CN110966116A - Free charge grain assembly fixture of solid rocket engine - Google Patents
Free charge grain assembly fixture of solid rocket engine Download PDFInfo
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- CN110966116A CN110966116A CN201911084657.XA CN201911084657A CN110966116A CN 110966116 A CN110966116 A CN 110966116A CN 201911084657 A CN201911084657 A CN 201911084657A CN 110966116 A CN110966116 A CN 110966116A
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- explosive
- explosive column
- solid rocket
- rocket engine
- assembly fixture
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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
- F02K9/24—Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Portable Nailing Machines And Staplers (AREA)
Abstract
The invention relates to a free-filling grain assembly tool with a position calibration function, which is suitable for a free filling process of a solid rocket engine grain. This frock comprises powder column support, position sleeve, hexagon socket head cap screw and locating pin, and the boss of powder column support forms clearance fit relation with the recess of position sleeve, and it can guarantee accurately that the pinhole on powder column sub-assembly and the engine housing corresponds each other, has avoided the wide-angle rotation adjustment of follow-up in-process powder column sub-assembly, and the efficiency of powder column assembly can promote by a wide margin.
Description
Technical Field
The invention relates to the field of solid rocket engine manufacturing, and relates to a tool for freely filling and assembling explosive columns in the production process of a solid rocket engine.
Background
For a solid rocket engine, a free filling structure is a charging form with high filling coefficient, and different from direct casting molding (wall-attached casting) in an engine shell, a charge column is filled into the engine in a filling mode, a head part is fixedly bonded with a front end socket of the shell, and the rest part is in a free state. Because the explosive columns are independently cast and molded without considering stress strain generated by solidification and cooling, the solid explosive columns can be directly adopted for filling, the mass ratio of the engine can be effectively improved, and the aim of light overall design is fulfilled.
For the free filling process, the fixation of the drug column is often confined by a positioning pin, and is not all-directional. The explosive column assembly consists of an explosive column and a seal head, wherein the explosive column and the seal head are connected in a gluing mode, and the pin hole is positioned at the tail end of the seal head. Therefore, the outer diameter of the charge and the inner diameter of the housing are usually closely matched to prevent torsional failure of the charge under tangential forces. This means that the pin hole position of the cartridge assembly and the shell needs to be aligned accurately at one time. If the grain is plugged into the shell and then the pin hole position is calibrated, large resistance needs to be overcome in the process of rotating the grain, great difficulty is caused to assembly, and the structural integrity of the grain can be damaged. Meanwhile, due to the large application of the existing large-diameter freely-filled grains, the original technical method cannot meet the requirement of large-batch production.
Disclosure of Invention
The invention aims to provide a free-filling grain assembly tool with a position calibration function, which is suitable for a free filling process of a solid rocket engine grain.
In order to achieve the purpose, the invention provides a free charge grain assembly tool of a solid rocket engine, which comprises: the explosive column comprises an explosive column support, a positioning sleeve, inner hexagonal cylindrical screws and positioning pins, wherein a boss of the explosive column support and a groove of the positioning sleeve form a clearance fit relation, the explosive column support is installed on the explosive column through the inner hexagonal cylindrical screws, and the positioning sleeve is fixed on a shell of an engine through the positioning pins.
The assembling tool for freely filling the explosive columns in the solid rocket engine is characterized in that the number of the hexagon socket head cap screws is 12.
The assembly tool for freely filling the explosive columns into the solid rocket engine is characterized in that a groove structure is arranged on the inner circle of the positioning sleeve, the center line of the groove structure is marked on the outer side of the groove, and 6 positioning through holes which are uniformly distributed on the circumference are formed in the circumference of the positioning sleeve.
The assembly tool for freely filling the explosive columns in the solid rocket engine is characterized in that a boss structure is arranged on the outer side of the inner circle of the explosive column support, and 12 positioning through holes distributed circumferentially are formed in the outer circumferential surface of the explosive column support.
The assembling tool for freely filling the explosive column of the solid rocket engine is characterized in that the center of the end face of the explosive column bracket is provided with an M18 threaded hole.
Above-mentioned solid rocket engine freely loads grain assembly fixture, wherein, grain support top and position sleeve excircle all contain 6 through-holes that play and subtract heavy effect.
The assembling tool for the free-loading explosive column of the solid rocket engine is characterized in that pin through holes corresponding to each other are formed in the tail end of the seal head on the explosive column and the outer side of the front end of the engine shell.
According to the assembly tool for freely loading the explosive columns in the solid rocket engine, the explosive column support and the concave-convex platform structure of the positioning sleeve form a clearance fit relation, so that the explosive column assembly and a positioning pin hole in the engine shell are guaranteed to be corresponding to each other.
According to the assembly tool for freely filling the explosive columns into the solid rocket engine, the relative position of the positioning sleeve and the shell is pre-calibrated by aligning the central line on the groove with the reference line on the shell of the engine.
The assembling tool for freely filling the explosive columns into the solid rocket engine is characterized in that the locating sleeve is connected with the engine shell through 6 locating pins, and the length of each pin is not more than the sum of the depths of the locating through holes in the locating sleeve and the engine shell.
A free charge grain assembly tool of a solid rocket engine comprises a grain bracket, a positioning sleeve, an inner hexagonal cylindrical head screw and a positioning pin; the inner circle of the positioning sleeve is provided with a groove structure, the outer side of the groove is marked with a central line of the groove structure, and the circumferential surface of the positioning sleeve is provided with 6 positioning through holes which are uniformly distributed circumferentially; the outer side of the inner circle of the medicine column bracket is provided with a boss structure, the outer circumferential surface of the bracket is provided with 12 positioning through holes which are distributed circumferentially, and the center of the end surface of the bracket is provided with a threaded hole of M18; the top end of the explosive column support and the excircle of the positioning sleeve both comprise 6 through holes for reducing weight.
The size adjustment through the whole tool can be suitable for the free filling of all pin-connected solid rocket engine explosive columns. The explosive column component is connected with the engine shell through a positioning pin, and the tail end of an end socket on the explosive column component and the outer side of the front end of the engine shell are provided with pin through holes corresponding to each other.
Through the concave-convex platform structure of the explosive column bracket and the locating sleeve forms a clearance fit relation, the mutual correspondence of the positions of the locating pin holes on the explosive column component and the engine shell is ensured.
The relative position of the locating sleeve and the shell is pre-calibrated by aligning the center line of the groove with the reference line of the engine shell.
The front end of the explosive column assembly is used as a reserved threaded hole for final assembly, the threaded hole is mutually corresponding to 12 positioning through holes on the outer side of the explosive column support, and the threaded hole and the 12 positioning through holes are connected through an inner hexagonal socket head cap screw. The locating sleeve is connected with the engine shell through 6 locating pins, and the length of each pin does not exceed the sum of the depths of the locating through holes in the locating sleeve and the engine shell.
The engine shell provided with the locating sleeve is vertically placed, then the explosive column component provided with the explosive column support is hung into the engine shell, and the corresponding concave lug boss is kept in the process to assemble the explosive column. The M18 threaded through hole in the center of the end face of the grain support is used for installing a lifting hook in the assembling process.
In order to realize the one-time assembly of the explosive column component, the positioning sleeve and the explosive column bracket form a clearance fit relationship through respective concave-convex structures, so that the accuracy of the relative position of the explosive column component and the engine shell in the assembly process is ensured. The explosive column bracket is arranged on the explosive column assembly through 12 inner hexagonal socket head screws, and the positioning sleeve is fixed on the engine shell through a positioning pin. During the process of installing the locating sleeve, the pre-calibration of the explosive column assembly is realized by aligning the center line of the outer side of the groove in the structure with the reference line of the engine shell. Then, the explosive column component provided with the explosive column support is hung into the shell, and the boss on the explosive column support is aligned to the groove on the shell positioning sleeve, so that the initial assembly of the explosive column component can be completed.
The invention solves the problems that the grain components are difficult to rotate, manpower and material resources are wasted and high-efficiency production cannot be realized in the production and assembly process of the existing solid rocket engine, and avoids the quality hidden trouble which is easy to generate in the correction process.
The tool structure is suitable for free charge processes of explosive columns with similar structures, and is particularly suitable for assembling explosive column assemblies with larger overall dimensions and more concentrated mass. The tool adopts a screw and pin connection mode, is convenient and quick to install and use, avoids the difficulty of follow-up large-amplitude angle correction, and improves the assembly efficiency of the explosive column assembly.
Compared with the traditional installation technology, the invention has the advantages that:
(1) the assembly fixture with the position calibration function is used, and the assembly process is efficient and rapid. Compared with the existing mode of carrying out position alignment through visual inspection, the assembly accuracy is greatly improved.
(2) The concave-convex structure between the explosive column bracket and the positioning sleeve is matched to realize the one-time assembly of the explosive column assembly, thereby avoiding the correction of subsequent manual rotation and reducing the working strength of operators.
(3) The installation of explosive column support and position sleeve adopts hexagon socket head cap screw and locating pin, easy operation, and operating personnel can install fast and dismantle.
(4) The time and the labor cost in the assembling process are greatly saved. Because the original adoption of the formula of directly hanging into assembly of grain, the grain quality is great, and closely laminates with the casing, and the manual work is difficult to revise after the grain hangs into. After the tool is used, the pre-calibration of the position of the tool is only needed to be noticed, and the assembly of the explosive column component can be easily completed.
Drawings
The assembly tool for freely filling the explosive columns in the solid rocket engine is provided by the following embodiments and attached drawings.
Figure 1 is a schematic view of a cartridge assembly.
Fig. 2 is a partial structural schematic diagram of a typical engine, wherein fig. 2a is a schematic diagram of a seal head of a charge assembly, and fig. 2b is a schematic diagram of a front section of an engine shell.
Fig. 3 is an overall schematic view of the tool of the present invention after installation.
FIG. 4 is a schematic view of the structure of the drug column holder of the present invention.
FIG. 5 is a schematic view of the structure of the positioning sleeve of the present invention.
Fig. 6 is a schematic view of the dowel pin structure of the present invention.
Wherein: 1. carrying out grain treatment; 2. sealing the end; 3. a threaded hole; 4. a pin hole on the end socket; 5. a pin hole in the front section of the engine housing; 6. a drug column support; 7. a positioning sleeve; 8. a socket head cap screw; 9. positioning a pin; 10. a boss; 11. positioning the through hole; 12. an inner groove; 13. a centerline; 14. a pin hole on the positioning sleeve; 15. the shock attenuation through-hole.
Detailed Description
The present invention will be described in further detail below with reference to fig. 1 to 6.
The charging tool provided by the invention is implemented by taking a solid rocket engine of a certain typical model as an example to finish the assembly of the explosive column assembly, and the specific mode is as follows:
1. and (3) mounting the end with short hole distance of the tool positioning sleeve 7 into the engine shell, aligning the central line 13 outside the groove with the datum line on the shell, and aligning the pin hole 14 on the positioning sleeve with the pin hole 5 on the front section of the engine shell. Then the positioning sleeve 7 is fixed on the shell by six positioning pins 9 and then turned over until the head part faces upwards.
2. The explosive column bracket 6 is arranged at the end socket 2 of the explosive column assembly, the positioning through hole 11 on the explosive column bracket 6 is aligned with the threaded hole 3 of the end socket, and then the explosive column bracket 6 is fixed on the excircle of the end socket 2 of the explosive column assembly by twelve inner hexagonal socket head cap screws 8.
3. And then, an O-shaped sealing ring is arranged in a sealing groove of the end socket of the medicine column assembly according to requirements, the metal side surface of the end socket 2 is coated with lubricating grease, and the medicine column 1 is coated with talcum powder.
4. The charge combination is lifted so that its boss 10 is aligned with the internal recess 12 in the housing locating sleeve and is lifted into the housing. Finally, two persons can pull downwards from two sides to expose the medicine column to a depth of no more than 20.
5. And after the pin hole 4 of the end socket is observed to be aligned with the pin hole 5 of the front section of the engine shell in the observation hole, whether the O-shaped sealing ring is cut or not is checked. After confirmation, 3 pins were knocked in circumferentially spaced apart rows in the wells.
6. The roll-over table is then swung to the horizontal and the product is hung onto the mounting bracket. And after the explosive column assembling tool is disassembled, other pins are sequentially knocked in, so that all the pins are ensured to be assembled in place.
7. Finally, the straps are assembled in place and tightened.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. The utility model provides a solid rocket engine freely loads grain assembly fixture which characterized in that, the frock includes: the explosive column comprises an explosive column support, a positioning sleeve, inner hexagonal cylindrical screws and positioning pins, wherein a boss of the explosive column support and a groove of the positioning sleeve form a clearance fit relation, the explosive column support is installed on the explosive column through the inner hexagonal cylindrical screws, and the positioning sleeve is fixed on a shell of an engine through the positioning pins.
2. The assembly fixture for freely filling explosive columns into a solid rocket engine according to claim 1, wherein the number of the hexagon socket head cap screws is 12.
3. The assembly fixture for freely filling the explosive columns into the solid rocket engine according to claim 1, wherein the inner circle of the positioning sleeve is provided with a groove structure, the outer side of the groove is marked with a central line of the groove structure, and the circumferential surface of the positioning sleeve is provided with 6 positioning through holes which are uniformly distributed on the circumference.
4. The assembly fixture for freely filling the explosive columns in the solid rocket engine according to claim 1, wherein the outer side of the inner circle of the explosive column support is provided with a boss structure, and the outer circumferential surface of the explosive column support is provided with 12 positioning through holes distributed circumferentially.
5. The assembly fixture for freely charging explosive columns in a solid rocket engine as recited in claim 4, wherein said explosive column support has a threaded hole M18 in the center of its end face.
6. The assembly fixture for freely filling the explosive column of the solid rocket engine according to claim 1, wherein the top end of the explosive column support and the outer circle of the positioning sleeve both comprise 6 through holes for reducing weight.
7. The assembly fixture for freely filling the explosive column of the solid rocket engine according to claim 1, wherein the tail end of the seal head on the explosive column and the outer side of the front end of the engine shell are provided with pin through holes corresponding to each other.
8. The assembly fixture for freely filling the explosive column in the solid rocket engine according to claim 1, wherein the explosive column assembly is ensured to correspond to the position of the positioning pin hole on the engine shell through the clearance fit relationship formed by the concave-convex platform structures of the explosive column bracket and the positioning sleeve.
9. The assembly fixture for freely charging explosive columns in a solid rocket engine according to claim 3, wherein the relative position of the locating sleeve and the shell is pre-calibrated by aligning a center line on the groove with a reference line on the engine shell.
10. The assembly fixture for freely filling the explosive columns into the solid rocket engine according to claim 1, wherein the locating sleeve is connected with the engine shell through 6 locating pins, and the length of the pins does not exceed the sum of the depths of the locating through holes in the locating sleeve and the engine shell.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911084657.XA CN110966116B (en) | 2019-11-08 | 2019-11-08 | Free charge grain assembly fixture of solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911084657.XA CN110966116B (en) | 2019-11-08 | 2019-11-08 | Free charge grain assembly fixture of solid rocket engine |
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| CN110966116A true CN110966116A (en) | 2020-04-07 |
| CN110966116B CN110966116B (en) | 2021-03-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911084657.XA Active CN110966116B (en) | 2019-11-08 | 2019-11-08 | Free charge grain assembly fixture of solid rocket engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114483375A (en) * | 2021-12-29 | 2022-05-13 | 湖北航天化学技术研究所 | Engine isolation core inserting device |
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| CN106121862A (en) * | 2016-08-11 | 2016-11-16 | 西北工业大学 | A kind of solid rocket motor grain fixing device |
| CN106596395A (en) * | 2016-10-27 | 2017-04-26 | 上海新力动力设备研究所 | Apparatus for measuring adhesive strength of free loading grain of solid rocket engine |
| CN107965399A (en) * | 2017-12-07 | 2018-04-27 | 上海新力动力设备研究所 | A kind of powder column of resistance to ablation support plate for being applicable in free loading propellant solid propellant rocket |
| CN109723575A (en) * | 2018-11-26 | 2019-05-07 | 西安现代控制技术研究所 | A kind of hollow charge free loading propellant mode and method for realizing more thrust schemes |
| CN110195665A (en) * | 2019-06-21 | 2019-09-03 | 北京理工大学 | A kind of air storing type solid propellant power device of reloading |
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2019
- 2019-11-08 CN CN201911084657.XA patent/CN110966116B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0359408A2 (en) * | 1988-08-17 | 1990-03-21 | Talley Automotive Products, Inc. | Filter assembly for non-welded inflator device |
| CN1553135A (en) * | 2003-05-26 | 2004-12-08 | 黄振芬 | Process for filling solid rocket propellant for artillery ammunition |
| US20060075890A1 (en) * | 2004-10-13 | 2006-04-13 | Propellant Fracturing & Stimulation, Llc | Propellant for fracturing wells |
| CN203499853U (en) * | 2013-07-19 | 2014-03-26 | 晋西工业集团有限责任公司 | Rocket propellant grain fixing device |
| CN104696106A (en) * | 2013-12-10 | 2015-06-10 | 上海新力动力设备研究所 | Connection structure of opening clamping key of solid rocket engine |
| CN106121862A (en) * | 2016-08-11 | 2016-11-16 | 西北工业大学 | A kind of solid rocket motor grain fixing device |
| CN106596395A (en) * | 2016-10-27 | 2017-04-26 | 上海新力动力设备研究所 | Apparatus for measuring adhesive strength of free loading grain of solid rocket engine |
| CN107965399A (en) * | 2017-12-07 | 2018-04-27 | 上海新力动力设备研究所 | A kind of powder column of resistance to ablation support plate for being applicable in free loading propellant solid propellant rocket |
| CN109723575A (en) * | 2018-11-26 | 2019-05-07 | 西安现代控制技术研究所 | A kind of hollow charge free loading propellant mode and method for realizing more thrust schemes |
| CN110195665A (en) * | 2019-06-21 | 2019-09-03 | 北京理工大学 | A kind of air storing type solid propellant power device of reloading |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114483375A (en) * | 2021-12-29 | 2022-05-13 | 湖北航天化学技术研究所 | Engine isolation core inserting device |
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| CN110966116B (en) | 2021-03-09 |
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