A solid rocket engine physical cleaning device and a cleaning method
The solid rocket motor cleaning device, which utilizes cryogenic ring cutting and automated control, solves the problems of low safety, low efficiency, and environmental impact in existing cleaning technologies, achieving efficient and safe propellant cleaning and reuse.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- 西安中天含能材料装备有限公司
- Filing Date
- 2021-04-09
- Publication Date
- 2026-07-21
AI Technical Summary
The existing propellant cleanup process for solid rocket engines is characterized by high safety risks, low efficiency, serious environmental problems, and significant waste of propellant resources.
The system employs a low-temperature annular cutting method, which uses the engine's revolution and the tool's rotation to form an annular groove array. The tool then uses linear motion to cut the material into strips and blocks. Combined with a vortex cold air generator, the system provides real-time humidification and cooling, enabling automated remote control.
It improves the efficiency of drug removal, reduces safety risks, reduces environmental pollution, and allows the propellant to be reused, thus avoiding resource waste.
Smart Images
Figure CN113123896B_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of solid rocket engine replacement and cleaning technology, and specifically relates to a physical cleaning device and cleaning method for solid rocket engines. Background Technology
[0002] The disposal of solid rocket and missile engines is an extremely difficult, technologically demanding, and low-safety-factor task. How to effectively remove solid propellant from the engine while ensuring a certain level of safety and achieving effective recycling of the engine casing is one of the major challenges facing researchers and engineers. Traditional methods using cutting tools require close-range manual labor, which not only poses health risks due to the propellant's chemicals but also greatly increases the risk of combustion and explosion after mechanical impact. Alternatively, high-pressure water jet cutting, while reducing the cutting temperature, has extremely low efficiency and easily leads to aerosol accumulation, increasing the likelihood of secondary disasters.
[0003] The delayed replacement of existing solid rocket and missile engines, and the propellant cleaning process, present the following problems: 1. The solid propellant cleaning process mostly involves boring and cutting the propellant column. Since propellant is a flammable and explosive hazardous material, production efficiency is very low due to safety concerns, and the cleaning process poses certain safety risks; 2. Large engines use high-pressure water cutting to cut solid propellants, generating a large amount of industrial wastewater. This wastewater contains a large amount of oxidizer ammonium perchlorate and other harmful components, which are difficult to treat harmlessly, leading to environmental problems; 3. Due to the addition of desensitizing agents and high-pressure water, the propellant formula undergoes physicochemical changes during the cleaning process, resulting in the propellant being essentially ineffective and causing a waste of energetic materials. Summary of the Invention
[0004] To address the aforementioned propellant cleaning issues, the present invention aims to provide a physical cleaning device and method for solid rocket engines. By employing low-temperature, ring-cutting techniques, the cleaning efficiency and safety of the cleaning process are improved, environmental pollution is reduced, and the decommissioned propellant material after cutting is safely cleaned and reused.
[0005] The technical solution of this invention is as follows: a physical cleaning device for a solid rocket motor, comprising a base and a working platform fixedly installed on the base, wherein: the working platform is inclined and has a parallel slide rail, and the parallel slide rail is provided with a tool feeding mechanism, a first slide rail seat for the rocket motor, and a second slide rail seat for the rocket motor in sequence from high to low; the tool feeding mechanism is provided with a tool conversion disc, and a ring cutter and a scraper are fixedly connected to the tool conversion disc respectively; the second slide rail seat for the rocket motor is provided with an explosion-proof servo motor and a second transmission gear, and the second transmission gear is connected to a second fixed chuck for the rocket motor; the first slide rail seat for the rocket motor is provided with a first transmission gear, and the first transmission gear is connected to a first fixed chuck for the rocket motor; the first fixed chuck and the second fixed chuck for the rocket motor are used to position the two ends of the rocket motor.
[0006] The upper part of the second slide seat of the rocket engine is provided with a propellant discharge hole at the connection between the second fixed chuck of the rocket engine and the propellant discharge hole. A propellant discharge groove is provided below the propellant discharge hole, and a propellant collection box is provided at the bottom of the propellant discharge groove.
[0007] The circumferential cutting blade includes a circumferential cutting blade rod and an isolation sleeve installed on the outer surface of the circumferential cutting blade rod. Multiple circumferential cutting blades are fixedly arranged in parallel at equal intervals on the outer side of the isolation sleeve. The isolation sleeve is fastened to the circumferential cutting blade rod by a clamping nut. The circumferential cutting blade rod is hollow inside and has a circumferential cutting blade rod cold air channel. Several through cold air holes are distributed on the surface of the circumferential cutting blade rod and the isolation sleeve. The cold air holes are connected to the circumferential cutting blade rod cold air channel.
[0008] The distance between adjacent annular blades of the aforementioned circumferential cutter is 50mm.
[0009] The shovel includes a shank and a shovel head mounted at the end of the shank. The shovel head is provided with a three-sided blade and a cooling air groove. The shank has a shank cooling air channel inside, which is connected to the cooling air groove.
[0010] The cutting tool feeding mechanism is also equipped with a vortex cold air generator, and the air outlet of the vortex cold air generator is connected to the cold air channel of the circumferential cutting tool rod of the circumferential cutting tool and the cold air channel of the scraper rod of the scraper.
[0011] Several safety pads are provided on the parallel slide rail below the rocket engine.
[0012] The work platform is tilted, with an angle of 15 to 90 degrees to the horizontal plane.
[0013] A physical cleaning method for solid rocket motors includes the following steps: S1: Install the solid rocket motor to be cleaned on the solid rocket motor physical cleaning device; by adjusting the distance between the first slide seat and the second slide seat of the rocket motor, and using the first fixed chuck and the second fixed chuck of the rocket motor, position both ends of the rocket motor; S2: Adjust the tool conversion disc to align the ring cutter with the solid rocket motor to be cleaned. Adjust the ring cutter to the cutting position through the tool feed mechanism. Start the solid rocket motor physical cleaning device. The device moves from the inner hole of the rocket motor in a planetary compound motion. The explosion-proof servo motor drives the second transmission gear and the first transmission gear to rotate, thereby driving the rocket motor fixed by the first fixed chuck and the second fixed chuck to rotate. That is, the rocket motor revolves around the center and the ring cutter rotates on its own axis, which quickly cuts the propellant into an array of ring seams. Then the ring cutter is withdrawn. S3: Adjust the tool conversion disc, align the shovel with the solid rocket motor to be cleaned, start the solid rocket motor physical cleaning device, and use the rocket motor's revolution and the shovel's linear motion to cut the ring-shaped tablet into small pieces. S4: Due to the tilted setting of the working platform, when the rocket engine is rotating, the propellant cut by the rocket engine in S3 is discharged from the propellant discharge slot below the propellant discharge hole into the propellant collection box due to gravity, thus completing the propellant cleaning process.
[0014] In steps S2 and S3, the vortex cold air generator on the tool feed mechanism continuously blows humid cold air onto the cutting edge of the tool through the cold air channel of the circumferential cutting bar and the cold air channel of the scraper bar, which are connected to the air outlet of the vortex cold air generator, so that the cutting surface is in a cold and humid state and static electricity is eliminated.
[0015] The technical advantages of this invention are as follows: 1. This invention uses engine revolution and cutter rotation to cut the propellant into an annular groove array, and engine revolution and cutter linear motion to cut the propellant into strips; the entire cleaning process achieves low-speed and high-efficiency propellant cleaning, with efficiency dozens of times higher than traditional machine tool cleaning at the same cutting speed. 2. This invention uses a vortex cold air generator to continuously blow moist cold air onto the cutting edge of the cutter, achieving instant humidification and cooling during the cleaning process, eliminating static electricity, and ensuring the safety of the cleaning process. 3. This invention uses physical cutters for cleaning operations, which is green and environmentally friendly compared to high-pressure water cutting methods, and the cut propellant can be reused, avoiding the environmental problems caused by disposal; at the same time, the cleaning process is fully remotely automated, and personnel work in a safe isolation area, eliminating the risk of personal safety accidents at the work site. Attached Figure Description
[0016] Figure 1 This is a schematic diagram of a physical cleaning device for a solid rocket engine according to an embodiment of the present invention.
[0017] Figure 2 This is a schematic diagram of the ring cutter of a physical cleaning device for a solid rocket engine according to an embodiment of the present invention.
[0018] Figure 3 This is a schematic diagram of the shovel blade of a physical cleaning device for a solid rocket engine according to an embodiment of the present invention.
[0019] Reference numerals: 1-Pulp collection box; 2-Rocket engine; 3-Safety pad; 4-Working platform; 5-Circular cutter; 6-Shovel; 7-Vortex cold air generator; 8-Cut tool feed mechanism; 9-Slide rail; 10-Equipment base; 11-Cut tool conversion disc; 12-Rocket engine first fixed chuck; 13-Rocket engine second fixed chuck; 14-Pulp discharge hole; 15-Pulp discharge groove; 16-Rocket engine first slide seat; 17-Rocket engine second slide seat; 18-Second transmission gear; 19-Explosion-proof servo motor; 20-First transmission gear; 51-Circular cutter rod; 52-Circular cutter blade; 53-Clamping nut; 54-Isolation sleeve; 55-Circular cutter rod cold air channel; 56-Cold air hole; 61-Shovel rod; 62-Shovel head; 63-Blade; 64-Cold air groove; 65-Shovel rod cold air channel.
[0020] The following will provide further explanation in conjunction with the accompanying drawings; Detailed Implementation Example 1
[0021] To overcome the problems of low production efficiency, safety hazards, and significant pollution associated with existing chemical cleaning processes using waterjet cutting, this invention provides... Figure 1 This invention discloses a physical propellant removal device for a solid rocket engine. The device uses the engine's revolution and the cutter's rotation to cut the propellant into an annular groove array. The engine's revolution and the cutter's linear motion further cut the propellant into strips or blocks. The entire removal process achieves low-speed, high-efficiency propellant cleaning. Furthermore, this invention uses physical cutters for the removal operation, which is more environmentally friendly than high-pressure water cutting. The cut propellant can also be reused, avoiding the environmental problems associated with its disposal.
[0022] like Figure 1As shown, a physical cleaning device for a solid rocket motor includes a base 10 and a working platform 4 fixedly installed on the base 10. The working platform 4 is inclined and has a parallel slide rail 9. The parallel slide rail 9 has a tool feed mechanism 8, a first rocket motor slide rail 16, and a second rocket motor slide rail 17 arranged sequentially from high to low. The tool feed mechanism 8 has a tool conversion disc 11, on which a ring cutter 5 and a scraper 6 are fixedly connected. The second rocket motor slide rail 17 has an explosion-proof servo motor 19 and a second transmission gear 18, which is connected to a second rocket motor fixed chuck 13. The first rocket motor slide rail 16 has a first transmission gear 20, which is connected to a first rocket motor fixed chuck 12. The first and second fixed chucks are used to position the two ends of the rocket motor 2.
[0023] In actual use, by adjusting the distance between the first slide seat 16 and the second slide seat 17 of the rocket engine, and using the first fixed chuck 12 and the second fixed chuck 13 of the rocket engine, the two ends of the rocket engine 2 are positioned; by adjusting the tool conversion disc 11, the ring cutter 5 is aligned with the solid rocket engine 2 to be cleaned, and the ring cutter 5 is adjusted to the cutting position by the tool feed mechanism 8. The solid rocket engine physical cleaning device is started, and the device moves from the inner hole of the rocket engine 2 in a planetary compound motion, which drives the second transmission gear 1 through the explosion-proof servo motor 19. 8. The first transmission gear 20 rotates, thereby driving the rocket engine 2, which is fixed by the first fixed chuck 12 and the second fixed chuck 13 of the rocket engine, to rotate. That is, the rocket engine 2 revolves and the ring cutter 5 rotates, which quickly cuts the propellant into an array of rings, and then the ring cutter 5 is withdrawn. By adjusting the cutter conversion disc 11, the shovel 6 is aligned with the solid rocket engine 2 to be cleaned, and the solid rocket engine physical cleaning device is started. By using the revolution of the rocket engine 2 and the linear motion of the shovel 6, the ring-shaped propellant is cut into small pieces, thereby achieving low-speed and high-efficiency cleaning of the engine propellant. Example 2
[0024] Based on Embodiment 1, in this embodiment, preferably, a propellant discharge hole 14 is provided at the upper part of the rocket engine second slide seat 17 where it is connected to the rocket engine second fixed chuck 13, a propellant discharge groove 15 is provided below the propellant discharge hole 14, and a propellant collection box 1 is provided at the bottom of the propellant discharge groove 15.
[0025] In actual use, the cut propellant is recovered through the propellant collection box 1 and can be reused. Example 3
[0026] Based on Example 1, in this example, as Figure 2 As shown, preferably, the circumferential cutting blade 5 includes a circumferential cutting blade rod 51 and an isolation sleeve 54 installed on the outer surface of the circumferential cutting blade rod 51. A plurality of circumferential cutting blades 52 are fixedly arranged at equal distances on the outer side of the isolation sleeve 54. The isolation sleeve 54 is fastened to the circumferential cutting blade rod 51 by a clamping nut. The circumferential cutting blade rod 51 is hollow inside and has a circumferential cutting blade rod cold air channel 55. A plurality of through cold air holes 56 are distributed on the surface of the circumferential cutting blade rod 51 and the isolation sleeve 54. The cold air holes 56 communicate with the circumferential cutting blade rod cold air channel 55.
[0027] In actual use, the outer side of the isolation sleeve 54 is fixed with multiple circumferential cutting blades 52 that are evenly and parallelly distributed. These blades can quickly and simultaneously cut the propellant into a circumferential array from the engine's inner bore. Simultaneously, the circumferential cutting rod 51 is hollow and has a cooling air channel 55. Several through-holes 56 are distributed on the surfaces of the circumferential cutting rod 51 and the isolation sleeve 54, and these holes 56 communicate with the cooling air channel 55. During cutting, a continuous flow of moist, cold air is blown onto the cutting edge through the cooling air channel 55, keeping the cutting surface cool and moist and eliminating static electricity. Example 4
[0028] Based on Embodiment 3, in this embodiment, preferably, the distance between adjacent annular blades 52 of the circumferential cutter 5 is 50mm.
[0029] In actual use, the outer side of the isolation sleeve 54 is fixed with a plurality of parallel ring-cutting blades 52 that are equally spaced. The parallel ring-cutting blades 52 can quickly cut the propellant into a 50mm ring-slit array from the engine inner hole in one go. Example 5
[0030] Based on Example 1, in this example, as Figure 3 As shown, preferably, the shovel 6 includes a shovel shank 61 and a shovel head 62 installed at the end of the shovel shank 61. The shovel head 62 is provided with a three-sided blade 63 and a cooling air groove 64. The shovel shank 61 is provided with a shovel cooling air channel 65 inside, and the shovel cooling air channel 65 is connected to the cooling air groove 64.
[0031] In actual use, the scraper head 62 is equipped with a three-sided blade 63, which can cut the annular tablet into small pieces through linear movement. The scraper head 62 is equipped with a cooling air groove 64, and the blade shank 61 has a blade shank cooling air channel 65 inside, which is connected to the cooling air groove 64. During cutting, the blade shank cooling air channel 65 and the cooling air groove 64 can continuously blow moist and cold air onto the cutting edge of the blade, keeping the cutting surface in a cool and moist state and eliminating static electricity. Example 6
[0032] Based on Embodiment 1, in this embodiment, preferably, the tool feed mechanism 8 is further provided with a vortex cold air generator 12, and the air outlet of the vortex cold air generator 12 is connected to the cold air channel 55 of the circumferential cutting rod of the circumferential cutting blade 5 and the cold air channel 65 of the scraper rod of the scraper 6.
[0033] In actual use, the vortex cold air generator 12 continuously blows humid cold air to the cutting edge of the tool, and the compressed air is cooled to -10~0 degrees Celsius by the airflow vortex condenser, so that the cutting surface is in a cold and humid state, eliminating static electricity generated during the cutting process and reducing the temperature of the cutting surface. This achieves instant humidification and cooling during the cleaning process, eliminates static electricity, and ensures the safety of the cleaning process. Example 7
[0034] Based on Embodiment 1, in this embodiment, preferably, a plurality of safety pads 3 are provided on the parallel slide rail 9 below the rocket engine 2.
[0035] In actual use, the safety pad 3 prevents the elimination of static electricity generated by the rocket engine 2 during its revolution, ensuring the safety of the cleaning process. Example 8
[0036] Based on Embodiment 1, in this embodiment, preferably, the working platform 4 is tilted, with an angle of 15 to 90 degrees with the horizontal plane.
[0037] In actual use, the working platform 4 is tilted, with an angle of 15 to 90 degrees to the horizontal plane. When the rocket engine 2 is rotating, the propellant cut by the rocket engine 2 can be quickly discharged from the propellant discharge slot 15 below the propellant discharge hole 14 into the propellant collection box 1 due to gravity, thereby realizing the recovery of the propellant blocks after cutting. Example 9
[0038] A method for physical removal of propellants from a solid rocket motor, using any one of the solid rocket motor physical removal devices described in Examples 1-8 above, includes the following steps: S1: Install the solid rocket motor 2 to be cleaned on the solid rocket motor physical cleaning device; by adjusting the distance between the first slide seat 16 and the second slide seat 17 of the rocket motor, and using the first fixed chuck 12 and the second fixed chuck 13 of the rocket motor, position both ends of the rocket motor 2. S2: Adjust the tool conversion disc 11, align the ring cutter 5 with the solid rocket motor 2 to be cleaned, adjust the ring cutter 5 to the cutting position through the tool feed mechanism 8, start the solid rocket motor physical cleaning device, and drive the second transmission gear 18 and the first transmission gear 20 to rotate through the explosion-proof servo motor 19 from the inner hole of the rocket motor 2 in a planetary compound motion, thereby driving the rocket motor 2 fixed by the first fixed chuck 12 and the second fixed chuck 13 to rotate. That is, the rocket motor 2 revolves around the revolution plus the ring cutter 5 rotates, quickly cutting the propellant into a ring slit array, and then the ring cutter 5 is withdrawn. S3: Adjust the tool conversion disc 11, align the shovel 6 with the solid rocket motor 2 to be cleaned, start the solid rocket motor physical cleaning device, and use the revolution of the rocket motor 2 plus the linear motion of the shovel 6 to cut the ring-shaped drug tablet into small pieces. S4: Due to the tilted setting of the working platform 4, when the rocket engine 2 is rotating, the propellant cut by the rocket engine 2 in S3 is discharged from the propellant discharge groove 15 below the propellant discharge hole 14 into the propellant collection box 1 due to gravity, thus completing the propellant cleaning process.
[0039] In steps S2 and S3, the vortex cold air generator 12 on the tool feed mechanism 8 continuously blows humid cold air onto the cutting edge of the tool through the ring cutting bar cold air channel 55 and the scraper bar cold air channel 65, which are connected to the air outlet of the vortex cold air generator 12, so that the cutting surface is in a cold and humid state and static electricity is eliminated.
[0040] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.
Claims
1. A physical cleaning device for solid rocket motors, characterized in that: Includes a device base (10) and a work platform (4) fixedly mounted on the device base (10), wherein: The work platform (4) is inclined and has a parallel slide rail (9) on it. The parallel slide rail (9) is provided with a tool feed mechanism (8), a first slide rail seat (16) of the rocket engine and a second slide rail seat (17) of the rocket engine from high to low. The work platform (4) is inclined and the angle between it and the horizontal plane is 15 to 90 degrees. The tool feed mechanism (8) is provided with a tool conversion disc (11). A ring cutter (5) and a scraper (6) are fixedly connected on the tool conversion disc (11). The ring cutter (5) includes a ring cutter rod (51) and an isolation sleeve (54) installed on the outer surface of the ring cutter rod (51). Multiple ring cutter blades (52) are fixedly arranged at equal distances on the outer side of the isolation sleeve (54). The isolation sleeve (54) is fastened to the ring cutter rod (51) by a clamping nut. The ring cutter rod (51) is hollow inside and has a ring cutter rod cold air channel (55). A number of through cold air holes (56) are distributed on the surface of the ring cutter rod (51) and the isolation sleeve (54). The cold air holes (56) are connected to the ring cutter rod cold air channel (55). The second slide seat (17) of the rocket engine is equipped with an explosion-proof servo motor (19) and a second transmission gear (18). The second transmission gear (18) is connected to the second fixed chuck (13) of the rocket engine. The first slide seat (16) of the rocket engine is equipped with a first transmission gear (20). The first transmission gear (20) is connected to the first fixed chuck (12) of the rocket engine. The first fixed chuck (12) and the second fixed chuck (13) of the rocket engine are used to position the two ends of the rocket engine (2).
2. The physical cleaning device for a solid rocket motor according to claim 1, characterized in that: The upper part of the second slide seat (17) of the rocket engine is connected to the second fixed chuck (13) of the rocket engine and a propellant discharge hole (14) is provided. A propellant discharge groove (15) is provided below the propellant discharge hole (14) and a propellant collection box (1) is provided at the bottom of the propellant discharge groove (15).
3. The physical cleaning device for a solid rocket motor according to claim 1, characterized in that: The distance between adjacent circumferential cutting blades (52) of the circumferential cutting blade (5) is 50 mm.
4. The physical cleaning device for a solid rocket motor according to claim 1, characterized in that: The shovel (6) includes a shank (61) and a shovel head (62) installed at the end of the shank (61). The shovel head (62) is provided with a three-sided blade (63) and a cold air groove (64). The shank (61) is provided with a shank cold air channel (65) inside, and the shank cold air channel (65) is connected to the cold air groove (64).
5. The physical cleaning device for a solid rocket motor according to claim 1, characterized in that: The tool feed mechanism (8) is also equipped with a vortex cold air generator (12), and the air outlet of the vortex cold air generator (12) is connected to the cold air channel (55) of the ring cutting bar of the ring cutting knife (5) and the cold air channel (65) of the shovel bar of the shovel (6).
6. The physical cleaning device for a solid rocket motor according to claim 1, characterized in that: Several safety pads (3) are provided on the parallel slide rail (9) below the rocket engine (2).
7. A method for physical cleaning of propellants in a solid rocket motor, using any one of the physical cleaning devices for solid rocket motors as described in claims 1-6, characterized in that: Includes the following steps: S1: Install the solid rocket engine (2) to be cleaned on the solid rocket engine physical cleaning device; by adjusting the distance between the first slide seat (16) and the second slide seat (17) of the rocket engine, and using the first fixed chuck (12) and the second fixed chuck (13) of the rocket engine, position the two ends of the rocket engine (2); S2: Adjust the tool conversion plate (11), align the ring cutter (5) with the solid rocket motor (2) to be cleaned, adjust the ring cutter (5) to the cutting position through the tool feed mechanism (8), start the solid rocket motor physical cleaning device, and drive the second transmission gear (18) and the first transmission gear (20) to rotate through the explosion-proof servo motor (19) in a planetary compound motion from the inner hole of the rocket motor (2), thereby driving the rocket motor (2) fixed by the first fixed chuck (12) and the second fixed chuck (13) to rotate. That is, the rocket motor (2) revolves and the ring cutter (5) rotates, quickly cutting the propellant into a ring seam array, and then the ring cutter (5) is withdrawn. S3: Adjust the tool conversion disc (11), align the shovel (6) with the solid rocket motor (2) to be cleaned, start the solid rocket motor physical cleaning device, and use the revolution of the rocket motor (2) plus the linear motion of the shovel (6) to cut the ring-shaped drug tablet into small pieces. S4: Due to the tilt setting of the working platform (4), when the rocket engine (2) is rotating, the propellant cut by the rocket engine (2) in S3 is discharged from the propellant discharge groove (15) below the propellant discharge hole (14) to the propellant collection box (1) due to gravity, thus completing the propellant cleaning process.
8. The physical cleaning method for a solid rocket motor according to claim 7, characterized in that: In steps S2 and S3, the vortex cold air generator (12) provided on the tool feed mechanism (8) continuously blows humid cold air to the cutting edge of the tool through the ring cutting bar cold air channel (55) and the scraper bar cold air channel (65) connected to the air outlet of the vortex cold air generator (12), so that the cutting surface is in a cold and humid state and static electricity is eliminated.