CN111707431B

CN111707431B - Device and method for testing explosion-proof shock wave performance of cabin protection structure

Info

Publication number: CN111707431B
Application number: CN202010404079.XA
Authority: CN
Inventors: 栗志杰; 杨丰源; 柳占立; 庄茁; 崔一南; 由小川
Original assignee: Tsinghua University
Current assignee: Tsinghua University
Priority date: 2020-05-13
Filing date: 2020-05-13
Publication date: 2021-06-11
Anticipated expiration: 2040-05-13
Also published as: CN111707431A

Abstract

The invention discloses a testing device for detecting the explosion-proof shock wave performance of a cabin protection structure and a method for detecting the effectiveness of the testing device, and relates to the field of mechanics, wherein the testing device comprises: the system comprises an equivalent cabin system, a protective structure supporting system and a testing system, wherein the equivalent cabin system is obtained by reconstructing a real cabin structure according to each size of the internal space of the real cabin based on an equal proportion principle and is used for simulating the real cabin; the protective structure supporting system provides constraint force for the baffle of the structure to be measured so as to truly reflect the constraint and deformation states of the baffle of the structure to be measured under the action of explosion shock waves under the condition of a real cabin; the test system is used for researching the dynamic evolution process of the shock wave in the cabin structure and measuring pressure data and acceleration data. The performance testing device provided by the invention is used as an effective testing means for the explosion-proof shock wave performance of the cabin protection structure, can also be used for researching the scale law effect of the explosion-proof shock wave performance of the cabin structure, and has important value and extremely high practicability.

Description

Device and method for testing explosion-proof shock wave performance of cabin protection structure

Technical Field

The invention relates to the field of mechanics, in particular to a testing device for detecting the explosion-proof shock wave performance of a cabin protection structure and a method for detecting the effectiveness of the testing device.

Background

In modern battlefield environments, the intense shock waves generated upon detonation of high-equivalent explosives have tremendous destructive power, causing significant damage to critical compartments within surrounding armor, such as: the damage of landmine explosion to the interior of an armored vehicle, the damage of torpedo explosion to a ship cabin body, the damage of the implosion of a ship key cabin body to surrounding cabins and the like are achieved, therefore, the improvement of the performance of the cabin structure for protecting explosion shock waves is of great importance to the protection of the armored key cabin body, and an effective experimental testing device is the basis of such research.

Under the current situation, the test of the explosion-proof shock wave performance of the cabin protection structure is generally based on the experiment of a real cabin. The test cost of the test is high, the test period is long, and the test is not beneficial to screening high-performance protective structures through a large number of tests. In addition, the evaluation of the cabin protective structure explosion-proof shock wave performance is generally based on the damage form of the protective structure, but the index cannot completely reflect the effect of the cabin protective structure explosion-proof shock wave. In particular, when the protective structure itself is not damaged, the blast shock waves passing through the protective structure can also damage the protected target in the cabin. Therefore, it is necessary to establish a simple but effective experimental test method for the explosion-proof shock wave performance of the cabin protection structure and to provide a more reasonable test index for evaluating the performance of the protection structure, which is a clear problem to be solved.

Disclosure of Invention

In view of the above problems, the present invention provides a testing apparatus for detecting the performance of a cabin protection structure against an explosion shock wave and a method for detecting the effectiveness thereof, which solves the above problems.

The embodiment of the invention provides a testing device for detecting explosion impact resistance of a cabin protection structure, which comprises: the device comprises an equivalent cabin system, a protective structure supporting system and a testing system, wherein the device can evaluate the performance of the explosion-proof shock wave of a real cabin structure;

the equivalent cabin system comprises: the baffle structure and the space adjusting structure are used for reconstructing the real cabin structure based on an equal proportion principle according to each size of the internal space of the real cabin and are used for simulating the real cabin;

the baffle structure includes: the structure comprises a structure baffle to be tested, four side baffles, four front baffles, a back baffle and a movable baffle, wherein the four side baffles, the back baffle and the structure baffle to be tested are respectively combined and connected to form the equivalent cabin; the structure baffle to be detected is a baffle made of a material to be detected for preventing explosion shock waves, the structure form and the size of the structure baffle to be detected are the same as the real cabin protection structure form, and the front end face of the structure baffle to be detected is a wave-facing surface;

the space adjusting structure includes: the adjusting screw and the fixing nut are used for adjusting the position of the movable baffle through the combined action of the adjusting screw and the fixing nut so as to adjust the internal space of the equivalent cabin, so that each size proportion of the internal space of the equivalent cabin truly reflects each size proportion of the internal space of the real cabin;

the protective structure support system comprises: the structure baffle to be measured is connected with the side baffles and the front baffles through the rigidity adjusting devices, the rigidity adjusting devices provide restraint force for the structure baffle to be measured, and the size of the restraint force can be determined based on a theoretical calculation or numerical simulation method so as to truly reflect the restraint and deformation states of the structure baffle to be measured under the action of explosion shock waves under the real cabin condition;

the test system comprises: the free field pressure sensor, the reflecting surface pressure sensor and the acceleration sensor are used for completely measuring the shock wave resistance of the cabin protection structure and the dynamic evolution process of the shock wave in the cabin;

the free field pressure sensor is used for measuring pressure data of the explosion shock wave entering the equivalent cabin at a corresponding position;

the reflecting surface pressure sensor is used for measuring pressure data after the explosion shock waves entering the equivalent cabin and the explosion shock waves reflected by the movable baffle are superposed;

the acceleration sensor is used for measuring acceleration data of the baffle of the structure to be measured under the action of the explosion shock waves.

Optionally, the side baffles, the movable baffles and the back baffles of the baffle structure are assembled by adopting a unitized splicing process, each baffle for splicing has multiple specifications, and is provided with a connecting end so as to splice cross section sizes of any proportion according to the scaling of the equivalent cabin;

the longitudinal size of the equivalent cabin system is adjusted by adjusting the position of the movable baffle plate, so that the space size proportion of the equivalent cabin is consistent with that of the real cabin, and the real cabin is reconstructed according to different scaling ratios.

Optionally, one end of the adjusting screw is fixed to the movable baffle, and the other end of the adjusting screw penetrates through the rear baffle;

adjusting the position of the adjusting screw rod to enable the movable baffle to move back and forth along the inner walls of the four side baffles so as to adjust the inner space of the equivalent cabin;

after the adjustment of the inner space of the equivalent cabin is finished, the position of the adjusting screw rod is fixed through the fixing nut, so that each size proportion of the inner space of the equivalent cabin truly reflects each size proportion of the inner space of the real cabin.

Optionally, the baffle structure further comprises: the four front baffles are respectively fixed at preset positions in front of the inner walls of the four side baffles and are used for fixedly connecting the plurality of groups of rigidity adjusting devices;

each group of rigidity adjusting devices in the multiple groups of rigidity adjusting devices comprises: two axial stiffness adjusters and one rotational stiffness adjuster;

one end of one of the two axial stiffness regulators is fixed with the baffle of the structure to be tested, and the other end of the axial stiffness regulator is fixed with the inner wall of the side baffle to provide lateral constraint force for the baffle of the structure to be tested;

one end of the other axial stiffness adjuster in the two axial stiffness adjusters is fixed with the baffle of the structure to be tested, and the other end of the other axial stiffness adjuster is fixed with the front surface of the front baffle to provide a normal restraining force for the baffle of the structure to be tested;

one end of the rotary rigidity regulator is fixed with the baffle of the structure to be tested, and the other end of the rotary rigidity regulator is fixed with the side baffle to provide rotary constraint force for the baffle of the structure to be tested;

the installation positions of the multiple groups of rigidity adjusting devices are symmetrical up and down, left and right, and the number of the rigidity adjusting devices is 4 and multiples of 4.

Optionally, the two axial stiffness adjusters and the one rotational stiffness adjuster are both springs;

the axial stiffness regulator providing lateral constraint force is a lateral spring, and the axial stiffness regulator providing normal constraint force is a normal spring;

the rotary rigidity regulator providing the rotary constraint force is a bending moment spring;

the stiffness values of the lateral springs, the normal springs and the bending moment springs are obtained based on theoretical analysis or calculation simulation.

Optionally, the free-field pressure sensor is disposed in the equivalent cabin through a support rod, the position of the free-field pressure sensor is determined by the relative position of the protected target in the real cabin, and the number of the free-field pressure sensor is determined by the number of measurement position points required by the protected target in the real cabin, and the free-field pressure sensor is specifically used for measuring pressure data generated by the action of the explosion shock wave entering the equivalent cabin on the protected target;

the reflecting surface pressure sensors are 5 pressure sensors embedded on the movable baffle, the sensing surfaces of the 5 pressure sensors are flush with the front end surface of the movable baffle and are respectively positioned at the central position and the peripheral symmetrical position of the front end surface of the movable baffle, and the 5 pressure sensors are fixed through holes prefabricated on the movable baffle and are specifically used for measuring pressure data of explosion shock waves entering the equivalent cabin after being reflected by the movable baffle;

acceleration sensor is for being fixed in 5 acceleration sensor on the structure baffle back wave surface that awaits measuring, these 5 acceleration sensor are located respectively the central point of the structure baffle back wave surface that awaits measuring puts and symmetrical position all around, and these 5 acceleration sensor pass through the prefabricated hole of the structure baffle that awaits measuring is fixed, specifically is used for measuring under the blast shock wave effect the acceleration data of structure baffle that awaits measuring.

Optionally, the test system further comprises: a signal acquisition device;

the free field pressure sensor, the reflecting surface pressure sensor and the acceleration sensor are all connected with the signal acquisition equipment through cables, and the data acquired by the free field pressure sensor, the reflecting surface pressure sensor and the acceleration sensor are sent to the signal acquisition equipment;

the movable baffle plate and the back baffle plate are provided with holes, and the cable penetrates through the holes and is connected with the signal acquisition equipment.

Optionally, a first sealing treatment technology is adopted between the inner wall of the equivalent cabin and the movable baffle, and between the baffle of the structure to be tested and the four side baffles, so as to ensure that the equivalent cabin is a closed cabin, and simulate a closed structure of a real cabin;

holes prefabricated on the movable baffle plate and openings of the movable baffle plate and the back baffle plate adopt a second sealing treatment technology to ensure that the equivalent cabin is a closed cabin so as to simulate the closed structure of a real cabin;

the first sealing treatment technology is realized on the basis of aluminum alloy metal, the surface of the aluminum alloy metal is subjected to super-lubrication treatment, vaseline is coated on the surface of the aluminum alloy metal, and the super-lubrication sealing treatment technology can be realized at the joint of the aluminum alloy metal and the vaseline;

the second sealing treatment technology is realized based on the silica gel sealing ring, and the sealing treatment technology is realized by the deformation characteristic of the silica gel sealing ring under high pressure.

Optionally, a connecting device is arranged on the rear end face of the back baffle, and the testing device is fixed on the base at the tail end of the shock tube testing platform through the connecting device, so that the test on the explosion impact resistance of the cabin protection structure is realized.

The embodiment of the present invention further provides a method for detecting validity of a testing apparatus for detecting explosion impact resistance of a cabin protective structure, where the testing apparatus is the testing apparatus for detecting explosion impact resistance of a cabin protective structure as described in any one of the above, and the method includes:

step 1: preparing a side baffle, a back baffle and a movable baffle based on a unitized splicing process according to the size ratio and the determined scaling ratio of the internal space structure of the real cabin, and determining the position of the movable baffle so that the internal space structure of the equivalent cabin is a reduced model of the internal space structure of the real cabin in the same scale;

step 2: based on a theoretical method or a numerical simulation method, obtaining values of two axial rigidities and one bending rigidity of the boundary section of the baffle plate of the structure to be tested under the structural dimension of the internal space of the equivalent cabin, and adjusting the two axial rigidity regulators and the rotary rigidity regulator according to the values to provide proper supporting conditions for the baffle plate of the structure to be tested;

and step 3: arranging and installing the free field pressure sensor, the reflecting surface pressure sensor and the acceleration sensor according to the test requirements, and completing the debugging of the signal acquisition equipment;

and 4, step 4: sealing holes prefabricated on the movable baffle, the movable baffle and the openings of the back baffle and the movable baffle between the inner wall of the equivalent cabin and the movable baffle and between the baffle of the structure to be tested and the four side baffles respectively by adopting a sealing treatment technology to form a closed equivalent cabin, and finally forming an integral testing device;

and 5: fixing the integral testing device on a base at the tail end of a shock tube testing platform through the connecting device, and enabling the wave-facing surface to face the direction of the explosive shock waves so that the explosive shock waves vertically act on the wave-facing surface;

step 6: according to the load requirement of the explosion shock wave, selecting a proper membrane to carry out a shock wave tube experiment, wherein the shock wave formed by high-pressure gas in the shock wave tube acts on the baffle plate of the structure to be tested to generate acceleration, and formed acceleration data is sensed by the acceleration sensor and transmitted to the signal acquisition equipment through the cable; the explosion shock wave enters the equivalent cabin after passing through the baffle of the structure to be detected, the transmission pressure generated by compressing the air in the equivalent cabin reaches the surfaces of the free field pressure sensor and the reflecting surface pressure sensor, and the pressure data formed by the transmission pressure reaches the surfaces of the free field pressure sensor and the reflecting surface pressure sensor and is transmitted to the signal acquisition equipment through the cable;

and 7: and obtaining deformation information of the baffle of the structure to be tested, pressure information at a specific position in the equivalent cabin and pressure information after reflection and superposition of the inner wall of the equivalent cabin based on the obtained acceleration data and the pressure data, evaluating the damage condition of the protected target under corresponding conditions by combining the damage index of the protected target, and determining the explosion-proof shock wave performance of the cabin protection structure by integrating the test result and the damage condition of the protected target.

According to the performance testing device, an equivalent cabin system which reconstructs a real cabin structure based on an equal proportion principle replaces a large-size real cabin, and the explosion shock wave resistance performance of the cabin protection structure is tested; the real cabins in different forms are effectively scaled in the same proportion by the unit splicing technology of the baffle structure of the equivalent cabin system and the position of the movable baffle is adjusted, the real cabins can be reconstructed in series by adopting different scaling ratios, and the influence rule of the size effect of the equivalent cabin on the test result is researched; determining the boundary supporting condition of a baffle plate of a structure to be detected in an equivalent cabin system based on the constraint action information of an adjacent cabin and an auxiliary structure when the real cabin protection structure deforms under the action of the explosion shock wave, establishing a supporting system of the protection structure, and truly reflecting the constraint state and the dynamic evolution process of the cabin protection structure under the action of the explosion shock wave; the equivalent cabin forms a closed test chamber by using a sealing technology, so that the explosion shock wave can be effectively prevented from being diffracted to enter the cabin to influence the measurement result; deformation information of a protective structure (namely a baffle of a structure to be detected) under explosion shock waves and evolution information of the pressure of the shock waves in the cabin can be obtained through a plurality of acceleration sensors and pressure sensors (including a free field pressure sensor and a reflecting surface pressure sensor), wherein the evolution information comprises pressure information of any space position in the cabin and pressure information after reflection on the inner wall of the cabin; and the damage of the protected target can be evaluated by combining with the damage threshold of the protected target, so that the comprehensive protection performance of the cabin protection structure for preventing the explosion shock wave is further determined. The performance testing device provided by the invention is used as an effective testing means for the explosion-proof shock wave performance of the cabin protection structure, can also be used for researching the scale law effect of the explosion-proof shock wave performance of the cabin structure, and has important value and extremely high practicability.

Drawings

Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:

FIG. 1 is a schematic diagram of a testing apparatus for detecting explosion impact resistance of a cabin protection structure according to an embodiment of the present invention;

FIG. 2 is a schematic diagram of the location of 5 pressure sensors on the front face of a moving barrier in accordance with an embodiment of the present invention;

FIG. 3 is a schematic model of a base and a base to which a pressure sensor is attached according to an embodiment of the present invention;

FIG. 4 is a schematic view of an actual cabin and an equivalent cabin of an embodiment of the present invention;

FIG. 5 is a graph of pressure data in a closed test chamber tested using a shock tube experimental platform in an embodiment of the present invention;

FIG. 6 is a schematic diagram of a device for testing the pressure amplitude performance of the high molecular polymer material in attenuating the explosive shock wave according to an embodiment of the present invention;

FIG. 7 is a schematic view of a cubic test chamber in an embodiment of the present invention;

FIG. 8 is a front view of a device for testing the pressure amplitude performance of the high molecular weight polymer material in attenuating the explosive shock wave according to an embodiment of the present invention.

Detailed Description

In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below. It should be understood that the specific embodiments described herein are merely illustrative of the invention, but do not limit the invention to only some, but not all embodiments.

Referring to fig. 1, a schematic diagram of a testing apparatus for detecting explosion and impact resistance of a cabin protection structure according to an embodiment of the present invention is shown, the apparatus including: equivalent cabin system, protective structure braced system, test system, testing arrangement can assess the performance of true cabin structure blast shock wave of preventing.

Specifically, the equivalent cabin system comprises: the baffle structure and the space adjusting structure are obtained by reconstructing the real cabin structure according to all sizes of the internal space of the real cabin on the basis of an equal proportion principle and are used for simulating the real cabin so as to reflect the environment, relevant parameters, properties and the like of the real cabin. The baffle structure includes: the structure comprises a structure baffle to be tested, four side baffles, four front baffles, a back baffle and a movable baffle, wherein the four side baffles, the back baffle and the structure baffle to be tested are respectively combined and connected to form an equivalent cabin; the structure baffle to be detected is a baffle made of a material to be detected for preventing explosion shock waves, namely, the structure baffle to be detected is a protective structure, the structure form and the size of the structure baffle to be detected are the same as the real cabin protective structure form, and the front end face of the structure baffle to be detected is a wave-facing surface, namely the wave-facing surface of the whole cabin protective structure. The back baffle is provided with a connecting device on the rear end face, and the whole testing device can be fixed on the base at the tail end of the shock tube testing platform through the connecting device, so that the test on the explosion impact resistance of the cabin protection structure is realized. The four front baffles are respectively fixed at preset positions in front of the inner walls of the four side baffles and are used for fixedly connecting a plurality of groups of rigidity adjusting devices, and the four front baffles are specifically described below and are not repeated herein.

In the embodiment of the invention, the side baffle, the movable baffle and the back baffle of the baffle structure are assembled by adopting a unitized splicing process, and the corresponding splicing units have various specifications and are provided with connecting ends, so that cross section sizes of any proportion can be spliced according to the scaling of an equivalent cabin; the longitudinal size of the equivalent cabin system is adjusted by adjusting the position of the movable baffle plate, so that the space size proportion of the equivalent cabin is consistent with that of the real cabin, and the real cabin is reconstructed according to different scaling ratios.

In an embodiment of the present invention, the space adjusting structure includes: one end of the adjusting screw rod is fixed on the movable baffle, the other end of the adjusting screw rod penetrates through the rear baffle, and a hole is naturally formed at the position corresponding to the rear baffle through which the adjusting screw rod penetrates; the position of the adjusting screw rod is adjusted, so that the movable baffle can move back and forth along the inner walls of the four side baffles, and the inner space of the equivalent cabin can be adjusted; after the adjustment of the inner space of the equivalent cabin is finished, the position of the adjusting screw rod is fixed through the fixing nut, so that all sizes of the inner space of the equivalent cabin are fixed, and all size proportions of the inner space of the equivalent cabin can truly reflect all size proportions of the inner space of the real cabin.

In an embodiment of the present invention, a protective structure support system includes: the structure baffle to be measured is connected with the side baffles and the front baffles through the multiple groups of rigidity adjusting devices, and the multiple groups of rigidity adjusting devices can provide constraint force for the structure baffle to be measured so as to truly reflect the constraint and deformation states of the structure baffle to be measured under the real cabin condition under the action of the explosion shock waves.

Specifically, each group of rigidity adjusting devices in the multiple groups of rigidity adjusting devices comprises: two axial stiffness adjusters and one rotational stiffness adjuster; one end of one axial stiffness regulator in each of the two axial stiffness regulators is fixed with the baffle of the structure to be tested, and the other end of the axial stiffness regulator is fixed with the inner wall of the side baffle to provide lateral constraint force for the baffle of the structure to be tested; one end of the other axial stiffness regulator in the two axial stiffness regulators is fixed with the baffle of the structure to be tested, and the other end of the other axial stiffness regulator is fixed with the front surface of the front baffle to provide a normal restraining force for the baffle of the structure to be tested; one end of the rotating rigidity regulator is fixed with the baffle of the structure to be measured, and the other end of the rotating rigidity regulator is fixed with the side baffle, so that rotating constraint force is provided for the baffle of the structure to be measured. Both the two axial stiffness adjusters and the one rotational stiffness adjuster can be springs, and of course, any other stiffness adjuster can be adopted, and only the requirement of the restraining force needs to be met, and the springs are one of the preferred choices.

Referring to fig. 1, in the embodiment of the present invention, the axial stiffness adjuster providing the lateral restraining force is a lateral spring, and the axial stiffness adjuster providing the normal restraining force is a normal spring; the rotary rigidity regulator providing the rotary constraint force is a bending moment spring; the stiffness numerical values of the lateral springs, the normal springs and the bending moment springs are obtained based on theoretical analysis or calculation simulation. During installation, if one group of lateral springs, normal springs and bending moment springs are installed at the middle positions of the baffle plate of the structure to be tested and the side baffle plate above the baffle plate, the other group of lateral springs, normal springs and bending moment springs are symmetrically installed at the middle positions of the baffle plate of the structure to be tested and the side baffle plate below the baffle plate of the structure to be tested; the third group of lateral springs, the normal springs and the bending moment springs are required to be arranged at the middle positions of the structural baffle to be tested and the right side baffle, and the fourth group of lateral springs, the normal springs and the bending moment springs are required to be arranged at the middle positions of the structural baffle to be tested and the left side baffle; if one group of lateral springs, normal springs and bending moment springs are arranged at the position, deviating to the right, of the middle of the baffle plate of the structure to be tested and the side baffle plate above, the other group of lateral springs, normal springs and bending moment springs are symmetrically arranged at the position, deviating to the left, of the middle of the baffle plate of the structure to be tested and the side baffle plate below; the third group of lateral springs, normal springs and bending moment springs are arranged at the right-biased positions between the baffle of the structure to be tested and the right side baffle, and the fourth group of lateral springs, normal springs and bending moment springs are required to be arranged at the left-biased positions between the baffle of the structure to be tested and the left side baffle; in short, the installation positions of the multiple groups of rigidity adjusting devices need to be symmetrical up, down, left and right, and the number of the rigidity adjusting devices is 4 and multiples of 4. In addition, it should be noted that the lateral springs, the normal springs, and the bending moment springs of the same group are not installed on the same vertical or horizontal plane, but they need to be as close as possible.

In the embodiment of the invention, considering that the damage form of the explosion shock wave to the protected target in the real cabin is complex and various, in order to more accurately determine the explosion shock wave preventing effect of the baffle of the structure to be tested, three sets of test sensors are arranged, and the whole test system comprises: the device comprises a free field pressure sensor, a reflecting surface pressure sensor, an acceleration sensor and signal acquisition equipment, and is used for completely measuring the performance of the cabin protective structure for preventing shock waves and the dynamic evolution process of the shock waves in the cabin. The free field pressure sensor is arranged in the equivalent cabin through the supporting rod, the position of the free field pressure sensor is determined by the relative position of the protected target in the real cabin, the number of the free field pressure sensor is determined by the number of measuring position points required by the protected target in the real cabin, and the free field pressure sensor can be understood as follows: if the protected target is in the center position in the real cabin, the position of the free field pressure sensor is in the center position in the equivalent cabin, the free field pressure sensor can be identical to the protected target in the real cabin, and the pressure data of the explosion shock wave entering the equivalent cabin, which is measured by the free field pressure sensor, is equivalent to the pressure data of the explosion shock wave entering the real cabin and generated by the action of the explosion shock wave on the protected target. The number of the free field pressure sensors can be selected according to the requirement, and if the number of the free field pressure sensors is two, the number of the measurement positions required by the protected target is two. The free field pressure sensor may be selected from the PCB113a22 model sensor.

In the embodiment of the invention, after the explosion shock wave enters the equivalent cabin through the baffle with the structure to be tested, the explosion shock wave is reflected on the surface of the movable baffle, and the reflected wave and the incident wave have larger pressure amplitude after being superposed and can cause larger damage to a protected target, so that 5 reflecting surface pressure sensors are arranged on the movable baffle to test the pressure curve after reflection superposition.

In the embodiment of the present invention, the reflecting surface pressure sensors are 5 pressure sensors embedded in the movable baffle, and the sensing surfaces of the 5 pressure sensors are flush with the front end surface of the movable baffle and are respectively located at the central position and the peripheral symmetrical position of the front end surface of the movable baffle, referring to fig. 2, which shows a schematic position diagram of the 5 pressure sensors on the front end surface of the movable baffle according to the embodiment of the present invention. The 5 pressure sensors are fixed through holes prefabricated on the movable baffle plate and are specifically used for measuring pressure data after superposition of explosion shock waves entering the equivalent cabin and the explosion shock waves reflected by the movable baffle plate. The 5 pressure sensors may be selected from the PCB113B21 model sensors.

It should be noted that 5 pressure sensors can be fixed through holes prefabricated on the movable baffle, and a base can also be machined through holes on the movable baffle, which can better fix the pressure sensors. Referring to fig. 3, a model schematic diagram of the base and the base behind the fixed pressure sensor in the embodiment of the present invention is shown, and it should be noted that, in order to more intuitively show the base and the base behind the fixed pressure sensor, fig. 3 does not show the front end face of the movable baffle. The base is that the level runs through movable baffle, and the inside processing of the trompil of base has the internal thread, and the internal thread corresponds the external screw thread on pressure sensor's surface, just so can be so that pressure sensor through inside, the rotatory adjustment position of external screw thread, and then the response face of adjustment pressure sensor and the preceding terminal surface parallel and level of movable baffle and towards the wave front, and for further fastening pressure sensor, after the position of having adjusted pressure sensor, can also use the bolt to fix pressure sensor.

In the embodiment of the invention, the acceleration sensors are 5 acceleration sensors fixed on the back wave surface of the baffle of the structure to be detected, the 5 acceleration sensors are respectively positioned at the central position and the peripheral symmetrical position of the back wave surface of the baffle of the structure to be detected, and the 5 acceleration sensors are fixed through holes prefabricated by the baffle of the structure to be detected and are specifically used for measuring acceleration data of the baffle of the structure to be detected under the action of explosive shock waves, so that the speed change and the deformation process of the baffle of the structure to be detected can be obtained through formula calculation. It should be noted that the holes for fixing 5 acceleration sensors do not penetrate through the baffle of the structure to be measured, and the holes can be fixed by matching with the external threads of the acceleration sensors in a manner of processing internal threads by using a method similar to the above-mentioned base. Of course, 5 acceleration sensors may be optionally bonded to the structural baffle to be tested, but due to the insecurity of bonding, the structural baffle to be tested may fall off after being impacted by the explosive shock wave in the testing process.

In the embodiment of the invention, the free field pressure sensor, the reflecting surface pressure sensor and the acceleration sensor are all connected with the signal acquisition equipment through cables, and the data acquired by the free field pressure sensor, the reflecting surface pressure sensor and the acceleration sensor are sent to the signal acquisition equipment; the movable baffle and the back baffle are provided with openings, and the cable penetrates through the openings and is connected with the signal acquisition equipment.

In the embodiment of the invention, the equivalent cabin needs to adopt a sealing treatment technology to simulate the sealing structure of the real cabin, so that a first sealing treatment technology is adopted between the inner wall of the equivalent cabin and the movable baffle, and between the baffle of the structure to be tested and the four side baffles to ensure that the equivalent cabin is the sealing cabin so as to simulate the sealing structure of the real cabin; the holes prefabricated on the movable baffle plate, the holes of the movable baffle plate and the back baffle plate and the holes of the back baffle plate penetrated by the adjusting bolts all adopt a second sealing treatment technology to ensure that the equivalent cabin is a closed cabin so as to simulate the closed structure of a real cabin. The first sealing treatment technology is realized on the basis of aluminum alloy metal, the surface of the aluminum alloy metal is subjected to super-lubrication treatment, and vaseline is coated on the surface of the aluminum alloy metal, so that the super-lubrication sealing treatment technology can be realized at the joint between the inner wall of the equivalent cabin and the movable baffle and the joint between the baffle of the structure to be detected and the four side baffles. The second sealing treatment technology is realized based on the silica gel sealing ring, and the sealing treatment technology is realized by utilizing the deformation characteristic of the silica gel sealing ring under the high pressure of the explosion shock wave, so that a closed space is formed among the baffle plate of the structure to be detected, the side baffle plate and the movable baffle plate.

In the above process, in order to better determine the equivalent cabin from the real cabin, the inventor finally designs the equivalent cabin through a great amount of research, actual measurement and analysis. In general, the real cabin has a larger volume and higher experimental cost, so that the equivalent cabin is considered for testing. By adjusting the position of the movable baffle, the equivalent cabin can be a reduced model with the same proportion of each side length of the real cabin. For the structure baffle to be measured which is of great concern, the baffle can be obviously bent and deformed under the action of the explosive shock wave, so that the boundary supporting condition of the baffle needs to be specially designed.

Referring to fig. 4, which shows a schematic diagram of an actual chamber and an equivalent chamber according to an embodiment of the present invention, when a portion is selected from a large-sized bent plate structure for analysis according to the basic analysis principle of solid mechanical deformation, the boundary section of the selected portion includes three functions: axial force F_NShear force F_TAnd a bending moment M. In order to more accurately restore the deformation state of the baffle of the structure to be detected corresponding to the real cabin condition, in the design of the equivalent cabin system, a plurality of groups of rigidity adjusting devices need to be arranged at the boundary section of the baffle of the structure to be detected, wherein each group of rigidity adjusting devices comprises three rigidity adjusters which respectively provide the three functions (namely constraint force) for the baffle of the structure to be detected, and therefore each group of rigidity adjusting devices comprises two axial rigidity adjusters and one bending moment rigidity adjuster.

The specific stiffness value of the adjusting device can be obtained based on theoretical analysis or calculation simulation. The four sides of the rectangular baffle plate of the structure to be measured at least need one set of rigidity adjusting device, and the specific needed number can be selected according to actual experiments. In addition, the sealing treatment technology can ensure that the equivalent cabin forms a closed test space, so that the explosion shock waves are prevented from entering the equivalent cabin through diffraction to influence an experimental result, and by the mode, a large-size closed environment of the real cabin can be simulated based on the small-size equivalent cabin test space.

Based on the test device for detecting the explosion impact resistance of the cabin protection structure, the embodiment of the invention also provides a method for detecting the effectiveness of the test device for detecting the explosion impact resistance of the cabin protection structure, which comprises the following steps:

step 2: based on a theoretical method or a numerical simulation method, obtaining values of two axial rigidities and one bending rigidity of the boundary section of the baffle of the structure to be detected under the equivalent cabin internal space structure size, and adjusting two axial rigidity regulators and a rotary rigidity regulator according to the values to provide proper supporting conditions for the baffle of the structure to be detected;

and step 3: arranging and installing a free field pressure sensor, a reflecting surface pressure sensor and an acceleration sensor according to the test requirements, and completing debugging of signal acquisition equipment;

and 4, step 4: sealing holes prefabricated on the movable baffle and openings of the movable baffle and the back baffle between the inner wall of the equivalent cabin and the movable baffle and between the baffle of the structure to be tested and the four side baffles respectively by adopting a sealing treatment technology to form a closed equivalent cabin, and finally forming an integral testing device;

and 5: fixing the integral testing device on a base at the tail end of a shock tube testing platform through a connecting device, and enabling a wave-facing surface to face the direction of the explosive shock waves so as to enable the explosive shock waves to vertically act on the wave-facing surface;

step 6: according to the load requirement of explosion shock waves, selecting a proper membrane to carry out a shock tube experiment, wherein shock waves formed by high-pressure gas in the shock tube act on the baffle of the structure to be tested to generate acceleration, and formed acceleration data are sensed by an acceleration sensor and transmitted to signal acquisition equipment through a cable; the explosion shock wave enters the equivalent cabin after passing through the baffle of the structure to be detected, the transmission pressure generated by compressing the air in the equivalent cabin reaches the surfaces of the free field pressure sensor and the reflecting surface pressure sensor, and the formed pressure data is sensed by the free field pressure sensor and the reflecting surface pressure sensor and is transmitted to the signal acquisition equipment through the cable;

and 7: based on the obtained acceleration data and pressure data, deformation information of the baffle of the structure to be detected, pressure information at a specific position in the equivalent cabin and pressure information after reflection and superposition of the inner wall of the equivalent cabin are obtained, damage conditions of the protected target under corresponding conditions are evaluated by combining damage indexes of the protected target, and the explosion-proof shock wave performance of the cabin protection structure is determined by combining the test results of the experiment and the damage conditions of the protected target.

Among the above-mentioned shock tube experiment platform, the principle that produces the shock wave is for setting up a driving pressure to broken aluminium system diaphragm, makes high-pressure gas form the shock wave in the shock tube, and this shock wave can directly be used to whole testing arrangement's the wave front that faces, and its each item parameter can have set up according to existing data, and wherein can set up the driving pressure and be 5MPa, and this parameter can be adjusted according to the experiment requirement by oneself.

In addition, the method for detecting the effectiveness of the test device for the explosion impact resistance of the cabin protection structure can be completed by using a field explosive explosion test, and the method has the same effect.

Referring to fig. 5, a graph of pressure data in a closed testing chamber tested by using a shock tube experimental platform in the embodiment of the present invention is shown, in which a horizontal axis in fig. 5 represents time in milliseconds (ms), and a vertical axis represents pressure data after an explosion shock wave passes through a baffle of a structure to be tested and is reflected and superimposed by an inner wall of an equivalent cabin, and the unit is megapascals (MPa).

In the embodiment of the invention, after the pressure sensors and the acceleration sensors measure the pressure information and the acceleration information, the damage condition of the protected target in the equivalent cabin can be evaluated through the pressure index and the impulse index acting on the protected target and the displacement index of the cabin protection structure under the action of the explosion shock wave.

The explosion shock wave can be reflected when acting on the surface of the protected target, the superposition of the reflected wave and the incident wave can cause the rapid lifting of the shock wave pressure in the air at the front end of the protected target, and the shock wave pressure acting on the protected target is far greater than the shock wave pressure in the air. The relationship between the total pressure peak value after the reflected wave and the incident wave are superposed and the pressure peak value of the incident wave can be expressed as follows:

wherein: p_atmAt atmospheric pressureStrong, P₀Is the peak pressure, P, of the incident wave_sThe pressure peak value after the reflection wave and the reflection of the incident wave are superposed, namely the pressure peak value acting on the protected target. The formula (1) can obtain that the total pressure peak value after the reflection of the solid surface is 2-8 times of the pressure peak value of the incident wave, and the larger the peak value of the incident wave is, the larger the amplification factor is. The pressure peak value can be used as an evaluation index of human body or equipment safety.

Based on the previous research results, the pressure peak index P of the shock wave_sThe biomechanical injury index which can be used for evaluating the craniocerebral injury degree is as follows: when P is present_s>The head of the human body is marked to have severe craniocerebral injury when the pressure is 235 kPa; when 173kPa<P_s<235kPa, which represents that the head of the human body has mild craniocerebral injury; when P is present_s<173kPa, which indicates that the head of the human body does not have craniocerebral injury.

The explosion shock wave impulse is the cumulative effect of shock wave pressure on time, is an important factor causing human body injury, and has a coupling effect with the shock wave pressure peak value. The impact wave pressure peak value-impulse biological damage index provided by the embodiment of the invention can be used for evaluating the lung damage degree of a human body under the action of impact waves, wherein the damage index can be subdivided into an impact wave positive pressure peak value-positive pressure impulse index and a negative pressure peak value-negative pressure impulse index. Compared with the positive pressure peak value-positive pressure impulse, the absolute value of the negative pressure peak value-negative pressure impulse is relatively small, but the negative pressure peak value-negative pressure impulse causes the lung tissue to be in a stretching state, so that the alveolar tissue is more easily torn and damaged; meanwhile, the liquid in the lung tissue is in a negative pressure state, so that a cavity effect is easily generated to form local high pressure, and the pulmonary alveolus is perforated. Therefore, the proposal and establishment of the damage evaluation index of the negative pressure peak value-negative pressure impulse have important research and application values.

For the positive pressure peak value-positive pressure impulse damage index, the positive pressure peak value is the positive pressure peak value in the free field, and the positive pressure impulse value I₊The specific expression of (A) is as follows:

wherein p (t) is pressure data measured by the pressure sensor, t₁Initial beam time, t, of the action of shock wave pressure₊The positive pressure duration in the first fluctuation cycle of the shock wave pressure.

For the negative pressure peak value-negative pressure impulse damage index, the negative pressure peak value is the negative pressure peak value in the free field, and the specific expression of the negative pressure impulse is as follows:

wherein, t_-The duration of the negative pressure in the first fluctuation cycle of the shock wave pressure. Based on acceleration information A (t) acquired by an acceleration sensor arranged on the cabin protective structure, speed information V (t) and displacement information D (t) of the cabin protective structure under the action of explosion shock waves can be obtained, and the specific expression is as follows:

wherein: t is t₁、t₂The start and end times of the action of the shock wave pressure.

By combining with the damage threshold of the protected target, the safety conditions of key equipment and personnel in the cabin can be evaluated through the pressure index, the impulse index and the displacement index.

In addition, the equivalent cabin system in the embodiment of the invention is equivalent to the real cabin through the size adjustment in one direction (namely, the size adjustment is carried out through moving the baffle), and it can be understood that the construction of the equivalent cabin system can also realize the equivalent in a wider range through the size adjustment in two directions. For real cabins with more complex geometries or irregular shapes, the construction principle of equivalent cabin systems is applicable. And reconstructing the real cabin structures with different shapes according to different scaling ratios to prepare corresponding equivalent cabin systems.

The reflecting surface pressure sensor in the embodiment of the invention is arranged on the movable baffle, and it can be understood that the reflecting surface pressure sensor can also be arranged on other baffles of an equivalent cabin structure in the same way according to the specific position of a protected object in a real cabin so as to measure the reflecting pressure at the baffle where the reflecting surface pressure sensor is arranged. By the mode, the universality of the testing device in the embodiment of the invention can be greatly expanded, so that the testing device has a wider application range.

Through the embodiment, the performance testing device disclosed by the invention replaces a large-size real cabin with an equivalent cabin system which is reduced in the same proportion, and tests the explosion-proof shock wave performance of the cabin protection structure; the real cabins in different forms are effectively scaled in the same proportion by the unit splicing technology of the baffle structure of the equivalent cabin system and the position of the movable baffle is adjusted, the real cabins can be reconstructed in series by adopting different scaling ratios, and the influence rule of the size effect of the equivalent cabin on the test result is researched; determining the boundary supporting condition of a baffle plate of a structure to be detected in an equivalent cabin system based on the constraint action information of an adjacent cabin and an auxiliary structure when the real cabin protection structure deforms under the action of the explosion shock wave, establishing a supporting system of the protection structure, and truly reflecting the constraint state and the dynamic evolution process of the cabin protection structure under the action of the explosion shock wave; the equivalent cabin forms a closed test chamber by using a sealing technology, so that the explosion shock wave can be effectively prevented from being diffracted to enter the cabin to influence the measurement result; deformation information of the baffle of the structure to be detected under the explosion shock wave and evolution information of the shock wave pressure in the cabin can be obtained through the acceleration sensors and the pressure sensors, wherein the evolution information comprises pressure information of any space position in the cabin and pressure information reflected on the inner wall of the cabin; and the damage of the protected target can be evaluated by combining with the damage threshold of the protected target, so that the comprehensive protection performance of the cabin protection structure for preventing the explosion shock wave is further determined. The performance testing device provided by the invention is used as an effective testing means for the explosion-proof shock wave performance of the cabin protection structure, can also be used for researching the scale law effect of the explosion-proof shock wave performance of the cabin structure, and has important value and extremely high practicability.

In addition, the inventor also designs another simpler and more convenient simple test device for the explosion-proof shock wave performance of the cabin protection structure and a method for detecting the effectiveness of the simple test device based on the existing shock tube experiment platform, and certainly, because the method is simpler and only uses a small number of pressure sensors, the obtained data may have a larger difference with the data under the real cabin condition, but the test device can still effectively test the explosion-proof shock wave performance of the cabin protection structure.

Referring to fig. 6, a schematic diagram of a simple testing device for the explosion shock wave resistance of a cabin protection structure according to an embodiment of the present invention is shown, the device includes: a steel sheet, wherein the steel sheet comprises: the front baffle plate 10, the rear baffle plate 20 and four small steel plates 30; the device comprises, in addition to the steel plate: reinforcing plate 40, pressure sensor 50, and set screw 60.

Specifically, four small steel plates 30 are perpendicular to the cross section of the front baffle 10 to form a cubic test chamber, the cross section is a wave-facing surface of the device, the pressure sensor 50 is fixed on the front baffle 10 through a base, the sensing surface of the pressure sensor 50 is flush with the surface of the cross section of the front baffle 10, and the base is located in the cubic test chamber; in the embodiment of the present invention, in order to induce the explosion shock wave to enter the sealed test chamber in an omnibearing manner (the sealed test chamber is explained in the corresponding places below), the explosion shock wave compresses the air in the sealed test chamber to generate the transmission pressure, 5 pressure sensors are used, one of the 5 pressure sensors is located at the center position of the sealed test chamber, and the other 4 pressure sensors can be distributed around the center position and have the same relative position, as shown in fig. 7, 1#, 2#, 3#, 4#, and 5# in fig. 7 respectively represent 5 pressure sensors, wherein 1# is located at the center position of the sealed test chamber, and 2#, 3#, 4#, and 5# are distributed around the center position and have the same relative position, so as to verify the test result repeatability of the whole test device.

The material of the cabin protection structure is fixed on the cross section of the front baffle 10 through the reinforcing plate 40 and the fixing screw 60, so that the cubic test chamber becomes a closed test chamber which is used for preventing the explosion shock wave from being diffracted and reaching the sensing surface of the pressure sensor 50 to influence the pressure data sensed by the pressure sensor 50. Because the material of the cabin protection structure can be bent and deformed under the action of the explosion shock wave, in order to form the closed test chamber, the material of the cabin protection structure is tightly attached to the front baffle plate 10 by using the reinforcing plate 40 and the fixing screw rod 60, wherein the reinforcing plate 40 is made of hollow steel, and the area of the hollow part is larger than the cross-sectional area of the closed test chamber. Of course, it can be understood that the high molecular polymer material, the reinforcing plate 40 and the front baffle 10 are provided with corresponding holes corresponding to the positions through which the fixing screws 60 pass, so that the fixing screws 60 can pass through, and then bolts are required for fastening.

Referring to fig. 8, a front view of a simple testing device for the explosion shock wave resistance of the cabin protection structure according to the embodiment of the present invention is shown, and in fig. 8, the hole of the front baffle 10 is not shown for simplicity of illustration.

The rear baffle 20 is fixed with the front baffle 10 through a fixing screw 60, the rear baffle 20 is used for blocking reflected waves of explosion shock waves so as to eliminate the influence of the reflected waves on pressure data sensed by the pressure sensor 50, and it can be understood that holes are also formed in the position, corresponding to the fixing screw 60, of the rear baffle 20, and bolts are also required to be used for screwing and fixing; the pressure sensor 50 is used to sense pressure data of a transmission pressure generated when the explosion shock wave compresses air of the sealed test chamber when the explosion shock wave enters the sealed test chamber.

The base is formed by trompil processing on preceding baffle 10 to the trompil level of this base runs through whole preceding baffle 10, and the inside processing of trompil of base has the internal thread, and the internal thread corresponds the external screw thread on pressure sensor 50's surface, so that pressure sensor 50 is through inside and outside screw thread rotation adjusting position, and then adjusts pressure sensor 50's the response face and the surperficial parallel and level of the cross section of preceding baffle 10.

The base is provided with: and bolts, in the case that the sensing surface of the pressure sensor 50 is flush with the surface of the cross section of the front baffle 10, by tightening the bolts to fix the position of the pressure sensor 50, the pressure sensor 50 is connected with the pressure signal collecting device through the signal collecting line. Referring to fig. 3, the left side of fig. 3 is a schematic view showing an internal model of the base, and in conjunction with fig. 6, the base can be understood as being directly formed on the front baffle 10 and internally provided with internal threads, and the right side of fig. 3 is a schematic view showing a model of the base after the pressure sensor 50 is fixed, and the pressure sensor 50 is rotated to a position where its sensing surface is flush with the surface of the base, that is, the sensing surface of the pressure sensor 50 is flush with the surface of the cross section of the front baffle 10 by using its external threads and internal threads inside the base, and then is fixed and screwed by bolts.

The 5 pressure sensors of the embodiment of the invention all use PBC113B21 type pressure sensors, the 5 PBC113B21 type pressure sensors are in one-to-one correspondence with the bases, that is, 5 bases are also arranged on the front baffle 10, and the 5 PBC113B21 type pressure sensors are respectively fixed on the front baffle 10 through the 5 bases.

The connecting cable of each of the 5 PBC113B21 type pressure sensors passes through the tailgate 20 and is connected to the signal acquisition device, and naturally, the tailgate 20 also needs to be provided with holes through which the cable can pass.

The fixing screw 60 is also used for fixing the simple test device for the explosion-proof shock wave performance of the cabin protection structure on the support frame so as to complete the related test.

The material thickness of cabin protective structure can be confirmed by the test needs by oneself, and under general condition, just can be together fixed with testing arrangement with cabin protective structure's material through the bolt, certainly, when cabin protective structure's material is fixed with testing arrangement, need use a reinforcing plate 40, guarantee the airtight of test chamber. In addition, if needed, a rubber gasket can be used for keeping the test chamber closed, so that a better effect is achieved.

The embodiment of the invention also provides a method for detecting the effectiveness of the simple test device for the explosion-proof shock wave performance of the cabin protection structure, wherein the test device is the simple test device for the explosion-proof shock wave performance of the cabin protection structure, and the method comprises the following steps:

step 1: fixing the material of the cabin protection structure on the cross section of the front baffle 10 to form an integral testing device;

step 2: fixing the integral testing device at the tail end of a test section of a shock tube experiment platform;

and step 3: the front surface of the wave-facing surface of the integral testing device faces the direction of the shock wave, so that the shock wave vertically acts on the wave-facing surface;

and 4, step 4: the high-pressure gas enters the closed test chamber after shock waves formed in the shock tube pass through the material of the cabin protection structure, transmission pressure generated by compressing air in the closed test chamber reaches the surface of the pressure sensor 50, pressure data formed by the transmission pressure reaches the surface of the pressure sensor 50, the pressure data is sensed by the pressure sensor 50 and is transmitted to the pressure signal acquisition equipment through the cable, and then a protection performance result of the material of the cabin protection structure is obtained.

In addition, the method for detecting the effectiveness of the simple test device for the explosion-proof shock wave performance of the cabin protection structure can be completed by using a field explosive explosion test, and has the same effect.

In conclusion, the performance testing device disclosed by the invention can prevent the explosion shock wave from being diffracted through the closed testing chamber and reaching the sensing surface of the pressure sensor; the rear baffle blocks the reflected wave of the explosion shock wave, and the influence of diffraction or reflected wave on the pressure sensor sensing pressure data is reduced; when the plurality of pressure sensors are used for sensing the explosion shock waves in an all-around manner and entering the closed test chamber, the explosion shock waves compress air in the closed test chamber to generate transmission pressure, so that the pressure amplitude data entering the closed test chamber after the material protection of the chamber protection structure is accurately tested.

It is further noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, or article that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, or article.

The embodiments of the present invention have been described in connection with the accompanying drawings, and the principles and embodiments of the present invention are described herein using specific examples, which are provided only to help understand the method and the core idea of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.

Claims

1. A test device for detecting explosion impact resistance of a cabin protection structure, the device comprising: the test device can evaluate the performance of explosion-proof shock waves of a real cabin structure;

the free field pressure sensor is arranged in the equivalent cabin through a support rod, the position of the free field pressure sensor is determined by the relative position of the protected target in the real cabin, the number of the free field pressure sensor is determined by the number of measuring position points required by the protected target in the real cabin, and the free field pressure sensor is used for measuring pressure data generated by the action of explosion shock waves entering the equivalent cabin on the protected target;

the reflecting surface pressure sensors are 5 pressure sensors embedded on the movable baffle, the sensing surfaces of the 5 pressure sensors are flush with the front end surface of the movable baffle and are respectively positioned at the central position and the peripheral symmetrical position of the front end surface of the movable baffle, and the 5 pressure sensors are fixed through holes prefabricated on the movable baffle and are used for measuring pressure data after superposition of explosion shock waves entering the equivalent cabin and the explosion shock waves reflected by the movable baffle;

the acceleration sensor is for being fixed in 5 acceleration sensor on the structure baffle back wave surface that awaits measuring, and these 5 acceleration sensor are located respectively the central point of structure baffle back wave surface that awaits measuring puts and symmetrical position all around, and these 5 acceleration sensor pass through the prefabricated hole of structure baffle that awaits measuring is fixed for measure under the blast shock wave effect, the acceleration data of structure baffle that awaits measuring.

2. The device according to claim 1, wherein the baffle structures are assembled by adopting a unitized splicing process, each baffle for splicing has multiple specifications and is provided with a connecting end so as to splice cross-sectional dimensions of any proportion according to the scaling of the equivalent cabin;

3. The device of claim 1, wherein one end of the adjusting screw is fixed to the moving baffle, and the other end passes through the back baffle;

4. The apparatus of claim 1, wherein the baffle structure further comprises: the four front baffles are respectively fixed at preset positions in front of the inner walls of the four side baffles and are used for fixedly connecting the plurality of groups of rigidity adjusting devices;

5. The device of claim 4, wherein the two axial stiffness adjusters and the one rotational stiffness adjuster are both springs;

6. The apparatus of claim 1, wherein the test system further comprises: a signal acquisition device;

7. The device according to claim 6, characterized in that a first sealing treatment technology is adopted between the inner wall of the equivalent cabin and the movable baffle, and between the baffle of the structure to be tested and the four side baffles, so as to ensure that the equivalent cabin is a closed cabin to simulate the closed structure of a real cabin;

8. The device according to claim 1, wherein a connecting device is arranged on the rear end face of the back baffle, and the testing device is fixed on a base at the tail end of the shock tube testing platform through the connecting device so as to test the explosion impact resistance of the cabin protection structure.

9. A method for testing the effectiveness of a test device for testing the explosion impact resistance of a cabin protective structure, wherein the test device is a test device for testing the explosion impact resistance of a cabin protective structure according to any one of claims 1 to 8, the method comprising: