Overhanging missile hyperstatic multi-point support combined static test system

Abstract

The application provides a statically indeterminate multi-point support combined static test system for a multi-hanging missile, which comprises a bearing support module, a tooling module, a static loading module, a test module and a plurality of slider loading tools; the bearing support module comprises a bearing structure and a support structure; the hanging missile comprises a missile body and a plurality of sliders, the plurality of sliders are installed on the missile body and are distributed along the length direction of the missile body; the number of the sliders corresponds to the number of the slider loading tools one by one, and the tooling module is connected with the missile body; the static loading module can provide a force for the missile body through the tooling module; and the test module is used for testing the stress condition of the missile body. The test system scheme of the application is simple and convenient to operate, can safely and reliably perform static test verification on the statically indeterminate multi-point support of the multi-hanging missile, has low test cost, fully meets the requirements of the static test of the multi-hanging missile, and can more truly simulate the real stress state of the missile hanging under the air hanging condition of the missile.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of missile structure static test, in particular to a multi-hanging missile hyperstatic multi-point support combined static test system. BACKGROUND

[0002] The hanging is an important component of the missile structure, and as one of the important mechanical interfaces between the missile and the launching frame, it should not only meet the specified interface size in design, but also have high strength, so as to fully guarantee the safety of the launching device and the missile weapon system. During the missile hanging flight transportation, all kinds of loads on the missile body are borne by the hanging, so the mechanical environment used by the hanging is more severe than that of other parts of the missile structure. According to the past experience of model development and the situation exposed by the previous failures, the hanging is one of the main positions of the missile structure damage. Therefore, the strength design of the missile hanging is one of the important contents of the overall design of the missile structure, and the hanging static test is one of the important links of the strength design.

[0003] In order to improve the damage safety of the missile hanging structure, the hyperstatic support form is generally adopted in the design of the missile hanging, and the commonly used support points are 4 points or 6 points. The hyperstatic structure is a geometrically invariant system with redundant constraints, the internal force and deformation distribution is relatively uniform, and the structure itself has strong protection ability, and after some redundant constraints are damaged, the structure can still maintain the geometric invariance. Therefore, the hyperstatic structure is very common in common engineering structures, such as continuous steel structure bridge and frame structure house. However, the hyperstatic design causes certain complexity in the verification of the structure test, and the connection stiffness of the test tooling and the hanging needs to be considered to ensure that the loads at each support point of the hanging structure are properly and evenly distributed during the static test, resulting in greater difficulty in the design of the static test system. In order to reduce the test difficulty and simplify the test method, the current static test of the multi-hanging missile is to respectively conduct static test on a single hanging, which cannot truly simulate the load distribution on the multi-hanging, resulting in a large difference between the boundary conditions of the ground test and the real hanging flight transportation boundary conditions. Therefore, a special multi-hanging missile hyperstatic multi-point support combined static test system needs to be designed to solve the above problems.

[0004] The patent document CN 207703504 U discloses an airplane static test engine loading simulation piece, which comprises a static test frame, the left and right ends of the static test frame are respectively provided with a fixed flange, the outer side of the fixed flange is provided with a fixed seat, the left part of the upper end of the static test frame is provided with a longitudinal support, the right side of the longitudinal support is provided with a longitudinal main shaft seat, and the upper end of the longitudinal main shaft seat is provided with a longitudinal main shaft. However, it is suitable for the static test of the airplane, and is not suitable for the hyperstatic test of the multi-hanging missile. SUMMARY

[0005] Aiming at the defects in the prior art, the present application aims to provide a statically indeterminate multi-point support combined static test system for a multi-hanging missile.

[0006] According to the present application, a statically indeterminate multi-point support combined static test system for a multi-hanging missile is provided, comprising a bearing support module, a tooling module, a static load module, a test module and a plurality of slider load toolings.

[0007] The bearing support module comprises a bearing structure and a support structure; the bearing structure is used for bearing the hanging missile, and the support structure is used for providing support points for the tooling module.

[0008] The hanging missile is installed on the bearing structure through the slider load tooling.

[0009] The hanging missile comprises a missile body and a plurality of sliders, the plurality of sliders are installed on the missile body and are distributed along the length direction of the missile body; the number of the sliders corresponds to the number of the slider load toolings one by one, and the sliders and the slider load toolings cooperate with each other.

[0010] The tooling module is connected with the missile body.

[0011] The static load module can provide an acting force for the missile body through the tooling module.

[0012] The test module is used for testing the stress condition of the missile body.

[0013] Preferably, the number of the sliders and the slider load toolings is both 2.

[0014] The bearing structure comprises third and fourth struts; the third and fourth struts are arranged in the length direction of the hanging missile at the bottom of the hanging missile.

[0015] Preferably, the two sliders comprise a front slider and a rear slider; the two slider load toolings comprise a front slider load tooling and a rear slider load tooling.

[0016] The front slider load tooling is installed at the top of the fourth strut, and the rear slider load tooling is installed at the top of the third strut.

[0017] Preferably, the tooling module comprises an axial force load tooling and a transverse force load tooling.

[0018] One end of the axial force load tooling is connected with one end of the missile body close to the fourth strut; the axial force load tooling is installed at the center of mass of the missile body.

[0019] The axial force load tooling and the transverse force load tooling are connected with the static load module.

[0020] Preferably, the static loading module comprises a loading control device, an axial force applying assembly and a lateral force applying assembly;

[0021] The axial force loading tool is connected with the loading control device through the axial force applying assembly;

[0022] The lateral force loading tool is connected with the loading control device through the lateral force applying assembly.

[0023] Preferably, the support structure comprises a first column and a second column;

[0024] The first column is provided with a first mounting position, and the second column is provided with a second mounting position; the first mounting position is used for connecting with the axial force loading tool, and the second mounting position is used for connecting with the lateral force loading tool.

[0025] Preferably, the axial force applying assembly comprises an axial force sensor, an axial force actuator cylinder, an axial force hydraulic loading pipeline and an axial force sensor lead wire;

[0026] The axial force actuator cylinder is installed on the axial force loading tool, and the axial force actuator cylinder is connected with the loading control device through the axial force hydraulic loading pipeline; the axial force actuator cylinder can apply axial force to the projectile under the action of the loading control device;

[0027] The axial force sensor is installed on the axial force loading tool and used for measuring the axial force received by the projectile; the axial force sensor is electrically connected with the loading control device through the axial force sensor lead wire.

[0028] Preferably, the lateral force applying assembly comprises a lateral force sensor, a lateral force actuator cylinder, a lateral force hydraulic loading pipeline and a lateral force sensor lead wire;

[0029] The lateral force actuator cylinder is installed on the lateral force loading tool; the lateral force actuator cylinder is connected with the loading control device through the lateral force hydraulic loading pipeline; the lateral force actuator cylinder can apply lateral force to the projectile through the lateral force loading tool under the action of the loading control device;

[0030] The lateral force sensor is installed on the lateral force loading tool and used for measuring the lateral force received by the projectile; the lateral force sensor is electrically connected with the loading control device through the lateral force sensor lead wire.

[0031] Preferably, the front sliding block and the rear sliding block each have two support points, and the four support points form a statically indeterminate structure.

[0032] Preferably, the test module comprises a strain displacement test device, a first displacement meter, a second displacement meter, a first strain gauge and a second strain gauge;

[0033] The first displacement meter, the second displacement meter, the first strain gauge and the second strain gauge are connected with the variable displacement testing device through wires,

[0034] The testing module is used for measuring the elastic deformation of the projectile and the stress of the support points of the front and rear sliders.

[0035] Compared with the prior art, the present application has the following beneficial effects:

[0036] 1. The test system of the present application is simple in scheme, convenient to operate, and can safely and reliably verify the statically indeterminate multi-point support of the multi-hung missile.

[0037] 2. The test system of the present application is low in cost, fully meets the requirements of the static test of the multi-hung missile, and can more realistically simulate the actual stress state of the missile hanging under the condition of the missile flying in the air.

[0038] 3. The present application has important engineering value for the ground design verification of the static test of the missile hanging. DETAILED DESCRIPTION

[0039] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments with reference to the following drawings:

[0040] Figure 1 Fig. 1 is a schematic diagram of the composition structure of the multi-hung missile statically indeterminate multi-point support combined static test system of the present application;

[0041] Figure 2 Fig. 2 is a schematic diagram of the detailed structure of the multi-hung missile statically indeterminate multi-point support combined static test system of the present application;

[0042] Figure 3 Fig. 3 is a schematic diagram of the cooperation of the front and rear sliders and the front and rear slider loading tool of the present application;

[0043] Figure 4 Fig. 4 is a schematic diagram of the front and rear slider of the present application;

[0044] Figure 5 Fig. 5 is a schematic diagram of the cooperation of the front and rear sliders and the front and rear slider loading tool of the present application when the rear baffle is embodied;

[0045] Figure 6 Fig. 6 is a schematic diagram of the axial force loading tool structure of the present application.

[0046] In the drawings:

[0047] DETAILED DESCRIPTION

[0048] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0049] This invention provides a multi-suspension missile hyperstatic multi-point support combined static test system, such as... Figures 1-6 As shown, it includes a load-bearing support module 100, a tooling module 500, a static loading module 300, a testing module 400, and multiple slider loading tooling.

[0050] The load-bearing support module 100 includes a load-bearing structure and a support structure; the load-bearing structure is used to support the suspended missile 200, and the support structure is used to provide support points for the tooling module 500.

[0051] The suspended missile 200 is mounted on the supporting structure via the slider loading fixture; the suspended missile 200 includes a missile body 9 and multiple sliders, all of which are mounted on the missile body 9 and distributed along the length of the missile body 9; the number of sliders corresponds one-to-one with the number of slider loading fixtures, and the sliders and slider loading fixtures cooperate with each other; it is worth noting that the sliders mentioned in this article are the suspension in the suspended missile 200.

[0052] The tooling module 500 is connected to the projectile 9; the static loading module 300 can provide force to the projectile 9 through the tooling module 500; the test module 400 is used to test the force on the projectile 9.

[0053] like Figures 1-6 As shown, in a preferred embodiment, there are two sliders and two slider loading fixtures. The two sliders include a front slider 10 and a rear slider 11; the two slider loading fixtures include a front slider loading fixture 5 and a rear slider loading fixture 6. The front slider 10 and the front slider loading fixture 5 cooperate with each other, and the rear slider 11 and the rear slider loading fixture 6 cooperate with each other. Specifically, as shown... Figures 3-5 As shown, the front slider 10 and the rear slider 11 each have two support points, and the four support points form a statically indeterminate structure.

[0054] The support structure comprises a first column 1 and a second column 2; the first column 1 is provided with a first mounting position 32, and the second column 2 is provided with a second mounting position 33; the bearing structure comprises a third column 3 and a fourth column 4; the third column 3 and the fourth column 4 are arranged in the length direction of the hanging missile 200 at the bottom of the hanging missile 200; specifically, the front sliding block loading tool 5 is installed at the top of the fourth column 4, and the rear sliding block loading tool 6 is installed at the top of the third column 3. In a preferred example, the first column 1, the second column 2, the third column 3 and the fourth column 4 are installed on the ground of the static test chamber through foundation bolts.

[0055] The missile body 9 is installed on the front sliding block loading tool 5 and the rear sliding block loading tool 6 through the front sliding block 10 and the rear sliding block 11; this design can simultaneously load the front hanging and the rear hanging (i.e. the front sliding block 10 and the rear sliding block 11), which is the same as the load on the third column 3 and the fourth column 4, simulating the scenario of the missile body 9 in the actual launch cylinder.

[0056] As shown in the drawings, Figure 4 In a preferred example, the rear end of the rear sliding block loading tool 6 is further provided with a rear baffle 30, and the rear sliding block 11 of the missile body 9 is further provided with a check ring, which is in abutment with the baffle 30, for limiting the axial movement of the missile body to the rear, so as to perform axial loading.

[0057] The tool module 500 comprises an axial force loading tool 7 and a transverse force loading tool 8; one end of the axial force loading tool 7 is connected to the end of the missile body 9 close to the fourth column 4, and the other end of the axial force loading tool 7 is connected to the first mounting position 32; the axial force loading tool 7 is installed at the center of mass of the missile body 9, ensuring that the transverse load is loaded to the center of mass of the missile body; the axial force loading tool 7 and the transverse force loading tool 8 are connected to the static loading module 300. Specifically, the front end of the missile body 9 is fixedly connected to the axial force loading tool 7, and the center of mass of the missile body 9 is connected to the transverse force loading tool 8. In a preferred example, as shown in the drawings, Figure 6 The axial force loading tool 7 is provided with a ball head top rod 31 to facilitate axial loading.

[0058] The static loading module 300 comprises a loading control device 12, an axial force applying assembly and a transverse force applying assembly; the axial force loading tool 7 is connected to the loading control device 12 through the axial force applying assembly; the transverse force loading tool 8 is connected to the loading control device 12 through the transverse force applying assembly. The first mounting position 32 is used to connect the axial force loading tool 7, and the second mounting position 33 is used to connect the transverse force loading tool 8.

[0059] The axial force applying assembly comprises an axial force sensor 13, an axial force actuator 15, an axial force hydraulic loading pipeline 17, and an axial force sensor wire 19; the axial force actuator 15 is installed on the axial force loading tool 7, and the axial force actuator 15 is connected with the loading control device 12 through the axial force hydraulic loading pipeline 17; the axial force actuator 15 can apply an axial force to the elastic body 9 under the action of the loading control device 12; the axial force sensor 13 is installed on the axial force loading tool 7, and is used for measuring the axial force applied to the elastic body 9, so that the loading control device 12 controls the loading of the axial force actuator 15; the axial force sensor 13 is electrically connected with the loading control device 12 through the axial force sensor wire 19.

[0060] The lateral force applying assembly comprises a lateral force sensor 14, a lateral force actuator 16, a lateral force hydraulic loading pipeline 18, and a lateral force sensor wire 20; the lateral force actuator 16 is installed on the lateral force loading tool 8; the lateral force actuator 16 is connected with the loading control device 12 through the lateral force hydraulic loading pipeline 18; the lateral force actuator 16 can apply a lateral force to the elastic body 9 through the lateral force loading tool 8 under the action of the loading control device 12; the lateral force sensor 14 is installed on the lateral force loading tool 8, and is used for measuring the lateral force applied to the elastic body 9, so that the loading control device 12 controls the loading of the lateral force actuator 16; the lateral force sensor 14 is electrically connected with the loading control device 12 through the lateral force sensor wire 20.

[0061] The test module 400 comprises a strain displacement test device 21, a first displacement meter 22, a second displacement meter 23, a first strain gauge 24, and a second strain gauge 25; the first displacement meter 22, the second displacement meter 23, the first strain gauge 24, and the second strain gauge 25 are connected with the strain displacement test device 21 through wires; the test module 400 is used for measuring the displacement of the elastic body 9 and the stress of the front and rear slider support points. Specifically, the first displacement meter 22, the second displacement meter 23, the first strain gauge 24, and the second strain gauge 25 are connected with the strain displacement test device 21 through a first test data line 26, a second test data line 27, a third test data line 28, and a fourth test data line 29, respectively; more specifically, the first displacement meter 22 and the second displacement meter 23 are arranged at different positions of the elastic body 9; the first strain gauge 24 is arranged on the front slider 10, and the second strain gauge 25 is arranged on the rear slider 11; the first displacement meter 22 and the second displacement meter 23 are used for measuring the elastic deformation of the elastic body 9; and the first strain gauge 24 and the second strain gauge 25 are used for measuring the stress of the front and rear slider support points.

[0062] The application utilizes the static loading module 300 to exert axial static force and transverse static force on the projectile body 9, and utilizes the test module 400 to record the deformation of the projectile body 9 and the stress of the support points of the front and rear sliding blocks, so that the statically indeterminate multi-point support of the multi-hung missile can be reliably verified by static test, and in addition to the test of the missile with only front and rear sliding blocks, i.e. two hangers, the test record and verification of the multi-hung missile can also be carried out by increasing the number of sliding block loading tools. It is worth noting that during the test, the static loading module 300 only exerts static force on the projectile body 9, and the position of the projectile body does not produce macro displacement, and the design of the sliding block on the projectile body 9 is for the design of the launch after the projectile body 9 is really installed in the missile launch cylinder.

[0063] The multi-hung missile statically indeterminate multi-point support combined static test system provided by the application has the advantages of simple scheme, convenient operation, safe and reliable static test verification of the statically indeterminate multi-point support of the multi-hung missile, low test cost, full satisfaction of the requirements of the static test of the multi-hung missile, real simulation of the actual stress state of the missile hanging under the air hanging condition of the missile, and important engineering value for the ground design verification of the static test of the missile hanging.

[0064] In the description of the present application, it should be understood that the orientations or positional relationships indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0065] The specific embodiments of the application are described above. It should be understood that the application is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the application. In the case of no conflict, the embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other.

Claims

1. A hyperstatic multi-point support combined static test system for a multi-hanger missile, characterized in that, The system comprises a bearing support module (100), a tooling module (500), a static force loading module (300), a test module (400) and a plurality of slider loading tools; The bearing support module (100) comprises a bearing structure and a support structure; the bearing structure is used for bearing a hanging missile (200), and the support structure is used for providing a support point for the tooling module (500); The hanging missile (200) is installed on the bearing structure through the slider loading tool; The hanging missile (200) comprises a missile body (9) and a plurality of sliders, the plurality of sliders are installed on the missile body (9) and are distributed along the length direction of the missile body (9); the number of the sliders corresponds to the number of the slider loading tools one by one, and the sliders and the slider loading tools are matched with each other; The tooling module (500) is connected with the missile body (9); The static force loading module (300) can provide a force for the missile body (9) through the tooling module (500); The test module (400) is used for testing the stress condition of the missile body (9); The number of the sliders and the number of the slider loading tools are both 2; The bearing structure comprises a third support column (3) and a fourth support column (4); the third support column (3) and the fourth support column (4) are arranged at the bottom of the hanging missile (200) along the length direction of the hanging missile (200); The two sliders comprise a front slider (10) and a rear slider (11); the two slider loading tools comprise a front slider loading tool (5) and a rear slider loading tool (6); The front slider loading tool (5) is installed at the top of the fourth support column (4), and the rear slider loading tool (6) is installed at the top of the third support column (3).

2. The hyperstatic multi-point support combined static test system for multiple suspension missiles according to claim 1, characterized in that, The tooling module (500) comprises an axial force loading tool (7) and a transverse force loading tool (8); One end of the axial force loading tool (7) is connected with one end of the missile body (9) close to the fourth support column (4); the axial force loading tool (7) is installed at the center of mass of the missile body (9); The axial force loading tool (7) and the transverse force loading tool (8) are connected with the static force loading module (300).

3. The hyperstatic multi-point support combined static test system of a multiple suspension missile according to claim 2, characterized in that, The static force loading module (300) comprises a loading control device (12), an axial force applying assembly and a transverse force applying assembly; The axial force loading tool (7) is connected with the loading control device (12) through the axial force applying assembly; The transverse force loading tool (8) is connected with the loading control device (12) through the transverse force applying assembly.

4. The hyperstatic multi-point support combined static test system of the multiple suspension missile according to claim 2, characterized in that, The support structure comprises a first vertical column (1) and a second vertical column (2); The first vertical column (1) is provided with a first mounting position (32), and the second vertical column (2) is provided with a second mounting position (33); the first mounting position (32) is used for being connected with the axial force loading tool (7), and the second mounting position (33) is used for being connected with the transverse force loading tool (8).

5. The hyperstatic multi-point support combined static test system of multi-hanging missiles according to claim 3, characterized in that, The axial force applying assembly comprises an axial force sensor (13), an axial force actuator cylinder (15), an axial force hydraulic loading pipeline (17) and an axial force sensor lead wire (19). The axial force actuator (15) is installed on the axial force loading tool (7), and the axial force actuator (15) is connected with the loading control device (12) through an axial force hydraulic loading pipeline (17), and the axial force actuator (15) can apply an axial force to the elastic body (9) under the action of the loading control device (12). The axial force sensor (13) is installed on the axial force loading tool (7) and used for measuring the axial force borne by the elastic body (9); and the axial force sensor (13) is electrically connected with the loading control device (12) through an axial force sensor lead wire (19).

6. The hyperstatic multi-point support combined static test system of multi-hanging missiles according to claim 3, characterized in that, The lateral force applying assembly comprises a lateral force sensor (14), a lateral force actuator (16), a lateral force hydraulic loading pipeline (18) and a lateral force sensor lead wire (20). The lateral force actuator (16) is installed on the lateral force loading tool (8); the lateral force actuator (16) is connected with the loading control device (12) through the lateral force hydraulic loading pipeline (18), and the lateral force actuator (16) can apply a lateral force to the elastic body (9) through the lateral force loading tool (8) under the action of the loading control device (12). The lateral force sensor (14) is installed on the lateral force loading tool (8) and used for measuring the lateral force borne by the elastic body (9); and the lateral force sensor (14) is electrically connected with the loading control device (12) through the lateral force sensor lead wire (20).

7. The hyperstatic multi-point support combined static test system of multi-hanging missiles according to claim 1, characterized in that, The front sliding block (10) and the rear sliding block (11) each have two support points, and the four support points form an over-determinate structure.

8. The hyperstatic multi-point support combined static test system of multi-hanging missiles according to claim 1, characterized in that, The test module (400) comprises a strain displacement test device (21), a first displacement meter (22), a second displacement meter (23), a first strain gauge (24) and a second strain gauge (25). The first displacement meter (22), the second displacement meter (23), the first strain gauge (24) and the second strain gauge (25) are connected with the displacement test device (21) through lead wires. The test module (400) is used for measuring the elastic deformation of the elastic body (9) and the stress of the support points of the front and rear sliding blocks.

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