CN219927958U - Large-load light stealth composite material fuselage structure - Google Patents
Large-load light stealth composite material fuselage structure Download PDFInfo
- Publication number
- CN219927958U CN219927958U CN202321352639.7U CN202321352639U CN219927958U CN 219927958 U CN219927958 U CN 219927958U CN 202321352639 U CN202321352639 U CN 202321352639U CN 219927958 U CN219927958 U CN 219927958U
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- frame
- fuselage
- wing
- front fuselage
- butt joint
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- 239000002131 composite material Substances 0.000 title claims abstract description 14
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 27
- 210000001503 joint Anatomy 0.000 claims abstract description 22
- 230000002787 reinforcement Effects 0.000 claims description 6
- 125000006850 spacer group Chemical group 0.000 claims description 5
- 239000000463 material Substances 0.000 claims 1
- 230000007797 corrosion Effects 0.000 abstract description 3
- 238000005260 corrosion Methods 0.000 abstract description 3
- 238000012423 maintenance Methods 0.000 abstract description 3
- 238000005192 partition Methods 0.000 abstract description 3
- 230000005540 biological transmission Effects 0.000 abstract 1
- 238000005452 bending Methods 0.000 description 4
- 238000005728 strengthening Methods 0.000 description 4
- 230000008093 supporting effect Effects 0.000 description 4
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000011084 recovery Methods 0.000 description 3
- 238000012546 transfer Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 239000003351 stiffener Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Moulding By Coating Moulds (AREA)
Abstract
The utility model provides a large-load light stealth composite material fuselage structure, which comprises a front fuselage inner frame and a front fuselage outer skin structure at the outer side of the front fuselage inner frame; the front fuselage inner frame comprises a frame and a longitudinal element on the periphery of the frame, the frame comprises a front fuselage butt joint frame, a front fuselage front reinforcing frame, a wing front connecting frame, a wing rear connecting frame and a front fuselage middle reinforcing frame which are sequentially arranged from the tail to the nose direction, and at least one partition frame is uniformly distributed on one side of the nose. The utility model has the advantages of clear force transmission path of the fuselage structure, simple and reliable structure, light weight, low cost, convenient use and maintenance, good corrosion resistance and fatigue resistance, low crack propagation rate, adaptability to the working conditions of high strength and complex load condition and ensured service life.
Description
Technical Field
The utility model belongs to the technical field of aerospace, and particularly relates to a high-load light stealth composite material fuselage structure.
Background
The fuselage is the main loading component of both civil aircraft and military aircraft, and is also responsible for connecting the aircraft components into a whole. Therefore, the fuselage is subjected to loads of its own, as well as loads transferred to the fuselage by other components connected thereto. Generally, the lift force generated by the fuselage is small, but the zero lift resistance is large, so that the maximum cross-sectional area of the fuselage is as small as possible, which is beneficial to improving the performance of the aircraft. Along with the development of aviation technology, not only is good aerodynamic performance required, but also good stealth performance is required, the stealth performance can improve the survivability of a military aircraft or a special-purpose aircraft, the cross-sectional area of a fuselage has a large influence on loading requirements, but when the fuselage with the stealth performance requirement in the prior art ensures a certain volume, the surface area of the fuselage is large, the specular reflection and the scattering cross section of edge diffraction are large, the stealth performance is poor, the generated friction resistance is increased, and the resistance can influence the flight speed of the aircraft. While fuselage with smaller fuselage cross-sectional area generally has better stealth performance, in order to improve structural strength and stability, the internal frame structure is complex and occupies a larger proportion of space, directly affecting loading capacity, and therefore, it is necessary to improve the existing fuselage structure.
Disclosure of Invention
In view of the above, the present utility model is directed to overcoming the defects in the prior art, and providing a high-load light stealth composite fuselage structure.
In order to achieve the above purpose, the technical scheme of the utility model is realized as follows:
a high-load light stealth composite material fuselage structure comprises a front fuselage inner frame and a front fuselage outer skin structure on the outer side of the front fuselage inner frame; the front fuselage inner frame comprises a frame and a longitudinal element at the periphery of the frame, the frame comprises a front fuselage butt joint frame, a front fuselage front reinforcing frame, a wing front connecting frame, a wing rear connecting frame and a front fuselage middle reinforcing frame which are sequentially arranged from the tail to the head direction,
at least one bulkhead is distributed on one side of the nose towards the front frame, between the front frame and the rear frame, between the rear frame and the middle frame and between the middle frame and the middle frame;
the front fuselage butt joint frame is connected with the front fuselage front reinforcement frame, the front fuselage front reinforcement frame is connected with the wing front connection frame, the front fuselage butt joint frame is connected with the wing front connection frame, and the wing front connection frame is connected with the wing rear connection frame through short trusses;
the longitudinal element comprises a plurality of stringers arranged along the length direction of the fuselage, a front fuselage butt joint frame, a front fuselage front reinforcing frame and a front fuselage middle reinforcing frame, which are all fixed with the stringers, and the outer edges of the front fuselage butt joint frame, the front fuselage front reinforcing frame and the front fuselage middle reinforcing frame are all provided with flanging structures attached to the outer skin structure of the front fuselage.
Further, wing connectors are arranged on the wing front connecting frame, the wing rear connecting frame and the spacer frame between the wing front connecting frame and the wing rear connecting frame.
Further, the front fuselage outer skin structure is glue riveted with the flanging structures of the frames into a whole.
Further, the forward fuselage outer skin structure is adhesively riveted to each stringer.
Further, the front fuselage outer skin structure is integrally formed by prepreg.
Further, the longitudinal member includes four stringers disposed about the upper left, lower left, upper right and lower right of the frame.
Furthermore, a slot is arranged on the middle reinforcing frame of the front fuselage or the rear connecting frame of the wing, and a plug matched with the slot is arranged on the stringer.
Further, each of the stringers is integrally formed from a prepreg.
Compared with the prior art, the utility model has the following advantages:
in the fuselage structure provided by the utility model, the longitudinal members effectively bear the axial force generated when the fuselage is bent, the longitudinal members also have supporting effect on the skin, the critical stress of the skin in compression and shear instability is improved, the aerodynamic force born by the longitudinal members and acting on the skin is transferred to the reinforcing frame, the butt joint frame, the connecting frame and each partition frame, the fuselage structure has clear force transfer path, simple and reliable structure, light weight, low cost, convenient use and maintenance, good corrosion resistance and fatigue resistance, low crack expansion rate, adaptability to the working conditions of high strength and complex load condition and ensured service life.
Drawings
The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the utility model and do not constitute an undue limitation on the utility model. In the drawings:
FIG. 1 is a schematic diagram of the structure of the present utility model;
fig. 2 is a schematic view of the present utility model in an exploded state.
Detailed Description
It should be noted that, without conflict, the embodiments of the present utility model and features of the embodiments may be combined with each other.
In the description of the utility model, it should be understood that the terms "center," "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships that are based on the orientation or positional relationships shown in the drawings, merely to facilitate describing the utility model and simplify the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be configured and operate in a particular orientation, and therefore should not be construed as limiting the utility model. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the utility model, unless otherwise indicated, the meaning of "a plurality" is two or more.
In the description of the utility model, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. For example, the parts of the frame structure which are not explicitly connected in a specific manner can be connected by connecting pieces, or can be bonded or connected in other manners, so long as the fixing or mounting of the structural members at corresponding positions can be realized. The specific meaning of the above terms in the creation of the present utility model can be understood by those of ordinary skill in the art in a specific case.
The utility model will be described in detail below with reference to the drawings in connection with embodiments.
A high load light stealth composite fuselage structure, as shown in fig. 1 and 2, comprises a front fuselage inner frame and a front fuselage outer skin structure outside the front fuselage inner frame, wherein the front fuselage outer skin structure comprises a front fuselage upper skin 12 and a front fuselage lower skin 13. The front fuselage inner frame comprises a frame 1 and a longitudinal element on the periphery of the frame, the frame comprises a front fuselage butt joint frame 2, a front fuselage front reinforcing frame 3, a wing front connecting frame 4, a wing rear connecting frame 5 and a front fuselage middle reinforcing frame 6 which are sequentially arranged from the tail to the nose direction, at least one bulkhead 7 is uniformly distributed between the front fuselage front reinforcing frame and the wing front connecting frame, between the wing front connecting frame and the wing rear connecting frame, between the wing rear connecting frame and the front fuselage middle reinforcing frame and between the front fuselage middle reinforcing frame to one side of the nose. It should be noted that each spacer is fixed by the stringers to at least one side of the corresponding frame structure (e.g., stiffener, connector, interface).
The front frame butt joint frame is connected with the front frame front reinforcement frame, the front frame front reinforcement frame is connected with the wing front connection frame, the front frame butt joint frame is connected with the wing front connection frame, the wing front connection frame is connected with the wing rear connection frame through the short trusses 8, and the short trusses are prevented from being overlapped with the long trusses, so that the frame is better in integrity and higher in strength.
The longitudinal element includes several stringers 9 that follow fuselage length direction and arrange, and preceding fuselage butt joint frame, preceding strengthening frame and preceding fuselage middle part strengthening frame all are fixed with each stringer, and preceding fuselage butt joint frame, preceding strengthening frame and preceding fuselage middle part strengthening frame outer fringe all are equipped with the turn-ups structure of laminating with preceding fuselage outer skin structure. Through the connection and supporting function of the stringers and the stringers, the structural strength of the fuselage is increased, the working stress level is reduced, and the rigidity change tends to be gentle. The front fuselage outer skin structure bears the aerodynamic force of the fuselage, simultaneously bears the shearing force and bending moment in the bending deformation of the fuselage, and together with the reinforcing frames, the connecting frames, the stringers and the short stringers, bears the axial force caused by the bending moment. Typically, the longitudinal members include four stringers disposed about the upper left, lower left, upper right and lower right of the frame.
The longitudinal members are used for bearing axial force generated when the fuselage is bent, in addition, each stringer and each short stringer have supporting effect on the skin, so that the critical stress of the skin in compression and shear instability is improved, and the aerodynamic force born by the longitudinal members and acting on the skin is transferred to the reinforcing frame, the butt joint frame, the connecting frame and each bulkhead. The formers serve to maintain the cross-sectional shape of the fuselage and are also subjected to distributed stresses caused by bending deformations of the fuselage, while the formers also support the skin and stringers.
The wing front connecting frame, the wing rear connecting frame and the spacer frame between the wing front connecting frame and the wing rear connecting frame are respectively provided with a wing connector 10, and are fixedly connected with a wing spar connector through the wing connectors. The front frame and the rear frame are used as the frame for connecting the recovery umbrella, and bear the instantaneous concentrated load caused by the interaction of the air resistance of the recovery umbrella and the flying speed of the airplane when the recovery umbrella is opened. The butt-joint frame is used as a frame for mounting the engine and mainly bears the axial load of the engine and also bears the normal load brought by partial weight of the engine. In order to make the butt joint of the front and rear fuselage better connect, reduce the stress level of the joint, the butt joint bulkhead can be widened and thickened, and double rows of rivets are arranged during assembly.
The middle reinforcing frame of the front fuselage or the rear connecting frame of the wing are provided with the slots, the stringers are provided with plugs 11 matched with the slots, and the combination degree among the components is high and the structural stability is good. As an example, the front fuselage outer skin structure is glue-riveted with the flange structures of the frames. The front fuselage outer skin structure is adhesively riveted to each stringer. The front fuselage outer skin structure is integrally formed by prepreg. Each stringer is integrally formed from a prepreg. During assembly, the skin structure, the spacer frames, the connecting frames and the flanging of the reinforcing frames are glued and riveted into a whole, and the flanging is connected with the skin to play a role in crack arrest, so that longitudinal crack expansion under the action of hoop stress is prevented. In addition, the outer surfaces of the stringers and the short stringers are flush with the corresponding outer surfaces of the frames, the skin structure is firmly attached to the frames, and cracks are effectively prevented from being generated at the joints of the machine body when the machine body is subjected to external pressure.
In the fuselage structure provided by the utility model, the longitudinal members effectively bear the axial force generated when the fuselage is bent, the longitudinal members also have supporting effect on the skin, the critical stress of the skin in compression and shear instability is improved, the aerodynamic force born by the longitudinal members and acting on the skin is transferred to the reinforcing frame, the butt joint frame, the connecting frame and each partition frame, the fuselage structure has clear force transfer path, simple and reliable structure, light weight, low cost, convenient use and maintenance, good corrosion resistance and fatigue resistance, low crack expansion rate, adaptability to the working conditions of high strength and complex load condition and ensured service life.
The above embodiments are merely preferred embodiments of the present utility model and are not intended to limit the present utility model, and any modifications, equivalent substitutions, improvements, etc. within the spirit and principle of the present utility model should be included in the protection scope of the present utility model.
Claims (8)
1. A high-load light stealthy combined material fuselage structure which characterized in that: the front fuselage outer skin structure comprises a front fuselage inner frame and a front fuselage outer skin structure at the outer side of the front fuselage inner frame; the front fuselage inner frame comprises a frame and a longitudinal element at the periphery of the frame, the frame comprises a front fuselage butt joint frame, a front fuselage front reinforcing frame, a wing front connecting frame, a wing rear connecting frame and a front fuselage middle reinforcing frame which are sequentially arranged from the tail to the head direction,
at least one bulkhead is distributed on one side of the nose towards the front frame, between the front frame and the rear frame, between the rear frame and the middle frame and between the middle frame and the middle frame;
the front fuselage butt joint frame is connected with the front fuselage front reinforcement frame, the front fuselage front reinforcement frame is connected with the wing front connection frame, the front fuselage butt joint frame is connected with the wing front connection frame, and the wing front connection frame is connected with the wing rear connection frame through short trusses;
the longitudinal element comprises a plurality of stringers arranged along the length direction of the fuselage, a front fuselage butt joint frame, a front fuselage front reinforcing frame and a front fuselage middle reinforcing frame, which are all fixed with the stringers, and the outer edges of the front fuselage butt joint frame, the front fuselage front reinforcing frame and the front fuselage middle reinforcing frame are all provided with flanging structures attached to the outer skin structure of the front fuselage.
2. A heavy-duty lightweight stealth composite fuselage structure as defined in claim 1, wherein: and wing connectors are arranged on the wing front connecting frame, the wing rear connecting frame and the spacer frame between the wing front connecting frame and the wing rear connecting frame.
3. A heavy-duty lightweight stealth composite fuselage structure as defined in claim 1, wherein: the front fuselage outer skin structure and the flanging structures of the frames are glued and riveted into a whole.
4. A heavy-duty lightweight stealth composite fuselage structure as defined in claim 1, wherein: the front fuselage outer skin structure is adhesively riveted to each stringer.
5. A heavy-duty lightweight stealth composite fuselage structure as defined in claim 1, wherein: the front fuselage outer skin structure is integrally formed by prepreg.
6. A heavy-duty lightweight stealth composite fuselage structure as defined in claim 1, wherein: the longitudinal members include four stringers disposed about the upper left, lower left, upper right and lower right of the frame.
7. A heavy-duty lightweight stealth composite fuselage structure as defined in claim 6, wherein: the middle reinforcing frame of the front fuselage or the rear connecting frame of the wing is provided with a slot, and the stringer is provided with a plug matched with the slot.
8. A heavy-duty lightweight stealth composite fuselage structure as defined in claim 6, wherein: each stringer is integrally formed from a prepreg.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321352639.7U CN219927958U (en) | 2023-05-31 | 2023-05-31 | Large-load light stealth composite material fuselage structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321352639.7U CN219927958U (en) | 2023-05-31 | 2023-05-31 | Large-load light stealth composite material fuselage structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219927958U true CN219927958U (en) | 2023-10-31 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321352639.7U Active CN219927958U (en) | 2023-05-31 | 2023-05-31 | Large-load light stealth composite material fuselage structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219927958U (en) |
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2023
- 2023-05-31 CN CN202321352639.7U patent/CN219927958U/en active Active
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