CN104443426B - A kind of Titanium Alloy Aircraft frame beam-like part manufacture method - Google Patents
A kind of Titanium Alloy Aircraft frame beam-like part manufacture method Download PDFInfo
- Publication number
- CN104443426B CN104443426B CN201410524921.8A CN201410524921A CN104443426B CN 104443426 B CN104443426 B CN 104443426B CN 201410524921 A CN201410524921 A CN 201410524921A CN 104443426 B CN104443426 B CN 104443426B
- Authority
- CN
- China
- Prior art keywords
- titanium alloy
- alloy profile
- welding block
- frame beam
- profile
- 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.)
- Active
Links
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 190
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 55
- 238000000034 method Methods 0.000 title claims abstract description 49
- 238000003466 welding Methods 0.000 claims abstract description 98
- 238000005452 bending Methods 0.000 claims abstract description 53
- 238000003801 milling Methods 0.000 claims abstract description 29
- 238000005485 electric heating Methods 0.000 claims abstract description 11
- 238000010438 heat treatment Methods 0.000 claims 1
- 238000003754 machining Methods 0.000 abstract description 7
- 238000005242 forging Methods 0.000 description 16
- 238000005516 engineering process Methods 0.000 description 10
- 239000000463 material Substances 0.000 description 9
- 230000008901 benefit Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 5
- 230000004927 fusion Effects 0.000 description 3
- 210000003205 muscle Anatomy 0.000 description 3
- 239000000956 alloy Substances 0.000 description 2
- 239000004918 carbon fiber reinforced polymer Substances 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 238000005476 soldering Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002301 combined effect Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 210000000744 eyelid Anatomy 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 238000001953 recrystallisation Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000007790 solid phase Substances 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Landscapes
- Pressure Welding/Diffusion-Bonding (AREA)
- Forging (AREA)
- Bending Of Plates, Rods, And Pipes (AREA)
Abstract
The invention discloses a kind of Titanium Alloy Aircraft frame beam-like part manufacture method, including: initial titanium alloy profile is carried out electric heating stretch bending, it is thus achieved that reach the bending titanium alloy profile that radius of curvature requires; Welding block is done curved reciprocating fricting movement with certain frequency at the pre-welding position bent on titanium alloy profile, after fricting movement certain time, welding block is welded on web and/or the base plate of bending titanium alloy profile; Milling bends the overlap that welds of titanium alloy profile and welding block, and according to manufacturing the dimensional requirement of Titanium Alloy Aircraft frame beam-like part, milling bends titanium alloy profile and welding block, it is thus achieved that meet the titanium alloy component of dimensional requirement. Add man-hour at part, the step of electric heating stretch bending and reciprocating friction welding can reversed order, this method also can realize the manufacture of titanium alloy frame beam-like part. Improve stock utilization by the Titanium Alloy Aircraft frame beam-like part manufacture method of the present invention, lower process costs and improve working (machining) efficiency simultaneously.
Description
Technical field
The present invention relates to metal molding field, relate generally to a kind of Titanium Alloy Aircraft frame beam-like part manufacture method.
Background technology
Modern times, airframe was still based on semi-monocoque structure, was mainly made up of the aircraft skin (thin skin, Varying-thickness eyelid covering, band muscle integral panel etc.) of curved profile, in length and breadth skeleton (stringer and bulkhead etc.). And bulkhead class part is the important form of airframe structure, it is characterized by that profile has curvature feature request and local has the feature structure such as rib, muscle. These load-bearing frame components, its forming quality is directly connected to the assembly precision of aircraft, complete machine aerodynamic configuration, service life, become and affect aircraft development and ensure the key problem in technology of aircraft entirety military service performance, be also one of principal element affecting aircraft manufacturing cycle, cost and benefit.
In recent years, multiple material (CarbonFiberReinforcedPolymer/Plastic, the CFRP) fuselage of fibre reinforced becomes one of advanced civil aircraft fuselage structure major programme, as Boeing 787 and Air Passenger A350XWB adopt full composite material fuselage. Have the good electromotive force compatibility and the resistance to impact of titanium alloy material excellence itself due to titanium alloy material and composite, the application in civil aircraft of the titanium alloy frame beam-like part is increasingly extensive. Titanium alloy frame beam-like part becomes the primary structure of multiple material fuselage load-carrying member, for load-bearing bulkhead beam length purlin, central authorities' wing box, main landing gear gear mechanism support and hatch door frame.
Traditional machining manufacture of titanium alloy frame class part is titanium alloy forging base, then adopts numerical controlled machinery processing method to obtain the feature structure such as local ribs, muscle. Titanium alloy forging needs individually be designed according to External Shape and manufacture, and generally commercially supplies unlike titanium alloy plate, section bar, tubing etc. Titanium alloy forging or die forging need large-scale special equipment, and Mega-boule forging or small-sized forging part need a few kiloton pressurized hydraulic machines, and large-scale forging part then needs the ultra-large type hydraulic press of several ten thousand tons. Titanium alloy forging needs to experience strict thermal process flow process to ensure comprehensive mechanical property. For ensureing whole parts size precision, often the reserved significantly surplus of forging, causes after machining that waste of material is serious.
In sum, existing titanium alloy component at least there is problems in that in manufacturing
1, owing to a large amount of surplus reserved by the blank after forging, material mechanical processing removal amount is big, and stock utilization is low;
2, needing forging and the big main flow technique of machining two, the manufacturing cycle is long;
3, Forging Technology is obtained in that good mechanical performance, but artificial in mechanical processing process destroys texture and the streamline that Forging Technology is formed, and then reduces component military service performance.
Summary of the invention
For the problem such as titanium alloy frame beam-like part cost height and process cycle length in prior art, the integration system technology for making that the present invention proposes to be combined titanium alloy profile electric heating stretch wrap forming with linear friction welding technology manufactures titanium alloy frame beam-like part. The present invention is that the near-net-shape technology of a kind of novelty is (after near-net-shape technology refers to part forming, only need a small amount of processing or do not reprocess, can be used as the forming technique of mechanical component), in combination with can solve the problem that Airplane frame beam-like part adopts the problems such as forging mechanical processing technique stock utilization is low.
For reaching above-mentioned purpose, the present invention proposes a kind of Titanium Alloy Aircraft frame beam-like part manufacture method, including: step 1, initial titanium alloy profile is carried out electric heating stretch bending, it is thus achieved that reach the bending titanium alloy profile that radius of curvature requires; Step 2, does curved reciprocating fricting movement by welding block with certain frequency pre-welding position on described bending titanium alloy profile, after fricting movement certain time, is welded on by described welding block on web and/or the base plate of bending titanium alloy profile; Step 3, bends the overlap that welds of titanium alloy profile and welding block described in milling, and according to manufacturing the dimensional requirement of Titanium Alloy Aircraft frame beam-like part, bends titanium alloy profile and welding block, it is thus achieved that meet the titanium alloy component of described dimensional requirement described in milling.
For reaching above-mentioned purpose, the present invention proposes a kind of Titanium Alloy Aircraft frame beam-like part manufacture method, including: step 1 ', welding block is done linear reciprocation fricting movement with certain frequency pre-welding position on initial titanium alloy profile, after fricting movement certain time, described welding block is welded on web and/or the base plate of initial titanium alloy profile; Step 2 ', initial titanium alloy profile described in milling welds overlap with welding block; Step 3 ', the initial titanium alloy profile having welded described welding block is carried out electric heating stretch bending, it is thus achieved that reach the bending titanium alloy profile having welded welding block that radius of curvature requires; Step 4 ', according to the dimensional requirement manufacturing Titanium Alloy Aircraft frame beam-like part, bend titanium alloy profile and welding block described in milling, it is thus achieved that meet the titanium alloy component of described dimensional requirement.
Improve stock utilization by the Titanium Alloy Aircraft frame beam-like part manufacture method of the present invention of the present invention, lower process costs and improve working (machining) efficiency simultaneously.
Accompanying drawing explanation
Accompanying drawing described herein is used for providing a further understanding of the present invention, constitutes the part of the application, is not intended that limitation of the invention. In the accompanying drawings:
Fig. 1 is the Titanium Alloy Aircraft frame beam-like part manufacture method flow chart of one embodiment of the invention.
Fig. 2 is the concrete grammar flow chart of step 1 in Fig. 1.
Fig. 3 is the Titanium Alloy Aircraft frame beam-like part manufacture method flow chart of another embodiment of the present invention.
Fig. 4 is step 3 in Fig. 3 ' concrete grammar flow chart.
Fig. 5 A to Fig. 5 D is the schematic flow sheet of the L-shaped titanium alloy component manufacture of the present invention one specific embodiment.
Fig. 6 A to Fig. 6 E is the schematic flow sheet of the U-shaped titanium alloy component manufacture of the present invention one specific embodiment.
Fig. 7 is the part-structure schematic diagram of the linear friction welding of the present invention one specific embodiment.
Fig. 8 A is that L-shaped titanium alloy profile is applied the schematic diagram of upset force by the present invention one specific embodiment.
Fig. 8 B is that U-shaped titanium alloy profile is applied the schematic diagram of upset force by the present invention one specific embodiment.
Detailed description of the invention
Hereinafter coordinate graphic and embodiments of the invention, the present invention is expanded on further and reaches the technological means that predetermined goal of the invention is taked.
Fig. 1 is the titanium alloy frame beam-like part manufacture method flow chart of one embodiment of the invention. As it is shown in figure 1, the method includes:
Step 1, carries out electric heating stretch bending to initial titanium alloy profile, it is thus achieved that reach the bending titanium alloy profile that radius of curvature requires;
Step 2, does curved reciprocating fricting movement with certain frequency at the pre-welding position bent on titanium alloy profile by welding block, after fricting movement certain time, is welded on by welding block on web and/or the base plate of bending titanium alloy profile;
Step 3, milling bends the overlap that welds of titanium alloy profile and welding block, and according to manufacturing the dimensional requirement of Titanium Alloy Aircraft frame beam-like part, milling bends titanium alloy profile and welding block, it is thus achieved that meet the titanium alloy component of dimensional requirement.
In the present embodiment, as in figure 2 it is shown, be the detailed step flow process of step 1 in Fig. 1, including:
Step 11, utilizes the clamp of stretch bending machine to clamp the two ends of initial titanium alloy profile, sets operating current, initial titanium alloy profile is heated;
Step 12, after temperature reaches requirement, the radius of curvature requirement according to titanium alloy component, utilize the clamp of stretch bending machine that initial titanium alloy profile is carried out stretch bending, it is thus achieved that to reach the bending titanium alloy profile that radius of curvature requires.
In the present embodiment, step 2 includes: utilize linear friction welder, welding block is done curved reciprocating fricting movement with certain frequency at the pre-welding position bent on titanium alloy profile, after fricting movement certain time, welding block is welded on web and/or the base plate of bending titanium alloy profile.
In the present embodiment, step 3 includes: utilize Digit Control Machine Tool, and milling bends the overlap that welds of titanium alloy profile and welding block, and according to manufacturing the dimensional requirement of Titanium Alloy Aircraft frame beam-like part, milling bending titanium alloy profile and welding block, it is thus achieved that meet the titanium alloy component of dimensional requirement.
The initial titanium alloy profile that the Titanium Alloy Aircraft frame beam-like part manufacture method of the present embodiment utilizes can be U-shaped, V-arrangement or L-shaped titanium alloy profile.
Relative to the order of abovementioned steps, yet another embodiment of the present invention, different in sequence of steps, but the initial titanium alloy profile adopted and the titanium alloy component obtained are identical.
Fig. 3 is the Titanium Alloy Aircraft frame beam-like part manufacture method flow chart of one embodiment of the invention. As it is shown on figure 3, the method includes:
Step 1 ', welding block is done linear reciprocation fricting movement with certain frequency pre-welding position on initial titanium alloy profile, after fricting movement certain time, welding block is welded on web and/or the base plate of initial titanium alloy profile;
Step 2 ', milling initial titanium alloy profile welds overlap with welding block;
Step 3 ', the initial titanium alloy profile having welded welding block is carried out electric heating stretch bending, it is thus achieved that reach the bending titanium alloy profile having welded welding block that radius of curvature requires;
Step 4 ', according to the dimensional requirement manufacturing Titanium Alloy Aircraft frame beam-like part, milling bending titanium alloy profile and welding block, it is thus achieved that meet the titanium alloy component of dimensional requirement.
In the present embodiment, step 1 ' including: utilize linear friction welder, welding block is done linear reciprocation fricting movement with certain frequency pre-welding position on initial titanium alloy profile, after fricting movement certain time, welding block is welded on web and/or the base plate of initial titanium alloy profile.
In the present embodiment, as shown in Figure 4, for step 3 in Fig. 3 ' concrete steps, including:
Step 31 ', utilize the clamp of stretch bending machine to clamp the two ends of the initial titanium alloy profile having welded welding block, set operating current, the initial titanium alloy profile having welded welding block is heated;
Step 32 ', after temperature reaches requirement, radius of curvature requirement according to titanium alloy component, utilizes the clamp of stretch bending machine that the initial titanium alloy profile having welded welding block is carried out stretch bending, it is thus achieved that reach the bending titanium alloy profile having welded welding block that radius of curvature requires.
In the present embodiment, step 2 ' including: utilizing Digit Control Machine Tool, milling initial titanium alloy profile welds overlap with welding block;
Step 4 ' including: utilize Digit Control Machine Tool, according to the dimensional requirement manufacturing Titanium Alloy Aircraft frame beam-like part, milling bending titanium alloy profile and welding block, it is thus achieved that meet the titanium alloy component of dimensional requirement.
The initial titanium alloy profile that the Titanium Alloy Aircraft frame beam-like part manufacture method of the present embodiment utilizes is U-shaped, V-arrangement or L-shaped titanium alloy profile.
In order to above-mentioned Titanium Alloy Aircraft frame beam-like part manufacture method is carried out apparent explanation, illustrate below in conjunction with specific embodiment, however, it should be noted that this embodiment is merely to be better described the present invention, it is not intended that and the present invention is limited improperly.
Fig. 5 A to Fig. 5 D is the schematic flow sheet of the L-shaped titanium alloy component manufacture of the present invention one specific embodiment. As shown in Fig. 5 A to Fig. 5 D, in conjunction with the manufacture method of Fig. 1, to manufacture L-shaped titanium alloy component:
First, shown in Fig. 5 A, adopt stretch bending machine, clamp L-shaped titanium alloy profile 1 two ends by clamp 2.
Setting electric current 1000��4000A, pulse width 1��1000ms, L-shaped titanium alloy profile 1 is heated by electric current by clamp 2.
When temperature reaches 650��750 DEG C, L-shaped titanium alloy profile 1 is applied the prestretching amount of 0.5��1.5% by clamp 2, then L-shaped titanium alloy profile 1 is coated on mould by clamp 2, then L-shaped titanium alloy profile 1 is carried out the benefit amount of drawing (always stretching gauge with 2%, mend the amount of drawing corresponding with prestretching amount) of 1.5��0.5%.
Now, the L-shaped titanium alloy profile 1 after bending reaches target part radius of curvature requirement, takes off L-shaped titanium alloy profile 1 blank after bending.
Processing welding block 3, reserved 5��20% surpluses compared with target floor size. (welding block 3 obtains the floor of target size after milling. )
Shown in Fig. 5 B, adopt linear friction soldering equipment, clamp welding block 3 by fixture, at technological parameter (frequency of vibration 10��100Hz, friction pressure 1��10atm, upset force 1.1��11atm, in fraction time 10��60s, amplitude 1��3mm) under weld, welding block 3 is welded on the web of the L-shaped titanium alloy profile 1 after bending, after all welding blocks 3 have welded, it is thus achieved that with the L-shaped titanium alloy profile 1 of welding block 3, i.e. part just base.
In this step, Fig. 5 B illustrates direction of vibration 6 and the direction of upset force 5.
Finally, shown in Fig. 5 C and Fig. 5 D, Digit Control Machine Tool is utilized, unnecessary overlap 4 is removed by CNC milling cutter 8, and according to the L-shaped titanium alloy profile 1 of target part size milling welding block 3 with bending, obtain the floor 7 of target size after milling, and obtain the titanium alloy component of target size.
Fig. 6 A to Fig. 6 E is the schematic flow sheet of the U-shaped titanium alloy component manufacture of the present invention one specific embodiment.As shown in Fig. 6 A to Fig. 6 E, in conjunction with the manufacture method of Fig. 3, to manufacture U-shaped titanium alloy component:
First, machining titanium alloy welding block 3, reserved 5��20% surpluses compared with target floor size. (welding block 3 obtains the floor of target size after milling. )
Shown in Fig. 6 A, adopt linear friction soldering equipment, clamp welding block 3 by fixture, at technological parameter (frequency of vibration 10��100Hz, friction pressure 1��10atm, upset force 1.1��11atm, in fraction time 10��60s, amplitude 1��3mm) under weld, welding block 3 is welded on two coxostermums and the base plate of the initial blank of U-shaped titanium alloy profile 9, after all welding blocks 3 have welded, it is thus achieved that with the U-shaped titanium alloy profile 9 of welding block 3, i.e. part just base.
In this step, Fig. 6 B illustrates direction of vibration 6 and the direction of upset force 5.
Shown in Fig. 6 B, utilize Digit Control Machine Tool to be removed by the welding block 3 surrounding overlap of welding, namely obtain the floor 7 of target size.
Shown in Fig. 6 C, utilize stretch bending machine, clamped the two ends of part just base by clamp 2.
Setting electric current 1000��4000A, pulse width 1��1000ms, part just base is heated by electric current by clamp 2.
When temperature reaches 650��750 DEG C, part just base is applied the prestretching amount of 0.5��1.5% by clamp 2, then part just base is coated on mould by clamp 2, and part just base then carries out the benefit amount of drawing (always stretching gauge with 2%, mend the amount of drawing corresponding with prestretching amount) of 1.5��0.5%.
Now part just base reaches target part radius of curvature requirement, is taken off.
Shown in Fig. 6 D and Fig. 6 E, utilize Digit Control Machine Tool, remove the part overlap 4 that just base is unnecessary by CNC milling cutter 8, and according to the U-shaped titanium alloy profile 9 of target part size milling welding block 3 with bending, it is thus achieved that the titanium alloy component of target size.
In the present embodiment, Fig. 7 is the partial structurtes schematic diagram of linear friction welder; Fig. 8 A and Fig. 8 B respectively to L-shaped titanium alloy profile, U-shaped titanium alloy profile apply upset force schematic diagram.
Shown in Fig. 7, Fig. 8 A, Fig. 8 B, titanium alloy profile 10 is mounted on linear friction welder, put into floor workpiece 11 simultaneously, utilize vibration tool 13 by floor workpiece 11 with certain frequency pre-welding position on titanium alloy profile 10, linear reciprocation fricting movement is done along direction of vibration 6, after fricting movement certain time, under the effect of upset force 5, by floor frock 12, floor workpiece 11 is welded on web and/or the base plate of titanium alloy profile 10.
In the present embodiment, titanium alloy profile 10 can be L-shaped titanium alloy profile 1, U-shaped titanium alloy profile 9 or V-arrangement titanium alloy profile.
Linear friction welding (the LinearFrictionWelding adopted in the present invention, LFW) it is make clamping workpiece and target workpiece planar do linear reciprocal movement and frictional heat by certain friction pressure, there is atoms permeating and recrystallization in interface under the combined effect of power and temperature, thus reaching the effect of solid diffusivity.
Linear friction welding is Solid-phase welding technology, and weld properties has clear superiority with microstructure than fusion weld form. Additionally, the generally pre-made allowance of section bar and floor, therefore thickness is thicker than general sheet material, if adopting fusion weld can relate to the problem such as through welding, even weld, and linear friction welding is to contact frictional heat by face to weld, compare fusion weld more for process advantage.
The titanium alloy profile electric heating stretch wrap forming technique (TitaniumProfileHotStretchForming adopted in the present invention, TP-HSF), it is utilize the characteristic that titanium alloy heat conductivility is low, resistance coefficient is big, sectional material blank bending forming process continues through bigger electric current, the Joule heat that this section of sectional material blank self-resistance produces is utilized to be heated, the technique being heated to forming temperature stretch wrap forming. Can be widely applied to the field that part requirements is higher, such as the bending forming of the constitutional details such as carry-on frame, edge strip.
Utilizing the Airplane frame class part that the Titanium Alloy Aircraft frame beam-like part manufacture method of the present invention produces, main body has uiform section section bar feature mostly, and simply in member body, Similarity of Local Characteristic Structure occurs in some position.
Additionally, in actual applications, manufacture different from titanium alloy forging, the similar market supply state that is in such as titanium alloy profile and sheet material, tubing or the wire rod that the present invention adopts, decreasing all too many levels such as the melting ingot before section bar shapes, extrusion process design and production, cost declines to a great extent. Section bar bears three-dimensional compressive stress state in extrusion process, and material intrinsic mechanical performance is excellent, is combined with linear friction welding, it is thus achieved that the characteristic size structure beyond main body section, it is possible to retain its original streamline and texture characteristic. In conjunction with the welding performance that titanium alloy linear friction welding is excellent, electric heating stretch wrap forming and linear friction welding manufacturing technology ensure that the mechanical performance of part. Additionally, have significant advantage compared with forging in stock utilization.
Improve stock utilization by the Titanium Alloy Aircraft frame beam-like part manufacture method of the present invention of the present invention, lower process costs and improve working (machining) efficiency simultaneously.
Particular embodiments described above; the purpose of the present invention, technical scheme and beneficial effect have been further described; it is it should be understood that; the foregoing is only specific embodiments of the invention; the protection domain being not intended to limit the present invention; all within the spirit and principles in the present invention, any amendment of making, equivalent replacement, improvement etc., should be included within protection scope of the present invention.
Claims (10)
1. a Titanium Alloy Aircraft frame beam-like part manufacture method, it is characterised in that including:
Step 1, carries out electric heating stretch bending to initial titanium alloy profile, it is thus achieved that reach the bending titanium alloy profile that radius of curvature requires;
Step 2, does curved reciprocating fricting movement by welding block with certain frequency pre-welding position on described bending titanium alloy profile, after fricting movement certain time, is welded on by described welding block on web and/or the base plate of bending titanium alloy profile;
Step 3, bends the overlap that welds of titanium alloy profile and welding block described in milling, and according to manufacturing the dimensional requirement of Titanium Alloy Aircraft frame beam-like part, bends titanium alloy profile and welding block, it is thus achieved that meet the titanium alloy component of described dimensional requirement described in milling.
2. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 1, it is characterised in that described step 1 includes:
Step 11, utilizes the clamp of stretch bending machine to clamp the two ends of described initial titanium alloy profile, sets operating current, described initial titanium alloy profile is heated;
Step 12, after temperature reaches requirement, the radius of curvature requirement according to titanium alloy component, utilize the clamp of described stretch bending machine that described initial titanium alloy profile is carried out stretch bending, it is thus achieved that to reach the bending titanium alloy profile that radius of curvature requires.
3. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 1, it is characterised in that described step 2 includes:
Utilize linear friction welder, welding block is done curved reciprocating fricting movement with certain frequency pre-welding position on described bending titanium alloy profile, after fricting movement certain time, described welding block is welded on web and/or the base plate of bending titanium alloy profile.
4. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 1, it is characterized in that, described step 3 includes: utilize Digit Control Machine Tool, bending titanium alloy profile described in milling welds overlap with welding block, and according to manufacturing the dimensional requirement of Titanium Alloy Aircraft frame beam-like part, titanium alloy profile and welding block is bent, it is thus achieved that meet the titanium alloy component of described dimensional requirement described in milling.
5. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 1, it is characterised in that described initial titanium alloy profile is U-shaped, V-arrangement or L-shaped titanium alloy profile.
6. a Titanium Alloy Aircraft frame beam-like part manufacture method, it is characterised in that including:
Step 1 ', welding block is done linear reciprocation fricting movement with certain frequency pre-welding position on initial titanium alloy profile, after fricting movement certain time, described welding block is welded on web and/or the base plate of initial titanium alloy profile;
Step 2 ', initial titanium alloy profile described in milling welds overlap with welding block;
Step 3 ', the initial titanium alloy profile having welded described welding block is carried out electric heating stretch bending, it is thus achieved that reach the bending titanium alloy profile having welded welding block that radius of curvature requires;
Step 4 ', according to the dimensional requirement manufacturing Titanium Alloy Aircraft frame beam-like part, bend titanium alloy profile and welding block described in milling, it is thus achieved that meet the titanium alloy component of described dimensional requirement.
7. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 6, it is characterised in that described step 1 ' including:
Utilize linear friction welder, welding block is done linear reciprocation fricting movement with certain frequency pre-welding position on initial titanium alloy profile, after fricting movement certain time, described welding block is welded on web and/or the base plate of initial titanium alloy profile.
8. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 6, it is characterised in that described step 3 ' including:
Step 31 ', utilize the clamp of stretch bending machine to clamp the two ends of the initial titanium alloy profile having welded welding block, set operating current, to the described initial titanium alloy profile heating having welded welding block;
Step 32 ', after temperature reaches requirement, radius of curvature requirement according to titanium alloy component, utilizes the clamp of described stretch bending machine that the described initial titanium alloy profile having welded welding block is carried out stretch bending, it is thus achieved that reach the bending titanium alloy profile having welded welding block that radius of curvature requires.
9. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 6, it is characterised in that described step 2 ' including: utilizing Digit Control Machine Tool, initial titanium alloy profile described in milling welds overlap with welding block;
Described step 4 ' including: utilize Digit Control Machine Tool, according to the dimensional requirement manufacturing Titanium Alloy Aircraft frame beam-like part, bend titanium alloy profile and welding block described in milling, it is thus achieved that meet the titanium alloy component of described dimensional requirement.
10. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 6, it is characterised in that described initial titanium alloy profile is U-shaped, V-arrangement or L-shaped titanium alloy profile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410524921.8A CN104443426B (en) | 2014-10-08 | 2014-10-08 | A kind of Titanium Alloy Aircraft frame beam-like part manufacture method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410524921.8A CN104443426B (en) | 2014-10-08 | 2014-10-08 | A kind of Titanium Alloy Aircraft frame beam-like part manufacture method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104443426A CN104443426A (en) | 2015-03-25 |
| CN104443426B true CN104443426B (en) | 2016-06-08 |
Family
ID=52890336
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410524921.8A Active CN104443426B (en) | 2014-10-08 | 2014-10-08 | A kind of Titanium Alloy Aircraft frame beam-like part manufacture method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104443426B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105750839A (en) * | 2016-04-20 | 2016-07-13 | 北京航空航天大学 | Combining and manufacturing method of titanium alloy curvature component with ribs |
| CN109202263B (en) * | 2017-09-15 | 2021-02-02 | 中国航空制造技术研究院 | Linear friction welding method |
| CN109202386B (en) * | 2018-11-08 | 2020-06-23 | 宝鸡市泛美材料科技有限公司 | Method for improving weld joint structure of titanium and titanium alloy plate |
| CN110756983A (en) * | 2019-11-27 | 2020-02-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for manufacturing three-dimensional structure by linear friction welding |
| CN111644498B (en) * | 2020-06-12 | 2021-09-10 | 中国航空制造技术研究院 | Control method for electrothermal stretch bending process of titanium alloy section and stretch bending forming device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101331002A (en) * | 2005-12-16 | 2008-12-24 | 空中客车英国有限公司 | Structural element and manufacturing method |
| US7526851B1 (en) * | 2004-05-27 | 2009-05-05 | The Boeing Company | Conformal vacuum cup apparatus and method |
| CN201776333U (en) * | 2010-09-14 | 2011-03-30 | 上海海都化学科技有限公司 | Titanium alloy drawing machine tool |
| CN102006986A (en) * | 2008-03-07 | 2011-04-06 | 空中客车公司 | Method and device for producing a curved section made from composite material and resulting section |
| CN103272908A (en) * | 2013-06-13 | 2013-09-04 | 沈阳飞机工业（集团）有限公司 | Stretch forming method for titanium skin part |
| CN103878238A (en) * | 2014-03-28 | 2014-06-25 | 中国航空工业集团公司北京航空制造工程研究所 | Flexible mold used for profile stretch bending |
-
2014
- 2014-10-08 CN CN201410524921.8A patent/CN104443426B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7526851B1 (en) * | 2004-05-27 | 2009-05-05 | The Boeing Company | Conformal vacuum cup apparatus and method |
| CN101331002A (en) * | 2005-12-16 | 2008-12-24 | 空中客车英国有限公司 | Structural element and manufacturing method |
| CN102006986A (en) * | 2008-03-07 | 2011-04-06 | 空中客车公司 | Method and device for producing a curved section made from composite material and resulting section |
| CN201776333U (en) * | 2010-09-14 | 2011-03-30 | 上海海都化学科技有限公司 | Titanium alloy drawing machine tool |
| CN103272908A (en) * | 2013-06-13 | 2013-09-04 | 沈阳飞机工业（集团）有限公司 | Stretch forming method for titanium skin part |
| CN103878238A (en) * | 2014-03-28 | 2014-06-25 | 中国航空工业集团公司北京航空制造工程研究所 | Flexible mold used for profile stretch bending |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104443426A (en) | 2015-03-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104443426B (en) | A kind of Titanium Alloy Aircraft frame beam-like part manufacture method | |
| RU2568229C2 (en) | Production of turbomachine blade metallic stiffness element | |
| Scheffler et al. | Incremental sheet metal forming on the example of car exterior skin parts | |
| US20090250834A1 (en) | Formed sheet metal composite tooling | |
| US9718265B2 (en) | Method for producing a composite sheet metal part having a metallic region, and corresponding molding tool | |
| Lingam et al. | Automatic feature recognition and tool path strategies for enhancing accuracy in double sided incremental forming | |
| EP2736707A2 (en) | Methods and systems for forming reinforced composite articles having variable thickness corners | |
| CN102639287A (en) | Method for making a metal reinforcement for a turbine engine blade | |
| EP2873620B1 (en) | Repair method for fuselage components of aircraft or spacecraft | |
| EP3153302A1 (en) | Method for obtaining a welded joint between elements of different materials, and a hybrid component obtained through this method | |
| JP2010500932A (en) | Manufacturing method of workpiece made of fiber composite material, and fiber composite part in the shape of a deformed material having a cross-sectional contour that varies over the entire length | |
| CN105183932A (en) | Stamping computer simulation calculating method with consideration of mold deformation | |
| EP3109033A1 (en) | Compression mould, compression moulding tool and compression moulding method | |
| Zafar et al. | Analysis of hydro-mechanical deep drawing and the effects of cavity pressure on quality of simultaneously formed three-layer Al alloy parts | |
| EP2868460A1 (en) | Device and method of manufacturing omega stringers | |
| EP3216691A1 (en) | Airframe component and methods for manufacturing an airframe component | |
| CN109093270B (en) | Device and method for forming and manufacturing large-sized plate welding cabin body opening cover | |
| CN104213059A (en) | Titanium alloy double layer curved surface wing plate part heat treatment deformation control method | |
| CN104707926B (en) | A kind of large-scale arc forging stock molding forging method | |
| CN102672418B (en) | Forming process for stand column of stainless steel car body side wall | |
| CN106738505A (en) | A kind of manufacturing method of composite material forming mold with composite structure | |
| Wang et al. | Research on a wrinkle-free forming method using low-melting alloy for sheet metal | |
| CN107128508B (en) | A kind of straight wing forming method | |
| Albert et al. | Smart process combination for aluminum/plastic hybrid components | |
| CN203792608U (en) | Improved structure of automobile interior trim part forging hydraulic press |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 100024 North East military villa, eight Li bridge, Chaoyang District, Beijing Patentee after: China Institute of Aeronautical Manufacturing Technology Address before: 100024 North East military villa, eight Li bridge, Chaoyang District, Beijing Patentee before: Beijing Aviation Manufacturing Engineering Institute of China Aviation Industry Group Company |
|
| CP01 | Change in the name or title of a patent holder |