam root 232.
It can be seen that in the case of same load, the jib-length 233 that free end 231 is arrived between root 232 is shorter,
Then the internal stress of cantilever beam and deformation are smaller, and intensity is bigger, and structure is more stable.
But, it is increasingly complex to hang the load transmission form of box section 100, for example, installing section before having at free end 231
140 save 160 two load transmission positions with rear installation, there is top connection 110, center tap 150 and hound 170 at root 232
Load transmission position at three, wherein such as top connection 110 adds the carrying position of cantilever, and then improves its strength character, but
On the other hand, the setting of top connection 110 can also increase the load of local location, so as to reduce strength character.Therefore, it is necessary to right
Top connection 110 carries out more deep analysis along the position in course, to determine position of the optimal top connection of load performance along course
Put.
As Figure 10 adaptively shown in, the present invention have chosen four positions along course, and with existing hanging box section
Top connection 51 in 10 is compared and analyzed along the position Lt in course.This four positions are respectively：With existing hanging box section
Top connection 51 in 10 be in course position lo in same perpendicular, wainscot 120 centre position Lm, with engine
Load 221 is in the position Le in the same perpendicular and position Lf at preceding installation section 140.
Figure 11 shows the load corresponding to each course position in the form of radar map.Wherein, with 110,140,150,
160th, 170,121,122 signified radial alignments are represented in top connection 110, preceding installation section 140, center tap 150, rear installation section
160th, the load transmitted after hound 170, wainscot front panel portion 121 and wainscot in plate portion 122, the polygon pair of five closures
Should be in position Lt and above-mentioned top connection 110 to the present invention of the top connection 51 in existing hanging box section 10 along course
Four course positions Lo, Lm, Le and the Lf chosen, and the vertex of this five closed polygons then load at corresponding position
Size, wherein closer to circular, then it represents that corresponding load is smaller.
From the figure, it can be seen that for wainscot front panel portion 121, as top connection 110 is from the hanging box section of the prior art
The correspondence position of 10 top connection 51 constantly reduces towards preceding 140 movement of installation section, load therein, and for top connection 110
For, its load change does not follow the rule of increasing or decreasing then.As it can be seen that hanging box section 100 top connection 110 from existing
During the correspondence position of the top connection 51 of the hanging box section 10 of technology is moved towards preceding installation section 140, the load of different piece
Lotus changing rule simultaneously differs.In the present invention, the area enclosed using five closed polygons in the radar map shown in Figure 11
It is horizontal that the overall load of hanging box section 100 is assessed as index.
Table 1 shows the relative scale (wherein setting the area of Le as 1) of five closed polygon areas：
Table 1
| Course position | Lt | Lo | Lm | Le | Lf |
| Area | 2.16 | 3.77 | 2.70 | 1.00 | 2.13 |
It can be seen that at course position Le, the position in same perpendicular is in the load 221 of engine
Place, the overall load of hanging box section 100 are minimum, i.e. course position Le is the optimum position of hanging box section 100.
<Connection mode between the wall member of wainscot>
Below by by taking the plate portion of four pieces of triangles shown in attached drawing as an example, to describe each plate portion of composition wainscot 120
Between connection mode.
A kind of connection mode of wainscot 120 is that each plate portion is integrally connected together.For example, can be to an entire plate
Material carries out the processing of forging, machining etc., so as to form raised construction as shown in figure 12, protrusion construction includes upper wall
Plate portion 122, wainscot left plate portion 123 and wainscot right panel portion 124 after plate front panel portion 121, wainscot.Or or first
The plate portion of four pieces of triangles is formed, then this four pieces of triangle plate portions are welded together by way of welding etc., with
Form the structure of one.
Another connection mode of wainscot 120 is plate portion 122, wainscot left plate after wainscot front panel portion 121, wainscot
Portion 123 and wainscot right panel portion 124 are removably joined together.For example, four pieces of plate portions are detachably connected to bolt
Together.
For integrally formed wainscot 120, since each plate portion is formed integrally together, its strength character is most
It is good, but in maintenance, it is necessary to carry out installation and removal operation to whole wainscot 120, therefore it is not easy to assemble, and then be not easy to
Maintenance.
And for each plate portion is removably joined together wainscot 120, can be according to maintenance needs neatly
Selection dismounts any one or more therefore easy to repair in each plate portion.But, since each plate portion is by such as bolt
Deng component be removably joined together, therefore compared with the wainscot 120 being formed as one, by being detachably connected to
The strength character for the wainscot 120 that plate portion together is formed is remarkably decreased.
As the compromise of the wainscot 120 for integral type and the wainscot 120 removably assembled, the present invention carries
Go out the dismountable scheme in part.As shown in figure 12, plate portion 122, wainscot left plate portion 123, wainscot left plate portion 123 after wainscot
Be formed as one, and wainscot front panel portion 121 then by the components such as bolt removably with plate portion after wainscot 122, wainscot
The integrated component that left plate portion 123 and wainscot right panel portion 124 are formed links together, as shown in figure 12.
It is that obtained wainscot 120 is easier to repair by the way that wainscot front panel portion 121 is arranged to removably, and
Plate portion 122, wainscot left plate portion 123 and wainscot right panel portion 124 are integrally formed after wainscot, it can be ensured that by wainscot 120
Strength character maintain in certain level.
<Connection mode between wainscot and sidewall paneling>
In addition, can be integrally formed between wainscot 120 and sidewall paneling 130, or can also be removably
Link together, such as pass through the modes such as bolt.For angle easy to repair, wainscot 120 and side wall are preferably
Plate 130 is removably joined together.
<The mounting means of top connection>
As shown in figure 13, in the hanging box section 100 of the present invention, wainscot 120 is formed as raised form, in wainscot
120 top needs to set platform 125, for installing top connection 110.Top connection 110 can be installed to by welding
On wainscot 120, it can be also releasably attached to by the fastener of bolt etc. on wainscot 120.
<Form the quantity of the plate portion of wainscot>
The above description of this invention is carried out by taking the plate portion that wainscot 120 includes four triangles as an example.It is right below
The situation of other quantity plate portion is inquired into.
Figure 14 shows that the wainscot 120 including three plate portions and the schematic of the wainscot 120 including seven plate portions bow
What view, wherein arrow A indicated is the course of aircraft, and arrow C instructions are the lateral of aircraft.It can be seen that such as three,
Seven are waited in the situation of odd number plate portion, and at least one in preceding installation section 140 and center tap 150 can be configured to bear tiltedly
To load, and this overall load that can increase hanging box section 100 is horizontal.
Figure 15 and Figure 16 is respectively illustrated including two plate portions (after i.e. rectangular wainscot front panel portion 121 and wainscot
Plate portion 122) wainscot 120 and wainscot 120 including six plate portions, the example as the situation of even number plate portion.Can be with
See, in the case where wainscot 120 is made of even number plate portion, it can be ensured that the load of preceding installation section 140 and center tap 150
Direction is consistent with course A.
Further, as can see from Figure 16, at six and in the situation of more even number plate portion, in order to upper wall
The plate portion quantity of plate 120 matches, it is necessary to increase the quantity of sidewall paneling 130, such as in the situation of six plate portions, hanging box
The two side walls plate 130 to link together angular relative to each otherly is provided with every side of section 100.This can cause to hang box section
The increase of 100 aerodynamic loading, while can also increase design, manufacture and the cost of assembling.
Therefore, in the present invention it is preferred that wainscot 120 is by two rectangular plate portions or four plates triangular in shape
Portion is spliced.
Claims (10)
1. a kind of hanging box section of aircraft engine hanging, the hanging box section include：Body；Hanging-engine connecting portion, institute
State hanging-engine connecting portion to be formed on the body, and the engine of aircraft is connected by the hanging-engine connecting portion
It is connected to the hanging box section；And hanging-wing connection, the hanging-wing connection are formed on the body, and
The hanging box section is connected on the wing or fuselage of the aircraft by the hanging-wing connection；It is characterized in that,
The body includes：Wainscot；Bottom plate, the bottom plate are oppositely disposed with the wainscot；And sidewall paneling, the side
Siding is connected between the wainscot and the bottom plate, wherein, the wainscot is composed of at least two plate portions, is formed
For raised construction, also, the hanging-wing connection includes the top connection that is arranged on the wainscot.
2. hanging box section as claimed in claim 1, it is characterised in that the vertical height of the top connection is 150~216mm's
In the range of.
3. as claimed in claim 1 hanging box section, it is characterised in that the course of the top connection along the aircraft be positioned at
The load of the engine is at the position in same perpendicular.
4. hanging box section as claimed in claim 1, it is characterised in that the top of the wainscot is provided with platform, it is described
Top connection is fixedly or detachably installed on the platform.
5. hanging box section as claimed in claim 1, it is characterised in that the wainscot includes four be mutually connected to each other
Triangle plate portion, is respectively plate portion, wainscot left plate portion and wainscot right panel portion after wainscot front panel portion, wainscot.
6. hanging box section as claimed in claim 5, it is characterised in that plate portion, the wainscot left plate portion after the wainscot
The component being formed as one with the wainscot right panel portion, the wainscot front panel portion removably with the integral component phase
Connection.
7. hanging box section as claimed in claim 1, it is characterised in that the wainscot includes wainscot front panel portion and wainscot
Plate portion afterwards, plate portion links together along the course of the aircraft after the wainscot front panel portion and the wainscot.
8. hanging box section as claimed in claim 1, it is characterised in that the wainscot removably connects with the sidewall paneling
Connect.
9. hanging box section as claimed in claim 4, it is characterised in that the hanging-engine connecting portion includes：Preceding installation
Section, installs the front end that section is arranged on the course along the aircraft of the body before described；And rear installation section, installed after described
Section is arranged on the bottom plate；And/or
Hanging-the wing connection further includes center tap, and the center tap is arranged on the boat along the aircraft of the body
To rear end.
10. a kind of hanging of aircraft engine, including such as hanging box section according to any one of claims 1 to 9 and it is connected to
At least one pneumatic rectification part in the hanging box section.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711239526.5A CN107963225B (en) | 2017-11-30 | 2017-11-30 | Aircraft engine hanger and hanging box section thereof |
| PCT/CN2018/115170 WO2019105219A1 (en) | 2017-11-30 | 2018-11-13 | Aircraft engine suspension and suspension box section thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711239526.5A CN107963225B (en) | 2017-11-30 | 2017-11-30 | Aircraft engine hanger and hanging box section thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107963225A true CN107963225A (en) | 2018-04-27 |
| CN107963225B CN107963225B (en) | 2021-06-04 |
Family
ID=61999243
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711239526.5A Active CN107963225B (en) | 2017-11-30 | 2017-11-30 | Aircraft engine hanger and hanging box section thereof |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN107963225B (en) |
| WO (1) | WO2019105219A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606686A (en) * | 2018-12-10 | 2019-04-12 | 彩虹无人机科技有限公司 | A kind of universal unmanned plane emitter switching beam |
| WO2019105219A1 (en) * | 2017-11-30 | 2019-06-06 | 中国商用飞机有限责任公司 | Aircraft engine suspension and suspension box section thereof |
| CN112644718A (en) * | 2020-12-29 | 2021-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Unmanned aerial vehicle's engine suspended structure |
| CN112776993A (en) * | 2019-11-05 | 2021-05-11 | 中国航发商用航空发动机有限责任公司 | Aircraft and suspended structure thereof |
| CN113237661A (en) * | 2021-05-10 | 2021-08-10 | 中国商用飞机有限责任公司 | Device and method for measuring dynamic test load of wing-mounted engine |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3118944B1 (en) * | 2021-01-20 | 2023-12-08 | Airbus Operations Sas | PRIMARY STRUCTURE OF A MAST FOR FIXING AN AIRCRAFT ENGINE. |
| CN113581476B (en) * | 2021-08-11 | 2024-08-20 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Engine back support structure and aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0453360A1 (en) * | 1990-04-19 | 1991-10-23 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Aviation engine with high bypass ratio and of the type with front contra-rotating fan |
| CN101272953A (en) * | 2005-09-28 | 2008-09-24 | 法国空中客车公司 | Aircraft engine assembly including engine and mounts for the engine |
| CN101282876A (en) * | 2005-10-07 | 2008-10-08 | 法国空中客车公司 | Rigid structure for aircraft engine hanger and pylon comprising same |
| CN103101628A (en) * | 2013-02-06 | 2013-05-15 | 中国商用飞机有限责任公司 | Front mounting joint integrated with airplane hanging |
| CN106585999A (en) * | 2015-10-16 | 2017-04-26 | 空中客车运营简化股份公司 | Aircraft engine pylon |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2738034B1 (en) * | 1995-08-23 | 1997-09-19 | Snecma | DEVICE FOR SUSPENDING A TURBOPROPELLER |
| FR2878229B1 (en) * | 2004-11-23 | 2008-04-18 | Airbus France Sas | SYSTEM FOR ATTACHING A MOTOR MAT TO THE WING OF AN AIRCRAFT |
| FR2889505B1 (en) * | 2005-08-05 | 2007-09-14 | Airbus France Sas | PRIMARY STRUCTURE OF PERFECTED AIRCRAFT ENGINE MAT |
| FR2926788B1 (en) * | 2008-01-25 | 2010-04-02 | Snecma | ATTACHING A MULTIFLUX TURBOREACTOR TO AN AIRCRAFT |
| CN107963225B (en) * | 2017-11-30 | 2021-06-04 | 中国商用飞机有限责任公司 | Aircraft engine hanger and hanging box section thereof |
-
2017
- 2017-11-30 CN CN201711239526.5A patent/CN107963225B/en active Active
-
2018
- 2018-11-13 WO PCT/CN2018/115170 patent/WO2019105219A1/en active Application Filing
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0453360A1 (en) * | 1990-04-19 | 1991-10-23 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Aviation engine with high bypass ratio and of the type with front contra-rotating fan |
| CN101272953A (en) * | 2005-09-28 | 2008-09-24 | 法国空中客车公司 | Aircraft engine assembly including engine and mounts for the engine |
| CN101282876A (en) * | 2005-10-07 | 2008-10-08 | 法国空中客车公司 | Rigid structure for aircraft engine hanger and pylon comprising same |
| CN103101628A (en) * | 2013-02-06 | 2013-05-15 | 中国商用飞机有限责任公司 | Front mounting joint integrated with airplane hanging |
| CN106585999A (en) * | 2015-10-16 | 2017-04-26 | 空中客车运营简化股份公司 | Aircraft engine pylon |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019105219A1 (en) * | 2017-11-30 | 2019-06-06 | 中国商用飞机有限责任公司 | Aircraft engine suspension and suspension box section thereof |
| CN109606686A (en) * | 2018-12-10 | 2019-04-12 | 彩虹无人机科技有限公司 | A kind of universal unmanned plane emitter switching beam |
| CN112776993A (en) * | 2019-11-05 | 2021-05-11 | 中国航发商用航空发动机有限责任公司 | Aircraft and suspended structure thereof |
| CN112644718A (en) * | 2020-12-29 | 2021-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Unmanned aerial vehicle's engine suspended structure |
| CN113237661A (en) * | 2021-05-10 | 2021-08-10 | 中国商用飞机有限责任公司 | Device and method for measuring dynamic test load of wing-mounted engine |
| CN113237661B (en) * | 2021-05-10 | 2022-02-25 | 中国商用飞机有限责任公司 | Device and method for measuring dynamic test load of wing-mounted engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107963225B (en) | 2021-06-04 |
| WO2019105219A1 (en) | 2019-06-06 |
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