Aerospace equipment surface spraying equipment

Abstract

The present invention belongs to the field of spraying technology, specifically, an aerospace equipment surface spraying device, including an equipment base; a sliding groove is opened at the end of the equipment base; a paint box is slidably connected to the sliding groove through an electric slider; a paint pump is installed inside the paint box; two spray racks are arranged to relatively fit the inner and outer surfaces of the aerospace equipment shell, and the paint pump draws the paint inside the paint box and sends it to two atomizing nozzles, and the two atomizing nozzles evenly spray the inner and outer surfaces of the aerospace equipment shell synchronously, thereby improving the spraying efficiency of the aerospace equipment shell, and a diverter block is slid inside the diverter box, and the position of the diverter groove is adjusted by sliding to control the connection state of two No. 1 material guide pipes, so as to play a role in spraying different types of shells in different areas, and a limit rod is used to penetrate the diverter box and insert into the limit groove, so as to play a role in limiting the diversion position of the diverter block.

Description

Technical Field

[0001] The invention belongs to the field of spraying technology, in particular to a surface spraying device for aerospace equipment. Background Art

[0002] Aerospace equipment generally refers to aviation materials. Aviation materials are a general term for various materials used to manufacture aircraft and airborne equipment. During the production of aerospace equipment, it is often necessary to paint the parts and components of the aerospace equipment and then assemble them to increase the service life of the parts and components.

[0003] A patent application with publication number CN112058542A discloses an aerospace shell painting device that is easy to spray evenly, including a base, an exhaust fan is provided at the bottom inner end of the base, the exhaust fan and the base are connected together by bolts, and an adsorption plate is provided inside the base just above the exhaust fan. This application improves and optimizes the supporting structure of the painting device, which can facilitate the support of the shell when painting the internal shell of an aerospace vehicle.

[0004] The above-mentioned aerospace equipment spraying equipment mainly adjusts and supports the shell through an improved support device to facilitate uniform spraying of the shell. However, when spraying the aerospace equipment shell, since both the inner and outer surfaces of the shell need to be sprayed, the current aerospace equipment spraying equipment is difficult to quickly and synchronously spray the inner and outer surfaces of the shell, resulting in low spraying efficiency of the aerospace equipment shell.

[0005] To this end, the present invention provides a surface spraying device for aerospace equipment. Summary of the invention

[0006] In order to make up for the deficiencies of the prior art, at least one technical problem raised in the background technology is solved.

[0007] The technical solution adopted by the present invention to solve its technical problems is: an aerospace equipment surface spraying device described in the present invention includes an equipment base; a sliding groove is opened at the end of the equipment base; a paint box is slidably connected to the sliding groove through an electric slider; a paint pump is installed inside the paint box; a feed pipe is fixedly connected to the output end of the paint pump; a diverter assembly is provided at the end of the feed pipe away from the paint pump, and the diverter assembly is used to control the path of paint spraying; two No. 1 material guide pipes are fixedly connected to the diverter assembly; the ends of the two No. 1 material guide pipes away from the diverter assembly are respectively fixedly connected to spray racks, and the two spray racks are symmetrically arranged; an atomizing nozzle is installed on the outside of the spray rack; a fixing mechanism is provided at the end of the equipment base, and the fixing mechanism is used to fix the aerospace equipment.

[0008] Preferably, the diverter assembly includes a diverter box, a diverter block and a diverter groove; the diverter box is fixedly connected to one end of the feed pipe away from the paint pump, and the outside of the diverter box is connected to two No. 1 feed pipes; the diverter block is slidably connected to the inner wall of the diverter box; the diverter groove is opened inside the diverter block.

[0009] Preferably, a plurality of limit grooves are provided inside the diverter block; a limit rod is inserted inside the limit groove, and the limit rod passes through the inside of the diverter box; an elastic member No. 1 is sleeved on the outside of the limit rod, and the elastic member No. 1 is sleeved between the limit rod and the diverter box.

[0010] Preferably, the fixing mechanism includes a fixing seat, a servo motor, a limit plate and a matching component; the fixing seat is fixedly connected to the end of the equipment base away from the paint box; the servo motor is fixedly connected to the outside of the fixing seat; the limit plate is fixedly connected to the output end of the servo motor; the matching component is arranged on the outside of the paint box, and is used to cooperate with the limit plate to clamp the aerospace equipment.

[0011] Preferably, the mating assembly includes a fixing frame, a connecting rod, a clamping plate and a No. 2 elastic member; the fixing frame is fixedly connected to the outside of the paint box near the fixing seat; the two connecting rods are fixedly connected to the inner walls on both sides of the fixing frame; the two clamping plates are slidably connected to the outside of the connecting rod; the No. 2 elastic member is sleeved on the outside of the connecting rod, and the No. 2 elastic member is sleeved between the fixing frame and the clamping plate.

[0012] Preferably, a pulley frame is fixedly connected to the outside of the two clamping plates; and a sliding wheel is rotatably connected to the inner wall of the pulley frame.

[0013] Preferably, a No. 2 material guide pipe is fixedly connected to the interior of the spray rack, and the No. 2 material guide pipe is connected to the No. 1 material guide pipe; a connecting pipe is fixedly connected to the interior of the spray rack; a roller is rotatably connected to the inner wall of the spray rack; a spray plate is fixedly connected to the outside of the roller; a sealing assembly is provided inside the spray rack near the connecting pipe, and the sealing assembly is used to control spraying at the spray plate.

[0014] Preferably, the sealing assembly includes a solenoid valve, a fixed rod, a sliding block and a No. 3 elastic part; the solenoid valve is fixed between the No. 1 material guide pipe and the atomizing nozzle; the fixed rod is fixed to the inside of the spray frame; the sliding block is slidably connected to the outside of the fixed rod; the No. 3 elastic part is sleeved on the outside of the fixed rod, and the No. 3 elastic part is sleeved between the spray frame and the sliding block.

[0015] Preferably, a first shielding plate is fixedly connected to the outside of the spray rack near the atomizing nozzle; and a second shielding plate is fixedly connected to the outside of the spray plate.

[0016] Preferably, a plurality of anti-skid protrusions are fixedly connected to the outside of the limiting plate; and the plurality of anti-skid protrusions are located at the protruding parts of the limiting plate.

[0017] The beneficial effects of the present invention are as follows:

[0018] 1. The aerospace equipment surface spraying equipment described in the present invention has two spray racks that are relatively fitted to the inner and outer surfaces of the aerospace equipment shell, and a paint pump draws paint from the paint box and sends it to two atomizing nozzles. The two atomizing nozzles spray the inner and outer surfaces of the aerospace equipment shell evenly and synchronously, thereby improving the spraying efficiency of the aerospace equipment shell. The diverter block is slid inside the diverter box, and the position of the diverter slot is adjusted by sliding to control the connectivity of the two No. 1 material guide pipes, thereby playing a role in spraying different types of shells in different areas. A limit rod is inserted through the diverter box into the limit slot to play a role in limiting the diversion position of the diverter block. One end of the shell is inserted into the limit plate, and the two sliding wheels on the clamping plate are fitted to the other end of the shell to clamp, thereby playing a role in limiting and fixing the shell. In addition, the two sliding wheels can assist in rotation when spraying the inner and outer walls of the shell, thereby improving the spraying effect on the inner and outer walls of the shell.

[0019] 2. The aerospace equipment surface spraying equipment described in the present invention diverts part of the paint transported in the No. 1 material guide pipe through the No. 2 material guide pipe, and transports the paint from the connecting pipe to the spray plate to spray the inclined surface of the shell. The equipment is suitable for spraying shells with inclined surfaces, thereby improving the adaptability of the spraying equipment. The equipment relies on a solenoid valve installed at the connection between the No. 1 material guide pipe and the atomizing nozzle. The solenoid valve controls the transport of the paint in the atomizing nozzle, and can independently control the spraying state of the atomizing nozzle or the spray plate. The No. 1 baffle plate and the No. 2 baffle plate are respectively fixed at the atomizing nozzle and the spray plate for shielding, thereby reducing large-area splashing of part of the paint sprayed, and reducing the uneven spraying of the inner and outer surfaces of the aerospace equipment shell. The equipment relies on a plurality of anti-skid protrusions fixed at the protruding parts of the limit plate, which play an anti-skid role when the aerospace equipment shell is inserted on the limit plate, thereby improving the stability of the aerospace equipment shell during rotation spraying. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The present invention will be further described below in conjunction with the accompanying drawings.

[0021] Figure 1 is a stereogram of the present invention;

[0022] Figure 2 It is a structural schematic diagram of the limiting plate in the present invention;

[0023] Figure 3 It is a structural schematic diagram of the sliding wheel in the present invention;

[0024] Figure 4 It is a partial structural cross-sectional view of the diverter box in the present invention;

[0025] Figure 5It is a partial structural sectional view of the spraying rack in the present invention.

[0026] In the figure: 1. Equipment base; 11. Sliding groove; 12. Paint box; 13. Feed pipe; 14. No. 1 feed pipe; 15. Spray rack; 16. Atomizing nozzle; 2. Diverter box; 21. Diverter block; 22. Diverter groove; 3. Limiting groove; 31. Limiting rod; 32. No. 1 elastic part; 4. Fixed seat; 41. Servo motor; 42. Limiting plate; 5. Fixed frame; 51. Connecting rod; 52. Clamping plate; 53. No. 2 elastic part; 6. Pulley frame; 61. Sliding wheel; 7. No. 2 feed pipe; 71. Connecting pipe; 72. Roller; 73. Spray plate; 8. Solenoid valve; 81. Fixed rod; 82. Sliding block; 83. No. 3 elastic part; 9. No. 1 baffle plate; 91. No. 2 baffle plate. DETAILED DESCRIPTION

[0027] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further explained below in conjunction with specific implementation methods.

[0028] like Figures 1 to 5 As shown, an aerospace equipment surface spraying device described in an embodiment of the present invention comprises an equipment base 1; a sliding groove 11 is provided at the end of the equipment base 1; a paint box 12 is slidably connected to the sliding groove 11 through an electric slider; a paint pump is installed inside the paint box 12; a feed pipe 13 is fixedly connected to the output end of the paint pump; a diversion component is provided at the end of the feed pipe 13 away from the paint pump, and the diversion component is used to control the path of paint spraying; two No. 1 material guide pipes 14 are fixedly connected to the diversion component; the ends of the two No. 1 material guide pipes 14 away from the diversion component are respectively fixedly connected to spray racks 15, and the two spray racks 15 are symmetrically arranged; an atomizing nozzle 16 is installed on the outside of the spray rack 15; a fixing mechanism is provided at the end of the equipment base 1, and the fixing mechanism is used to fix the aerospace equipment; When spraying the inner and outer surfaces of the aerospace equipment shell, first place the aerospace equipment shell at the end of the equipment base 1, use a fixing mechanism to fix the aerospace equipment shell in a limited position, and the electric slider drives the paint box 12 to slide in the sliding groove 11. The paint box 12 slides close to the aerospace equipment shell, and the two spray racks 15 are relatively fitted to the inner and outer surfaces of the aerospace equipment shell. Then the paint pump draws the paint inside the paint box 12 and transports it to the diversion component through the feed pipe 13. The diversion component is used to separate the transported paint into two No. 1 guide pipes 14. The paint is atomized and sprayed by the atomizing nozzles 16 installed on the outside of the two spray racks 15. As the fixing mechanism adjusts the angle of the aerospace equipment shell, the two atomizing nozzles 16 evenly spray the inner and outer surfaces of the aerospace equipment shell synchronously, thereby improving the spraying efficiency of the aerospace equipment shell.

[0029] like Figures 1 to 4 As shown, the diverter assembly includes a diverter box 2, a diverter block 21 and a diverter slot 22; the diverter box 2 is fixedly connected to the end of the feed pipe 13 away from the paint pump, and the outside of the diverter box 2 is connected to two No. 1 feed guide pipes 14; the diverter block 21 is slidably connected to the inner wall of the diverter box 2; the diverter slot 22 is opened inside the diverter block 21; when spraying the surface of the aerospace equipment shell, due to the different spraying areas of different types of shells, some shells only need to spray the outer wall or the inner wall separately, and the diverter box 2 is used to connect the feed pipe 13 and the two No. 1 feed guide pipes 14, and the diverter block 21 slides inside the diverter box 2, and the position of the diverter slot 22 is adjusted by sliding to control the connection state of the two No. 1 feed guide pipes 14. When only When spraying the outer wall of the shell, press the diverter block 21 and slide it down to the bottom of the diverter box 2. At this time, the feed pipe 13 is connected to the No. 1 feed guide pipe 14 above through the diverter groove 22, so that the outer wall of the shell can be sprayed; when only the inner wall of the shell needs to be sprayed, pull up the diverter block 21 and slide it to the top of the inner part of the diverter box 2. At this time, the feed pipe 13 is connected to the No. 1 feed guide pipe 14 below through the diverter groove 22, so that the inner wall of the shell can be sprayed; when it is necessary to spray the inner and outer walls of the shell at the same time, slide the diverter block 21 to the middle part of the inner part of the diverter box 2. At this time, the feed pipe 13 is respectively connected to the two No. 1 feed guide pipes 14 through the diverter groove 22, so that the inner and outer walls of the shell can be sprayed at the same time, which plays the role of spraying different types of shells in different areas.

[0030] The interior of the diverter block 21 is provided with a plurality of limit grooves 3; the interior of the limit grooves 3 is inserted with a limit rod 31, and the limit rod 31 passes through the interior of the diverter box 2; the exterior of the limit rod 31 is sleeved with an elastic member 32, and the elastic member 32 is sleeved between the limit rod 31 and the diverter box 2; when the diverter block 21 is limited in its sliding diversion position, the limit rod 31 is penetrated through the interior of the diverter box 2, and after the diversion position of the diverter block 21 is adjusted by sliding, the limit rod 31 is pulled by the elastic force of the elastic member 32 to be inserted into the corresponding limit groove 3, so that the diversion position of the diverter block 21 is limited, and when the diversion position of the diverter block 21 needs to be adjusted, the limit rod 31 is pulled out of the limit groove 3, the elastic member 32 is pulled by force, and after the diverter block 21 is slid, the limit rod 31 is inserted into another limit groove 3 again, thereby fixing the diversion position of the diverter block 21.

[0031] like Figure 1 and Figure 2As shown, the fixing mechanism includes a fixing seat 4, a servo motor 41, a limit plate 42 and a matching component; the fixing seat 4 is fixedly connected to the end of the equipment base 1 away from the paint box 12; the servo motor 41 is fixedly connected to the outside of the fixing seat 4; the limit plate 42 is fixedly connected to the output end of the servo motor 41; the matching component is arranged on the outside of the paint box 12, and the matching component is used to cooperate with the limit plate 42 to clamp the aerospace equipment; when the aerospace equipment shell is fixedly sprayed, the fixing seat 4 is fixed to the side of the end of the equipment base 1 away from the paint box 12, and the aerospace equipment shell is inserted into the output end of the servo motor 41 and connected to the limit plate 42, and then the paint box 12 drives the matching component to clamp and fix the aerospace equipment shell, and as the output end of the servo motor 41 drives the clamped aerospace equipment shell to rotate, the inner and outer surfaces of the aerospace equipment shell are sprayed synchronously, which plays a role in fixing and clamping the aerospace equipment shell.

[0032] It should be noted that the aerospace equipment shell should not be clamped too tightly, and it is only necessary to assist in clamping and limiting the shell to prevent the aerospace equipment shell from being difficult to rotate during spraying.

[0033] like Figures 1 to 3 As shown, the matching assembly includes a fixing frame 5, a connecting rod 51, a clamping plate 52 and a second elastic member 53; the fixing frame 5 is fixedly connected to the outside of the paint box 12 near the fixing seat 4; the two connecting rods 51 are fixedly connected to the inner walls on both sides of the fixing frame 5; the two clamping plates 52 are slidably connected to the outside of the connecting rod 51; the second elastic member 53 is sleeved on the outside of the connecting rod 51, and the second elastic member 53 is sleeved between the fixing frame 5 and the clamping plate 52; when the aerospace equipment shell is clamped and limited, the aerospace equipment shell After being inserted into the limit plate 42, the paint box 12 is used to drive the fixing frame 5 to approach and penetrate into the interior of the aerospace equipment shell. The two clamping plates 52 are attached to the outside of the aerospace equipment shell at one end away from the limit plate 42. As the paint box 12 drives the fixing frame 5 to continue to penetrate into the shell, the two clamping plates 52 slide on the two connecting rods 51 respectively, and the two clamping plates 52 squeeze the two No. 2 elastic parts 53, so that the aerospace equipment shell is stably limited and clamped, thereby improving the spraying effect on the inner and outer surfaces of the aerospace equipment shell.

[0034] The outside of the two clamping plates 52 is fixedly connected with a pulley frame 6; the inner wall of the pulley frame 6 is rotatably connected with a sliding wheel 61; when the inner and outer walls of the aerospace equipment shell are rotated and sprayed after being clamped, the pulley frames 6 are respectively installed using the front ends of the two clamping plates 52, and the inner walls of the two pulley frames 6 are rotatably connected to the sliding wheels 61, and the sliding wheels 61 are attached to the outside of the aerospace equipment shell. As the output end of the servo motor 41 drives the shell on the limit plate 42 to rotate, the two sliding wheels 61 are attached to one end of the aerospace equipment shell to squeeze and assist in rotation. The setting of the two sliding wheels 61 assisting in rotation can reduce the situation where the aerospace equipment shell is difficult to rotate and spray after being clamped.

[0035] like Figures 1 to 5 As shown, the interior of the spray rack 15 is fixedly connected with a No. 2 material guide pipe 7, and the No. 2 material guide pipe 7 is connected to the No. 1 material guide pipe 14; the interior of the spray rack 15 is fixedly connected with a connecting pipe 71; the inner wall of the spray rack 15 is rotatably connected with a rotating roller 72; the exterior of the rotating roller 72 is fixedly connected with a spray plate 73; the interior of the spray rack 15 is provided with a plugging component near the connecting pipe 71, and the plugging component is used to control the spraying at the spray plate 73; when spraying the inner and outer surfaces of aerospace equipment shells with inclined surfaces, traditional aerospace equipment shell spraying equipment is difficult to adapt The inclined surface is sprayed by utilizing a rotating roller 72 and a spray plate 73 to rotate at the front end of the spray rack 15. Rotating the rotating roller 72 can adjust the spray angle of the spray plate 73. After adjusting the angle to match the inclined surface of the shell, the paint is pumped from the No. 1 material guide pipe 14, and part of the paint is transported from the No. 2 material guide pipe 7 to the inside of the spray rack 15. After passing through the sealing component in the open state, the paint is transported from the connecting pipe 71 to the spray plate 73 for spraying, so that the inner and outer surfaces of the shell of aerospace equipment with an inclined surface are sprayed synchronously. This is suitable for spraying shells with inclined surfaces and improves the adaptability of the spraying equipment.

[0036] The blocking assembly includes an electromagnetic valve 8, a fixed rod 81, a sliding block 82 and a third elastic member 83; the electromagnetic valve 8 is fixedly connected between the No. 1 guide pipe 14 and the atomizing nozzle 16; the fixed rod 81 is fixedly connected to the inside of the spray frame 15; the sliding block 82 is slidably connected to the outside of the fixed rod 81; the third elastic member 83 is sleeved on the outside of the fixed rod 81, and the third elastic member 83 is sleeved between the spray frame 15 and the sliding block 82; when spraying the shell surface with an inclined surface, since part of the shell only needs to spray the inclined surface, the electromagnetic valve 8 is fixed at the connection between the No. 1 guide pipe 14 and the atomizing nozzle 16 to control the blocking of the paint transported in the No. 1 guide pipe 14 from entering the atomizing nozzle 16, so that all the paint transported at the No. 1 guide pipe 14 enters the spray frame 15 from the No. 2 guide pipe 7, and the paint presses the sliding block 82 on the fixed rod 81 to slide down, and the No. 3 elastic member 83 is squeezed and contracted. The connecting pipe 71 blocked by the sliding block 82 is punched open, and the paint is delivered by the connecting pipe 71 to the spray plate 73 for spraying, thereby controlling the inclined surface of the spray shell at the spray plate 73 separately. At the same time, if it is necessary to control the spray shell surface at the atomizing nozzle 16 separately, the power of the paint pump is set to two gears. When the power of the paint pump is in the first gear, the solenoid valve 8 is in the open state. Although part of the paint can enter the interior of the No. 2 material guide pipe 7, the paint delivered by the first gear power is difficult to punch the sliding block 82 down to open the blockage at the connecting pipe 71, thereby realizing the function of separately controlling the spraying at the atomizing nozzle 16. If it is necessary to open the atomizing nozzle 16 and the spray plate 73 at the same time for spraying, the power of the spray pump needs to be set to the second gear. At this time, the solenoid valve 8 is in the open state, and the paint delivered at the No. 2 material guide pipe 7 can punch the sliding block 82 down and open the connecting pipe 71, thereby realizing the function of synchronous spraying at the atomizing nozzle 16 and the spray plate 73.

[0037] like Figures 1 to 3 , Figure 5 As shown, a No. 1 baffle plate 9 is fixedly connected to the outside of the spray rack 15 near the atomizing nozzle 16; a No. 2 baffle plate 91 is fixedly connected to the outside of the spray plate 73; when spraying the inner and outer surfaces of the aerospace equipment shell, two No. 1 baffle plates 9 are fixed at the two atomizing nozzles 16, and the No. 1 baffle plate 9 can block the paint sprayed from the atomizing nozzle 16. The two No. 2 baffle plates 91 are also fixed at the spraying points of the two spray plates 73. The setting of the No. 1 baffle plate 9 and the No. 2 baffle plate 91 can reduce the large-area splashing of part of the paint sprayed, and reduce the uneven spraying of the inner and outer surfaces of the aerospace equipment shell.

[0038] like Figure 1 and Figure 2As shown, a plurality of anti-skid protrusions are fixed to the outside of the limiting plate 42; the plurality of anti-skid protrusions are located at the protruding parts of the limiting plate 42; when the aerospace equipment shell is fixed and limited, the plurality of anti-skid protrusions are fixed at the protruding parts of the limiting plate 42, and the provision of the plurality of anti-skid protrusions can increase the friction between the aerospace equipment shell and the inner wall, thereby playing an anti-skid role when the aerospace equipment shell is inserted on the limiting plate 42, and improving the stability of the aerospace equipment shell during rotation and spraying.

[0039] Working process: When spraying the inner and outer surfaces of the aerospace equipment shell, first place the aerospace equipment shell at the end of the equipment base 1, use a fixing mechanism to fix the aerospace equipment shell in a limited position, and the electric slider drives the paint box 12 to slide in the sliding groove 11. The paint box 12 slides close to the aerospace equipment shell, and the two spray racks 15 are relatively fitted to the inner and outer surfaces of the aerospace equipment shell. Then the paint pump extracts the paint inside the paint box 12 and transports it to the diversion component through the feed pipe 13. The diversion component is used to separate the transported paint into two No. 1 guide pipes 14, and the paint is sprayed by the atomizing nozzle 1 installed outside the two spray racks 15. 6 places of atomization spraying, as the fixing mechanism adjusts the angle of the aerospace equipment shell, the two atomizing nozzles 16 evenly spray the inner and outer surfaces of the aerospace equipment shell synchronously, thereby improving the spraying efficiency of the aerospace equipment shell; when spraying the surface of the aerospace equipment shell, due to the different spraying areas of different types of shells, some shells only need to spray the outer wall or the inner wall separately, and the diverter box 2 is used to connect the feed pipe 13 and the two No. 1 guide pipes 14, and the diverter block 21 slides inside the diverter box 2, and the position of the diverter slot 22 is adjusted by sliding to control the connection state of the two No. 1 guide pipes 14. When only the outer wall of the shell needs to be sprayed , press the diverter block 21 and slide it down to the bottom of the diverter box 2. At this time, the feed pipe 13 is connected to the No. 1 feed guide pipe 14 above through the diverter groove 22, so that the outer wall of the shell can be sprayed; when only the inner wall of the shell needs to be sprayed, pull up the diverter block 21 and slide it to the top of the inner part of the diverter box 2. At this time, the feed pipe 13 is connected to the No. 1 feed guide pipe 14 below through the diverter groove 22, so that the inner wall of the shell can be sprayed; when the inner and outer walls of the shell need to be sprayed at the same time, slide the diverter block 21 to the middle part of the inner part of the diverter box 2. At this time, the feed pipe 13 is connected to the two No. 1 feed guide pipes 14 respectively through the diverter groove 22, so that the inner and outer walls of the shell can be sprayed at the same time The shunt block 21 is slidably mounted on the shunting member 22, and the shunting member 22 is slidably mounted on the shunting member 22. The shunting member 22 is slidably mounted on the shunting member 22, and the shunting member 22 is slidably mounted on the shunting member 22. The shunting member 22 is slidably mounted on the shunting member 22, and the shunting member 22 is shunted to a desired position. The shunting member 22 is slidably mounted on the shunting member 22, and the shunting member 22 is shunted to a desired position.

[0040] When the aerospace equipment shell is fixedly sprayed, the fixing seat 4 is fixed to the side of the end of the equipment base 1 away from the paint box 12, and the aerospace equipment shell is inserted into the output end of the servo motor 41 and connected to the limit plate 42. Then the paint box 12 drives the matching components to clamp and fix the aerospace equipment shell. As the output end of the servo motor 41 drives the clamped aerospace equipment shell to rotate, the inner and outer surfaces of the aerospace equipment shell are sprayed synchronously, which plays a role in fixing and clamping the aerospace equipment shell; when the aerospace equipment shell is fixed and limited, a plurality of anti-skid protrusions are fixed to the protruding part of the limit plate 42. The provision of a plurality of anti-skid protrusions can increase the friction between the inner wall of the aerospace equipment shell, and play an anti-skid role when the aerospace equipment shell is inserted on the limit plate 42, thereby improving the stability of the aerospace equipment shell during rotation and spraying; when the aerospace equipment shell is clamped and limited, after the aerospace equipment shell is inserted on the limit plate 42, the paint box 12 is used to drive the fixing frame 5 Approaching and penetrating into the interior of the aerospace equipment shell, the two clamping plates 52 are fitted to the outside of one end of the aerospace equipment shell away from the limit plate 42. As the paint box 12 drives the fixing frame 5 to continue to penetrate into the shell, the two clamping plates 52 slide on the two connecting rods 51 respectively, and the two clamping plates 52 squeeze the two second elastic members 53 to apply force, so that the aerospace equipment shell is stably limited and clamped, thereby improving the spraying effect on the inner and outer surfaces of the aerospace equipment shell; when the aerospace equipment shell is clamped and rotated to spray the inner and outer walls, the pulley frames 6 are respectively installed at the front ends of the two clamping plates 52, and the inner walls of the two pulley frames 6 are both rotatably connected to the sliding wheels 61, and the sliding wheels 61 are fitted to the outside of the aerospace equipment shell. As the output end of the servo motor 41 drives the shell on the limit plate 42 to rotate, the two sliding wheels 61 are fitted to one end of the aerospace equipment shell to squeeze and assist in rotation. The setting of the two sliding wheels 61 assisting in rotation reduces the situation where the aerospace equipment shell is difficult to rotate and spray after being clamped;

[0041] When spraying the inner and outer surfaces of some aerospace equipment shells with inclined surfaces, it is difficult for traditional aerospace equipment shell spraying equipment to adapt to the inclined surfaces for spraying. The roller 72 is used to cooperate with the spray plate 73 to rotate at the front end of the spray rack 15. The rotating roller 72 can adjust the spray angle of the spray plate 73. After adjusting the angle to adapt to the inclined surface of the shell, the paint is pumped from the inside of the No. 1 guide pipe 14, and part of the paint is transported from the No. 2 guide pipe 7 to the inside of the spray rack 15. After passing through the plugging component in the open state, the paint is pumped from the connecting pipe 71. The spray plate 73 is sprayed, so that the inner and outer surfaces of the shell of the aerospace equipment with the bevel are sprayed synchronously, which is suitable for the shell spraying with the bevel, and improves the adaptability of the spraying equipment; when spraying the shell surface with the bevel, since part of the shell only needs to spray the bevel, the electromagnetic valve 8 is fixed at the connection between the No. 1 guide pipe 14 and the atomizing nozzle 16 to control and block the paint transported in the No. 1 guide pipe 14 from entering the atomizing nozzle 16, so that all the paint transported at the No. 1 guide pipe 14 enters from the No. 2 guide pipe 7. In the spraying rack 15, the sliding block 82 on the paint stamping fixed rod 81 slides down, the third elastic member 83 is squeezed and contracted, and the connecting pipe 71 originally blocked by the sliding block 82 is stamped open, and the paint is sent to the spraying plate 73 by the connecting pipe 71 for spraying, which plays a role in controlling the spraying shell slope at the spraying plate 73 separately. At the same time, if it is necessary to control the spraying shell surface at the atomizing nozzle 16 separately, the power of the paint pump is set to two gears. When the power of the paint pump is in the first gear, the solenoid valve 8 is in the open state. Although part of the paint can enter the second gear, The paint delivered by the first gear power is inside the No. 1 guide pipe 7, but it is difficult for the sliding block 82 to slide down and open the blockage at the connecting pipe 71, so as to realize the function of controlling the spraying at the atomizing nozzle 16 alone. If it is necessary to open the atomizing nozzle 16 and the spray plate 73 for spraying at the same time, the power of the spray pump needs to be set to the second gear. At this time, the solenoid valve 8 is in the open state, and the paint delivered by the No. 2 guide pipe 7 can press the sliding block 82 to slide down and open the connecting pipe 71, so as to realize the function of synchronous spraying at the atomizing nozzle 16 and the spray plate 73;

[0042] When spraying the inner and outer surfaces of the aerospace equipment shell, two No. 1 baffles 9 are fixed at the two atomizing nozzles 16. The No. 1 baffles 9 can block the paint sprayed from the atomizing nozzles 16. The two No. 2 baffles 91 are also fixed at the spraying points of the two spray plates 73. The setting of the No. 1 baffles 9 and the No. 2 baffles 91 can reduce the large-area splashing of part of the paint sprayed, and reduce the uneven spraying of the inner and outer surfaces of the aerospace equipment shell.

[0043] The above shows and describes the basic principles, main features and advantages of the present invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments. The above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. An aerospace equipment surface spraying device, characterized in that: The invention comprises an equipment base (1); a sliding groove (11) is provided at the end of the equipment base (1); a paint box (12) is slidably connected to the sliding groove (11) via an electric slider; a paint pump is installed inside the paint box (12); a feed pipe (13) is fixedly connected to the output end of the paint pump; a flow divider assembly is provided at one end of the feed pipe (13) away from the paint pump, and the flow divider assembly is used to control the path of paint spraying; two No. 1 material guide pipes (14) are fixedly connected to the flow divider assembly; one end of the two No. 1 material guide pipes (14) away from the flow divider assembly is respectively fixedly connected to a spray rack (15), and the two spray racks (15) are symmetrically arranged; an atomizing nozzle (16) is installed outside the spray rack (15); a fixing mechanism is provided at the end of the equipment base (1), and the fixing mechanism is used to fix aerospace equipment; The flow diversion assembly comprises a flow diversion box (2), a flow diversion block (21) and a flow diversion groove (22); the flow diversion box (2) is fixedly connected to an end of the material delivery pipe (13) away from the paint pump, and the outside of the flow diversion box (2) is connected to two No. 1 material guide pipes (14); the flow diversion block (21) is slidably connected to the inner wall of the flow diversion box (2); the flow diversion groove (22) is arranged inside the flow diversion block (21); A plurality of limit slots (3) are provided inside the flow dividing block (21); a limit rod (31) is inserted inside the limit slot (3), and the limit rod (31) passes through the inside of the flow dividing box (2); a first elastic member (32) is sleeved outside the limit rod (31), and the first elastic member (32) is sleeved between the limit rod (31) and the flow dividing box (2).

2. The surface spraying equipment for aerospace equipment according to claim 1, characterized in that: The fixing mechanism comprises a fixing seat (4), a servo motor (41), a limit plate (42) and a matching component; the fixing seat (4) is fixedly connected to the end of the equipment base (1) away from the paint box (12); the servo motor (41) is fixedly connected to the outside of the fixing seat (4); the limit plate (42) is fixedly connected to the output end of the servo motor (41); the matching component is arranged on the outside of the paint box (12), and is used to cooperate with the limit plate (42) to clamp the aerospace equipment.

3. The surface spraying equipment for aerospace equipment according to claim 2, characterized in that: The mating assembly comprises a fixing frame (5), a connecting rod (51), a clamping plate (52) and a second elastic member (53); the fixing frame (5) is fixedly connected to the outside of the paint box (12) near the fixing seat (4); the two connecting rods (51) are fixedly connected to the inner walls on both sides of the fixing frame (5); the two clamping plates (52) are slidably connected to the outside of the connecting rod (51); the second elastic member (53) is sleeved on the outside of the connecting rod (51), and the second elastic member (53) is sleeved between the fixing frame (5) and the clamping plate (52).

4. The surface spraying equipment for aerospace equipment according to claim 3, characterized in that: The outsides of the two clamping plates (52) are fixedly connected to a pulley frame (6); the inner wall of the pulley frame (6) is rotatably connected to a sliding wheel (61).

5. The surface spraying equipment for aerospace equipment according to claim 1, characterized in that: A No. 2 material guide pipe (7) is fixedly connected to the interior of the spray rack (15), and the No. 2 material guide pipe (7) is connected to the No. 1 material guide pipe (14); a connecting pipe (71) is fixedly connected to the interior of the spray rack (15); a rotating roller (72) is rotatably connected to the inner wall of the spray rack (15); a spray plate (73) is fixedly connected to the exterior of the rotating roller (72); a blocking component is provided inside the spray rack (15) near the connecting pipe (71), and the blocking component is used to control spraying at the spray plate (73).

6. The surface spraying equipment for aerospace equipment according to claim 5, characterized in that: The blocking assembly comprises a solenoid valve (8), a fixed rod (81), a sliding block (82) and a third elastic member (83); the solenoid valve (8) is fixedly connected between a first material guide tube (14) and an atomizing nozzle (16); the fixed rod (81) is fixedly connected to the inside of a spraying frame (15); the sliding block (82) is slidably connected to the outside of the fixed rod (81); the third elastic member (83) is sleeved on the outside of the fixed rod (81), and the third elastic member (83) is sleeved between the spraying frame (15) and the sliding block (82).

7. The surface spraying equipment for aerospace equipment according to claim 5, characterized in that: A first shielding plate (9) is fixedly connected to the outside of the spraying frame (15) near the atomizing nozzle (16); and a second shielding plate (91) is fixedly connected to the outside of the spraying plate (73).

8. The surface spraying equipment for aerospace equipment according to claim 2, characterized in that: A plurality of anti-skid protrusions are fixedly connected to the outside of the limiting plate (42); the plurality of anti-skid protrusions are located at the protruding parts of the limiting plate (42).

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