CN104443426A - Aircraft titanium alloy frame beam type part manufacturing method - Google Patents
Aircraft titanium alloy frame beam type part manufacturing method Download PDFInfo
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- CN104443426A CN104443426A CN201410524921.8A CN201410524921A CN104443426A CN 104443426 A CN104443426 A CN 104443426A CN 201410524921 A CN201410524921 A CN 201410524921A CN 104443426 A CN104443426 A CN 104443426A
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Abstract
The invention discloses an aircraft titanium alloy frame beam type part manufacturing method. The method includes the steps that electric heat stretch bending are conducted on an initial titanium alloy sectional material to obtain a bent titanium alloy sectional material meeting the requirement for the curvature radius; a welding block conducts curve reciprocating friction motion at a pre-welded portion of the bent titanium alloy sectional material at definite frequency, and after friction motion lasts for a certain period of time, the welding block is welded to a web plate or/and a bottom plate of the bent titanium alloy sectional material; welding flash of the bent titanium alloy sectional material and the welding block is milled and cut, the bent titanium alloy sectional material and the welding block are milled and cut according to the dimensional requirements of manufacturing of aircraft titanium alloy frame beam type parts, and a titanium alloy part meeting the dimensional requirements is obtained. During part machining, the sequence of the procedures of electric heat stretch bending and reciprocating friction welding can be exchanged. The titanium alloy frame beam type parts can be manufactured according to the method. According to the aircraft titanium alloy frame beam type part manufacturing method, the utilization rate of materials is increased, and machining efficiency is improved while process cost is reduced.
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, primarily of the aircraft skin (thin skin, Varying-thickness covering, band muscle integral panel etc.) of curved profile, in length and breadth skeleton (long purlin and bulkhead etc.) composition.And bulkhead class part is the important form of airframe structure, it is characterized by profile and there is curvature feature request and locally there is 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, becoming the key problem in technology affecting aircraft development and ensure overall aircraft military service performance, is also one of the principal element affecting aircraft manufacturing cycle, cost and benefit.
In recent years, multiple material (Carbon Fiber Reinforced Polymer/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.Because titanium alloy material and composite material have the Dent resistance of good electromotive force compatibility and titanium alloy material excellence itself, the application of titanium alloy frame beam-like part in civil aircraft is increasingly extensive.Titanium alloy frame beam-like part becomes the keystone configuration of multiple material fuselage load-carrying member, for load-bearing bulkhead beam length purlin, central 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 job operation to obtain the feature structure such as local ribs, muscle.Titanium alloy forging needs to carry out design and manufacture separately according to External Shape, generally commercially supplies unlike titanium alloy plate, section bar, tubing etc.Titanium alloy forging or die forging need large-scale specialized equipment, and Mega-boule forging or small-sized die-forged part need a few kiloton pressurized hydraulic machine, and large-scale die-forged part then needs the ultra-large type hydraulic compressor 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 waste of material serious after machine up.
In sum, during existing titanium alloy component manufactures, at least there is following problem:
1, because a large amount of surplus reserved by the blank after forging, material mechanical processing removal amount is large, and stock utilization is low;
2, need the large main flow technique of forging and machine up two, the manufacturing cycle is long;
3, Forging Technology can obtain good mechanical characteristics, but the texture destroying Forging Technology formation artificial in mechanical processing process and streamline, and then reduce component military service performance.
Summary of the invention
The problems such as high and process cycle is long for titanium alloy frame beam-like part cost in prior art, the present invention proposes the integration system technology for making of titanium alloy profile electric heating stretch-wrap forming and linear friction welding combine with technique to manufacture titanium alloy frame beam-like part.The present invention is that a kind of near-net-shape technology of novelty is (after near-net-shape technology refers to part forming, only need a small amount of processing or do not reprocess, just can be used as the forming technique of mechanical component), both combinations can solve Airplane frame beam-like part and adopt the problems such as forging mechanical processing technique stock utilization is low.
For achieving the above object, the present invention proposes a kind of Titanium Alloy Aircraft frame beam-like part manufacture method, comprising: step 1, electric heating stretch bending is carried out to initial titanium alloy profile, obtain the bending titanium alloy profile reaching radius of curvature requirement; Step 2, does curved reciprocating fricting movement by welding block with the pre-welding position of certain frequency on described bending titanium alloy profile, after fricting movement certain time, on the web that described welding block is welded on bending titanium alloy profile and/or base plate; Step 3, bending titanium alloy profile described in milling welds overlap with welding block, and according to manufacturing the dimensional characteristic of Titanium Alloy Aircraft frame beam-like part, described in milling, bending titanium alloy profile and welding block, obtain the titanium alloy component meeting described dimensional characteristic.
For achieving the above object, the present invention proposes a kind of Titanium Alloy Aircraft frame beam-like part manufacture method, comprise: step 1 ', welding block is done linear reciprocation fricting movement with the pre-welding position of certain frequency on initial titanium alloy profile, after fricting movement certain time, on the web that described welding block is welded on initial titanium alloy profile and/or base plate; Step 2 ', initial titanium alloy profile described in milling welds overlap with welding block; Step 3 ', electric heating stretch bending is carried out to the initial titanium alloy profile welding described welding block, obtains the bending titanium alloy profile having welded welding block reaching radius of curvature requirement; Step 4 ', according to the dimensional characteristic manufacturing Titanium Alloy Aircraft frame beam-like part, described in milling, bending titanium alloy profile and welding block, obtain the titanium alloy component meeting described dimensional characteristic.
Improve stock utilization by Titanium Alloy Aircraft frame beam-like part manufacture method of the present invention, lower process costs and improve work efficiency simultaneously.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide a further understanding of the present invention, forms a application's part, does not form limitation of the invention.In the accompanying drawings:
Fig. 1 is the Titanium Alloy Aircraft frame beam-like part manufacture method diagram of circuit of one embodiment of the invention.
Fig. 2 is the concrete grammar diagram of circuit of step 1 in Fig. 1.
Fig. 3 is the Titanium Alloy Aircraft frame beam-like part manufacture method diagram of circuit of another embodiment of the present invention.
Fig. 4 is step 3 in Fig. 3 ' concrete grammar diagram of circuit.
Fig. 5 A to Fig. 5 D is the schematic flow sheet that the L shape titanium alloy component of the present invention one specific embodiment manufactures.
Fig. 6 A to Fig. 6 E is the schematic flow sheet that the U-shaped titanium alloy component of the present invention one specific embodiment manufactures.
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 the present invention one specific embodiment applies the schematic diagram of upset force to L shape titanium alloy profile.
Fig. 8 B is that the present invention one specific embodiment applies the schematic diagram of upset force to U-shaped titanium alloy profile.
Detailed description of the invention
Below coordinating graphic and embodiments of the invention, setting forth the technological means that the present invention takes for reaching predetermined goal of the invention further.
Fig. 1 is the titanium alloy frame beam-like part manufacture method diagram of circuit of one embodiment of the invention.As shown in Figure 1, the method comprises:
Step 1, carries out electric heating stretch bending to initial titanium alloy profile, obtains the bending titanium alloy profile reaching radius of curvature requirement;
Step 2, does curved reciprocating fricting movement by welding block with the pre-welding position of certain frequency on bending titanium alloy profile, after fricting movement certain time, on web welding block being welded on bending titanium alloy profile and/or base plate;
Step 3, what milling bent titanium alloy profile and welding block welds overlap, and according to manufacturing the dimensional characteristic of Titanium Alloy Aircraft frame beam-like part, milling bends titanium alloy profile and welding block, obtains the titanium alloy component meeting dimensional characteristic.
In the present embodiment, as shown in Figure 2, be the detailed step flow process of step 1 in Fig. 1, comprise:
Step 11, utilizes the clamp of stretch bending machine to clamp the two ends of initial titanium alloy profile, and setting working current, heats initial titanium alloy profile;
Step 12, after temperature reaches requirement, according to the radius of curvature requirement of titanium alloy component, utilizes the clamp of stretch bending machine to carry out stretch bending to initial titanium alloy profile, obtains the bending titanium alloy profile reaching radius of curvature requirement.
In the present embodiment, step 2 comprises: utilize linear friction welder, welding block is done curved reciprocating fricting movement with the pre-welding position of certain frequency on bending titanium alloy profile, after fricting movement certain time, on web welding block being welded on bending titanium alloy profile and/or base plate.
In the present embodiment, step 3 comprises: utilize numerically-controlled machine tool, and what milling bent titanium alloy profile and welding block welds overlap, and according to manufacturing the dimensional characteristic of Titanium Alloy Aircraft frame beam-like part, milling bends titanium alloy profile and welding block, obtains the titanium alloy component meeting dimensional characteristic.
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 shape titanium alloy profile.
Relative to the order of abovementioned steps, the present invention also has another embodiment, different in sequence of steps, but the initial titanium alloy profile adopted is identical with the titanium alloy component obtained.
Fig. 3 is the Titanium Alloy Aircraft frame beam-like part manufacture method diagram of circuit of one embodiment of the invention.As shown in Figure 3, the method comprises:
Step 1 ', welding block is done linear reciprocation fricting movement with the pre-welding position of certain frequency on initial titanium alloy profile, after fricting movement certain time, on web welding block being welded on initial titanium alloy profile and/or base plate;
Step 2 ', milling initial titanium alloy profile welds overlap with welding block;
Step 3 ', electric heating stretch bending is carried out to the initial titanium alloy profile having welded welding block, obtains the bending titanium alloy profile having welded welding block reaching radius of curvature requirement;
Step 4 ', according to the dimensional characteristic manufacturing Titanium Alloy Aircraft frame beam-like part, milling bends titanium alloy profile and welding block, obtains the titanium alloy component meeting dimensional characteristic.
In the present embodiment, step 1 ' comprising: utilize linear friction welder, welding block is done linear reciprocation fricting movement with the pre-welding position of certain frequency on initial titanium alloy profile, after fricting movement certain time, on web welding block being welded on initial titanium alloy profile and/or base plate.
In the present embodiment, as shown in Figure 4, be step 3 in Fig. 3 ' concrete steps, comprising:
Step 31 ', utilize the clamp of stretch bending machine to clamp to have welded the two ends of the initial titanium alloy profile of welding block, setting working current, to the initial titanium alloy profile heating of having welded welding block;
Step 32 ', after temperature reaches requirement, according to the radius of curvature requirement of titanium alloy component, utilize the clamp of stretch bending machine to carry out stretch bending to the initial titanium alloy profile having welded welding block, obtain the bending titanium alloy profile having welded welding block reaching radius of curvature requirement.
In the present embodiment, step 2 ' comprising: utilize numerically-controlled machine tool, what milling bent titanium alloy profile and welding block welds overlap;
Step 4 ' comprising: utilize numerically-controlled machine tool, according to the dimensional characteristic manufacturing Titanium Alloy Aircraft frame beam-like part, milling bends titanium alloy profile and welding block, obtains the titanium alloy component meeting dimensional characteristic.
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 shape titanium alloy profile.
In order to more clearly explain above-mentioned Titanium Alloy Aircraft frame beam-like part manufacture method, be described below in conjunction with specific embodiment, but it should be noted that this embodiment is only to better the present invention is described, do not form and the present invention is limited improperly.
Fig. 5 A to Fig. 5 D is the schematic flow sheet that the L shape titanium alloy component of the present invention one specific embodiment manufactures.As shown in Fig. 5 A to Fig. 5 D, the manufacture method of composition graphs 1, to manufacture L shape titanium alloy component:
First, shown in composition graphs 5A, adopt stretch bending machine, clamp L shape titanium alloy profile 1 two ends by clamp 2.
Setting electric current 1000 ~ 4000A, pulse width 1 ~ 1000ms, electric current is heated by clamp 2 pairs of L shape titanium alloy profiles 1.
When temperature reaches 650 ~ 750 DEG C, clamp 2 pairs of L shape titanium alloy profiles 1 apply the prestretching amount of 0.5 ~ 1.5%, then L shape titanium alloy profile 1 is coated on mould by clamp 2, then L shape titanium alloy profile 1 is carried out to the benefit amount of drawing (always to stretch gauge with 2%, mend the amount of drawing corresponding with prestretching amount) of 1.5 ~ 0.5%.
Now, the L shape titanium alloy profile 1 after bending reaches the requirement of target part radius of curvature, takes off L shape 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 composition graphs 5B, adopt linear friction soldering equipment, clamp welding block 3 by fixture, at technological parameter (oscillation frequency 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 shape titanium alloy profile 1 after bending, after all welding blocks 3 have welded, obtain the L shape titanium alloy profile 1 with welding block 3, i.e. part just base.
In this step, the direction of direction of vibration 6 and upset force 5 is illustrated in Fig. 5 B.
Finally, shown in composition graphs 5C and Fig. 5 D, numerically-controlled machine tool is utilized, unnecessary overlap 4 is removed by CNC milling cutter 8, and according to target part size milling welding block 3 and bending L shape titanium alloy profile 1, 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 that the U-shaped titanium alloy component of the present invention one specific embodiment manufactures.As shown in Fig. 6 A to Fig. 6 E, the manufacture method of composition graphs 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 composition graphs 6A, adopt linear friction soldering equipment, clamp welding block 3 by fixture, at technological parameter (oscillation frequency 10 ~ 100Hz, friction pressure 1 ~ 10atm, upset force 1.1 ~ 11atm, in fraction time 10 ~ 60s, amplitude 1 ~ 3mm) under weld, on two coxostermums welding block 3 being welded to the initial blank of U-shaped titanium alloy profile 9 and base plate, after all welding blocks 3 have welded, obtain the U-shaped titanium alloy profile 9 with welding block 3, i.e. part just base.
In this step, the direction of direction of vibration 6 and upset force 5 is illustrated in Fig. 6 B.
Shown in composition graphs 6B, utilize numerically-controlled machine tool to be removed by the welding block 3 surrounding overlap of welding, namely obtain the floor 7 of target size.
Shown in composition graphs 6C, utilize stretch bending machine, clamped the two ends of the first base of part by clamp 2.
Setting electric current 1000 ~ 4000A, pulse width 1 ~ 1000ms, electric current is by the just base heating of clamp 2 pairs of parts.
When temperature reaches 650 ~ 750 DEG C, clamp 2 pairs of parts just base apply the prestretching amount of 0.5 ~ 1.5%, then clamp 2 by part just base be coated on mould, then to part just base carry out the benefit amount of drawing (always to stretch gauge with 2%, mend the amount of drawing corresponding with prestretching amount) of 1.5 ~ 0.5%.
Now the first base of part reaches the requirement of target part radius of curvature, is taken off.
Shown in composition graphs 6D and Fig. 6 E, utilize numerically-controlled machine tool, remove the part overlap 4 that just base is unnecessary by CNC milling cutter 8, and according to target part size milling welding block 3 and bending U-shaped titanium alloy profile 9, obtain the titanium alloy component of target size.
In the present embodiment, Fig. 7 is the local structure schematic diagram of linear friction welder; Fig. 8 A and Fig. 8 B is respectively the schematic diagram to L shape titanium alloy profile, U-shaped titanium alloy profile applying upset force.
Shown in composition graphs 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 the pre-welding position of certain frequency 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, on web floor workpiece 11 being welded on titanium alloy profile 10 by floor frock 12 and/or base plate.
In the present embodiment, titanium alloy profile 10 can be L shape titanium alloy profile 1, U-shaped titanium alloy profile 9 or V-arrangement titanium alloy profile.
Linear friction welding (the Linear Friction Welding adopted in the present invention, LFW) be make holding 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 action of power and temperature, thus reach the effect of solid diffusivity.
Linear friction welding is Solid-phase welding technology, and weld properties has clear superiority with microstructure than autogenous welding form.In addition, section bar and floor be pre-made allowance usually, and therefore the general sheet material of Thickness Ratio is thick, if adopt fusion weld can relate to the problem such as through welding, even weld, and linear friction welding is welded by face contact friction heat-dissipating, compare fusion weld and have more standby process advantage.
Titanium alloy profile electric heating stretch-wrap forming technique (the Titanium Profile Hot StretchForming adopted in the present invention, TP-HSF), utilize the characteristic that titanium alloy heat conductivility is low, resistance coefficient is large, larger electric current is continued through in sectional material blank bending forming process, the joule heat utilizing this section of sectional material blank self-resistance to produce heats, and is heated to the technique of forming temperature stretch-wrap forming.The field higher to part requirements can be widely used in, as the bending forming of the constructional delailss such as carry-on frame, edge strip.
Utilize the Airplane frame class part that Titanium Alloy Aircraft frame beam-like part manufacture method of the present invention produces, main body has uniform cross section section bar feature mostly, and just in member body, Similarity of Local Characteristic Structure appears in some position.
In addition, in actual applications, manufacture different from titanium alloy forging, the similar market supply states that are in such as the titanium alloy profile that the present invention adopts and sheet material, tubing or wire rod, decrease all too many levels such as the melting ingot before section bar is shaped, extrusion process design and production, cost declines to a great extent.Section bar bears three-dimensional compressive stress state in crumpling process, and material intrinsic mechanical characteristics is excellent, is combined with linear friction welding, obtains the characteristic dimension structure beyond main body section, can retain its original streamline and texture characteristic.In conjunction with the welding performance of titanium alloy linear friction welding excellence, electric heating stretch-wrap forming and linear friction welding manufacturing technology can ensure the mechanical characteristics of part.In addition, in stock utilization, there is significant advantage compared with forging.
Improve stock utilization by Titanium Alloy Aircraft frame beam-like part manufacture method of the present invention, lower process costs and improve work efficiency simultaneously.
Above-described specific embodiment; object of the present invention, technical scheme and beneficial effect are further described; be understood that; the foregoing is only specific embodiments of the invention; the protection domain be not intended to limit the present invention; within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (10)
1. a Titanium Alloy Aircraft frame beam-like part manufacture method, is characterized in that, comprising:
Step 1, carries out electric heating stretch bending to initial titanium alloy profile, obtains the bending titanium alloy profile reaching radius of curvature requirement;
Step 2, does curved reciprocating fricting movement by welding block with the pre-welding position of certain frequency on described bending titanium alloy profile, after fricting movement certain time, on the web that described welding block is welded on bending titanium alloy profile and/or base plate;
Step 3, bending titanium alloy profile described in milling welds overlap with welding block, and according to manufacturing the dimensional characteristic of Titanium Alloy Aircraft frame beam-like part, described in milling, bending titanium alloy profile and welding block, obtain the titanium alloy component meeting described dimensional characteristic.
2. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 1, it is characterized in that, described step 1 comprises:
Step 11, utilizes the clamp of stretch bending machine to clamp the two ends of described initial titanium alloy profile, setting working current, to described initial titanium alloy profile heating;
Step 12, after temperature reaches requirement, according to the radius of curvature requirement of titanium alloy component, utilizes the clamp of described stretch bending machine to carry out stretch bending to described initial titanium alloy profile, obtains the bending titanium alloy profile reaching radius of curvature requirement.
3. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 1, it is characterized in that, described step 2 comprises:
Utilize linear friction welder, welding block is done curved reciprocating fricting movement with the pre-welding position of certain frequency on described bending titanium alloy profile, after fricting movement certain time, on the web that described welding block is welded on bending titanium alloy profile and/or base plate.
4. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 1, it is characterized in that, described step 3 comprises: utilize numerically-controlled machine tool, bending titanium alloy profile described in milling welds overlap with welding block, and according to manufacturing the dimensional characteristic of Titanium Alloy Aircraft frame beam-like part, described in milling, bending titanium alloy profile and welding block, obtain the titanium alloy component meeting described dimensional characteristic.
5. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 1, is characterized in that, described initial titanium alloy profile is U-shaped, V-arrangement or L shape titanium alloy profile.
6. a Titanium Alloy Aircraft frame beam-like part manufacture method, is characterized in that, comprising:
Step 1 ', welding block is done linear reciprocation fricting movement with the pre-welding position of certain frequency on initial titanium alloy profile, after fricting movement certain time, on the web that described welding block is welded on initial titanium alloy profile and/or base plate;
Step 2 ', initial titanium alloy profile described in milling welds overlap with welding block;
Step 3 ', electric heating stretch bending is carried out to the initial titanium alloy profile welding described welding block, obtains the bending titanium alloy profile having welded welding block reaching radius of curvature requirement;
Step 4 ', according to the dimensional characteristic manufacturing Titanium Alloy Aircraft frame beam-like part, described in milling, bending titanium alloy profile and welding block, obtain the titanium alloy component meeting described dimensional characteristic.
7. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 6, is characterized in that, described step 1 ' comprising:
Utilize linear friction welder, welding block is done linear reciprocation fricting movement with the pre-welding position of certain frequency on initial titanium alloy profile, after fricting movement certain time, on the web that described welding block is welded on initial titanium alloy profile and/or base plate.
8. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 6, is characterized in that, described step 3 ' comprising:
Step 31 ', utilize the clamp of stretch bending machine to clamp to have welded the two ends of the initial titanium alloy profile of welding block, setting working current, to described initial titanium alloy profile heating of having welded welding block;
Step 32 ', after temperature reaches requirement, according to the radius of curvature requirement of titanium alloy component, utilize the clamp of described stretch bending machine to carry out stretch bending to the described initial titanium alloy profile having welded welding block, obtain the bending titanium alloy profile having welded welding block reaching radius of curvature requirement.
9. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 6, is characterized in that, described step 2 ' comprising: utilize numerically-controlled machine tool, bending titanium alloy profile described in milling welds overlap with welding block;
Described step 4 ' comprising: utilize numerically-controlled machine tool, according to the dimensional characteristic manufacturing Titanium Alloy Aircraft frame beam-like part, described in milling, bending titanium alloy profile and welding block, obtain the titanium alloy component meeting described dimensional characteristic.
10. Titanium Alloy Aircraft frame beam-like part manufacture method according to claim 6, is characterized in that, described initial titanium alloy profile is U-shaped, V-arrangement or L shape titanium alloy profile.
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| 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 |
| CN111644498A (en) * | 2020-06-12 | 2020-09-11 | 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 |
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