CN212667637U

CN212667637U - Drainage structure of aircraft

Info

Publication number: CN212667637U
Application number: CN202021725314.5U
Authority: CN
Inventors: 许灯顺; 贺集乐; 孟令赛; 周斌; 徐庆华
Original assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Current assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority date: 2020-08-18
Filing date: 2020-08-18
Publication date: 2021-03-09
Anticipated expiration: 2030-08-18

Abstract

The application belongs to the technical field of aircraft drainage, in particular to aircraft drainage structure. The method comprises the following steps: a first opening is formed at the junction of the first stringer and the common frame on the inner side of the lower wallboard of the fuselage to form a longitudinal first circulation passage; a second opening is arranged at the junction of the first stringer and the reinforcing frame to form a transverse second circulation passage; the lowest part of the lower wall plate of the body is provided with a first drainage hole, and the first circulation passage and the second circulation passage are both intersected with the first drainage hole; a third opening is formed at the intersection of the second stringer and the common rib on the inner side of the lower wing panel to form a third spanwise flow passage; a fourth opening is arranged at the intersection of the second stringer and the reinforcing rib to form a chord-wise fourth circulation passage; the lowest part of the wing lower wall plate is provided with a second drain hole, and the third flow passage and the fourth flow passage are all intersected with the second drain hole. The method and the device can meet the drainage requirement of the aircraft under the condition of basically having no influence on the outer surface of the aircraft.

Description

Drainage structure of aircraft

Technical Field

The application belongs to the technical field of aircraft drainage, in particular to aircraft drainage structure.

Background

The design requirements of the aircraft drainage scheme are as follows: firstly, the accumulated water in the aircraft is guaranteed to be drained out of the aircraft under the ground state; the second is to reduce the impact on the outer surface of the aircraft. The existing drainage scheme at home and abroad has great destructiveness on the outer surface of the aircraft.

Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

SUMMERY OF THE UTILITY MODEL

The object of the present application is to provide an aircraft drainage structure to solve at least one problem existing in the prior art.

The technical scheme of the application is as follows:

an aircraft drainage structure comprising:

a lower wall plate of the fuselage, the inner side of the lower wall plate of the fuselage is provided with a first stringer along the longitudinal direction, and is provided with a common frame and a reinforcing frame along the transverse direction, wherein,

a first opening is formed in a frame web plate of the common frame at the intersection of the first stringer and the common frame to form a longitudinal first circulation passage;

a second opening is arranged between the first stringer and the reinforcing frame at the intersection of the first stringer and the reinforcing frame to form a transverse second flow passage;

a first drainage hole is formed in the lowest position of the lower wall plate of the body, and the first circulation passage and the second circulation passage are intersected with the first drainage hole;

a wing lower wall plate, the inner side of which is provided with a second stringer along the spanwise direction and is provided with a common rib and a reinforcing rib along the chordwise direction, wherein,

a rib web plate of the common rib is provided with a third opening at the intersection of the second stringer and the common rib to form a third flow passage in the unfolding direction;

a fourth opening is arranged between the second stringer and the reinforcing rib at the intersection of the second stringer and the reinforcing rib to form a chordwise fourth flow passage;

the lowest part of the lower wing wall plate is provided with a second drain hole, and the third flow passage and the fourth flow passage are intersected with the second drain hole.

Optionally, the first stringers are disposed in parallel in a longitudinal direction on an inner side of the fuselage lower panel.

Optionally, the inner side of the fuselage bottom wall panel is provided with first longitudinal members at both ends in the transverse direction.

Optionally, the first opening is triangular.

Optionally, the second stringers are arranged in a plurality in parallel in a spanwise direction inboard of the wing lower panel.

Optionally, the inner side of the wing lower panel is provided with second longitudinal members at both chordwise ends.

Optionally, the third opening is circular.

Utility model has the following beneficial technical effects:

the utility model provides an aircraft drainage structures, destruction aircraft surface that can be less reduces the influence to the aircraft surface, and simple structure with aircraft structure integrated design, can satisfy the aircraft drainage requirement under the condition that basically does not have the influence to the aircraft surface.

Drawings

FIG. 1 is a schematic view of an overall fuselage drainage structure of an aircraft drainage structure according to an embodiment of the present application;

FIG. 2 is a schematic view of a first opening of an aircraft drainage structure according to one embodiment of the present application;

FIG. 3 is a schematic view of a second opening of an aircraft drainage structure according to one embodiment of the present application;

FIG. 4 is a schematic view of an overall wing drainage configuration of an aircraft drainage configuration of one embodiment of the present application;

FIG. 5 is a schematic view of a third opening of an aircraft drainage structure according to one embodiment of the present application;

FIG. 6 is a schematic view of a fourth opening of an aircraft drainage structure according to one embodiment of the present application.

Wherein:

11-a lower fuselage panel; 12-a common frame; 13-a reinforcement frame; 14-a first longitudinal member; 15-a first stringer; 16-a first opening; 17-a second opening; 18-a first drain hole; 21-wing lower wall plate; 22-common rib; 23-reinforcing ribs; 24-a second longitudinal member; 25-a second stringer; 26-a third opening; 27-a fourth opening; 28-second drain hole.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.

The present application is described in further detail below with reference to fig. 1 to 6.

The application provides an aircraft drainage structure arranged on a fuselage lower wall panel 11 and a wing lower wall panel 21.

Specifically, as shown in fig. 1, a first stringer 15 is longitudinally disposed on the inner side of the fuselage bottom wall panel 11, and a normal frame 12 and a reinforcing frame 13 are transversely disposed, wherein a first opening 16 is formed in a frame web of the normal frame 12 at an intersection of the longitudinally disposed first stringer 15 and the transversely disposed normal frame 12, so as to form a longitudinal first flow passage, so that accumulated water in the fuselage of the aircraft can flow along the first flow passage. A second transverse flow path is formed at the intersection of the longitudinally disposed first stringer 15 and the transversely disposed stiffening frame 13 by providing a second opening 17 between the first stringer 15 and the stiffening frame 13, so that standing water in the fuselage of the aircraft can flow along the second flow path; first drainage hole 18 has been seted up to the lowest of wallboard 11 under the fuselage, and first circulation route and second circulation route all intersect in first drainage hole 18, and ponding in the aircraft fuselage is by first circulation route and the final first drainage hole 18 that flows to the low department of second circulation route to from the aircraft of first drainage hole 18 discharge.

As shown in fig. 4, a second stringer 25 is arranged on the inner side of the wing lower wall plate 21 in the span-wise direction, and a common rib 22 and a reinforcing rib 23 are arranged in the chord-wise direction, wherein a third opening 26 is formed on a rib web of the common rib 22 at the intersection of the second stringer 25 arranged in the span-wise direction and the common rib 22 arranged in the chord-wise direction, so that a third flow passage in the span-wise direction is formed, and the ponding in the wing of the aircraft can flow along the third flow passage; at the intersection of the spanwise disposed second stringer 25 and the chordwise disposed stiffener 23, a chordwise fourth flow path is formed by providing a fourth opening 27 between the second stringer 25 and the stiffener 23, such that water trapped within the aircraft wing can flow along the fourth flow path; the lowest part of the wing lower wall plate 21 is provided with a second drain hole 28, the third flow passage and the fourth flow passage are both intersected with the second drain hole 28, and accumulated water in the wing of the aircraft finally flows to the second drain hole 28 at the lower part through the third flow passage and the fourth flow passage and is drained out of the aircraft from the second drain hole 28.

In a preferred embodiment of the present application, a plurality of first stringers 15 may be disposed in parallel along a longitudinal direction on an inner side of the fuselage lower wall panel 11, and openings through which ponding water passes are disposed between the first stringers 15 and each of the normal frames 12 and the reinforcing frames 13 of the fuselage to form a ponding circulation path, and finally, the ponding water is discharged from the aircraft through the lowest drainage hole to achieve a drainage effect at the fuselage. In the present embodiment, the first longitudinal members 14 are further provided on the inner side of the lower fuselage wall 11 at both ends in the lateral direction.

In a preferred embodiment of the present application, the first opening 16 and the second opening 17 are schematically illustrated in fig. 2 to 3, wherein the first opening 16 is arranged in a triangular shape.

In a preferred embodiment of the present application, a plurality of second stringers 25 may also be arranged in parallel along the span direction on the inner side of the wing lower wall panel 21, and openings for passing ponding water are provided between the second stringers 25 and each of the normal ribs 22 and the reinforcing ribs 23 of the wing to form a ponding water circulation path, and finally the ponding water is discharged from the aircraft through the lowest drainage hole to achieve the drainage effect at the wing. In this embodiment, the inner side of the wing lower wall panel 21 is further provided with second longitudinal members 24 at both chordwise ends.

In a preferred embodiment of the present application, the third opening 26 and the fourth opening 27 are schematically illustrated in fig. 5 to 6, wherein the third opening 26 is provided in a circular shape.

The application relates to an aircraft drainage structure, according to the specific appearance characteristics of aircraft, for example: the front part is high, the back part is low, the two sides are high, the middle part is low, the front part is high, the back part is high, the middle part is low, the front part is high, the middle part is low, and the like, and the front part and the back part are designed by combining the integrated design of the specific structural scheme of the aircraft, namely, a circulation passage from a high point to a low point is designed in the aircraft, and a drain hole is arranged at the lowest point. By arranging only a small number of drainage holes at the lowest point, the accumulated water in the aircraft flows to the lowest point in the aircraft and is drained from the lowest point to the outside of the aircraft.

The utility model provides an aircraft drainage structures, less destruction aircraft surface reduces the influence to the aircraft surface, and the wash port size that reasonable control was seted up can greatly reduced the influence to the surface, can reach no influence level basically.

The utility model relates to a can satisfy unmanned aerial vehicle's drainage design scheme, this technique is simple effective, with aircraft structure integrated design, can satisfy the aircraft drainage requirement under the condition that basically does not have the influence to the aircraft surface.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. An aircraft drainage structure, comprising:

a fuselage bottom panel (11), the inside of the fuselage bottom panel (11) being provided with a first stringer (15) in the longitudinal direction and a normal frame (12) and a reinforcement frame (13) in the transverse direction, wherein,

a first opening (16) is formed in a frame web plate of the common frame (12) at the intersection of the first stringer (15) and the common frame (12) to form a longitudinal first circulation passage;

a second opening (17) is arranged between the first stringer (15) and the reinforcing frame (13) at the intersection of the first stringer (15) and the reinforcing frame (13) to form a transverse second flow path;

a first drainage hole (18) is formed in the lowest position of the lower wall plate (11) of the body, and the first circulation passage and the second circulation passage are intersected with the first drainage hole (18);

a wing lower wall plate (21), wherein the inner side of the wing lower wall plate (21) is provided with a second stringer (25) along the spanwise direction, and is provided with a common rib (22) and a reinforcing rib (23) along the chordwise direction, wherein,

a third opening (26) is formed in a rib web plate of the common rib (22) at the intersection of the second stringer (25) and the common rib (22) to form a third flow passage in the unfolding direction;

a fourth opening (27) is arranged between the second stringer (25) and the reinforcing rib (23) at the intersection of the second stringer (25) and the reinforcing rib (23) to form a chord-wise fourth flow passage;

the lowest part of the wing lower wall plate (21) is provided with a second drain hole (28), and the third flow passage and the fourth flow passage are all intersected with the second drain hole (28).

2. The aircraft drainage structure according to claim 1, wherein the first stringers (15) are disposed in parallel in a longitudinal direction on an inner side of the fuselage bottom panel (11).

3. The aircraft drainage structure according to claim 2, characterized in that the inner side of the fuselage bottom wall panel (11) is provided with first longitudinal members (14) at both ends in the transverse direction.

4. The aircraft drainage structure according to claim 3, characterized in that the first opening (16) is triangular.

5. The aircraft drainage structure of claim 1, wherein the second stringers (25) are arranged in parallel in a spanwise direction on an inner side of the wing lower panel (21).

6. The aircraft drainage structure according to claim 5, characterized in that the inner side of the wing lower panel (21) is provided with second longitudinal members (24) at both chordwise ends.

7. The aircraft drainage structure according to claim 6, characterized in that the third opening (26) is circular.