CN113931762A - Assembly device and process for internal snap ring type solid rocket engine - Google Patents
Assembly device and process for internal snap ring type solid rocket engine Download PDFInfo
- Publication number
- CN113931762A CN113931762A CN202111180798.9A CN202111180798A CN113931762A CN 113931762 A CN113931762 A CN 113931762A CN 202111180798 A CN202111180798 A CN 202111180798A CN 113931762 A CN113931762 A CN 113931762A
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- snap ring
- combustion chamber
- ring
- assembling
- extrusion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P21/00—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
- B23P21/002—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control the units stationary whilst being composed
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Automatic Assembly (AREA)
Abstract
The invention provides an internal snap ring type solid rocket engine assembly device and a process, and specifically comprises the following steps: step S1, assembling a front seal head and a front medicine baffle plate; step S2, assembling a front seal head and charging; the front end enclosure and the charging are assembled on a powder column die closing tool, and the external diameter of the charging is limited by two die closing half rings; step S3, assembling a rear medicine baffle plate; step S4, assembling a combustion chamber; assembling the combustion chamber and the front end enclosure subjected to the step S3 on a combustion chamber pressure tool; step S5, assembling a snap ring; the combustion chamber and the snap ring subjected to the step S4 are assembled on the snap ring extruding tool; and step S6, assembling the initiating explosive device. The final assembly device and the final assembly process greatly shorten the assembly time of products, improve the assembly quality and the assembly efficiency of the products, eliminate the potential safety hazards of assembly of operators, save the labor cost, and can complete the assembly work by only 1 assembler at least.
Description
Technical Field
The invention belongs to the field of solid rocket engines, relates to rocket engine assembly, and particularly relates to an inner snap ring type solid rocket engine assembly device and process.
Background
The solid rocket engine with internal clamping ring mainly comprises a front end socket, a front medicine baffle plate, a medicine column, a combustion chamber, a rear medicine baffle plate, a sealing ring, a clamping ring and other parts. Wherein, the connection mode between combustion chamber and the preceding head is the connection of interior snap ring formula. During the assembly process of the solid rocket engine, three difficulties mainly exist:
first, the powder charge is free filling formula, many root canal shape medicine, and the combustion chamber with many with tubular charge assembling process, because arrange comparatively loose, lack the restraint between the charge, hardly arrange according to the design condition homogeneous alignment to an ideal circular to cause combustion chamber internal diameter and the mismatch of the biggest external diameter of powder charge two, the phenomenon that the powder charge hardly gets into the combustion chamber often appears.
Secondly, in the assembling process of the front end enclosure and the combustion chamber, the sealing ring is arranged at the position of the sealing groove of the front end enclosure, so that the maximum outer diameter of the front end enclosure is increased, and the sealing ring part of the front end enclosure is difficult to press into the combustion chamber in the process of pressing the front end enclosure into the combustion chamber. In addition, because the engine is connected for interior snap ring formula, the combustion chamber has the snap ring groove structure, even the preceding head barely gets into in the combustion chamber, in case the sealing washer moves combustion chamber snap ring groove department, the axial motion resistance between preceding head and the combustion chamber barrel section will greatly increased in the twinkling of an eye. In the assembling process, the front seal head is often clamped at the position of the clamping ring groove of the combustion chamber, and the phenomenon of difficult advancing and retreating occurs, so that assembling work is not stopped, and sometimes an assembling worker even has to use brute force, so that the sealing ring is damaged, and the assembling fails.
Thirdly, in the process of assembling the snap ring, because the snap ring is a linear metal part, the snap ring can be forcibly assembled into the engine snap ring groove only by adopting a strong knocking process. The dynamics of knocking often appears in this in-process and controls improperly, causes snap ring local fracture, rolls over in combustion chamber snap ring inslot, in involving the fire operation in addition, strikes technology and brings the potential safety hazard easily, also can bring certain potential safety hazard to the assembler.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an inner snap ring type solid rocket engine assembly device and process, and solve the technical problem that the assembly efficiency and safety of the assembly process in the prior art need to be further improved.
In order to solve the technical problems, the invention adopts the following technical scheme:
an inner snap ring type solid rocket engine assembly device comprises a grain die assembly tool, a combustion chamber compression tool and a snap ring extrusion tool;
the explosive column die-closing tool comprises two die-closing half rings which can be assembled together and have the same structure, the inner walls of the two die-closing half rings are divided into a front sealing head section and a powder charging section along the axial direction, a sealing ring groove is formed in the position, close to the powder charging section, of the front sealing head section, the inner diameter of the sealing ring groove is larger than that of the front sealing head section, and the inner diameter of the front sealing head section is larger than that of the powder charging section;
the combustion chamber compression tool comprises an annular upper disc and an annular lower disc which are parallelly, coaxially and relatively fixedly arranged, a compression cylinder is arranged between the upper disc and the lower disc, two ends of the compression cylinder are open and are in a stepped cylindrical shape, the caliber of the top end of the compression cylinder is smaller than that of the bottom end of the compression cylinder, and a shaft shoulder is arranged at the upper part, close to the top end, of the compression cylinder;
the edge of the inner ring of the upper disc is provided with a pressure ring cylinder seat which is axially and upwards protruded, a pressure ring is arranged in the pressure ring cylinder seat, and the bottom end of the pressure ring can be pressed on a shaft shoulder of the pressure cylinder;
the combustion chamber is placed in the pressing cylinder, the bottom end of the pressing cylinder is limited and installed in the combustion chamber through a pair of snap ring inlet limiting half rings which are assembled together, a snap ring inlet plug is arranged on the inner wall of each snap ring inlet limiting half ring, and the snap ring inlet plug is embedded into a snap ring inlet formed in the side wall of the combustion chamber;
and the lower disc is used for placing a front seal head and charge combination aligned with the combustion chamber.
The clamping ring extrusion tool comprises a base, wherein a pair of combustion chamber fixed semi-rings are arranged on the base; the base is detachably provided with a snap ring frame, the snap ring frame is provided with snap ring guide grooves, the snap ring guide grooves are perpendicular to the central axis of the combustion chamber fixed by the combustion chamber fixed semi-rings, and the inner ends of the snap ring guide grooves are aligned with the snap ring inlets of the combustion chamber; an extrusion base is fixedly arranged on the snap ring frame at the outer end of the snap ring guide groove, an extrusion rod is installed on the extrusion base, the inner end of the extrusion rod is propped against a snap ring extrusion sliding block used for extruding the snap ring to enter the snap ring inlet, and an extrusion key at the bottom of the snap ring extrusion sliding block is clamped into the snap ring guide groove and used for extruding the snap ring to move.
The invention also has the following technical characteristics:
the two die closing half rings, the pair of snap ring inlet limiting half rings and the pair of combustion chamber fixing half rings are respectively and correspondingly provided with connecting lug seats, and the connecting lug seats are connected through bolts.
The inner ring edge of the lower disc is provided with a bottom cylinder seat which is axially and downwards protruded; the upper disc and the lower disc are fixedly supported through a plurality of stud bolts.
The clamping ring and the clamping ring barrel seat are installed in a threaded fit mode, and a first rotating rod is arranged at the top end of the clamping ring.
The extrusion rod and the extrusion base are installed in a threaded fit mode, and a second rotating rod is arranged at the outer end of the extrusion rod.
The base on seted up a plurality of screw thread mounting holes, all can be through the detachable installation snap ring frame of countersunk screw on every screw thread mounting hole.
The invention also provides an assembly process of the internal snap ring type solid rocket engine, which adopts the assembly device of the internal snap ring type solid rocket engine.
Specifically, the process comprises the following steps:
step S1, assembling a front seal head and a front medicine baffle plate;
step S2, assembling a front seal head and charging;
the front end enclosure and the charging are assembled on a powder column die closing tool, and the external diameter of the charging is limited by two die closing half rings;
step S3, assembling a rear medicine baffle plate;
step S4, assembling a combustion chamber;
assembling the combustion chamber and the front end enclosure subjected to the step S3 on a combustion chamber pressure tool;
step S5, assembling a snap ring;
the combustion chamber and the snap ring subjected to the step S4 are assembled on the snap ring extruding tool;
and step S6, assembling the initiating explosive device.
Compared with the prior art, the invention has the following technical effects:
the final assembly device and the process can be used in the assembly process of the inner snap ring type solid rocket engine, so that the assembly quality and the assembly efficiency of the engine are improved, and the safety risk in the assembly process is reduced.
(II) the final assembly device and the final assembly process greatly shorten the assembly time of the product, improve the assembly quality and the assembly efficiency of the product, eliminate the assembly potential safety hazard of operators, save the labor cost, and can complete the assembly work by only 1 assembler at least.
Drawings
Fig. 1 is a front view structure schematic diagram of a grain die assembly tool.
Fig. 2 is a schematic top view of the powder column clamping tool.
FIG. 3 is a schematic front view of the pressure extension fixture of the combustion chamber.
FIG. 4 is a schematic top view of the combustor press-extension fixture.
Fig. 5 is a front structural schematic view of the snap ring extrusion tool.
FIG. 6 is a schematic top view of a snap ring extrusion tooling.
FIG. 7 is a flow chart of the final assembly process of the present invention.
The meaning of the individual reference symbols in the figures is: 1-a grain die assembly tool, 2-a combustion chamber compression tool and 3-a clamp ring extrusion tool;
101-mold closing half ring, 102-front sealing head section, 103-charge section and 104-sealing ring groove;
201-upper disc, 202-lower disc, 203-pressing cylinder, 204-shaft shoulder, 205-pressing cylinder seat, 206-pressing ring, 207-clamping ring inlet limiting half ring, 208-clamping ring inlet plug, 209-bottom cylinder seat, 210-first rotating rod and 211-stud bolt;
301-base, 302-combustion chamber stationary half ring, 303-snap ring frame, 304-snap ring guide groove, 305-extrusion base, 306-extrusion rod, 307-snap ring extrusion slide block, 308-second rotation rod, 309-thread installation hole, 310-extrusion key.
The present invention will be explained in further detail with reference to examples.
Detailed Description
The inner snap ring type solid rocket engine comprises a front end socket, a front medicine baffle plate, a medicine charge part, a rear medicine baffle plate, a combustion chamber, a snap ring, a sealing ring and other parts, wherein the parts are known parts.
The present invention is not limited to the following embodiments, and all equivalent changes based on the technical solutions of the present invention fall within the protection scope of the present invention.
Example 1:
the embodiment provides an assembly device of an internal clamping ring type solid rocket engine, which comprises a grain die assembly tool 1, a combustion chamber pressure extension tool 2 and a clamping ring extrusion tool 3;
the powder column die-closing tool 1 comprises two die-closing half rings 101 which can be assembled together and have the same structure, wherein the inner walls of the two die-closing half rings 101 are divided into a front head sealing section 102 and a powder charging section 103 along the axial direction, a sealing ring groove 104 is formed in the position, close to the powder charging section 103, of the front head sealing section 102, the inner diameter of the sealing ring groove 104 is larger than that of the front head sealing section 102, and the inner diameter of the front head sealing section 102 is larger than that of the powder charging section 103;
as shown in fig. 3 and 4, the combustion chamber compression and extension tool 2 comprises an annular upper disc 201 and an annular lower disc 202 which are parallel, coaxial and relatively fixedly arranged, a compression cylinder 203 is arranged between the upper disc 201 and the lower disc 202, two ends of the compression cylinder 203 are open and are in a stepped cylindrical shape, the caliber of the top end of the compression cylinder 203 is smaller than that of the bottom end, and a shaft shoulder 204 is arranged at the upper part, close to the top end, of the compression cylinder 203;
the edge of the inner ring of the upper disc 201 is provided with a pressure ring cylinder seat 205 which is axially and upwards protruded, a pressure ring 206 is arranged in the pressure ring cylinder seat 205, and the bottom end of the pressure ring 206 can be pressed on a shaft shoulder 204 of the pressure cylinder 203;
the combustion chamber is placed in the pressing cylinder 203, the combustion chamber is limited and installed at the bottom end of the pressing cylinder 203 through a pair of snap ring inlet limiting half rings 207 which are assembled together, a snap ring inlet plug 208 is arranged on the inner wall of each snap ring inlet limiting half ring 207, and the snap ring inlet plug 208 is embedded into a snap ring inlet formed in the side wall of the combustion chamber;
the lower disc 202 is used for placing a front seal head and charge combination aligned with the combustion chamber;
as shown in fig. 5 and 6, the clamping ring extrusion tooling 3 comprises a base 301, wherein a pair of combustion chamber stationary half rings 302 are arranged on the base 301; a snap ring frame 303 is detachably mounted on the base 301, a snap ring guide groove 304 is formed in the snap ring frame 303, the snap ring guide groove 304 is perpendicular to the central axis of the combustion chamber fixed by the pair of combustion chamber fixed half rings 302, and the inner end of the snap ring guide groove 304 is aligned with a snap ring inlet of the combustion chamber; an extrusion base 305 is fixedly arranged on the snap ring frame 303 at the outer end of the snap ring guide groove 304, an extrusion rod 306 is installed on the extrusion base 305, the inner end of the extrusion rod 306 is propped against a snap ring extrusion sliding block 307 for extruding the snap ring to enter the snap ring inlet, and an extrusion key 310 at the bottom of the snap ring extrusion sliding block 307 is clamped into the snap ring guide groove (304) for extruding the snap ring to move.
As a preferable scheme of the present embodiment, the two mold closing half rings 101, the pair of snap ring inlet limit half rings 207, and the pair of combustion chamber stationary half rings 302 are respectively provided with connecting lug seats, and the connecting lug seats are connected by bolts.
As a preferable scheme of this embodiment, the inner ring edges of the lower disc 202 are each provided with a bottom cylindrical seat 209 protruding downward in the axial direction, and the upper disc 201 and the lower disc 202 are fixedly supported by a plurality of stud bolts 211. It is ensured that the lower plate 202 can be stably placed on the table without the table coming into contact with the plurality of stud bolts 211.
As a preferable scheme of this embodiment, the pressing ring 206 and the pressing ring cylinder base 205 are installed in a screw-fit manner, and the top end of the pressing ring 206 is provided with a first rotating rod 210. The screw thread is more stable in rotation and pressing, and the controllability is stronger.
As a preferable scheme of this embodiment, the pressing rod 306 and the pressing base 305 are installed by screw-fitting, and a second rotating rod 308 is provided on the outer end of the pressing rod 306. The screw thread rotary extrusion is more stable, and the controllability is stronger.
As a preferable scheme of this embodiment, the base 301 has a plurality of threaded mounting holes 309, and each threaded mounting hole 309 can detachably mount the snap ring frame 303 through a countersunk screw. The mounting position of the snap ring frame 303 can be selected according to actual requirements.
Example 2:
the embodiment provides an assembly process of an internal snap ring type solid rocket engine, which adopts the assembly device of the internal snap ring type solid rocket engine in the embodiment.
Specifically, the process comprises the following steps:
step S1, assembling a front seal head and a front medicine baffle plate;
the specific process of step S1 is: and (3) sleeving a sealing ring into a sealing groove of the front end enclosure, vertically erecting the front end enclosure on an antistatic worktable, and slowly sleeving a front medicine baffle into the front end enclosure from the upper part.
Step S2, assembling a front seal head and charging;
the front sealing head and the charge are assembled on the charge column die assembly tool 1, and the outer diameter of the charge is limited by the two die assembly half rings 101;
the specific process of step S2 is: and taking out the explosive column die-closing tool 1, assembling the two die-closing half rings 101 with the front end enclosure along the horizontal direction respectively, fixing the two die-closing half rings 101 by using bolts, and uniformly arranging the explosive columns along the inner diameters of the die-closing half rings 101 in sequence and the circumferential direction to control the maximum outer diameter of the explosive charges within the inner diameter of the die-closing half rings 101.
Step S3, assembling a rear medicine baffle plate;
the specific process of step S3 is: the rear medicine baffle plate is arranged at the rear end of the medicine filling.
Step S4, assembling a combustion chamber;
assembling the combustion chamber and the front end enclosure subjected to the step S3 on the combustion chamber pressure tool 2;
the specific process of step S4 is: taking out the combustion chamber pressure extension tool 2, sleeving the pressure cylinder 203 on the combustion chamber, taking care that the positions of a clamp ring inlet of the combustion chamber and a clamp ring inlet plug 208 on a clamp ring inlet limiting half ring 207 are consistent, surrounding a pair of clamp ring inlet limiting half rings 207 outside the pressure cylinder 203, and embedding the clamp ring inlet plug 208 into the clamp ring inlet of the combustion chamber; then the combination body of the pressing cylinder 203 and/or the combustion chamber is lifted and slowly sleeved into the combination body of the front seal head and the explosive from top to bottom; and then the explosive column die assembly tool 1 is removed, the lower disc 202 is integrally placed, and the front end enclosure is limited by utilizing the matching relation between the inner diameter of the lower disc 202 and the front end enclosure. Through a plurality of stud bolts 211 installation hanging wall 201 on lower wall 202, slow screw in clamping ring barrel holder 205 to the clamping ring, after meetting the resistance, stop, insert first rotary rod 210, from last down the clockwise slow rotation first rotary rod 210 of looking at, utilize the axial pressure that the spiral pressure stretched the motion and brought, accomplish the assembly between combustion chamber and the preceding head, after the assembly targets in place, demolish combustion chamber pressure and stretch frock 2.
Step S5, assembling a snap ring;
the combustion chamber and the snap ring after the step S4 are assembled on the snap ring extrusion tool 3;
the specific process of step S5 is: taking out the snap ring assembly tool 3, fixing the combustion chamber product after the step S4 through the combustion chamber fixing half ring 302 on the base 301, paying attention to that the snap ring inlet of the combustion chamber is vertically upward, mounting the snap ring frame 303 on the base 301, paying attention to that the positioning square boss at the bottom of the snap ring frame 303 is matched with the square concave hole of the thread mounting hole 309 on the base 301 in place, and fixing the base 301 and the snap ring frame 303 together by using a sunk screw. The snap ring is taken out and placed in the snap ring guide groove 304 above the snap ring frame 303; the clamp ring extrusion sliding block 307 is placed on the clamp ring frame 303, and the extrusion key 310 at the bottom of the clamp ring extrusion sliding block 307 is pressed at the rear end of the clamp ring; screwing the extrusion rod 306 into the extrusion base 305 through threads, and pressing the inner end of the extrusion rod 306 into the hemispherical concave hole of the clamping ring extrusion sliding block 307; and inserting the second rotating rod 308 into a through hole at the rear end of the extrusion rod 306, slowly rotating the second rotating rod 308 clockwise when the second rotating rod is seen from right to left, slowly pushing the snap ring into the engine snap ring groove from the snap ring inlet of the combustion chamber at a constant speed, and removing the snap ring assembly tool 3 after finishing.
And step S6, assembling the initiating explosive device.
The specific process of step S5 is: and assembling the initiating explosive device to the front end socket of the engine by using an adjustable wrench, so that the final assembly process of the product is finished.
Claims (8)
1. An internal clamping ring type solid rocket engine assembly device is characterized by comprising a grain die assembly tool (1), a combustion chamber pressing and stretching tool (2) and a clamping ring extrusion tool (3);
the explosive column die-closing tool (1) comprises two die-closing half rings (101) which can be assembled together and have the same structure, the inner walls of the two die-closing half rings (101) are divided into a front sealing head section (102) and an explosive charging section (103) along the axial direction, a sealing ring groove (104) is formed in the position, close to the explosive charging section (103), of the front sealing head section (102), the inner diameter of the sealing ring groove (104) is larger than that of the front sealing head section (102), and the inner diameter of the front sealing head section (102) is larger than that of the explosive charging section (103);
the combustion chamber pressure extension tool (2) comprises an annular upper disc (201) and an annular lower disc (202) which are parallelly, coaxially and relatively fixedly arranged, a pressure cylinder (203) is arranged between the upper disc (201) and the lower disc (202), two ends of the pressure cylinder (203) are open and are in a stepped cylinder shape, the caliber of the top end of the pressure cylinder (203) is smaller than that of the bottom end, and a shaft shoulder (204) is arranged on the upper part, close to the top end, of the pressure cylinder (203);
the edge of the inner ring of the upper disc (201) is provided with a pressure ring cylinder seat (205) which protrudes upwards in the axial direction, a pressure ring (206) is installed in the pressure ring cylinder seat (205), and the bottom end of the pressure ring (206) can be pressed on a shaft shoulder (204) of the pressure cylinder (203);
the combustion chamber is placed in the pressing cylinder (203), the bottom end of the pressing cylinder (203) is limited and installed in the combustion chamber through a pair of snap ring inlet limiting half rings (207) which are assembled together, a snap ring inlet plug (208) is arranged on the inner wall of each snap ring inlet limiting half ring (207), and the snap ring inlet plug (208) is embedded into a snap ring inlet formed in the side wall of the combustion chamber;
the lower disc (202) is used for placing a front seal head and charge combination aligned with the combustion chamber;
the clamping ring extrusion tool (3) comprises a base (301), and a pair of combustion chamber fixed half rings (302) are arranged on the base (301); the combustion chamber is characterized in that a clamping ring frame (303) is detachably arranged on the base (301), a clamping ring guide groove (304) is formed in the clamping ring frame (303), the clamping ring guide groove (304) is perpendicular to the central axis of a combustion chamber fixed by the pair of combustion chamber fixed semi-rings (302), and the inner end of the clamping ring guide groove (304) is aligned with a clamping ring inlet of the combustion chamber; an extrusion base (305) is fixedly arranged on a snap ring frame (303) at the outer end of the snap ring guide groove (304), an extrusion rod (306) is installed on the extrusion base (305), the inner end of the extrusion rod (306) is propped against a snap ring extrusion sliding block (307) used for extruding the snap ring to enter a snap ring inlet, and an extrusion key (310) at the bottom of the snap ring extrusion sliding block (307) is clamped into the snap ring guide groove (304) and used for extruding the snap ring to move.
2. The assembly device of an internal-snap ring type solid rocket engine according to claim 1, wherein said two mold closing half rings (101), said pair of snap ring inlet limiting half rings (207) and said pair of combustion chamber stationary half rings (302) are respectively provided with connecting lug seats, and said connecting lug seats are connected with each other by bolts.
3. The internal-snap ring solid rocket engine assembly device according to claim 1, wherein the inner ring edges of said lower disk (202) are each provided with a bottom cylinder seat (209) protruding axially downward; the upper plate (201) and the lower plate (202) are fixedly supported through a plurality of stud bolts (211).
4. The assembly device of an internal snap ring type solid rocket engine according to claim 1, wherein the press ring (206) is installed with the press ring barrel base (205) in a threaded fit manner, and the top end of the press ring (206) is provided with a first rotating rod (210).
5. An internal clasp type solid rocket engine assembly device according to claim 1, wherein the extrusion rod (306) is installed with the extrusion base (305) by screw thread fit, and the outer end of the extrusion rod (306) is provided with a second rotating rod (308).
6. The internal snap ring type solid rocket engine assembly device according to claim 1, wherein said base (301) is provided with a plurality of threaded mounting holes (309), each threaded mounting hole (309) is detachably mounted with a snap ring bracket (303) by means of a countersunk screw.
7. An internal-clasp solid-rocket engine assembly process, characterized in that it uses an internal-clasp solid-rocket engine assembly according to any one of claims 1 to 6.
8. The internal clasp type solid rocket engine assembly process of claim 7, wherein the process comprises the steps of:
step S1, assembling a front seal head and a front medicine baffle plate;
step S2, assembling a front seal head and charging;
the front end enclosure and the charge are assembled on a charge column die closing tool (1), and the outer diameter of the charge is limited by two die closing half rings (101);
step S3, assembling a rear medicine baffle plate;
step S4, assembling a combustion chamber;
assembling the combustion chamber and the front end enclosure subjected to the step S3 on a combustion chamber compression and extension tool (2);
step S5, assembling a snap ring;
the combustion chamber and the clamping ring which are processed in the step S4 are assembled on the clamping ring extrusion tool (3);
and step S6, assembling the initiating explosive device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111180798.9A CN113931762B (en) | 2021-10-11 | 2021-10-11 | Internal clamp ring type solid rocket engine assembly device and process |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111180798.9A CN113931762B (en) | 2021-10-11 | 2021-10-11 | Internal clamp ring type solid rocket engine assembly device and process |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113931762A true CN113931762A (en) | 2022-01-14 |
| CN113931762B CN113931762B (en) | 2022-08-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111180798.9A Active CN113931762B (en) | 2021-10-11 | 2021-10-11 | Internal clamp ring type solid rocket engine assembly device and process |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4999997A (en) * | 1985-11-18 | 1991-03-19 | Thiokol Corporation | Radial pulse motor igniter-sustain grain |
| CN105888881A (en) * | 2016-04-14 | 2016-08-24 | 湖北三江航天江河化工科技有限公司 | Connecting and sealing device |
| US20180073466A1 (en) * | 2016-09-15 | 2018-03-15 | Gary C. Rosenfield | Rocket Apparatuses, Systems and Methods |
| CN109826722A (en) * | 2019-03-06 | 2019-05-31 | 西安近代化学研究所 | A kind of wedge shape piecemeal check ring joint structure |
-
2021
- 2021-10-11 CN CN202111180798.9A patent/CN113931762B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4999997A (en) * | 1985-11-18 | 1991-03-19 | Thiokol Corporation | Radial pulse motor igniter-sustain grain |
| CN105888881A (en) * | 2016-04-14 | 2016-08-24 | 湖北三江航天江河化工科技有限公司 | Connecting and sealing device |
| US20180073466A1 (en) * | 2016-09-15 | 2018-03-15 | Gary C. Rosenfield | Rocket Apparatuses, Systems and Methods |
| CN109826722A (en) * | 2019-03-06 | 2019-05-31 | 西安近代化学研究所 | A kind of wedge shape piecemeal check ring joint structure |
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| Publication number | Publication date |
|---|---|
| CN113931762B (en) | 2022-08-19 |
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