CN113070577A - Laser shock strengthening device and method for welding seam part of aerospace propellant storage tank - Google Patents
Laser shock strengthening device and method for welding seam part of aerospace propellant storage tank Download PDFInfo
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- CN113070577A CN113070577A CN202110378402.5A CN202110378402A CN113070577A CN 113070577 A CN113070577 A CN 113070577A CN 202110378402 A CN202110378402 A CN 202110378402A CN 113070577 A CN113070577 A CN 113070577A
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- focusing head
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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
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/352—Working by laser beam, e.g. welding, cutting or boring for surface treatment
- B23K26/356—Working by laser beam, e.g. welding, cutting or boring for surface treatment by shock processing
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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
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/12—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
- B23K20/122—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding using a non-consumable tool, e.g. friction stir welding
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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
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/20—Bonding
- B23K26/21—Bonding by welding
- B23K26/24—Seam welding
Abstract
The invention provides a device and a method for strengthening the laser shock of a welding seam part of a space propellant storage tank, comprising a storage tank moving component and a laser shock strengthening component; the storage tank moving assembly controls the aerospace propellant storage tank to rotate along the circumferential direction; a laser focusing head is arranged on a laser focusing head moving structure of the laser shock strengthening assembly, and the laser focusing head is controlled to move along a fixed path; the laser propagation light path structure propagates parallel laser beams emitted by the laser to the laser focusing head; and the laser beam focused by the laser focusing head acts on the welding area where the friction stir welding long weld and the fusion welding girth weld of the aerospace propellant storage tank are located to perform impact strengthening. According to the invention, according to the characteristics of friction stir welding and fusion welding heat input, different sizes of impact regions are selected for different welding seams to carry out laser impact strengthening, the internal dislocation density of the material in the welding seam softening region is increased, the tensile property and reliability of a joint are improved, a participating compressive stress field is generated in the welding seam region, and the service life of the whole aerospace propellant storage tank is prolonged.
Description
Technical Field
The invention relates to the technical field of laser shock strengthening of weld surfaces, in particular to a device and a method for laser shock strengthening of weld positions of a spacecraft propellant storage box.
Background
The propellant storage tank is widely applied in the field of aerospace manufacturing, the main structure of the propellant storage tank is an aluminum alloy cylindrical tank body, long and straight weld joints are usually welded by friction stir welding, and a plurality of sections of cylindrical tank bodies are spliced and then connected into a whole by fusion welding and girth welding. In the aluminum alloy welding process, crystal grains can be coarsened in areas with certain widths on two sides of a welding line, and simultaneously, a strengthening phase dispersed and distributed in a base material can be dissolved and coarsened to form a softening area. The softening zone is the weakest region among the aluminum alloy welded joint usually, and hardness is low and produce concentrated strain easily, seriously reduces the whole mechanical properties of joint, for guaranteeing that the storage tank has sufficient intensity, needs increase the storage tank wall thickness, leads to storage tank lightweight design to be difficult to realize, has increased transmission and flight cost. The recycling of propellant tanks in the aeronautical field has become a trend in all countries, a single propellant tank may need to perform several missions of the propellant, thus placing higher demands on the fatigue performance of the propellant tank. However, local expansion of materials occurs in a welding area during welding, the materials are rigidly restrained during cooling, a large residual tensile stress usually exists in the welding seam area after welding, fatigue cracks are easy to germinate under the action of fatigue loads during service, fatigue damage is generated, and the reliability and safety performance of the propellant storage tank are seriously reduced. Therefore, the propellant storage tank welding seam is strengthened through a special strengthening method, the mechanical property of a welding seam softening area is improved, and the stress distribution state of the welding seam area is improved, so that the integral reliability and service life of the propellant storage tank are improved, and the propellant storage tank welding seam strengthening method has important significance for the development of the future aerospace field.
The existing common weld reinforcement method for large-scale components mainly comprises ultrasonic impact reinforcement, shot peening reinforcement and laser impact reinforcement. Ultrasonic impact strengthening is that ultrasonic wave drives an impact head to rapidly impact the surface of a workpiece at a very high frequency and generate plastic deformation, so that near-surface grains can be refined and surface residual compressive stress can be obtained, but the surface roughness of a storage tank can be greatly increased, and other surface defects can be induced. The shot blasting technology is characterized in that high-pressure gas drives hard shot to rapidly impact the surface of a weld joint to cause plastic deformation of the surface of a material, and also can effectively refine near-surface grains in a strengthening area to generate a field participating in compressive stress, and the shot blasting technology is widely applied to the field of strengthening of fusion welding and friction stir welding joints. However, as the shot diameter adopted by the shot blasting technology is small, an independent shot blasting working room is usually required to be established, a shot blasting filtering system is arranged to prevent air pollution, and the working environment is severe; meanwhile, shot peening also increases the surface roughness of the reinforcement, affecting the fatigue properties of the component.
The laser shock peening technology generates plasma explosion on the surface of a part to be strengthened through high-power-density laser beams, the generated explosion shock waves are transmitted to the interior of a material, and the material is extruded to generate plastic deformation. The existing research shows that the laser shock peening can effectively refine grains on the shock surface, improve the hardness and the tensile property of the material, form a larger residual compressive stress field in a certain depth of the material and greatly improve the fatigue property of the material. The laser shock peening process has good controllability, is more stable and deeper in action compared with ultrasonic shock peening and shot peening strengthening processes, has better working environment and is green and environment-friendly. Most of the existing laser shock peening equipment is only suitable for small components or flat components with simpler structures, and for some workpieces with various welding seam forms and complicated shock paths, an expensive flexible light guide arm is generally required to be adopted, and the equipment is difficult to be applied to strengthening components with larger sizes. The aerospace propellant storage tanks have various sizes and long friction stir welding seams and fusion welding girth welding seams, and because the welding methods used by the two types of welding seams are completely different in principle, the difference between the softening zone position and the stress distribution state of the welding seams is large, and a scientific and reasonable laser shock strengthening device and a matched strengthening method are lacked for effectively strengthening the welding area of the storage tanks.
Therefore, the problem to be solved by those skilled in the art is how to provide a device and a method for effectively strengthening the welding area of friction stir welding long weld and fusion welding girth weld of a spacecraft propellant tank.
Disclosure of Invention
In view of the above, the invention provides a device and a method for strengthening the weld joint of a spacecraft propellant storage tank by laser shock, wherein the light emitting height is adjusted by a laser focusing head moving structure and a laser propagation light path structure so as to strengthen the storage tanks with different diameters, the long weld joint of the friction stir welding of the storage tank can be strengthened by laser shock by adjusting the light emitting horizontal position, the storage tank is driven to rotate by a storage tank moving component, the weld joint of the fusion welding ring of the storage tank can be strengthened by laser shock, and according to the input characteristics of the friction stir welding and the fusion welding heat, impact areas with different sizes are selected for strengthening by laser shock, the dislocation density in the material of the weld joint softening area is increased, crystal grains are refined, the tensile property and the reliability of the joint are improved, a participating pressure stress field is generated in the weld joint area, and the.
In order to achieve the purpose, the invention adopts the following technical scheme:
a laser shock strengthening device for a welding seam part of a space propellant storage tank comprises: a storage tank moving component and a laser shock strengthening component;
the space propellant tank is transversely placed on the tank moving assembly, and the tank moving assembly controls the space propellant tank to rotate along the circumferential direction;
the laser shock peening component comprises a laser, a laser focusing head moving structure and a laser propagation light path structure; the laser focusing head moving structure is provided with the laser focusing head and controls the laser focusing head to move along a fixed path; the laser propagation light path structure is erected on the laser focusing head moving structure and is used for propagating the parallel laser beams emitted by the laser to the laser focusing head; and the laser beam focused by the laser focusing head acts on the welding areas of the friction stir welding long weld and the fusion welding girth weld of the aerospace propellant storage tank to perform impact strengthening.
Preferably, the laser focusing head moving structure comprises a horizontal lead screw; the horizontal lead screw is erected at the top of the aerospace propellant storage box through a vertical supporting structure, and a horizontal movement stepping motor is assembled on the horizontal lead screw to drive the laser focusing head to move along the horizontal direction.
Preferably, the vertical support structure comprises a vertical lead screw; and the vertical lead screw is provided with a vertical motion stepping motor, and the horizontal lead screw is connected with the vertical motion stepping motor and drives the horizontal lead screw to move along the vertical direction.
Preferably, the laser propagation light path structure comprises a light guide hollow upright post, a first reflecting mirror and a second reflecting mirror;
the light guide hollow upright post is covered outside the vertical supporting structure and is provided with a light inlet window;
a first reflecting mirror and a second reflecting mirror are oppositely arranged at different height positions of the vertical supporting structure; the height of the first reflecting mirror is consistent with that of a laser emitting end of the laser, and the height of the second reflecting mirror is consistent with that of a laser receiving end of the laser focusing head.
Parallel laser beams emitted by the laser are incident to the inner side of the light guide hollow upright post through the light inlet window and are incident to the laser focusing head through the first reflecting mirror and the second reflecting mirror in sequence along the laser propagation direction.
Preferably, the vertical support structure comprises a vertical lead screw; the vertical lead screw is provided with a vertical motion stepping motor, and the horizontal lead screw is connected with the vertical motion stepping motor and drives the horizontal lead screw to move along the vertical direction;
and the second reflecting mirror is arranged on the vertical motion stepping motor and moves synchronously with the vertical motion stepping motor.
Preferably, the vertical screw rod is not superposed with the central axis of the light guide hollow upright column, and has certain offset, so that the propagation of laser is not influenced.
Preferably, a third reflecting mirror is installed in the laser focusing head and used for changing the propagation path of the laser beam, reflecting the laser from horizontal propagation to vertical propagation, and converging and irradiating the laser on the welding area where the friction stir welding long weld and the fusion welding ring weld on the surface of the aerospace propellant storage tank are located by the focusing lens.
Preferably, the horizontal height of a second reflecting mirror inside the light guide hollow upright post is consistent with that of a third reflecting mirror in the laser focusing head; the horizontal movement speed of the laser focusing head is 1-25 mm/s.
Preferably, the tank moving assembly comprises a plurality of roller load-bearing supports for supporting the aerospace propellant tank; the roller bearing support is provided with a roller driving motor and a roller, the roller is attached to the aerospace propellant storage tank, and the movement speed is controlled by the roller driving motor; and the plurality of rollers simultaneously move to drive the aerospace propellant storage tank to rotate along the circumferential direction of the aerospace propellant storage tank.
Preferably, the device also comprises a working platform and a moving platform; the mobile platform is movably connected with the working platform; the storage box moving assembly is fixed on the moving platform. The storage box moving assembly can move on the working platform, and the storage box is convenient to hoist, transport and adjust in position.
Preferably, the working platform is a horizontal base of the whole device, namely, the laser focusing head moving structure and the laser propagation light path structure can be both arranged on the working platform.
The invention also provides a laser shock strengthening method for the welding seam part of the aerospace propellant storage tank, which comprises the following steps:
firstly, sequentially arranging an absorption layer and a restraint layer on the surfaces of a welding area, namely a friction stir welding long weld joint and a fusion welding ring weld joint, of a spacecraft propellant storage tank to be reinforced, and measuring laser shock reinforcement ranges on the welding area and two sides to enable a laser focusing head to be aligned to the reinforcement range;
driving a laser focusing head to the initial position of the long friction stir welding seam through a laser focusing head moving structure, emitting laser spots with set sizes by the laser focusing head to irradiate the surface of the aerospace propellant storage tank for laser shock strengthening, driving the laser focusing head to horizontally move at a constant speed to complete single laser shock strengthening of one horizontal path at the same time, driving the aerospace propellant storage tank to rotate by a certain angle through a storage tank moving assembly to continue laser shock strengthening of the next horizontal path, and repeating the steps until the laser shock strengthening area of the long friction stir welding seam is completely strengthened;
driving a laser focusing head to the edge starting position of a laser shock strengthening area of a fusion welding ring welding seam through a laser focusing head moving structure, emitting laser spots with set sizes by the laser focusing head to irradiate the surface of a space propellant storage tank to carry out laser shock strengthening, driving the space propellant storage tank to continuously rotate to a set angle at a certain speed by a storage tank moving assembly to complete single laser shock strengthening of one circumferential path, driving the laser focusing head to horizontally move to a set length at a constant speed by the laser focusing head moving structure to continue laser shock strengthening of the next circumferential path, and repeating the steps until the laser shock strengthening area of the fusion welding ring welding seam is completely strengthened;
and fourthly, removing the absorption layer and the restraint layer after the long welding seam of the friction stir welding and the fusion welding girth welding seam are strengthened, and then completing the comprehensive strengthening of the welding seam of the aerospace propellant storage tank.
Preferably, the step one is preceded by:
the height of the laser focusing head is adjusted through the laser focusing head moving structure, so that laser can obtain the required spot size after being converged at the top of the aerospace propellant storage box.
Preferably, the shape of the light spot adopted in the second step and the third step is circular, and the diameter of the laser light spot obtained by adjusting the height of the laser focusing head is 2-8 mm.
Preferably, the absorption layer in the first step is 15-75 μm thick black paint or aluminum foil for protecting the surface of the material and improving the laser absorption rate; the laser shock strengthening area is the welding seam and two sides of the welding seam, because the heat input of the electric arc welding is higher compared with the friction stir welding, and the heat affected zone of the welding seam is wider, the width of the softening area of the fusion welding girth welding seam is larger, the width of the shock area of the fusion welding girth welding seam is 6-10 times of the width of the welding seam, and the width of the shock area of the long welding seam of the friction stir welding is 3-5 times of the width of the welding seam.
Preferably, the restraint layer in the first step is a uniform-speed flowing water layer with the thickness of 1-2 mm and is used for restraining shock waves generated by plasma explosion; the laser single pulse energy is 5-80J, the light emitting frequency is 3 Hz-15 Hz, the light spot overlapping rate is 30% -70%, and the laser shock strengthening times are 1-5.
Through the technical scheme, compared with the prior art, the invention has the beneficial effects that:
1. the invention has wide applicability, can carry out laser shock strengthening on the space propellant storage tanks with different lengths and different diameters by the motion matching of the horizontal lead screw, the focusing laser head and the roller bearing bracket in the actual production, and has wide process application range;
2. the light guide hollow upright post adopted in the invention has simple structure and easy maintenance of the light path, and common optical elements are adopted in the whole light path, so that the laser shock strengthening can be carried out on the long welding line of the friction stir welding and the fusion welding girth welding line without adopting a flexible light guide arm, thereby saving the production cost;
3. the invention has simple light spot movement mode, can complete the strengthening of different impact areas only by rotating the storage box and matching with the horizontal movement of the laser focusing head, is easy to realize automatic control and improves the production efficiency;
4. the invention adopts different impact strengthening strategies aiming at two types of welding seams on the aerospace propellant storage tank, not only can obtain a larger residual compressive stress field in a welding seam area, but also can effectively improve the comprehensive mechanical property of an aluminum alloy welding joint softening area, thereby greatly improving the safety and the service life of the aerospace propellant storage tank.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts;
FIG. 1 is a schematic structural diagram of a laser shock peening apparatus for a spacecraft propellant storage tank according to an embodiment of the present invention;
fig. 2 is a schematic view illustrating an internal structure of a light guide hollow column and propagation of a laser path according to an embodiment of the present invention;
FIG. 3 is a schematic view of an internal structure of a non-light-conducting hollow column according to an embodiment of the present invention;
FIG. 4 is a side view of a tank moving assembly carrying a tank according to an embodiment of the present invention;
FIG. 5 is a schematic view of the arrangement of a laser shock peening absorption layer and a constraining layer provided by an embodiment of the present invention;
FIG. 6 is a schematic diagram of a laser spot movement path when a friction stir welding long weld is strengthened according to an embodiment of the present invention;
fig. 7 is a schematic diagram of a movement path of a laser spot when a fusion welding girth weld is strengthened according to an embodiment of the present invention.
In the figure: 1-a laser; 2-parallel laser beam; 3-light guide hollow upright post; 4-horizontal lead screw; 5-horizontally moving the stepping motor; 6-laser focusing head; 7-non-light-conducting hollow upright post; 8-friction stir welding of long weld joints; 9-fusion welding the circumferential weld; 10-focusing the laser beam; 11-a spacecraft propellant tank; 12-rubber rollers; 13-a roller driving motor; 14-roller load-bearing supports; 15-moving the platform; 16-a working platform; 17-a light entrance window; 18-vertical lead screw; 19-mirror connecting shaft; 20-a vertical motion stepper motor; 21-mirror connecting rod; 22-vertical movement of 45 ° total reflection mirror; 23-horizontal lead screw; 24-a horizontal motion stepper motor; 25-horizontal movement of a 45-degree total reflection mirror; 26-a focusing lens; 27-fixing a 45-degree total reflection mirror; 28-an absorbent layer; 29-a constraining layer; 30-laser spot; 31-friction stir welding a long welding seam laser shock strengthening area; 32-friction stir welding long weld laser shock strengthening light spot movement path; 33-melting the weld seam laser shock strengthening area of the welding ring; and 34-melting the welding seam of the welding ring and strengthening the movement path of the light spot by laser shock.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The first aspect of this embodiment provides a device for strengthening the weld joint of a spacecraft propellant storage tank by laser shock, refer to fig. 1, which is a schematic diagram of the overall structure of the device for strengthening the weld joint of a spacecraft propellant storage tank disclosed in this embodiment. The method comprises the following steps: a storage tank moving component and a laser shock strengthening component;
the space propellant storage tank is transversely placed on the storage tank moving assembly, and the storage tank moving assembly controls the space propellant storage tank to rotate along the circumferential direction;
the laser shock peening component comprises a laser, a laser focusing head moving structure and a laser propagation light path structure; the laser focusing head moving structure is provided with a laser focusing head and controls the laser focusing head to move along a fixed path; the laser propagation light path structure is erected on the laser focusing head moving structure and is used for propagating the parallel laser beams emitted by the laser to the laser focusing head; and the laser beam focused by the laser focusing head acts on the welding area where the friction stir welding long weld and the fusion welding girth weld of the aerospace propellant storage tank are located to perform impact strengthening.
The working principle of the invention is as follows: the laser shock peening is used for generating plastic deformation on the near surface layer of the welding area, the residual tensile stress field after welding is converted into a compressive stress field, the fatigue performance of the welding seam is improved, the dislocation density in the material can be increased, the crystal grains are refined, and the hardness and the tensile property of the welding area, particularly the joint softening area, are greatly improved. The reciprocating of the first removal structure of laser focus among the strengthening device can adjust the first height of laser focus to different storage tank diameters and focus on, and the horizontal migration through the first removal structure of laser focus and the rotation of storage tank cooperate, guarantees that the laser facula can carry out the shock peening to all impact regions according to required facula overlap joint rate.
The laser 1 in this embodiment can generate the parallel laser beam 2 by setting the laser single pulse energy and the light emission frequency.
In one embodiment, the laser focusing head moving structure comprises a horizontal lead screw; the horizontal lead screw is erected at the top of the aerospace propellant storage box through a vertical supporting structure, and a horizontal movement stepping motor is assembled on the horizontal lead screw to drive the laser focusing head to move along the horizontal direction.
The vertical support structure in this embodiment may be a fixed support structure, or may be a height-adjustable support structure.
In one embodiment, the vertical support structure comprises a vertical lead screw; the vertical lead screw is provided with a vertical motion stepping motor, and the horizontal lead screw is connected with the vertical motion stepping motor to drive the horizontal lead screw to move along the vertical direction.
In one embodiment, the laser propagation light path structure comprises a light guide hollow upright post, a first reflecting mirror and a second reflecting mirror; the light guide hollow upright post is covered outside the vertical supporting structure and is provided with a light inlet window; a first reflecting mirror and a second reflecting mirror are oppositely arranged at different height positions of the vertical supporting structure; the height of the first reflecting mirror is consistent with that of the laser emitting end of the laser, and the height of the second reflecting mirror is consistent with that of the laser receiving end of the laser focusing head. Parallel laser beams emitted by the laser are incident to the inner side of the light guide hollow upright post through the light inlet window and are incident to the laser focusing head through the first reflecting mirror and the second reflecting mirror in sequence along the laser propagation direction.
Referring to fig. 2, the schematic diagram of the internal structure of the light guide hollow upright 3 is shown, the vertical support structures are arranged at two ends of the horizontal screw, the light guide hollow upright is covered outside the vertical support structure at one end, the light path propagation path is provided inside the light guide hollow upright, the hollow upright is covered outside the vertical support structure at the other end, and the light path structure is not arranged inside the light guide hollow upright. The light guide hollow stand column is provided with a light inlet window at the bottom of one side, the other side is completely opened, the horizontal lead screw can be freely moved in the vertical direction, and the non-light guide hollow stand column does not have the effect of conducting laser, so that the light inlet window does not need to be opened at the bottom, a reflector does not need to be installed inside the light guide hollow stand column, only one side is completely opened, the inside can adopt the matching mode of a guide rod and a slide block, and the matching mode of a vertical lead screw and a stepping motor can also be adopted. The two ends of the horizontal lead screw are respectively connected with the sliding blocks or the vertical motion stepping motors with the same horizontal height in the two upright posts, and the horizontal lead screw can be guaranteed to freely move in the vertical direction when the vertical motion stepping motors in the light guide hollow upright posts synchronously move. The light guide hollow upright post and the hollow upright post are fixed on two sides of the working platform.
Referring to fig. 2, which shows a schematic diagram of laser path propagation, a first reflecting mirror installed at the bottom of the light guide hollow upright is a fixed 45-degree total reflection mirror, and is used for changing a laser beam propagation path for the first time and reflecting laser from horizontal propagation to vertical propagation. And a second reflector connecting shaft is assembled on the vertical supporting structure, and the second reflector is a vertical 45-degree total reflector and is connected with the reflector connecting shaft through a reflector connecting rod and used for changing a laser beam propagation path for the second time and reflecting the laser from vertical propagation to horizontal propagation. And a third reflecting mirror in the laser focusing head is a full-reflecting mirror which moves horizontally by 45 degrees and is used for changing the propagation path of the laser beam for the third time, reflecting the laser from horizontal propagation to vertical propagation and converging and irradiating the laser on the welding area where the long welding seam of the friction stir welding and the fusion welding girth welding seam on the surface of the space propellant storage tank are located by a focusing lens.
In the present embodiment, the horizontal movement speed of the laser focusing head is 1 to 25 mm/s.
In one embodiment, the vertical support structure comprises a vertical lead screw; a vertical motion stepping motor is assembled on the vertical screw rod, and the horizontal screw rod is connected with the vertical motion stepping motor and drives the horizontal screw rod to move along the vertical direction; and the second reflecting mirror is arranged on the vertical motion stepping motor and moves synchronously with the vertical motion stepping motor. The second reflecting mirror in the embodiment adopts a total reflecting mirror which vertically moves by 45 degrees.
Fig. 2 shows a schematic diagram of the internal structure of the light guide hollow column 3 and the propagation of the laser path, wherein one side of the bottom of the light guide hollow column 3 is provided with a light inlet window 17, and the other side is completely open. The bottom of the light guide hollow upright post 3 is provided with a fixed 45-degree total reflection mirror 27, and a vertical screw 18 arranged in the light guide hollow upright post 3 is not superposed with the central axis of the light guide hollow upright post and has certain offset. The vertical lead screw 18 is provided with a vertical motion stepping motor 20, and a vertical motion 45-degree total reflection mirror 22 is connected with the vertical motion stepping motor 20 through a mirror connecting shaft 19 and a mirror connecting rod 21. The focusing laser head 6 can be driven by a horizontal movement stepping motor 24 to freely move in the horizontal direction, a horizontal movement 45-degree total reflection mirror 25 and a focusing lens 26 are arranged in the focusing laser head 6, the height of the horizontal movement 45-degree total reflection mirror 25 is consistent with that of a vertical movement 45-degree total reflection mirror 22, and a parallel laser beam 2 is reflected twice in the light guide hollow upright post and horizontally enters the focusing laser head 6 to be focused to obtain a focusing laser beam 10.
Fig. 3 shows the internal structure of the non-light-conducting hollow upright post 7, which is only provided with a vertical screw 18 and a vertical movement stepping motor 20 inside, and two ends of a horizontal screw 23 are respectively connected with the vertical movement stepping motor 20 in the light-conducting hollow upright post 3 and the non-light-conducting hollow upright post 7 and can be driven by the vertical movement stepping motor 20 to move freely in the vertical direction.
In one embodiment, the vertical screw rod is not overlapped with the central axis of the light guide hollow upright post, and has certain offset, so that the propagation of laser is not influenced.
In one embodiment, the tank moving assembly comprises a plurality of roller load-bearing supports for supporting the aerospace propellant tank; the roller bearing support is provided with a roller driving motor and a roller, the roller is attached to the aerospace propellant storage tank, and the movement speed is controlled by the roller driving motor; a plurality of gyro wheels simultaneous movement drives space propellant storage tank and rotates along self circumference.
In the embodiment, the roller driving motor is connected with the roller shaft through the coupler inside the bearing support, and the roller shaft is parallel to the central shaft of the aerospace propellant storage box to drive the aerospace propellant storage box to rotate around the central shaft. The rubber roller can be adopted, the surface of the aerospace propellant storage tank is not damaged, and meanwhile, the rotation friction force is provided.
Figure 4 shows a side view of the tank-moving assembly carrying the tank, the tank-moving assembly comprising a moving platform 15, 6 roller load-bearing supports 14. The moving platform 15 can freely move on the working platform 16, the roller bearing supports 14 can adjust relative positions on the moving platform, each roller bearing support 14 is provided with a rubber roller 12 and a roller driving motor 13, the rubber rollers 12 are attached to the aerospace propellant storage tank 11, and the roller driving motors 13 can drive the rubber rollers 12 to move so as to enable the aerospace propellant storage tank 11 to rotate.
In this embodiment, a motor-driven universal wheel and other devices may be installed below the mobile platform 15, so that the mobile platform 15 may freely move and be fixed on the working platform 16.
In one embodiment, the working platform is a horizontal base of the whole device, namely, both the laser focusing head moving structure and the laser propagation light path structure can be arranged on the working platform.
The invention also provides a laser shock strengthening method for the welding seam part of the aerospace propellant storage tank, wherein an absorption layer 28 and a restraint layer 29 are required to cover the surface of the welding area before laser shock strengthening is carried out, and the arrangement schematic diagram of the absorption layer and the restraint layer is shown in fig. 5. When the focused laser beam 10 irradiates the surface of the workpiece, the laser energy is absorbed by the absorption layer 28 and generates plasma explosion, and the generated shock wave is restrained by the restraint layer 29 and propagates to the interior of the aerospace propellant storage tank 11 to induce plastic deformation, so that a residual compressive stress field is formed.
The specific implementation process and the device working principle of the laser shock peening method for the aerospace propellant storage tank provided by the invention are described in detail with reference to fig. 1-7: in one embodiment, firstly, the long friction stir welding seam is placed at the top through the storage tank moving assembly, the laser focusing head is driven to reach one end of the long welding seam of the welding seam for laser shock strengthening through the movement of the horizontal lead screw, then the laser focusing head is adjusted to reach the position of the fusion welding girth welding seam, the storage tank is driven to rotate through the storage tank moving assembly to strengthen the girth welding seam, and finally a residual compressive stress field is formed in the welding area. In another embodiment, firstly, the long friction stir welding seam is placed at the top through the storage tank moving assembly, the height of the laser focusing head is controlled and adjusted through the matching of the vertical lead screw and the horizontal lead screw, the laser focusing head is driven to reach one end of the long welding seam of the welding seam for laser shock strengthening, then the laser focusing head is adjusted to reach the position of the fusion welding seam of the ring, the storage tank is driven to rotate through the storage tank moving assembly to strengthen the ring welding seam, and finally a residual compressive stress field is formed in the welding area.
The following concrete steps of carrying out laser shock strengthening on the aerospace propellant storage tank through the matching of the movement of the vertical lead screw and the movement of the horizontal lead screw are provided:
(1) adjusting the relative position of 6 roller bearing supports 14 on a storage tank moving assembly on a moving platform 15 according to the diameter of a space propellant storage tank 11 to be processed, starting a vertical motion stepping motor 20 to drive a horizontal lead screw 23 to move, and adjusting the height of a laser focusing head 6 so that a focused laser beam 10 is converged at the top of the storage tank after a laser is started to obtain a required spot size;
(2) the moving platform 15 is started, the moving platform moves horizontally on the working platform 16, the aerospace propellant storage tank 11 is placed on the 6 roller bearing supports 14 after the storage tank is guaranteed not to interfere with the horizontal lead screw 4 during hoisting, and the rubber rollers 12 are attached to the aerospace propellant storage tank 11. Measuring laser shock strengthening ranges 31 and 33 in the welding line area and two sides of a long welding line 8 and a fusion welding ring welding line 9 to be strengthened, arranging an absorption layer 28 with the thickness of 15-75 microns on the surface of the laser shock strengthening ranges, arranging a restraint layer 29 with the thickness of 1-2 mm on the surface of the absorption layer 28, wherein the width of the shock area of the fusion welding ring welding line is 6-10 times of the width of the welding line, and the width of the shock area of the long welding line of the friction stir welding is 3-5 times of the width of the welding line. The storage tank is transported by the moving platform 15 to a position right below the laser focusing head 6. Firstly, reinforcing a friction stir welding long weld joint, starting 6 roller driving motors 13, driving a space propellant storage tank 11 to rotate by the movement of rubber rollers 12, and placing the edge of a friction stir welding long weld joint laser impact area 31 at the top;
(3) referring to FIG. 6, a horizontal path for friction stir welding long weld reinforcement is shown, a laser focusing head 6 is driven to an initial position of a friction stir welding long weld 8 by a horizontal movement stepping motor 5, then, laser single pulse energy is selected to be 5-80J on a laser 1, light emitting frequency is 3 Hz-15 Hz, selected spot overlapping rate is 30% -70%, the laser 1 is started, a parallel laser beam 2 is generated and is emitted into a light guide hollow upright 3, then the parallel laser beam is horizontally emitted below a horizontal screw rod 4 after being reflected twice and enters the laser focusing head 6, a laser spot 30 with the diameter of 2-8 mm is formed after being reflected and focused and is irradiated to the surface of a storage tank for laser shock reinforcement, the movement speed of the horizontal stepping motor 5 is adjusted according to the light emitting frequency and the required spot overlapping rate, so that the laser focusing head moves horizontally at a constant speed of 1-25 mm/s to complete laser shock reinforcement on a straight line, then, the 6 rubber rollers 12 move to drive the aerospace propellant storage tank 11 to rotate for a certain angle to continue to perform laser shock strengthening, and the steps are repeated until the friction stir welding long-weld laser shock strengthening area 31 is completely strengthened, wherein the number of times of shock is 1-5;
(4) referring to FIG. 7, the circumferential path of the fusion weld reinforcement is shown. After all friction stir welding long weld joints on the storage tank are strengthened, the laser 1 is closed, the laser focusing head 6 is driven to the edge of the fusion welding girth weld joint laser shock strengthening area 33 through the horizontal movement stepping motor 5, and the laser 1 is opened. When the circumferential weld laser shock strengthening is carried out, firstly, the laser light spot 30 moves horizontally, then the rubber roller 12 moves to drive the aerospace propellant storage tank 11 to rotate for a certain angle for continuous shock, so that the horizontal moving speed of the laser focusing head needs to be determined according to the required light spot lap joint rate and the light emitting frequency, and the process is repeated until the circumferential weld area is completely strengthened;
(5) and (3) after all the friction stir welding long welding seams 8 and the fusion welding girth welding seams 9 are strengthened, the laser 1 is closed, the absorption layer 28 and the constraint layer 29 are removed, and then the comprehensive strengthening of the welding seams of the space propellant storage tank 11 is completed.
Example (b):
the aerospace propellant storage tank material is 2219 aluminum alloy in this embodiment, and the storage tank diameter is 2m, and total length 6m needs to carry out laser shock peening to the outside 2 friction stir welding long weld joints that width is 20mm of storage tank and 3 fusion welding girth weld joints that width is 15 mm.
The relative position of the 6 roller bearing supports 14 on the moving platform 15 is adjusted to ensure that the aerospace propellant storage tank 11 can be stably placed. The vertical movement stepping motor 20 is started to drive the horizontal lead screw 23 to move, the height distance between the laser focusing head 6 and the moving platform is adjusted to be 2.4m, the moving platform 15 is started to move horizontally on the working platform 16, after the storage tank is guaranteed not to interfere with the horizontal lead screw 4 during hoisting, the aerospace propellant storage tank 11 is placed on the 6 roller bearing supports 14, and the rubber rollers 12 are attached to the aerospace propellant storage tank 11. Spraying an absorbing layer 28 with the thickness of 30 microns on the surfaces of a long friction stir welding seam and a fusion welding girth welding seam which need to be reinforced, measuring laser shock strengthening ranges 31 and 33 in the welding seam area and two sides, wherein the width of the laser shock strengthening area 31 of the long friction stir welding seam is 80mm, the width of the laser shock strengthening area 33 of the fusion welding girth welding seam is 120mm, and conveying the storage tank to the position under a laser focusing head 6 through a moving platform 15.
Firstly, 2 friction stir welding long welding seams 8 are strengthened, 6 roller driving motors 13 are started, rubber rollers 12 move to drive a space propellant storage tank 11 to rotate, and the edge of a friction stir welding long welding seam laser impact area 31 is arranged at the top. Starting the horizontal motion stepping motor 5 to drive the laser focusing head 6 to the initial position of the long welding line 8 of the friction stir welding, and spraying water flow flowing at a constant speed through a water gun to arrange a water layer with the thickness of 1mm at the laser spot irradiation position to serve as a restraint layer. Then selecting laser single pulse energy of 30J on a laser 1, emitting light frequency of 5Hz, and selecting a spot lap ratio of 50%, starting the laser 1, generating parallel laser beams 2, emitting the parallel laser beams into a light guide hollow upright 3, reflecting the parallel laser beams twice below a horizontal screw rod 4, horizontally emitting the laser beams into a laser focusing head 6, forming laser spots 30 with the diameter of 4mm after reflection and focusing, irradiating the laser spots onto the surface of the storage tank for laser shock strengthening, adjusting the movement speed of a horizontal stepping motor 5 according to the light emitting frequency and the required spot lap ratio, enabling the laser focusing head to horizontally move at the speed of 10mm/s to complete laser shock strengthening on a straight line, driving a space propellant storage tank 11 to rotate for a certain angle through the movement of 6 rubber rollers 12 to continue laser shock strengthening, and reciprocating until a long weld joint laser shock strengthening area 31 of friction stir welding is completely strengthened at a constant speed, the path of movement of the spot is shown in figure 6, with 2 impacts per weld. And stopping the laser after one friction stir welding long weld is strengthened, starting 6 roller driving motors 13, driving the space propellant storage tank 11 to rotate by the movement of the rubber rollers 12, placing the edge of the other friction stir welding long weld laser impact area 31 at the top, and repeating the strengthening process.
And after all the friction stir welding long welding lines on the storage tank are strengthened, the laser 1 is closed. The laser focusing head 6 is driven by the horizontal movement stepping motor 5 to the edge of the fusion welding girth weld laser shock strengthening area 33, and the laser 1 is opened. When the laser shock strengthening of the circumferential weld is carried out, firstly, the laser light spot 30 moves horizontally, then the rubber roller 12 moves to drive the aerospace propellant storage tank 11 to rotate for a certain angle to continue to carry out shock, the horizontal moving speed of the laser focusing head is determined to be 10mm/s according to the required light spot lap joint rate and the light emitting frequency, the laser focusing head reciprocates until the complete strengthening of the welding seam area of the fusion welding ring is completed, the movement path of the light spot is shown in figure 7, and each welding seam carries out two times of shock. And stopping the laser 1 after each welding line is impacted, moving the laser focusing head 6 to the edge of the laser impact strengthening area 33 of the next fusion welding ring welding line, and repeating the strengthening process.
And (3) after all the friction stir welding long weld joints 8 and the fusion welding circumferential weld joints 9 are strengthened, the laser 1 is closed, the organic solvent is used for cleaning residual black paint on the surface of the space propellant storage tank 11, and after drying, the comprehensive strengthening of the weld joints of the space propellant storage tank 11 is completed.
The device and the method for strengthening the weld joint of the aerospace propellant storage tank by laser shock are described in detail, specific examples are applied in the device to explain the principle and the implementation mode of the device, and the description of the embodiments is only used for helping to understand the method and the core idea of the device; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. The utility model provides a space propellant storage tank welding seam position laser shock strengthening device which characterized in that includes: a storage tank moving component and a laser shock strengthening component;
the space propellant tank is transversely placed on the tank moving assembly, and the tank moving assembly controls the space propellant tank to rotate along the circumferential direction;
the laser shock peening component comprises a laser, a laser focusing head moving structure and a laser propagation light path structure; the laser focusing head moving structure is provided with the laser focusing head and controls the laser focusing head to move along a fixed path; the laser propagation light path structure is erected on the laser focusing head moving structure and is used for propagating the parallel laser beams emitted by the laser to the laser focusing head; and the laser beam focused by the laser focusing head acts on the welding areas of the friction stir welding long weld and the fusion welding girth weld of the aerospace propellant storage tank to perform impact strengthening.
2. The laser shock peening apparatus for the weld joint of the aerospace propellant storage tank according to claim 1, wherein the laser focusing head moving structure comprises a horizontal lead screw; the horizontal lead screw is erected at the top of the aerospace propellant storage box through a vertical supporting structure, and a horizontal movement stepping motor is assembled on the horizontal lead screw to drive the laser focusing head to move along the horizontal direction.
3. The aerospace propellant tank weld joint laser shock peening apparatus of claim 2, wherein the vertical support structure comprises a vertical lead screw; and the vertical lead screw is provided with a vertical motion stepping motor, and the horizontal lead screw is connected with the vertical motion stepping motor and drives the horizontal lead screw to move along the vertical direction.
4. The laser shock peening device for the weld joint of the aerospace propellant tank according to claim 2, wherein the laser propagation light path structure comprises a light guide hollow upright, a first reflecting mirror and a second reflecting mirror;
the light guide hollow upright post is covered outside the vertical supporting structure and is provided with a light inlet window;
a first reflecting mirror and a second reflecting mirror are oppositely arranged at different height positions of the vertical supporting structure; the height of the first reflecting mirror is consistent with that of a laser emitting end of the laser, and the height of the second reflecting mirror is consistent with that of a laser receiving end of the laser focusing head.
Parallel laser beams emitted by the laser are incident to the inner side of the light guide hollow upright post through the light inlet window and are incident to the laser focusing head through the first reflecting mirror and the second reflecting mirror in sequence along the laser propagation direction.
5. The aerospace propellant tank weld joint laser shock peening apparatus of claim 4, wherein the vertical support structure comprises a vertical lead screw; the vertical lead screw is provided with a vertical motion stepping motor, and the horizontal lead screw is connected with the vertical motion stepping motor and drives the horizontal lead screw to move along the vertical direction;
and the second reflecting mirror is arranged on the vertical motion stepping motor and moves synchronously with the vertical motion stepping motor.
6. The laser shock peening device for the weld joint part of the space propellant storage tank according to claim 1, wherein a third reflecting mirror is installed in the laser focusing head and used for changing the propagation path of a laser beam, reflecting the laser from horizontal propagation to vertical propagation, and converging and irradiating the laser on the welding area where the friction stir welding long weld joint and the fusion welding girth weld joint on the surface of the space propellant storage tank are located by a focusing lens.
7. The laser shock peening apparatus for weld seam of aerospace propellant tanks according to claim 1, wherein the tank moving assembly includes a plurality of roller load-bearing supports for supporting the aerospace propellant tank; the roller bearing support is provided with a roller driving motor and a roller, the roller is attached to the aerospace propellant storage tank, and the movement speed is controlled by the roller driving motor; and the plurality of rollers simultaneously move to drive the aerospace propellant storage tank to rotate along the circumferential direction of the aerospace propellant storage tank.
8. The laser shock peening apparatus for the weld joint of the aerospace propellant tank according to claim 1, further comprising a working platform and a moving platform; the mobile platform is movably connected with the working platform; the storage box moving assembly is fixed on the moving platform.
9. A laser shock peening method of a aerospace propellant tank weld joint laser shock peening apparatus according to any one of claims 1 to 8, comprising the steps of:
firstly, sequentially arranging an absorption layer and a restraint layer on the surfaces of a welding area, namely a friction stir welding long weld joint and a fusion welding ring weld joint, of a spacecraft propellant storage tank to be reinforced, and measuring laser shock reinforcement ranges on the welding area and two sides to enable a laser focusing head to be aligned to the reinforcement range;
driving a laser focusing head to the initial position of the long friction stir welding seam through a laser focusing head moving structure, emitting laser spots with set sizes by the laser focusing head to irradiate the surface of the aerospace propellant storage tank for laser shock strengthening, driving the laser focusing head to horizontally move at a constant speed to complete single laser shock strengthening of one horizontal path at the same time, driving the aerospace propellant storage tank to rotate by a certain angle through a storage tank moving assembly to continue laser shock strengthening of the next horizontal path, and repeating the steps until the laser shock strengthening area of the long friction stir welding seam is completely strengthened;
driving a laser focusing head to the edge starting position of a laser shock strengthening area of a fusion welding ring welding seam through a laser focusing head moving structure, emitting laser spots with set sizes by the laser focusing head to irradiate the surface of a space propellant storage tank to carry out laser shock strengthening, driving the space propellant storage tank to continuously rotate to a set angle at a certain speed by a storage tank moving assembly to complete single laser shock strengthening of one circumferential path, driving the laser focusing head to horizontally move to a set length at a constant speed by the laser focusing head moving structure to continue laser shock strengthening of the next circumferential path, and repeating the steps until the laser shock strengthening area of the fusion welding ring welding seam is completely strengthened;
and fourthly, removing the absorption layer and the restraint layer after the long welding seam of the friction stir welding and the fusion welding girth welding seam are strengthened, and then completing the comprehensive strengthening of the welding seam of the aerospace propellant storage tank.
10. The laser shock peening method of claim 9, wherein the first step further comprises:
the height of the laser focusing head is adjusted through the laser focusing head moving structure, so that laser can obtain the required spot size after being converged at the top of the aerospace propellant storage box.
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