CN215794411U

CN215794411U - Integrated skin for reducing weight of airplane structure

Info

Publication number: CN215794411U
Application number: CN202121926986.7U
Authority: CN
Inventors: 吴家鑫; 邹瑜光; 左轶; 冯欣; 肖春婷
Original assignee: Jc General Aircraft Design Manufacturing Dalian Co ltd
Current assignee: Jc General Aircraft Design Manufacturing Dalian Co ltd
Priority date: 2021-08-17
Filing date: 2021-08-17
Publication date: 2022-02-11
Anticipated expiration: 2031-08-17

Abstract

The utility model discloses an integrated skin for reducing the structural weight of an airplane, which comprises an upper airfoil skin, a skin web and a lower airfoil skin which are of an integrated structure, wherein one side of the skin web is connected with the upper airfoil skin, the other side of the skin web is connected with the lower airfoil skin, an accommodating cavity is formed by the upper airfoil skin, the skin web, the lower airfoil skin and the lower airfoil skin, a plurality of vertical stabilizer middle ribs are arranged in the accommodating cavity at intervals, one end of each vertical stabilizer middle rib is connected with the skin web, the other end of each vertical stabilizer middle rib is connected with a rear wing beam, and the rear wing beam is positioned on the opening side of the accommodating cavity. According to the application, the front wing spar of the vertical stabilizer, the upper wing skin of the vertical stabilizer and the lower wing skin of the vertical stabilizer are designed into an integrated skin, so that the structural weight of the vertical stabilizer is reduced, and the stress concentration of the connecting hole is also reduced.

Description

Integrated skin for reducing weight of airplane structure

Technical Field

The utility model relates to the field of design and manufacture of airplanes, in particular to an integrated skin for reducing the weight of an airplane structure.

Background

The vertical stabilizer of the airplane is a fixed part of a vertical tail and plays a role in balancing the course; spars are longitudinal members of the airfoil that are primarily subjected to bending moments and shear forces; the wing ribs are transverse stress frameworks in the wing surface, generally conform to the shape of the wing profile, and are used for maintaining the section shape of the wing surface and bearing local loads of the skin.

In the prior art, the vertical stabilizer of the airplane is formed by connecting a front wing beam, an upper wing surface skin of the vertical stabilizer, a lower wing surface skin of the vertical stabilizer, a plate-shaped metal wing rib, a reinforcing part, a rear wing beam and a front edge skin together through a fastener; the vertical stabilizer structure is formed by connecting a plurality of parts through fasteners, so that the weight is large, the parts are required to be provided with connecting holes when being connected, the connecting hole areas are mostly stress concentration areas, and the stress is too concentrated to cause cracks at the lap joint of the skin and the front wing beam and even to break.

SUMMERY OF THE UTILITY MODEL

To prior art have above-mentioned problem, this application designs into integral type covering with the front spar of perpendicular stabilizer, the upper airfoil skin of perpendicular stabilizer and the lower airfoil skin of perpendicular stabilizer, has both alleviateed the structural weight of perpendicular stabilizer, has still reduced the stress concentration of connecting hole.

In order to achieve the purpose, the technical scheme of the application is as follows: the utility model provides a alleviate integral type covering of aircraft structure weight, includes last airfoil skin, skin web and the lower airfoil skin of a body structure, skin web one side links to each other with last airfoil skin, and the opposite side links to each other with lower airfoil skin, and the three forms one and holds the chamber, and the interval is provided with a plurality of perpendicular planes of ann in this holds the chamber, and rib one end links to each other with the skin web in every perpendicular plane of ann, and the other end links to each other with the back spar, the back spar is located the opening side that holds the chamber.

Furthermore, a front edge skin is lapped at the connecting and bending part of the skin web plate and the upper airfoil skin and the connecting and bending part of the skin web plate and the lower airfoil skin, and a front edge cavity is formed between the front edge skin and the skin web plate.

Furthermore, one end of the front edge skin is connected with a wing tip fairing, and a front edge end rib plate is obliquely arranged at the top of the other end of the front edge skin.

Further, a front edge rib plate a is arranged at the wing root end of the front edge cavity, and a support piece is arranged at the wing tip end; at least one leading edge rib b is arranged inside the leading edge cavity.

Furthermore, the vertical stabilizing surface middle ribs are a vertical stabilizing surface middle rib a, a vertical stabilizing surface middle rib b and a vertical stabilizing surface middle rib c respectively, and the vertical stabilizing surface middle rib a is located at the root end of the accommodating cavity.

Furthermore, one end of each of the vertical stabilizer middle rib a and the vertical stabilizer middle rib b is connected with a reinforcing short beam, the other end of each of the vertical stabilizer middle ribs is located in a reinforcing guard plate, the reinforcing short beams are in contact with the inner wall of the skin web, and the reinforcing guard plates are located on two sides of the rear wing beam.

Furthermore, the support piece comprises a leading edge rib plate c, a leading edge rib plate d and a vertical stabilizing surface middle rib d, wherein the leading edge rib plate c and the leading edge rib plate d are connected with the leading edge short beam and are positioned in the leading edge cavity, and the vertical stabilizing surface middle rib d is positioned at the wing tip end of the accommodating cavity.

Furthermore, wing tip reinforcing band plates are arranged on two sides of the skin web plate, and the leading edge rib plate c is located between the wing tip reinforcing band plates.

As a further step, a plurality of sets of lightening holes are arranged on the skin web.

Furthermore, a plurality of crimping lightening holes are formed in the rear wing beam, the vertical stabilizer middle rib a, the vertical stabilizer middle rib b, the vertical stabilizer middle rib c, the reinforcing short beam, the leading edge rib plate a and the leading edge rib plate b.

Due to the adoption of the technical scheme, the utility model can obtain the following technical effects: according to the application, the front wing beam of the vertical stabilizer, the upper wing skin of the vertical stabilizer and the lower wing skin of the vertical stabilizer are designed into an integrated skin, so that the structural weight of the vertical stabilizer can be reduced, the number of connecting holes of the vertical stabilizer is also reduced, and the stress concentration of the connecting holes is reduced; the skin web plate does not need workers to additionally perform assembly work such as riveting and the like, can be integrally installed with surrounding structural parts, saves the time of the workers and improves the working efficiency.

Drawings

FIG. 1 is an exploded view of an integral skin for reducing the weight of an aircraft structure;

FIG. 2 is a schematic illustration of an integral skin structure for reducing the weight of an aircraft structure;

the sequence numbers in the figures illustrate: 1-leading edge skin, 2-integrated skin, 3-leading edge end rib plate, 4-leading edge rib plate a, 5-leading edge rib plate b, 6-reinforced short beam, 7-vertical stabilizer middle rib a, 8-vertical stabilizer middle rib b, 9-reinforced guard plate, 10-rear wing spar, 11-vertical stabilizer middle rib c, 12-wing tip reinforced band plate, 13-wing tip fairing, 14-leading edge rib plate c, 15-leading edge rib plate d, 16-leading edge short beam and 17-vertical stabilizer middle rib d.

Detailed Description

The embodiments of the present invention are implemented on the premise of the technical solution of the present invention, and detailed embodiments and specific operation procedures are given, but the scope of the present invention is not limited to the following embodiments.

Example 1

The vertical fin structure is not only subjected to its own aerodynamic and inertial loads, but also to the concentrated loads transmitted by the rudder through its suspension and steering joints. To achieve sufficient critical flutter speed and to ensure proper rudder deflection, the vertical stabilizer is typically designed for stiffness, and the choice of design directly affects its stiffness and strength properties. As shown in fig. 1-2, the vertical stabilizer of the present application is formed by connecting a front edge skin, an integral skin, a metal rib plate, a reinforcing short beam, a reinforcing member, a rear wing beam and a wing tip fairing through fasteners, wherein the metal rib plate, the reinforcing short beam and the rear wing beam are provided with lightening holes with bent edges, i.e. lightening the structure, so that the rigidity of parts is ensured, the lightening holes also leave routing lines and steel cable arrangement channels for an avionic system and a construction system, and the problem that the steel cables cannot be arranged and routed because the vertical stabilizer is a closed box body is solved. The integrated skin designs the conventional vertical stable surface front wing beam, the upper wing surface skin of the vertical stable surface and the lower wing surface skin of the vertical stable surface into a whole, so that the weight of a part overlapping area is reduced, meanwhile, the stress concentration of a connecting fastener and a connecting hole is reduced, and the skin web plate of the integrated skin is provided with a bent edge lightening hole to fully lighten the part. The skin web is used as a front wing beam, the load of the root part of the wing is the largest when the vertical stabilizing surface structure bears the load, and the strength of the vertical stabilizing surface is improved by adding the reinforcing short beam on the inner side of the root part of the skin web. The integral skin appearance is formed by connecting a plate-shaped metal rib plate with a wing-shaped skin through a rivet to maintain the wing-shaped shape of the vertical stabilizer and bear the local load of the skin. The integral type covering is great with the consideration root load when the back wing spar is connected, so increase at back wing spar root and strengthen backplate and rivet with the integral type covering, improve the holistic intensity of perpendicular stabilizer in order to guarantee perpendicular stabilizer design requirement.

It will be evident to those skilled in the art that the utility model is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the utility model being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.

Claims

1. The utility model provides a lighten integral type covering of aircraft structure weight, its characterized in that, includes last airfoil skin, skin web and the lower airfoil skin of a body structure, skin web one side links to each other with last airfoil skin, and the opposite side links to each other with lower airfoil skin, and the three forms one and holds the chamber, and the interval is provided with a plurality of perpendicular planes of ann in this holds the chamber, and rib one end links to each other with the skin web in every perpendicular plane of ann, and the other end links to each other with the back wing spar, the back wing spar is located the opening side that holds the chamber.

2. The integral skin for reducing the weight of an aircraft structure as recited in claim 1, wherein a leading edge skin is overlapped at the connecting and bending part of the skin web and the upper airfoil skin and the connecting and bending part of the skin web and the lower airfoil skin, and a leading edge cavity is formed between the leading edge skin and the skin web.

3. The integral skin for reducing the weight of an aircraft structure of claim 2, wherein the leading edge skin has a tip fairing attached to one end and a leading edge tip rib angled to the top of the other end.

4. The integral skin for reducing the weight of an aircraft structure as recited in claim 2, wherein the root end of the leading edge cavity is provided with a leading edge rib a, and the tip end is provided with a strut member; at least one leading edge rib b is arranged inside the leading edge cavity.

5. The integral skin for reducing the weight of an aircraft structure of claim 1, wherein the plurality of vertical stabilizer center ribs are a vertical stabilizer center rib a, a vertical stabilizer center rib b, and a vertical stabilizer center rib c, respectively, and the vertical stabilizer center rib a is located at a root end of the receiving cavity.

6. The integral skin for reducing the weight of the aircraft structure according to claim 5, wherein the rib a in the vertical stabilizer and the rib b in the vertical stabilizer are connected with a short reinforcing beam at one end and positioned in a reinforcing guard plate at the other end, the short reinforcing beam is in contact with the inner wall of a web of the skin, and the reinforcing guard plate is positioned on two sides of the rear wing spar.

7. The integral skin for reducing the weight of an aircraft structure according to claim 4, wherein the support comprises a leading edge rib plate c, a leading edge rib plate d and a vertical stabilizing surface middle rib d, wherein the leading edge rib plate c and the leading edge rib plate d are connected with the leading edge short beam, the leading edge rib plate c and the leading edge rib plate d are located in the leading edge cavity, and the vertical stabilizing surface middle rib d is located at the wing tip end of the accommodating cavity.

8. The integral skin for reducing the weight of an aircraft structure of claim 1, wherein the skin web is flanked by tip stiffened straps, and wherein the leading edge rib c is located between the tip stiffened straps.

9. The unitary skin for reducing the weight of an aircraft structure of claim 1, wherein the skin web is provided with a plurality of sets of lightening holes.

10. The integral skin for reducing the weight of an aircraft structure according to claim 1, wherein the rear spar, the vertical stabilizer bar a, the vertical stabilizer bar b, the vertical stabilizer bar c, the reinforcing short beam, the leading edge rib plate a and the leading edge rib plate b are provided with a plurality of crimping lightening holes.