CN212206879U - Tensile and compressive stress test device for bonding interface of solid rocket engine - Google Patents
Tensile and compressive stress test device for bonding interface of solid rocket engine Download PDFInfo
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- CN212206879U CN212206879U CN202020822837.5U CN202020822837U CN212206879U CN 212206879 U CN212206879 U CN 212206879U CN 202020822837 U CN202020822837 U CN 202020822837U CN 212206879 U CN212206879 U CN 212206879U
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Abstract
The utility model relates to a tensile and compressive stress test device for a bonding interface of a solid rocket engine, which comprises an ES10-240 impact tester produced by Suzhou Dongzi vibration tester Limited; the standard test piece is consistent with the solid rocket engine material and simulates the bonding structure standard test piece of the solid rocket engine combustion chamber interface, and comprises a suspension rod, a seat body, a standard balancing weight and a nut. The utility model discloses utilize current vibration test platform, pedestal through bonding structure standard test piece and fixed this bonding structure standard test piece, suspension rod and fastener, can predict the damage law of solid rocket engine combustion chamber interface under the tension and compression stress effect through the damage law of bonding structure standard test piece under the tension and compression stress effect, provide data support for aassessment solid rocket engine combustion chamber interface mechanical properties, to extension solid rocket engine life, reduce the maintenance cost, improve and use maintenance efficiency and guarantee that the normal work of guided missile all has extremely important meaning.
Description
Technical Field
The utility model relates to a solid rocket engine bonding interface damage aassessment field specifically is a solid rocket engine bonding interface tension and compression stress test device.
Background
The solid rocket engine is subjected to vibration load action during road transportation, railway transportation, carrier-borne duty and boat-borne duty, alternating stress can be generated on the bonding interface of the solid rocket engine under the action of the vibration load, and the mechanical property of the bonding interface of the solid rocket engine can be reduced under the action of the long-term alternating stress, so that the structural integrity of the solid rocket engine is endangered.
At present, no experimental device specially used for evaluating the tensile and compressive stress of the bonding interface of the solid rocket engine exists.
Disclosure of Invention
The utility model aims at disclosing a be used for solid rocket engine bonding structure to draw pressure stress test device specially, the technical scheme who takes is:
a solid rocket engine bonding interface tension and compression stress test device is different from the prior art in that: comprises that
ES10-240 vibration test bench manufactured by eastern diamond vibration test bench, Suzhou;
the bonding structure standard test piece is consistent with a solid rocket engine material and simulates a combustion chamber interface of the solid rocket engine, the bonding structure standard test piece comprises a propellant test block, liners are arranged on two sides of the propellant test block, heat insulation layers are arranged on the outer sides of the liners, a structural layer is arranged on the outer side of the heat insulation layers, and a first screw rod is welded on the outer side of the structural layer;
the suspension rod comprises a second screw rod and a connecting block fixedly connected with the second screw rod, a first screw hole with the axis vertical to the axis of the second screw rod is formed in the connecting block, and the first screw hole can be in threaded connection with the first screw rod;
the base body comprises a bottom plate which can be fixedly connected with a bedplate of the ES10-240 vibration test bed, two vertical plates are fixedly connected on the bottom plate, and a plurality of through holes which can be penetrated by the second screw rods are formed in the vertical plates;
the standard balancing weight is provided with a second screw hole in threaded connection with the first screw rod;
and the nut is in threaded connection with the first screw rod or the second screw rod so as to tightly back the standard balancing weight or fasten the suspension rod on the vertical plate.
Furthermore, a total of 4 through holes are uniformly arranged near the top end of the vertical plate, and the distance between the through holes is such that the bonding structure standard test pieces mounted on the through holes do not interfere with each other in the vibration process of the ES10-240 impact test bed, and the height of the through holes is such that the bonding structure standard test pieces mounted on the through holes do not interfere with the bottom plate in the vibration process of the ES10-240 impact test bed.
Furthermore, the sections of the propellant test block, the lining, the heat insulating layer and the structural layer are square, and the side length is 20 mm; the thickness of propellant test block is 5mm, the thickness of lining is 1mm, the thickness of heat insulating layer is 4 mm.
Further, the length of the second screw rod on the outer side of the vertical plate is such that the bonding structure standard test piece mounted on the vertical plate does not interfere with the vertical plate during the vibration process of the ES10-240 impact test bed.
The utility model discloses fill the current technology blank, utilize current vibration test platform, through the pedestal of adhesive structure standard test piece and fixed this adhesive structure standard test piece, suspension rod and fastener, can predict the damage law of solid rocket engine combustion chamber interface under the tension and compression stress effect through the damage law of adhesive structure standard test piece under the tension and compression stress effect, provide data support for aassessment solid rocket engine combustion chamber interface mechanical properties, to extension solid rocket engine life, reduce the maintenance cost, it guarantees that the normal work of guided missile all has extremely important meaning to improve the use maintenance efficiency.
Drawings
Fig. 1 is a schematic structural diagram of the standard test piece with the bonding structure of the present invention.
Fig. 2 is a schematic structural view of the seat body of the present invention.
Fig. 3 is a schematic structural diagram of the standard counterweight of the present invention.
Fig. 4 is a schematic structural view of the suspension rod of the present invention.
Fig. 5 is an assembly diagram of the present invention during the test.
Detailed Description
The present invention will be further described with reference to the accompanying drawings.
Example 1, a solid rocket engine bonding interface tensile and compressive stress test apparatus as shown in fig. 1-5, comprising an ES10-240 vibration test bench manufactured by toyowa vibration test bench ltd;
4 bonding structure standard test pieces 1 which are consistent with materials of the solid rocket engine and simulate the interface of a combustion chamber of the solid rocket engine, wherein each bonding structure standard test piece 1 comprises a propellant test block 11, liners 12 are arranged on two sides of each propellant test block 11, heat insulation layers 13 are arranged on the outer sides of the liners 12, a structural layer 14 is arranged on the outer sides of the heat insulation layers 13, and first screw rods 15 are welded on the outer sides of the structural layers 14; the sections of the propellant test block 11, the lining 12, the heat insulating layer 13 and the structural layer 14 are square, and the side length is 20 mm; the thickness of propellant test block 11 is 5mm, the thickness of lining 12 is 1mm, and the thickness of heat insulating layer 13 is 4 mm.
4 suspension rods 6, each suspension rod comprises a second screw 61 and a connecting block 62 fixedly connected with the second screw, a first screw hole 63 with the axis vertical to the axis of the second screw is formed in the connecting block, and the first screw hole can be in threaded connection with the first screw; the length of the second screw rod on the outer side of the vertical plate is such that the bonding structure standard test piece mounted on the vertical plate does not interfere with the vertical plate in the vibration process of the ES10-240 impact test bed.
The base body 2 comprises a bottom plate 21 fixedly connected with a bedplate of the ES10-240 impact test bed through screws, two vertical plates 22 are fixedly connected on the bottom plate 21, and each vertical plate 22 is provided with 4 through holes 23 through which the screw rods 15 can pass; the through holes 23 are uniformly arranged in a row close to the top end of the vertical plate, and the distance between the through holes is the minimum requirement that the bonding structure standard test pieces 1 mounted on the through holes do not interfere with each other in the vibration process of the ES10-240 impact test bed. The height is such that the bonded structure standard specimen mounted thereon does not interfere minimally with the base plate during vibration of the ES10-240 impact test stand.
4 standard balancing weights 3, wherein the standard balancing weights 3 are provided with second screw holes 31 which are in threaded connection with the first screw rods 15;
16 nuts 4, wherein the nuts are in threaded connection with the first screw or the second screw so as to tightly back the standard balancing weight or fasten the suspension rod on the vertical plate.
The weight and the size of the bonding structure standard test piece 1 and the standard balancing weight 3 meet the national military standard.
When the test is carried out, firstly, the bonding structure standard test piece 1, the balance weight and the suspension rod are assembled together:
respectively screwing 1 nut into a first screw rod on one side of 4 bonding structure standard test pieces 1, enabling the distance between the outer end face of each nut and the free end of each first screw rod to exceed the depth of a screw hole of a standard balancing weight, then screwing the standard balancing weight on the first screw rod on the side, and then tightly backing up the standard balancing weight and the first screw rod by using a socket wrench or a fork wrench; then 1 nut is screwed in the first screw rod on the other side of the bonding structure standard test piece 1 respectively, so that the distance between the outer end face of the nut and the free end of the first screw rod exceeds the depth of the first screw hole 63 of the suspension rod 4, then the suspension rods 4 are screwed with the first screw rod on the other side of the bonding structure standard test piece 1 respectively, and a socket wrench or a fork wrench is used for tightly backing the suspension rods and the first screw rod. The assembly is thus formed.
Then install the assembly body on the riser:
1 nut of screw in respectively earlier on the second screw rod of 4 bull sticks for the distance of the outer terminal surface of this nut and the free end of second screw rod exceeds nut thickness plus riser 22 thickness, then penetrates 4 through-holes 23 of one side riser respectively with the second screw rod from its free end, and reuse 4 nuts are screwed in on the second screw rod and are screwed with box spanner or fork spanner from the inboard of riser, make 4 bull sticks fasten respectively on 2 risers.
After the installation is finished, the ES10-240 impact test bed is started to run for a set time according to a set frequency, after the time is over, the damage conditions of 4 bonding structure standard test pieces 1 are respectively counted, then, the change rule of the tensile and compressive stress is summarized according to the statistical result, so that the change rule and the damage rule of the tensile and compressive stress of the bonding interface of the solid rocket engine are further deduced, data support is provided for evaluating the mechanical property of the bonding interface of the solid rocket engine, has extremely important significance for prolonging the service life of the solid rocket engine, reducing the maintenance cost, improving the use and maintenance efficiency and ensuring the normal work of the missile, and the change rule and the damage rule of the bonding structure tensile and compressive stress of the standard test piece of the bonding structure can be used for providing data support for evaluating the damage of the solid rocket engine under the action of impact load during road transportation, shipborne or shipborne duty.
In embodiment 2, the other embodiments are the same as those in embodiment 1, except that 4 assemblies are also mounted on the vertical plate on the other side, and the obtained results of the change rule and the damage rule of the tensile stress and the compressive stress are more practical and the conclusion is more accurate due to more test pieces or more batches of experimental data.
Claims (4)
1. The utility model provides a solid rocket engine bonding interface tension and compression stress test device which characterized in that: comprises that
ES10-240 vibration test bench manufactured by eastern diamond vibration test apparatus, Suzhou;
the bonding structure standard test piece (1) is consistent with a solid rocket engine material and simulates a solid rocket engine combustion chamber interface, the bonding structure standard test piece (1) comprises a propellant test block (11), liners (12) are arranged on two sides of the propellant test block (11), a heat insulating layer (13) is arranged on the outer side of each liner (12), a structural layer (14) is arranged on the outer side of each heat insulating layer (13), and a first screw (15) is welded on the outer side of each structural layer (14);
the suspension rod (6) comprises a second screw rod (61) and a connecting block (62) fixedly connected with the second screw rod (61), a first screw hole (63) with the axis vertical to the axis of the second screw rod (61) is formed in the connecting block (62), and the first screw hole (63) can be in threaded connection with the first screw rod (15);
the base body (2) comprises a bottom plate (21) which can be fixedly connected with a bedplate of the ES10-240 vibration test bed, two vertical plates (22) are fixedly connected on the bottom plate (21), and a plurality of through holes (23) through which the second screw rods (61) can pass are formed in the vertical plates (22);
a standard balancing weight (3), wherein the standard balancing weight (3) is provided with a second screw hole (31) which is in threaded connection with the first screw rod (15);
the nut (4) is in threaded connection with the first screw (15) or the second screw (61) to tighten the standard balancing weight (3) or fasten the suspension rod (6) on the vertical plate (22).
2. The solid rocket engine bonding interface tensile and compressive stress test device of claim 1, wherein: a row of 4 through holes (23) are uniformly formed near the top end of the vertical plate (22), and the distance between the through holes is such that the bonding structure standard test pieces (1) mounted on the through holes do not interfere with each other in the vibration process of the ES10-240 vibration test bed, and the height of the through holes is such that the bonding structure standard test pieces (1) mounted on the through holes do not interfere with the bottom plate (21) in the vibration process of the ES10-240 vibration test bed.
3. The solid rocket engine bonding interface tensile and compressive stress test device of claim 1, wherein: the sections of the propellant test block (11), the lining (12), the heat insulating layer (13) and the structural layer (14) are square, and the side length is 20 mm; the thickness of the propellant test block (11) is 5mm, the thickness of the lining layer (12) is 1mm, and the thickness of the heat insulating layer (13) is 4 mm.
4. The solid rocket engine bonding interface tensile and compressive stress test device of claim 1, wherein: the length of the second screw (61) on the outer side of the vertical plate (22) is such that the bonding structure standard test piece (1) mounted on the vertical plate does not interfere with the vertical plate in the vibration process of the ES10-240 vibration test bed.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202020822837.5U CN212206879U (en) | 2020-05-18 | 2020-05-18 | Tensile and compressive stress test device for bonding interface of solid rocket engine |
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| CN202020822837.5U CN212206879U (en) | 2020-05-18 | 2020-05-18 | Tensile and compressive stress test device for bonding interface of solid rocket engine |
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| CN212206879U true CN212206879U (en) | 2020-12-22 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112665769A (en) * | 2021-03-15 | 2021-04-16 | 南昌新宝路航空科技有限公司 | Method for detecting machining stress of numerical control aviation thin-walled part |
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2020
- 2020-05-18 CN CN202020822837.5U patent/CN212206879U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112665769A (en) * | 2021-03-15 | 2021-04-16 | 南昌新宝路航空科技有限公司 | Method for detecting machining stress of numerical control aviation thin-walled part |
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