CN110625113B - Rapid preparation method of airplane structure crack reinforcing part - Google Patents

Rapid preparation method of airplane structure crack reinforcing part Download PDF

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CN110625113B
CN110625113B CN201910794325.4A CN201910794325A CN110625113B CN 110625113 B CN110625113 B CN 110625113B CN 201910794325 A CN201910794325 A CN 201910794325A CN 110625113 B CN110625113 B CN 110625113B
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printing
checking
heat treatment
reinforcement
dimensional drawing
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CN110625113A (en
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张洁
刘世华
蔡小叶
范朝
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State Run Wuhu Machinery Factory
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State Run Wuhu Machinery Factory
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/20—Direct sintering or melting
    • B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/30—Process control
    • B22F10/36—Process control of energy beam parameters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/60—Treatment of workpieces or articles after build-up
    • B22F10/64—Treatment of workpieces or articles after build-up by thermal means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/80—Data acquisition or data processing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y10/00—Processes of additive manufacturing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y50/00—Data acquisition or data processing for additive manufacturing
    • B33Y50/02—Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
    • 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
    • B64F5/40—Maintaining or repairing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
    • B22F2003/248—Thermal after-treatment
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency

Abstract

The invention relates to the technical field of airplane structure crack repair, in particular to a method for quickly preparing an airplane structure crack reinforcing part, which comprises the following specific steps: s1: structural cracks are found; s2: drawing a reinforcing part drawing; s3: the SLA prints the check parts; s4: checking, installing and optimizing the three-dimensional model; s5: an SLM manufacturing machine part; s6: heat treatment; the technological method for rapidly preparing the airplane structure crack reinforcing piece by rapidly preparing the reinforcing piece inspection piece through SLA photocuring 3D printing and finally manufacturing the machine part assembly through selective SLM laser melting additive manufacturing greatly shortens the preparation period of the reinforcing piece, reduces the cost, improves the material utilization rate, and has great economic value and military value.

Description

Rapid preparation method of airplane structure crack reinforcing part
Technical Field
The invention relates to the technical field of airplane structure crack repair, in particular to a method for quickly preparing an airplane structure crack reinforcing part.
Background
Structural crack reinforcements for aircraft are patch reinforcements for airframe cracks found during repairs. The traditional reinforcing part preparation process comprises the following steps: 1) according to the crack position, considering assembly, drawing a three-dimensional drawing of the reinforcement; 2) and machining a fitting part according to a drawing and performing trial assembly. Optimizing a three-dimensional drawing according to the checking and assembling condition; 3) and machining a qualified reinforcement according to the optimized three-dimensional drawing. Wherein the machining reinforcing piece flow is as follows: the method comprises the following steps of plate initial processing, quenching treatment, finish machining, stress relief annealing and surface treatment. Basically, the time consumption is more than 20 days, the cost is high, and the material waste is huge.
Disclosure of Invention
In order to solve the problems, the invention provides a method for quickly preparing a crack reinforcement of an airplane structure.
A method for quickly preparing an airplane structure crack reinforcing part comprises the following specific steps:
s1: structural cracks are found;
s2: drawing a reinforcing part drawing: drawing a three-dimensional drawing of the structural crack reinforcement piece according to the position of the crack;
s3: SLA printing and fitting: storing the drawn three-dimensional drawing in an STL format, and guiding the drawing into an SLA photocuring nonmetal 3D printer;
s4: and (3) checking, installing and optimizing the three-dimensional model: checking and packaging after printing, and adjusting the size of the three-dimensional drawing according to the checking and packaging condition; repeatedly printing, checking and installing until the size is completely proper, and storing the drawing;
s5: SLM manufacturing machine parts: after the three-dimensional drawing of the reinforcement is determined, storing the three-dimensional drawing in an STL format, and guiding the three-dimensional drawing to SLM laser selective melting equipment for preparing the reinforcement;
s6: and (3) heat treatment: and carrying out heat treatment on the prepared reinforcing piece.
The main process parameters of the part inspection and printing in the step S3 are as follows:
laser power: 500 mW;
focusing the light spot: 0.15 mm;
moving speed of the light spot: 5-10 m/S;
single-layer printing thickness: 0.1 mm.
The error of the moving speed of the light spot is 1/6-1/8.
The specific process parameters of the reinforcing part in the step S5 are as follows:
laser power: 180W;
the diameter of the light spot: 70 μm;
single-layer powder laying thickness: 50 μm;
scanning speed: 1100-1300 mm/s.
The heat treatment of the step S6 is a titanium alloy heat treatment process with the process parameter of 850 ℃/2 h.
The invention has the beneficial effects that: the technological method for rapidly preparing the airplane structure crack reinforcing piece by rapidly preparing the reinforcing piece inspection piece through SLA photocuring 3D printing and finally manufacturing the machine part assembly through selective SLM laser melting additive manufacturing greatly shortens the preparation period of the reinforcing piece, reduces the cost, improves the material utilization rate, and has great economic value and military value.
Drawings
The invention is further illustrated with reference to the following figures and examples.
FIG. 1 is a schematic view of the flow structure of the present invention;
FIG. 2 is a front view of the reinforcement of the present invention;
FIG. 3 is a schematic top view of the reinforcement member of the present invention;
fig. 4 is a left side view of the reinforcing member of the present invention.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further explained below.
As shown in fig. 1 to 4, a method for rapidly preparing an aircraft structural crack reinforcement includes the following specific steps:
s1: structural cracks are found;
s2: drawing a reinforcing part drawing: drawing a three-dimensional drawing of the structural crack reinforcement piece according to the position of the crack;
s3: SLA printing and fitting: storing the drawn three-dimensional drawing in an STL format, and guiding the drawing into an SLA photocuring nonmetal 3D printer;
s4: and (3) checking, installing and optimizing the three-dimensional model: checking and packaging after printing, and adjusting the size of the three-dimensional drawing according to the checking and packaging condition; repeatedly printing, checking and installing until the size is completely proper, and storing the drawing;
s5: SLM manufacturing machine parts: after the three-dimensional drawing of the reinforcement is determined, storing the three-dimensional drawing in an STL format, and guiding the three-dimensional drawing to SLM laser selective melting equipment for preparing the reinforcement;
s6: and (3) heat treatment: and carrying out heat treatment on the prepared reinforcing piece.
The main process parameters of the part inspection and printing in the step S3 are as follows:
laser power: 500 mW;
focusing the light spot: 0.15 mm;
moving speed of the light spot: 5-10 m/S;
single-layer printing thickness: 0.1 mm.
The error of the moving speed of the light spot is 1/6-1/8.
The specific process parameters of the reinforcing part in the step S5 are as follows:
laser power: 180W;
the diameter of the light spot: 70 μm;
single-layer powder laying thickness: 50 μm;
scanning speed: 1100-1300 mm/s.
The heat treatment of the step S6 is a titanium alloy heat treatment process with the process parameter of 850 ℃/2 h.
The traditional mechanical processing and photocuring printing inspection piece are compared to obtain a comparison result:
Figure BDA0002180480000000031
comparing the traditional machining and the laser selective area reinforcing part to obtain a comparison result:
Figure BDA0002180480000000032
Figure BDA0002180480000000041
and (4) conclusion: the rapid preparation airplane structure crack reinforcing piece of the final assembling machine part combination is manufactured by adopting SLA photocuring 3D printing rapid preparation reinforcing piece assembling piece and SLM laser selective melting additive manufacturing, compared with the traditional machining, the preparation period of the reinforcing piece is shortened, the cost is reduced, the material utilization rate is improved, the cost is saved by more than 2000 elements when a single reinforcing piece is manufactured in the whole process, the saving period is nearly 200 hours, the material utilization rate is greatly improved, and the rapid preparation airplane structure crack reinforcing piece has high economic value and military value.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are merely illustrative of the principles of the invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims (4)

1. A method for quickly preparing an airplane structure crack reinforcing part is characterized by comprising the following steps: the method comprises the following specific steps:
s1: structural cracks are found;
s2: drawing a reinforcing part drawing: drawing a three-dimensional drawing of the structural crack reinforcement piece according to the position of the crack;
s3: SLA printing and fitting: storing the drawn three-dimensional drawing in an STL format, and guiding the drawing into an SLA photocuring nonmetal 3D printer;
s4: and (3) checking, installing and optimizing the three-dimensional model: checking and packaging after printing, and adjusting the size of the three-dimensional drawing according to the checking and packaging condition; repeatedly printing, checking and installing until the size is completely proper, and storing the drawing;
s5: SLM manufacturing machine parts: after the three-dimensional drawing of the reinforcement is determined, storing the three-dimensional drawing in an STL format, and guiding the three-dimensional drawing to SLM laser selective melting equipment for preparing the reinforcement;
s6: and (3) heat treatment: carrying out heat treatment on the prepared reinforcement;
the main process parameters of the part inspection and printing in the step S3 are as follows:
laser power: 500 mW;
focusing the light spot: 0.15 mm;
moving speed of the light spot: 5-10 m/S;
single-layer printing thickness: 0.1 mm.
2. The method for rapidly manufacturing the aircraft structural crack reinforcing member according to the claim 1, wherein the method comprises the following steps: the error of the moving speed of the light spot is 1/6-1/8.
3. The method for rapidly manufacturing the aircraft structural crack reinforcing member according to the claim 1, wherein the method comprises the following steps: the specific process parameters of the reinforcing part in the step S5 are as follows:
laser power: 180W;
the diameter of the light spot: 70 μm;
single-layer powder laying thickness: 50 μm;
scanning speed: 1100-1300 mm/s.
4. The method for rapidly manufacturing the aircraft structural crack reinforcing member according to the claim 1, wherein the method comprises the following steps: the heat treatment of the step S6 is a titanium alloy heat treatment process with the process parameter of 850 ℃/2 h.
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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103860293A (en) * 2014-03-07 2014-06-18 北京大学第三医院 Individualized reversal design and manufacturing method for full knee joint replacing prosthesis
CN105377534A (en) * 2013-07-09 2016-03-02 西门子公司 Adaptation method and production method for components produced by SLM
CN105455925A (en) * 2016-01-11 2016-04-06 佛山市安齿生物科技有限公司 Method for preparing bone repair implant on basis of selective laser melting technology
CN105880467A (en) * 2016-06-01 2016-08-24 洛阳双瑞精铸钛业有限公司 Method for producing high-accuracy PS powder model precision castings
CN106623924A (en) * 2016-12-07 2017-05-10 中北大学 Method for forming functionally graded material on basis of selection laser melted powder metallurgy
CA2941842A1 (en) * 2015-12-01 2017-06-01 The Boeing Company Multi-planar fiber matrix tool-less preform for resin infusion
CN109604602A (en) * 2019-01-31 2019-04-12 攀枝花三帝科技有限公司 A kind of production method of 3D printing hearing aid shell

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105377534A (en) * 2013-07-09 2016-03-02 西门子公司 Adaptation method and production method for components produced by SLM
CN103860293A (en) * 2014-03-07 2014-06-18 北京大学第三医院 Individualized reversal design and manufacturing method for full knee joint replacing prosthesis
CA2941842A1 (en) * 2015-12-01 2017-06-01 The Boeing Company Multi-planar fiber matrix tool-less preform for resin infusion
CN105455925A (en) * 2016-01-11 2016-04-06 佛山市安齿生物科技有限公司 Method for preparing bone repair implant on basis of selective laser melting technology
CN105880467A (en) * 2016-06-01 2016-08-24 洛阳双瑞精铸钛业有限公司 Method for producing high-accuracy PS powder model precision castings
CN106623924A (en) * 2016-12-07 2017-05-10 中北大学 Method for forming functionally graded material on basis of selection laser melted powder metallurgy
CN109604602A (en) * 2019-01-31 2019-04-12 攀枝花三帝科技有限公司 A kind of production method of 3D printing hearing aid shell

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