An underwater launching simulation experiment system for an aircraft

Abstract

The application discloses an aircraft underwater launching simulation experiment system, which comprises a water tank module, a launching module, a projectile replacing module, a diaphragm replacing module, a recovery module, a pneumatic knife gate valve module and a control cabinet. The launching module is arranged below the water tank module, the projectile replacing module is arranged between the launching module and the water tank module, the diaphragm replacing module is arranged inside the water tank module and above a projectile inlet hole of the water tank module, the recovery module is arranged above the water tank module, and the pneumatic knife gate valve module is arranged at the bottom of the water tank module. The aircraft underwater launching simulation experiment system realizes continuous launching of experimental projectiles in the aircraft underwater launching simulation experiment through cooperation of the water tank module, the launching module, the projectile replacing module, the diaphragm replacing module, the recovery module and the pneumatic knife gate valve module, and the complicated operation of projectile replacing is reduced through cooperation of the control cabinet, the test efficiency is improved, and the diaphragm replacing module places the diaphragm above the bottom plate of the water tank, so that the influence of water in the inlet pipeline on the launching state of the projectile caused by placing the diaphragm at the lower part of the water tank is reduced.

Description

Technical Field

[0001] This invention relates to the field of underwater launch simulation technology for aircraft, and more specifically to an underwater launch simulation experimental system for aircraft. Background Technology

[0002] Most current underwater launch simulation systems for aircraft fall into two categories: large-scale experiments conducted in reservoirs and small-scale experiments conducted indoors using water tanks. Existing indoor underwater launch simulation systems for aircraft are mostly designed for single use only. After launch, manual operation is required to achieve a second launch, which cannot achieve continuous launch of experimental missiles. The work before each launch is cumbersome and wastes a lot of time.

[0003] In addition, current underwater launch simulation systems for aircraft typically have a leak-proof diaphragm installed below the water tank during the design process. This results in a longer channel for the projectile to enter the water, which in turn increases water resistance and interferes with the observation of the actual situation of the projectile entering the water. Alternatively, the launch system may be placed directly in the water, causing the projectile to float after launch and requiring a certain amount of time to retrieve the experimental projectile. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide an underwater launch simulation experimental system for aircraft, which can realize the continuous launch of experimental projectiles, reduce the influence of water in the injection pipe on the launch state of the projectile caused by the diaphragm being placed at the bottom of the water tank, facilitate the observation of the actual situation of the experimental projectile entering the water, and improve experimental efficiency.

[0005] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is as follows.

[0006] An underwater launch simulation system for an aircraft includes a water tank module, a launch module, a bomb changing module, a membrane changing module, a recovery module, a pneumatic gate valve module, and a control cabinet. The launch module is located below the water tank module, the bomb changing module is located between the launch module and the water tank module, the membrane changing module is located inside the water tank module and above the bomb inlet, the recovery module is located inside the upper part of the water tank module, and the pneumatic gate valve module is located at the bottom of the water tank module. The launch port of the launch module, the bomb inlet of the water tank module, and the bomb inlet of the recovery module are aligned at their centers. The controlled ends of the water tank module, launch module, bomb changing module, membrane changing module, and pneumatic gate valve module are respectively connected to the output end of the control cabinet.

[0007] The aforementioned underwater launch simulation experimental system for aircraft includes a water tank module comprising a water tank body, three vertical sides of which are made of plexiglass panels, and a high-speed camera is mounted on the outer side of the water tank body opposite to the plexiglass panels; a circulating filter assembly is installed on the bottom plate of the water tank body, and the controlled end of the circulating filter assembly is connected to the output end of the control cabinet.

[0008] The aforementioned underwater launch simulation experimental system for aircraft includes a pneumatic gate valve module. The pneumatic gate valve is located below the bottom plate at the bottom of the water tank body, and the controlled end of the pneumatic gate valve is connected to the output end of the control cabinet.

[0009] The aforementioned underwater launch simulation experimental system for an aircraft includes a launch module comprising a launch compartment, an internal launch chamber, and a launch cavity. The top of the launch cavity extends through the top surface of the launch compartment, and a sabot for supporting the experimental projectile is slidably disposed within the launch cavity. The top and bottom of the launch compartment are respectively provided with a first air inlet and a second air inlet for pressurizing the launch cavity and launching the sabot and the experimental projectile. The first and second air inlets are respectively connected to an inflation assembly, the controlled end of which is connected to the output end of a control cabinet. The launch compartment also includes a negative pressure adsorption assembly for negative pressure adsorption of the sabot for relaunch, the controlled end of which is connected to the output end of the control cabinet.

[0010] The aforementioned underwater launch simulation experimental system for aircraft has an interception flange at the top of the launch chamber to prevent the sabot from being launched into the water tank along with the experimental missile, and the launch port is located at the center of the interception flange.

[0011] The aforementioned underwater launch simulation experimental system for aircraft has a launch cavity extending out of the launch bay connected to a pressure relief port.

[0012] The aforementioned underwater launch simulation experimental system for an aircraft includes a missile changing module comprising a first gear, a stepper motor, and a second gear. The first gear and the second gear mesh and drive each other, and the second gear is connected to the motor shaft of the stepper motor. The first gear is equipped with missile locking components arranged in a circular pattern and at uniform intervals. After rotation, the missile locking components and the experimental missile they hold are aligned with the center of the missile inlet hole in the water tank. The controlled ends of the stepper motor and the missile locking components are respectively connected to the output end of the control cabinet.

[0013] The aforementioned underwater launch simulation experimental system for aircraft includes a membrane changing module comprising a membrane moving assembly and a pneumatic clamping assembly. The membrane moving assembly includes symmetrically arranged slide rails, with two slide rails symmetrical about the center of the projectile inlet. A mounting plate is slidably positioned between the slide rails, and membranes are evenly spaced on the mounting plate. One end of the mounting plate is connected to a rope, and the other end of the rope is connected to a drive motor. The pneumatic clamping assembly is positioned above the membranes and corresponds to the projectile inlet of the water tank module. The pneumatic clamping assembly is connected to a hollow turntable via a connecting arm. The controlled ends of the drive motor, the pneumatic clamping assembly, and the hollow turntable are respectively connected to the output end of the control cabinet.

[0014] The aforementioned underwater launch simulation experimental system for an aircraft includes a recovery module comprising a recovery box with a missile inlet located at the bottom of the recovery box; a shock-absorbing and buffering assembly is provided between the recovery box and the top of the water tank module; an elastic plate is provided inside the recovery box, and a first spring is provided between the elastic plate and the recovery box, with the elastic plate inclined above the missile inlet.

[0015] The aforementioned underwater launch simulation experimental system for aircraft includes a shock absorption and buffer assembly comprising a lower spring seat disposed on the top of the recovery tank, an upper spring seat disposed on the top surface inside the water tank module, and a second spring connecting the upper spring seat and the lower spring seat; the bottom surface of the upper spring seat is provided with an upper guide sleeve, the top surface of the lower spring seat is provided with a lower guide post that is slidably fitted with the upper guide sleeve, and the second spring is sleeved on the outer periphery of the upper guide sleeve and the lower guide post.

[0016] Due to the adoption of the above technical solutions, the technical progress achieved by this invention is as follows.

[0017] This invention provides an underwater launch simulation system for aircraft. The coordinated operation of a water tank module, launch module, missile changing module, membrane changing module, recovery module, pneumatic gate valve module, and control cabinet enables continuous launch of experimental missiles in underwater launch simulation experiments. This reduces the cumbersome missile changing operation and improves experimental efficiency. In the membrane changing module, the membrane is placed above the bottom plate of the water tank. After launch, the experimental missile breaks through the membrane and directly enters the water tank, reducing the time the missile spends in the injection pipe and minimizing the impact of water in the injection pipe on the missile's launch state caused by placing the membrane at the bottom of the water tank. This solves the problem of the delay caused by placing the membrane at the bottom of the water tank. The problem of long shells entering the water and interfering with the observation of the shell entry process was solved by using a pneumatic clamping assembly and a hollow turntable to seal the diaphragm with the shell entry hole without affecting the firing of the next test shell. The problem of large water loss in the water tank during firing was solved by using a diaphragm replacement module and a pneumatic knife gate valve system, which provides a foundation for the reliability of continuous experiments. The use of a recovery box to recover the test shells after firing avoids the process of retrieving test shells from the water and reduces labor intensity. The elastic plate of the recovery box moves the test shell away from the shell entry position, preventing the test shell after firing from blocking the shell entry and affecting the entry of the next test shell.

[0018] During the experiment, the invention also uses a high-speed camera to observe and record the situation inside the water tank in a timely manner. After the experimental data is collected, a three-dimensional trajectory can be generated, which is convenient for data analysis. At the same time, the circulating filtration system ensures that the water in the tank is clear and will not affect the observation due to turbidity. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the specific structure of the present invention; Figure 2 This is a schematic diagram of the specific structure of the water tank module described in this invention; Figure 3 This is a top view of the water tank module described in this invention; Figure 4 This is a schematic diagram of the specific structure of the transmitting module described in this invention; Figure 5 This is a schematic diagram of the internal structure of the transmitting module described in this invention; Figure 6 This is a schematic diagram of the specific structure of the ammunition changing module described in this invention; Figure 7 This is a top view of the reloading module described in this invention; Figure 8 This is a schematic diagram of the specific structure of the membrane replacement module described in this invention; Figure 9 This is another schematic diagram of the membrane replacement module described in this invention; Figure 10 This is a schematic diagram of the specific structure of the recycling module described in this invention.

[0020] Among them: 1. Water tank module, 101. Water tank body, 102. Acrylic glass panel, 103. High-speed camera, 104. Circulating filter assembly, 105. Base plate; Launch module, 201. Launch compartment, 202. First air inlet, 203. Second air inlet, 204. Pressure detection port, 205. Launch chamber, 206. Experimental missile, 207. Missile sabot, 208. Pressure relief port, 209. Interception flange, 210. Lower sealing flange seat, 211. Upper sealing flange seat, 212. Lifting lug; The cartridge changing module includes: 301. First gear; 302. Mounting shaft; 303. Stepper motor; 304. Motor mounting base; 305. Second gear; 306. Cartridge locking assembly. Membrane changing module, 401. Hollow rotary table, 402. Slide rail, 403. Pneumatic clamping assembly, 404. Mounting plate, 405. Membrane sheet, 406. Pulley, 407. Rope, 408. Drive motor, 409. Connecting arm; Recovery module, 501. Recovery box, 502. Projectile inlet, 503. Elastic plate, 504. First spring, 505. Lower spring seat, 506. Upper spring seat, 507. Second spring, 508. Lower guide post, 509. Upper guide sleeve; 6. Pneumatic knife gate valve module, 601. Pneumatic knife gate valve. Detailed Implementation

[0021] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0022] An underwater launch simulation experimental system for aircraft, such as Figures 1 to 10As shown, the system includes a water tank module 1, a launch module 2, a bomb changing module 3, a membrane changing module 4, a recovery module 5, a pneumatic gate valve module 6, and a control cabinet. The launch module 2 is located below the water tank module 1. The bomb changing module 3 is located between the launch module 2 and the water tank module 1. The membrane changing module 4 is located inside the water tank module 1 and is used to seal the bomb inlet of the water tank to prevent liquid leakage. The recovery module 5 is located inside the upper part of the vertical module 1 and is used to recover the experimental bomb after launch. The pneumatic gate valve module 6 is located at the bottom of the water tank module 1 and is used to control the water flow. The launch port of the launch module 2, the bomb inlet of the water tank module 1, and the bomb inlet 502 of the recovery module 5 are aligned at the center.

[0023] The controlled ends of water tank module 1, launching module 2, bomb changing module 3, membrane changing module 4, and pneumatic knife gate valve module 6 are respectively connected to the output end of the control cabinet.

[0024] The water tank module 1 includes a water tank body 101. The three vertical sides of the water tank body 101 are made of plexiglass panels 102. A high-speed camera 103 is installed on the outside of the water tank body 101 opposite to the plexiglass panels 102. The high-speed camera 103 is mounted on the ground by a bracket and is opposite to the plexiglass panels, which is convenient for photographing the water entry state of the experimental projectile.

[0025] The main body 101 of the water tank is equipped with a circulating filter assembly 104 to prevent the water inside the tank from becoming turbid and affecting the experimental observation.

[0026] The circulating filter assembly 104 adopts a conventional water circulating filter structure, and the controlled end of the circulating filter assembly 104 is connected to the output end of the control cabinet.

[0027] The launching module 2 includes a launching compartment 201, a launching cavity 205 is provided inside the launching compartment 201, the top of the launching cavity 205 is provided through the top surface of the launching compartment 201, and a sabot 207 for supporting the experimental projectile 206 is slidably provided inside the launching cavity 205.

[0028] The top and bottom of the launch chamber 201 are respectively provided with a first air inlet 202 and a second air inlet 203 that communicate with the launch cavity 201. The first air inlet 202 and the second air inlet 203 are respectively connected to the inflation assembly. The controlled end of the inflation assembly is connected to the output end of the control cabinet and is used to inflate and pressurize the inside of the launch cavity 205 to launch the sabot 207 and the experimental missile 206 and launch them into the water tank body.

[0029] The top of the launch compartment 201 is also equipped with a pressure detection port 204, which is used to monitor the internal pressure of the launch compartment in real time.

[0030] The launch compartment 201 is also equipped with a negative pressure adsorption assembly, which is used to adsorb the sabot 207 under negative pressure for relaunch.

[0031] The controlled end of the negative pressure adsorption component is connected to the output end of the control cabinet. The negative pressure adsorption component adopts a conventional negative pressure adsorption structure, which is used to adsorb the projectile sabot 207 to the bottom of the launch cavity after the launch is completed so that the experimental projectile can be supported again before the next launch.

[0032] The top of the launch chamber 205 is equipped with an interception flange 209, and the launch port is located in the center of the interception flange 209. The size of the launch port is equal to the maximum diameter of the experimental projectile and smaller than the outer diameter of the sabot 207, so as to prevent the sabot from being launched into the water tank along with the experimental projectile.

[0033] The upper part of the launch chamber 205 extending out of the launch compartment 201 is connected to the pressure relief port 208, which is used to relieve pressure after the experimental missile is launched.

[0034] The launch chamber 201, which is connected to the launch cavity 205, is provided with an upper sealing flange seat 211 and a lower sealing flange seat 210 on its top and lower parts, respectively, to ensure the airtightness of the launch chamber.

[0035] The launch compartment 201 is equipped with a lifting lug 212 on its top to facilitate the adjustment of the launch compartment's position.

[0036] The cartridge changing module 3 includes a first gear 301, a stepper motor 303, and a second gear 305. The first gear 301 and the second gear 305 mesh and drive each other. The second gear 305 is connected to the motor shaft of the stepper motor 303. The controlled end of the stepper motor 303 is connected to the output end of the control cabinet.

[0037] The first gear 301 is provided with projectile locking components 306 arranged in a circular pattern and at uniform intervals. The controlled end of the projectile locking components 306 is connected to the output end of the control cabinet and is used to clamp and lock the experimental projectile 206. The projectile can be changed through the cooperation of the first gear 301 and the second gear 305.

[0038] After rotation, the projectile locking assembly 306 and the experimental projectile 206 it holds are aligned with the center of the water tank inlet hole, facilitating entry into the water tank after launch.

[0039] In this embodiment, there are 4 projectile locking components, which means that 4 experimental projectiles can be launched continuously.

[0040] The center of the first gear 301 is mounted on the bottom of the water tank body 101 via the mounting shaft 302, and the stepper motor 303 is mounted on the lower frame of the water tank body 101 via the motor mounting base 304.

[0041] The membrane replacement module 4 includes a membrane moving assembly and a pneumatic pressing assembly 403. The membrane moving assembly is used to move the new membrane above the inlet hole, and the pneumatic pressing assembly 403 is used to press the membrane onto the inlet hole to prevent water leakage.

[0042] The diaphragm moving assembly includes slide rails 402 symmetrically arranged on the bottom plate 105 of the water tank body 101, with the two slide rails being symmetrical about the center of the bullet inlet. A mounting plate 404 is slidably arranged between the slide rails 402. Diaphragms 405 are evenly arranged on the mounting plate 404. One end of the mounting plate 404 is connected to a rope 407, and the other end of the rope 407 is connected to a drive motor 408. The controlled end of the drive motor 408 is connected to the output end of the control cabinet to control the contraction of the rope to drive the diaphragms to move and achieve diaphragm replacement.

[0043] The drive motor 408 is located on the upper part of the water tank body 101. The drive motor is waterproofed to prevent water from entering and damaging the drive motor. A pulley 406 for changing the direction of the rope 407 is also installed on the base plate 105.

[0044] The pneumatic pressing assembly 403 is positioned above the diaphragm and corresponds to the bullet inlet hole, which facilitates the pneumatic pressing assembly to press the diaphragm onto the bullet inlet hole to seal the bullet inlet hole.

[0045] The pneumatic clamping assembly 403 is connected to the hollow turntable 401 via the connecting arm 409. The hollow turntable drives the pneumatic clamping assembly to rotate, so that after the diaphragm is clamped, the pneumatic clamping assembly is offset into the bullet hole, which will not affect the re-firing of the test bullet.

[0046] The controlled ends of the pneumatic clamping assembly 403 and the hollow turntable 401 are respectively connected to the output end of the control cabinet.

[0047] The recovery module 5 includes a recovery box 501, a projectile inlet 502 located at the bottom of the recovery box 501, a shock-absorbing buffer assembly between the recovery box 501 and the top of the water tank body 101, an elastic plate 503 inside the recovery box 501, a first spring 504 between the elastic plate 503 and the recovery box 501, and the elastic plate 503 is inclined above the projectile inlet 502 to facilitate the movement of the test projectile into the recovery box 501 after entering the box, without blocking the projectile inlet 502.

[0048] The shock absorption and buffer assembly includes a lower spring seat 505 disposed on the top of the recovery tank 501, an upper spring seat 506 disposed on the top surface inside the water tank body 101, and a second spring 507 connecting the upper spring seat 506 and the lower spring seat 505.

[0049] The bottom surface of the upper spring seat 506 is provided with an upper guide sleeve 509, and the top surface of the lower spring seat 505 is provided with a lower guide post 508 that is slidably fitted with the upper guide sleeve 509. The second spring 507 is sleeved on the outer periphery of the upper guide sleeve 509 and the lower guide post 508.

[0050] The pneumatic gate valve module includes a pneumatic gate valve 601, which is located below the bottom plate 105 at the bottom of the water tank body 101. The controlled end of the pneumatic gate valve 601 is connected to the output end of the control cabinet and is used to seal the water tank inlet after the experimental projectile is launched to prevent a large amount of water in the water tank from flowing out and affecting subsequent experiments. After the membrane is replaced, the pneumatic gate valve 601 is activated to open the water tank inlet, so that the next experimental projectile can break through the membrane.

[0051] The working process of this invention is as follows: First, the test projectile 206 is rotated above the launch port by the projectile replacement module 2, and the clamping of the test projectile by the projectile body locking component 306 is released, so that the test projectile falls into the projectile tray 207 through the launch port to support the test projectile. At this time, the pneumatic knife gate valve 601 is in the open state, and the diaphragm 405 is sealed on the projectile inlet of the water tank module.

[0052] Next, air is pumped into the launch chamber 205 through the inflation assembly, which pushes the sabot and the experimental projectile upward. The experimental projectile 206 breaks through the diaphragm 405 above the inlet hole and enters the water, and continues to move upward. It is then recovered into the recovery box 501 through the inlet 502.

[0053] During the launch of the experimental missile, a high-speed camera will record and observe the internal conditions of the water tank in order to evaluate the launch performance.

[0054] After the test projectile passes through the inlet hole, the pneumatic gate valve 601 closes to prevent a large amount of water from flowing out. At the same time, the membrane replacement module 4 operates, moving the new membrane to the top of the inlet hole through the membrane moving assembly, and then sealing and pressing the membrane onto the inlet hole through the pneumatic pressing assembly 403 to form a sealed structure. Then, the pneumatic gate valve 601 is opened to prepare for the next launch.

[0055] After the sabot 207 moves to the top of the launch chamber, it will be limited by the interception flange and will not enter the water tank body with the test missile. Instead, it will move to the bottom of the launch chamber under the action of the negative pressure adsorption component in order to carry out the next launch.

[0056] After the membrane replacement is completed, the new test missile is rotated back above the launch port through the missile replacement module, and the above operation is repeated until all test missiles have been launched and the experiment is stopped.

[0057] This invention provides an underwater launch simulation system for aircraft. Through the coordinated operation of a water tank module, launch module, missile changing module, membrane changing module, recovery module, pneumatic gate valve module, and control cabinet, it enables continuous launch of experimental missiles in underwater launch simulation experiments. This reduces the cumbersome missile changing operation and improves experimental efficiency. In the membrane changing module, the membrane is placed above the bottom plate of the water tank. After launch, the experimental missile breaks through the membrane and directly enters the water tank, reducing the time the missile spends in the injection pipe and minimizing the impact of water in the injection pipe on the missile launch state caused by the membrane being placed at the bottom of the water tank. The pneumatic clamping assembly and hollow turntable work together to seal the diaphragm with the inlet hole, ensuring that the next test missile launch is not affected. The diaphragm replacement module and pneumatic gate valve system work together to solve the problem of large water loss in the water tank during launch, providing a foundation for the reliability of continuous experiments. The recovery box is used to recover the test missiles after launch, avoiding the process of retrieving test missiles from the water and reducing labor intensity. The elastic plate of the recovery box moves the test missile away from the inlet position, preventing the test missile after launch from blocking the inlet and affecting the entry of the next test missile.

[0058] During the experiment, the invention also uses a high-speed camera to observe and record the situation inside the water tank in a timely manner. After the experimental data is collected, a three-dimensional trajectory can be generated, which is convenient for data analysis. At the same time, the circulating filtration system ensures that the water in the tank is clear and will not affect the observation due to turbidity.

Claims

1. An underwater launch simulation experimental system for aircraft, characterized in that: The system includes a water tank module (1), a launch module (2), a bomb changing module (3), a membrane changing module (4), a recovery module (5), a pneumatic gate valve module (6), and a control cabinet. The launch module (2) is located below the water tank module (1), the bomb changing module (3) is located between the launch module (2) and the water tank module (1), the membrane changing module (4) is located inside the water tank module (1) and above the bomb inlet of the water tank module, the recovery module (5) is located inside the water tank module (1) and above it, and the pneumatic gate valve module (6) is located at the bottom of the water tank module (1). The launch port of the launch module (2), the bomb inlet of the water tank module (1), and the bomb inlet (502) of the recovery module (5) are aligned at the center. The controlled ends of the water tank module (1), the launch module (2), the bomb changing module (3), the membrane changing module (4), and the pneumatic gate valve module (6) are respectively connected to the output end of the control cabinet. The cartridge changing module (3) includes a first gear (301), a stepper motor (303), and a second gear (305). The first gear (301) and the second gear (305) mesh and drive each other. The second gear (305) is connected to the motor shaft of the stepper motor (303). The first gear (301) is provided with cartridge locking components (306) arranged in a circular pattern and at uniform intervals. After rotation, the cartridge locking components (306) and the experimental cartridge (206) held by them are aligned with the center of the cartridge inlet hole of the water tank. The controlled ends of the stepper motor (303) and the cartridge locking components (306) are respectively connected to the output end of the control cabinet. The membrane replacement module (4) includes a membrane moving assembly and a pneumatic pressing assembly (403); the membrane moving assembly includes symmetrically arranged slide rails (402), the two slide rails (402) are symmetrical about the center of the bullet inlet hole, and an mounting plate (404) is slidably arranged between the slide rails (402). The mounting plate (404) is provided with membranes (405) evenly spaced on it. One end of the mounting plate (404) is connected to a rope (407), and the other end of the rope (407) is connected to a drive motor (408). The membrane moving assembly moves the new membrane to above the bullet inlet hole; the pneumatic pressing assembly (403) is arranged above the membrane and corresponds to the bullet inlet hole of the water tank module (1); the pneumatic pressing assembly (403) is connected to the hollow turntable (401) through a connecting arm (409); the controlled ends of the drive motor (408), the pneumatic pressing assembly (403), and the hollow turntable (401) are respectively connected to the output end of the control cabinet; The recycling module (5) includes a recycling box (501) with a projectile inlet (502) located at the bottom of the recycling box (501); a shock-absorbing buffer assembly is provided between the recycling box (501) and the top of the water tank module (1); an elastic plate (503) is provided inside the recycling box (501), and a first spring (504) is provided between the elastic plate (503) and the recycling box (501); the elastic plate (503) is inclined above the projectile inlet (502); The shock absorption and buffer assembly includes a lower spring seat (505) disposed on the top of the recycling box (501), an upper spring seat (506) disposed on the top surface inside the water tank module (1), and a second spring (507) connecting the upper spring seat (506) and the lower spring seat (505); the bottom surface of the upper spring seat (506) is provided with an upper guide sleeve (509), the top surface of the lower spring seat (505) is provided with a lower guide post (508) that is slidably fitted with the upper guide sleeve (509), and the second spring (507) is sleeved on the outer periphery of the upper guide sleeve (509) and the lower guide post (508).

2. The underwater launch simulation experimental system for aircraft according to claim 1, characterized in that: The water tank module (1) includes a water tank body (101), the three vertical sides of the water tank body (101) are made of plexiglass panels (102), and a high-speed camera (103) is provided on the outside of the water tank body (101) opposite to the plexiglass panels (102); a circulating filter assembly (104) is installed on the bottom plate (105) at the bottom of the water tank body (101), and the controlled end of the circulating filter assembly (104) is connected to the output end of the control cabinet.

3. The underwater launch simulation experimental system for aircraft according to claim 2, characterized in that: The pneumatic knife gate valve module (6) includes a pneumatic knife gate valve (601), which is located below the bottom plate (105) at the bottom of the water tank body (101). The controlled end of the pneumatic knife gate valve (601) is connected to the output end of the control cabinet.

4. The underwater launch simulation experimental system for aircraft according to claim 1, characterized in that: The launching module (2) includes a launching compartment (201), inside which is a launching cavity (205). The top of the launching cavity (205) extends through the top surface of the launching compartment (201). Inside the launching cavity (205), a projectile support (207) for supporting the experimental projectile (206) is slidably arranged. The top and bottom of the launching compartment (201) are respectively provided with a first air inlet (202) and a second air inlet (203) for pressurizing the launching cavity (205) and launching the projectile support (207) and the experimental projectile (206). The first air inlet (202) and the second air inlet (203) are respectively connected to an inflation assembly. The controlled end of the inflation assembly is connected to the output end of the control cabinet. Inside the launching compartment (201), a negative pressure adsorption assembly for negative pressure adsorption of the projectile support (207) for relaunch is also provided. The controlled end of the negative pressure adsorption assembly is connected to the output end of the control cabinet.

5. The underwater launch simulation experimental system for aircraft according to claim 4, characterized in that: The top of the launch chamber (205) is provided with an interception flange (209) to prevent the sabot from being launched into the water tank along with the test projectile, and the launch port is located at the center of the interception flange (209).

6. The underwater launch simulation experimental system for aircraft according to claim 4, characterized in that: The upper part of the launch cavity (205) extending out of the launch compartment (201) is connected to the pressure relief port (208).

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