CN212243788U

CN212243788U - Combined type aircraft ventral fin structure

Info

Publication number: CN212243788U
Application number: CN202020762079.2U
Authority: CN
Inventors: 胡斌; 刘世群; 王健; 曹红伟; 龚丽娟
Original assignee: AVIC Shaanxi Aircraft Industry Group Corp Ltd
Current assignee: Shaanxi Aircraft Industry Co Ltd
Priority date: 2020-05-09
Filing date: 2020-05-09
Publication date: 2020-12-29
Anticipated expiration: 2030-05-09

Abstract

The utility model belongs to the technical field of the aviation, specifically be a modular aircraft ventral fin structure, constitute including floorbar, stringer, bulkhead, covering, leading edge and U type roof beam. The skin material adopts a thin aluminum plate with the thickness of 0.8mm, and a process method of roll riveting forming is adopted, so that the problem of no construction access is solved; 14 stringers are arranged on the skin and are longitudinally arranged along the fuselage to enhance the rigidity of the ventral fin; 16 ventral fin partition plates are arranged and respectively correspond to the machine body frame, so that the bending resistance of ventral fins is enhanced; the ventral fin bottom beam is an L-shaped machined part and mainly used for transmitting the load on the ventral fin to the fuselage; and 15Z-shaped plate bending pieces are arranged on the inner side of the front edge of the ventral fin and used for maintaining the aerodynamic shape of the ventral fin. The utility model overcomes small-size ventral fin bears the weight of can not strong, shortcoming such as manufacturability is not good enough, has advantages such as simple structure, light in weight, with low costs.

Description

Combined type aircraft ventral fin structure

Technical Field

The utility model belongs to the technical field of the aviation, a modular aircraft ventral fin structure is related to, and specifically speaking provides a supply big medium-sized cargo airplane to use, by the aircraft ventral fin structure that covering, stringer, baffle, leading edge riveting are constituteed.

Background

The ventral fin structure of the airplane is widely applied to airplanes at home and abroad, is mainly applied to special airplanes for a transporter, and is used for solving the problem that the course stability is reduced under the large attack angle state of the airplane. The aircraft ventral fin structure material comprises a composite material structure and a metal material, and the composite material ventral fin structure is light in weight, good in rigidity and easy to form a complex thin-wall structure, so that the application is more. However, the composite material has poor anisotropy and fatigue resistance, and cracks, tearing and other conditions are difficult to avoid in use. The ventral fins of large and medium-sized transport planes are positioned in an airflow turbulence area at the rear lower part of the tail section of the plane body, strong unstable airflow can generate an excitation effect on the ventral fins, and therefore the damage of the ventral fin structure is fatigue damage under the action of cyclic load. The project is designed aiming at the use environment of large and medium-sized conveyors, and is made of all-aluminum alloy materials, so that the structural size is large, and the pneumatic load is moderate. The ventral fin structure has the advantages of simple structure, light weight, low cost and the like, and achieves the purpose of realizing optimal performance with minimum weight and economic cost.

SUMMERY OF THE UTILITY MODEL

The utility model overcomes the defects in the prior art, provides a ventral fin structure which is used for large and medium-sized transport machines and has the advantages of simple structure, light weight, low cost and the like.

Technical scheme

As shown in fig. 1, a combined aircraft ventral fin structure is provided, comprising a skin 4, stringers 2, bulkheads 3, U-beams 6, bottom beams 1 and leading edges 5.

The skin 4 is made of a thin aluminum plate with the thickness of 0.6-1.5 mm; according to the condition of uniform stress distribution, the single ventral fin has N long trusses 2, and N/2 ventral fins are longitudinally arranged along the fuselage and are arranged at a distance of 80-120mm on the left and right sides by taking the central plane of the ventral fin as a reference.

The partition boards 3 are 1.0-1.5mm in specification, and are N in number and respectively correspond to the frame of the machine body.

The U-shaped beam 6 is a plate bending piece with the specification of 1.0-1.5mm, is in a U shape and is used for connecting the front edge 5 and the partition plate 3.

The bottom beam 1 is L-shaped, the thickness of the joint of the bottom beam and the fuselage is 3-5mm, and the thickness of the joint of the bottom beam and the skin is 3-5 mm. The effect is to transfer the load on the ventral fins to the fuselage.

Inside the leading edge 5 are mounted several plate benders 7 for maintaining the aerodynamic profile of the ventral fin.

The skin 4, the stringer 2, the clapboard 3, the U-shaped beam 6, the bottom beam 1 and the front edge 5 are formed by riveting.

The U-shaped beam 6 is made of aluminum alloy plates.

The partition plate 3 is an aluminum alloy plate with a bent edge.

The bottom beam 1 is an machined part.

The plate bending piece 7 is Z-shaped.

Technical effects

The utility model provides a ventral fin structure which is used for large and medium-sized transport machines and has the advantages of simple structure, light weight, low cost and the like. The skin 4 is made of a thin aluminum plate with the thickness of 0.6-1.5mm, and a roll riveting forming process method is adopted, so that the problem that no construction passage exists is solved; the single ventral fin has N long trusses 2, and N/2 ventral fins are longitudinally arranged along the fuselage and arranged at intervals of 80-120mm on the left and right sides by taking the central plane of the ventral fin as a reference, so that the rigidity of the ventral fin can be enhanced. And N ventral fin partition plates are arranged and respectively correspond to the machine body frame, so that the bending resistance of the ventral fins is enhanced. The U-shaped beam 6 is a plate bending piece made of aluminum plate and is in a U shape and used for connecting the ventral fin front edge 5 and the partition plate 3. The ventral fin bottom beam 1 is an L-shaped machined part and mainly used for transmitting load on the ventral fin to a fuselage. The inner side of the ventral fin front edge 5 is provided with N Z-shaped plate bending pieces 7 for maintaining the pneumatic shape of the ventral fin.

Drawings

FIG. 1 is a schematic view of the structure of ventral fin

FIG. 2 is a view showing the structure of the partition, stringer, U-shaped beam, leading edge

Wherein: 1. bottom beam 2, stringer 3, bulkhead 4, skin 5, front edge 6, U-shaped beam 7, plate bending piece

Detailed Description

Combine the attached drawing right the utility model relates to a modular aircraft ventral fin structure:

a combined ventral fin structure of an airplane is provided, which comprises a bottom beam, a stringer, a bulkhead, a skin, a front edge and a U-shaped beam.

The skin is made of a thin aluminum plate, a process method of roll riveting forming is adopted, and the ventral fin is narrow in process construction path; the total number of the single ventral fins is 14 stringers, and the 7 ventral fins are arranged along the longitudinal direction of the fuselage and are arranged at intervals of 95mm by taking the center plane of the ventral fin as a reference. The ventral fin partition plate is made of aluminum plates, and the total number of the ventral fin partition plates is 16, and the ventral fin partition plates correspond to the machine body frame respectively. The edge of the clapboard is provided with a stringer through hole. The long purlins at the left and right sides are connected together by the section bar and the partition board at the through hole of the long purlins. The front edge of the ventral fin clapboard is riveted with the U-shaped beam bent edge at the front edge, and the end of the clapboard is riveted with the web plate of the U-shaped beam by a section bar. The U-shaped beam is a plate bending piece made of aluminum plates and is in a U shape and used for connecting the front edge of the ventral fin and the partition plate. The ventral fin bottom beam is an L-shaped machining piece and mainly used for transmitting load on the ventral fin to the fuselage. The front edge is made of an aluminum plate, and 15Z-shaped plate bending pieces are arranged on the inner side of the front edge. The leading edge is butted with the ventral fin skin through a U-shaped beam.

Claims

1. A combined type aircraft ventral fin structure comprises a skin (4), a stringer (2), a clapboard (3), a U-shaped beam (6), a bottom beam (1) and a front edge (5); the method is characterized in that:

the skin (4) is made of a thin aluminum plate; according to the condition of uniform stress distribution, a single ventral fin has N long trusses (2), N/2 ventral fins are arranged along the longitudinal direction of the fuselage at a distance of 80-120mm on the left and right sides by taking the central plane of the ventral fin as a reference; the partition boards (3) have the specification of 1.0-1.5mm, and are N in number and respectively correspond to the frame of the machine body; the U-shaped beam (6) is a plate bending piece (7) with the specification of 1.0-1.5mm, is U-shaped and is connected with the front edge (5) and the partition plate (3); the bottom beam (1) is L-shaped, and a plurality of plate bending pieces (7) are arranged on the inner side of the front edge (5) to maintain the pneumatic appearance of the ventral fin; the skin (4), the stringer (2), the partition plate (3), the U-shaped beam (6), the bottom beam (1) and the front edge (5) are formed by riveting.

2. A combined aircraft ventral fin structure according to claim 1, characterised in that: the U-shaped beam (6) is made of aluminum alloy plates.

3. A combined aircraft ventral fin structure according to claim 1, characterised in that: the partition plate (3) is an aluminum alloy plate with a bent edge.

4. A combined aircraft ventral fin structure according to claim 1, characterised in that: the bottom beam (1) is an machined part.

5. A combined aircraft ventral fin structure according to claim 1, characterised in that: the plate bending piece (7) is Z-shaped.

6. A combined aircraft ventral fin structure according to claim 1, characterised in that: the thickness of the joint of the bottom beam (1) and the fuselage is 3-5mm, and the thickness of the joint of the bottom beam (1) and the skin is 3-5 mm.

7. A combined aircraft ventral fin structure according to claim 1, characterised in that: the thickness of the thin aluminum plate is 0.6-1.5 mm.