A small-scale universal modal testing device for rockets

Abstract

This application proposes a small-scale universal modal testing device for rockets, comprising a suspension mechanism for suspending the rocket body and a testing mechanism with an impact end, wherein the impact end can impact the rocket body around a first axis. It also includes a drive mechanism for driving the impact end to impact the rocket body, and a testing platform for mounting the suspension mechanism and the testing mechanism. In use, the impact end is rotated around the rocket body with the first axis as the center and stopped at a suitable position. At this point, the drive mechanism drives the impact end to impact the rocket body. Compared to existing technologies that only include four impact points (left, right, top, and bottom), the impact end that can surround the rocket body has more impact positions, allowing for more flexible adjustment and facilitating the simulation of multi-position impact tests.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of rocket test, in particular to a general modal test device for small rocket. BACKGROUND

[0002] The rocket is a forward-propelled flying vehicle by the reaction force generated by the working medium of the rocket engine. In order to ensure the structural stability of the rocket, a plurality of rocket structure related tests will be carried out, including buffeting model wind tunnel test, structural thermal elastic test, vibration characteristic test of the whole rocket and its components, etc.

[0003] In the prior art, when testing the natural frequency of the rocket body with two open ends, a plurality of spring hangers are usually used to hoist the rocket body, and a plurality of sensors are arranged on the rocket body in a circumferential and axial direction. Then, the rocket body is knocked by tools in multiple positions (usually six directions, i.e. up, down, left, right, front and back, up and down are the radial direction of the rocket body, and front and back are the axial direction of the rocket body), and the rocket body moves slightly. The displacement is obtained through the sensors, so as to complete the test of the natural frequency of the rocket body. However, the test device only has four tools for applying impact in the radial direction of the rocket body, and the impact points of the tools are fixed, which is not convenient for simulating the test of multiple position impacts. SUMMARY

[0004] In view of the above defects or deficiencies in the prior art, the present application aims to provide a general modal test device for small rocket, comprising:

[0005] A test platform having a mounting surface thereon;

[0006] A suspension mechanism arranged on the mounting surface for hoisting a rocket body, wherein the axis of the rocket body is a first axis, and the extension direction of the first axis is a first direction;

[0007] A test mechanism arranged on the mounting surface and having a knocking end capable of moving in a circumferential direction of the rocket body with the first axis as the center;

[0008] A driving mechanism for driving the knocking end to knock the rocket body.

[0009] According to the technical scheme provided by the embodiments of the present application, the test mechanism comprises a surrounding assembly arranged on the mounting surface, the surrounding assembly comprises a circular arc guide rail arranged outside the rocket body and coaxially arranged with the rocket body, a sliding seat matched with the circular arc guide rail is arranged on the circular arc guide rail, the sliding seat can move in a circumferential direction of the circular arc guide rail with the first axis as the center, and a knocking assembly is arranged at the end of the sliding seat away from the circular arc guide rail, and the end of the knocking assembly close to the rocket body is the knocking end.

[0010] According to the technical solution provided in the embodiments of this application, the surrounding assembly further includes an outer gear ring disposed on the arc guide rail away from the slide end, a drive motor is provided on the side of the slide away from the arc guide rail, and a drive gear is connected to the output shaft of the drive motor, the drive gear meshing with the outer gear ring.

[0011] According to the technical solution provided in the embodiments of this application, the arc guide rail is composed of two semicircular guide rails distributed on both sides of the rocket body along the second direction, and the external gear ring is composed of two semicircular gear rings distributed on both sides of the rocket body along the second direction, wherein the second direction is perpendicular to the first direction.

[0012] According to the technical solution provided in the embodiments of this application, the testing mechanism further includes two support assemblies respectively disposed on the side of the semicircular gear ring away from the semicircular guide rail. One end of the support assembly is detachably connected to the testing platform, and the support assembly can drive the semicircular gear ring and the semicircular guide rail to move along a third direction; the third direction is perpendicular to the first direction and the second direction.

[0013] According to the technical solution provided in the embodiments of this application, a first column is provided on the test platform corresponding to each of the bracket components, and the extension direction of the first column is the third direction; each of the bracket components includes a sleeve sleeved outside the first column and connected to the semi-circular toothed ring, and the sleeve can be raised and lowered along the first column.

[0014] According to the technical solution provided in the embodiments of this application, the testing mechanism is provided with a centering component near the end of the rocket body, and the centering component is used to ensure that the rocket body and the circular guide rail are coaxially arranged.

[0015] According to the technical solution provided in the embodiments of this application, the suspension mechanism includes a plurality of beam frame assemblies distributed along the first direction on the test platform. Each beam frame assembly includes two second columns distributed along the second direction on both sides of the rocket body, a crossbeam spanning the tops of the two second columns, and two suspension ropes disposed at the bottom of the crossbeam. The ends of the two suspension ropes away from the crossbeam are connected to the two ends of the rocket body along the second direction.

[0016] According to the technical solution provided in the embodiments of this application, the suspension mechanism further includes a positioning component disposed on the mounting surface, the positioning component being used for positioning the two second columns of each beam frame assembly.

[0017] According to the technical solution provided in the embodiments of this application, the positioning component includes a plurality of T-shaped grooves arranged along the second direction on the mounting surface. The opening of each T-shaped groove faces the rocket body and extends in the first direction. A T-shaped nut that can slide along the first direction is provided in the T-shaped groove, and each second column is threadedly connected to the T-shaped nut.

[0018] According to the technical solution provided in the embodiments of this application, the rocket body is equipped with a vibration sensor. When the rocket body is impacted, the vibration sensor can obtain the natural frequency of the rocket body.

[0019] In summary, this application proposes a small-scale universal modal testing device for rockets, comprising a suspension mechanism for suspending the rocket body and a testing mechanism with an impact end, wherein the impact end can impact the rocket body around a first axis. It also includes a drive mechanism for driving the impact end to impact the rocket body, and a testing platform for mounting the suspension mechanism and the testing mechanism. In use, the impact end is rotated around the rocket body with the first axis as the center and stopped at a suitable position. At this point, the drive mechanism drives the impact end to impact the rocket body. Compared to existing technologies that only include four impact points (left, right, top, and bottom), the impact end, which can surround the rocket body, has more impact positions, is more flexible in adjustment, and facilitates simulation of multi-position impact tests. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the structure of a small rocket universal modal testing device provided in an embodiment of this application;

[0021] Figure 2 A schematic diagram of the semicircular guide rail and semicircular gear ring of a small rocket universal modal testing device provided in this application embodiment;

[0022] Figure 3 A schematic diagram of the drive gear and semi-circular gear ring of a small rocket universal modal testing device provided in this application embodiment;

[0023] Figure 4 A schematic diagram of the crossbeam and second column of a general modal testing device for a small rocket provided in this application embodiment;

[0024] Figure 5 for Figure 4 A magnified view of a portion of region A in the middle;

[0025] Figure 6 This is a schematic diagram of the structure of a laser ranging sensor and drive mechanism for a small rocket universal modal testing device provided in an embodiment of this application.

[0026] The text labels in the image represent:

[0027] 1. Test platform; 2. Rocket body; 21. Vibration sensor;

[0028] 3. Suspension mechanism; 31. Second column; 32. Crossbeam; 33. Suspension rope; 34. Second base plate; 35. T-slot; 36. T-nut;

[0029] 4. Testing mechanism; 41. Semicircular guide rail; 42. Slide block; 43. Widening plate; 44. Mechanical element; 45. Impact column; 46. Semicircular gear ring; 48. Drive motor; 49. Drive gear; 410. Connecting frame; 411. Sleeve; 412. First column; 413. First base plate; 414. Pre-connecting plate; 415. Laser rangefinder sensor; 5. Drive mechanism. Detailed Implementation

[0030] The present application will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, only the parts relevant to the invention are shown in the accompanying drawings.

[0031] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0032] As mentioned in the background section, in view of the problems in the prior art, this application proposes a small rocket universal modal test device, comprising:

[0033] Test platform 1, wherein the test platform 1 has a mounting surface;

[0034] The suspension mechanism 3 is disposed on the mounting surface and is used to suspend the rocket body 2. The axis of the rocket body 2 is a first axis, the extension direction of the first axis is a first direction, and the first direction is the front-back direction.

[0035] Test mechanism 4, which is located on the mounting surface, has an impact end that can move circumferentially around the rocket body 2 with the first axis as the center. The impact end can move circumferentially around the rocket body 2, so any position in the circumferential direction can be selected as the impact point.

[0036] The driving mechanism 5 is used to drive the impact end to impact the rocket body 2. The driving mechanism 5 is a linear motor. The impact end is located at the end of the linear motor near the rocket body 2. The linear motor can push the impact end to move along a straight line towards the rocket body 2 and generate an impact.

[0037] In use, the impact end is rotated around the rocket body 2 with the first axis as the center and stopped at a suitable position. At this time, the impact end is driven by the drive mechanism 5 to impact the rocket body 2. Compared with the prior art which only includes four impact points on the left, right and up and down, the impact end that can surround the rocket body 2 has more impact positions, making the adjustment more flexible and convenient for simulating multi-position impact tests.

[0038] In a preferred embodiment, the testing mechanism 4 includes a surrounding assembly disposed on the mounting surface. The surrounding assembly includes an arcuate guide rail sleeved on the outside of the rocket body 2 and coaxially disposed with the rocket body 2. A slide block 42 is provided on the end face of the arcuate guide rail. The slide block 42 can move circumferentially along the arcuate guide rail with the first axis as the center. An impact assembly is provided at the end of the slide block 42 away from the arcuate guide rail. The impact end is the end of the impact assembly closer to the rocket body 2.

[0039] like Figure 2 and Figure 3 As shown, the arc guide rail is annular, with a limiting groove on both its inner and outer walls. The arc guide rail has a first sidewall near the slide block, and the slide block has a first groove near the arc guide rail. The circular guide rail is disposed in the first groove, and the bottom wall of the first groove fits against the first sidewall. The two side walls of the first groove are provided with limiting protrusions that match the limiting groove. The outer wall of the limiting protrusion fits against the inner wall of the limiting groove. By moving each of the limiting protrusions along the annular limiting groove, the slide block 42 can move circumferentially along the arc guide rail with the first axis as the center.

[0040] The slide block 42 is provided with a widening plate 43 at the end away from the arc guide rail, increasing the installation area of ​​the slide block 42. The drive mechanism 5 is provided on the widening plate 43. The drive mechanism includes a push rod provided near the rocket body 2. The impact assembly is provided at the end of the push rod near the rocket body 2. The impact assembly includes a mechanical element 44 provided on one side of the drive mechanism 5. The mechanical element 44 is provided with an impact column 45 near the end of the rocket body 2. The impact column 45 near the end of the rocket body 2 is the impact end. The impact end is spherical in shape, which reduces the contact area during impact, making the impact force on the rocket body 2 more concentrated. In addition, since the slide block 42 can move circumferentially along the arc guide rail with the first axis as the center, it drives the drive mechanism 5, the mechanical element 44, the impact column 45 and the impact end provided on the slide block 42 to surround the rocket body 2. Ultimately, the impact end can select any position on the circumference of the rocket body 2 as the impact point.

[0041] In a preferred embodiment, the surrounding assembly further includes an external gear ring disposed at the end of the arc guide rail away from the slide 42, and a drive motor 48 is disposed on the side of the slide 42 away from the arc guide rail. The output shaft of the drive motor 48 is connected to a drive gear 49, and the external gear ring meshes with the drive gear 49.

[0042] like Figure 3 As shown, the drive motor 48 drives the drive gear 49 to rotate. Due to the meshing relationship between the drive gear 49 and the external gear ring, the drive gear 49 rolls along the external gear ring, thereby driving the slide block 42 to move along the arc guide rail. Optionally, the drive motor 48 is a servo motor.

[0043] In a preferred embodiment, the arc guide rail is composed of two semicircular guide rails 41 distributed along the second direction on both sides of the rocket body 2, and the external gear ring is composed of two semicircular gear rings 46 distributed along the second direction on both sides of the rocket body 2, wherein the second direction is perpendicular to the first direction.

[0044] like Figure 2 As shown, the second direction is the left-right direction. The semicircular guide rail 41 on the right or the semicircular toothed ring 46 correspond to each other. By separating the two semicircular guide rails 41 to the left and right respectively, and then selecting other positions in the axial direction of the rocket body 2, that is, moving them back and forth along the rocket body 2, the two semicircular guide rails 41 can be recombined to form the arc guide rail. Thus, without disassembling the rocket body 2, the surrounding component can be moved back and forth to adjust the position of the impact point along the axial direction.

[0045] In a preferred embodiment, the testing mechanism 4 further includes two support assemblies respectively disposed on the side of the semicircular gear ring 46 away from the semicircular guide rail 41. One end of each support assembly is detachably connected to the testing platform 1, and the support assembly can drive the semicircular gear ring 46 and the semicircular guide rail 41 to move along a third direction; the third direction is perpendicular to the first direction and the second direction.

[0046] like Figure 2 and Figure 3 As shown, the third direction is the up-down direction. The semicircular toothed ring 46 and the semicircular guide rail 41 are installed on the test platform 1 through the bracket assembly to ensure their stability during use. At the same time, the function of vertical movement makes it easy to adjust the position of the center of the arc guide rail relative to the first axis, so that the center is located on the first axis, avoiding data errors caused by eccentric impact.

[0047] In a preferred embodiment, the test platform 1 is provided with a first column 412 corresponding to each of the bracket components, and the extension direction of the first column 412 is the third direction; each of the bracket components includes a sleeve 411 sleeved on the first column 412 and connected to the semi-circular toothed ring 46, and the sleeve 411 can be raised and lowered along the first column 412;

[0048] like Figure 2 and Figure 3 As shown, optionally, each side wall of the first column 412 is provided with a row of first screw holes at equal intervals along the vertical direction. The sleeve 411 is provided with a first through hole at a position corresponding to each of the first screw holes. A first bolt is provided through the first through hole. The first bolt is threadedly connected to the first screw hole to fix the bracket assembly. At the same time, the sleeve 411 can move up and down according to the connection of the first bolt to different first screw holes. In addition, the bracket assembly can be raised and lowered by conventional electric mechanism, starting mechanism or hydraulic mechanism, which will not be described in detail here.

[0049] like Figure 3 As shown, a connecting frame 410 is provided between the semicircular toothed ring 46 and the sleeve 411. The semicircular guide rail 41 and the semicircular toothed ring 46 are both connected to the connecting frame 410 by threads. The connecting frame 410 is fixedly connected to the sleeve 411. When the semicircular guide rail 41 forms the arc guide rail, the two ends of the two connecting frames 410 abut against each other and are detachably connected by threads, which makes it easy to ensure that the arc guide rail remains stable during use and can be detached.

[0050] In a preferred embodiment, the suspension mechanism 3 includes a plurality of beam frame assemblies distributed along the first direction on the test platform 1. Each beam frame assembly includes two second columns 31 distributed along the second direction on both sides of the rocket body 2, a crossbeam 32 spanning the tops of the two second columns 31, and two suspension ropes 33 disposed at the bottom of the crossbeam 32. The ends of the two suspension ropes 33 away from the crossbeam 32 are connected to the two ends of the rocket body 2 along the second direction.

[0051] like Figure 4As shown, a first lifting ring is connected to the top of the suspension rope 33, and the first lifting ring is connected to the crossbeam 32. A second lifting ring is connected to the bottom of the suspension rope 33, and the second lifting ring is connected to the rocket body 2. Thus, the rocket body 2 and the crossbeam 32 are connected by the suspension rope 33 to suspend the rocket body 2. Optionally, a plurality of second screw holes are arranged in an array on the bottom surface of the crossbeam 32 along the second direction. The top of the first lifting ring has a second bolt that is threadedly connected to the second screw hole. By changing the position of the second screw hole that is threadedly connected to the first lifting ring, the position of the rocket body 2 can be changed along the second direction.

[0052] In a preferred embodiment, the suspension mechanism 3 further includes a positioning component disposed on the mounting surface, the positioning component being used for positioning the two second columns 31 of each beam frame assembly;

[0053] like Figure 1 and Figure 4 As shown, this ensures that the spacing between the two second columns 31 of the same beam frame assembly remains fixed, and that no deviation in the spacing between the two second columns 31 occurs when the beam frame assembly is adjusted along the axial direction of the rocket body 2.

[0054] In a preferred embodiment, the positioning component includes a plurality of T-slots 35 arranged along the second direction on the mounting surface. The opening of each T-slot 35 faces the rocket body 2 and extends in the first direction. A T-nut 36 that can slide along the first direction is provided in the T-slot 35. Each second post 31 is threadedly connected to the T-nut 36.

[0055] like Figure 5 As shown, each of the second columns 31 has a second base plate 34 at its bottom end. A third bolt passes through the third through hole and connects to the T-nut 36, thereby realizing the installation of the second column 31 and the test platform 1. When it is necessary to adjust each of the beam frame components, it is only necessary to loosen the third bolt, so that the T-nut 36 slides along the T-slot 35, thereby realizing the movement of the second column 31 and thus realizing the adjustment of the position of each of the beam frame components. The top of the second column 31 is threadedly connected to the crossbeam 32.

[0056] In a preferred embodiment, the testing mechanism 4 is provided with a centering component near the end of the rocket 2, the centering component being used to ensure that the rocket body 2 is coaxially arranged with the arc guide rail.

[0057] The centering component is located on the end face of the push rod near the rocket body 2, including a laser range sensor 415 located on the push rod near the end of the rocket body 2 and on one side of the mechanical element 44. After the test device is assembled, the test mechanism 4 is driven to rotate along the arc guide rail by the drive motor 48. When it rotates to the top and bottom of the arc guide rail, the laser range sensor 415 can obtain the first vertical distance between itself and the rocket body 2. By comparing the two first vertical distances, it can be determined whether the axis of the rocket body 2 and the axis of the arc guide rail are in a straight line in the vertical direction. If they are not in a straight line, the height of the rocket body 2 can be adjusted by adjusting the position of the sleeve 411 on the first column 412.

[0058] When the testing mechanism 4 drives the laser rangefinder 415 to rotate to both ends of the circular guide rail along the second direction, the laser rangefinder 415 can obtain the second vertical distance between the laser rangefinder 415 and the rocket body 2 at this time. By comparing the two second vertical distances, it can be determined whether the axis of the rocket body 2 and the axis of the circular guide rail are in a straight line along the left and right direction. If they are not in a straight line, the position of the rocket body 2 in the left and right direction can be adjusted by adjusting the position of the first hanging ring on the crossbeam 32.

[0059] In a preferred embodiment, the rocket body 2 is provided with a vibration sensor 47. When the rocket body 2 is impacted, the vibration sensor 47 can obtain the natural frequency of the rocket body 2.

[0060] like Figure 1 As shown, during modal testing, the rocket body 2 is impacted by the test mechanism 4, causing it to oscillate. The natural frequency can be obtained through the vibration sensor 47, and a data model can be established or an existing data model can be verified based on this data. The correspondence between different forces and natural frequencies can be obtained through the mechanical element 44.

[0061] During the modal testing phase, the laser rangefinder 415 continuously acquires the distance between itself and the rocket body 2. When the distance measured by the laser rangefinder 415 is less than a set threshold, it is considered that the rocket body 2 oscillates after being impacted and then contacts the impact end again. Therefore, this part of the data is not reliable due to the interference of the secondary impact, and so this part of the data will be filtered out. In addition, when the rocket body 2 oscillates after the impact, the laser rangefinder 415 can acquire the distance between itself and the rocket body 2 during the oscillation process, so the amplitude of the rocket body 2 can be obtained, which can be used to verify the accuracy of the vibration sensor 21.

[0062] Optionally, two laser rangefinders 415 are provided, respectively located on both sides of the mechanical element 44. When the impact end impacts the rocket body 2, if the direction of the impact force on the rocket body 2 is not perpendicular to the axis of the rocket body 2, the magnitude of the force perpendicular to the rocket body 2 can be calculated from the distance data obtained by the two laser rangefinders 415.

[0063] In a preferred embodiment, such as Figure 2 and Figure 3 As shown, the support assembly also includes a first base plate 413 located at the bottom of the first column 412. The first base plate 413 is bolted to a pre-connecting plate 414, allowing the two support assemblies to be connected via the pre-connecting plate 414. This improves the overall integrity of the two support assemblies and enhances the stability of the arc guide rail and the external gear ring after assembly. Simultaneously, the pre-connecting plate 414 is connected to the test platform 1. The front and rear ends of the pre-connecting plate 414 are provided with multiple fourth through holes corresponding to the T-slot 35. A fourth bolt passes through each of the fourth through holes and is threadedly connected to the T-nut 36, ultimately achieving the connection between each support assembly and the test platform 1. By loosening the fourth bolt and the T-nut 36, the pre-connecting plate 414 and the test mechanism 4 can be moved along the T-slot 35 via the T-nut 36. This allows for adjustment of the impact position along the axial direction without separating the two semi-circular guide rails 41. Combined with adjustment after separation, this makes the operation of adjusting the impact position along the axial direction more flexible.

[0064] This document uses specific examples to illustrate the principles and implementation methods of this application. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this application. The above descriptions are only preferred embodiments of this application. It should be noted that due to the limitations of written expression, while there are objectively infinite specific structures, those skilled in the art can make several improvements, modifications, or changes without departing from the principles of this invention, and can also combine the above technical features in an appropriate manner. These improvements, modifications, changes, or combinations, or the direct application of the inventive concept and technical solution to other situations without modification, should all be considered within the scope of protection of this application.

Claims

1. A small rocket universal modal test device, characterized by, The utility model relates to a test platform for small rockets, comprising: a test platform (1) having a mounting surface; a suspension mechanism (3) provided on the mounting surface for hoisting a rocket body (2), the axis of the rocket body (2) being a first axis, and the extension direction of the first axis being a first direction; a test mechanism (4) provided on the mounting surface and having an impact end capable of moving circumferentially around the rocket body (2) with the first axis as the center; a driving mechanism (5) for driving the impact end to impact the rocket body (2). In use, the impact end is rotated around the rocket body (2) with the first axis as the center, and after the impact end is stopped, the driving mechanism (5) is used to drive the impact end to impact the rocket body (2).

2. The small rocket universal modal test device according to claim 1, characterized in that, The test mechanism (4) comprises a surrounding assembly provided on the mounting surface, the surrounding assembly comprises a circular arc guide rail provided outside the rocket body (2) and coaxially with the rocket body (2), the circular arc guide rail is provided with a sliding seat (42) matched therewith, the sliding seat (42) is capable of moving circumferentially around the circular arc guide rail with the first axis as the center, and the sliding seat (42) is provided with an impact assembly at the end away from the circular arc guide rail, and the impact assembly close to the rocket body (2) is the impact end.

3. The small rocket universal modal test device according to claim 2, characterized in that, The surrounding assembly further comprises an external gear ring provided at the end of the circular arc guide rail away from the sliding seat (42), the side of the sliding seat (42) away from the circular arc guide rail is provided with a driving motor (48), the output shaft of the driving motor (48) is drivingly connected with a driving gear (49), and the driving gear (49) is in mesh with the external gear ring.

4. The small rocket universal modal test device according to claim 3, characterized in that, The circular arc guide rail is composed of two semicircular guide rails (41) distributed on both sides of the rocket body (2) along a second direction, and the external gear ring is composed of two semicircular gear rings (46) distributed on both sides of the rocket body (2) along the second direction, and the second direction is perpendicular to the first direction.

5. The small rocket universal modal test device according to claim 4, characterized in that, The test mechanism (4) further comprises two support assemblies respectively provided at the sides of the semicircular gear rings (46) away from the semicircular guide rails (41), one end of each support assembly is detachably connected with the test platform (1), and the support assembly can drive the semicircular gear ring (46) and the semicircular guide rail (41) to move along a third direction; the third direction is perpendicular to the first direction and the second direction.

6. The small rocket universal modal test device according to claim 5, wherein The test platform (1) is provided with a first stand (412) corresponding to each support assembly, the extension direction of the first stand (412) being the third direction; each support assembly comprises a sleeve (411) sleeved outside the first stand (412) and connected with the semicircular gear ring (46), and the sleeve (411) can be raised and lowered along the first stand (412).

7. The universal modal test device for small rockets according to claim 4, characterized in that, The suspension mechanism (3) comprises a plurality of beam frame assemblies distributed on the test platform (1) along the first direction, each of the beam frame assemblies comprises two second vertical columns (31) distributed on both sides of the rocket body (2) along the second direction, a crossbeam (32) spanning the top of the two second vertical columns (31), and two suspension ropes (33) arranged at the bottom of the crossbeam (32), the two suspension ropes (33) are connected to the two ends of the rocket body (2) along the second direction away from the ends of the crossbeam (32).

8. The universal modal test device for small rockets according to claim 7, characterized in that The suspension mechanism (3) further comprises a positioning assembly arranged on the mounting surface, and the positioning assembly is used for positioning the two second vertical columns (31) of each of the beam frame assemblies.

9. The universal modal test device for small rockets according to claim 8, characterized in that The positioning assembly comprises a plurality of T-shaped grooves (35) arranged on the mounting surface along the second direction, the opening of each of the T-shaped grooves (35) faces the rocket body (2), and the extension direction is the first direction, and the T-shaped groove (35) is provided with a T-shaped nut (36) which can slide along the first direction, and each of the second vertical columns (31) is threadedly connected with the T-shaped nut (36).

10. The universal modal test device for small rockets according to claim 2, characterized in that, The test mechanism is provided with a centering assembly near the end of the rocket body (2), and the centering assembly is used for ensuring that the rocket body (2) is coaxially arranged with the circular arc guide rail.

11. The universal modal test device for small rockets according to claim 1, characterized in that, The rocket body (2) is provided with a vibration sensor (21), and when the rocket body (2) is impacted, the vibration sensor (21) can obtain the natural frequency of the rocket body (2).

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