CN214084720U - Light composite material aircraft frame beam structure standard bonding pi type spare - Google Patents
Light composite material aircraft frame beam structure standard bonding pi type spare Download PDFInfo
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- CN214084720U CN214084720U CN202022248606.0U CN202022248606U CN214084720U CN 214084720 U CN214084720 U CN 214084720U CN 202022248606 U CN202022248606 U CN 202022248606U CN 214084720 U CN214084720 U CN 214084720U
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Abstract
The utility model discloses a light-duty combined material aircraft frame roof beam structure standard pi type spare that bonds, including pi type connecting piece, pi type connecting piece is "pi" type, pi type spare comprises pi type connecting piece horizontal arrangement combination more than 2. The utility model discloses simple structure, convenient operation, streamlined production that can be quick has practiced thrift the design cost of manufacture greatly, and in the structure of various models, different curved surfaces that can be general, has not only reduced aircraft designer's design cycle, has also reduced cost of manufacture and cycle.
Description
Technical Field
The utility model belongs to the technical field of the connecting piece, concretely relates to light-duty combined material aircraft frame roof beam structure standard bonding pi type spare.
Background
The existing stage light and small aircraft (including man and unmanned) has small volume and high requirements on specific strength and specific stiffness, and in order to improve the comprehensive performance of the aircraft, wings, empennage and the like of the aircraft are produced by adopting an integrated glue joint curing molding process form, namely, frame beams are carved by standard composite material plates, skins are molded in a mold cavity, and the upper and lower wing surface skins and the frame beam structure of the aircraft adopt an integrated glue joint curing form in the mold; according to the mode, the production efficiency is improved, the cost of the assembly tool is reduced, and the comprehensive performance of the aircraft is improved. To achieve this effect, there are two process forms: 1. the frame beam is of a plate type structure formed by cutting standard plates; 2. and the frame beam is flanged in a mode of opening the die.
The inventor finds that the prior arts have at least the following technical problems in the practical use process:
1. the frame beam is of a plate type structure formed by cutting a standard plate, the bonding surface of the skin and the frame beam is narrow in the mode, and the bonding strength can be ensured only by improving the bonding glue; the defect is that the operation difficulty is high, the requirement on the proficiency of personnel is high, the quality is not easy to control, the potential safety hazard is large, and the structural weight of the aircraft is increased;
2. the frame roof beam adopts the form of die sinking to carry out the turn-ups preparation, and the turn-ups can greatly increased covering and the bonding area of frame roof beam, has greatly improved bonding strength and reliability, and the defect is no matter adopt "I" roof beam or "C word" roof beam, all need make assembling die processing preparation, and the processing degree of difficulty is big, production cycle length, and the frame roof beam mould need all be reprocessed in the change of covering technology, has improved the research and development manufacturing cost of aircraft.
Disclosure of Invention
For overcoming the existence not enough, the utility model discloses an inventor is through long-term exploration attempt and experimental and the effort many times, constantly reform transform and the innovation, has provided a light-duty combined material aircraft frame roof beam structure standard bonding pi type spare, its simple structure, convenient operation, streamlined production that can be quick, has practiced thrift the design cost of manufacture greatly, and can general various models, in the structure of different curved surfaces, has not only reduced aircraft designer's design cycle, has also reduced cost of manufacture and cycle.
In order to realize the purpose, the utility model adopts the technical scheme that: the standard bonding pi-shaped piece of the frame beam structure of the light composite material aircraft comprises a pi-shaped connecting piece, wherein the pi-shaped connecting piece is in a pi shape, and the pi-shaped piece is formed by horizontally arranging and combining more than 2 pi-shaped connecting pieces.
According to a light-duty combined material aircraft frame roof beam structure standard pi type spare that bonds, its further preferred technical scheme is: the side of the pi-shaped piece is provided with a through hole or is in a closed shape.
According to a light-duty combined material aircraft frame roof beam structure standard pi type spare that bonds, its further preferred technical scheme is: the number of the through holes is one less than that of the pi-shaped connecting pieces.
According to a light-duty combined material aircraft frame roof beam structure standard pi type spare that bonds, its further preferred technical scheme is: the upper bottom surface of the pi-shaped piece is in a downward concave arc shape.
According to a light-duty combined material aircraft frame roof beam structure standard pi type spare that bonds, its further preferred technical scheme is: the pi-shaped piece is made of synthetic fibers.
According to a light-duty combined material aircraft frame roof beam structure standard pi type spare that bonds, its further preferred technical scheme is: and a channel is reserved on the inner side of the pi-shaped piece.
According to a light-duty combined material aircraft frame roof beam structure standard pi type spare that bonds, its further preferred technical scheme is: and two sides of the pi-shaped piece are also provided with groove lines.
According to a light-duty combined material aircraft frame roof beam structure standard pi type spare that bonds, its further preferred technical scheme is: the slot line is arranged below the through hole.
According to a light-duty combined material aircraft frame roof beam structure standard pi type spare that bonds, its further preferred technical scheme is: the number of the groove lines on each side of the pi-shaped piece is 2.
According to a light-duty combined material aircraft frame roof beam structure standard pi type spare that bonds, its further preferred technical scheme is: the upper bottom surface of the pi-shaped piece is provided with grooves, and the number of the grooves is the same as that of the through holes or the upper bottom surface is closed.
Compared with the prior art, the technical scheme of the utility model have following advantage beneficial effect:
1. the pi-shaped part is a connecting piece, can be produced in a production line rapidly, greatly saves the design and manufacturing cost, and can be used in structures with various types and different curved surfaces; the design cycle of an aircraft designer is reduced, and the manufacturing cost and cycle are also reduced; compared with the current frame beam with a plate type structure, the operation is simple, the requirement on personnel is low, the bonding strength is improved by about 95 percent, the bonding area of the plate type structure is small, and the surface-to-line bonding is changed into the surface-to-surface bonding by adopting the Pi-shaped piece through the strength of the T-shaped piece on the basis of the plate type structure, so that the technical reliability is greatly improved; compared with the existing I-shaped beam and C-shaped beam, the method has the advantages that the mold cost of the beam is completely saved, the manufacturing cost is saved, and the mold and manufacturing cost of the frame beam are not needed to be worried when the design of the aircraft changes. The use of the pi-shaped piece can achieve the same strength of an I-shaped beam and a C-shaped beam.
2. The through hole of the pi-shaped piece can enable the pi-shaped piece to change according to the curvature of a surface to be bonded, when the pi-shaped piece is bonded with a curved surface with larger curvature, the through hole can provide a compressible space or increase a stretched space no matter in the positive direction or the negative direction, and the bonding problem caused by the change of the curved surface is not worried.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 is a schematic structural view of the pi-shaped part of the present invention.
Fig. 2 is a schematic structural view of the pi-shaped connector of the present invention.
Fig. 3 is a side view of fig. 1.
Fig. 4 is a schematic view of the combination of the pi-shaped member and the frame beam.
FIG. 5 is a schematic diagram of the bonding and clamping of the skin and the frame beam.
The labels in the figure are respectively: 1. a pi-shaped connector; 2. a pi-shaped piece; 3. a frame beam; 4. covering a skin; 5. a through hole; 6. a slot line; 7. and an upper bottom surface.
Detailed Description
To make the objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention are clearly and completely described below, and it is obvious that the described embodiments are some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention. Thus, the detailed description of the embodiments of the present invention provided below is not intended to limit the scope of the claimed invention, but is merely representative of selected embodiments of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it may not be further defined and explained in subsequent figures.
Example (b):
as shown in figures 1-5, the utility model discloses a light-duty combined material aircraft frame roof beam structure standard bonding pi type spare, including pi type connecting piece 1, pi type connecting piece 1 is "pi" type, pi type spare 2 comprises pi type connecting piece 1 horizontal arrangement combination more than 2.
Specifically, the side of pi type spare 2 is provided with the through-hole or is the closure, the quantity of through-hole is less one than pi type connecting piece 1, the last bottom surface of pi type spare 2 is the arc of undercut, pi type spare 2 adopts synthetic fiber such as carbon fiber or nylon to make, a passageway is left to the inboard of pi type spare 2 for place frame roof beam 3.
It is worth mentioning that two sides of the pi-shaped part 2 are also provided with groove lines 6, the groove lines 6 are arranged below the through holes 5, the number of the groove lines on each side of the pi-shaped part 2 is 2, the upper bottom surface 7 of the pi-shaped part 2 is provided with grooves, and the number of the grooves is the same as that of the through holes 5 or the upper bottom surface is closed.
The pi-shaped part 2 is a structural body with a shape similar to pi, and can be widely used in a frame beam 3 and skin 4 structure of an aircraft; taking a certain small aircraft at the present stage as an example, after the frame beam 3 of the aircraft is carved by a carving machine, the pi-shaped piece 2 and the frame beam 3 are bonded, and then mold closing glue is simply smeared above the pi-shaped piece 2 to bond and close the mold.
The pi-shaped part 2 is a composite material part, is made of a carbon fiber, glass fiber or nylon reinforced matrix composite material and is mainly used for bonding and die assembly of a frame beam 3 structure and a skin 4 structure of a composite material aircraft so as to improve the bonding strength between the frame beam 3 and the skin 4. As shown in fig. 3, the lower part of the pi-shaped piece 2 is bonded with a frame beam 3 made of a plate, the pi-shaped piece 2 is adapted according to the standard plate in the market and is tightly matched, the bonding part of the frame beam 3 is coated with resin glue, and the pi-shaped piece 2 can be directly pre-bonded and bonded with the pi-shaped piece in a pre-assembling way, and the bonding strength is high after curing (as shown in fig. 4).
After the pi-shaped piece 2 and the frame beam 3 are combined (as shown in fig. 4), mold closing operation can be started, and the other side of the pi-shaped piece 2 is coated with mold closing glue to perform bonding and mold closing operation of the skin 4 and the frame beam 3 (as shown in fig. 5). The special design is adopted above the pi-shaped piece 2, after mold closing glue is simply coated, the glue can be blocked from flowing outwards during mold closing due to the fact that the bonding surface has taper, and bonding reliability is improved.
The pi-shaped part 2 is a standard bonding part, can be produced quickly in a flow line, greatly saves the design and manufacturing cost, and can be universally used in structures with various models and different curved surfaces; the design cycle of an aircraft designer is reduced, and the manufacturing cost and cycle are also reduced; compared with the current frame beam 3 with a plate type structure, the operation is simple, the requirement on personnel is low, the bonding strength is improved by about 95 percent, the bonding area of the plate type structure is small, and the surface-to-line bonding is changed into the surface-to-surface bonding by adopting the Pi-shaped part 2 and the T-shaped part strength on the basis of the plate type structure, so that the technical reliability is greatly improved; compared with the existing I-shaped beam and C-shaped beam, the method has the advantages that the mold cost of the beam is completely saved, the manufacturing cost is saved, and the mold and manufacturing cost of the frame beam 3 are not needed to be worried when the design of the aircraft changes. The use of the pi-shaped member 2 can achieve the same strength of an I-shaped beam and a C-shaped beam.
The through holes 5 of the pi-shaped part 2 can enable the pi-shaped part 2 to change according to the curvature of a surface to be bonded, when the pi-shaped part 2 is bonded to a curved surface with larger curvature, the through holes 5 can provide a compressible space or increase a stretched space no matter in the positive direction or the negative direction, and the bonding problem caused by the change of the curved surface is not worried.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
In the present disclosure, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact between the first and second features, or may comprise contact between the first and second features not directly. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. The first feature being "under," "below," and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or merely indicates that the first feature is at a lower level than the second feature.
The above is only a preferred embodiment of the present invention, and it should be noted that the above preferred embodiment should not be considered as limiting the present invention, and the protection scope of the present invention should be subject to the scope defined by the claims. It will be apparent to those skilled in the art that various modifications and enhancements can be made without departing from the spirit and scope of the invention, and such modifications and enhancements are intended to be within the scope of the invention.
Claims (10)
1. The light composite material aircraft frame beam structure standard bonding pi-shaped piece is characterized by comprising a pi-shaped connecting piece (1), wherein the pi-shaped connecting piece (1) is in a pi shape, and the pi-shaped piece (2) is formed by horizontally arranging and combining more than 2 pi-shaped connecting pieces (1).
2. A light composite material aircraft frame beam structure standard bonding pi-shaped member according to claim 1, characterized in that the side of the pi-shaped member (2) is provided with a through hole or is closed.
3. A light composite material aircraft frame beam structure standard bonding pi-type spare of claim 2, characterized in that, the quantity of the through-hole is one less than the quantity of pi-type connecting piece (1).
4. A light composite material aircraft frame beam structure standard bonding pi-shaped member as claimed in claim 3, characterized in that the upper bottom surface of the pi-shaped member (2) is in the shape of an arc sunken downwards.
5. A light composite material aircraft frame beam structure standard bonding pi-shaped member according to claim 4, characterized in that the pi-shaped member (2) is made of synthetic fiber.
6. A light composite material aircraft frame beam structure standard bonding pi-shaped member according to any one of claims 1 to 5, characterized in that a channel is left on the inner side of the pi-shaped member (2).
7. A light composite material aircraft frame beam structure standard bonding pi-shaped member according to claim 6, characterized in that the pi-shaped member (2) is also provided with slot lines (6) on two sides.
8. A light composite material aircraft frame beam structure standard bonding pi-type spare of claim 7, characterized in that, the slot line (6) sets up under through-hole (5).
9. A light composite material aircraft frame beam structure standard bonding pi-shaped member according to claim 8, characterized in that the number of the groove lines (6) on each side of the pi-shaped member (2) is 2.
10. A light composite material aircraft frame beam structure standard bonding pi-shaped member according to claim 4, characterized in that the upper bottom surface of the pi-shaped member (2) is provided with grooves or the upper bottom surface of the pi-shaped member (2) is closed, and the number of the grooves is the same as the number of the through holes (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022248606.0U CN214084720U (en) | 2020-10-12 | 2020-10-12 | Light composite material aircraft frame beam structure standard bonding pi type spare |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202022248606.0U CN214084720U (en) | 2020-10-12 | 2020-10-12 | Light composite material aircraft frame beam structure standard bonding pi type spare |
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| CN214084720U true CN214084720U (en) | 2021-08-31 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114476016A (en) * | 2022-03-04 | 2022-05-13 | 沃飞长空科技(成都)有限公司 | Method for connecting components and aircraft |
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2020
- 2020-10-12 CN CN202022248606.0U patent/CN214084720U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114476016A (en) * | 2022-03-04 | 2022-05-13 | 沃飞长空科技(成都)有限公司 | Method for connecting components and aircraft |
| CN114476016B (en) * | 2022-03-04 | 2024-04-12 | 成都沃飞天驭科技有限公司 | Method for connecting components and aircraft |
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