CN109774964A - Composite material fuselage pairing type frame - Google Patents
Composite material fuselage pairing type frame Download PDFInfo
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- CN109774964A CN109774964A CN201910082708.9A CN201910082708A CN109774964A CN 109774964 A CN109774964 A CN 109774964A CN 201910082708 A CN201910082708 A CN 201910082708A CN 109774964 A CN109774964 A CN 109774964A
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- 239000002131 composite material Substances 0.000 title claims abstract description 20
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 108
- 239000010959 steel Substances 0.000 claims abstract description 108
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims abstract description 22
- 239000004677 Nylon Substances 0.000 claims abstract description 8
- 229920001778 nylon Polymers 0.000 claims abstract description 8
- 230000002787 reinforcement Effects 0.000 claims abstract description 4
- 239000000463 material Substances 0.000 claims description 4
- 238000003466 welding Methods 0.000 claims description 3
- 238000003032 molecular docking Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 10
- 238000004519 manufacturing process Methods 0.000 description 8
- 238000010276 construction Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- -1 L-type frame Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000010079 rubber tapping Methods 0.000 description 1
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Abstract
The invention discloses a kind of composite material fuselage pairing type frame, it includes the fixed plate peace vertical fin butt junction location hole of frame assembly, nine snap-gauges of fuselage pairing, central wing box end rib；Frame assembly includes nylon pedestal, square steel pedestal, floor, floor reinforcement and column；Nine snap-gauges of fuselage pairing respectively include three snap-gauges of three snap-gauges of forebody, three snap-gauges of rear body and vertical fin, are fixed after fuselage pairing with nine snap-gauges；The fixed plate of central wing box end rib includes upper and lower two parts；The present invention can position completely in composite material fuselage pairing, guarantee that left and right fuselage can be docked according to the position of design, while further include aperture when hanging down horizontal tail docking.
Description
Technical field
The invention belongs to composite material tooling technical fields, and in particular to a kind of composite material fuselage pairing type frame.
Background technique
When manufacturing composite material fuselage, die joint selects to need pairing after finalization of the manufacture in the aircraft plane of symmetry.
Currently, most commonly used pairing tool is former manufacture mold, but being waited during fabrication due to fuselage has flange to cause
Original mould pairing can not be used, while in order to guarantee not influencing the manufacture of product component in assembly and can accurately determine
Position, it is therefore necessary to a kind of type frame that can carry out fuselage pairing is designed, thus it is proposed that a kind of composite material fuselage pairing
Type frame.
Summary of the invention
The purpose of the present invention is to provide composite material fuselage pairing type frame, to solve mesh mentioned above in the background art
Before, most commonly used pairing tool is former manufacture mold, but being waited during fabrication due to fuselage has flange to lead to not using original
Mold pairing, while in order to guarantee not influencing the manufacture of product component in assembly and can be accurately positioned, therefore having must
Design a kind of the problem of can carrying out the type frame of fuselage pairing.
To achieve the above object, the invention provides the following technical scheme: composite material fuselage pairing type frame, it includes frame
The fixed plate peace vertical fin butt junction location hole of component, nine snap-gauges of fuselage pairing, central wing box end rib；
Frame assembly includes nylon pedestal, square steel pedestal, floor, floor reinforcement and column；Nine cards of fuselage pairing
Plate respectively includes three snap-gauges of three snap-gauges of forebody, three snap-gauges of rear body and vertical fin, uses after fuselage pairing
Nine snap-gauges are fixed；The fixed plate of central wing box end rib includes upper and lower two parts.
Preferably, the frame assembly specifically includes column A, column B, column C, column D, column E, column F, four Kong Li
Column, twin columns bracket, cantilever shalving, column G, column H, column I, column J, column K, column L, gusset A, gusset B, support, connection
Plate A, it connecting plate B, connecting plate C, left unsplit bedplate, right unsplit bedplate, marks time, the positioning of small support, double columns, pedestal and flatness
Part.
Preferably, the left unsplit bedplate and the right unsplit bedplate include square steel, L-type frame, steel plate and small steel plate, square steel
The table top of main body is constituted with steel plate, the L-type frame is combined into square on each steel plate.
Preferably, the pedestal includes cushion block, screw rod, nut, step nut, nylon support, retaining ring and hexagon-headed bolt,
The retaining ring lower part have concave groove for and screw rod cooperate, there is locating rod on top, is inserted into the small steel plate, pedestal passes through
Screw rod and nut adjust the height of the left unsplit bedplate and the right unsplit bedplate.
Preferably, described to mark time including step nut, flatness locating piece and retaining ring.
Preferably, the column includes chassis A, square steel workpiece A, snap-gauge connector A and snap-gauge connector B, indsole
Disk A and square steel workpiece A pass through welded connecting；Snap-gauge connector A and snap-gauge connector B is connected by bolt and square steel workpiece A
It connects, chassis A is connect by screw with left unsplit bedplate and right unsplit bedplate；It is opened up on snap-gauge connector A and snap-gauge connector B
There is pin hole；Four hole column includes chassis A, square steel workpiece B, snap-gauge connector C and snap-gauge connector D, wherein chassis A with
Square steel workpiece B passes through welded connecting；Snap-gauge connector C and snap-gauge connector D is connect by bolt with square steel workpiece B, bottom
Disk A is connect by screw with left unsplit bedplate and right unsplit bedplate；Pin hole and snap-gauge connection there are four being opened on snap-gauge connector C
Pin hole there are two being opened on part D.
Preferably, the twin columns bracket includes chassis B, snap-gauge connector E, square steel workpiece C, snap-gauge connector F and card
Plate connector G, wherein chassis B and square steel workpiece C pass through welded connecting；Snap-gauge connector E, snap-gauge connector F and snap-gauge connect
Fitting G is connect by bolt with square steel workpiece C, and chassis B is connect by screw with left unsplit bedplate and right unsplit bedplate；Snap-gauge
Pin hole is provided on connector E, connecting plate B and snap-gauge connector G；Cantilever shalving is by chassis A, square steel workpiece D, snap-gauge connector
H and gusset A, wherein for chassis A and square steel workpiece D by being welded to connect, snap-gauge connector H and square steel workpiece D pass through welding
Connection, gusset A and square steel workpiece D are bolted, and are provided with pin hole on gusset A and snap-gauge connector H；Support includes bottom
Disk A, square steel workpiece E and snap-gauge connector I, wherein chassis A and square steel workpiece E is by being welded to connect, snap-gauge connector I
With square steel workpiece E by being welded to connect, pin hole is provided on snap-gauge connector I.
Preferably, the small support includes chassis A, square steel workpiece F and snap-gauge connector J, wherein chassis A and square steel
For workpiece F by being welded to connect, snap-gauge connector J and square steel workpiece F are provided with pin on snap-gauge connector J by being welded to connect
Hole；Double columns include chassis B, square steel workpiece G, snap-gauge connector K and snap-gauge connector L, wherein chassis B and square steel processing
Part G passes through welded connecting；Snap-gauge connector K, snap-gauge connector L are connect by bolt with square steel workpiece G, and chassis B passes through spiral shell
Nail is connect with left unsplit bedplate and right unsplit bedplate；Pin hole is provided on snap-gauge connector K and snap-gauge connector L.
Compared with prior art, the beneficial effects of the present invention are: the present invention can be complete in composite material fuselage pairing
Positioning guarantees that left and right fuselage can be docked according to the position of design, while further including aperture when hanging down horizontal tail docking.
Detailed description of the invention
Fig. 1 is the structural diagram of the present invention；
Fig. 2 is left unsplit bedplate structural schematic diagram of the invention；
Fig. 3 is tread structure schematic diagram of the invention；
Fig. 4 is pillar construction schematic diagram of the invention；
Fig. 5 is four hole pillar construction schematic diagrames of the invention；
Fig. 6 is twin columns supporting structure schematic diagram of the invention；
Fig. 7 is cantilever shalving structural schematic diagram of the invention；
Fig. 8 is bearing structure illustration of the invention；
Fig. 9 is small bearing structure illustration of the invention；
Figure 10 is double pillar construction schematic diagrames of the invention；
Figure 11 is frame assembly structural schematic diagram of the invention；
Figure 12 is another embodiment of the invention structural schematic diagram；
In figure: 1, column A；2, column B；3, column C；4, column D；5, column E；6, column F；7, four Kong Lizhu；8, double
Column holder；9, cantilever shalving；10, column G；11, column H；12, column I；13, column J；14, column K；15, column L；16, gusset
A；17, gusset B；18, support；19, connecting plate A；20, connecting plate B；21, connecting plate C；22, left unsplit bedplate；23, right integral bottom
Seat；24, it marks time；25, small support；26, double columns；27, pedestal；28, flatness locating piece；30, square steel；31, L-type frame；32, steel
Plate；33, small steel plate；34, cushion block；35, screw rod；36, nut；37, step nut；38, nylon support；39, retaining ring；40, chassis
A；41, square steel workpiece A；42, snap-gauge connector A；43, snap-gauge connector B；44, square steel workpiece B；45, snap-gauge connector C；
46, snap-gauge connector D；47, chassis B；48, snap-gauge connector E；49, square steel workpiece C；50, snap-gauge connector F；51, snap-gauge
Connector G；52, square steel workpiece D；53, snap-gauge connector H；54, square steel workpiece E；55, snap-gauge connector I；56, square steel adds
Workpiece F；57, snap-gauge connector J；58, square steel workpiece G；59, snap-gauge connector K；60, snap-gauge connector L；201, the first from left number
Snap-gauge；202, right No.1 snap-gauge；203, the second from left snap-gauge；204, right No. two snap-gauges；205, left No. three snap-gauges；206, right No. three cards
Plate；207, left No. four snap-gauges；208, right No. four snap-gauges；209, left No. ten snap-gauges；210, right No. ten snap-gauges；211, left No. six cards
Plate；212, right No. six snap-gauges；213, left No. seven snap-gauges；214, right No. seven snap-gauges；215, left No. eight snap-gauges；216, right No. eight cards
Plate；217, left No. nine snap-gauges；218, right No. nine snap-gauges.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
Embodiment one
Fig. 1-Figure 11 is please referred to, the present invention provides a kind of technical solution: composite material fuselage pairing type frame, it includes frame
The fixed plate peace vertical fin butt junction location hole of component, nine snap-gauges of fuselage pairing, central wing box end rib；
Frame assembly includes nylon pedestal, square steel pedestal, floor, floor reinforcement and column；Nine cards of fuselage pairing
Plate respectively includes three snap-gauges of three snap-gauges of forebody, three snap-gauges of rear body and vertical fin, uses after fuselage pairing
Nine snap-gauges are fixed；The fixed plate of central wing box end rib includes upper and lower two parts.
In the present embodiment, it is preferred that frame assembly specifically include column A1, column B2, column C3, column D4, column E5,
Column F6, it four hole columns 7, twin columns bracket 8, cantilever shalving 9, column G10, column H11, column I12, column J13, column K14, stands
Column L15, gusset A16, gusset B17, support 18, connecting plate A19, connecting plate B20, connecting plate C21, left unsplit bedplate 22, the right side are whole
Body pedestal 23, mark time 24, small support 25, double columns 26, pedestal 27 and flatness locating piece 28, as shown in Figure 1.
Wherein left unsplit bedplate 22 and right unsplit bedplate 23 include square steel 30, L-type frame 31, steel plate 32 and small steel plate 33, side
Steel 30 and steel plate 32 constitute the table top of main body, and L-type frame 31 is combined into square on each steel plate 32, rise and reinforce steel plate 32
Local stiffness effect, small steel plate 33 are mainly used for the positioning of pedestal 27, as shown in Figure 2.
Pedestal 27 includes cushion block 34, screw rod 35, nut 36, step nut 37, nylon support 38, retaining ring 39 and turret head spiral shell
Bolt, 39 lower part of retaining ring have concave groove for and screw rod 35 cooperation, there is locating rod on top, is inserted into small steel plate 33, pedestal 27
The height of left unsplit bedplate 22 and right unsplit bedplate 23 is adjusted by screw rod 35 and nut 36, as shown in Figure 3.
Mark time 24 include L-type material bracket, L aperture angle section and fixation steel plate be first welded into L with L-type material during the installation process
Section bar support, then fixation steel plate is welded on L-type material bracket, then L aperture angle section is welded on fixation steel plate, is then used
Screw tap tapping on the square steel 30 of unsplit bedplate will be marked time with bolt and 24 be connected to left unsplit bedplate 22 and right unsplit bedplate 23
On, as shown in Figure 4.
Flatness locating piece 28 is made of 16 locating pieces, its main function is measured with locator is recorded a demerit, and is passed through
The screw rod 35 and nut 36 of pedestal 27 are adjusted, guaranteeing that left unsplit bedplate 22 and right unsplit bedplate 23 are in horizontality；
In the present embodiment, it is preferred that column includes that chassis A40, square steel workpiece A41, snap-gauge connector A42 and snap-gauge connect
Fitting B43, wherein chassis A40 and square steel workpiece A41 pass through welded connecting；Snap-gauge connector A42 and snap-gauge connector B43 is logical
It crosses bolt to connect with square steel workpiece A41, chassis A40 is connect by screw with left unsplit bedplate 22 and right unsplit bedplate 23；Card
Pin hole is offered on plate connector A42 and snap-gauge connector B43, as shown in Figure 5；
Four hole columns 7 include chassis A40, square steel workpiece B44, snap-gauge connector C45 and snap-gauge connector D46, wherein
Chassis A40 and square steel workpiece B44 pass through welded connecting；Snap-gauge connector C45 and snap-gauge connector D46 passes through bolt and square steel
Workpiece B44 connection, chassis A40 are connect by screw with left unsplit bedplate 22 and right unsplit bedplate 23；On snap-gauge connector C45
It opens there are four pin hole, is opened on snap-gauge connector D46 there are two pin hole, it is as shown in Figure 6 for fixing chuck plate.
In the present embodiment, it is preferred that twin columns bracket 8 includes chassis B47, snap-gauge connector E48, square steel workpiece C49, card
Plate connector F50 and snap-gauge connector G51, wherein chassis B47 and square steel workpiece C49 pass through welded connecting；Snap-gauge connector
E48, snap-gauge connector F50 and snap-gauge connector G51 connects by bolt with square steel workpiece C49, chassis B47 pass through screw and
Left unsplit bedplate 22 and right unsplit bedplate 23 connect；It is provided on snap-gauge connector E48, connecting plate B20 and snap-gauge connector G51
Pin hole is used for fixing chuck plate, as shown in Figure 7；
Cantilever shalving 9 is by chassis A40, square steel workpiece D52, snap-gauge connector H53 and gusset A16, wherein chassis A40 and
Square steel workpiece D52 by being welded to connect, snap-gauge connector H53 and square steel workpiece D52 by being welded to connect, gusset A16 and
Square steel workpiece D52 is bolted, and is provided with pin hole on gusset A16 and snap-gauge connector H53, is used for fixing chuck plate, such as
Shown in Fig. 8；
Support 18 includes chassis A40, square steel workpiece E54 and snap-gauge connector I55, wherein chassis A40 and square steel processing
By being welded to connect, snap-gauge connector I55 and square steel workpiece E54 are opened on snap-gauge connector I55 part E54 by being welded to connect
There is pin hole, is used for fixing chuck plate, as shown in Figure 9.
In the present embodiment, it is preferred that small support 25 includes chassis A40, square steel workpiece F56 and snap-gauge connector J57,
In, by being welded to connect, snap-gauge connector J57 and square steel workpiece F56 are connected by welding by chassis A40 and square steel workpiece F56
It connects, is provided with pin hole on snap-gauge connector J57, be used for fixing chuck plate, as shown in Figure 10；
Double columns 26 include chassis B47, square steel workpiece G58, snap-gauge connector K59 and snap-gauge connector L60, wherein
Chassis B47 and square steel workpiece G58 pass through welded connecting；Snap-gauge connector K59, snap-gauge connector L60 pass through bolt and square steel
Workpiece G58 connection, chassis B47 are connect by screw with left unsplit bedplate 22 and right unsplit bedplate 23；Snap-gauge connector K59 and
It is provided with pin hole on snap-gauge connector L60, as shown in figure 11.
Embodiment two
Snap-gauge component is by the first from left snap-gauge 201, right No.1 snap-gauge 202, the second from left snap-gauge 203, right No. two snap-gauges 204, a left side
No. three snap-gauges 205, right No. three snap-gauges 206, left No. four snap-gauges 207, right No. four snap-gauges 208, left No. six snap-gauges 211, right No. six cards
Plate 212, left No. seven snap-gauges 213, right No. seven snap-gauges 214, left No. eight snap-gauges 215, right No. eight snap-gauges 216, left No. nine snap-gauges 217,
Right No. nine snap-gauges 218, left No. ten snap-gauges 209, right No. ten snap-gauges 210 form；
The first from left snap-gauge 201, the second from left snap-gauge 203, left No. three snap-gauges 205, left No. four snap-gauges 207, left No. six snap-gauges
211, left No. nine snap-gauges 217 and column A1, left No. seven snap-gauges 213, left No. eight snap-gauges 215 column B2, column C3, column D4, are stood
Column E5, column F6, column G10, column H11, column I12, column J13, column K14, pass through burnished bolt between column L15 and connect
It connects；
Right No.1 snap-gauge 202, right No. two snap-gauges 204, right No. three snap-gauges 206, right No. four snap-gauges 208, right No. six snap-gauges
212, the erection sequence of right No. seven snap-gauges 214, right No. eight snap-gauges 216, right No. nine snap-gauges 218 is, after left snap-gauge is installed,
Left fuselage is placed into left snap-gauge, using two positioning finger settings of left No. ten snap-gauges 209, right fuselage is preloaded onto left fuselage,
Then from front to back, it is sequentially clamped in snap-gauge, it is specific as shown in figure 12.
It although an embodiment of the present invention has been shown and described, for the ordinary skill in the art, can be with
A variety of variations, modification, replacement can be carried out to these embodiments without departing from the principles and spirit of the present invention by understanding
And modification, the scope of the present invention is defined by the appended.
Claims (8)
1. composite material fuselage pairing type frame, it is characterised in that: it includes nine snap-gauges, centers of frame assembly, fuselage pairing
The fixed plate peace vertical fin butt junction location hole of wing box end rib；
Frame assembly includes nylon pedestal, square steel pedestal, floor, floor reinforcement and column；Nine snap-gauges of fuselage pairing point
Not Bao Kuo three snap-gauges of forebody, three snap-gauges of rear body and vertical fin three snap-gauges, with nine after fuselage pairing
Snap-gauge is fixed；The fixed plate of central wing box end rib includes upper and lower two parts.
2. composite material fuselage pairing type frame according to claim 1, it is characterised in that: the frame assembly specifically includes
Column A (1), column B (2), column C (3), column D (4), column E (5), column F (6), four Kong Lizhu (7), twin columns bracket
(8), cantilever shalving (9), column G (10), column H (11), column I (12), column J (13), column K (14), column L (15), angle
Plate A (16), gusset B (17), support (18), connecting plate A (19), connecting plate B (20), connecting plate C (21), left unsplit bedplate
(22), right unsplit bedplate (23), mark time (24), small support (25), double columns (26), pedestal (27) and flatness locating piece
(28)。
3. composite material fuselage pairing type frame according to claim 2, it is characterised in that: the left unsplit bedplate (22) and
The right unsplit bedplate (23) includes square steel (30), L-type frame (31), steel plate (32) and small steel plate (33), square steel (30) and steel plate
(32) table top of main body is constituted, the L-type frame (31) is combined into square on each steel plate (32).
4. composite material fuselage pairing type frame according to claim 2, it is characterised in that: the pedestal (27) includes cushion block
(34), screw rod (35), nut (36), step nut (37), nylon support (38), retaining ring (39) and hexagon-headed bolt, the gear
Circle (39) lower part have concave groove for and screw rod (35) cooperate, there is locating rod on top, is inserted into the small steel plate (33), bottom
Seat (27) adjusts the height of the left unsplit bedplate (22) and the right unsplit bedplate (23) by screw rod (35) and nut (36)
Degree.
5. composite material fuselage pairing type frame according to claim 2, it is characterised in that: mark time (24) include L-type
Material bracket, L aperture angle section and fixation steel plate.
6. composite material fuselage pairing type frame according to claim 2, it is characterised in that: the column includes chassis A
(40), square steel workpiece A (41), snap-gauge connector A (42) and snap-gauge connector B (43), wherein chassis A (40) and square steel are processed
Part A (41) passes through welded connecting；Snap-gauge connector A (42) and snap-gauge connector B (43) passes through bolt and square steel workpiece A (41)
Connection, chassis A (40) are connect by screw with left unsplit bedplate (22) and right unsplit bedplate (23)；Snap-gauge connector A (42) and
Pin hole is offered on snap-gauge connector B (43)；Four Kong Lizhu (7) includes chassis A (40), square steel workpiece B (44), card
Plate connector C (45) and snap-gauge connector D (46), wherein chassis A (40) and square steel workpiece B (44) pass through welded connecting；Card
Plate connector C (45) and snap-gauge connector D (46) is connect by bolt with square steel workpiece B (44), and chassis A (40) passes through screw
It is connect with left unsplit bedplate (22) and right unsplit bedplate (23)；Pin hole and snap-gauge connection there are four being opened on snap-gauge connector C (45)
Pin hole there are two being opened on part D (46).
7. composite material fuselage pairing type frame according to claim 2, it is characterised in that: the twin columns bracket (8) includes
Chassis B (47), snap-gauge connector E (48), square steel workpiece C (49), snap-gauge connector F (50) and snap-gauge connector G (51),
Middle chassis B (47) and square steel workpiece C (49) pass through welded connecting；Snap-gauge connector E (48), snap-gauge connector F (50) and card
Plate connector G (51) is connect by bolt with square steel workpiece C (49), and chassis B (47) passes through screw and left unsplit bedplate (22)
It is connected with right unsplit bedplate (23)；Pin is provided on snap-gauge connector E (48), connecting plate B (20) and snap-gauge connector G (51)
Hole；Cantilever shalving (9) is by chassis A (40), square steel workpiece D (52), snap-gauge connector H (53) and gusset A (16), wherein chassis A
(40) and square steel workpiece D (52) is by being welded to connect, and snap-gauge connector H (53) and square steel workpiece D (52) are connected by welding
It connects, gusset A (16) and square steel workpiece D (52) are bolted, and are provided on gusset A (16) and snap-gauge connector H (53)
Pin hole；Support (18) includes chassis A (40), square steel workpiece E (54) and snap-gauge connector I (55), wherein chassis A (40) and
Square steel workpiece E (54) is by being welded to connect, and snap-gauge connector I (55) and square steel workpiece E (54) are by being welded to connect, snap-gauge
Connector I is provided with pin hole on (55).
8. composite material fuselage pairing type frame according to claim 2, it is characterised in that: the small support (25) includes bottom
Disk A (40), square steel workpiece F (56) and snap-gauge connector J (57), wherein chassis A (40) and square steel workpiece F (56) pass through
It is welded to connect, snap-gauge connector J (57) and square steel workpiece F (56) are provided with pin on snap-gauge connector J (57) by being welded to connect
Hole；Double columns (26) include chassis B (47), square steel workpiece G (58), snap-gauge connector K (59) and snap-gauge connector L (60),
Wherein, chassis B (47) and square steel workpiece G (58) pass through welded connecting；Snap-gauge connector K (59), snap-gauge connector L (60) are logical
It crosses bolt to connect with square steel workpiece G (58), chassis B (47) passes through screw and left unsplit bedplate (22) and right unsplit bedplate (23)
Connection；Pin hole is provided on snap-gauge connector K (59) and snap-gauge connector L (60).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910082708.9A CN109774964A (en) | 2019-01-28 | 2019-01-28 | Composite material fuselage pairing type frame |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910082708.9A CN109774964A (en) | 2019-01-28 | 2019-01-28 | Composite material fuselage pairing type frame |
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| CN109774964A true CN109774964A (en) | 2019-05-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910082708.9A Pending CN109774964A (en) | 2019-01-28 | 2019-01-28 | Composite material fuselage pairing type frame |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112722318A (en) * | 2021-01-18 | 2021-04-30 | 成都纵横鹏飞科技有限公司 | Unmanned aerial vehicle assembly and debugging rack |
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Application publication date: 20190521 |