A large overload experiment system simulating missile launching conditions

Abstract

The application discloses a large-overload experiment system simulating missile launching conditions, and belongs to the technical field of aerospace experiment equipment, which comprises a shock wave converging device for placing explosives, a wave generator, a carrying platform, a test product, a rotating pull rope and an energy absorption device, the energy absorption device is arranged above the test product through a support, the energy absorption device comprises a middle shaft and first energy absorption sheets, the impact force generated after the explosion of the explosives in the shock wave converging device is transmitted to the test product through the wave generator and the carrying platform, when the test product flies out due to the impact and acceleration, the rotating pull rope drives the test product to rotate around the energy absorption device, the transverse movement of the test product is converted into rotation, the unique movement conversion mode effectively converts the kinetic energy of the product, and the speed of the test product is gently reduced, the time required for deceleration is greatly reduced, after the experiment is completed, the experiment can be repeated by only replacing the first energy absorption sheets, and the project cycle can be greatly shortened.

Description

Technical Field

[0001] This invention belongs to the field of aerospace experimental equipment technology, specifically relating to a high overload experimental system for simulating missile launch conditions. Background Technology

[0002] With the rapid development of aerospace, vehicle collision safety, and weapon systems, high-overload testing has become an important means of verifying the impact resistance of equipment. In such tests, especially explosion tests, test pieces often need to withstand extremely high acceleration or impact loads in a very short time. The products produced after the test will have extremely high speeds, making it difficult to bring them to a safe and stable stop; most of them must be destroyed and discarded, resulting in a huge waste of resources. Therefore, knowing how to safely and controllably decelerate products to a stop after testing is crucial for avoiding resource waste and saving costs.

[0003] Common recovery methods used in high overload experiments include sandbox recovery, water-damped recovery, and air-damped recovery. However, these methods have high experimental requirements and certain drawbacks. In addition, plastic deformation of metal, as a common energy absorption method, can also absorb the energy generated by the product, achieving deceleration. However, while current devices that convert the product's kinetic energy into metal plastic deformation can stably convert and absorb the generated energy, enabling product recovery and reuse, the amount of metal consumed during the recovery process is enormous. Summary of the Invention

[0004] The technical problem solved by this invention is to provide a high overload test system that simulates missile launch conditions, simulates missile launch, and then uses an energy absorption device to decelerate and recover the product after the experiment.

[0005] Technical Solution: To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0006] A high-overload experimental system simulating missile launch conditions includes a shock wave focusing element for placing explosives, a waveform generator corresponding to the shock wave focusing element, a mounting platform corresponding to the waveform generator, a test specimen connected to the mounting platform, a rotating rope connected to the test specimen, and an energy-absorbing device connected to the rotating rope. The energy-absorbing device is mounted above the test specimen via a bracket. The energy-absorbing device includes an intermediate shaft and a first energy-absorbing fragment mounted on the intermediate shaft. The impact force generated by the explosion of the explosives in the shock wave focusing element is transmitted to the test specimen through the waveform generator and the mounting platform. When the test specimen is impacted and accelerates outward, the rotating rope causes the test specimen to rotate around the energy-absorbing device.

[0007] Preferably, the intermediate shaft is connected to the test sample via two rotating pull ropes, and a deceleration sail is provided between the two rotating pull ropes. When the rotating pull ropes drive the test sample to rotate around the energy-absorbing device, the deceleration sail continuously wraps around the first energy-absorbing elastic piece and causes the first energy-absorbing elastic piece to undergo plastic deformation.

[0008] Preferably, a sleeve is connected to the intermediate shaft, and a plurality of first energy-absorbing springs are arrayed on the outer circumferential sidewall of the sleeve. The direction in which the first energy-absorbing springs extend outward from the outer circumferential sidewall of the sleeve corresponds to the direction of rotation of the test sample around the energy-absorbing device.

[0009] Preferably, the sleeve is provided with a boss corresponding to the first energy-absorbing spring, and when the deceleration sail wraps around the first energy-absorbing spring, it presses the first energy-absorbing spring onto the boss.

[0010] Preferably, it also includes a guide rail connected to the waveform generator and the mounting platform, a guide rail base for supporting the guide rail, a second energy-absorbing spring sheet disposed on the guide rail base, and an anti-collision box connected to the guide rail base.

[0011] Preferably, multiple second energy-absorbing shrapnels are arranged along the forward direction of the mounting platform.

[0012] Preferably, the test specimen is connected to the mounting platform via a shear pin, and the shear pin breaks under the impact force when the mounting platform transmits the impact force to the test specimen.

[0013] Preferably, a first containment space is formed within the shock wave focusing element, and the explosive is located within the first containment space. The first containment space is frustum-shaped, with a diameter D1 at the outlet and a diameter D2 at the inlet. The waveform generator is located at the outlet of the first containment space.

[0014] Preferably, the first energy-absorbing spring is detachably connected to the sleeve.

[0015] Preferably, the anti-collision box adopts a honeycomb aluminum structure.

[0016] Beneficial effects: Compared with the prior art, the present invention has the following advantages:

[0017] 1. The experimental device provided by the present invention adopts a hanging connection. By suspending the test sample, the lateral movement of the test sample is converted into rotation. When the test sample rotates, it can counteract the work done by gravity and gradually reduce the kinetic energy of the test sample. The tension of the rope can also effectively prevent the test sample from flying out due to excessive speed. This unique motion conversion mode effectively converts the kinetic energy of the product, gently reduces the speed of the test sample, avoids secondary collision and impact of the test sample, improves the repeatability of the test and the efficiency of test sample recovery, and improves the safety of the test.

[0018] 2. A deceleration sail is installed between the rotating ropes. When the large area of ​​the canvas comes into contact with the air, it will generate huge air resistance, which can effectively reduce the kinetic energy of the test sample.

[0019] 3. The first energy-absorbing piece is deformed by rotating and wrapping it. Compared with the deformation caused by collision, this method can avoid generating a large amount of debris and improve the safety of the experiment.

[0020] 4. The energy-absorbing device uses a rotating first energy-absorbing spring with an arc-shaped protrusion to maximize the deformation of the spring, allowing it to absorb more energy and greatly reducing the time required for deceleration. After the experiment is completed, only the first energy-absorbing spring needs to be replaced to repeat the experiment, which can significantly shorten the project cycle. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the overall system structure of Embodiment 1 of the present invention;

[0022] Figure 2 yes Figure 1 Enlarged view of point A in the middle;

[0023] Figure 3 This is a schematic diagram of the cross-sectional structure of the energy absorption device in Example 1;

[0024] Figure 4 This is a schematic diagram of the waveform generator and mounting platform structure in Example 1;

[0025] Figure 5 This is an enlarged view of the test sample in Example 1;

[0026] Figure 6 This is a perspective view of the shock wave focusing component.

[0027] Figure 7 This is a schematic diagram of the side structure of the device in Embodiment 1;

[0028] Figure 8 yes Figure 6 A sectional view along line AA.

[0029] Figure 9 This is a schematic diagram of the cross-sectional structure of the honeycomb aluminum plate in Example 1;

[0030] Figure 10 This is a schematic diagram of the overall system structure of Embodiment 2 of the present invention;

[0031] Figure 11 This is a schematic diagram of the shock wave focusing component structure in Embodiment 2 of the present invention. Detailed Implementation

[0032] The present invention will be further illustrated below with reference to specific embodiments. These embodiments are implemented based on the technical solutions of the present invention, and it should be understood that these embodiments are only used to illustrate the present invention and are not intended to limit the scope of the present invention.

[0033] Example 1

[0034] like Figure 1 and Figure 6 As shown, a high overload experimental system simulating missile launch conditions includes a shock wave focusing component 1, a support 2, a rotating rope 3, an energy absorption device 4, a waveform generator 6, a mounting platform 7, a test sample 9, a guide rail 11, a guide rail base 12, and a crash box 13. A first accommodating space 101 is formed within the shock wave focusing component 1. The first accommodating space 101 is a horizontally arranged frustum shape and gradually contracts from one end to the other. The diameter at the outlet of the frustum-shaped first accommodating space 101 is D1, and the diameter at the inlet is D2. The first accommodating space 101 within the shock wave focusing component 1 is used to place explosives. The shock wave generated by the explosion gradually converges to the outlet in the first accommodating space 101, generating a powerful impact force. The outer wall of the shock wave focusing component 1 is thick enough to fully withstand the impact generated by the explosion.

[0035] like Figure 1 , Figure 4 , Figure 5 , Figure 8 and Figure 9 As shown, the guide rail 11 is connected to one end of the first receiving space 101 of the shock wave focusing component 1. The guide rail 11 is cylindrical, and two guide rails 11 are arranged side by side. The two guide rails 11 are parallel to the axis of the first receiving space 101. The guide rail base 12 is connected to the bottom end of the two guide rails 11 and fixes the two guide rails 11 at the same height. One side of the waveform generator 6 is attached to the outlet of the first receiving space 101, and the mounting platform 7 is attached to the other side of the waveform generator 6. The waveform generator 6 includes a receiving platform 61, a honeycomb aluminum plate 62, and a first slide 63. The first slide 63 is slidably connected to the guide rail 11. The first slide 63 has two grooves corresponding to the guide rail 11. Multiple rows of balls are provided in the grooves. The multiple rows of balls can convert sliding friction into rolling friction, reducing motion resistance, so that the first slide 63 can slide along the two guide rails 11. The receiving platform 61 is connected to the first slide 63. The inner side of the receiving platform 61 is attached to the outlet of the first receiving space 101. The honeycomb aluminum plate 62 is connected to the outer side of the receiving platform 61. The honeycomb aluminum plate 62 has multiple regular hexagonal first through holes 621. The first through holes 621 penetrate from the inner side of the honeycomb aluminum plate 62 to the outer side of the honeycomb aluminum plate 62. The multiple first through holes 621 are arrayed on the honeycomb aluminum plate 62 to form a honeycomb structure. The honeycomb aluminum plate 62 is made of aluminum alloy.

[0036] like Figure 1 , Figure 4 , Figure 5 and Figure 8 As shown, the mounting platform 7 is attached to the outside of the waveform generator 6. The mounting platform 7 includes a second back plate 71, a second shelf 72, and a second slide 73. The second slide 73 is slidably connected to the guide rail 11. The structure and shape of the second slide 73 are the same as those of the first slide 63. The lower end surface of the second slide 73 is also provided with two grooves corresponding to the guide rail 11. Multiple rows of balls are provided in the grooves. The multiple rows of balls can convert sliding friction into rolling friction, reducing motion resistance, so that the second slide 73 can slide along the two guide rails 11. The lower ends of the second back plate 71 and the second shelf 72 are both The test sample 9 is fixedly connected to the second slide 73 and connected to the upper end of the second placement plate 72 via the shear pin 14. The upper surface of the second placement plate 72 is provided with a positioning hole corresponding to the shear pin 14. The shear pin 14 is interference-fitted with the positioning hole to fix the test sample 9 on the second placement plate 72. The height of the second back plate 71 is higher than that of the second placement plate 72. When the test sample 9 is connected to the second placement plate 72, one side of the test sample 9 is attached to the second back plate 71. When the second slide 73 is attached to one side of the first slide 63, the second back plate 71 is attached to the outer surface of the honeycomb aluminum plate 62.

[0037] like Figure 1 , Figure 4 , Figure 5 and Figure 6 As shown, the impact force generated by the explosion of the explosive in the shock wave focusing component 1 acts on the receiving platform 61. The honeycomb aluminum plate 62 can change the acceleration waveform generated by the explosion. The side of the mounting platform 7 bears the impact transmitted from the waveform generator 6. After the mounting platform 7 is impacted, it is transmitted to the test sample 9 on it. The shear pin 14 breaks under the action of huge impact force, so that the test sample 9 gets huge acceleration and flies out. During this process, the shear pin 14 breaks and absorbs some energy.

[0038] like Figure 1 , Figure 2 , Figure 4 , Figure 5 and Figure 7As shown, the support 2 is located in front of the shock wave focusing component 1. The support 2 includes two rectangular frames, which are respectively located on both sides of the guide rail base 12 and connected to the guide rail base 12. The energy absorption device 4 is connected to the top of the support 2. The energy absorption device 4 spans between the two rectangular frames and is fixedly connected to the two rectangular frames respectively. The energy absorption device 4 is located above and in front of the test sample 9. The energy absorption device 4 includes an intermediate shaft 41, a sleeve 43 and a plurality of first energy absorption springs 5. The two ends of the intermediate shaft 41 are respectively connected to the two rectangular frames of the support 2. The sleeve 43 is sleeved outside the intermediate shaft 41 and is fixedly connected to the intermediate shaft 41. In this embodiment, twelve first energy absorption springs 5 ​​are provided. The first energy absorption springs 5 ​​are made of spring steel. The twelve first energy absorption springs 5 ​​are arrayed on the outer circumferential side wall of the sleeve 43. The angle between the first energy absorption spring 5 and the corresponding radius of the sleeve 43 is α, where 90° < α < 180°. The energy absorption device 4 is connected to the test sample 9 via two rotating pull ropes 3. The rotating pull ropes 3 are steel wire ropes. The test sample 9 is connected to a lifting eye screw 91. The rotating pull ropes 3 are connected to the lifting eye screw 91 on the test sample 9. One end of the two rotating pull ropes 3 is connected to the test sample 9, and the other end is connected to the intermediate shaft 41. The connection points of the two rotating pull ropes 3 and the intermediate shaft 41 are located on both sides of the sleeve 43. A deceleration sail 10 is provided between the two rotating pull ropes 3. The deceleration sail 10 is made of existing nylon canvas. In this embodiment, since the width of the test sample 9 is small, the distance between the two rotating pull ropes 3 at the end where the test sample 9 is located is smaller than the distance at the end where the intermediate shaft 41 is located. As a result, the deceleration sail 10 is an inverted trapezoid with a narrow bottom and a wide top. The impact force generated by the explosion of the explosive inside the shock wave focusing component 1 is transmitted to the test sample 9 through the waveform generator 6 and the mounting platform 7. When the test sample 9 is accelerated outward due to the impact, the rotating rope 3 drives the test sample 9 to rotate around the energy absorption device 4, thereby converting the horizontal motion of the test sample 9 into rotational motion around the energy absorption device 4. The two rotating ropes 3 constrain each other during the rotational motion of the test sample 9 to prevent the test sample 9 from deviating. The first energy-absorbing elastic piece 5 extends outward from the outer circumferential side wall of the sleeve 43 in a direction corresponding to the rotational direction of the test sample 9 around the energy absorption device 4. When the test sample 9 rotates around the energy absorption device 4, the deceleration sail 10 on the rotating rope 3 can wrap around and press the first energy-absorbing elastic piece 5 on the energy absorption device 4 along the motion trajectory, causing the first energy-absorbing elastic piece 5 to undergo plastic deformation, gradually consuming the kinetic energy of the test sample 9. In addition, during the rotation of the test sample 9, the large-area deceleration sail 10 will generate huge air resistance, reducing the kinetic energy of the test sample 9. During the upward motion, it can also consume a certain amount of energy by counteracting the work of gravity.

[0039] like Figure 2 and Figure 3As shown, the outer circumferential sidewall of the sleeve 43 is provided with multiple protrusions 44, each corresponding to a single first energy-absorbing spring 5. The side of the protrusion 44 closest to the first energy-absorbing spring 5 is arc-shaped. When the deceleration sail 10 wraps around the first energy-absorbing spring 5, it presses the first energy-absorbing spring 5 onto the protrusion 44. Because one side of the protrusion 44 is arc-shaped, it can better fit the pressed first energy-absorbing spring 5, causing plastic deformation of the first energy-absorbing spring 5. In this embodiment, the protrusion 44 and the sleeve 43 are integrally connected, and the first energy-absorbing spring 5 is detachably connected to the protrusion 44 by bolts. After the experiment is completed, only a new first energy-absorbing spring 5 needs to be replaced for reuse.

[0040] like Figure 1 and Figure 7 As shown, the outermost ends of the guide rail 11 and the guide rail base 12 are connected to the anti-collision box 13. The guide rail base 12 is provided with a second energy-absorbing spring 121. The second energy-absorbing spring 121 is located between the two guide rails 11 and close to the outermost end of the guide rail base 12. Multiple second energy-absorbing springs 121 are arranged at equal intervals along the forward direction of the mounting platform 7. After the test sample 9 is impacted and flies out, the waveform generator 6 and the mounting platform 7 continue to move forward along the guide rail 11. After hitting the second energy-absorbing spring 121, the speed gradually decreases. Finally, it stops after hitting the honeycomb structure anti-collision box 13. The anti-collision box 13 adopts a honeycomb aluminum structure. The anti-collision box 13 is provided with multiple regular hexagonal through holes to form a honeycomb structure. The anti-collision box 13 is made of aluminum alloy.

[0041] Example 2

[0042] like Figure 10 and Figure 11 As shown, the difference from Embodiment 1 is that the shock wave focusing component 1 in this embodiment includes a second housing 18 and a second base 19. The second housing 18 is hollow to form a second accommodating space. The second housing 18 has an opening 181 on the left side, which is a rectangular opening. The second housing 18 has an outlet on the right side. The second base 19 includes a baffle 191 located inside the opening 181. Explosives are placed on the baffle 191 to direct the explosion impact direction to the right. The second housing 18 also has multiple second through holes 182 on the left side, which serve to reduce noise. The second accommodating space gradually narrows towards the outlet. The shock wave generated by the explosion gradually converges in the second accommodating space to the outlet, generating a strong impact force at the outlet to drive the waveform generator 6.

[0043] The above are merely preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A high-overload experimental system simulating missile launch conditions, characterized in that, The device includes a shock wave focusing component (1) for placing explosives, a waveform generator (6) corresponding to the shock wave focusing component (1), a mounting platform (7) corresponding to the waveform generator (6), a test specimen (9) connected to the mounting platform (7), a rotating pull rope (3) connected to the test specimen (9), and an energy-absorbing device (4) connected to the rotating pull rope (3). The energy-absorbing device (4) is mounted above the test specimen (9) via a bracket (2). The energy-absorbing device (4) includes an intermediate shaft (41) and a first energy-absorbing spring (5) mounted on the intermediate shaft (41). The impact force generated after the explosives in the shock wave focusing component (1) explode is transmitted to the test specimen (9) through the waveform generator (6) and the mounting platform (7). When the test specimen (9) is impacted and accelerates out, the rotating pull rope (3) drives the test specimen (9) to rotate around the energy-absorbing device (4).

2. The high overload experimental system for simulating missile launch conditions according to claim 1, characterized in that, The intermediate shaft (41) is connected to the test specimen (9) through two rotating pull ropes (3). A deceleration sail (10) is provided between the two rotating pull ropes (3). When the rotating pull ropes (3) drive the test specimen (9) to rotate around the energy absorption device (4), the deceleration sail (10) continuously wraps around the first energy absorption spring (5) and causes the first energy absorption spring (5) to plastically deform.

3. The high overload experimental system for simulating missile launch conditions according to claim 2, characterized in that, A sleeve (43) is connected to the intermediate shaft (41), and a plurality of first energy-absorbing springs (5) are arrayed on the outer circumferential sidewall of the sleeve (43). The first energy-absorbing springs (5) extend outward from the outer circumferential sidewall of the sleeve (43) in a direction corresponding to the rotation direction of the test sample (9) around the energy-absorbing device (4).

4. The high overload experimental system for simulating missile launch conditions according to claim 3, characterized in that, The sleeve (43) is provided with a boss (44) corresponding to the first energy-absorbing spring (5). When the deceleration sail (10) wraps around the first energy-absorbing spring (5), it presses the first energy-absorbing spring (5) onto the boss (44).

5. The high overload experimental system for simulating missile launch conditions according to claim 1, characterized in that, It also includes a guide rail (11) connected to the waveform generator (6) and the mounting platform (7), a guide rail base (12) for supporting the guide rail (11), a second energy-absorbing spring (121) disposed on the guide rail base (12), and a crash box (13) connected to the guide rail base (12).

6. The high overload experimental system for simulating missile launch conditions according to claim 5, characterized in that, Multiple second energy-absorbing springs (121) are arranged along the forward direction of the mounting platform (7).

7. The high overload experimental system for simulating missile launch conditions according to claim 2, characterized in that, The test specimen (9) is connected to the mounting platform (7) via a shear pin (14). When the mounting platform (7) transmits the impact force to the test specimen (9), the shear pin (14) breaks under the impact force.

8. The high overload experimental system for simulating missile launch conditions according to claim 1, characterized in that, The shock wave focusing member (1) forms a first containment space, and the explosive is located in the first containment space. The first containment space is frustum-shaped, with the diameter at the outlet of the frustum-shaped first containment space being D1 and the diameter at the inlet being D2. The waveform generator (6) is located at the outlet of the first containment space.

9. The high overload experimental system for simulating missile launch conditions according to claim 3, characterized in that, The first energy-absorbing spring (5) is detachably connected to the sleeve (43).

10. The high overload experimental system for simulating missile launch conditions according to claim 5, characterized in that, The anti-collision box (13) adopts a honeycomb aluminum structure.

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