CN107063840B - Device for single skirt axial tension test of solid rocket engine shell - Google Patents
Device for single skirt axial tension test of solid rocket engine shell Download PDFInfo
- Publication number
- CN107063840B CN107063840B CN201611083786.3A CN201611083786A CN107063840B CN 107063840 B CN107063840 B CN 107063840B CN 201611083786 A CN201611083786 A CN 201611083786A CN 107063840 B CN107063840 B CN 107063840B
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- end frame
- rocket engine
- solid rocket
- engine shell
- round
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- 239000007787 solid Substances 0.000 title claims abstract description 49
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 54
- 239000010959 steel Substances 0.000 claims abstract description 54
- 239000002905 metal composite material Substances 0.000 claims 1
- 239000007769 metal material Substances 0.000 claims 1
- 238000000034 method Methods 0.000 description 3
- 239000004568 cement Substances 0.000 description 2
- 239000004576 sand Substances 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0016—Tensile or compressive
- G01N2203/0017—Tensile
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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)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Testing Of Engines (AREA)
Abstract
The invention relates to a device for a single-skirt axial tension test of a solid rocket engine shell, which comprises an end frame assembly, the solid rocket engine shell and concrete, wherein the end frame assembly comprises an end frame, round steel and a steel plate, the outer side of the upper end of the end frame is connected with a joint of the solid rocket engine shell, a round hole in the inner side of the upper end of the end frame is used for fixing the round steel, and a through hole in the lower end of the end frame is used for fixing the end frame and a test bed through a bolt; the solid rocket engine shell is fixedly arranged on the end frame of the end frame assembly, concrete is filled in the solid rocket engine shell, and the height of the concrete is flush with the upper surface of the steel plate. The device is simple in connection, safe and reliable, and can be applied to a single skirt axial tension test of the shell of the solid rocket engine and an axial tension test with inconsistent loading of the front skirt and the rear skirt of the shell of the solid rocket engine.
Description
Technical Field
The invention relates to a shaft pull test device, in particular to a device for a single skirt shaft pull test of a solid rocket engine shell.
Background
When only one skirt or the front skirt and the rear skirt of the solid rocket engine shell are not loaded uniformly, a method needs to be designed to meet the requirements of tests in order to obtain the axial tension load of the skirt of the solid rocket engine shell.
The existing test method can only apply axial tension load to two skirts of the solid rocket engine shell at the same time, and can not apply axial tension load to a single skirt.
Disclosure of Invention
The invention aims to solve the technical problem of providing a device for a single-skirt axial pull test of a solid rocket engine shell, so as to solve the problem of the single-skirt axial pull test of the solid rocket engine shell.
In order to solve the existing technical problems, the technical scheme adopted by the invention is as follows: a device for a single-skirt axial tension test of a solid rocket engine shell comprises an end frame assembly, the solid rocket engine shell and concrete, wherein the end frame assembly comprises an end frame, round steel and a steel plate, a plurality of through holes are formed in the outer side of the upper end of the end frame and in positions corresponding to connector screw holes of the solid rocket engine shell, the through holes in the outer side of the upper end of the end frame are used for connecting the end frame and a connector of the solid rocket engine shell together through bolts, a plurality of round holes are uniformly distributed in the inner side of the upper end of the end frame, the round holes in the inner side of the upper end of the end frame are used for fixing threaded round steel to the round holes in the inner side of the upper end of the end frame, a plurality of through holes are formed in the outer side of the lower end of the end frame, and the end frame and a test bed are fixed through bolts; threads are arranged at two ends of the round steel, one end of the round steel is fixed on a round hole on the inner side of the upper end of the end frame through a nut, and the other end of the round steel is fixed on a steel plate through a nut; the middle of the steel plate is provided with a through hole, the steel plate is installed at one end of the round steel through the through hole and is fixed by a nut, and the upper surface of the steel plate is flush with the equator line at the end socket of the solid rocket engine shell; the solid rocket engine shell is fixedly arranged on an end frame of the end frame assembly, concrete is filled in the solid rocket engine shell, and the height of the concrete is flush with the upper surface of the steel plate.
Has the advantages that:
the device is simple in connection, safe and reliable, realizes the purpose of obtaining the single skirt axial tension load of the solid rocket engine shell, and can be applied to the single skirt axial tension test of the solid rocket engine shell and the axial tension test with inconsistent loading of the front skirt and the rear skirt of the solid rocket engine shell.
Drawings
FIG. 1 is a schematic view of the combination of the apparatus used for the solid rocket motor case single skirt axial pull test;
FIG. 2 is a schematic view of an end frame assembly;
FIG. 3 is a schematic end block diagram;
in the figure: the structure comprises a detachable end frame assembly 1, a solid rocket engine shell 2, bolts 3, concrete 4, an end frame 5, round steel 6, nuts 7 and a steel plate 8.
Detailed Description
The present invention will be further described with reference to the following embodiments.
As shown in figure 1, the device for the solid rocket engine shell single skirt axial tension test mainly comprises a detachable end frame assembly 1, a solid rocket engine shell 2, bolts 3 and concrete 4.
As shown in fig. 2, the detachable end frame assembly is composed of an end frame 5, round steel 6, a nut 7 and a steel plate 8. Both sides of the round steel 6 are provided with threads with certain length. The steel plate 8 is provided with through holes. The surface of the steel plate 8 is provided with a through hole which is connected with the round steel 6 and used for fixing the solidified concrete.
As shown in fig. 3, one side of the end frame 5 is provided with a plurality of through holes with different distribution circles, and the other side is provided with a plurality of through holes. A plurality of through holes are formed in the outer side of the upper end of the end frame 5 and in positions corresponding to joint screw holes of the solid rocket motor shell 2 and used for connecting the end frame 5 with a joint of the solid rocket motor shell 2 through bolts, and a plurality of round holes are uniformly distributed in the inner side of the upper end of the end frame 5 and used for fixing threaded round steel 6 to the round holes in the inner side of the end frame 5; the outer side of the lower end of the end frame 5 is provided with a plurality of through holes, and the end frame 5 is fixed with the test bed through bolts.
The invention provides a device. Fix the steel sheet to threaded round steel one end with the nut, the distance of steel sheet apart from the round steel terminal surface is 30mm, then reuse nut with threaded round steel other end fixed to the inboard round hole of end frame, through the distance of nut adjustment steel sheet apart from round steel one end, make steel sheet and head department equator line parallel and level, then with the bolt with the end frame with the articulate of solid rocket engine housing, be 1 with cement and sand weight ratio at last: 2, filling the concrete into the solid rocket engine shell, wherein the height of the concrete is flush with that of the steel plate, after the concrete is solidified, one end of the end frame is fixed on a ground test bed by using bolts, and a load is applied to a single skirt of the combustion chamber shell, so that the solid rocket engine skirt axial tension test can be performed.
When the method is specifically implemented, the steel plate is fixed at one end (A) of the round steel with the thread according to the sequence of the nut, the steel plate and the nut, and the nut is fixed at the other end (B) of the round steel with the thread; one end (B) of the round steel penetrates through holes on the inner sides of different distribution circles of the end frame, and then the round steel is fixed on the end frame through nuts; fixing the end frame assembly to the solid rocket engine shell joint by using bolts; mixing cement and sand according to the weight ratio of 1: 2, filling the concrete into the shell of the solid rocket engine, wherein the height of the concrete is flush with that of the steel plate, and waiting for the concrete to be cured;
when the solid rocket engine shell skirt axial tension test is carried out, one end of the end frame is fixed, and the solid rocket engine shell skirt is loaded.
The method can be applied to the solid rocket engine shell single-skirt or double-skirt axial pull test, and can also be applied to the axial pull test of the solid rocket engine shell with inconsistent loading of the front skirt and the rear skirt. The invention is proved to be feasible by experiments, and the axial tension load of the solid rocket engine shell skirt is obtained.
Claims (3)
1. The utility model provides a device that solid rocket engine housing single skirt axle pulled test, includes end frame assembly (1), solid rocket engine housing (2) and concrete (4), its characterized in that:
the end frame assembly (1) comprises an end frame (5), round steel (6) and a steel plate (8), wherein a plurality of through holes are formed in the outer side of the upper end of the end frame (5) and in positions corresponding to joint screw holes of a solid rocket engine shell (2), the through holes in the outer side of the upper end of the end frame (5) are used for connecting the end frame (5) and a joint of the solid rocket engine shell (2) together through bolts (3), a plurality of round holes are uniformly distributed in the inner side of the upper end of the end frame (5), the round holes in the inner side of the upper end of the end frame (5) are used for fixing the round steel (6) with threads to the round holes in the inner side of the upper end of the end frame (5), a plurality of through holes are formed in the outer side of the lower end of the end frame (5), and the through holes in the outer side of the lower end of the end frame (5) are used for fixing the end frame (5) and a test bed through bolts; threads are arranged at two ends of the round steel (6), one end of the round steel (6) is fixed on a round hole at the inner side of the upper end of the end frame (5) through a nut, and the other end of the round steel (6) is fixed on a steel plate (8) through a nut (7); a through hole is formed in the middle of the steel plate (8), the steel plate (8) is installed at one end of the round steel (6) through the through hole and is fixed by the nut (7), and the upper surface of the steel plate (8) is flush with the equator line of the end socket of the solid rocket engine shell (2);
the solid rocket engine shell (2) is fixedly arranged on an end frame (5) of the end frame assembly (1), concrete (4) is filled into the solid rocket engine shell (2), and the height of the concrete (4) is flush with the upper surface of the steel plate (8).
2. The apparatus of claim 1, wherein: the end frame (5) is made of high-strength steel.
3. The apparatus of claim 1, wherein: the solid rocket engine shell (2) is made of metal materials or composite materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611083786.3A CN107063840B (en) | 2016-11-30 | 2016-11-30 | Device for single skirt axial tension test of solid rocket engine shell |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611083786.3A CN107063840B (en) | 2016-11-30 | 2016-11-30 | Device for single skirt axial tension test of solid rocket engine shell |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107063840A CN107063840A (en) | 2017-08-18 |
| CN107063840B true CN107063840B (en) | 2021-11-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611083786.3A Active CN107063840B (en) | 2016-11-30 | 2016-11-30 | Device for single skirt axial tension test of solid rocket engine shell |
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| CN (1) | CN107063840B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114184386B (en) * | 2021-11-29 | 2023-07-21 | 西安航天动力测控技术研究所 | Spherical solid rocket engine testing device |
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| CN107063840A (en) | 2017-08-18 |
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