CN104482089A - Aircraft standard spring calculation method - Google Patents
Aircraft standard spring calculation method Download PDFInfo
- Publication number
- CN104482089A CN104482089A CN201410744261.4A CN201410744261A CN104482089A CN 104482089 A CN104482089 A CN 104482089A CN 201410744261 A CN201410744261 A CN 201410744261A CN 104482089 A CN104482089 A CN 104482089A
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- CN
- China
- Prior art keywords
- spring
- load
- aircraft
- computational methods
- diameter
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F1/00—Springs
- F16F1/02—Springs made of steel or other material having low internal friction; Wound, torsion, leaf, cup, ring or the like springs, the material of the spring not being relevant
- F16F1/04—Wound springs
- F16F1/06—Wound springs with turns lying in cylindrical surfaces
Abstract
The invention relates to an aircraft standard spring calculation method and belongs to the field of aircraft spring machining and manufacturing. By the aid of calculation, the operation circle number n, total circle number n1, height H1 under maximum load, extension length L and weight G of a spring can be acquired, data and tolerances required during turning and fitting can be determined, and determination is completed by querying P, n, Dw, H0 limit deviation tables. By the aid of the method, the parameters of the spring meet the design requirements, and the accurate application of the standard spring to aircraft loading is improved greatly; the method is rapid and convenient to implement, working efficiency is improved greatly, cost is saved, and the purposes of saving energy, protecting environment and reducing pollution can be achieved.
Description
Technical field
The present invention relates to a kind of Aircraft Standard part spring computational methods, belong to aircraft spring manufacturing field.
Background technique
Have a lot for aircraft upper spring, main point of standard piece spring and non-standard component spring, what solve now is the manual calculation problem of standard piece spring.Current research be circular section cold drawn wire cylindrically coiled spring, be divided into stage clip and extension spring, extension spring is divided into again A type and Type B two kinds, the elastic load of spring is divided into one, two, third-class a few class.Make a slight spring, develop technical process according to data demands such as different materials, shape, specifications.In decades, the technique manufacturing spring is all each entry value that the method calculated by hand calculates spring, and the process need of manual calculation is consulted process parameter, carried out papery computing.This all wants the expensive time, and manual calculation easily makes mistakes, and wastes a large amount of human and material resources, also unclean, not environmentally.
Aircraft Standard part spring material mainly contains II a group, 50CrVA, 65Si
2mnWA these three kinds, according to different materials, looks into spring standard piece handbook, draws load p, pitch t and individual pen amount of deformation f, calculates number of turns n, tension values H again by several different formula
1, and make the tolerance up and down of these values.Each operation, as turner, pincers worker all will be done by tolerance, can not deviation.Though spring is little, data are extremely many.All the time, calculating these data is all that technician manually computes, trifling especially, numerous and diverse.Need meticulous during calculating.When task is nervous, once make mistakes in chaos, part production process is obstructed or is produced band hidden danger part, installs and will produce larger impact aboard.Aircraft to be installed many various dissimilar springs, so the process modification invention of spring is just particularly important.
Summary of the invention
In order to overcome above-mentioned defect, the object of the present invention is to provide a kind of Aircraft Standard part spring computational methods, increase work efficiency, accuracy is high, greatly improve standard piece spring aboard load apply accurately.
To achieve these goals, the present invention adopts following technological scheme:
A kind of Aircraft Standard part spring computational methods::
By spring wire diameter d, spring outer diameter D
w, and the free height H of spring
0, look into spring standard piece handbook, learn load p, individual pen amount of deformation f and spring pitch t;
According to these known conditions, by following computational methods:
H
0=t n+ (n
z-0. 5) d--------two ends polish
H
0=t n+ (n
z+ 1) d--------two ends do not polish
When d≤0.8mm steel wire spring, end face allows not grind or few mill
H
1= H
0 ▔f ·n
L=π·D·n
1
By above-mentioned computational methods, the number of effective coils n of spring, number of total coils n can be calculated
1,height H under maximum load
1, also have length of run L and the weight G of spring, and then determine that spring is in turner, the data clamping man-hour requirement and tolerance, by looking into load p, n, D
w, H
0the form of limit deviation determine;
Wherein: P: maximum allowable load; H
0: the free height of spring; N: number of effective coils n
1: number of total coils; n
z: support the number of turns (getting 2 when getting 2.5, d > 3 during d≤3); D: mean diameter of coil; D
w: spring outer diameter; D
n: spring inside diameter; T: spring pitch; D: spring wire diameter; F: the individual pen amount of deformation under maximum allowable load; L: spring length of run; G: spring weight.
Beneficial effect of the present invention:
1, the invention enables spring parameters to meet designing requirement, greatly improve standard piece spring aboard load apply accurately.
2, the present invention is quick and easy, greatly increases work efficiency.
3, the present invention is cost-saving, realizes energy-saving and environmental protection, decreasing pollution.
Embodiment
Describe the present invention below in conjunction with embodiment:
A kind of Aircraft Standard part spring computational methods:
By spring wire diameter d, spring outer diameter D
w, and the free height H of spring
0, look into spring standard piece handbook, learn load p, individual pen amount of deformation f and spring pitch t;
According to these known conditions, by following computational methods:
H
0=t n+ (n
z-0. 5) d--------two ends polish
H
0=t n+ (n
z+ 1) d--------two ends do not polish
When d≤0.8mm steel wire spring, end face allows not grind or few mill
H
1= H
0 ▔f ·n
L=π·D·n
1
By above-mentioned computational methods, the number of effective coils n of spring, number of total coils n can be calculated
1,height H under maximum load
1, also have length of run L and the weight G of spring, and then determine that spring is in turner, the data clamping man-hour requirement and tolerance, by looking into load p, n, D
w, H
0the form of limit deviation determine;
Wherein: P: maximum allowable load; H
0: the free height of spring; N: number of effective coils n
1: number of total coils; n
z: support the number of turns (getting 2 when getting 2.5, d > 3 during d≤3); D: mean diameter of coil; D
w: spring outer diameter; D
n: spring inside diameter; T: spring pitch; D: spring wire diameter; F: the individual pen amount of deformation under maximum allowable load; L: spring length of run; G: spring weight.
By computational methods, calculate the manufacturing data of spring, establishment spring technical process, spring production workshop section produces by technical process operation the qualified spring meeting designing requirement.
This method not only quick, computing environment cleans, and result of calculation is accurate.Greatly improve standard piece spring aboard load apply accurately, for aviation industry makes new contribution.
Claims (1)
1. Aircraft Standard part spring computational methods, is characterized in that:
By spring wire diameter d, spring outer diameter D
w, and the free height H of spring
0, look into spring standard piece handbook, learn load p, individual pen amount of deformation f and spring pitch t;
According to these known conditions, by following computational methods:
H
0=t n+ (n
z-0. 5) d--------two ends polish
H
0=t n+ (n
z+ 1) d--------two ends do not polish
When d≤0.8mm steel wire spring, end face allows not grind or few mill
H
1= H
0 ▔ f ·n
L=π·D·n
1
By above-mentioned computational methods, the number of effective coils n of spring, number of total coils n can be calculated
1,height H under maximum load
1, also have length of run L and the weight G of spring, and then determine that spring is in turner, the data clamping man-hour requirement and tolerance, by looking into load p, n, D
w, H
0the form of limit deviation determine;
Wherein: P: maximum allowable load; H
0: the free height of spring; N: number of effective coils n
1: number of total coils; n
z: support the number of turns (getting 2 when getting 2.5, d > 3 during d≤3); D: mean diameter of coil; D
w: spring outer diameter; D
n: spring inside diameter; T: spring pitch; D: spring wire diameter; F: the individual pen amount of deformation under maximum allowable load; L: spring length of run; G: spring weight.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410744261.4A CN104482089A (en) | 2014-12-09 | 2014-12-09 | Aircraft standard spring calculation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410744261.4A CN104482089A (en) | 2014-12-09 | 2014-12-09 | Aircraft standard spring calculation method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104482089A true CN104482089A (en) | 2015-04-01 |
Family
ID=52756667
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410744261.4A Pending CN104482089A (en) | 2014-12-09 | 2014-12-09 | Aircraft standard spring calculation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104482089A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2384166A1 (en) * | 1977-03-16 | 1978-10-13 | Schmitthelm Fa Ernst | MOTOR VEHICLE SPRING FOR USE AS A TRAVEL CONTROL SPRING AND AS A VALVE SPRING |
| JPH01131341A (en) * | 1987-11-16 | 1989-05-24 | Honda Motor Co Ltd | Noncircular cross-sectional coil spring |
| CN102472345A (en) * | 2009-07-31 | 2012-05-23 | 日本发条株式会社 | Coil spring |
| CN102537163A (en) * | 2012-02-06 | 2012-07-04 | 山东宁津弹簧有限公司 | Design method for total coil number of spring |
| CN104295647A (en) * | 2014-09-26 | 2015-01-21 | 无锡市天力五金弹簧厂 | Tensile spring |
-
2014
- 2014-12-09 CN CN201410744261.4A patent/CN104482089A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2384166A1 (en) * | 1977-03-16 | 1978-10-13 | Schmitthelm Fa Ernst | MOTOR VEHICLE SPRING FOR USE AS A TRAVEL CONTROL SPRING AND AS A VALVE SPRING |
| JPH01131341A (en) * | 1987-11-16 | 1989-05-24 | Honda Motor Co Ltd | Noncircular cross-sectional coil spring |
| CN102472345A (en) * | 2009-07-31 | 2012-05-23 | 日本发条株式会社 | Coil spring |
| CN102537163A (en) * | 2012-02-06 | 2012-07-04 | 山东宁津弹簧有限公司 | Design method for total coil number of spring |
| CN104295647A (en) * | 2014-09-26 | 2015-01-21 | 无锡市天力五金弹簧厂 | Tensile spring |
Non-Patent Citations (3)
| Title |
|---|
| HEZYCQ: "弹簧的设计方法", 《百度文库》 * |
| 李和平: ""圆柱螺旋压缩弹簧的设计计算"", 《井冈山师范学院学报》 * |
| 皮亚南: ""弹簧的应用与设计计算"", 《锻压机械》 * |
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|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150401 |