CN212206879U - A tensile and compressive stress test device for bonding interface of solid rocket motor - Google Patents

Abstract

The utility model relates to a tensile and compressive stress test device for the bonding interface of a solid rocket motor, comprising an ES10-240 impact tester produced by Suzhou Dongling Vibration Testing Instrument Co., Ltd.; The standard test piece of the bonding structure, suspension rod, seat body, standard counterweight, and nut. The utility model utilizes the existing vibration test bench, through the bonding structure standard test piece and the seat body, the suspension rod and the fastener for fixing the bonding structure standard test piece, the tensile and compressive stress of the bonding structure standard test piece can be achieved by bonding the structure standard test piece. The damage law of the solid rocket motor combustion chamber interface under the action of tensile and compressive stress is used to predict the damage law of the solid rocket motor combustion chamber interface, which provides data support for evaluating the mechanical properties of the solid rocket motor combustion chamber interface. It is extremely important to use and maintain the efficiency to ensure the normal operation of the missile.

Description

A tensile and compressive stress test device for bonding interface of solid rocket motor

technical field

The utility model relates to the field of damage assessment of the bonding interface of a solid rocket motor, in particular to a tensile and compressive stress test device of the bonding interface of a solid rocket motor.

Background technique

The solid rocket motor will be subjected to vibration loads during road transportation, railway transportation, ship-borne duty and boat-borne duty. Under the action of these vibration loads, the bonding interface of the solid rocket motor will generate alternating stress, and the long-term alternating stress will act. It will lead to the decline of the mechanical properties of the solid rocket motor bonding interface and endanger the structural integrity of the solid rocket motor.

At present, there is no experimental device specially used to evaluate the tensile and compressive stress of the bonding interface of solid rocket motor.

SUMMARY OF THE INVENTION

The purpose of this utility model is to disclose a kind of test device specially used for solid rocket motor bonding structure tensile and compressive stress, and the technical scheme adopted is:

A tensile and compressive stress test device for a bonding interface of a solid rocket motor, which is different from the prior art in that it includes:

ES10-240 vibration test bench produced by Suzhou Dongling Vibration Test Bench Co., Ltd.;

The bonding structure standard test piece is consistent with the solid rocket motor material and simulates the solid rocket motor combustion chamber interface. The bonding structure standard test piece includes a propellant test block, and the two sides of the propellant test block are linings. The outer side of the lining layer is a thermal insulation layer, the outer side of the thermal insulation layer is a structural layer, and the outer side of the structural layer is welded with a first screw;

A suspension rod, the suspension rod includes a second screw rod, a connecting block fixedly connected with the second screw rod, a first screw hole whose axis is perpendicular to the axis of the second screw rod is opened on the connecting block, and the first screw hole is the hole can be screwed with the first screw;

A seat body, the seat body includes a bottom plate that can be fixedly connected with the platform of the ES10-240 vibration test bench, two vertical plates are fixed on the bottom plate, and a plurality of The through hole through which the two screws pass;

a standard counterweight block, the standard counterweight block has a second screw hole screwed with the first screw rod;

a nut, the nut is screwed with the first screw rod or the second screw rod to back tighten the standard weight block or fasten the suspension rod on the vertical plate.

Further, a total of 4 through holes are evenly arranged near the top of the vertical plate, and the spacing is so that the standard test piece of the bonding structure installed on it will not be affected during the vibration of the ES10-240 impact test bench. Interfering with each other, the height is such that the standard test piece of the bonding structure installed thereon does not interfere with the base plate during the vibration of the ES10-240 impact test bench.

Further, the cross section of the propellant test block, the lining layer, the thermal insulation layer and the structural layer is a square, and the side length is 20 mm; the thickness of the propellant test block is 5 mm, the thickness of the lining layer is 1 mm, and the thickness of the thermal insulation layer is 4mm.

Further, the length of the second screw on the outside of the vertical plate is such that the standard test piece of the bonding structure installed on the vertical plate does not contact the ES10-240 impact test bench during vibration. Vertical plate interference.

The utility model fills the gap of the current technology, utilizes the existing vibration test bench, and can pass the standard test of the bonding structure by bonding the standard test piece of the bonding structure and the seat body, the suspension rod and the fastener for fixing the standard test piece of the bonding structure. The damage law of parts under tensile and compressive stress can be used to predict the damage law of solid rocket motor combustion chamber interface under tensile and compressive stress. It is of great significance to reduce maintenance costs and improve the efficiency of use and maintenance to ensure the normal operation of missiles.

Description of drawings

Fig. 1 is the structural schematic diagram of the standard test piece of the bonding structure of the present invention.

FIG. 2 is a schematic diagram of the structure of the seat of the present invention.

Fig. 3 is the structural schematic diagram of the standard counterweight of the present invention.

FIG. 4 is a schematic structural diagram of a suspension rod of the present invention.

FIG. 5 is a schematic view of the assembly of the present utility model during the test.

Detailed ways

The present utility model will be further described below in conjunction with the accompanying drawings.

Embodiment 1, a solid rocket motor bonding interface tensile and compressive stress test device as shown in Figures 1-5, including an ES10-240 vibration test bench produced by Suzhou Dongling Vibration Test Bench Co., Ltd.;

4 standard test pieces 1 for bonding structure that are consistent with the material of the solid rocket motor and simulate the interface of the combustion chamber of the solid rocket motor. The standard test piece 1 for the bonding structure includes a propellant test block 11. The side is the lining layer 12, the outer side of the lining layer 12 is the thermal insulation layer 13, the outer side of the thermal insulation layer 13 is the structural layer 14, the outer side of the structural layer 14 is welded with the first screw 15; the propellant test block 11, the lining layer 12. The cross section of the heat insulating layer 13 and the structural layer 14 is square, and the side length is 20 mm; the thickness of the propellant test block 11 is 5 mm, the thickness of the lining layer 12 is 1 mm, and the thickness of the heat insulating layer 13 is 4 mm.

Four suspension rods 6, the suspension rods include a second screw 61, a connecting block 62 fixedly connected to the second screw, and a first screw hole 63 whose axis is perpendicular to the axis of the second screw is provided on the connecting block , the first screw hole can be screwed with the first screw; the length of the second screw on the outside of the vertical plate is such that the standard test piece of the bonding structure installed on the vertical plate is The ES10-240 impact test bench does not interfere with the vertical plate during the vibration process.

A base body 2, the base body 2 includes a bottom plate 21 fixed to the table plate of the ES10-240 impact test bench by screws, and two vertical plates 22 are fixed on the bottom plate 21, each of the vertical plates 22 are provided with four through holes 23 that can accommodate the screw 15 to pass through; the through holes 23 are evenly arranged in a row near the top of the vertical plate, and the spacing is such that the standard test piece 1 of the bonding structure installed on it is in the place. The ES10-240 impact test bench does not interfere with each other during the vibration process as the minimum requirement. The height is the minimum requirement that the standard specimen of the bonding structure installed thereon does not interfere with the bottom plate during the vibration of the ES10-240 impact test bench.

4 standard weights 3, the standard weights 3 have second screw holes 31 screwed with the first screw 15;

16 nuts 4, the nuts are screwed with the first screw rod or the second screw rod to back tighten the standard weight block or fasten the suspension rod on the vertical plate.

The weight and size of the standard specimen 1 of the bonding structure and the standard counterweight 3 meet the requirements of the national military standard.

When conducting the test, first assemble the standard specimen 1 of the bonded structure, the counterweight and the suspension rod together:

A nut is screwed into the first screw on one side of the four bonding structure standard test pieces 1, so that the distance between the outer end surface of the nut and the free end of the first screw exceeds the depth of the screw hole of the standard counterweight, and then the standard Screw the weight on the first screw on this side, then use a socket wrench or fork wrench to back-tighten the standard weight and the first screw; Insert a nut so that the distance between the outer end surface 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, and then connect the 4 suspension rods to the other side of the bonding structure standard test piece 1 respectively. Screw the first screw, use a socket wrench or a fork wrench to back-tighten the suspension rod and the first screw. The assembly is thus formed.

Then mount the assembly on the riser:

First screw a nut into the second screw rod of the four suspension rods, so that the distance between the outer end surface of the nut and the free end of the second screw rod exceeds the thickness of the nut plus the thickness of the vertical plate 22, and then the second screw rod is separated from its free end. Insert into the 4 through holes 23 of the vertical plate on one side, then screw 4 nuts into the second screw from the inner side of the vertical plate and tighten with a socket wrench or a fork wrench, so that the 4 suspension rods are respectively fastened on the 2nd screw. a stand.

In this way, the installation is completed, start the ES10-240 impact test bench, and make it run for the set time at the set frequency. After the time is over, count the damage of 4 standard test pieces of bonding structure 1 respectively, and then summarize according to the statistical results. The change law of its tensile and compressive stress, and then infer the change law and damage law of the tensile and compressive stress of the solid rocket motor bonding interface, provide data support for evaluating the mechanical properties of the solid rocket motor bonding interface, and prolong the service life of the solid rocket motor and reduce the damage. It is of great significance to maintain the cost of maintenance and improve the efficiency of use and maintenance to ensure the normal operation of the missile, and it can be used to evaluate the road transportation, shipborne or boat-borne through the change law and damage law of the tensile and compressive stress of the bonding structure standard test piece. Provide data support for the damage of solid rocket motors under impact load on duty.

Example 2, the other is the same as Example 1, the difference is that 4 assemblies are also installed on the vertical plate on the other side, more test pieces or more batches of experimental data, the variation law of tensile and compressive stress obtained The results of the damage law are more in line with reality, and the conclusion is more accurate.

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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