CN216805791U - Sectional type aircraft ventral fin structure - Google Patents
Sectional type aircraft ventral fin structure Download PDFInfo
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- CN216805791U CN216805791U CN202122678108.4U CN202122678108U CN216805791U CN 216805791 U CN216805791 U CN 216805791U CN 202122678108 U CN202122678108 U CN 202122678108U CN 216805791 U CN216805791 U CN 216805791U
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Abstract
The utility model discloses a sectional type aircraft ventral fin structure, which comprises: the ventral fin front cover, the ventral fin middle section and the ventral fin rear cover; the ventral fin middle section includes that metal rivets skeleton and combined material middle section covering, and metal rivets the skeleton and includes: the metal riveting frame comprises a metal plate frame structure and a plurality of machining joints, wherein the machining joints are fixedly connected in the metal plate frame structure at intervals, top joints stretch out of the upper end of an upper web girder to be fixedly connected with the lower part of a machine body through top joints, a middle-section skin is arranged to be of a U-shaped structure and wraps the bottom and the side part of the metal riveting frame, and the middle-section skin is riveted with the metal riveting frame; the ventral fin front cover and the ventral fin rear cover are both cover bodies formed by medium-temperature curing epoxy glass cloth prepreg and are respectively connected to the front end and the rear end of the middle section of the ventral fin. The technical scheme provided by the embodiment of the utility model solves the problems of low weight utilization efficiency, poor assembly manufacturability, inconvenient disassembly and maintenance, long manufacturing period, high cost and the like of the conventional aircraft ventral fin structure under the condition of larger ventral fins.
Description
Technical Field
The present application relates to, but is not limited to, the technical field of aircraft structural design, and more particularly, to a segmented aircraft ventral fin structure.
Background
The ventral fins of the airplane are arranged on the lower part of the rear fuselage of the airplane, so that the pneumatic performance of the airplane can be improved, and the course stability can be improved.
At present, the skeleton of the ventral fin of the domestic general aircraft is mostly an integral tube beam type or a metal riveting structure, the weight utilization efficiency is low under the great condition of the ventral fin, the assembly manufacturability is poor, the disassembly is inconvenient to maintain, the manufacturing cycle is long, and the cost is high.
SUMMERY OF THE UTILITY MODEL
The purpose of the utility model is as follows: in order to solve the technical problems, the embodiment of the utility model provides a segmented aircraft ventral fin structure, which aims to solve the problems of low weight utilization efficiency, poor assembly manufacturability, inconvenient disassembly and maintenance, long manufacturing period, high cost and the like of the existing aircraft ventral fin structure under the condition of larger ventral fin due to the adoption of an integral tube beam type or metal riveting structure.
The technical scheme of the utility model is as follows: the embodiment of the utility model provides a sectional type aircraft ventral fin structure, which comprises: sectional type aircraft ventral fin structure fixed mounting includes under the aircraft fuselage: the ventral fin front cover 1, the ventral fin middle section 2 and the ventral fin rear cover 3 are sequentially arranged from front to back along the center line of the airplane;
wherein, ventral fin middle section 2 includes metal riveting skeleton and combined material middle section covering 6, metal riveting skeleton includes: the metal plate frame structure 7 is a frame structure formed by an upper web beam, a lower web beam and a plurality of web ribs which are arranged at intervals and are arranged between the upper web beam and the lower web beam along the center line of the airplane, the web ribs are fixedly connected between the upper web beam and the lower web beam at intervals, the plurality of machine joints 8 are fixedly connected between the upper web beam and the lower web beam at intervals, a top joint extends out of the upper end of the upper web beam to be fixedly connected with the lower part of the airplane body through a top joint, the composite material middle section skin 6 is arranged to be a U-shaped structure and is wrapped at the bottom and the side part of the metal riveting framework, and the middle section skin 6 is riveted with the metal riveting framework;
the ventral fin front cover and the ventral fin rear cover 3 are both cover bodies formed by adopting intermediate-temperature curing epoxy glass cloth prepreg 4 and are respectively connected to the front end and the rear end of the ventral fin middle section 2.
Optionally, in the segmented aircraft ventral fin structure described above, the metal riveted skeleton of the ventral fin middle section further includes: an anti-abrasion steel plate 9;
the anti-abrasion steel plate 9 is of a U-shaped structure and wraps the bottom of the rear end of the middle section skin 6 on the outer side of the ventral fin middle section 2.
Optionally, in the segmented aircraft ventral fin structure described above, the metal riveting framework specifically includes: four machining joints 8;
the positions of the four machining joints 8 correspond to the separating surfaces of the airplane fuselage frame, wherein two machining joints 8 are respectively arranged at the front end and the rear end of the sheet metal frame structure 7, and the other two machining joints 8 are arranged between the web ribs;
and the ventral fin middle section 2 is in threaded connection with four frames of the airplane body through top end joints of the four machining joints 8, and is used for transferring and diffusing the impact load borne by the ventral fin middle section to the airplane body structure.
Alternatively, in the segmented aircraft ventral fin structure described above,
the ventral fin shield comprises: the ventral fin front cover is in threaded connection with an machining connector 8 at the front end of the ventral fin middle section 2 through the front cover body.
Alternatively, in the segmented aircraft ventral fin structure as described above,
the ventral fin rear cover 3 is of a laminated plate structure formed by adopting medium-temperature curing epoxy glass cloth prepreg 4, and the ventral fin rear cover 3 is in threaded connection with a machining connector 8 at the rear end of the ventral fin middle section 2.
Alternatively, in the segmented aircraft ventral fin structure described above,
the separating surfaces of the ventral fin front cover 1, the ventral fin middle section 2 and the ventral fin rear cover 3 correspond to the separating surface of the airplane body frame.
Alternatively, in the segmented aircraft ventral fin structure as described above,
the composite material middle section skin 6 of the ventral fin middle section 2, and the tops of the ventral fin front cover 1 and the ventral fin rear cover 3 are provided with flanges, and are in threaded connection with the belly of the fuselage through the flanges.
The utility model has the beneficial effects that: according to the sectional type ventral fin structure of the airplane, provided by the embodiment of the utility model, the structural characteristics of large length and narrow section of the ventral fin of the airplane and the maintenance requirements on the ventral fin and the tail cover are considered, the technical scheme provided by the embodiment of the utility model specifically splits the whole ventral fin of the airplane into a front section, a middle section and a rear section according to the design separation plane of the airplane body, and each section selects different structural forms according to the position of the airplane body and the self function of the airplane body, and each section has different functions. The sectional type aircraft ventral fin structure provided by the embodiment of the utility model can obviously improve the weight utilization rate, improve the assembly manufacturability, shorten the manufacturing period and reduce the manufacturing and assembly cost. The front, middle and rear ventral fins are connected with the fuselage structure through screws, so that the mounting, dismounting and maintenance of each part are facilitated. The sectional type aircraft ventral fin structure provided by the embodiment of the utility model optimizes the aircraft ventral fin structure to the maximum extent under the condition of ensuring that the ventral fin bears the aerodynamic force requirement, so that the aircraft ventral fin can functionally play the roles of improving the aerodynamic performance of the aircraft and increasing the course stability; structurally, the structure has different structural forms through segmentation and each segment, so that the structure weight is reduced to the maximum extent, the assembly manufacturability is improved, the processing period is shortened, the cost is reduced, and the rapid installation, maintenance and disassembly of the ventral fin are realized. The segmented ventral fin structure of the airplane can be widely applied to various airplanes.
Drawings
The accompanying drawings 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 example serve to explain the principles of the utility model and not to limit the utility model.
FIG. 1 is a schematic view of a mounting position of a segmented ventral fin structure of an aircraft according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a segmented ventral fin structure of an aircraft according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of a middle section of an abdominal fin in a segmented ventral fin structure of an aircraft according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a ventral fin front cover in a ventral fin structure of a sectional type aircraft according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of a ventral fin rear cover in a segmented ventral fin structure of an aircraft according to an embodiment of the present invention.
The ventral fin structure comprises a ventral fin front cover 1, a ventral fin middle section 2, a ventral fin rear cover 3, a medium-temperature cured epoxy glass cloth prepreg 4, a foam core 5, a middle section skin 6, a sheet metal frame structure 7, a machining joint 8 and an anti-abrasion steel plate 9.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
It has been described in the above background art that the skeleton of the conventional aircraft ventral fin structure is generally an integral tubular beam type or metal riveted structure, which can cause the problems of low weight utilization efficiency, poor assembly manufacturability, inconvenient disassembly and maintenance, long manufacturing period, high cost and the like under the condition that the ventral fin is large.
Aiming at various problems of the conventional aircraft ventral fin structure, the embodiment of the utility model provides a sectional aircraft ventral fin structure, which optimizes the structure to the maximum extent under the condition of ensuring that the ventral fin bears aerodynamic requirements.
The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.
Fig. 1 is a schematic view of an installation position of a segmented aircraft ventral fin structure on an aircraft according to an embodiment of the present invention, and fig. 2 is a schematic view of an overall structure of the segmented aircraft ventral fin structure according to an embodiment of the present invention. Referring to fig. 1 and 2, the segmented ventral fin structure of an aircraft according to an embodiment of the present invention is fixedly mounted on a lower belly of an aircraft fuselage, and mainly includes three parts: the ventral fin front cover 1, the ventral fin middle section 2 and the ventral fin rear cover 3 are sequentially arranged from front to back along the central line of the airplane, and as shown in fig. 2, the heights of the ventral fin front cover 1, the ventral fin middle section 2 and the ventral fin rear cover 3 are gradually increased from front to back.
Fig. 3 is a schematic structural diagram of a middle section of an abdominal fin in a segmented aircraft abdominal fin structure according to an embodiment of the present invention, which is combined with the structure of the middle section 2 of the abdominal fin shown in fig. 2 and 3, and includes a metal riveted skeleton and a composite material middle section skin 6; wherein, metal riveting skeleton includes: sheet metal frame structure 7 and machine add joint 8, sheet metal frame structure 7 is for adopting along the upper and lower two webs roof beam of aircraft central line setting and connecting in on, the frame construction that the web rib that a plurality of intervals between two webs roof beam set up down formed, 8 interval fixed connection in on of a plurality of machine add joint between two webs roof beams down, and the top connects and stretches out in last web roof beam upper end, in order to connect through the top and fuselage lower part fixed connection, combined material middle section covering 6 sets up to the U-shaped structure, the parcel is in the bottom and the lateral part of metal riveting skeleton, and combined material middle section covering 6 is riveted with metal riveting skeleton.
As shown in fig. 1 and 2, the ventral fin front cover and the ventral fin rear cover 3 are both cover bodies formed by using a medium-temperature cured epoxy glass cloth prepreg 4 and are respectively connected to the front end and the rear end of the ventral fin middle section 2.
In an implementation manner of the embodiment of the present invention, the metal riveting framework at the middle section of the ventral fin further includes: and an abrasion-proof steel plate 9. As shown in fig. 3, the wear-resistant steel plate 9 is also provided in a U-shaped configuration, and wraps the bottom of the rear end of the center skin 6 outside the ventral fin center section 2.
In a specific implementation of the embodiment of the present invention, the metal riveting framework may specifically include: four machined joints 8; the positions of the four machining joints 8 correspond to the parting surfaces of the airplane fuselage frame, wherein two machining joints 8 are respectively arranged at the front end and the rear end of the sheet metal frame structure 7, and the other two machining joints 8 are arranged between the web ribs; as shown in fig. 3, the two middle machined joints 8 are located between two web ribs of the sheet metal frame structure 7.
In this implementation, based on the structural relationship between the four machined joints 8 and the four frames of the fuselage on the parting plane, the ventral fin middle section 2 is screwed with the four frames of the aircraft fuselage specifically through the top joints of the four machined joints 8, and the impact load borne by the ventral fin middle section can be transferred and diffused to the fuselage structure through an extremely direct force transmission path.
In an implementation manner of the embodiment of the present invention, as shown in fig. 4, a schematic structural diagram of a ventral fin front cover in a segmented ventral fin structure provided in the embodiment of the present invention is shown, where in the implementation manner, the ventral fin front cover includes: the ventral fin front cover is in threaded connection with an machining connector 8 at the front end of the ventral fin middle section 2 through the front cover body.
In an implementation manner of the embodiment of the present invention, as shown in fig. 5, a schematic structural diagram of a ventral fin rear cover in a segmented ventral fin structure of an aircraft according to the embodiment of the present invention is provided, in the implementation manner, the ventral fin rear cover 3 is a laminated plate structure formed by using a medium-temperature cured epoxy glass cloth prepreg 4, and the ventral fin rear cover 3 is screwed with a machining joint 8 at the rear end of a ventral fin middle section 2.
In the above embodiments of the present invention, since the segmented aircraft ventral fin structure is designed based on the separating plane of the aircraft fuselage frame structure and divides the ventral fin front cover 1, the ventral fin middle section 2, and the ventral fin rear cover 3, the separating plane of the ventral fin front cover 1, the ventral fin middle section 2, and the ventral fin rear cover 3 corresponds to the separating plane of the aircraft fuselage frame.
Further, the composite material middle section skin 6 of the ventral fin middle section 2 and the top of the skin structures of the ventral fin front cover 1 and the ventral fin rear cover 3 in the embodiments of the utility model are provided with flanges, and the flanges can be screwed with the belly of the fuselage.
According to the sectional type ventral fin structure of the airplane, provided by the embodiment of the utility model, the structural characteristics of large length and narrow section of the ventral fin of the airplane and the maintenance requirements on the ventral fin and the tail cover are considered, the technical scheme provided by the embodiment of the utility model specifically splits the whole ventral fin of the airplane into a front section, a middle section and a rear section according to the design separation plane of the airplane body, and each section selects different structural forms according to the position of the airplane body and the self function of the airplane body, and each section has different functions. The segmented aircraft ventral fin structure provided by the embodiment of the utility model can obviously improve the weight utilization rate, improve the assembly manufacturability, shorten the manufacturing period and reduce the manufacturing and assembly cost. The front, middle and rear ventral fins are connected with the fuselage structure through screws, so that the mounting, dismounting and maintenance of each part are facilitated. The sectional type aircraft ventral fin structure provided by the embodiment of the utility model optimizes the aircraft ventral fin structure to the maximum extent under the condition of ensuring that the ventral fin bears the aerodynamic force requirement, so that the aircraft ventral fin can functionally play the roles of improving the aerodynamic performance of the aircraft and increasing the course stability; structurally, the structure has different structural forms through segmentation and each segment, so that the structure weight is reduced to the maximum extent, the assembly manufacturability is improved, the processing period is shortened, the cost is reduced, and the rapid installation, maintenance and disassembly of the ventral fin are realized.
The following provides a detailed description of an embodiment of a segmented aircraft ventral fin structure according to an embodiment of the present invention.
The segmented aircraft ventral fin structure provided by the specific embodiment comprises: the ventral fin comprises a ventral fin front cover 1, a ventral fin middle section 2 and a ventral fin rear cover 3; the ventral fin front cover 1 is formed by bonding and curing three layers of medium-temperature cured epoxy glass cloth prepreg 4 and a foam core 5; the ventral fin middle section 2 is formed by riveting a middle section skin 6, a sheet metal frame structure 7, a machining joint 8 and an anti-abrasion steel plate 9; the ventral fin rear cover 3 is formed by curing a medium-temperature curing epoxy glass cloth prepreg 4; the connection of the sectional ventral fin and the fuselage is in bolt joint.
The segmented airplane ventral fin structure provided by the embodiment is applied to a KT52 type airplane at present, and can be widely applied to various types of airplanes. Under the condition of ensuring that the ventral fin bears the aerodynamic force requirement, the structure is optimized to the maximum extent, so that the ventral fin of the airplane can functionally play the roles of improving the aerodynamic performance of the airplane and increasing the course stability; structurally, the structure has different structural forms through segmentation and each segment, so that the structure weight is reduced to the maximum extent, the assembly manufacturability is improved, the processing period is shortened, the cost is reduced, and the rapid installation, maintenance and disassembly of the ventral fin are realized.
Referring to fig. 1 to 5, the segmented ventral fin structure of the aircraft is formed by screwing a ventral fin front cover 1, a ventral fin middle section 2 and a ventral fin rear cover 3.
Firstly, the separating surfaces of the ventral fin front cover 1, the ventral fin middle section 2 and the ventral fin rear cover 3 are the same as the design separating surface of the airplane, so that the maintenance of the airplane structure and the disassembly and assembly of each ventral fin section are facilitated. Secondly, based on the position of the ventral fin and the load born by the ventral fin, the specific structure of the three ventral fins is designed and formed according to the calculation of the ground rubbing angle of the airplane.
On one hand, the middle section 2 of the ventral fin can bear impact load when the ventral fin lands on the ground, so that the middle section 2 of the ventral fin is in a structural form of a metal riveting framework and a composite material middle section skin 6; the metal riveting framework is formed by riveting a sheet metal frame structure 7, a machining joint 8 and an anti-abrasion steel plate 9, after the metal riveting framework is in threaded connection with four frames of the airplane body through the machining joint 8, impact load can be diffused to the structure of the airplane body through a very direct force transmission path, and the anti-abrasion steel plate 9 can be made of a stainless steel plate and plays an anti-abrasion role when the airplane touches the ground and is provided with a tail boom; the ventral fin middle section skin 6 is formed by adopting a middle-temperature cured epoxy glass cloth prepreg 4, maintains a theoretical appearance for the ventral fin middle section 2 and bears lateral pneumatic load together with a metal riveting framework, the ventral fin middle section skin 6 is riveted with the metal riveting framework, and a flanging at the upper part of the middle section skin 6 is in threaded connection with a fuselage.
On the other hand, since the ventral fin front cover 1 and the ventral fin rear cover 3 receive only lateral aerodynamic loads during flight of the aircraft, the structural forms of the ventral fin front cover 1 and the ventral fin rear cover 3 can be determined by the fact that the lateral area of the ventral fin front cover 1 is large and the lateral area of the ventral fin rear cover 2 is small. The ventral fin front cover 1 is formed by bonding and curing three layers of medium-temperature cured epoxy glass cloth prepreg 4 and a foam core 5, and the foam core 5 can play a role in improving the overall rigidity of the ventral fin front cover 1; in order to reduce the weight of the structure, the ventral fin rear cover 3 is of a laminated plate structure, and the material is still the medium-temperature curing epoxy glass cloth prepreg 4.
Furthermore, in this embodiment, the connection among the ventral fin front cover 1, the ventral fin middle section 2 and the ventral fin rear cover 3 is a screw joint, the ventral fin front cover 1 and the ventral fin rear cover 3 are both screw-connected to the machining joint 8 of the ventral fin middle section 2, and the upper part is directly screw-connected to the fuselage skin
Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the utility model as defined by the appended claims.
Claims (7)
1. The utility model provides a sectional type aircraft ventral fin structure, a serial communication port, sectional type aircraft ventral fin structure fixed mounting includes in the belly under the aircraft fuselage: the ventral fin front cover (1), the ventral fin middle section (2) and the ventral fin rear cover (3) are sequentially arranged from front to back along the center line of the airplane;
wherein, ventral fin middle section (2) are including metal riveting skeleton and combined material middle section covering (6), metal riveting skeleton includes: the aircraft comprises a metal plate frame structure (7) and an machined joint (8), wherein the metal plate frame structure (7) is a frame structure formed by an upper web beam and a lower web beam which are arranged along the central line of an aircraft and a plurality of web ribs which are arranged at intervals and connected between the upper web beam and the lower web beam, the machined joints (8) are fixedly connected between the upper web beam and the lower web beam at intervals, a top end joint of each machined joint (8) extends out of the upper end surface of the upper web beam to be fixedly connected with the lower part of an aircraft body through the top end joint, a composite material middle section skin (6) is arranged to be of a U-shaped structure and wraps the bottom and the side of a metal riveting framework, and the middle section skin (6) is riveted with the metal riveting framework;
the ventral fin front cover and the ventral fin rear cover (3) are both cover bodies formed by curing epoxy glass cloth prepreg (4) at medium temperature and are respectively connected to the front end and the rear end of the ventral fin middle section (2).
2. The segmented aircraft ventral fin structure of claim 1, wherein the metal riveted skeleton of the ventral fin mid-section further comprises: an anti-wear steel plate (9);
the wear-resistant steel plate (9) is of a U-shaped structure and wraps the bottom of the rear end of the middle section skin (6) on the outer side of the ventral fin middle section (2).
3. The segmented aircraft ventral fin structure according to claim 2, wherein the metal riveted skeleton comprises in particular: four machining joints (8);
the positions of the top end joints of the four machining joints (8) correspond to the separating surfaces of the airframe frame of the airplane, wherein two machining joints (8) are respectively arranged at the front end and the rear end of the sheet metal frame structure (7), and the other two machining joints (8) are arranged between the ventral ribs;
and the ventral fin middle section (2) is in threaded connection with four frames of the airplane body through top end joints of the four machining joints (8) and is used for transferring and diffusing the impact load born by the ventral fin middle section to the airplane body structure.
4. The segmented aircraft ventral fin structure of claim 2,
the ventral fin shield comprises: the ventral fin structure comprises three layers of medium-temperature curing epoxy glass cloth prepregs (4) and a foam core (5), wherein the foam core (5) is filled and bonded in a front cover body formed by the three layers of medium-temperature curing epoxy glass cloth prepregs (4), and the ventral fin front cover is in threaded connection with an machining joint (8) at the front end of the ventral fin middle section (2) through the front cover body.
5. The segmented aircraft ventral fin structure of claim 2,
the ventral fin rear cover (3) is of a laminated plate structure formed by adopting a medium-temperature cured epoxy glass cloth prepreg (4), and the ventral fin rear cover (3) is in threaded connection with a machining joint (8) at the rear end of the ventral fin middle section (2).
6. A segmented aircraft ventral fin structure according to any one of claims 1 to 5,
the separating surfaces of the ventral fin front cover (1), the ventral fin middle section (2) and the ventral fin rear cover (3) correspond to the separating surface of the airplane body frame.
7. The segmented aircraft ventral fin structure according to any one of claims 1 to 5,
the composite material middle section skin (6) of the ventral fin middle section (2) and the tops of the ventral fin front cover (1) and the ventral fin rear cover (3) are provided with flanges, and are in threaded connection with the belly of the fuselage through the flanges.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122678108.4U CN216805791U (en) | 2021-11-03 | 2021-11-03 | Sectional type aircraft ventral fin structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122678108.4U CN216805791U (en) | 2021-11-03 | 2021-11-03 | Sectional type aircraft ventral fin structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216805791U true CN216805791U (en) | 2022-06-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122678108.4U Active CN216805791U (en) | 2021-11-03 | 2021-11-03 | Sectional type aircraft ventral fin structure |
Country Status (1)
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|---|---|
| CN (1) | CN216805791U (en) |
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2021
- 2021-11-03 CN CN202122678108.4U patent/CN216805791U/en active Active
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