Device and method for testing strength of installation structure of aircraft energy storage equipment

Abstract

The invention discloses an aircraft energy storage equipment installation structure strength test device and test method, and the test device comprises a test frame structure, a fuselage constraint tool, an upward load loading structure, a lateral load loading structure, a forward load loading structure, and an energy storage equipment test fake part. The fuselage constraint tool is installed on the test frame structure and used for stably and firmly constraining a fuselage test piece, the energy storage equipment test fake piece is installed on the fuselage test piece, and the upward load loading structure, the lateral load loading structure and the forward load loading structure are respectively installed on the test frame structure. The testing device is used for loading loads in different directions on the energy storage equipment testing fake part, so that strength verification of the energy storage equipment mounting structure in different directions is realized. The airplane energy storage equipment installation structure strength test device and test method have the advantages of simple operation, low cost, high reliability and strong versatility.

Description

Technical Field

[0001] The invention relates to the field of aircraft structure strength testing, and specifically provides an aircraft energy storage equipment installation structure strength testing device and a testing method. Background Art

[0002] New energy aircraft are aircraft that use hydrogen fuel and electricity as propulsion energy, which can solve the carbon emission problem of traditional fuel aircraft. Energy storage equipment is often a large concentrated mass in new energy aircraft. During the aircraft development process, there are high requirements for the installation structure of the concentrated mass on these aircraft. Not only must it meet the needs of its installation, but it must also consider the inertial load under emergency landing conditions to ensure that the concentrated mass of these energy storage devices is firmly installed. Article 23.561 of CCAR23 clearly requires that the aircraft should be able to protect the safety of the occupants in emergency landing conditions. The concentrated mass in the cabin that may harm the occupants must be able to withstand the inertial impact force upward (3.0 G), lateral (4.5 G), and forward (18.0 G) to ensure that these concentrated masses and their installation structures are not damaged. Therefore, in order to meet these requirements, the concentrated mass of these energy storage devices and their installation structures must be strength verified. However, these energy storage devices are installed with concentrated mass within the aircraft body structure. Due to space and load limitations, it is difficult to load and complete loading in a timely manner using traditional heavy object loading methods during strength tests. It also cannot simulate the actual load conditions of the aircraft, resulting in reduced accuracy of the test results.

[0003] Therefore, it is an urgent need in aircraft research and development to develop a test device and test method for structural strength testing of aircraft energy storage equipment installation to accurately simulate the actual working conditions of the aircraft and achieve accurate loading. Summary of the invention

[0004] In view of this, an object of the present invention is to provide an aircraft energy storage device installation structure strength test device and test method to solve the problems existing in the existing aircraft energy storage device installation structure strength test.

[0005] On one hand, the present invention provides an aircraft energy storage device installation structure strength test device, comprising: a test frame structure, a fuselage restraint tooling, an upward load loading structure, a lateral load loading structure, a forward load loading structure and an energy storage device test dummy; The test frame structure includes a base platform, frame columns, a top longitudinal beam and a top cross beam. The frame columns are four and are installed at intervals on the base platform. The top longitudinal beams are two and are installed on the tops of two groups of frame columns in pairs, forming two groups of parallel gantry structures. The top cross beam is installed across the top of the two top longitudinal beams and can move along the extension direction of the top longitudinal beams. The fuselage restraint tooling is fixedly installed on the basic platform and is located between the two groups of gantry structures, and is used to fix the fuselage test piece, wherein the fuselage test piece is provided with an energy storage device installation structure, and the energy storage device installation structure is used to cooperate with the installation of the energy storage device test dummy; The upward load loading structure includes a first servo electric cylinder, a first loading rod and a first tension and pressure sensor, wherein the first servo electric cylinder is installed on the top crossbeam, the first loading rod is vertically arranged and one end of which is fixedly connected to the output end of the first servo electric cylinder through the first tension and pressure sensor, and the other end of the first loading rod is used to connect to the loading connection interface of the energy storage device test dummy; The lateral load loading structure includes a lateral loading support column, a second servo electric cylinder, a second loading rod and a second tension and pressure sensor, wherein the lateral loading support column is installed on the base platform, the second servo electric cylinder is installed on the lateral loading support column, the second loading rod is horizontally arranged and one end of the second loading rod is fixedly connected to the output end of the second servo electric cylinder through the second tension and pressure sensor, and the other end of the second loading rod is used to connect to the loading connection interface of the energy storage device test dummy; The forward load loading structure includes a pulley support frame, a pulley, a third servo electric cylinder, a wire rope and a third tension and pressure sensor, wherein the pulley support frame is fixedly arranged above the base platform, the pulley is installed on the pulley support frame, the third servo electric cylinder is installed on the top cross beam, one end of the wire rope is fixedly connected to the output end of the third servo electric cylinder through the third tension and pressure sensor, and the other end of the wire rope passes around the pulley for connecting to the loading connection interface of the energy storage device test dummy.

[0006] Preferably, the base platform is provided with a multi-hole matrix to meet the different installation requirements of the components installed thereon.

[0007] Further preferably, a guide rail and a slider are installed on the top of the top longitudinal beam, and the top cross beam is slidably installed on the guide rail of the top longitudinal beam through the slider and is locked by a stopper.

[0008] Further preferably, the top crossbeam and the side loading support column are both provided with two rows of mounting holes along their length direction for adjusting the mounting position of the servo electric cylinder.

[0009] Further preferably, the fuselage restraint tooling includes a left wing-body separation surface restraint tooling, a right wing-body separation surface restraint tooling, a left main start restraint tooling, a right main start restraint tooling and a front start restraint tooling; the lower parts of the left wing-body separation surface restraint tooling, the right wing-body separation surface restraint tooling, the left main start restraint tooling, the right main start restraint tooling and the front start restraint tooling are all connected to the basic platform; the upper parts of the left wing-body separation surface restraint tooling, the right wing-body separation surface restraint tooling, the left main start restraint tooling, the right main start restraint tooling and the front start restraint tooling are respectively used to connect with the left wing-body separation surface interface, the right wing-body separation surface interface, the main landing gear left installation interface, the main landing gear right installation interface and the front landing gear installation interface of the fuselage test piece.

[0010] Further preferably, the left wing-body separation surface constraint tooling and the right wing-body separation surface constraint tooling are respectively slidably mounted on a mounting seat and locked by a stopper, and the mounting seat is fixedly mounted on the basic platform.

[0011] Further preferably, the left and right ends of the pulley support frame are respectively fixed to the left wing-body separation surface constraint tooling and the right wing-body separation surface constraint tooling.

[0012] Further preferably, the energy storage device test dummy includes a hydrogen cylinder test dummy and a battery pack test dummy, and both the hydrogen cylinder test dummy and the battery pack test dummy are provided with upward, sideways and forward loading connection interfaces.

[0013] The present invention also provides a method for testing the strength of an aircraft energy storage device installation structure, using the above-mentioned aircraft energy storage device installation structure strength testing device, the testing method comprises the following steps: Install the energy storage device test dummy in the energy storage device installation structure of the fuselage test piece; Installing the fuselage restraint tooling on the test frame structure according to the size of the fuselage test piece; Connecting the fuselage test piece to the fuselage restraint tooling to restrain the fuselage test piece; Performing an upward load condition test, a lateral load condition test, and a forward load condition test on the energy storage device installation structure; The upward load condition test method is as follows: The upward load loading structure is installed, wherein the first servo electric cylinder is installed on the top crossbeam and is located directly above the energy storage device test dummy, the first loading rod is vertically arranged and one end is fixedly connected to the output end of the first servo electric cylinder through the first tension and pressure sensor, and the other end of the first loading rod is connected to the loading connection interface of the energy storage device test dummy; thereafter, the first servo electric cylinder is turned on and loaded according to the set load value until unloading is completed, thereby completing the loading of the upward load condition test; The lateral load condition test method is as follows: The lateral load loading structure is installed, wherein the lateral loading support column is installed on the base platform and is located on one side of the energy storage device test dummy, the second servo electric cylinder is installed on the lateral loading support column, the second loading rod is horizontally arranged and one end is fixedly connected to the output end of the second servo electric cylinder through the second tension and pressure sensor, and the other end of the second loading rod is connected to the loading connection interface of the energy storage device test dummy; thereafter, the second servo electric cylinder is turned on and loaded according to the set load value until unloading is completed, thereby completing the loading of the lateral load condition test; The forward load condition test method is as follows: The forward load loading structure is installed, wherein the pulley support frame is fixedly arranged above the base platform, the pulley is installed on the pulley support frame, the third servo electric cylinder is installed on the top crossbeam and is located directly above the pulley, one end of the wire rope is fixedly connected to the output end of the third servo electric cylinder through the third tension and pressure sensor, and the other end of the wire rope bypasses the pulley and is connected to the loading connection interface of the energy storage device test dummy; thereafter, the third servo electric cylinder is turned on and loaded according to the set load value until unloaded after completion, thereby completing the loading of the forward load condition test.

[0014] The aircraft energy storage equipment installation structure strength test device provided by the present invention has reasonable structure, simple operation, low cost, high reliability and strong versatility, and provides a test platform for the static strength test of the installation structure of general aviation new energy aircraft energy storage equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments: Figure 1 A structural schematic diagram of an upward load condition test using the aircraft energy storage device installation structural strength test device provided by the present invention; Figure 2 It is a schematic diagram of the connection between the upward load loading structure and the energy storage device test dummy; Figure 3 A schematic diagram of the structure of a lateral load condition test using the aircraft energy storage device installation structural strength test device provided by the present invention; Figure 4 It is a schematic diagram of the connection between the lateral load loading structure and the energy storage device test dummy; Figure 5 It is a schematic diagram of the connection between the forward load loading structure and the energy storage device test dummy; Figure 6 It is the installation diagram of the test frame structure and the fuselage restraint tooling; Figure 7 It is the front view of the test frame structure and fuselage restraint tooling; Figure 8 This is a schematic diagram of the structure of the hydrogen cylinder test dummy; Fig. 9 Schematic diagram of the structure of the battery pack test dummy. DETAILED DESCRIPTION

[0016] The present invention will be further explained below in conjunction with specific implementation schemes, but the present invention is not limited thereto.

[0017] like Figures 1 to 9 As shown, the present invention provides an aircraft energy storage device installation structure strength test device, comprising: a test frame structure 100, a fuselage restraint tooling 200, an upward load loading structure 300, a lateral load loading structure 400, a forward load loading structure and an energy storage device test dummy 600; The test frame structure 100 includes a base platform 101, frame columns 102, a top longitudinal beam 103 and a top cross beam 104. The frame columns 102 are four and are installed at intervals on the base platform 101. The top longitudinal beams 103 are two and are installed on the tops of two groups of frame columns 102, forming two groups of parallel gantry structures. The top cross beam 104 is installed across the top of the two top longitudinal beams 103 and can move along the extension direction of the top longitudinal beams 103. The fuselage restraint tooling 200 is fixedly mounted on the basic platform 101 and located between the two gantry structures, and is used to fix the fuselage test piece 700, wherein the fuselage test piece 700 is provided with an energy storage device mounting structure, and the energy storage device mounting structure is used to cooperate with the installation of the energy storage device test dummy 600; The upward load loading structure 300 includes a first servo electric cylinder 301, a first loading rod 302 and a first tension and pressure sensor 303, wherein the first servo electric cylinder 301 is installed on the top crossbeam 104, the first loading rod 302 is vertically arranged and one end of the first loading rod 302 is fixedly connected to the output end of the first servo electric cylinder 301 through the first tension and pressure sensor 303, and the other end of the first loading rod 302 is used to connect to the loading connection interface of the energy storage device test dummy 600; The lateral load loading structure 400 includes a lateral loading support column 401, a second servo electric cylinder 402, a second loading rod 403 and a second tension and pressure sensor 404, wherein the lateral loading support column 401 is installed on the basic platform 101, the second servo electric cylinder 402 is installed on the lateral loading support column 401, the second loading rod 403 is horizontally arranged and one end is fixedly connected to the output end of the second servo electric cylinder 402 through the second tension and pressure sensor 404, and the other end of the second loading rod 403 is used to connect to the loading connection interface of the energy storage device test dummy 600; The forward load loading structure includes a pulley support frame 501, a pulley 502, a third servo electric cylinder 503, a wire rope 504 and a third tension and pressure sensor 505, wherein the pulley support frame 501 is fixedly arranged above the base platform 101, the pulley 502 is installed on the pulley support frame 501, the third servo electric cylinder 503 is installed on the top crossbeam 104, one end of the wire rope 504 is fixedly connected to the output end of the third servo electric cylinder 503 through the third tension and pressure sensor 505, and the other end of the wire rope 504 bypasses the pulley 502 for connecting to the loading connection interface of the energy storage device test dummy 600.

[0018] The aircraft energy storage device installation structure strength test device can perform strength test and assessment on the energy storage device installation structure on the fuselage test piece. The test process is as follows: first, install the energy storage device test dummy 600 on the fuselage test piece 700, and install the fuselage test piece 700 on the test frame structure 100 through the fuselage constraint tooling 200. Then, use the upward load loading structure 300, the lateral load loading structure 400 and the forward load loading structure to load the energy storage device test dummy 600 upward, laterally and forward respectively to achieve strength verification. Among them, the positions of the upward load loading structure 300, the lateral load loading structure 400 and the forward load loading structure are adjustable to adapt to fuselage test pieces of different sizes. Each loading structure uses a servo electric cylinder to realize load output, and the load is transmitted through a loading rod or a wire rope. The tension pressure sensor is used to detect the size of the loading load, so as to achieve accurate loading.

[0019] As an improvement of the technical solution, Figure 1 , Figure 3 , Figure 6 As shown, the base platform 101 is provided with a multi-hole matrix to meet the different installation requirements of the components installed thereon.

[0020] In order to adjust the position of the top crossbeam, as an improvement of the technical solution, a guide rail and a slider are installed on the top of the top longitudinal beam 103, and the top crossbeam 104 is slidably installed on the guide rail of the top longitudinal beam 103 through the slider and locked by a stopper.

[0021] As an improvement of the technical solution, the top crossbeam 104 and the side loading support column 401 are both provided with two rows of mounting holes along their length direction for adjusting the mounting position of the servo electric cylinder.

[0022] As an improvement of the technical solution, Figure 6 , Figure 7 As shown, the fuselage constraint tooling 200 includes a left wing-body separation surface constraint tooling 201, a right wing-body separation surface constraint tooling 202, a left main start constraint tooling 203, a right main start constraint tooling 204 and a front start constraint tooling 205; the lower parts of the left wing-body separation surface constraint tooling 201, the right wing-body separation surface constraint tooling 202, the left main start constraint tooling 203, the right main start constraint tooling 204 and the front start constraint tooling 205 are all connected to the basic platform 101; the upper parts of the left wing-body separation surface constraint tooling 201, the right wing-body separation surface constraint tooling 202, the left main start constraint tooling 203, the right main start constraint tooling 204 and the front start constraint tooling 205 are respectively used to connect with the left wing-body separation surface interface, the right wing-body separation surface interface, the main landing gear left installation interface, the main landing gear right installation interface and the front landing gear installation interface of the fuselage test piece 700.

[0023] As an improvement of the technical solution, Figure 6 , Figure 7 As shown, the left wing-body separation surface constraint tooling 201 and the right wing-body separation surface constraint tooling 202 are respectively slidably mounted on the mounting seat 206 and locked by a stopper, and the mounting seat 206 is fixedly mounted on the basic platform 101, and is used to further adjust the positions of the left wing-body separation surface constraint tooling 201 and the right wing-body separation surface constraint tooling 202 on the basic platform 101.

[0024] As an improvement of the technical solution, the left and right ends of the pulley support frame 501 are respectively fixed to the left wing-body separation surface constraint tooling 201 and the right wing-body separation surface constraint tooling 202.

[0025] As an improvement of the technical solution, Figure 8 , Fig. 9 As shown, the energy storage device test dummy 600 includes a hydrogen cylinder test dummy 601 and a battery pack test dummy 602 , and both the hydrogen cylinder test dummy 601 and the battery pack test dummy 602 are provided with upward, sideways and forward loading connection interfaces.

[0026] The present invention also provides a method for testing the strength of an aircraft energy storage device installation structure, using the above-mentioned aircraft energy storage device installation structure strength testing device, the testing method comprises the following steps: Install the energy storage device test dummy 600 in the energy storage device installation structure of the fuselage test piece 700; Installing the fuselage restraint tooling 200 on the test frame structure 100 according to the size of the fuselage test piece 700; Connecting the fuselage test piece 700 to the fuselage restraint tooling 200 to restrain the fuselage test piece 700; Performing an upward load condition test, a lateral load condition test, and a forward load condition test on the energy storage device installation structure; The upward load condition test method is as follows: The upward load loading structure 300 is installed, wherein the first servo electric cylinder 301 is installed on the top crossbeam 104 and is located directly above the energy storage device test dummy 600, the first loading rod 302 is vertically arranged and one end is fixedly connected to the output end of the first servo electric cylinder 301 through the first tension and pressure sensor 303, and the other end of the first loading rod 302 is connected to the loading connection interface of the energy storage device test dummy 600; thereafter, the first servo electric cylinder 301 is turned on and loaded according to the set load value until unloading is completed, thereby completing the loading of the upward load condition test; The lateral load condition test method is as follows: The lateral load loading structure 400 is installed, wherein the lateral loading support column 401 is installed on the basic platform 101 and is located on one side of the energy storage device test dummy 600, the second servo electric cylinder 402 is installed on the lateral loading support column 401, the second loading rod 403 is horizontally arranged and one end is fixedly connected to the output end of the second servo electric cylinder 402 through the second tension and pressure sensor 404, and the other end of the second loading rod 403 is connected to the loading connection interface of the energy storage device test dummy 600; thereafter, the second servo electric cylinder 402 is turned on and loaded according to the set load value until unloading is completed, thereby completing the loading of the lateral load condition test; The forward load condition test method is as follows: The forward load loading structure is installed, wherein the pulley support frame 501 is fixedly arranged above the base platform 101, the pulley 502 is installed on the pulley support frame 501, the third servo electric cylinder 503 is installed on the top crossbeam 104 and is located directly above the pulley 502, one end of the steel wire rope 504 is fixedly connected to the output end of the third servo electric cylinder 503 through the third tension and pressure sensor 505, and the other end of the steel wire rope 504 bypasses the pulley 502 and is connected to the loading connection interface of the energy storage device test dummy 600; thereafter, the third servo electric cylinder 503 is turned on and loaded according to the set load value until unloaded after completion, thereby completing the loading of the forward load condition test.

[0027] The detailed description of the present invention is written in a progressive manner, emphasizing the differences between the various implementations, and similar parts thereof can be referred to each other.

[0028] The embodiments of the present invention are described in detail above with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge scope of ordinary technicians in this field without departing from the purpose of the present invention.

Claims

1. An aircraft energy storage equipment installation structure strength test device, characterized in that: include: A test frame structure (100), a fuselage restraint fixture (200), an upward load loading structure (300), a side load loading structure (400), a forward load loading structure and an energy storage device test dummy (600); The test frame structure (100) comprises a base platform (101), frame columns (102), a top longitudinal beam (103) and a top cross beam (104); the frame columns (102) are four and are installed at intervals on the base platform (101); the top longitudinal beams (103) are two and are installed on the tops of two groups of frame columns (102) in pairs, forming two groups of parallel gantry structures; the top cross beam (104) is installed across the tops of the two top longitudinal beams (103) and can move along the extension direction of the top longitudinal beams (103); The fuselage restraint tooling (200) is fixedly mounted on the base platform (101) and located between the two gantry structures, and is used to fix the fuselage test piece (700), wherein an energy storage device mounting structure is provided on the fuselage test piece (700), and the energy storage device mounting structure is used to cooperate with the installation of the energy storage device test dummy (600); The upward load loading structure (300) comprises a first servo electric cylinder (301), a first loading rod (302) and a first tension and pressure sensor (303), wherein the first servo electric cylinder (301) is mounted on the top crossbeam (104), the first loading rod (302) is vertically arranged and one end of the first loading rod (302) is fixedly connected to the output end of the first servo electric cylinder (301) via the first tension and pressure sensor (303), and the other end of the first loading rod (302) is used to connect to the loading connection interface of the energy storage device test dummy (600); The lateral load loading structure (400) comprises a lateral loading support column (401), a second servo electric cylinder (402), a second loading rod (403) and a second tension and pressure sensor (404), wherein the lateral loading support column (401) is mounted on the base platform (101), the second servo electric cylinder (402) is mounted on the lateral loading support column (401), the second loading rod (403) is arranged horizontally and one end of the second loading rod (403) is fixedly connected to the output end of the second servo electric cylinder (402) via the second tension and pressure sensor (404), and the other end of the second loading rod (403) is used to connect to the loading connection interface of the energy storage device test dummy (600); The forward load loading structure comprises a pulley support frame (501), a pulley (502), a third servo electric cylinder (503), a steel wire rope (504) and a third tension and pressure sensor (505), wherein the pulley support frame (501) is fixedly arranged above the base platform (101), the pulley (502) is installed on the pulley support frame (501), the third servo electric cylinder (503) is installed on the top crossbeam (104), one end of the steel wire rope (504) is fixedly connected to the output end of the third servo electric cylinder (503) through the third tension and pressure sensor (505), and the other end of the steel wire rope (504) is passed around the pulley (502) for connection with the loading connection interface of the energy storage device test dummy (600).

2. The aircraft energy storage device installation structure strength test device according to claim 1, characterized in that: The base platform (101) is provided with a porous lattice.

3. The aircraft energy storage device installation structure strength test device according to claim 1, characterized in that: A guide rail and a slider are installed on the top of the top longitudinal beam (103); the top cross beam (104) is slidably installed on the guide rail of the top longitudinal beam (103) via the slider and is locked via a stopper.

4. The aircraft energy storage device installation structure strength test device according to claim 1, characterized in that: The top crossbeam (104) and the side loading support column (401) are both provided with two rows of mounting holes along their length direction.

5. The aircraft energy storage device installation structure strength test device according to claim 1, characterized in that: The fuselage restraint tooling (200) comprises a left wing-body separation surface restraint tooling (201), a right wing-body separation surface restraint tooling (202), a left main start restraint tooling (203), a right main start restraint tooling (204) and a front start restraint tooling (205); the left wing-body separation surface restraint tooling (201), the right wing-body separation surface restraint tooling (202), the left main start restraint tooling (203), the right main start restraint tooling (204) and the front start restraint tooling (205) are The left wing-body separation surface constraint tooling (201), the right wing-body separation surface constraint tooling (202), the left main lift constraint tooling (203), the right main lift constraint tooling (204), and the front lift constraint tooling (205) are respectively used to connect to the left wing-body separation surface interface, the right wing-body separation surface interface, the main landing gear left installation interface, the main landing gear right installation interface, and the front landing gear installation interface of the fuselage test piece (700).

6. The aircraft energy storage device installation structure strength test device according to claim 5, characterized in that: The left wing-body separation surface restraint tooling (201) and the right wing-body separation surface restraint tooling (202) are respectively slidably mounted on a mounting seat (206) and locked by a stopper, and the mounting seat (206) is fixedly mounted on the base platform (101).

7. The aircraft energy storage device installation structure strength test device according to claim 5, characterized in that: The left and right ends of the pulley support frame (501) are respectively fixed to the left wing-body separation surface constraint tooling (201) and the right wing-body separation surface constraint tooling (202).

8. The aircraft energy storage device installation structure strength test device according to claim 1, characterized in that: The energy storage device test dummy (600) comprises a hydrogen bottle test dummy (601) and a battery pack test dummy (602), and both the hydrogen bottle test dummy (601) and the battery pack test dummy (602) are provided with upward, sideways and forward loading connection interfaces.

9. A method for testing the strength of an aircraft energy storage device installation structure, characterized in that: The aircraft energy storage device installation structure strength test device according to any one of claims 1 to 8 is used, and the test method comprises the following steps: Installing the energy storage device test dummy (600) in the energy storage device installation structure of the fuselage test piece (700); Installing a fuselage restraint tool (200) on the test frame structure (100) according to the size of the fuselage test piece (700); Connecting the fuselage test piece (700) to the fuselage restraint tooling (200) to restrain the fuselage test piece (700); Performing an upward load condition test, a lateral load condition test, and a forward load condition test on the energy storage device installation structure; The upward load condition test method is as follows: The upward load loading structure (300) is installed, wherein the first servo electric cylinder (301) is installed on the top crossbeam (104) and is located directly above the energy storage device test dummy (600), the first loading rod (302) is vertically arranged and one end is fixedly connected to the output end of the first servo electric cylinder (301) via the first tension and pressure sensor (303), and the other end of the first loading rod (302) is connected to the loading connection interface of the energy storage device test dummy (600); thereafter, the first servo electric cylinder (301) is turned on and loaded according to the set load value until unloading is completed, thereby completing the loading of the upward load condition test; The lateral load condition test method is as follows: The lateral load loading structure (400) is installed, wherein the lateral loading support column (401) is installed on the base platform (101) and is located on one side of the energy storage device test dummy (600), the second servo electric cylinder (402) is installed on the lateral loading support column (401), the second loading rod (403) is arranged horizontally and one end is fixedly connected to the output end of the second servo electric cylinder (402) through the second tension and pressure sensor (404), and the other end of the second loading rod (403) is connected to the loading connection interface of the energy storage device test dummy (600); then, the second servo electric cylinder (402) is turned on and loaded according to the set load value until unloading is completed, thereby completing the loading of the lateral load condition test; The forward load condition test method is as follows: The forward load loading structure is installed, wherein the pulley support frame (501) is fixedly arranged above the base platform (101), the pulley (502) is installed on the pulley support frame (501), the third servo electric cylinder (503) is installed on the top crossbeam (104) and is located directly above the pulley (502), one end of the steel wire rope (504) is fixedly connected to the output end of the third servo electric cylinder (503) through the third tension and pressure sensor (505), and the other end of the steel wire rope (504) bypasses the pulley (502) and is connected to the loading connection interface of the energy storage device test dummy (600); thereafter, the third servo electric cylinder (503) is turned on and loaded according to the set load value until unloading is completed, thereby completing the loading of the forward load condition test.

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