CN113070648B

CN113070648B - Machining process for aviation seat frame

Info

Publication number: CN113070648B
Application number: CN202110397693.2A
Authority: CN
Inventors: 刘迪; 荣伟; 迟壮; 王东辉; 高雄; 周广宇
Original assignee: China Zhongwang Holdings Ltd
Current assignee: China Zhongwang Holdings Ltd
Priority date: 2021-04-14
Filing date: 2021-04-14
Publication date: 2022-07-15
Anticipated expiration: 2041-04-14
Also published as: CN113070648A

Abstract

The invention belongs to the field of aluminum alloy processing and manufacturing, and relates to a processing technology of an aviation seat frame, which comprises the steps of firstly carrying out extrusion, then carrying out bending, punching and welding processing to obtain the required aviation seat frame, and carrying out heat treatment on the aluminum alloy aviation seat frame for reinforcement after processing; the problem of the aircraft seat frame performance intensity that prior art prepared can not tolerate huge impact force, influence passenger's comfort level is solved, through the improvement of processing technology method, promote aircraft seat frame performance intensity, reduce the aerial injury that the aircraft seat frame does not satisfy the performance requirement and thereby lead to.

Description

Machining process for aviation seat frame

Technical Field

The invention belongs to the field of aluminum alloy machining and manufacturing, and relates to a machining process of an aircraft seat frame.

Background

In the field of civil aviation, when an airliner accelerates in the air, a passenger can be pressed backwards by inertia, and a seat can bear backward acting force; the seat is also subjected to a forward force during an emergency deceleration of the aircraft for any reason. If the seat frame performance is not satisfactory, it may cause the passenger's body to be damaged by impact fractures, and the seat must be able to withstand significant impact forces in terms of performance strength.

Disclosure of Invention

In view of the above, the invention provides a processing technology of an aviation seat frame, which aims to solve the problems that the performance strength of the aviation seat frame prepared by the existing technology cannot tolerate huge impact force and the body comfort of passengers is affected.

In order to achieve the purpose, the invention provides the following technical scheme: an aviation seat frame processing technology comprises the following steps:

A. placing the 6082 aluminum alloy cast ingot in the T4 state in an extrusion die in an extrusion cylinder of an extruder for extrusion to obtain an aluminum alloy section, wherein the heating temperature of an aluminum alloy cast rod is 475-485 ℃, and the extrusion speed is 3.8-4.0 m/min;

B. quenching the extruded aluminum alloy section, wherein the quenching mode is water cooling, and the water temperature is 16-22 ℃;

C. placing the quenched aluminum alloy section in a stretcher for stretching and straightening, wherein the stretching rate is 1.1-1.3%;

D. sawing the stretched and straightened aluminum alloy section according to the size requirement;

E. naturally standing the sawed aluminum alloy section for aging treatment, wherein the aging time is 52-56 h;

F. bending the straight aluminum alloy section after the natural aging is finished into two sections of U-shaped frame products with 75 degrees;

G. punching and punching the bent section of the aluminum alloy section bar shown in the figure 1 into a required aperture shape;

H. welding a cross brace connecting rod at a position 110-120 mm away from the bent U-shaped opening frame to obtain a seat frame;

I. and (3) placing the processed seat frame into an aging furnace for heat treatment, wherein the heat treatment system is controlled to be (175 +/-3) DEG C.times.6 h.

And further, the yield strength of the aluminum alloy section extruded in the step A is 85-95 Mpa.

Further, the extruder in step A was a 1250T extruder.

Further, the quenching cooling speed in the step B is 25-30 ℃/s.

Further, the aging furnace in the step I is a floor type aging furnace.

The invention has the beneficial effects that:

1. the machining process of the aviation seat frame disclosed by the invention is used for finishing the finished aviation seat backrest through an early-stage aluminum machining process and later-stage deep machining. The performance requirements of the aluminum alloy products of the aviation seat frame can be improved, the acting force caused by the front and rear buffer forces of passengers in the air can be met, and the requirement for improving the product quality can be met.

2. The aviation seat frame prepared by the aviation seat frame processing technology disclosed by the invention has the advantages that the mechanical properties are far beyond the standard requirements, the production requirements can be met, the aviation seat frame is prepared by bending, the performance strength can bear huge impact force, and the application prospect is wide. The process method is stable, and the product performance effect is excellent.

Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims thereof.

Drawings

For the purposes of promoting a better understanding of the objects, aspects and advantages of the invention, reference will now be made to the following detailed description taken in conjunction with the accompanying drawings in which:

FIG. 1 is a cross-sectional view of a straight aluminum alloy profile in the machining process of the aircraft seat frame of the invention;

fig. 2 is a schematic structural diagram of an aircraft seat frame prepared by the processing technology of the aircraft seat frame.

Reference numerals: the seat comprises a seat frame 1, seat fabric mounting holes 2 and a cross brace connecting rod 3.

Detailed Description

The following embodiments of the present invention are provided by way of specific examples, and other advantages and effects of the present invention will be readily apparent to those skilled in the art from the disclosure herein. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present invention in a schematic way, and the features in the following embodiments and examples may be combined with each other without conflict.

Wherein the showings are for the purpose of illustration only and not for the purpose of limiting the invention, shown in the drawings are schematic representations and not in the form of actual drawings; to better illustrate the embodiments of the present invention, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; it will be understood by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted.

The same or similar reference numerals in the drawings of the embodiments of the present invention correspond to the same or similar components; in the description of the present invention, it should be understood that if there is an orientation or positional relationship indicated by terms such as "upper", "lower", "left", "right", "front", "rear", etc., based on the orientation or positional relationship shown in the drawings, it is only for convenience of description and simplification of description, but it is not an indication or suggestion that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and therefore, the terms describing the positional relationship in the drawings are only used for illustrative purposes, and are not to be construed as limiting the present invention, and the specific meaning of the terms may be understood by those skilled in the art according to specific situations.

Examples

A process for manufacturing an aircraft seat frame as shown in fig. 1, comprising the following steps:

A. placing the 6082 aluminum alloy cast ingot in the T4 state in an extrusion die in an extrusion cylinder of an extruder for extrusion to obtain an aluminum alloy section, wherein the heating temperature of an aluminum alloy cast rod is 475-485 ℃, and the extrusion speed is 3.8-4.0 m/min; the yield strength of the extruded aluminum alloy section is 85-95 Mpa;

C. placing the quenched aluminum alloy section in a stretcher for stretching and straightening, wherein the stretching rate is 1.1-1.3%; the shape of the aluminum alloy is irregular in extrusion, the profile can be straightened through subsequent elongation control, the process parameters are used for stretching and straightening the profile, and quenching residual stress can be eliminated after straightening; the effect cannot be achieved when the stretching rate given in the stretching and straightening process is too high or too low, or new residual stress is generated to distort crystal lattices, destroy the balance state among atoms, distort the crystal lattices, and cause the strength of the section to be increased, the yield strength to be higher and the material to be poor in molding; the subsequent processing process is easy to generate fracture or cracking phenomenon, so that waste products are generated;

E. naturally standing the sawed aluminum alloy section for aging treatment, wherein the aging time is 52-56 h, the yield strength of the section is not easy to guarantee control in the actual production process, the storage time needs to be adjusted, and the best processing effect can be guaranteed only when the yield strength is 85-95 Mpa;

F. bending the straight aluminum alloy section after the natural aging is finished into two sections of U-shaped frame product shapes with the angle of 75 degrees;

G. punching the bent section of the aluminum alloy section bar in the figure 1, wherein the hole is used for installing seat fabric, namely a seat fabric installing hole 2;

H. welding a cross brace connecting rod 3 at the position 110-120 mm away from the bent U-shaped opening frame to obtain the seat frame 1 shown in the figure 2;

I. and (3) placing the processed seat frame into a floor type aging furnace for heat treatment, wherein the heat treatment system is controlled to be (175 +/-3) DEG C multiplied by 6 h.

The mechanical property test is carried out on the straight aluminum alloy section after natural aging, and the test result is shown in table 1:

TABLE 1

As can be seen from the table 1, the mechanical properties of the straight aluminum alloy section prepared by the process are far beyond the standard requirements, the production requirements can be met, the straight aluminum alloy section is bent to prepare the aviation seat frame, the performance strength of the straight aluminum alloy section can bear huge impact force, and the straight aluminum alloy section has wide application prospects.

Finally, the above embodiments are only intended to illustrate the technical solutions of the present invention and not to limit the present invention, and although the present invention has been described in detail with reference to the preferred embodiments, it will be understood by those skilled in the art that modifications or equivalent substitutions may be made on the technical solutions of the present invention without departing from the spirit and scope of the technical solutions, and all of them should be covered by the claims of the present invention.

Claims

1. The machining process of the aircraft seat frame is characterized by comprising the following steps of:

A. placing a 6082 aluminum alloy cast ingot in a T4 state in an extrusion die in an extrusion cylinder of an extruder for extrusion to obtain an aluminum alloy section, wherein the heating temperature of an aluminum alloy cast rod is 475-485 ℃, and the extrusion speed is 3.8-4.0 m/min;

B. quenching the extruded aluminum alloy section, wherein the quenching mode is water cooling, the water temperature is 16-22 ℃, and the quenching cooling speed is 25-30 ℃/s;

E. naturally standing the sawed aluminum alloy section for aging treatment, wherein the aging time is 52-56 h, and the yield strength is 85-95 Mpa;

G. punching and punching the cross section of the bent aluminum alloy section into a shape with a required aperture;

I. and (3) placing the processed seat frame into an aging furnace for heat treatment, wherein the heat treatment system is controlled to be (175 +/-3) DEG C for 6 h.

2. The process for machining an aircraft seat frame according to claim 1, wherein the yield strength of the aluminum alloy section extruded in the step A is 85-95 MPa.

3. A process for manufacturing an aircraft seat frame according to claim 2, wherein the extruder in step a is a 1250T extruder.

4. A process for manufacturing an aircraft seat frame according to claim 3, wherein the ageing furnace in step I is a floor type ageing furnace.