Magnetorheological fluid aircraft landing gear buffer strut

A technology of aircraft landing gear and magnetorheological fluid, applied in mechanical equipment, springs/shock absorbers, shock absorbers, etc., can solve the problem of limited buffering and vibration damping effects, difficulty in ensuring effective control and normal operation, and throttling capability Change and other problems to achieve the effect of isolating vibration, meeting the requirements of shock drop, and reducing the natural frequency

Pending Publication Date: 2021-03-12
重庆茂创建筑工程有限公司
View PDF0 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] However, the throttling capacity with a certain adjustment effect formed only through the main oil hole and the oil needle has limited buffering and vibration reduction effects when dealing with various complex working conditions faced by the aircraft landing, and once the oil needle is designed and installed in place, this This throttling capability cannot be changed according to the complex working conditions faced by the aircraft
Correspondingly, when the magnetorheological buffer is intelligently transformed, the working medium is replaced by magnetorheological fluid, and the electromagnetic control of the flow channel is integrated in the structural design to achieve controllable damping force, if the structural design is not fundamentally innovated solution, it is difficult to ensure its effective control and normal operation due to the settlement of soft magnetic particles in magnetorheological fluids

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Magnetorheological fluid aircraft landing gear buffer strut
  • Magnetorheological fluid aircraft landing gear buffer strut
  • Magnetorheological fluid aircraft landing gear buffer strut

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0055] see figure 1 , the present embodiment discloses a magnetorheological fluid aircraft landing gear buffer strut including an outer cylinder 1 , an inner cylinder 2 , a floating piston 3 , a piston rod 4 , an electromagnetic control assembly 5 , a liner 6 and an oil needle 7 .

[0056] The outer cylinder 1 is a hollow cylinder with a closed upper end and a through hole I101 on the lower end surface.

[0057] The inner cylinder 2 is a hollow cylinder. The inner cylinder 2 is located inside the outer cylinder 1, and its upper end is connected to the closed part of the upper end of the outer cylinder 1, the two form a whole, and its lower end protrudes from the through hole I101 of the outer cylinder 1.

[0058] A through hole II201 is provided on the lower end surface of the inner cylinder 2 . An annular limiting platform 202 protrudes from the outer wall of the inner cylinder 2 . The annular limiting platform 202 is an annular flange. Four layers of through holes III20...

Embodiment 2

[0089] This embodiment discloses a relatively basic implementation, see figure 1 , a magnetorheological fluid aircraft landing gear buffer strut includes an outer cylinder 1, an inner cylinder 2, a floating piston 3, a piston rod 4, an electromagnetic control assembly 5, a liner 6 and an oil needle 7.

[0090] The outer cylinder 1 is a hollow cylinder with a closed upper end and a through hole I101 on the lower end surface.

[0091] The inner cylinder 2 is a hollow cylinder. The inner cylinder 2 is located inside the outer cylinder 1, and its upper end is connected to the closed part of the upper end of the outer cylinder 1, the two form a whole, and its lower end protrudes from the through hole I101 of the outer cylinder 1.

[0092] A through hole II201 is provided on the lower end surface of the inner cylinder 2 . Four layers of through holes III203 are opened on the inner wall of the inner cylinder 2 .

[0093] A cavity S is formed between the outer wall of the inner cy...

Embodiment 3

[0111] The main structure of this embodiment is the same as that of Embodiment 2, and the electromagnetic control assembly 5 includes a positioning column 52 , a top cover 54 , an electromagnetic element 55 , a power device 56 and a rotor 57 .

[0112] The closed end 41 of the piston rod 4 has a through hole VII413 in the center of the upper end surface. The upper end surface of the closed end 41 is provided with several blind holes 412 on the same circumference. The closed end 41 is threadedly connected to the lower end of the piston rod 4 .

[0113] There are multiple positioning posts 52 , and each positioning post 52 is correspondingly installed in a blind hole 412 of the closed end 41 .

[0114] The electromagnetic element 55 is located inside the piston rod 4 , and its lower end is fixed on the positioning post 52 . An outer coil 551 is wound on the electromagnetic element 55 .

[0115] The center of the end surface of the top cover 54 has a round hole II541. The end...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention discloses a magnetorheological fluid aircraft landing gear buffer strut which comprises an outer cylinder, an inner cylinder, a floating piston, a piston rod, an electromagnetic controlassembly, a lining cylinder and an oil needle. The inner cylinder is located in the outer cylinder; the floating piston is mounted between the inner cylinder and the outer cylinder; the lower end of the inner cylinder extends into the piston rod; the piston rod extends out of the outer cylinder; the electromagnetic control assembly is installed at the closed end of the piston rod; the electromagnetic control assembly generates a magnetic field after being electrified; the upper end of the lining cylinder sleeves the inner cylinder; the lower end of the lining cylinder is installed on the electromagnetic control assembly; and the oil needle comprises an upper cut-off section and a lower cut-off section which are connected to the two ends of a middle section. According to the magnetorheological fluid aircraft landing gear buffer strut provided by the invention, various complex working conditions facing aircraft landing can be met, the aircraft drop shock requirement can be met, the overall inherent frequency can also be effectively reduced, and vibration from the ground in the skating process is better isolated.

Description

technical field [0001] The invention relates to the technical field of buffering, in particular to a magnetorheological fluid aircraft landing gear buffering pillar. Background technique [0002] The buffer is an essential general-purpose part on the landing gear of modern aircraft. The main function of the buffer is to absorb the vertical kinetic energy during the landing and taxiing of the aircraft. The landing gear with good cushioning performance can make the aircraft and landing gear have lower aircraft overload, better stability, comfort and higher reliability during landing, taxiing and ground manipulation. Due to the highest efficiency and the best power absorption capacity in the oil-air buffer, at present, most of the landing gears at home and abroad use the oil-air buffer landing gear. Oil-pneumatic buffers generally have various forms such as single-cavity type and double-cavity type. Well adapted to the impact of falling loads, the double-air-cavity oil-air bu...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & AuthorityApplications(China)
IPC IPC(8): F16F9/53F16F9/36F16F9/32
CPCF16F9/535F16F9/36F16F9/3214F16F9/3207
Inventor不公告发明人
Owner重庆茂创建筑工程有限公司