CN212206923U

CN212206923U - Solid rocket engine bonding interface shear stress test device

Info

Publication number: CN212206923U
Application number: CN202020823811.2U
Authority: CN
Inventors: 李金飞; 王玉峰; 曲凯; 刘铁; 管旭; 黄敬如
Original assignee: Naval Aeronautical University
Current assignee: Naval Aeronautical University
Priority date: 2020-05-18
Filing date: 2020-05-18
Publication date: 2020-12-22
Anticipated expiration: 2030-05-18

Abstract

The utility model relates to a solid rocket engine interface damage aassessment field specifically is a solid rocket engine bonding interface shear stress test device includes ES10-240 vibration test platform, bonding structure standard test piece, pedestal, standard balancing weight, nut, gasket. The utility model discloses fill the current technology blank, utilize current vibration test platform, pedestal and the fastener through the fixed this bonding structure standard test piece of bonding structure standard test piece and design, can predict the damage law of solid rocket engine combustion chamber interface under the shear stress effect through the damage law of bonding structure standard test piece under the effect of shear stress, for aassessment solid rocket engine combustion chamber interface mechanical properties provides the data support, 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 use maintenance efficiency.

Description

Solid rocket engine bonding interface shear stress test device

Technical Field

The utility model relates to a solid rocket engine bonding interface damage aassessment field specifically is a solid rocket engine bonding interface shear 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 shear 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 shear stress test device specially, the technical scheme who takes is:

the utility model provides a solid rocket engine bonding interface shear 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 is consistent with a solid rocket engine material and simulates a bonding 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 sides of the heat insulation layers, and screws are welded on the outer sides of the structural layer;

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 screw rods are formed in the vertical plates;

the standard balancing weight is provided with a screw hole in threaded connection with the screw rod;

the nut is in threaded connection with the screw rod so as to tightly back the standard balancing weight or fasten the bonding structure standard test piece on the vertical plate;

the gasket is sleeved on the screw rod and is respectively abutted against the vertical plate or the structural layer so as to limit the distance between the structural layer and the vertical plate.

Furthermore, 12 through holes in total are uniformly formed in one of the vertical plates in 3 rows and 4 columns, 4 rectangular holes are formed in the other vertical plate at positions corresponding to the 4 columns of through holes, 2 through holes which are vertically arranged are formed in the vertical plate on the outer side of the two rectangular holes on the outer side, 2 through holes which are vertically arranged are formed in the vertical plate between the two rectangular holes in the middle, the number of the through holes is 18, and the distance between the through holes is such that the standard test pieces of the bonding structure which are inserted through the through holes do not interfere with each other in the vibration process of the ES10-240 vibration 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 width of the rectangular hole is larger than the outer diameter, the top surface and the bottom surface of the nut beyond the circumferential outer edge of the corresponding nut.

The utility model discloses fill the current technology blank, utilize current vibration test platform, pedestal and the fastener through the fixed this bonding structure standard test piece of bonding structure standard test piece and design, can predict the damage law of solid rocket engine combustion chamber interface under the shear stress effect through the damage law of bonding structure standard test piece under the effect of shear stress, for aassessment solid rocket engine combustion chamber interface mechanical properties provides the data support, 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 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 an assembly diagram of the present invention during the test.

Fig. 5 is another perspective of fig. 4.

Detailed Description

The present invention will be further described with reference to the accompanying drawings.

Example 1, a solid rocket motor bonding interface shear stress test apparatus as shown in fig. 1-5, comprising an ES10-240 vibration test bench (not shown) manufactured by toyowa vibration testing instrument ltd;

7 bonding structure standard test pieces 1 which are consistent with materials of the solid rocket engine and simulate a bonding interface 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 screws 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.

The base body 2 comprises a bottom plate 21 fixedly connected with a bedplate of the ES10-240 vibration test bed through screws, two vertical plates 22 are fixedly connected on the bottom plate 21, and a plurality of through holes 23 capable of allowing the screw rods 15 to pass through are formed in the vertical plates 22; one of the vertical plates 22 is uniformly provided with 12 through holes 23 in total of 3 rows and 4 columns, the other vertical plate 22 is provided with 4 rectangular holes 24 corresponding to the 4 columns of through holes 23, the vertical plate 22 outside the two rectangular holes 24 at the outer side is provided with 2 through holes 23 arranged vertically, the vertical plate 22 between the two rectangular holes 24 at the middle part is provided with 2 through holes 23 arranged vertically, the number of the through holes 23 is 18, and the distance between the through holes 23 is the minimum requirement that the bonding structure standard test pieces 1 penetrating through the through holes do not interfere with each other in the vibration process of the ES10-240 vibration test bed. The width of the rectangular hole 24 is larger than the outer diameter, the top surface and the bottom surface of the nut 4 beyond the circumferential outer edge of the corresponding nut 4. The rectangular hole 24 is used for enabling a socket wrench to penetrate through the rectangular hole 24 to screw the nut on the opposite side vertical plate, and assembly is facilitated.

7 standard balancing weights 3, wherein each standard balancing weight 3 is provided with a screw hole 31 in threaded connection with the screw rod 15;

14 nuts 4, wherein the nuts 4 are screwed with the screw 15 to tightly back the standard balancing weight 3 or fasten the bonding structure standard test piece 1 on the vertical plate 22;

42 gaskets 5, the gaskets 5 are sleeved on the screw 15, and the two outermost gaskets are respectively abutted against the vertical plate 22 or the structural layer 14 to limit the distance between the structural layer 14 and the vertical plate 22.

The weight and the size of the bonding structure standard test piece 1 and the standard balancing weight 3 meet the national military standard.

6 gaskets 5 are respectively sleeved on the screw rod on one side of each of the 7 bonding structure standard test pieces 1, the screw rod with the gaskets 5 respectively penetrates through 7 through holes 23 on the uppermost layer of the two vertical plates, and then 7 nuts are screwed in the screw rod from the inner side of the vertical plate and screwed by using a socket wrench or a fork wrench, so that the 7 bonding structure standard test pieces 1 are respectively fastened on the 2 vertical plates. And the screw rod end on the other side is respectively screwed in a nut, a standard balancing weight 3 is screwed in, and the nut and the standard balancing weight are tightened by reversely rotating the nut. After the assembly is finished, the ES10-240 vibration test bed is started to operate for a set time according to a set frequency, after the time is finished, the damage conditions of 7 standard test pieces 1 with the bonding structures are respectively counted, then, the change rule of the shear stress is summarized according to the statistical result, so that the change rule and the damage rule of the shear 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 shear stress of the bonding structure 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 the impact load during road transportation, shipborne or shipborne duty.

Embodiment 2 is the same as embodiment 1 except that 18 bonding structure standard test pieces 1 are fixed in each through hole 23, the number of standard balancing weights, nuts and gaskets is correspondingly increased, the results of the change rule and the damage rule of the shear stress obtained by the experimental data of more test pieces or more batches of the experimental data are more practical, and the conclusion is more accurate.

Claims

1. The utility model provides a solid rocket engine bonding interface shear stress test device which characterized in that: comprises that

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 screw (15) is welded on the outer side of each structural layer (14);

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) which can allow the screw rods (15) to pass through are formed in the vertical plates (22);

the standard balancing weight (3), the said standard balancing weight (3) has screw (31) screwed with said threaded spindle (15);

the nut (4) is in threaded connection with the screw (15) to tightly back the standard balancing weight (3) or fasten the bonding structure standard test piece (1) on the vertical plate (22);

the gasket (5) is sleeved on the screw (15) and is respectively abutted against the vertical plate (22) or the structural layer (14) to limit the distance between the structural layer (14) and the vertical plate (22).

2. The solid-rocket engine bonding interface shear stress test device of claim 1, wherein: one of the vertical plates (22) is uniformly provided with 12 through holes (23) in total in 3 rows and 4 columns, the other vertical plate (22) is provided with 4 rectangular holes (24) at positions corresponding to the 4 columns of through holes (23), the vertical plate (22) at the outer sides of the two rectangular holes (24) at the outer side is respectively provided with 2 through holes (23) which are vertically arranged, the vertical plate (22) between the two rectangular holes (24) at the middle part is provided with 2 through holes (23) which are vertically arranged, the number of the through holes (23) is 18 in total, and the distance between the through holes is the lowest requirement that the bonding structure standard test pieces (1) which are inserted through the through holes do not interfere with each other in the vibration process of the ES10-240 vibration test bed.

3. The solid-rocket engine bonding interface shear 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 shear stress test device of claim 2, wherein: the width of the rectangular hole (24) is larger than the outer diameter, the top surface and the bottom surface of the nut (4) and exceeds the circumferential outer edge of the corresponding nut (4).