CN109454352B - Cambered surface grid structure and preparation method thereof - Google Patents
Cambered surface grid structure and preparation method thereof Download PDFInfo
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- CN109454352B CN109454352B CN201811459868.2A CN201811459868A CN109454352B CN 109454352 B CN109454352 B CN 109454352B CN 201811459868 A CN201811459868 A CN 201811459868A CN 109454352 B CN109454352 B CN 109454352B
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- 238000002360 preparation method Methods 0.000 title claims abstract description 18
- 238000003466 welding Methods 0.000 claims abstract description 81
- 238000000034 method Methods 0.000 claims abstract description 27
- 230000008569 process Effects 0.000 claims abstract description 18
- 238000004519 manufacturing process Methods 0.000 claims abstract description 14
- 210000000988 bone and bone Anatomy 0.000 claims description 30
- 238000013461 design Methods 0.000 claims description 12
- 238000007514 turning Methods 0.000 claims description 3
- 238000010276 construction Methods 0.000 abstract description 3
- 230000035515 penetration Effects 0.000 abstract description 3
- 229910001069 Ti alloy Inorganic materials 0.000 description 11
- 238000005516 engineering process Methods 0.000 description 4
- 238000005520 cutting process Methods 0.000 description 3
- 238000009792 diffusion process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 238000001035 drying Methods 0.000 description 2
- 238000003698 laser cutting Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 239000010953 base metal Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000005484 gravity 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
- 238000005554 pickling Methods 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005549 size reduction Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
- 238000005406 washing Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K31/00—Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups
- B23K31/02—Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups relating to soldering or welding
- B23K31/022—Making profiled bars with soldered or welded seams
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/20—Bonding
- B23K26/21—Bonding by welding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K33/00—Specially-profiled edge portions of workpieces for making soldering or welding connections; Filling the seams formed thereby
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Plasma & Fusion (AREA)
- Laser Beam Processing (AREA)
Abstract
The invention provides a cambered surface grid structure and a preparation method thereof, wherein a joint form that blades are inserted into grooves on a rudder framework and a rudder frame is adopted, a process measure that a welding seam is welded for half of the length in a vertical upward welding station, then the welding seam is integrally turned over and then the other half of the length is welded is adopted, the construction problem caused by the penetration of the welding seam through a rudder surface is effectively solved, the operation process is greatly simplified, and the manufacturing quality and the manufacturing efficiency of the grid rudder surface are improved.
Description
Technical Field
The invention relates to the field of manufacturing of specific metal objects, in particular to an arc-surface grid structure and a preparation method thereof.
Background
Successful recovery of the falcon rocket by Space X in the united states indicates that it is feasible to recycle the rocket launch system, requiring the use of grid rudder surfaces during recovery. Space X adopts the control surface of aluminum alloy + coating earlier stage, and the feasibility and the reliability of rocket are retrieved in order to follow higher height in the later stage, have changed into titanium alloy grid structure, and this scheme is heavier than aluminium system structure, does not need the coating, and the flight controllability is better, can need not to maintain direct used repeatedly moreover, adopts the casting mode of working at present. Analysis shows that the melting point of pure titanium is as high as 1678 ℃, the wall thickness of a casting grid structure is recommended to be not less than 8mm, titanium alloy also belongs to a difficult-to-machine material in the aspect of machinability, and the grid structure also limits the realization of a machining process, so that the overall manufacturing cost is high, and a grid control surface can be the most expensive single component on a falcon 9 rocket body.
The specific research of recycling rocket carrying systems does not exist in China, grid structures applied to other industries are mainly manufactured by adopting superplastic forming and diffusion connection technologies, Chinese patents ZL201110203313.3 (publication No. CN102248383B, publication No. 2013.4.10), ZL201410332012.4 (publication No. CN104174751B, publication No. 2016.8.24) and ZL201610740254.6 (publication No. CN106363375B, publication No. 2018.7.13) and the like all provide specific solutions, titanium alloy thin plates can be used for manufacturing closed cavities in a relatively regular form, and finally, a titanium alloy grid structure with good quality can be manufactured. However, superplastic forming and diffusion bonding solutions also have some inherent problems: firstly, the technology is inevitable, such as low material utilization rate, size reduction caused by over-speed forming, incomplete welding of diffusion connection, damage to materials caused by thermal cycle above 900 ℃ and the like; secondly, the technical process is complicated, the threshold is higher, and the adaptability and the economical efficiency of the grid structure are obviously influenced for the inconsistent thickness specifications of the blades, the non-uniform included angles between the blades and the frame and the larger breadth size.
The titanium alloy welded structural part can generally lead the design to be lighter, the laser weldability of the titanium alloy is good, and the joint performance can generally reach the strength of the base metal. Chinese patent CN107717224A (published Japanese 2018.2.23) discloses a processing method of a titanium alloy hollow lightweight airfoil, and provides a laser welding method aiming at a large-size titanium alloy skin skeleton closed structure with a plane structure, wherein an internal core lattice is similar to a grid structure, but adjacent rib plates (equivalent to grid blades) are connected indirectly by laser welding with connecting ribs respectively, the frame is also formed by combining an integral frame and a split frame, the process is complex, the welding deformation is large, the integral thermal correction is required, and the cost is high.
Aiming at the demand of the reusable carrier rocket for the control surface, the early aluminum alloy grid structure of Space X is referenced domestically, the conventional grid is used as a basic pattern, the titanium alloy rudder bone structure is added on the basis of the plane single-frame grid, and the rudder bone penetrates through the whole grid. The overall upper and lower contour surfaces of the control surface are cylindrical. The thickness of the rudder bone structure is thicker than that of the rudder frame, the thickness of the rudder bone structure adopts a gradient structure design, and the cambered surface titanium alloy grid structure rudder surface is provided. The cylindrical surface of the control surface on which the upper cylindrical contour surface and the lower cylindrical contour surface are integrally arranged is coaxial with the outer surface of the carrying storage box.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an arc-surface grid structure and a preparation method thereof.
The cambered surface grid structure provided by the invention comprises a rudder bone, a rudder frame and blades; the rudder bone and the blades are arranged inside the rudder frame; the rudder bone is connected with the rudder frame;
-the blades are connected to the rudder bone; and/or
The blade is connected to the rudder frame.
Preferably:
-a groove of suitable size is provided where the rudder bone connects with the blade; and/or
A groove of suitable size is provided at the connection of the rudder frame and the blade;
wherein, the proper size refers to the size of the groove which can be matched with the end part of the blade.
The preparation method of the cambered surface grid structure provided by the invention comprises the following steps:
a joint design step: taking a rudder bone and a rudder frame with grooves with proper sizes as a joint design scheme; the proper size is the size of a groove which can be matched with the end part of the blade, and the proper size groove is respectively arranged at the joint of the rudder frame and the blade and the joint of the rudder frame and the blade;
a component preparation step: manufacturing a rudder bone, a rudder frame and a blade according to a joint design scheme;
a pretreatment step: assembling the rudder framework, the rudder frame and the blades in place through an auxiliary tool;
a welding step: and (4) welding the rudder bone, the rudder frame and the blades in a combined manner to complete the preparation.
Preferably, the preparation method of the cambered surface grid structure provided by the invention further comprises the following steps:
laser spot welding: before the welding step, all welds are fixed using laser spot welding.
Preferably, the process parameters of the laser spot welding step are as follows:
laser power: 500W-1000W;
welding speed: 0.5m/min-2 m/min.
Preferably, in the welding step, the first part of the butt-welding seam is welded by using a laser welding method; and then, integrally turning over the cambered surface grid structure, and welding the second part of the butt weld by adopting a laser welding method.
Preferably, the welding is performed using an upward vertical welding station.
Preferably, the laser welding process parameters are as follows:
laser power: 500W-5 kW;
welding speed: 0.5m/min-5 m/min.
Compared with the prior art, the invention has the following beneficial effects:
1. the cambered surface grating structure provided by the invention has the advantages of simple structure, good reliability and convenience in preparation;
2. according to the invention, by adopting a joint form that the blades are inserted into the rudder bone and the grooves on the rudder frame, the relative position positioning of the blades and the rudder bone rudder frame and the guiding of the crossed blades can be efficiently and rapidly realized; the assembly process of a large number of rudder bones, rudder frames and blade structures can be greatly simplified, and the assembly difficulty and workload are reduced; the size manufacturing precision of the product can be improved, and particularly the relation between the position and the included angle among the rudder bone, the rudder frame and the blade. Meanwhile, the center of gravity position deviation of the control surface can be reduced, and the control performance of the control surface during flying is improved;
3. by adopting the process measure that the welding station is vertically upwards welded, half length of the welding line is welded firstly, and then the whole body is turned over and then the other half length is welded, the invention can effectively solve the construction problem caused by the penetration of the welding line through the control surface and simplify the structural design of the tool. Meanwhile, repeated turnover welding can effectively improve the symmetry of welding heat input and reduce the welding deformation of the overall structure of the control surface.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of a preferred embodiment of a cambered surface grating structure provided by the present invention;
fig. 2 is a schematic view of laser welding in a preferred embodiment of the preparation method of the cambered grid structure provided by the invention.
The figures show that:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The cambered surface grid structure provided by the invention comprises a rudder framework 1, a rudder frame 2 and blades 3; the rudder bone 1 and the blades 3 are arranged inside the rudder frame 2; the rudder framework 1 is connected with the rudder frame 2;
the blades 3 are connected to the rudder bone 1; and/or
The blade 3 is connected to the rudder frame 2.
Preferably:
the rudder bone 1 is provided with a groove of suitable dimensions in connection with the blade 3; and/or
The connection of the rudder frame 2 and the blade 3 is provided with a groove of suitable size;
wherein, the proper size refers to the size of the groove which can be matched with the end part of the blade 3.
The preparation method of the cambered surface grid structure provided by the invention comprises the following steps:
a joint design step: the blade 3 is provided with a binding surface with the rudder bone 1 and the rudder frame 2, and is also provided with a butt weld joint, grooves with certain depth and length are formed in the rudder bone 1 and the rudder frame 2 at the binding surface, so that the blade 3 is inserted into the grooves in a joint form, and the rudder bone 1 and the rudder frame 2 with the grooves with proper sizes are used as a joint design scheme; the proper size is the size of a groove which can be matched with the end part of the blade 3, and the proper size groove is respectively arranged at the joint of the rudder frame 1 and the blade 3 and the joint of the rudder frame 2 and the blade 3;
a component preparation step: manufacturing a rudder bone 1, a rudder frame 2 and blades 3 according to a joint design scheme;
a pretreatment step: pickling, drying and marking the rudder bone 1, the rudder frame 2 and the blades 3, and then assembling the rudder bone 1, the rudder frame 2 and the blades 3 in place through an auxiliary tool;
a welding step: and (3) welding the rudder frame 1, the rudder frame 2 and the blades 3 in a combined manner to finish the preparation.
Specifically, the preparation method of the cambered surface grid structure provided by the invention further comprises the following steps:
laser spot welding: before the welding step, all welds are fixed using laser spot welding.
More specifically, the process parameters of the laser spot welding step are as follows:
laser power: 500W-1000W;
welding speed: 0.5m/min-2 m/min.
In the welding step, a first part of a butt welding seam is welded by adopting a laser welding method; and then, integrally turning over the cambered surface grid structure, and welding the second part of the butt weld by adopting a laser welding method. And welding is carried out by adopting an upward vertical welding station.
The laser welding process parameters are as follows:
laser power: 500W-5 kW;
welding speed: 0.5m/min-5 m/min.
Furthermore, the invention adopts the technical measures that the blade is inserted into the joint of the rudder rib and the groove on the rudder frame, the welding station is vertically upwards adopted, half length of the welding line is welded firstly, then the whole body is turned over and then the other half length is welded, the construction problem caused by the penetration of the welding line on the rudder surface is effectively solved, the operation process is greatly simplified, and the manufacturing quality and efficiency of the grille rudder surface are improved. Manufacturing a rudder frame 2 and blades 3 by adopting a wire-cutting titanium alloy plate; the rudder frame 1 is manufactured by machining, grooves are manufactured on the rudder frame 1 and the rudder frame 2, the binding surface of the bottom of each groove and the corresponding blade is a cylindrical surface, and the length of each welding point is 10 mm.
Further, preferred examples of the present invention are as follows:
according to dynamic calculation or service stress conditions of the control surface, the rudder rib 1 is designed in a gradient mode of reducing the thickness in a stepped mode, the maximum thickness is 15mm, the thickness of part of blades is 2mm, the thickness of part of blades is 4mm, the thickness of a frame is 4mm, the width of the blade 3 and the width of the control frame 2 are about 110mm, the control surface is guaranteed to be cylindrical integrally, and the radius of the cylindrical shape is 1900 mm. The blades 3 and the blades 3 adopt the mutually bayonet assembling position relationship, and the bayonet width is 2mm or 4mm, as shown in figure 1.
The blade 3 is inserted into the grooves on the rudder frame 1 and the rudder frame 2, as shown in fig. 1.
The manufacturing method of the grating comprises the following steps:
(1) preparing components, cutting the structures of the blade 3 and the rudder frame 2 by adopting a laser cutting technology, wherein the main process parameters of the laser cutting are as follows: the gas pressure is 0.1-10bar, the laser power is 1kW-10kW, and the cutting speed is 1m/min-5 m/min.
(2) The rudder bone 1 is machined.
(3) And (3) carrying out acid washing, drying and marking on the blade 3 and the rudder frame 2.
(4) Through auxiliary fixtures, the rudder framework 1, the rudder frame 2 and the blades 3 are installed in place.
(5) And 2 welding spots are spot-welded on each welding line by adopting a laser welding technology. The main process parameters of laser spot welding are as follows: the laser power is 500W-1500W, and the welding speed is 0.5m/min-2 m/min.
(6) Adopt laser welding process and weld the station in the vertical direction, select between blade 3 and blade 3, blade 3 and rudder frame 2, blade 3 and rudder bone 1, rudder frame 2 and rudder frame 2, rudder frame 2 and rudder bone 1's butt weld, weld the first half of this welding seam, the main technological parameter of laser welding is: the laser power is 500W-5kW, and the welding speed is 0.5m/min-5 m/min.
(7) The control surface is integrally turned over, the remaining half part of the welding line is welded by adopting a laser welding process and a vertical upward welding station, and the main process parameters of the laser welding are as follows: the laser power is 500W-5kW, and the welding speed is 0.5m/min-5 m/min.
(8) And (5) circularly performing the step (6) and the step (7).
(9) And (5) finishing welding.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (5)
1. The preparation method of the cambered surface grid structure is characterized by comprising the following steps of:
a joint design step: taking a rudder bone (1) with a groove with a proper size and a rudder frame (2) as a joint design scheme; the proper size refers to the size of a groove which can be matched with the end part of the blade (3), and the proper size groove is respectively arranged at the joint of the rudder frame (1) and the blade (3) and the joint of the rudder frame (2) and the blade (3);
a component preparation step: manufacturing a rudder framework (1), a rudder frame (2) and blades (3) according to a joint design scheme;
a pretreatment step: assembling a rudder framework (1), a rudder frame (2) and blades (3) in place through an auxiliary tool;
a welding step: the rudder frame (1), the rudder frame (2) and the blades (3) are combined and welded to complete the preparation;
in the welding step, a first part of a butt welding seam is welded by adopting a laser welding method; and then, integrally turning over the cambered surface grid structure, and welding the second part of the butt weld by adopting a laser welding method.
2. The method of manufacturing a cambered grid structure of claim 1, further comprising:
laser spot welding: before the welding step, all welds are fixed using laser spot welding.
3. The method for preparing the arc grid structure according to claim 2, wherein the process parameters of the laser spot welding step are as follows:
laser power: 500W-1000W;
welding speed: 0.5m/min-2 m/min.
4. The method of manufacturing a cambered grid structure of claim 1, wherein the welding is performed using an upward vertical welding station.
5. The method for preparing the arc grid structure according to claim 4, wherein the laser welding process parameters are as follows:
laser power: 500W-5 kW;
welding speed: 0.5m/min-5 m/min.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811459868.2A CN109454352B (en) | 2018-11-30 | 2018-11-30 | Cambered surface grid structure and preparation method thereof |
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| CN201811459868.2A CN109454352B (en) | 2018-11-30 | 2018-11-30 | Cambered surface grid structure and preparation method thereof |
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| CN109454352B true CN109454352B (en) | 2021-03-02 |
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Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0829424B1 (en) * | 1995-05-11 | 2003-04-09 | Vympel State Machine Building Design Bureau (Gosmkb "Vympel") | Rocket with lattice control surfaces |
| US7243879B2 (en) * | 2001-12-06 | 2007-07-17 | Kazak Composites, Incorporated | Lattice fin for missiles or other fluid-born bodies and method for producing same |
| US7829829B2 (en) * | 2007-06-27 | 2010-11-09 | Kazak Composites, Incorporated | Grid fin control system for a fluid-borne object |
| CN106197172B (en) * | 2016-09-08 | 2018-03-09 | 湖北航天技术研究院总体设计所 | A kind of locking certainly for positioning carrying integration folds grid rudder |
| CN107717224B (en) * | 2017-09-26 | 2020-04-07 | 北京普惠三航科技有限公司 | Processing method of titanium alloy hollow lightweight airfoil |
| CN108216574A (en) * | 2017-12-21 | 2018-06-29 | 北京有色金属研究总院 | A kind of gradient-structure lattice fin |
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