CN112027060B

CN112027060B - Energy-absorbing upright post for lower part of aircraft cargo compartment floor

Info

Publication number: CN112027060B
Application number: CN202010915897.6A
Authority: CN
Inventors: 汪洋; 吴志斌; 李琪; 刘富; 施萌; 高俊
Original assignee: Commercial Aircraft Corp of China Ltd
Current assignee: Commercial Aircraft Corp of China Ltd
Priority date: 2020-09-03
Filing date: 2020-09-03
Publication date: 2022-07-08
Anticipated expiration: 2040-09-03
Also published as: CN112027060A

Abstract

The invention relates to an energy-absorbing pillar (2) for the underside of a cargo compartment floor of an aircraft, the energy-absorbing pillar (2) having a first end (21) which is connected to a fuselage frame (3) of the aircraft and a second end (22) which is opposite the first end (21) in the longitudinal extension thereof and is connected to the cargo compartment floor (1) of the aircraft, the energy-absorbing pillar (2) comprising: a base portion (2.1) extending in a longitudinal direction thereof; and a rim (2.2) extending from each lateral side of the base part (2.1), the rim being bent in the same direction in relation to the base part (2.1) such that the energy-absorbing pillar (2) has a substantially C-shaped cross-sectional shape, characterized in that the base part (2.1) is a combination of a straight section and a corrugated section.

Description

Energy-absorbing upright post for lower part of aircraft cargo compartment floor

Technical Field

The invention relates to the field of aircraft manufacturing, in particular to an energy-absorbing upright column used at the lower part of a cargo compartment floor of an aircraft.

Background

In recent years, composite materials are widely used in civil aircraft structures and are gradually applied to main load-bearing structures. Compared with the traditional aluminum alloy material, the composite material can effectively reduce the quality of the airplane, greatly reduce the requirement on relevant inspection of the fatigue degree of the airplane body, and greatly improve the falling adaptation design difficulty of the airplane due to the brittle characteristic of the composite material. The lower structure of the cargo compartment floor is the part which contacts the ground firstly in the falling collision process, the structural response and the energy absorption efficiency of the lower structure influence the falling collision resistance effect of the integral fuselage, wherein the upright post of the cargo compartment floor made of the composite material not only can support the cargo compartment floor, but also is a key element for falling collision energy absorption of the lower structure of the cargo compartment.

The columns of the cargo compartment floor are usually C-shaped composite material columns, which are relatively simple to manufacture and assemble, but have low energy absorption efficiency due to crush failure and are easily unstable and break under a crash impact load, resulting in limited energy absorption.

Disclosure of Invention

Based on the prior art, the invention aims to provide an energy-absorbing upright post for the lower part of a cargo compartment floor of an airplane, which not only can be used for supporting the cargo compartment floor of the airplane and the load weight of the cargo compartment in the normal state of the airplane, but also can improve the energy-absorbing efficiency of the energy-absorbing upright post when the airplane crashes and reduce the load born by passengers when the passengers crash.

This object is achieved by the invention in the form of a following, energy-absorbing pillar for the lower part of the floor of a cargo compartment of an aircraft. The energy-absorbing pillar has a first end connected to a fuselage frame of the aircraft and a second end opposite the first end in the direction of its longitudinal extension and connected to a cargo compartment floor of the aircraft, the energy-absorbing pillar comprising: a base portion extending longitudinally therealong; and the flanges respectively extend from two transverse sides of the base body part, and are bent towards the same direction relative to the base body part, so that the energy-absorbing upright column has a cross-sectional shape which is approximately C-shaped, and the base body part is a combination of a straight line section and a corrugated section.

The base body is divided into the combination of the straight line section and the corrugated section, so that the stability of the energy-absorbing upright post is improved, the energy-absorbing upright post is not easy to break, and the energy-absorbing efficiency of the energy-absorbing upright post in crushing is further improved.

According to a preferred embodiment of the invention, the base part comprises at least two rectilinear segments at its two ends, each connected to a respective one of the flanges, and a corrugated segment between the two rectilinear segments.

The linear section provides a mounting location for the fasteners, thus eliminating the need for additional structure for connecting the energy-absorbing pillar to the fuselage frame and the aircraft cargo compartment floor of the aircraft, thereby reducing the weight of the overall structure and reducing the difficulty of assembly.

According to a preferred embodiment of the invention, at least one further straight section is included in the corrugated section.

According to a preferred embodiment of the invention, the corrugated section of the base part is of a corrugated shape formed by alternately connecting at least two identical semi-circular parts in an arcuate manner in opposite directions.

Compared with the common C-shaped energy-absorbing upright post without the corrugated structure with the same size, the energy-absorbing upright post has the advantage that the energy absorbed by the unit mass is obviously improved.

According to a preferred embodiment of the invention, the energy absorbing pillar is made of a composite material.

The composite material is used, so that the energy-absorbing upright post is torn in a layered manner when being cracked and is damaged from bottom to top, and a large amount of energy can be absorbed during the process, so that the energy-absorbing efficiency of the energy-absorbing upright post during crushing is improved.

According to a preferred embodiment of the invention, the energy-absorbing pillar has a chamfer at the first end in the direction of the wall thickness of the energy-absorbing pillar.

The beveling part provides a weak part, weakens the strength of the lower end of the energy-absorbing upright post, so that the energy-absorbing upright post is damaged from the weak part after the frame of the airplane body touches the ground, the stress of the energy-absorbing upright post intensively enters a stable crushing stage, and the energy-absorbing upright post is prevented from being directly broken under a large drop-impact load.

According to a preferred embodiment of the invention, the energy-absorbing pillar is arranged between the fuselage frame of the aircraft and the aircraft cargo compartment floor at an angle θ relative to the vertical, and the angle θ is between 0 and 85 °.

According to a preferred embodiment of the invention, the energy-absorbing pillar is integrally formed.

The integrally formed energy-absorbing upright post has the advantages of stable structure, simple assembly, light weight and simple manufacturing process.

According to a preferred embodiment of the present invention, the energy-absorbing pillar is connected to the fuselage frame of the aircraft and to the aircraft cargo compartment floor by a fastener, and the connection strength of the energy-absorbing pillar to the aircraft cargo compartment floor is higher than the connection strength of the energy-absorbing pillar to the fuselage frame of the aircraft. Therefore, after the fuselage frame of the airplane touches the ground, the fasteners at the lower end of the energy-absorbing upright post are immediately sheared and damaged, and the lower end of the energy-absorbing upright post directly contacts the fuselage frame, so that the integrity of the energy-absorbing upright post is maintained, and the energy-absorbing upright post is not broken.

According to a preferred embodiment of the present invention, the linear section of the energy-absorbing pillar is fixedly connected to the fuselage frame and the cargo compartment floor of the aircraft by high-lock bolts, respectively, and the number of the high-lock bolts used for connecting the energy-absorbing pillar to the cargo compartment floor is greater than the number of the high-lock bolts used for connecting the energy-absorbing pillar to the fuselage frame, so that the connection strength between the energy-absorbing pillar and the cargo compartment floor is higher than the connection strength between the energy-absorbing pillar and the fuselage frame. The high lock bolt used in the present invention is particularly suitable for composite materials.

According to a preferred embodiment of the invention, at least two energy-absorbing struts are arranged between the fuselage frame of the aircraft and the aircraft cargo compartment floor.

According to a preferred embodiment of the invention, adjacent energy-absorbing struts are arranged symmetrically to each other.

The energy absorbing uprights thus provide a more stable support for the aircraft cargo compartment floor in the normal state of the aircraft.

Drawings

For a better understanding of the above and other objects, features, advantages and functions of the present invention, reference should be made to the preferred embodiments illustrated in the accompanying drawings. Like reference numerals in the drawings refer to like parts. It will be appreciated by persons skilled in the art that the drawings are intended to illustrate preferred embodiments of the invention without any limiting effect on the scope of the invention, and that the various components in the drawings are not drawn to scale.

Fig. 1 shows a schematic structural view of an energy-absorbing pillar according to the invention for use under the floor of an aircraft cargo compartment.

FIG. 2 shows a perspective view of the energy absorbing pillar of FIG. 1.

Figure 3 shows a cross-section of the energy absorbing pillar of figure 2.

Fig. 4 shows a close-up view of a first end of the energy-absorbing strut of fig. 2 connected to a fuselage frame of an aircraft.

Fig. 5 shows an enlarged view of the connection of the energy-absorbing strut to the fuselage frame of the aircraft.

List of reference numerals

Aircraft cargo compartment floor 1

Energy-absorbing upright post 2

Fuselage frame 3 of an aircraft

First end 21 of an energy-absorbing pillar connected to the fuselage frame of an aircraft

Second end 22 of energy-absorbing pillar attached to aircraft cargo compartment floor

Base part 2.1

Edge strip 2.2

Corrugated section 2.12

Straight line segment 2.11

Bevel 4

Angle theta between energy-absorbing upright column and vertical direction

Detailed Description

The inventive concept of the present invention will be described in detail below with reference to the accompanying drawings. What has been described herein is merely a preferred embodiment in accordance with the present invention and other ways of practicing the invention will occur to those skilled in the art and are within the scope of the invention. In the following detailed description, directional terms, such as "upper", "lower", "inner", "outer", and the like, are used with reference to the orientation depicted in the accompanying drawings. Components of embodiments of the present invention can be positioned in a number of different orientations and the directional terminology is used for purposes of illustration and is in no way limiting.

The "bending" in the present invention does not merely mean that the adjacent portions are bent by pressing. In fact, the term "bent" in the present invention means that the adjacent portions and the portions connected to each other are angled with respect to each other.

In the invention, "longitudinal" refers to the length extension direction of the energy-absorbing upright column, and "transverse" refers to the width direction of the energy-absorbing upright column, wherein the transverse direction is vertical to the longitudinal direction. The wall thickness direction is respectively vertical to the transverse direction and the longitudinal direction of the energy-absorbing upright post.

Fig. 1 shows a schematic structural view of an energy-absorbing pillar 2 according to the invention for the lower part of the cargo compartment floor of an aircraft. An energy-absorbing pillar 2 for the lower part of the aircraft cargo compartment floor is mounted between the aircraft cargo compartment floor 1 and the fuselage frame 3 of the aircraft. In fig. 1, two energy-absorbing pillars 2 are schematically shown, the two energy-absorbing pillars 2 each being arranged at an angle θ to the vertical, as can be seen in the enlarged view of the connection of the energy-absorbing pillars 2 to the fuselage frame 3 of the aircraft in fig. 5. Preferably, the two energy-absorbing uprights 2 are arranged symmetrically.

FIG. 2 shows a perspective view of the energy absorbing pillar of FIG. 1. The energy-absorbing upright 2 is made of composite material. The energy-absorbing strut 2 is connected in its longitudinal direction with a first end 21 to the fuselage frame 3 of the aircraft and with a second end 22 to the aircraft cargo compartment floor 1.

The energy-absorbing pillar 2 comprises a base part 2.1 and flanges 2.2 extending from the base part 2.1 on both lateral sides thereof and bent in the same direction with respect to the base part 2.1, so that the energy-absorbing pillar 2 has a substantially C-shaped cross-section.

Figure 3 shows a cross section of the energy absorbing pillar 2 in figure 2. The cross section of the base part 2.1 is substantially corrugated. The base part 2.1 comprises a corrugated section 2.12 and two straight sections 2.11, the base part 2.1 being connected with the rim 2.2 in each case by the two straight sections 2.11 and the corrugated section 2.12 being connected between the two straight sections 2.11. The straight sections 2.11 are used for installing fastening elements when the energy-absorbing strut 2 is later installed, by means of which the energy-absorbing strut 2 is fastened to the fuselage frame 3 of the aircraft and to the aircraft cargo compartment floor 1. The cross section of the base body part 2.1 is preferably corrugated in shape, which is formed by a plurality of, in particular at least two, identical semi-circular parts which are alternately connected in an arched manner in opposite directions. It is also possible to include at least one further straight section in the corrugated section 2.12.

Fig. 4 shows a close-up view of a first end of the energy-absorbing strut 2 from fig. 2, which is connected to a fuselage frame 3 of an aircraft. The energy-absorbing pillar 2 has a chamfer 4 at its first end 21, which is connected to the fuselage frame 3 of the aircraft, in the direction of the wall thickness of the energy-absorbing pillar 2.

When the energy-absorbing strut 2 is installed, a first end 21 of the energy-absorbing strut 2 is fastened to the fuselage frame 3 of the aircraft by means of a fastening element and a second end 22 of the energy-absorbing strut 2 is fastened to the aircraft cargo compartment floor 1 by means of a fastening element, wherein the first end 21 has a chamfer. The fastener may be, for example, a high lock bolt. Of course any other suitable fastener is conceivable, for example by riveting or the like. Furthermore, the connection strength of the second end 22 of the energy-absorbing strut 2 to the aircraft cargo compartment floor 1 should be higher than the connection strength of the first end 21 of the energy-absorbing strut 2 to the aircraft fuselage frame 3, i.e. be more firmly fixed, for example, the first end 21 of the energy-absorbing strut 2 is fixed to the aircraft fuselage frame 3 by means of four high-lock bolts, while the second end 22 of the energy-absorbing strut 2 is fixed to the aircraft cargo compartment floor 1 by means of six high-lock bolts. Furthermore, the fasteners are each mounted at a straight section 2.11 of the energy absorbing pillar 2.

In addition, more than two energy-absorbing uprights 2 can be installed between the aircraft cargo compartment floor 1 and the fuselage frame 3 of the aircraft. Preferably, adjacent energy-absorbing pillars are symmetrically mounted to each other. The angle theta between the energy-absorbing upright 2 and the vertical direction is 0-85 degrees, and preferably 0 degrees.

The energy-absorbing pillar 2 according to the invention can be formed in one piece.

The energy-absorbing upright column used at the lower part of the cargo compartment floor of the airplane works in the following mode:

under the normal state of the airplane, the energy absorption upright post is used for supporting the cargo compartment floor of the airplane and the cargo compartment load weight at the lower part.

After the fuselage frame 3 of the airplane touches down during the crash of the airplane, the high-locking bolt connecting the energy-absorbing upright post 2 and the fuselage frame 3 of the airplane is firstly sheared and damaged due to the larger crash load, and at the moment, the fixing of the energy-absorbing upright post 2 and the fuselage frame 3 of the airplane is still kept and is not damaged due to the fact that the connecting strength of the energy-absorbing upright post 2 and the airplane cargo compartment floor 1 is higher than that of the energy-absorbing upright post 2 and the fuselage frame 3 of the airplane. In addition, since the energy-absorbing pillar 2 has a chamfer 4 at its first end 21 connected to the fuselage frame 3 of the aircraft, this results in a weak point at the first end 21, from which point the energy-absorbing pillar 2 can be broken without the energy-absorbing pillar breaking off directly. The composite material of the energy-absorbing upright column enables the energy-absorbing upright column to be torn in a layered mode and damaged from bottom to top, and a large amount of energy can be absorbed in the process, so that the energy-absorbing efficiency of the energy-absorbing upright column during crushing is improved.

Compared with the prior art, the energy-absorbing upright post for the lower part of the cargo compartment floor of the airplane has the following advantages:

1. the stability of the energy-absorbing column is improved by providing the base part 2.1 of the energy-absorbing column 2 with corrugated sections, in particular in the form of corrugations which are formed by alternately connecting a plurality of identical semicircular parts in an arched manner in opposite directions, so that the energy-absorbing column is not easily broken and the energy-absorbing efficiency of the energy-absorbing column is increased when the energy-absorbing column is crushed.

2. By providing the base portion 2.1 of the energy-absorbing pillar 2 with a corrugated section and a straight section, an installation location for the fastening is provided, so that no additional structure is required for connecting the energy-absorbing pillar to the fuselage frame of the aircraft and to the aircraft cargo compartment floor, thereby reducing the weight of the overall structure and the difficulty of assembly. In addition, compared with the common C-shaped energy-absorbing upright post without the corrugated section with the same size, the energy-absorbing upright post has the advantage that the energy absorbed by the unit mass is obviously improved.

3. The chamfer part constructed at the first end part 21 of the energy-absorbing upright post 2 connected with the fuselage frame 3 of the airplane weakens the strength of the lower end of the energy-absorbing upright post, so that the stress of the energy-absorbing upright post is concentrated to enter a stable crushing stage after the fuselage frame 3 of the airplane touches the ground, and the energy-absorbing upright post is prevented from being directly broken under a large drop-impact load.

4. By designing the connection strength of the second end part 22 of the energy-absorbing upright post 2 on the cargo compartment floor 1 of the airplane to be higher than the connection strength of the first end part 21 of the energy-absorbing upright post 2 on the fuselage frame 3 of the airplane, the fastener at the lower end of the energy-absorbing upright post is immediately sheared and damaged after the fuselage frame 3 of the airplane touches the ground, and the lower end of the energy-absorbing upright post directly contacts the fuselage frame, so that the integrity of the energy-absorbing upright post is maintained without breaking.

5. The composite material of the energy-absorbing upright post 2 enables the energy-absorbing upright post to be torn in a layered mode and damaged from bottom to top, and a large amount of energy can be absorbed in the process, so that the energy-absorbing efficiency of the energy-absorbing upright post during crushing is improved.

6. The high lock bolt used in the present invention is particularly suitable for composite materials.

7. By integrally forming the energy-absorbing upright post 2, the advantages of stable structure, simple assembly, light weight and simple manufacturing process are realized.

The scope of the invention is limited only by the claims. Persons of ordinary skill in the art, having benefit of the teachings of the present disclosure, will readily appreciate that alternative structures to the disclosed structures can be substituted for the possible embodiments and that the disclosed embodiments can be combined to create new embodiments that also fall within the scope of the appended claims.

Claims

1. An energy-absorbing pillar (2) for an aircraft cargo compartment floor lower portion, the energy-absorbing pillar (2) having a first end portion (21) connected to a fuselage frame (3) of an aircraft and a second end portion (22) opposite the first end portion (21) in the direction of its longitudinal extension and connected to an aircraft cargo compartment floor (1), the energy-absorbing pillar (2) comprising: a base portion (2.1) extending in a longitudinal direction thereof; and a rim (2.2) extending from each of the two lateral sides of the base part (2.1), the rim being bent in the same direction relative to the base part (2.1) such that the energy-absorbing pillar (2) has a substantially C-shaped cross-sectional shape, characterized in that the base part (2.1) is a combination of a straight section and a corrugated section, the base part (2.1) comprising at least two straight sections (2.11) at its two ends and connected to the respective rim (2.2) and a corrugated section (2.12) between the two straight sections (2.11), at least one further straight section being included in the corrugated section (2.12), and the outer surface of the straight section (2.11) being laterally flush with the outer surface of the corrugated section (2.12),

wherein, energy-absorbing stand (2) set up for vertical direction angle theta fuselage frame (3) with between aircraft cargo hold floor (1), and angle theta is between 0 to 85, energy-absorbing stand (2) straight line section (2.11) through high-locking bolt respectively with fuselage frame (3) and aircraft cargo hold floor (1) fixed connection, wherein energy-absorbing stand (2) with the number of high-locking bolt that aircraft cargo hold floor (1) was connected and is used is greater than with the number of high-locking bolt that uses is connected to fuselage frame (3), thereby makes energy-absorbing stand (2) with the joint strength on aircraft cargo hold floor (1) is than energy-absorbing stand (2) with the joint strength of fuselage frame (3) is higher.

2. Energy-absorbing pillar (2) for an aircraft cargo compartment floor lower part according to claim 1, characterized in that the corrugated section (2.12) of the base body part (2.1) is of a corrugated shape which is connected by at least two identical semicircular parts alternately arched in opposite directions.

3. Energy-absorbing pillar (2) for the lower part of the floor of a cargo compartment of an aircraft according to claim 1 or 2, characterized in that the energy-absorbing pillar (2) consists of a composite material.

4. Energy-absorbing pillar (2) for an aircraft cargo compartment underfloor according to claim 1 or 2, characterized in that the energy-absorbing pillar (2) has a chamfer (4) at the first end (21) in the direction of the wall thickness of the energy-absorbing pillar (2).

5. Energy-absorbing pillar (2) for the lower part of the floor of a cargo compartment of an aircraft according to claim 1 or 2, characterized in that the energy-absorbing pillar (2) is integrally formed.

6. Energy-absorbing pillar (2) for an aircraft cargo compartment floor lower part according to claim 1 or 2, characterized in that the energy-absorbing pillar (2) is connected with the fuselage frame (3) and the aircraft cargo compartment floor (1) by means of fasteners, the connection strength of the energy-absorbing pillar (2) with the aircraft cargo compartment floor (1) being higher than the connection strength of the energy-absorbing pillar (2) with the fuselage frame (3).

7. Energy-absorbing pillar (2) for an aircraft cargo compartment floor lower part according to claim 1 or 2, characterized in that at least two energy-absorbing pillars (2) are provided between the fuselage frame (3) and the aircraft cargo compartment floor (1).

8. Energy-absorbing pillar (2) for an aircraft cargo compartment underfloor according to claim 7, characterized in that adjacent energy-absorbing pillars (2) are arranged symmetrically to one another.