CN1250354C - Processing technology of 70KM rocket projectile fairing - Google Patents
Processing technology of 70KM rocket projectile fairing Download PDFInfo
- Publication number
- CN1250354C CN1250354C CN 01127979 CN01127979A CN1250354C CN 1250354 C CN1250354 C CN 1250354C CN 01127979 CN01127979 CN 01127979 CN 01127979 A CN01127979 A CN 01127979A CN 1250354 C CN1250354 C CN 1250354C
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- China
- Prior art keywords
- spinning
- processing
- time
- extrusion molding
- processing technology
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- 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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Links
- 238000005516 engineering process Methods 0.000 title claims abstract description 13
- 238000009987 spinning Methods 0.000 claims abstract description 32
- 238000007514 turning Methods 0.000 claims abstract description 13
- 238000001125 extrusion Methods 0.000 claims abstract description 11
- 238000000034 method Methods 0.000 claims abstract description 10
- 238000000137 annealing Methods 0.000 claims abstract description 8
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 5
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 5
- 230000032683 aging Effects 0.000 claims abstract description 4
- 238000010438 heat treatment Methods 0.000 claims description 7
- 239000004411 aluminium Substances 0.000 claims description 4
- 239000002131 composite material Substances 0.000 abstract description 2
- 229910052751 metal Inorganic materials 0.000 abstract description 2
- 239000002184 metal Substances 0.000 abstract description 2
- 238000003672 processing method Methods 0.000 abstract description 2
- 230000003746 surface roughness Effects 0.000 abstract description 2
- 208000012886 Vertigo Diseases 0.000 abstract 7
- 238000001192 hot extrusion Methods 0.000 abstract 1
- 238000000465 moulding Methods 0.000 abstract 1
- 239000002994 raw material Substances 0.000 abstract 1
- 238000003754 machining Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 241001504664 Crossocheilus latius Species 0.000 description 1
- 150000001875 compounds Chemical group 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
Landscapes
- Extrusion Of Metal (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
- Forging (AREA)
Abstract
A spinning processing technology for thick-wall composite parts relates to a processing technology for metal parts and mainly comprises the steps of (1) blank extrusion forming, (2) primary annealing, (3) primary turning processing, (4) primary spinning, (5) secondary annealing, (6) secondary spinning, (7) aging treatment and (8) secondary turning processing. The blank extrusion molding adopts a conventional aluminum hot extrusion molding method, the first spinning and the second spinning adopt offset spinning processing of a spinning machine, and other processing steps adopt conventional processing techniques. The processing method can ensure the precision and the strength of the processed workpiece, and save raw materials and processing time. The main technical indexes are that the wall thickness difference of the conical part is less than or equal to 0.07mm, and the mechanical property sigma isbNot less than 475MPa, not less than 7.5% and surface roughness Ra not more than 12.5 μm.
Description
Technical field:
The present invention relates to the processing technology of metal parts, is a kind of Thickwall composite component spinning production process, further is a kind of processing technology of 70KM rocket projectile radome fairing.
Background technology:
At present, the processing of rocket projectile housing is generally adopted the bar method for turning or is rolled the stone roller method for turning, bar turning rapidoprint utilization rate is lower than 10%, time-consuming, effort, take material, some precision indexs also are difficult to control, roll to grind turning processing and adopt to use after heating on the lathe again and roll the processing technology of delaying unloading and cutting, because the heating-up temperature of aluminium is lower, be difficult to accurately measure and the control temperature, part wall thickness, the material of processing are also inhomogeneous, and machining accuracy is difficult to guarantee.
Summary of the invention:
Technical problem to be solved by this invention provides a kind of precision and intensity that can guarantee work piece, save material and the compound parts machining process of heavy wall of machining period.
The technical solution adopted in the present invention mainly is to adopt the bad rotary pressing processing technology of hair, and concrete procedure of processing is:
1, blank extrusion molding;
2, once annealing;
3, turning processing;
4, spinning for the first time;
5, double annealing;
6, spinning for the second time;
7, Ageing Treatment;
8, secondary turning processing.
Wherein, 1, the blank extrusion molding adopts conventional aluminium thermal extrusion moulding method.
4, spinning and 6, the processing of the spinning machine of spinning employing for the second time stepped spinning for the first time.
The technological parameter of spinning is for the first time:
Reduction: 22.90%;
Feed rate: 0.4 (mm/r);
The speed of mainshaft: 100 (rpm);
Axial wrong distance: 0.5 (mm);
Footpath disclination distance: 0.3 (mm);
Roller working radius: 32 (mm);
Condition of heat treatment: 62 (HB).
The technological parameter of spinning is for the second time:
Reduction: 34.65%;
Feed rate: 0.5 (mm/r);
The speed of mainshaft: 100 (rpm);
Axial wrong distance: 0.5 (mm);
Footpath disclination distance: 0.2 (mm);
Roller working radius: 25 (mm);
Condition of heat treatment: 62 (HB).
Other processing step all adopts conventional processing technology.
Adopt the part the key technical indexes of the present invention's processing as follows:
The tapering part wall thickness is poor≤0.07mm;
Mechanical performance σ
b〉=475Mpa, δ 〉=7.5%;
Surface roughness Ra≤12.5 μ m
Processing method of the present invention can guarantee work piece precision and intensity, save material and machining period.
Specific embodiments:
Processing technology with 70KM rocket projectile radome fairing is an example, and concrete procedure of processing is:
1, blank extrusion molding;
2, once annealing;
3, turning processing;
4, spinning for the first time;
5, double annealing;
6, spinning for the second time;
7, Ageing Treatment;
8, secondary turning processing.
Wherein, 1, the blank extrusion molding adopts conventional aluminium thermal extrusion moulding method.
4, spinning and 6, the processing of the spinning machine of spinning employing for the second time stepped spinning for the first time.
The technological parameter of spinning is for the first time:
Reduction: 22.90%;
Feed rate: 0.4 (mm/r);
The speed of mainshaft: 100 (rpm);
Axial wrong distance: 0.5 (mm);
Footpath disclination distance: 0.3 (mm);
Roller working radius: 32 (mm);
Condition of heat treatment: 62 (HB).
The technological parameter of spinning is for the second time:
Reduction: 34.65%;
Feed rate: 0.5 (mm/r);
The speed of mainshaft: 100 (rpm);
Axial wrong distance: 0.5 (mm);
Footpath disclination distance: 0.2 (mm);
Roller working radius: 25 (mm);
Condition of heat treatment: 62 (HB).
Other processing step all adopts conventional processing technology.
The total cost of one-piece part is 1042 yuan, and is more over half than the part cost saving that bar method for turning is produced.
Claims (1)
1. the processing technology of a 70KM rocket projectile radome fairing is characterized in that: finished by following steps:
(1) blank extrusion molding;
(2) once annealing;
(3) turning processing;
(4) spinning for the first time;
(5) double annealing;
(6) spinning for the second time;
(7) Ageing Treatment;
(8) secondary turning processing;
Wherein, (1) blank extrusion molding adopts conventional aluminium thermal extrusion moulding method;
(4) spinning machine of spinning and (6) spinning employing for the second time for the first time stepped spinning processing;
The technological parameter of spinning is for the first time:
Reduction: 22.90%;
Feed rate: 0.4mm/r;
The speed of mainshaft: 100rpm;
Axial wrong distance: 0.5mm;
Footpath disclination distance: 0.3mm;
Roller working radius: 32mm;
Condition of heat treatment: 62HB;
The technological parameter of spinning is for the second time:
Reduction: 34.65%;
Feed rate: 0.5mm/r;
The speed of mainshaft: 100rpm;
Axial wrong distance: 0.5mm;
Footpath disclination distance: 0.2mm;
Roller working radius: 25mm;
Condition of heat treatment: 62HE.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01127979 CN1250354C (en) | 2001-07-27 | 2001-07-27 | Processing technology of 70KM rocket projectile fairing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01127979 CN1250354C (en) | 2001-07-27 | 2001-07-27 | Processing technology of 70KM rocket projectile fairing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1400067A CN1400067A (en) | 2003-03-05 |
| CN1250354C true CN1250354C (en) | 2006-04-12 |
Family
ID=4667882
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 01127979 Expired - Fee Related CN1250354C (en) | 2001-07-27 | 2001-07-27 | Processing technology of 70KM rocket projectile fairing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1250354C (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100453261C (en) * | 2007-01-27 | 2009-01-21 | 山西锦恒汽车部件有限公司 | Compound plastic forming method of casting aluminum alloy parts |
| CN102773323A (en) * | 2012-07-31 | 2012-11-14 | 华南理工大学 | Strong force rotary pressing molding method of nanocrystalline/superfine crystal carbon steel cylindrical piece |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104028607B (en) * | 2014-06-06 | 2016-03-23 | 中国航天科技集团公司长征机械厂 | A kind ofly improve the processing method that spinning subtracts thick pipe finished quality |
| CN107350758A (en) * | 2016-05-09 | 2017-11-17 | 重庆千迈机械制造有限公司 | Multiple extrusion forming shell case processing method |
| CN107243720B (en) * | 2017-04-26 | 2019-01-29 | 晋西工业集团有限责任公司 | A kind of heavy caliber combustion chamber rotation mouth manufacturing process |
| CN108127014B (en) * | 2017-12-06 | 2019-05-31 | 西安航天动力机械有限公司 | The wrong method away from reversed spinning of a kind of pair of wheel |
| CN108115364B (en) * | 2017-12-13 | 2020-10-13 | 航天特种材料及工艺技术研究所 | Thick plate double-rotating-wheel heating general-rotating forming method |
| CN108480930B (en) * | 2018-04-11 | 2019-10-01 | 重庆天骄航空动力有限公司 | A kind of processing method of low-pressure compressor casing |
| CN112171214B (en) * | 2020-05-22 | 2022-02-15 | 湖北三江航天江北机械工程有限公司 | Large-scale aeroelastic shell forming and processing method |
-
2001
- 2001-07-27 CN CN 01127979 patent/CN1250354C/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100453261C (en) * | 2007-01-27 | 2009-01-21 | 山西锦恒汽车部件有限公司 | Compound plastic forming method of casting aluminum alloy parts |
| CN102773323A (en) * | 2012-07-31 | 2012-11-14 | 华南理工大学 | Strong force rotary pressing molding method of nanocrystalline/superfine crystal carbon steel cylindrical piece |
| CN102773323B (en) * | 2012-07-31 | 2014-11-12 | 华南理工大学 | Strong force rotary pressing molding method of nanocrystalline/superfine crystal carbon steel cylindrical piece |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1400067A (en) | 2003-03-05 |
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