CN106596395B - Device for measuring bonding strength of freely-loaded explosive columns of solid rocket engine - Google Patents
Device for measuring bonding strength of freely-loaded explosive columns of solid rocket engine Download PDFInfo
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- CN106596395B CN106596395B CN201610957079.6A CN201610957079A CN106596395B CN 106596395 B CN106596395 B CN 106596395B CN 201610957079 A CN201610957079 A CN 201610957079A CN 106596395 B CN106596395 B CN 106596395B
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- G01N19/04—Measuring adhesive force between materials, e.g. of sealing tape, of coating
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Abstract
A test device for measuring the bonding strength of a freely-loaded grain of a solid rocket engine comprises: preceding switching frock, powder column sub-assembly, card key and back switching frock. The front rotary joint tool is of two axisymmetric split structures, and the lug bosses on the upper part and the lower part of the front rotary joint tool are used as bolt mounting interfaces to complete the butt joint of the two split structures and the circumferential fixation of the explosive column assembly in a bolt fastening mode; the explosive column assembly is formed by bonding a front end enclosure and an explosive column, the bonding surface is ensured to be consistent with the actual state of an engine, and a groove is formed in the outer molded surface of the front end enclosure along the circumferential direction; the clamping keys are of semicircular structures, and the two clamping keys are placed in a groove between the front transfer tool and a front end socket of the explosive column assembly together to complete axial fixation of the explosive column assembly; the inner molded surface of the rear transfer tool is used as a bonding surface with the explosive column, the axial length of the bonding surface is 2.5 times of that of the bonding surface of the front seal head and the explosive column, and the rear end of the rear transfer tool is used as an installation interface of a tensile testing machine through a section of cylindrical section.
Description
Technical Field
The invention relates to the field of solid rocket engines, in particular to a device for measuring the bonding strength of freely-filled explosive columns 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 independent casting moulding of explosive column need not consider the stress strain that solidification cooling produced, consequently can directly adopt solid explosive column to pack, can effectively promote the mass ratio of engine.
However, when the missile is vertically cold launched, the freely-filled grain is in a semi-free state in the engine, so that the deformation of the missile is greatly increased compared with an adherence pouring mode when the missile is overloaded, and meanwhile, the bonding strength of the shell front end socket is also examined. The deformation of the explosive column beyond expectation can change the structure of the inner cavity of the engine and influence the performance of the engine; the insufficient bonding interface strength of the explosive column and the shell front end socket can cause the explosive column to be separated by debonding, and the reliability of the engine is seriously influenced.
Based on the physical characteristics of the free filling structure, the key for determining the structural integrity, the environmental adaptability and the working reliability of the missile under the vertical cold launching condition is to accurately measure the bonding strength of the explosive column and the front end socket. Most of the static tensile tests adopted at present are test piece-level static tensile tests, and because the static tensile tests are greatly different from actual products in aspects such as tensile rate, boundary conditions and the like, larger errors exist.
Disclosure of Invention
The invention aims to solve the problems, and provides a device for measuring the bonding strength of a freely-filled grain of a solid rocket engine, which can accurately measure the bonding strength between the grain and a front end enclosure.
In order to solve the technical problem, the invention provides a device for measuring the bonding strength of a freely-filled grain of a solid rocket engine, which comprises: preceding switching frock, powder column sub-assembly, card key and back switching frock. The front rotary joint tool is of two axisymmetric split structures, the bosses on the upper part and the lower part of the front rotary joint tool are used as bolt installation interfaces, the butt joint of the two split structures and the circumferential fixation of the explosive column assembly are completed in a bolt fastening mode, a groove is formed in the inner molded surface of the front rotary joint tool along the circumferential direction, and the front end of the front rotary joint tool is used as an installation interface of a tensile testing machine through a section of cylindrical section; the explosive column assembly is formed by bonding a front end enclosure and an explosive column, the bonding surface is ensured to be consistent with the actual state of an engine, and a groove is formed in the outer molded surface of the front end enclosure along the circumferential direction; the clamping keys are of semicircular structures, and the two clamping keys are placed in a groove between the front transfer tool and a front end socket of the medicine component assembly together to complete axial fixation of the medicine column assembly; the inner molded surface of the rear transfer tool is used as a bonding surface with the explosive column, the axial length of the bonding surface is 2.5 times of that of the bonding surface of the front seal head and the explosive column, and the rear end of the rear transfer tool is used as an installation interface of the tensile testing machine through a section of cylindrical section.
Further, the front rotary joint tool is provided with a groove with the width of 4.5mm and the depth of 2.5mm along the circumferential direction at the position 20mm away from the rear end face, and the front end of the front rotary joint tool is used as a mounting interface of a tensile testing machine through a cylindrical section with the diameter phi of 10mm and the length of 30 mm.
Further, the groove bottom diameter of the front rotary tool is phi 228mm, and the outer diameter is phi 223 mm.
Further, the axial length of the bonding surface of the explosive column assembly is 38 mm.
Further, the front end socket of the grain assembly is provided with a groove which is 4.5mm wide and 2.75mm deep along the circumferential direction at the position 11mm away from the front end of the front end socket.
Further, the bottom diameter of a groove on a front seal head of the grain combination piece is phi 217.5mm, and the outer diameter is phi 223 mm.
Further, the said card key is a semi-circular ring body with inner diameter phi 218.6mm, outer diameter phi 228mm and width 4.1 mm.
Further, the axial length of the bonding surface of the rear adapter tool is 95 mm.
Further, the rear end of the rear adapter tool is used as a mounting interface of the tensile testing machine through a section of cylindrical section with the diameter phi of 10mm and the length of 30 mm.
Compared with the prior art, the device for measuring the bonding strength of the freely-filled grain of the solid rocket engine has the advantages and beneficial effects that:
1) through a specially designed test device, the bonding interface at the front end socket can be guaranteed to be firstly damaged in the test process, and the purpose of measuring the bonding strength of the front end socket is achieved;
2) by measuring the bonding strength of the explosive columns, the structural integrity, the environmental adaptability and the working reliability of the engine under the condition of vertical cold launching of the missile are improved.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments made with reference to the following drawings:
FIG. 1 is a schematic diagram of a device for measuring the bonding strength of a freely-packed grain of a solid rocket engine according to the present invention.
FIG. 2 is a schematic side view of the apparatus for measuring the bonding strength of the freely packed charge of a solid rocket engine according to the present invention.
Detailed Description
The present invention will be described in more detail below with reference to the accompanying drawings, which illustrate embodiments of the invention. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, the size and relative sizes of layers and regions may be exaggerated for clarity.
The solution provided by the invention is to provide a device for measuring the bonding strength of a freely-filled grain of a solid rocket engine, which comprises the following components: preceding switching frock 1, powder column sub-assembly 2, card key 3 and back switching frock 4. The front switching tool 1 is of two axisymmetric split structures, the bosses on the upper part and the lower part of the front switching tool are used as bolt mounting interfaces, the butt joint of the two split structures and the circumferential fixation of the explosive column assembly 2 are completed in a bolt fastening mode, a groove is formed in the inner molded surface of the front switching tool along the circumferential direction, and the front end of the front switching tool is used as a mounting interface of a tensile testing machine through a section of cylindrical section; the explosive column assembly 2 is formed by bonding a front end enclosure 21 and an explosive column 22, the bonding surface is ensured to be consistent with the actual state of an engine, and a groove is formed in the outer molding surface of the front end enclosure 21 along the circumferential direction; the clamp keys 3 are of semicircular ring structures, and the two clamp keys 3 are placed in a groove between the front transfer tool 1 and the front end socket 21 of the medicine component assembly 2 together to complete axial fixation of the medicine column assembly 2; the inner profile of the rear transfer tooling 4 is used as a bonding surface with the explosive column 22, the axial length of the bonding surface is 2.5 times of that of the bonding surface of the front seal head 21 and the explosive column 22, and the rear end of the rear transfer tooling is used as an installation interface of a tensile testing machine through a section of cylindrical section.
Taking an engine with the diameter phi of 230mm as an example, according to an engine development task book issued by the whole, the structural form of freely filling the chemical column is determined, and meanwhile, based on the system requirement of guided missile vertical cold launching, the strength of the bonding surface of the chemical column 22 and the shell of the front seal head 21 needs to be measured so as to meet the examination of the actual axial large overload on the bonding interface. According to the test requirements, a test device for measuring the bonding strength of the freely-filled grain of the solid rocket engine is adopted. Firstly, bonding the explosive column 22 and the front end socket 21 in place by adopting SW-2 glue to form an explosive column assembly 2, and simultaneously bonding the rear transfer tool 4 and the explosive column of the explosive column assembly 2 in place by adopting SW-2 glue; secondly, two semicircular clamping keys 3 are arranged in a groove between the explosive column assembly 2 and the front rotary joint tool 1, so that the axial position of the explosive column assembly 2 is fixed; finally, two M10 bolts are arranged in through holes of bosses on the upper side and the lower side of the front transfer tool 1, and the butt joint fastening of two split structures of the front transfer tool 1 and the circumferential fixing of the explosive column assembly 2 are completed. After all assembly and fastening connection are completed, the cylindrical section at the front end of the front switching tool 1 and the cylindrical section at the rear end of the rear switching tool 4 are used as installation interfaces of the whole test piece and a tensile testing machine, and actual tensile strength data when the front end socket 21 and the explosive column 22 in the explosive column assembly 2 are separated are recorded through the tensile testing machine, so that test measurement of the bonding strength of the freely-filled explosive columns is completed.
The testing device is applied to the type, the operability and the data validity of the testing device are verified, and on the basis of the testing data, the testing device passes the check of multiple ejection tests and flight tests, so that the bonding structure of the explosive column and the front end socket shell is reliable, and the overall requirements are met.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof.
Claims (5)
1. A device for measuring the bonding strength of a freely-loaded grain of a solid rocket engine comprises: the device comprises a front transfer tool, a grain assembly, a clamping key and a rear transfer tool;
the front rotary joint tool is of two axisymmetric split structures, the bosses on the upper part and the lower part of the front rotary joint tool are used as bolt installation interfaces, the butt joint of the two split structures and the circumferential fixation of the explosive column assembly are completed in a bolt fastening mode, a groove is formed in the inner molded surface of the front rotary joint tool along the circumferential direction, and the front end of the front rotary joint tool is used as an installation interface of a tensile testing machine through a section of cylindrical section;
the explosive column assembly is formed by bonding a front end enclosure and an explosive column, the bonding surface is ensured to be consistent with the actual state of an engine, and a groove is formed in the outer molded surface of the front end enclosure along the circumferential direction;
the clamping keys are of semicircular structures, and the two clamping keys are placed in a groove between the front transfer tool and a front end socket of the explosive column assembly together to complete axial fixation of the explosive column assembly;
the inner molded surface of the rear transfer tool is used as a bonding surface with the explosive column, the axial length of the bonding surface is 2.5 times of that of the bonding surface of the front seal head and the explosive column, and the rear end of the rear transfer tool is used as an installation interface of a tensile testing machine through a section of cylindrical section;
the front rotary joint tool is provided with a groove with the width of 4.5mm and the depth of 2.5mm at the position 20mm away from the rear end surface along the circumferential direction, and the front end of the front rotary joint tool is used as a mounting interface of a tensile testing machine through a cylindrical section with the diameter phi of 10mm and the length of 30 mm;
a groove with the width of 4.5mm and the depth of 2.75mm is arranged at the position 11mm away from the front end of the front seal head of the explosive column assembly along the circumferential direction;
the rear end of the rear transfer tool is used as a mounting interface of a tensile testing machine through a section of cylindrical section with the diameter phi of 10mm and the length of 30 mm;
the bottom diameter of the groove on the front seal head of the explosive column assembly is phi 217.5mm, and the outer diameter thereof is phi 223 mm.
2. The device for measuring the bonding strength of the freely packed powder column of the solid rocket engine according to claim 1, wherein the groove bottom diameter of the front adapter tool is phi 228mm, and the outer diameter is phi 223 mm.
3. The apparatus for measuring the adhesion strength of a freely packed charge of a solid rocket engine as recited in claim 1, wherein said charge assembly has an axial length of the adhesion surface of 38 mm.
4. The device for measuring the bonding strength of the freely packed powder column of the solid rocket engine according to claim 1, wherein the clamp key is a semi-circular ring body with an inner diameter phi 218.6mm, an outer diameter phi 228mm and a width of 4.1 mm.
5. The test device for measuring the bonding strength of the freely-loaded grain of solid rocket engine according to claim 1, wherein the axial length of the bonding surface of the rear adapter tool is 95 mm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610957079.6A CN106596395B (en) | 2016-10-27 | 2016-10-27 | Device for measuring bonding strength of freely-loaded explosive columns of solid rocket engine |
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| CN201610957079.6A CN106596395B (en) | 2016-10-27 | 2016-10-27 | Device for measuring bonding strength of freely-loaded explosive columns of solid rocket engine |
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| CN106596395A CN106596395A (en) | 2017-04-26 |
| CN106596395B true CN106596395B (en) | 2020-01-14 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109736966B (en) * | 2018-12-25 | 2021-11-16 | 内蒙合成化工研究所 | Shaping-free forming method for end face of silver-embedded wire explosive column of solid rocket engine |
| CN110449855B (en) * | 2019-08-16 | 2021-09-07 | 中国兵器装备集团自动化研究所 | Full-automatic missile engine assembly quality |
| CN110966116B (en) * | 2019-11-08 | 2021-03-09 | 上海新力动力设备研究所 | Free charge grain assembly fixture of solid rocket engine |
| CN114382612A (en) * | 2020-10-19 | 2022-04-22 | 内蒙古工业大学 | High-energy explosive column filling device |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2330419A (en) * | 1997-10-03 | 1999-04-21 | Aea Technology Plc | Method and apparatus for characterising a powder |
| CN203101171U (en) * | 2013-02-01 | 2013-07-31 | 西安理工大学 | Cylindrical soil sample installation clamp device |
| CN105092464A (en) * | 2014-05-13 | 2015-11-25 | 湖北航天化学技术研究所 | Gas source grain propellant-coating interference bonding strength detection method |
-
2016
- 2016-10-27 CN CN201610957079.6A patent/CN106596395B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2330419A (en) * | 1997-10-03 | 1999-04-21 | Aea Technology Plc | Method and apparatus for characterising a powder |
| CN203101171U (en) * | 2013-02-01 | 2013-07-31 | 西安理工大学 | Cylindrical soil sample installation clamp device |
| CN105092464A (en) * | 2014-05-13 | 2015-11-25 | 湖北航天化学技术研究所 | Gas source grain propellant-coating interference bonding strength detection method |
Non-Patent Citations (1)
| Title |
|---|
| 大型火箭发动机药柱与壳体粘结的探索;J.D.伯德;《12TH PROPULSION CONFERENCE》;阿拉巴马州汉次维尔聚硫化学公司;19800321;第2卷;72 * |
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Effective date of registration: 20200708 Address after: 201109 Minhang District, Shanghai Road, No. 1777 spring Patentee after: SHANGHAI AEROSPACE CHEMICAL APPLICATION Research Institute Address before: 201109 Minhang District, Shanghai Road, No. 1777 spring Patentee before: SHANGHAI XINLI POWER EQUIPMENT INSTITUTE |
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