CN103629290A

CN103629290A - Variable damping oil needle of airplane buffer

Info

Publication number: CN103629290A
Application number: CN201310619237.3A
Authority: CN
Inventors: 朱永健; 张万民; 张立军
Original assignee: Xian Aircraft Design and Research Institute of AVIC
Current assignee: Xian Aircraft Design and Research Institute of AVIC
Priority date: 2013-11-27
Filing date: 2013-11-27
Publication date: 2014-03-12
Anticipated expiration: 2033-11-27
Also published as: CN103629290B

Abstract

The invention belongs to an airplane buffer technology, and relates to a variable damping oil needle of an airplane buffer. The variable damping oil needle of the airplane buffer is a cylindrical needle body, and a plurality of grooves which are longitudinally distributed are formed in the outer surface of the needle body. From an initial segment, the four grooves used as control points are axially formed on the outer surface of the needle body, wherein the parameter of the sectional area of the oil needle on the initial segment is 1.07f. The first groove is located in the 0.27L position, wherein the parameter of the sectional area of the oil needle is 1.07f. The second groove is located in the 0.57L position, wherein the parameter of the sectional area of the oil needle is 0.96f. The third groove is located in the 0.8L position, wherein the parameter of the sectional area of the oil needle is 0.615f. The fourth groove is located in the 0.9L position, wherein the parameter of the sectional area of the oil needle is 0.48f. The parameter of the sectional area of the oil needle at the tail end is 0.3f. L is the structural stroke of the buffer, and f is the set oil hole area generated when two peak values of a perpendicular load are kept equal. According to the variable damping oil needle of the airplane buffer, a sunken area between the two peak values of the perpendicular load can be eliminated, the load becomes gentle, a work amount curve of the buffer is full, efficiency coefficients are increased to 80% and far exceed efficiency coefficients in an existing level, and the remarkable technical effect is achieved.

Description

A kind of aircraft buffer variable resistance Buddhist nun spindle

Technical field

The invention belongs to aircraft buffer technology, relate to a kind of aircraft buffer variable resistance Buddhist nun spindle.

Background technique

For common baby plane buffer damping device, the general damping device that adopts single oilhole form, but on the low side for large aircraft buffer list oilhole damper efficiency, the general spindle formula that adopts becomes damping device, spindle formula becomes damping device can improve buffer efficiency, but what kind of becomes damping constant, can improve to greatest extent buffer efficiency, also further investigate.

Baby plane buffer adopts single oilhole damping device both at home and abroad at present, and damping parameter is a constant, and normal load curve has a depression between two peak values, has affected the absorption of buffer energy, causes buffer efficiency not high.The spindle formula damping device mainly adopting for large aircraft buffer, spindle lower end is fixed in piston rod, spindle is smooth tapered cross-section, spindle and plunger gap jointly form damping device to cross pasta long-pending, and for this variable resistance Buddhist nun's apparatus structure form, variable resistance Buddhist nun's parameter curve is dull, can not fully improve the efficiency that becomes damping buffer, and during drop-test, variable resistance Buddhist nun's difficulty of parameter tuning, need to repair repeatedly.

Summary of the invention

The object of the invention is: provide a kind of and can make the aircraft buffer variable resistance Buddhist nun spindle that merit discharge curve is full, effectively improve damping effect.

Technological scheme of the present invention is: a kind of aircraft buffer variable resistance Buddhist nun spindle is cylindrical needle body, and needle body outer surface offers the groove of some longitudinal distributions, and needle body leading portion depth of groove is greater than needle rear end depth of groove.

Described aircraft buffer variable resistance Buddhist nun spindle is from the initial segment, and needle body outer surface is provided with 4 vertically as the groove at control point, and wherein, section start section spindle sectional area parameter is 1.07f; The first groove is at 0.27L place, and its spindle sectional area parameter is 1.07f; The second groove is at 0.57L place, and its spindle sectional area parameter is 0.96f; The 3rd groove is at 0.8L place, and its spindle sectional area parameter is 0.615f; The 4th groove is at 0.9L place, and its spindle sectional area parameter is 0.48f; End spindle sectional area parameter is 0.3f, wherein, and the structure stroke that L is buffer, stand oil hole area when f equates for two peak values of maintenance normal load.

Buffer structure stroke L is 70～90% of spindle length dimension.

Stand oil hole area f be spindle institute installation place piston rod cross section 1～2%.

Advantage of the present invention is: machine buffer variable resistance Buddhist nun spindle of the present invention is by offering the groove of particular arrangement and the degree of depth on needle body surface, can eliminate the depressed area between two peak values of normal load, make load mild, make the merit discharge curve of buffer more full, efficiency factor is increased to 80%, the existing level that surpasses far away, has significant technique effect.

Accompanying drawing explanation

Fig. 1 is variable resistance Buddhist nun spindle scheme of installation;

Fig. 2 is variable resistance Buddhist nun spindle structural representation;

Fig. 3 is that the A-A of Fig. 2 cuts open figure;

Fig. 4 is variable resistance Buddhist nun spindle groove control point schematic diagram;

Fig. 5 is variable resistance Buddhist nun spindle using effect schematic diagram,

Wherein, 1-urceolus, 2-plunger, 3-spindle, 4-piston rod.

Embodiment

Below in conjunction with drawings and Examples, the present invention will be further described:

Refer to Fig. 1, it is the mounting structure schematic diagram of aircraft buffer variable resistance Buddhist nun spindle of the present invention.Aircraft buffer variable resistance Buddhist nun spindle of the present invention, its lower end is arranged on piston rod 4 inside, insert in plunger 2 its upper end, the common buffer damping device that forms, when buffer compresses, piston rod 4 and spindle 3 quick insertion urceolus 1 inside, piston rod inner fluid Rapid Flow is crossed just face groove of spindle needle body like this, has produced damping force.Aircraft buffer variable resistance Buddhist nun spindle of the present invention is cylindrical needle body.Refer to Fig. 2, needle body outer surface offers the groove of some longitudinal distributions; Described aircraft buffer variable resistance Buddhist nun spindle is from the initial segment, and needle body outer surface is provided with vertically 4 and sees Fig. 4 as the groove at control point, and between each control point, is that level and smooth straight line connects.Wherein, section start section spindle sectional area parameter is 1.07f; The first groove is at 0.27L place, and its spindle sectional area parameter is 1.07f; The second groove is at 0.57L place, and its spindle sectional area parameter is 0.96f; The 3rd groove is at 0.8L place, and its spindle sectional area parameter is 0.615f; The 4th groove is at 0.9L place, and its spindle sectional area parameter is 0.48f; End spindle sectional area parameter is 0.3f, wherein, and the structure stroke that L is buffer, stand oil hole area when f equates for two peak values of maintenance normal load.Buffer structure stroke L is 70～90% of spindle length dimension.Stand oil hole area f be spindle institute installation place piston rod cross section 1～2%.

Adopt aircraft buffer variable resistance Buddhist nun spindle of the present invention, the sunk area between two peak values that the normal load of determining damping oil hole can be occurred is filled and led up, and makes normal load become mild shape; Can reduce the normal load of 5-10%, improve buffer absorption efficiency coefficient 5-10%.

In certain embodiment, spindle length is 550mm, buffer structure stroke 440mm, piston rod sectional area 23200mm ², stand oil hole area f is 330mm ², drop-test (rising without imitative) normal load peak value is reduced to 35T by 37.5T, has reduced by 6.7%, and normal load J curve effectJ is referring to Fig. 5, and buffer efficiency factor is increased to 80% by 75%.

Claims

1. an aircraft buffer variable resistance Buddhist nun spindle, is characterized in that, is cylindrical needle body, and needle body outer surface offers the groove of some longitudinal distributions, and needle body leading portion depth of groove is greater than needle rear end depth of groove.

2. aircraft buffer variable resistance Buddhist nun spindle according to claim 1, is characterized in that, from the initial segment, needle body outer surface is provided with 4 vertically as the groove at control point, and wherein, section start section spindle sectional area parameter is 1.07f; The first groove is at 0.27L place, and its spindle sectional area parameter is 1.07f; The second groove is at 0.57L place, and its spindle sectional area parameter is 0.96f; The 3rd groove is at 0.8L place, and its spindle sectional area parameter is 0.615f; The 4th groove is at 0.9L place, and its spindle sectional area parameter is 0.48f; End spindle sectional area parameter is 0.3f, wherein, and the structure stroke that L is buffer, stand oil hole area when f equates for two peak values of maintenance normal load.

3. aircraft buffer variable resistance Buddhist nun spindle according to claim 2, is characterized in that, buffer structure stroke L is 70～90% of spindle length dimension.

4. aircraft buffer variable resistance Buddhist nun spindle according to claim 3, is characterized in that, stand oil hole area f be spindle institute installation place piston rod cross section 1～2%.