CN113492221A - Solid rocket engine charging dissection method - Google Patents
Solid rocket engine charging dissection method Download PDFInfo
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- CN113492221A CN113492221A CN202110901650.3A CN202110901650A CN113492221A CN 113492221 A CN113492221 A CN 113492221A CN 202110901650 A CN202110901650 A CN 202110901650A CN 113492221 A CN113492221 A CN 113492221A
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- 239000007787 solid Substances 0.000 title claims abstract description 48
- 238000002224 dissection Methods 0.000 title claims abstract description 28
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000007493 shaping process Methods 0.000 claims abstract description 30
- 238000007789 sealing Methods 0.000 claims abstract description 11
- 238000005070 sampling Methods 0.000 claims abstract description 4
- 230000007704 transition Effects 0.000 claims description 65
- 239000002699 waste material Substances 0.000 claims description 14
- 239000003814 drug Substances 0.000 claims description 12
- 239000000843 powder Substances 0.000 claims description 10
- 239000002360 explosive Substances 0.000 claims description 6
- 229910052751 metal Inorganic materials 0.000 abstract description 4
- 239000002184 metal Substances 0.000 abstract description 4
- 210000003484 anatomy Anatomy 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000007599 discharging Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- DMFGNRRURHSENX-UHFFFAOYSA-N beryllium copper Chemical compound [Be].[Cu] DMFGNRRURHSENX-UHFFFAOYSA-N 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B27/00—Tools for turning or boring machines; Tools of a similar kind in general; Accessories therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B27/00—Tools for turning or boring machines; Tools of a similar kind in general; Accessories therefor
- B23B27/04—Cutting-off tools
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N1/00—Sampling; Preparing specimens for investigation
- G01N1/02—Devices for withdrawing samples
- G01N1/04—Devices for withdrawing samples in the solid state, e.g. by cutting
- G01N1/08—Devices for withdrawing samples in the solid state, e.g. by cutting involving an extracting tool, e.g. core bit
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B2200/00—Details of cutting inserts
- B23B2200/28—Angles
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- Engineering & Computer Science (AREA)
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- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Sampling And Sample Adjustment (AREA)
- Knives (AREA)
Abstract
The invention relates to a solid rocket engine charging dissection method, which comprises the steps of sampling solid rocket engine charging by using a solid rocket engine charging dissection knife group; the method specifically comprises the following steps: (a) clamping a solid rocket engine on a numerical control machine tool, and installing a charging dissection knife set of the solid rocket engine on a knife table; (b) cutting the end part by using an end face shaping knife to charge; (c) using an end face shaping cutter to cut the inner cavity along the axial direction for charging; (d) a sealing ring turning tool is used for axially pushing and cutting along the root part of the engine, and a charge part to be taken out is separated from the solid rocket engine shell; (e) cutting the part, which is away from the end face of the engine and has the required size, of the scheme in the radial direction by using a cutting knife, and cutting off the charge to be taken out; (f) the cylindrical charge sample was removed. The invention has high working efficiency, reduces the danger of operating personnel, and can sample the charge of the solid rocket engine under the condition of not damaging the metal shell structure of the engine.
Description
Technical Field
The invention belongs to the technical field of solid propellants, and particularly relates to a solid rocket engine charging dissection method.
Background
The solid rocket engine is an important part of rocket projectile equipment and has the characteristics of large army equipment quantity, high value and the like. After the solid rocket engine has or is about to reach the storage period given by a manufacturer, quality identification is needed to be carried out if the reliability and safety performance meet the requirements of battle technical indexes. Only if the sample inside the charge is taken out safely and reliably, the quality identification work such as charge physical and chemical performance test can be carried out. But the physical and chemical properties of the solid rocket engine charge stored in an overdue period are unknown, and the charge is positioned in the engine shell, so that the charge anatomy becomes a link with the highest risk degree and the highest difficulty coefficient in the quality identification work. Therefore, the method realizes the charge anatomy of the solid rocket engine and has great military economic benefits.
At present, the explosive charging dissection of the solid rocket engine adopts the field manual dissection or the form of destroying the engine shell, and the mode has the defects of low safety degree, low operation efficiency and high labor intensity.
Disclosure of Invention
The invention aims to provide a solid rocket engine charge dissection method which has high operation efficiency, reduces the danger of operators and can sample the charge of a solid rocket engine under the condition of not damaging the metal shell structure of the engine.
The invention adopts the following technical scheme:
a solid rocket engine charge dissection method comprises the steps of sampling solid rocket engine charges by using a solid rocket engine charge dissection knife group; the solid rocket engine explosive loading dissection knife tackle comprises an end face shaping knife, a sealing ring turning knife and a cutting knife;
the method specifically comprises the following steps:
(a) clamping a solid rocket engine on a numerical control machine tool, and installing a charging dissection knife set of the solid rocket engine on a knife table;
(b) after the cutter is adjusted, the personnel withdraw to the remote control room, the numerical control machine tool is started remotely, the end face shaping cutter is used for cutting end part powder charge, and a flat end part powder surface is obtained; after the machine is stopped, personnel enter the site to clean up the waste medicine;
(c) after the cutter is adjusted, the personnel withdraw to the remote control room, the numerical control machine tool is started remotely, the end face shaping cutter is used for cutting the inner cavity along the axial direction to charge the powder, so that a smooth inner cavity powder surface is obtained, and meanwhile, enough space is provided for the cutting-off cutter to cut off; after the machine is stopped, personnel enter the site to clean up the waste medicine;
(d) after the cutter is adjusted, people withdraw to a remote control room, the numerical control machine tool is started remotely, the sealing ring turning cutter is used for pushing and cutting along the axial direction of the root of the engine, and the charge part to be taken out is separated from the shell of the solid rocket engine; after the machine is stopped, personnel enter the site to clean up the waste medicine;
(e) after the tool is set, people withdraw to a remote control room, remotely start the numerical control machine, cut off the part, which is away from the end face of the engine and has the required size, of the scheme by using a cutting-off tool along the radial direction, and cut off the charge to be taken out; after the machine is stopped, personnel enter the site to clean up the waste medicine;
(f) the cylindrical charge sample was removed.
The end face reshaping knife comprises a reshaping knife handle with a square cross section and a reshaping knife head arranged at the end part of the reshaping knife handle, wherein the reshaping knife head is formed by enclosing a first inclined side face, a first top face, a first end face, a first bottom face and a first transition face; the intersection line of the first side inclined plane, the first end face and the first bottom face is a shaping cutter head edge part, the included angle between the first inclined side face and the vertical direction and the included angle between the first bottom face and the horizontal direction are both 8 degrees, and the included angle between the first end face and the vertical direction is 5 degrees; the included angle between the first top surface and the horizontal plane is 45 degrees, and the first top surface is in transition connection with the top of the shaping tool handle through an arc; the cutting part of the reshaping cutter head is parallel to the bottom surface of the reshaping cutter handle and is lower than the bottom surface of the reshaping cutter handle.
Wherein, the turning cutting edge part is provided with a triangular notch.
The top surfaces of the turning tool handle and the excessive long handle are arranged on the same horizontal plane in an integrated mode.
The transition long handle comprises a first transition handle, a second transition handle and a third transition handle which are connected in sequence, the front end of the first transition handle is fixedly connected with the tail end of the turning tool bit, and the tail end of the third transition handle is fixedly connected with the turning tool handle. The first transition handle is a right-angle trapezoidal frustum. The second transition handle is a cuboid. The third transition handle is a frustum of a square cone.
The small bottom surface of the first transition handle is the same as the tail end surface of the turning tool bit, and the two end surfaces of the second transition handle are respectively the same as the large bottom surface of the first transition handle and the small bottom surface of the third transition handle; the large bottom surface of the third transition handle is the same as the end surface of the turning tool handle.
The sealing ring turning tool comprises a turning tool handle, a transition long handle and a turning tool bit, wherein the turning tool bit comprises two symmetrically arranged second inclined side surfaces, a second bottom surface, a second end surface and a second top surface, the second bottom surface, the second end surface and the second top surface are respectively used for connecting the bottom end, the front end and the top end of the two second inclined side surfaces, the second top surface comprises a turning front top surface connected with the second end surface and a turning rear top surface connected with the top surface of the transition long handle, and the cutting edge part of the turning tool bit is formed by the intersection line of the turning front top surface and the second end surface; the included angle between the second end face and the vertical direction is 30 degrees, and the included angle between the top face and the second end face before turning is 45 degrees.
The cutting-off tool comprises a cutting-off tool shank, a transition square frustum, a connecting long handle, a straight arm perpendicular to the connecting long handle and a cutting-off tool bit arranged at the end part of the straight arm; the cutting tool bit comprises two symmetrically arranged third oblique side surfaces, a third bottom surface, a third end surface and a third top surface, wherein the third bottom surface, the third end surface and the third top surface are respectively used for connecting the bottom end, the front end and the top end of the two third oblique side surfaces; the included angle between the third end face and the horizontal direction is 30 degrees, and the included angle between the top face and the third end face before cutting is 45 degrees.
The invention has the beneficial effects that: the invention provides a remote explosive charge dissection technology for a solid rocket engine, which realizes remote internal explosive charge sampling of the solid rocket engine (without damaging the metal shell structure of the engine), eliminates potential safety hazards existing in the modes of manual on-site dissection or dissection by destroying the shell of the engine and the like, improves the operation efficiency, reduces the labor intensity and realizes man-machine isolation of dangerous operation.
Drawings
Fig. 1 is a schematic structural view of an end face truing knife.
Fig. 2 is a left side view of the structure of fig. 1.
Fig. 3 is a schematic structural view of a seal ring turning tool.
Fig. 4 is a schematic top view of fig. 3.
Fig. 5 is a schematic cross-sectional view a-a of the turning insert of fig. 4.
Fig. 6 is a schematic structural view of the cutting blade.
Fig. 7 is a schematic top view of the structure of fig. 6.
Fig. 8 is a left side view of the structure of fig. 6.
Figure 9 is a view of the anatomy of the present invention.
The solid rocket engine comprises a shaping cutter handle 1, a first inclined side face 2, a first top face 3, a first end face 4, a first bottom face 5, a first transition face 6, a turning cutter handle 7, a second inclined side face 8, a second bottom face 9, a second end face 10, a turning front top face 11, a turning rear top face 12, a triangular notch 13, a first transition handle 14, a second transition handle 15, a third transition handle 16, a cutting cutter handle 17, a transition square frustum 18, a connecting long handle 19, a straight arm 20, a third inclined side face 21, a third bottom face 22, a third end face 23, a cutting front top face 24, a cutting rear top face 25 and a solid rocket engine 26.
Detailed Description
The invention will be further illustrated with reference to specific embodiments. It should be understood that these examples are for illustrative purposes only and are not intended to limit the scope of the present invention.
Example 1
The solid rocket engine explosive loading dissection knife tackle comprises an end face shaping knife, a sealing ring turning knife and a cutting knife. The end face shaping cutter, the sealing ring turning cutter and the cutting cutter are all made of non-sparking beryllium copper materials.
As shown in fig. 1 to 2, the end face reshaping knife includes a reshaping knife handle 1 with a square cross section and a reshaping knife head arranged at an end of the reshaping knife handle 1, the reshaping knife head is formed by enclosing a first inclined side face 2, a first top face 3, a first end face 4, a first bottom face 5 and a first transition face 6, a front end of the first top face 3 is connected with the first end face 4, one side of the first top face 3 and one side of the first end face 4 are connected with the first inclined side face 2, a front end of the first bottom face 5 is connected with the first end face 4, a side end of the first bottom face 5 is connected with the first inclined side face 2, and the other side of the first bottom face 5 is connected with the first top face 3 through the first transition face 6; the intersection line of the first side inclined plane 2, the first end face 4 and the first bottom face 5 is a shaping cutter head edge part, the included angle between the first inclined side face 2 and the vertical direction and the included angle between the first bottom face 5 and the horizontal direction are both 8 degrees, and the included angle between the first end face 4 and the vertical direction is 5 degrees; the included angle between the first top surface 3 and the horizontal plane is 45 degrees, and the first top surface is in transition connection with the top of the shaping tool handle 1 through an arc; the cutting part of the shaping cutter head is parallel to the bottom surface of the shaping cutter handle 1 and is lower than the bottom surface of the shaping cutter handle 1. The first transition surface is beneficial to discharging waste materials in the turning process and preventing blockage.
As shown in fig. 3 to 5, the sealing ring turning tool includes a turning tool holder 7, a transition long handle and a turning tool bit, the turning tool bit includes two symmetrically arranged second inclined side surfaces 8, a second bottom surface 9, a second end surface 10 and a second top surface, the second bottom surface 9, the second end surface 10 and the second top surface are respectively used for connecting the bottom end, the front end and the top end of the two second inclined side surfaces 8, the second top surface includes a turning front top surface 11 connected with the second end surface 10 and a turning rear top surface 12 connected with the top surface of the transition long handle, and the intersection line of the turning front top surface 11 and the second end surface 10 forms a cutting part of the turning tool bit; the included angle between the second end face 10 and the vertical direction is 30 degrees, and the included angle between the turning front top face 11 and the second end face 10 is 45 degrees.
The turning blade part is provided with a triangular notch 13. The triangular notch is beneficial to discharging waste materials in the turning process, and blockage is prevented and treated.
The top surfaces of the turning tool handle 7 and the excessively long handle are arranged on the same horizontal plane in an integrated mode.
The transition long handle comprises a first transition handle 14, a second transition handle 15 and a third transition handle 16 which are connected in sequence, the front end of the first transition handle 14 is fixedly connected with the tail end of the turning tool bit, and the tail end of the third transition handle 16 is fixedly connected with the turning tool handle 7. The first transition handle 14 is a right-angled trapezoidal frustum. The second transition handle 15 is a cuboid. The third transition shank 16 is a frustum of a square pyramid.
The small bottom surface of the first transition handle 14 is the same as the tail end surface of the turning tool bit, and the two end surfaces of the second transition handle 15 are respectively the same as the large bottom surface of the first transition handle 14 and the small bottom surface of the third transition handle 16; the big bottom surface of the third transition handle 16 is the same as the end surface of the turning tool holder 7.
As shown in fig. 6 to 8, the cutting-off tool comprises a cutting-off tool shank 17, a transition frustum 18, a connecting long shank 19, a straight arm 20 perpendicular to the connecting long shank 19, and a cutting-off tool bit arranged at the end of the straight arm 20; the cutting-off cutter head comprises two third inclined side surfaces 21 which are symmetrically arranged, a third bottom surface 22, a third end surface 23 and a third top surface which are respectively used for connecting the bottom end, the front end and the top end of the two third inclined side surfaces 21, wherein the third top surface comprises a cutting front top surface 24 connected with the third end surface 23 and a cutting rear top surface 25 connected with the top surface of the straight arm 20, and the intersection line of the cutting front top surface 24 and the third end surface 23 forms a cutting-off cutter head edge part; the third end surface 23 forms an angle of 30 ° with the horizontal direction, and the top surface 24 forms an angle of 45 ° with the third end surface 23 before cutting.
Example 2
The solid rocket engine charge is remotely dissected by utilizing the dissecting knife set in the embodiment 1, namely, the solid rocket engine charge is sampled on the premise of not damaging the metal shell structure of the engine.
The method specifically comprises the following steps:
(1) the solid rocket engine 26 is clamped on a numerical control machine tool, and the solid rocket engine charging dissection knife set is arranged on the knife table.
(2) After the cutter is adjusted, the personnel withdraw to a remote control room, remotely start the numerical control machine, use the shaping knife of end face to cut the end charge (area of figure 9), get the smooth end charge surface; after the machine is stopped, personnel enter the site to clean up the waste medicine.
(3) After the cutter is adjusted, the personnel withdraw to a remote control room, the numerical control machine tool is started remotely, the end face shaping cutter is used for cutting inner cavity powder charge (region II in figure 9) along the axial direction, a flat inner cavity powder charge surface is obtained, and meanwhile, enough space is provided for the cutting-off cutter to cut off; after the machine is stopped, personnel enter the site to clean up the waste medicine.
(4) After the cutter is adjusted, people withdraw to a remote control room, the numerical control machine is started remotely, a sealing ring turning cutter is used for axially pushing and cutting along the root part (close to the heat insulation layer) of the engine (area III in figure 9), and a charge part needing to be taken out is separated from the shell of the solid rocket engine; after the machine is stopped, personnel enter the site to clean up the waste medicine.
(5) After the tool is set, the personnel withdraw to a remote control room, the numerical control machine tool is started remotely, the cutting-off tool is used for cutting along the radial direction at the position (area (r) in fig. 9) with the required size away from the scheme of the end surface of the engine, and the charge to be taken out is cut off; after the machine is stopped, personnel enter the site to clean up the waste medicine.
(6) The cylindrical charge sample was removed.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A solid rocket engine charge dissection method is characterized in that a solid rocket engine charge scalpel group is used for sampling solid rocket engine charges; the solid rocket engine explosive loading dissection knife tackle comprises an end face shaping knife, a sealing ring turning knife and a cutting knife;
the method specifically comprises the following steps:
(a) clamping a solid rocket engine on a numerical control machine tool, and installing a charging dissection knife set of the solid rocket engine on a knife table;
(b) after the cutter is adjusted, the personnel withdraw to the remote control room, the numerical control machine tool is started remotely, the end face shaping cutter is used for cutting end part powder charge, and a flat end part powder surface is obtained; after the machine is stopped, personnel enter the site to clean up the waste medicine;
(c) after the cutter is adjusted, the personnel withdraw to the remote control room, the numerical control machine tool is started remotely, the end face shaping cutter is used for cutting the inner cavity along the axial direction to charge the powder, so that a smooth inner cavity powder surface is obtained, and meanwhile, enough space is provided for the cutting-off cutter to cut off; after the machine is stopped, personnel enter the site to clean up the waste medicine;
(d) after the cutter is adjusted, people withdraw to a remote control room, the numerical control machine tool is started remotely, the sealing ring turning cutter is used for pushing and cutting along the axial direction of the root of the engine, and the charge part to be taken out is separated from the shell of the solid rocket engine; after the machine is stopped, personnel enter the site to clean up the waste medicine;
(e) after the tool is set, people withdraw to a remote control room, remotely start the numerical control machine, cut off the part, which is away from the end face of the engine and has the required size, of the scheme by using a cutting-off tool along the radial direction, and cut off the charge to be taken out; after the machine is stopped, personnel enter the site to clean up the waste medicine;
(f) the cylindrical charge sample was removed.
2. The solid rocket engine charge dissection method according to claim 1, wherein the end face shaping cutter comprises a shaping cutter handle (1) with a square cross section and a shaping cutter head arranged at the end of the shaping cutter handle (1), the shaping cutter head is formed by enclosing a first inclined side face (2), a first top face (3), a first end face (4), a first bottom face (5) and a first transition face (6), the front end of the first top face (3) is connected with the first end face (4), one side of the first top face (3) and the first end face (4) is connected with the first inclined side face (2), the front end of the first bottom face (5) is connected with the first end face (4), the side end of the first bottom face (5) is connected with the first inclined side face (2), and the other side of the first bottom face (5) is connected with the first top face (3) through the first transition face (6); the intersection line of the first side inclined plane (2), the first end face (4) and the first bottom face (5) is a shaping cutter head edge part, the included angle between the first inclined side face (2) and the vertical direction and the included angle between the first bottom face (5) and the horizontal direction are both 8 degrees, and the included angle between the first end face (4) and the vertical direction is 5 degrees; the included angle between the first top surface (3) and the horizontal plane is 45 degrees, and the first top surface is in transition connection with the top of the shaping cutter handle (1) through an arc; the cutting part of the shaping cutter head is parallel to the bottom surface of the shaping cutter handle (1) and is lower than the bottom surface of the shaping cutter handle (1).
3. A solid rocket engine charge dissection method according to claim 2, wherein the turning blade is provided with a triangular notch (13).
4. The solid rocket engine charging dissection method according to claim 3, characterized in that the top surfaces of the turning cutter handle (7) and the over-length handle are arranged in a same horizontal plane and in an integrated manner.
5. The solid rocket engine charging dissection method according to claim 4, characterized in that the transition long handle comprises a first transition handle (14), a second transition handle (15) and a third transition handle (16) which are connected in sequence, the front end of the first transition handle (14) is fixedly connected with the tail end of the turning cutter head, and the tail end of the third transition handle (16) is fixedly connected with the turning cutter handle (7); the first transition handle (14) is a right-angle trapezoidal frustum; the second transition handle (15) is a cuboid; the third transition handle (16) is a frustum of a square cone.
6. A solid rocket engine charge dissection method according to claim 5, characterized in that the small base of the first transition shank (14) is identical to the trailing face of the turning bit, and the two end faces of the second transition shank (15) are respectively identical to the large base of the first transition shank (14) and the small base of the third transition shank (16); the large bottom surface of the third transition handle (16) is the same as the end surface of the turning tool holder (7).
7. The solid rocket engine charge dissection method according to claim 1, wherein the sealing ring turning tool comprises a turning tool shank (7), a long transition shank and a turning tool bit, the turning tool bit comprises two symmetrically arranged second inclined side surfaces (8), a second bottom surface (9) for respectively connecting the bottom end, the front end and the top end of the two second inclined side surfaces (8), a second end surface (10) and a second top surface, the second top surface comprises a front turning top surface (11) connected with the second end surface (10) and a rear turning top surface (12) connected with the top surface of the long transition shank, and the intersection line of the front turning top surface (11) and the second end surface (10) forms a turning tool bit edge part; the included angle between the second end face (10) and the vertical direction is 30 degrees, and the included angle between the turning front top face (11) and the second end face (10) is 45 degrees.
8. The solid rocket engine charge dissection method according to claim 1, wherein the cutting knife comprises a cutting knife handle (17), a transition frustum pyramid (18), a connecting long handle (19), a straight arm (20) perpendicular to the connecting long handle (19) and a cutting knife head arranged at the end part of the straight arm (20); the cutting tool bit comprises two third inclined side surfaces (21) which are symmetrically arranged, a third bottom surface (22), a third end surface (23) and a third top surface, wherein the third bottom surface (22), the third end surface (23) and the third top surface are respectively used for connecting the bottom end, the front end and the top end of the two third inclined side surfaces (21), the third top surface comprises a cutting front top surface (24) connected with the third end surface (23) and a cutting rear top surface (25) connected with the top surface of the straight arm (20), and the cutting tool bit edge part is formed by the intersection line of the cutting front top surface (24) and the third end surface (23); the included angle between the third end face (23) and the horizontal direction is 30 degrees, and the included angle between the cutting front top face (24) and the third end face (23) is 45 degrees.
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| CN207960778U (en) * | 2018-01-05 | 2018-10-12 | 西安北方惠安化学工业有限公司 | A kind of useless medicine cleaning plant of engine interior |
| CN112518327A (en) * | 2020-11-16 | 2021-03-19 | 上海航天化工应用研究所 | Solid rocket engine dissection device and method |
| CN113111552A (en) * | 2021-04-08 | 2021-07-13 | 内蒙动力机械研究所 | Solid rocket engine grain structural integrity analysis modeling method |
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