Recovery device of underwater launching simulation experiment system of missile aircraft

Abstract

The invention discloses a recovery device of a missile aircraft underwater launching simulation experiment system, which comprises a water tank main body, a recovery cavity is mounted on the top surface in the water tank main body, and a guide mechanism is arranged at a missile inlet in the lower part of the recovery cavity; a limiting mechanism is mounted on the left side wall of the recovery cavity above the bullet inlet of the recovery cavity; a sealing mechanism is mounted in the recycling cavity above the limiting mechanism; a guide-out slide way is arranged on the right side of the recovery cavity; a guide plate is further arranged in the recycling cavity; through cooperation of the guiding mechanism, the limiting mechanism, the sealing mechanism and the guiding-out sliding way, after the head of the aircraft is launched out of the water surface, the missile aircraft can be stably guided into the recycling cavity and guided out of the recycling cavity along the guiding-out sliding way, and a compact, stable and high-reliability recycling system is formed; the efficient, safe and automatic recovery capacity is provided for continuous launching experiments, and the recovery efficiency is improved.

Description

Technical Field

[0001] This invention relates to the field of underwater launch technology for aircraft, and more specifically to a recovery device for an underwater launch simulation experiment system for missile-type aircraft. Background Technology

[0002] Currently, most underwater launch simulation experimental systems for missile-type aircraft adopt a disposable launch structure. After launch, the aircraft moves freely to the bottom of the water tank, requiring water to be drained for recovery, or experimental personnel to go down in waterproof suits to retrieve it. This causes inconvenience for repeated launches. Water drainage or manual retrieval is inefficient, takes a long time, and prolongs the cycle of repeated experiments. Moreover, the water is prone to becoming turbid during the recovery process, affecting the observation of the launch path.

[0003] While some simulation systems possess recovery mechanisms, these are mostly located outside or at the bottom of the water tank. During the launch and water entry process of ballistic missiles, their recovery presents the following problems: 1) Although the trajectory of a ballistic missile remains relatively stable while moving in water due to its high speed and pressure limitations, once the nose of the missile exits the water and contacts the air, the change in medium and the lack of an effective guidance and buffering mechanism above the water surface cause the tail to remain submerged or affected by waves, resulting in attitude disturbances and significant trajectory deviations, sometimes preventing it from entering the recovery channel; 2) In traditional simulation systems, the missile inlet of the recovery tank is usually open during the recovery phase. Once the missile enters the recovery tank, the inlet cannot be closed promptly, easily causing water backflow, clutter interference, and other problems, affecting the observation of continuous launches; 3) An automatic extraction structure is essential after the missile enters the recovery tank. The recovery tank must be removed after continuous launches to recover the missile, resulting in low recovery efficiency.

[0004] Furthermore, the applicant's previous invention patent application, publication number CN120887025A, entitled "An Underwater Launch Simulation Experiment System for Aircraft," disclosed the specific structure of an underwater launch simulation experiment system for aircraft, including 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 bomb inlet of its recovery module is normally open, and there is no corresponding guiding mechanism after the aircraft's nose emerges from the water surface. This fails to address the problem of the aircraft deviating due to changes in the medium during operation. Moreover, the recovered aircraft cannot be directly exported but must be temporarily stored inside the recovery tank. Only after the launch is completed can the entire recovery tank be removed to recover the launched aircraft. Recovery requires manual intervention, resulting in low efficiency. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide a recovery device for an underwater launch simulation experiment system for ballistic aircraft, which can solve the problems mentioned in the background art, such as the inability of the aircraft to stably enter the recovery channel due to changes in the medium during the launch process and the inability to export the recovered aircraft in a timely manner, thereby improving the recovery efficiency.

[0006] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is as follows.

[0007] A recovery device for an underwater launch simulation experiment system for missile-type aircraft includes a water tank body. A recovery chamber is installed on the top surface inside the water tank body. An adjustable guide mechanism is provided at the missile inlet at the lower part of the recovery chamber to guide the missile-type aircraft to the inlet after its nose emerges from the water. During launch, the bottom end of the guide mechanism is positioned above the water surface inside the water tank body and spaced apart from the water surface. A guide mechanism is installed on one side wall of the recovery chamber above the missile inlet to guide the missile-type aircraft as it enters the recovery chamber from the bottom. The system includes a limiting mechanism for restricting the movement of missile-type aircraft; a sealing mechanism for sealing the missile inlet is installed inside the recovery chamber located above the limiting mechanism; a downwardly inclined guide slide is provided on the side wall of the recovery chamber opposite to the limiting mechanism, the lower end of the guide slide penetrates the side wall of the water tank body and communicates with a collection box located on one side of the water tank body; the recovery chamber also includes a guide plate that works with the sealing mechanism to guide the missile-type aircraft to the guide slide, the guide plate is inclined downward, and the lower end of the guide plate is connected to the inlet of the guide slide.

[0008] Preferably, the bottom end face of the guide mechanism is located 0-2 cm above the water surface.

[0009] Preferably, the guiding mechanism includes a fixed outer cylinder and a retractable inner cylinder arranged coaxially. The retractable inner cylinder is slidably disposed inside the fixed outer cylinder. The bottom of the fixed outer cylinder is connected to the retractable inner cylinder by a locking pin. The side wall of the retractable inner cylinder has axially spaced pin holes that are connected to the locking pins. When launched, the distance between the bottom end face of the retractable inner cylinder extending out of the fixed outer cylinder and the water surface is 0-2cm.

[0010] Preferably, the limiting mechanism includes a limiting sleeve disposed on the lower outer side of the recovery chamber, a limiting rod slidably disposed inside the limiting sleeve, one end of the limiting rod penetrating the side wall of the recovery chamber and extending into the recovery chamber, and a limiting spring sleeved on the outside of the limiting rod located inside the limiting sleeve, one end of the limiting spring being connected to the inner end face of the limiting sleeve, and the other end being connected to the limiting rod.

[0011] Preferably, the sealing mechanism includes a cover plate disposed above the inlet of the recovery chamber, the cover plate being inclined downwards, the upper end of the cover plate being hinged to the inner left wall of the recovery chamber via a hinge shaft, the lower end of the cover plate being connected to a partition plate disposed at the bottom of the recovery chamber, the partition plate being parallel to and spaced apart from the left wall of the recovery chamber; a torsion spring is disposed on the hinge shaft connected to the cover plate, one end of the torsion spring being connected to the top of the cover plate, and the other end being connected to the side wall of the recovery chamber.

[0012] Preferably, the guide plate is disposed between the top of the partition plate and the right side wall of the recovery chamber. The guide plate, the cover plate, and the outlet slide have the same inclination angle. The guide plate and the cover plate in the sealed state are on the same inclination surface. The lower end of the guide plate is connected to the bottom wall of the outlet slide inlet.

[0013] Preferably, a buffer pad is provided on the top surface inside the recovery chamber to reduce the impact force when a ballistic aircraft enters the recovery chamber.

[0014] Preferably, the top of the recovery chamber is connected to the main body of the water tank via a shock absorber.

[0015] Due to the adoption of the above technical solutions, the technical progress achieved by this invention is as follows.

[0016] This invention provides a recovery device for an underwater launch simulation experiment system for ballistic missiles. Through the cooperation of a guiding mechanism, a limiting mechanism, a sealing mechanism, and an export slide, the ballistic missile can be stably guided into the recovery chamber after its nose emerges from the water and then exported from the recovery chamber along the export slide, forming a compact, stable, and highly reliable recovery system. This provides efficient, safe, and automated recovery capabilities for continuous launch experiments, thereby improving recovery efficiency.

[0017] This invention utilizes a retractable guiding mechanism to create an extended guiding channel, enabling projectile-type aircraft to quickly enter a stable streamlined path after launch from the water surface. This reduces deflection caused by changes in the medium after launch and ensures stable entry into the recovery chamber. The length of the guiding mechanism can also be adjusted according to the water level, ensuring that the bottom of the retractable inner cylinder maintains a suitable distance from the water surface. This guarantees that the projectile's nose section can stably enter the retractable inner cylinder without deviation after exiting the water. A double-safety structure is formed by a limiting mechanism and a sealing mechanism to prevent the projectile-type aircraft from falling back, and to ensure the inlet is sealed to meet the conditions for continuous launch. Through the sequentially connected and inclined cover plate, guide plate, and exit slide, the projectile automatically slides into the exit slide during descent and exits the water tank body along the slide. The entire recovery process requires no manual intervention, achieving automated recovery of the projectile.

[0018] This invention achieves the entire process of aircraft guidance, limiting, sealing, and recovery through the coordinated operation of purely mechanical structures, without relying on any electrical control components. The overall structure achieves full-process automation through mechanical design, avoiding the complexity and potential failure points of electrical control, and improving the reliability and simplicity of the system. 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 present invention in the launch state of a missile-type aircraft; Figure 3 This is a schematic diagram of the internal structure of the present invention; Figure 4 This is a schematic diagram of the internal structure of the recovery chamber described in this invention; Figure 5 This is a schematic diagram of the specific structure of the guiding mechanism described in this invention.

[0020] The components are as follows: 10. Water tank body, 20. Recovery chamber, 21. Buffer pad, 22. Shock absorber, 23. Guide plate, 30. Guide mechanism, 31. Fixed outer cylinder, 32. Telescopic inner cylinder, 33. Locking pin, 40. Limiting mechanism, 41. Limiting rod, 42. Limiting sleeve, 43. Limiting spring, 50. Sealing mechanism, 51. Cover plate, 52. Torsion spring, 53. Divider plate, 60. Outlet slide. Detailed Implementation

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

[0022] A recovery device for an underwater launch simulation experiment system for ballistic aircraft, such as Figures 1 to 5 As shown, it includes a water tank body 10, and a recovery chamber 20 is installed on the top surface inside the water tank body 10. An adjustable guide mechanism 30 is provided at the missile inlet at the bottom of the recovery chamber 20, which is used to guide the missile after it is launched out of the water surface to ensure that the missile enters the recovery chamber 20 stably without deviating.

[0023] During launch, the bottom end of the guide mechanism is positioned above the water surface inside the main body 10 of the water tank and is spaced apart from the water surface. The bottommost end face of the guide mechanism is 0-2cm above the water surface.

[0024] The upper part of the water tank body 10 is equipped with a transparent plexiglass observation window for recording the process of missile-type aircraft entering the water and being recovered.

[0025] A limiting mechanism 40 is installed on the left side wall of the recovery chamber 20, which is located above the missile inlet of the recovery chamber 20, to limit the missile after it enters the recovery chamber.

[0026] The recovery chamber 20 located above the limiting mechanism 40 is equipped with a sealing mechanism 50 to seal the projectile inlet.

[0027] The right side of the recovery chamber 20 is provided with a downwardly inclined outlet slide 60. The lower end of the outlet slide 60 penetrates the side wall of the water tank body 10 and communicates with the collection box provided on one side of the water tank body 10.

[0028] The recovery chamber 20 is also equipped with a guide plate 23 that works with the sealing mechanism 50 to guide the ballistic aircraft to the exit slide 60. The guide plate 23 is inclined downward and the lower end of the guide plate 23 is connected to the inlet of the exit slide 60.

[0029] A buffer pad 21 is provided on the top surface inside the recovery chamber 20 to reduce the impact force of the ballistic missile entering the recovery chamber and prevent damage to the ballistic missile.

[0030] The top of the recovery chamber 20 is connected to the water tank body 10 via a shock absorber 22. The shock absorber 22 includes a vertical shaft set on the top of the recovery chamber 20 and a shock-absorbing spring sleeved on the outer periphery of the vertical shaft. The top of the vertical shaft passes through the top of the water tank body 10. One end of the shock-absorbing spring is connected to the inner top surface of the water tank body, and the other end is connected to the top surface of the recovery chamber. It is used to buffer the impact force when the missile-type aircraft enters the recovery chamber. Together with the buffer pad, it absorbs the kinetic energy when the missile-type aircraft enters the chamber, preventing damage or rebound of the missile-type aircraft.

[0031] A sealing element is provided between the recovery chamber 20 and the water tank body 10 to ensure the airtightness of the water tank body.

[0032] The guide mechanism 30 includes a fixed outer cylinder 31 and a retractable inner cylinder 32 arranged coaxially. The retractable inner cylinder 32 is slidably disposed inside the fixed outer cylinder 31. The bottom of the fixed outer cylinder 31 is connected to the retractable inner cylinder 32 by a locking pin 33.

[0033] The retractable inner cylinder 32 has axially spaced pin holes that are connected to the locking pins 33 on its side wall for fixing the retractable inner cylinder. By connecting the locking pins to the pin holes at different heights on the retractable inner cylinder, the position of the retractable inner cylinder can be flexibly adjusted according to the water level.

[0034] During launch, the distance between the bottom end of the retractable inner cylinder 32, which extends out of the fixed outer cylinder 31, and the water surface is 0-2cm.

[0035] In the non-launching state, the retractable inner cylinder 32 is connected to the fixed outer cylinder 31 by the locking pin 33 inserted into the lower pin hole and kept in a retracted state to avoid interfering with bomb changing, membrane changing or maintenance operations.

[0036] Before launch, unlock the locking pin 33, slide out the retractable inner cylinder 32, select a suitable pin hole position according to the water level, and connect the locking pin 33 with the pin hole to connect the retractable inner cylinder 32 with the fixed outer cylinder 31 to form an integrated extended guide channel. At this time, the lower end of the retractable inner cylinder 32 is above the water surface, so that after the missile-type aircraft head is launched out of the water, it directly enters the retractable inner cylinder. The guide mechanism applies force to the missile body, which quickly enters a stable streamlined path, reducing the deflection caused by the change of medium during the launch of the aircraft, and providing accurate initial positioning for subsequent limiting and recovery.

[0037] The limiting mechanism 40 includes a limiting sleeve 42 disposed on the lower part of the outer side of the recovery chamber 20. A waterproof sealing ring is provided between the limiting sleeve 42 and the recovery chamber 20. A limiting rod 41 is slidably disposed inside the limiting sleeve 42. The right end of the limiting rod 41 penetrates the side wall of the recovery chamber 20 and extends into the interior of the recovery chamber 20. A limiting spring 43 is sleeved on the outer side of the limiting rod 41 located inside the limiting sleeve 42. One end of the limiting spring 43 is connected to the inner end face of the limiting sleeve 42, and the other end is connected to the limiting rod 41.

[0038] The right end of the limiting rod 41 located inside the recovery chamber 20 is inclined upward. When the ballistic missile enters the recovery chamber, it pushes the limiting rod into the limiting sleeve and compresses the limiting spring 43, ensuring that the ballistic missile enters the recovery chamber stably.

[0039] Once the bottom of the missile-type aircraft has completely entered the recovery chamber, the limiting rod automatically resets under the action of the limiting spring, thus limiting the missile-type aircraft and preventing it from falling into the water tank.

[0040] The sealing mechanism 50 includes a cover plate 51 disposed above the inlet of the recovery chamber 20. The cover plate 51 is inclined downward. The upper end of the cover plate 51 is hinged to the inner wall of the left side of the recovery chamber 20 via a hinge shaft. The lower end of the cover plate 51 is connected to a partition plate 53 disposed at the bottom of the recovery chamber 20. The partition plate 53 is parallel to and spaced apart from the left side wall of the recovery chamber 20.

[0041] Specifically, the lower end of the cover plate 51 overlaps the top surface of the partition plate 53, and a sealing element is provided between the lower end of the cover plate 51 and the top surface of the partition plate. The sealing of the bullet inlet is achieved by the cooperation between the partition plate 53 and the cover plate 51.

[0042] A torsion spring 52 is provided on the hinge shaft connected to the cover plate 51. One end of the torsion spring 52 is connected to the top of the cover plate 51, and the other end is connected to the side wall of the recovery chamber 20. It can push the cover plate open when the missile aircraft moves to the top of the cover plate and drive the cover plate to automatically reset after moving to the top of the cover plate, so as to achieve sealing.

[0043] The guide plate 23 is located between the top of the partition plate 53 and the right side wall of the recovery chamber 20. The guide plate 23, the cover plate 51 and the outlet slide 60 have the same tilt angle. The guide plate 23 and the cover plate 51 in the sealed state are on the same tilt surface. The lower end of the guide plate 23 is connected to the bottom wall of the outlet slide 60 inlet, which can ensure that the ballistic aircraft falls steadily into the outlet slide when it falls, and automatically slides out of the water tank under its own gravity and falls into the collection box outside the water tank body 10.

[0044] The partition plate 53 is attached to the side wall of the outer cylinder 31 to ensure that the missile-type aircraft can rise stably after entering the recovery chamber 20 along the guide mechanism 30 and push the cover plate 51 open.

[0045] The recycling operation of this invention is as follows: After launch, the missile-type aircraft enters the water tank body through the inlet at the bottom of the water tank body. When the nose of the missile-type aircraft emerges from the water surface, due to the limited distance between the bottom of the retractable inner cylinder and the water surface, it can quickly enter the recovery cavity 20 in sequence along the retractable inner cylinder 32 and the fixed outer cylinder 31 in the guide mechanism 30, avoiding the deviation of the aircraft's water exit trajectory due to changes in the medium during the launch process.

[0046] Meanwhile, during the upward movement of the missile-type aircraft, the limiting mechanism 40 and the sealing mechanism 50 are opened in sequence before entering the recovery chamber 20. During the upward movement of the missile-type aircraft into the recovery chamber, the limiting mechanism 40 and the sealing mechanism 50 are automatically reset, thereby limiting the missile-type aircraft and sealing the missile inlet of the recovery chamber.

[0047] After entering the recovery chamber, the ballistic aircraft continues to move until it impacts the buffer pad 21 on top of the recovery chamber. At this point, the kinetic energy of the ballistic aircraft is effectively absorbed and dispersed by the buffer pad. Meanwhile, when the recovery chamber is impacted, the shock absorber reduces the impact force of the ballistic aircraft.

[0048] Afterwards, the missile-type aircraft falls above the cover plate under its own gravity, and enters the discharge slide under the guidance of the guide plate 23. Finally, it slides out of the water tank body along the discharge slide, realizing unattended automatic recovery.

[0049] The opening and resetting operation of the limiting mechanism 40 during the movement of the missile-type aircraft is as follows: During the upward movement of the missile-type aircraft, the limiting rod 41 is gradually pushed into the limiting sleeve 42 and the limiting spring 43 is compressed, ensuring that the missile-type aircraft passes through the missile inlet at the bottom of the recovery chamber 20 and enters the recovery chamber 20. After the bottom of the missile-type aircraft enters the recovery chamber above the limiting mechanism, the pushing force on the limiting rod 41 is released, and the limiting spring 43 drives the limiting rod 41 to automatically reset, preventing the missile-type aircraft from falling.

[0050] The opening and resetting operation of the sealing mechanism 50 during the movement of the missile-type aircraft is as follows: As the missile-type aircraft moves, the cover plate 51 rotates upward around the hinge axis. When the cover plate 51 rotates to a certain angle, under the action of the aircraft's thrust, the cover plate 51 remains in the open state, ensuring that the missile-type aircraft stably enters the recovery chamber. When the bottom of the missile-type aircraft passes the lower end of the cover plate 51 and no longer contacts the cover plate 51, the cover plate 51 rotates downward and resets under the action of the torsion spring 52, sealing the missile inlet.

[0051] This invention provides a recovery device for an underwater launch simulation experiment system for ballistic aircraft. Through the cooperation of a guiding mechanism, a limiting mechanism, a sealing mechanism, and an export slide, the ballistic aircraft can be stably guided into the recovery chamber after launch and exported from the recovery chamber along the export slide, forming a compact, stable, and highly reliable recovery system. This provides efficient, safe, and automated recovery capabilities for continuous launch experiments, thereby improving recovery efficiency.

Claims

1. A recovery device for an underwater launch simulation experiment system for missile-type aircraft, comprising a water tank body (10), wherein a recovery cavity (20) is installed on the top surface inside the water tank body (10), characterized in that: The lower part of the recovery chamber (20) is equipped with a guide mechanism (30) of adjustable length, which guides the missile to the inlet of the recovery chamber (20) after the missile's nose emerges from the water. During launch, the bottom end of the guide mechanism (30) is positioned above the water surface inside the water tank body (10) and spaced apart from the water surface. A limiting mechanism (40) is installed on one side wall of the recovery chamber (20) above the inlet of the recovery chamber (20) to limit the missile after its bottom enters the recovery chamber. The recovery chamber (20) is located above the limiting mechanism (40). The internal structure is equipped with a sealing mechanism (50) to seal the missile inlet; the side wall of the recovery chamber (20) opposite to the limiting mechanism (40) is provided with a downwardly inclined outlet slide (60), the lower end of the outlet slide (60) penetrates the side wall of the water tank body (10) and communicates with the collection box provided on one side of the water tank body (10); the recovery chamber (20) is also provided with a guide plate (23) that cooperates with the sealing mechanism (50) to guide the missile to the outlet slide (60), the guide plate (23) is inclined downward, and the lower end of the guide plate (23) is connected to the inlet of the outlet slide (60).

2. The recovery device of the underwater launch simulation experiment system for missile-type aircraft according to claim 1, characterized in that: The bottom end face of the guide mechanism (30) is located 0-2cm above the water surface.

3. The recovery device for an underwater launch simulation experiment system for missile-type aircraft according to claim 1 or 2, characterized in that: The guiding mechanism (30) includes a fixed outer cylinder (31) and a retractable inner cylinder (32) arranged coaxially. The retractable inner cylinder (32) is slidably disposed inside the fixed outer cylinder (31). The bottom of the fixed outer cylinder (31) is connected to the retractable inner cylinder (32) through a locking pin (33). The side wall of the retractable inner cylinder (32) is provided with pin holes that are axially spaced and connected to the locking pins (33). When launched, the bottom end face of the retractable inner cylinder (32) extending out of the fixed outer cylinder (31) is 0-2 cm away from the water surface.

4. The recovery device of the underwater launch simulation experiment system for missile-type aircraft according to claim 1, characterized in that: The limiting mechanism (40) includes a limiting sleeve (42) disposed on the lower part of the outer side of the recovery cavity (20). A limiting rod (41) is slidably disposed inside the limiting sleeve (42). One end of the limiting rod (41) passes through the side wall of the recovery cavity (20) and extends into the recovery cavity (20). A limiting spring (43) is sleeved on the outer side of the limiting rod (41) located inside the limiting sleeve (42). One end of the limiting spring (43) is connected to the inner end face of the limiting sleeve (42), and the other end is connected to the limiting rod (41).

5. The recovery device of the underwater launch simulation experiment system for missile-type aircraft according to claim 1, characterized in that: The sealing mechanism (50) includes a cover plate (51) disposed above the inlet of the recovery chamber (20). The cover plate (51) is inclined downward. The upper end of the cover plate (51) is hinged to the inner wall of the left side of the recovery chamber (20) via a hinge shaft. The lower end of the cover plate (51) is connected to a partition plate (53) disposed at the bottom of the recovery chamber (20). The partition plate (53) is parallel to and spaced apart from the left side wall of the recovery chamber (20). A torsion spring (52) is disposed on the hinge shaft connected to the cover plate (51). One end of the torsion spring (52) is connected to the top of the cover plate (51), and the other end is connected to the side wall of the recovery chamber (20).

6. The recovery device of the underwater launch simulation experiment system for missile-type aircraft according to claim 5, characterized in that: The guide plate (23) is located between the top of the partition plate (53) and the right side wall of the recovery chamber (20). The guide plate (23), the cover plate (51) and the outlet slide (60) have the same inclination angle. The guide plate (23) and the cover plate (51) in the sealed state are on the same inclination surface. The lower end of the guide plate (23) is connected to the bottom wall of the outlet slide (60) inlet.

7. The recovery device of the underwater launch simulation experiment system for missile-type aircraft according to claim 1, characterized in that: The top surface inside the recovery chamber (20) is provided with a buffer pad (21) to reduce the impact force when a ballistic aircraft enters the recovery chamber.

8. The recovery device of the underwater launch simulation experiment system for missile-type aircraft according to claim 1, characterized in that: The top of the recovery chamber (20) is connected to the water tank body (10) via a shock absorber (22).

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