CN109515741A - A kind of aircraft main landing gear support joint forging part production technology - Google Patents
A kind of aircraft main landing gear support joint forging part production technology Download PDFInfo
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- CN109515741A CN109515741A CN201811480705.2A CN201811480705A CN109515741A CN 109515741 A CN109515741 A CN 109515741A CN 201811480705 A CN201811480705 A CN 201811480705A CN 109515741 A CN109515741 A CN 109515741A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Abstract
This application discloses a kind of aircraft main landing gear support joint forging part production technologies, comprising the following steps: following steps: heating → die forging → washes and repairs fiery inspection → quenching → timeliness → detection → examination before heating → pre- die forging → die forging before the preceding heating → forging → pre- die forging of ingot casting forging；Wherein: including: that mold heats in tool heating furnace, and ingot casting is heated to 420~440 DEG C in the step " heating before ingot casting forging ", keep the temperature 360-1080 minutes；It include: that pre- pressing mold heats in tool heating furnace, and by blank heating to 420~440 DEG C, keeps the temperature 210-630 minutes in the step " being heated before pre- die forging "；It include: that final pressure mould heats in tool heating furnace, and by blank heating to 420~440 DEG C, keeps the temperature 200-600 minutes in the step " being heated before die forging ".Aircraft provided herein main landing gear support joint forging part production technology, can produce good combination property, and processing capacity is small, on-deformable central wing front-axle beam frame, can replace import forging, meet the use demand of business aircraft.
Description
Technical field
This application involves workpiece to forge field, produces more particularly to a kind of aircraft main landing gear support joint forging part
Technique.
Background technique
The central wing front-axle beam frame of ARJ21 aircraft generally processes part using import open die forgings, and processing capacity is big, at high cost,
Process-cycle is long, easily-deformable, also, all processes part using import open die forgings, is easy to lead to nothing because of international policy factor
Method buying.And quotient flies ARJ21 aircraft and has entered mass-production stage, so needing using more economically, comprehensive performance is better
Central wing front-axle beam frame forging part processes part.
Therefore, the processing efficiency and service performance for how effectively improving aircraft central wing front-axle beam frame, are art technologies
The current technical issues that need to address of personnel.
Apply for content
The purpose of the application is to provide a kind of aircraft main landing gear support joint forging part production technology, used in improving
The comprehensive performance for entreating wing front-axle beam frame forging part, satisfies the use demand.
To achieve the above object, the application provides the following technical solutions:
A kind of aircraft main landing gear support joint forging part production technology, comprising the following steps:
Heating → die forging → washes and repairs fiery inspection before heating → pre- die forging → die forging before heating → forging → pre- die forging before ingot casting is forged
→ quenching → timeliness → detection → examination；
Wherein: including: that mold heats in tool heating furnace, and ingot casting is heated in the step " heating before ingot casting forging "
To 420~440 DEG C, 360-1080 minutes are kept the temperature；
It include: that pre- pressing mold heats in tool heating furnace, and blank heating is arrived in the step " being heated before pre- die forging "
420~440 DEG C, keep the temperature 210-630 minutes；
In the step " heating before die forging " include: that final pressure mould heats in tool heating furnace, and by blank heating to 420
~440 DEG C, keep the temperature 200-600 minutes.
It preferably, further include step " ingot casting examination " before the step " heating before ingot casting forging ", the step " test by ingot casting
Receive " it include: to obtain 7050 alloy cast ingots of the length, width and height having a size of 360 ± 10mm × 1280 ± 10mm × 540 ± 10mm；Alloy casting
The liquid hydrogen content of ingot answers≤0.10ml/100gAL.
Preferably, the step " forging " includes:
Blank is forged using 10000 tons of hydraulic pressure, hydraulic press and 6000 tons of hydraulic presses；Starting forging temperature 410~440
DEG C, final forging temperature >=350 DEG C；Blank is pressed into height H=320+10mm, amount of feeding 250-300mm；Width is adjusted to 500+
10mm；Press to height H=220+10mm, amount of feeding 250-300mm；Adjust the length, width and height size of blank are as follows: 1680+20mm ×
530+10mm×220+10mm。
Preferably, the step " pre- die forging " includes: to carry out pre- mould to blank using 30000 tons of hydraulic presses and pre- pressing mold
Forging；410~440 DEG C of starting forging temperature, final forging temperature >=380 DEG C measure and record piece by piece begin forging and final forging temperature；Blank is put into pre-
Die forging in pressing mold notices that blank pendulum occupies；Pre- die forging fire time is 2 fire, and the first under-voltage amount of fire controls 8-12mm, and the second fire is owed
Pressure amount controls 0-5mm；Mold temperature control be subject to blank measurement final forging temperature, if blank final forging temperature down to 380 DEG C,
Mold must return furnace and be heated according to the requirement of step " heating before pre- die forging ".
Preferably, the step " die forging " includes: to carry out die forging to blank using 30000 tons of hydraulic presses and final pressure mould；It opens
410~440 DEG C of temperature of forging, final forging temperature >=380 DEG C measure and record piece by piece begin forging and final forging temperature；Blank is put into final pressure mould
Interior die forging notices that blank pendulum occupies；Die forging fire time is 2 fire, and the first under-voltage amount of fire controls 8-12mm, the second under-voltage amount control of fire
0-6mm processed；Mold temperature control be subject to blank measurement final forging temperature, if blank final forging temperature is down to 380 DEG C, mold must
Furnace must be returned to be heated according to the requirement of step " heating before die forging ".
Preferably, the step " quenching " includes: to be charged using the dedicated material frame of quenching, in the edge-on discharging frame of forging, interval
150mm or more, single furnace maximum shove charge quantity must not exceed 16；Forging is at 1/2 thickness of tail position and forging thickest part
Bore each slotting 1 thermocouple in the hole 5 × 30mm of Φ；Furnace temperature stablizes the shove charge after 477 ± 5 DEG C；The maximum of forging is heat-treated thickness
118mm；Fixed temperature: 477 ± 5 DEG C, metal heat preservation 330 minutes, heat medium was air, water quenching of coming out of the stove after heat preservation, quenched water
Warm 60-71 DEG C, transfer time≤25 second, and record faithfully.
Preferably, the step " timeliness " include: using dedicated material frame charge, forging at 1/2 thickness of tail position and
Forging thickest part bores each slotting 1 thermocouple in the hole 5 × 30mm of Φ；Record faithfully the position and temperature data of two galvanic couples；Forging
It is spaced 150mm or more, and is put along aging furnace circulated air wind direction；Institution of prescription: 121 ± 5 DEG C of the first stage, metal heat preservation 4 is small
When；177 ± 5 DEG C of second stage, metal heat preservation 5.5 hours；Heat medium is air, is come out of the stove after heat preservation air-cooled.
Preferably, further include between the step " forging " and the step " being heated before pre- die forging " step " machining " and
Step " is washed and is repaired "；Wherein, the step " machining " include: charge length direction all after two so that processing main body length and width
It, will whole outer rib chamferings after height is having a size of 830+5mm × 518+5mm × 208+5mm.
It preferably, further include step " process trimming " between the step " pre- die forging " and the step " being heated before die forging "
It " washes and repairs " with step.
It preferably, further include step " trimming " between the step " wash and repair fiery inspection " and the step " quenching "；The step
Suddenly " trimming " includes: pre-set dimension processing flash, boss and the heat treatment process slot according to forging, and flash residual quantity is processed
To≤3mm.
Aircraft provided herein main landing gear support joint forging part production technology, comprising the following steps: ingot casting
Heating → die forging → washes and repairs fiery inspection → quenching → timeliness before heating → pre- die forging → die forging before the preceding heating → forging → pre- die forging of forging
→ detection → examination；Wherein: including: that mold heats in tool heating furnace, and will cast in the step " heating before ingot casting forging "
Ingot is heated to 420~440 DEG C, keeps the temperature 360-1080 minutes；It include: pre- pressing mold in tool in the step " being heated before pre- die forging "
It is heated in heating furnace, and by blank heating to 420~440 DEG C, keeps the temperature 210-630 minutes；In the step " being heated before die forging "
It include: that final pressure mould heats in tool heating furnace, and by blank heating to 420~440 DEG C, keeps the temperature 200-600 minutes.The aircraft
With main landing gear support joint forging part production technology, good combination property can be produced, processing capacity is small, on-deformable center
Wing front-axle beam frame can replace import forging, meet the use demand of business aircraft.
Detailed description of the invention
In order to illustrate the technical solutions in the embodiments of the present application or in the prior art more clearly, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of application for those of ordinary skill in the art without creative efforts, can be with
It obtains other drawings based on these drawings.
Fig. 1 is aircraft central wing front-axle beam frame forging part forging technology block diagram provided herein；
Fig. 2 is a kind of specific embodiment when aircraft central wing front-axle beam frame forging part forging provided herein frames up
Structural schematic diagram；
Fig. 3 is that position signal is arranged in the heat treatment thermocouple of aircraft central wing front-axle beam frame forging part provided herein
Figure；
Wherein: 1- forging, 2- material frame, the tail portion 3-, 4- forging thickest part, 5- test point.
Specific embodiment
The core of the application is to provide a kind of aircraft main landing gear support joint forging part production technology, used in improving
The comprehensive performance for entreating wing front-axle beam frame forging part, satisfies the use demand.
In order to make those skilled in the art more fully understand application scheme, with reference to the accompanying drawings and detailed description
The application is described in further detail.
Fig. 1 to Fig. 3 is please referred to, when Fig. 1 is that aircraft central wing front-axle beam frame forging part forging provided herein frames up
A kind of main view of specific embodiment；Fig. 2 is that aircraft central wing front-axle beam frame forging part forging provided herein frames up
When a kind of attached view of specific embodiment；Fig. 3 is at the heat of aircraft central wing front-axle beam frame forging part provided herein
It manages thermocouple and position view is set；Dimensional units in attached drawing are mm.
In this embodiment, aircraft main landing gear support joint forging part production technology, comprising the following steps:
Heating → die forging → washes and repairs fiery inspection before heating → pre- die forging → die forging before heating → forging → pre- die forging before ingot casting is forged
→ quenching → timeliness → detection → examination；
Wherein: including: that mold heats in tool heating furnace, and ingot casting is heated in step " heating before ingot casting forging "
420~440 DEG C, keep the temperature 360-1080 minutes；
In step " heating before pre- die forging " include: that pre- pressing mold heats in tool heating furnace, and by blank heating to 420~
440 DEG C, keep the temperature 210-630 minutes；
In step " heating before die forging " include: that final pressure mould heats in tool heating furnace, and by blank heating to 420~
440 DEG C, keep the temperature 200-600 minutes.
It further include step " ingot casting examination " before step " heating before ingot casting forging " on the basis of the respective embodiments described above,
Step " ingot casting examination " includes: to obtain 7050 alloys of the length, width and height having a size of 360 ± 10mm × 1280 ± 10mm × 540 ± 10mm
Ingot casting；The liquid hydrogen content of alloy cast ingot answers≤0.10ml/100gAL.
On the basis of the respective embodiments described above, step " forging " includes:
Blank is forged using 10000 tons of hydraulic pressure, hydraulic press and 6000 tons of hydraulic presses；Starting forging temperature 410~440
DEG C, final forging temperature >=350 DEG C；Blank is pressed into height H=320+10mm, amount of feeding 250-300mm；Width is adjusted to 500+
10mm；Press to height H=220+10mm, amount of feeding 250-300mm；Adjust the length, width and height size of blank are as follows: 1680+20mm ×
530+10mm×220+10mm。
On the basis of the respective embodiments described above, step " pre- die forging " includes: using 30000 tons of hydraulic presses and pre- pressing mold pair
Blank carries out pre- die forging；410~440 DEG C of starting forging temperature, final forging temperature >=380 DEG C measure and record piece by piece begin forging and finish-forging temperature
Degree；Blank is put into the forging of pre- pressing mold internal model, pays attention to that blank is put and occupied；Pre- die forging fire time is 2 fire, and the first under-voltage amount of fire controls 8-
12mm, the second under-voltage amount of fire control 0-5mm；Mold temperature control be subject to blank measurement final forging temperature, if blank finish-forging
Down to 380 DEG C, mold must return furnace and be heated according to the requirement of step " heating before pre- die forging " temperature.
On the basis of the respective embodiments described above, step " die forging " includes: using 30000 tons of hydraulic presses and final pressure mould to base
Material carries out die forging；410~440 DEG C of starting forging temperature, final forging temperature >=380 DEG C measure and record piece by piece begin forging and final forging temperature；Base
Material is put into die forging in final pressure mould, pays attention to that blank is put and occupies；Die forging fire time is 2 fire, and the first under-voltage amount of fire controls 8-12mm, the
The two under-voltage amounts of fire control 0-6mm；Mold temperature control be subject to blank measurement final forging temperature, if blank final forging temperature down to
380 DEG C, mold must return furnace and be heated according to the requirement of step " heating before die forging ".
On the basis of the respective embodiments described above, step " quenching " includes: to be charged using the dedicated material frame 2 of quenching, 1 side of forging
It stands up in material frame 2, is spaced 150mm or more, single furnace maximum shove charge quantity must not exceed 16；Forging 1 is thick in 3 position of tail portion 1/2
At degree and forging thickest part 4 bores each slotting 1 thermocouple in the hole 5 × 30mm of Φ；Furnace temperature stablizes the shove charge after 477 ± 5 DEG C；Forging 1
Maximum heat treatment thickness be 118mm；Fixed temperature: 477 ± 5 DEG C, metal heat preservation 330 minutes, heat medium was air, and heat preservation terminates
After come out of the stove water quenching, quench 60-71 DEG C of water temperature, transfer time≤25 second, and recording faithfully.
On the basis of the respective embodiments described above, step " timeliness " includes: to be charged using dedicated material frame 2, and forging 1 is in tail portion
At 3 position, 1/2 thickness and forging thickest part 4 bores each slotting 1 thermocouple in the hole 5 × 30mm of Φ；Record faithfully the position of two galvanic couples
It sets and temperature data；Forging 1 is spaced 150mm or more, and puts along aging furnace circulated air wind direction；Institution of prescription: first stage 121
± 5 DEG C, metal heat preservation 4 hours；177 ± 5 DEG C of second stage, metal heat preservation 5.5 hours；Heat medium is air, and heat preservation terminates
After come out of the stove it is air-cooled.
It further include step between step " forging " and step " being heated before pre- die forging " on the basis of the respective embodiments described above
" machining " and step " wash and repair "；Wherein, step " machining " include: charge length direction all after two so that processing master
It, will whole outer rib chamferings after body length, width and height are having a size of 830+5mm × 518+5mm × 208+5mm.
It further include step between step " pre- die forging " and step " being heated before die forging " on the basis of the respective embodiments described above
" process trimming " and step " wash and repair ".
It further include that step " is cut between step " wash and repair fiery inspection " and step " quenching " on the basis of the respective embodiments described above
Side "；Step " trimming " includes: pre-set dimension processing flash, boss and the heat treatment process slot according to forging 1, and flash is residual
Allowance is machined to≤3mm.
Embodiment:
Aircraft main landing gear support joint forging part production technology, comprising the following steps:
Step S1: ingot casting is checked and accepted
Cast ingot dimension 360 ± 10mm × 1280 ± 10mm × 540 ± 10mm；Chemical component audit alloy: 7050, chemistry at
Divide the requirement that should meet AMS-A-22771 latest edition；The liquid hydrogen content of alloy should be not more than 0.10ml/100gAL.
Step S2: heating before forging
Mold heating: small flat anvil is a set of to be heated in tool heating furnace, is heated fixed 450 DEG C of temperature, is heated at least 12 hours；Casting
Ingot heating: heating, 420~440 DEG C of heating temperature in sharing furnace, keeps the temperature 360-1080 minutes.
Step S3: forging
Use equipment: 10000 tons of hydraulic pressure, hydraulic presses, 6000 tons of hydraulic presses；Use tool: small flat anvil is a set of；Forging technology
It is required that: 410~440 DEG C of starting forging temperature, final forging temperature >=350 DEG C measure and record piece by piece begin forging and final forging temperature；Forging scheme
It is executed by work step is forged in attached drawing 1,1 fire is completed, and the direction of marked arrow is longitudinal inside forging in Fig. 1.It measures and remembers piece by piece
Record the final size of forging stock；Forging requires: it first requires to execute to " side of beating 1 " according to attached drawing 1, then substep pulls out along its length:
1. pressing to H=320+10mm, amount of feeding 250-300mm；
2. whole width is to 500+10mm；
3. pressing to H=220+10mm, amount of feeding 250-300mm；
4. whole width is smooth to length, width and height size: 680+20mm × 530+10mm × 220+10mm；
Mold temperature control be subject to blank measurement final forging temperature, if blank final forging temperature is down to 350 DEG C, mold must
Furnace must be returned and heated according to the requirement of step S2；The marking: alloy, batch, piece number are stamped with steel seal in forging stock end piece by piece.
Step S4: machining
All are machined out after two in charge length direction, process main body length, width and height size: 830+5mm × 518+5mm
All outer rib chamferings after × 208+5mm, wherein the chamfer angle of a corner angle is 125 °, remaining chamfer angle is 30 °, and
The corner angle position that chamfer angle is 125 ° is stayed in into blank material end, end prints D.
Step S5: it washes and repairs
It is executed by Q/SWA JGY035600.
Step S6: it is heated before pre- die forging
Mold heating: pre- pressing mold heats in tool heating furnace, heats fixed 450 DEG C of temperature, heats at least 24 hours；Blank adds
Heat: heating, 420~440 DEG C of heating temperature in sharing furnace, keeps the temperature 210-630 minutes.
Step S7: pre- die forging
Use equipment: 30000 tons of hydraulic presses；Use tool: pre- pressing mold；Forging technology requirement: starting forging temperature 410~440
DEG C, final forging temperature >=380 DEG C measure and record piece by piece begin forging and final forging temperature；Blank is put into pre- pressing mold internal model forging, pays attention to blank
During pendulum occupies；Pre- die forging fire (designing warmware thickness 113mm in sampling clout area): 2 fire are completed, and the first under-voltage amount of fire controls 8-
12mm, the second under-voltage amount of fire control 0-5mm；Mold temperature control be subject to blank measurement final forging temperature, if blank finish-forging
Down to 380 DEG C, mold must return furnace and be heated by the requirement of step S6 temperature；The marking: in forging stock end, steel seal is beaten piece by piece
Upper alloy, batch, piece number.
Step S8: process trimming
It requires to execute according to Q/SWA JGY035700.
Step S9: it washes and repairs
It is executed by Q/SWA JGY035600.
Step S10: it is heated before die forging
Mold heating: final pressure mould heats in tool heating furnace, heats fixed 450 DEG C of temperature, heats at least 24 hours；Blank adds
Heat: heating, 420~440 DEG C of heating temperature in sharing furnace, keeps the temperature 200-600 minutes.
Step S11: die forging
Use equipment: 30000 tons of hydraulic presses；Use tool: final pressure mould；Forging technology requirement: starting forging temperature 410~440
DEG C, final forging temperature >=380 DEG C measure and record piece by piece begin forging and final forging temperature；Blank is put into die forging in final pressure mould, pays attention to blank
During pendulum occupies；Die forging fire (gross weight boss designs warmware thickness 102.3mm): 2 fire, the first under-voltage amount 8-12mm of fire；Second fire
Under-voltage amount: 0-6mm；Mold temperature control be subject to blank measurement final forging temperature, if blank final forging temperature down to 380 DEG C,
Mold must return furnace and be heated according to the requirement of step S10；The marking: piece by piece forging stock end with steel seal stamp alloy, batch,
Heat, piece number.
Step S12: it washes and repairs fiery inspection
Forging 1 if any folding repair situations such as injuring underfill fire inspection not by when, allow to return pressure 1 fire time, execute step
S10。
Step S13: trimming
It requires to execute according to Q/SWA JGY035700；Flash is processed according to 1 digital-to-analogue of forging, processes boss and heat treatment work
Skill slot；Flash residual quantity≤3mm.
Step S14: quenching
Use equipment: 4# glowing furnace；Shove charge；It is charged with dedicated material frame 2 is quenched, in the edge-on discharging frame 2 of forging 1, interval
150mm or more, single furnace maximum shove charge quantity must not exceed 16；The signal that frames up such as attached drawing 2 executes；The position shown in attached drawing 3 of forging 1
It sets at 1/2 thickness and forging thickest part 4 bores each slotting 1 thermocouple in the hole 5 × 30mm of Φ；Furnace temperature stabilization fills after 477 ± 5 DEG C
Furnace；Quenching system: the maximum heat treatment thickness of this forging 1 is 118mm；Fixed temperature: 477 ± 5 DEG C, metal heat preservation 330 minutes, heating
Medium is air, water quenching of coming out of the stove after heat preservation, quenches 60-71 DEG C of water temperature；Transfer time≤25 second, and record faithfully.
Step S15: artificial aging
Use equipment: 12 tons of aging furnaces；Shove charge；Allow several quenching heat treatments batch conjunction furnace timeliness, single furnace maximum shove charge part
Number is no more than 16；It is charged with dedicated material frame 2, forging 1 is at 1/2 thickness of 3 position of tail portion shown in attached drawing 2 and forging is most thick
Bore each slotting 1 thermocouple in the hole 5 × 30mm of Φ in position 4；Record faithfully the position and temperature data of two galvanic couples；Forging 1 is spaced
150mm or more, and put along aging furnace circulated air wind direction.It frames up and illustrates as shown in Fig. 2；Institution of prescription: the first stage 121 ±
5 DEG C, metal heat preservation 4 hours；177 ± 5 DEG C of second stage, metal heat preservation 5.5 hours；Heat medium is air, after heat preservation
It comes out of the stove air-cooled.
Step S16: ultrasonic examination
100% water seaoning ultrasonic examination is carried out to forging 1 by AMS-STD-2154 requirement, flaw detection rank is B grades.Flaw detection
Process accessories are shown in concrete operations: 1 ultrasonic inspection technics card of Zuo Zhuqi support joint forging (A editions).
Step S17: sampling
Sample needed for 1 initial workpiece of support joint forging sampling drawing requirement obtains test is played by left master；It cuts at chemical component 3
Each 1, each 1 at low power test block 4；It cuts at longitudinal, long transverse direction and hyphen mechanical property sample 6 (2, each direction)；It cuts
Take 2, stress corrosion resistant sample, high power 2；Conductivity sample, each 1 at 6.
Step S18-1: mechanical property (stretching) test
Extension test carries out on tensile sample；It is tested by the requirement of ASTM B557.
Step S18-2: conductivity test
Conductivity test carries out on conductivity sample；The conductivity of test forging 1 is provided by ASTM E1004.
Step S18-3: macrostructure inspection
Macrostructure inspection carries out in low power test block；It is checked by the requirement of ASTM E 340.
Step S18-4: chemical component inspection
Chemical component inspection carries out in chemical component test block；It is checked by the requirement of EN 14242.
Step S18-5: microscopic examination
Microscopic examination carries out on high power sample；It is checked by the requirement of ASTM E 407.
Step S18-6: anti-stress corrosion performance test
Anti-stress corrosion performance test carries out in stress corrosion test block；It is tested by 47 requirement of ASTM G.
Step S19: finished product inspection and examination
Forging 1 is submitted inspection in batch and is checked and accepted；The outer dimension and surface quality of forging 1 are examed piece by piece, inspection result is answered
Meet the requirement of 1 drawing of forging；Examine that all control processes have been fully completed；Examine the marking of forging 1, marking content packet
It includes: 1 code name of forging, alloy state, hearth number, batch, serial number, heat treatment heat (batch) number and tested stamp；Examine all test reports
Accuse the requirement that should meet forging 1 drawing and AMS-A-22771 latest edition；Issue product quality certificate；In addition to described above,
It is remaining to be executed by Q/SWA JGY036300.
Step S20: Packaging and Labeling
Forging 1 is saved and is packed by 660 requirement cartonning of ASTM B；Remaining is executed by Q/SWA JGY036400.
Step S21: delivery and storage
Shipment makes marks according to MIL-STD-129, and each packing case should securely and clearly indicate the following contents:
Product standard (AMS-A-22771 latest edition), alloy and condition of heat treatment, batch, order number, quantity.
The main landing gear support joint forging part production technology of aircraft provided by the present embodiment, can produce comprehensive
Can be good, processing capacity is small, on-deformable central wing front-axle beam frame, can replace import forging, meet the use demand of business aircraft.
Detailed Jie has been carried out with main landing gear support joint forging part production technology to aircraft provided herein above
It continues.Specific examples are used herein to illustrate the principle and implementation manner of the present application, and the explanation of above embodiments is only
It is to be used to help understand the method for this application and its core ideas.It should be pointed out that for those skilled in the art
For, under the premise of not departing from the application principle, can also to the application, some improvement and modification can also be carried out, these improve and repair
Decorations are also fallen into the protection scope of the claim of this application.
Claims (10)
1. a kind of aircraft main landing gear support joint forging part production technology, which comprises the following steps:
Heating → die forging → washes and repairs fire and examine → quench before heating → pre- die forging → die forging before heating → forging → pre- die forging before ingot casting is forged
Fire → timeliness → detection → examination；
Wherein: including: that mold heats in tool heating furnace, and ingot casting is heated in the step " heating before ingot casting forging "
420~440 DEG C, keep the temperature 360-1080 minutes；
In the step " heating before pre- die forging " include: that pre- pressing mold heats in tool heating furnace, and by blank heating to 420~
440 DEG C, keep the temperature 210-630 minutes；
In the step " heating before die forging " include: that final pressure mould heats in tool heating furnace, and by blank heating to 420~
440 DEG C, keep the temperature 200-600 minutes.
2. aircraft according to claim 1 main landing gear support joint forging part production technology, which is characterized in that described
It further include step " ingot casting examination " before step " heating before ingot casting forging ", the step " ingot casting examination " includes: acquisition length, width and height
7050 alloy cast ingots having a size of 360 ± 10mm × 1280 ± 10mm × 540 ± 10mm；The liquid hydrogen content of alloy cast ingot answers≤
0.10ml/100gAL。
3. aircraft according to claim 1 main landing gear support joint forging part production technology, which is characterized in that described
Step " forging " includes:
Blank is forged using 10000 tons of hydraulic pressure, hydraulic press and 6000 tons of hydraulic presses；410~440 DEG C of starting forging temperature, eventually
Forge temperature >=350 DEG C；Blank is pressed into height H=320+10mm, amount of feeding 250-300mm；Width is adjusted to 500+10mm；
Press to height H=220+10mm, amount of feeding 250-300mm；Adjust the length, width and height size of blank are as follows: 1680+20mm × 530+
10mm×220+10mm。
4. aircraft according to claim 1 main landing gear support joint forging part production technology, which is characterized in that described
Step " pre- die forging " includes: to carry out pre- die forging to blank using 30000 tons of hydraulic presses and pre- pressing mold；Starting forging temperature 410~440
DEG C, final forging temperature >=380 DEG C measure and record piece by piece begin forging and final forging temperature；Blank is put into pre- pressing mold internal model forging, pays attention to blank
During pendulum occupies；Pre- die forging fire time is 2 fire, and the first under-voltage amount of fire controls 8-12mm, and the second under-voltage amount of fire controls 0-5mm；Mold
Temperature control be subject to blank measurement final forging temperature, if blank final forging temperature is down to 380 DEG C, mold must return furnace according to step
Suddenly the requirement " heated before pre- die forging " is heated.
5. aircraft according to claim 1 main landing gear support joint forging part production technology, which is characterized in that described
Step " die forging " includes: to carry out die forging to blank using 30000 tons of hydraulic presses and final pressure mould；410~440 DEG C of starting forging temperature, eventually
Temperature >=380 DEG C are forged, measure and record begin forging and final forging temperature piece by piece；Blank is put into die forging in final pressure mould, notices that blank puts position
Between two parties；Die forging fire time is 2 fire, and the first under-voltage amount of fire controls 8-12mm, and the second under-voltage amount of fire controls 0-6mm；Mold temperature control
System be subject to blank measurement final forging temperature, if blank final forging temperature is down to 380 DEG C, mold must return furnace according to step " mould
The requirement of heating before forging " is heated.
6. aircraft according to claim 1 main landing gear support joint forging part production technology, which is characterized in that described
Step " quenching " includes: to be charged using the dedicated material frame of quenching, in the edge-on discharging frame of forging, is spaced 150mm or more, single furnace maximum dress
Furnace quantity must not exceed 16；Forging is at 1/2 thickness of tail position and the forging thickest part brill hole 5 × 30mm of Φ is each 1 slotting
Thermocouple；Furnace temperature stablizes the shove charge after 477 ± 5 DEG C；The maximum heat treatment thickness of forging is 118mm；Fixed temperature: 477 ± 5 DEG C, gold
Belong to heat preservation 330 minutes, heat medium is air, water quenching of coming out of the stove after heat preservation, quenches 60-71 DEG C of water temperature, transfer time≤25
Second, and record faithfully.
7. aircraft according to claim 1 main landing gear support joint forging part production technology, which is characterized in that described
Step " timeliness " include: using dedicated material frame charge, forging at 1/2 thickness of tail position and forging thickest part bore Φ 5 ×
The hole 30mm is each to insert 1 thermocouple；Record faithfully the position and temperature data of two galvanic couples；Forging interval 150mm or more, and along when
Effect furnace circulated air wind direction is put；Institution of prescription: 121 ± 5 DEG C of the first stage, metal heat preservation 4 hours；177 ± 5 DEG C of second stage,
Metal heat preservation 5.5 hours；Heat medium is air, is come out of the stove after heat preservation air-cooled.
8. special according to claim 1 to the main landing gear support joint forging part production technology of aircraft described in 7 any one
Sign is, further includes that step " machining " and step " are washed between the step " forging " and the step " heating before pre- die forging "
It repairs "；Wherein, the step " machining " include: charge length direction all after two so that processing main body length, width and height having a size of
It, will whole outer rib chamferings after 830+5mm × 518+5mm × 208+5mm.
9. special according to claim 1 to the main landing gear support joint forging part production technology of aircraft described in 7 any one
Sign is, further includes step " process trimming " and step between the step " pre- die forging " and the step " heating before die forging "
" wash and repair ".
10. according to claim 1 to the main landing gear support joint forging part production technology of aircraft described in 7 any one,
It is characterized in that, further includes step " trimming " between the step " wash and repair fiery inspection " and the step " quenching "；The step " is cut
Side " includes: pre-set dimension processing flash, boss and the heat treatment process slot according to forging, and flash residual quantity is machined to≤
3mm。
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110834178A (en) * | 2019-10-28 | 2020-02-25 | 西安兴航航空科技股份有限公司 | Manufacturing method of Y-shaped connecting piece for spherical frame of airplane |
| CN112792271A (en) * | 2020-12-22 | 2021-05-14 | 西南铝业（集团）有限责任公司 | 7050 alloy forging production process |
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| JP2001286968A (en) * | 2000-04-10 | 2001-10-16 | Hoei Kogyo Kk | Forging method, forging stock to be used in the method, forging apparatus and under carriage part for vehicle |
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| CN110834178B (en) * | 2019-10-28 | 2021-09-14 | 西安兴航航空科技股份有限公司 | Manufacturing method of Y-shaped connecting piece for spherical frame of airplane |
| CN112792271A (en) * | 2020-12-22 | 2021-05-14 | 西南铝业（集团）有限责任公司 | 7050 alloy forging production process |
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