Multi-load ejection device and method

Abstract

The application provides a multi-load launching device and method. The multi-load launching device comprises a launching barrel assembly, a plurality of projectile assemblies, a projectile blocking mechanism and a projectile lifting mechanism, wherein the plurality of projectile assemblies are arranged in the launching barrel assembly, n (n≥2); the launching barrel assembly comprises a barrel, a projectile supply frame, a phase change power device and n-1 projectile locking mechanisms; the projectile blocking mechanism is arranged on the barrel and elastically contacts the front end of the first projectile assembly; the projectile locking mechanisms elastically contact the rear ends of the first to the n-1th projectile assemblies respectively; one end of the projectile lifting mechanism is connected to the barrel, and the other end of the projectile lifting mechanism is drivingly connected to the nth projectile assembly; a power cavity is formed between the first and the second projectile assemblies, and the phase change power device is connected to the power cavity. The application can realize the cold multi-load launching device of continuous multi-load in the same launching barrel, and has compact structure and safe and reliable use.

Description

Technical Field

[0001] This invention relates to the field of cold ejection technology, and more particularly to a multi-load ejection device and method. Background Technology

[0002] Existing multi-load ejection systems generally consist of a launch tube and a projectile housed within it. The launch tube launches the projectile using either hot launch or cold ejection methods. Hot launch utilizes the projectile's own rocket engine, ignited within the launch tube, to directly provide thrust. However, the high-temperature, high-pressure gases generated during this process return to the launch device and platform, causing severe ablation and impact loads, threatening the reusability and safety of the system. Cold ejection, on the other hand, involves sealing the bottom of the projectile and using a relatively low-temperature ejection propulsion system to propel it out of the launch tube.

[0003] Existing cold multi-load ejection devices, such as the cold ejection system based on CO2 liquid-gas phase change disclosed in patent publication number CN219172674U, trigger an instantaneous phase change of liquid CO2 through an initiator to generate high-pressure gas, which then pushes a piston to achieve ejection after breaking through a pressure plate. However, this system integrates the heavy gas generator and other power components with the ejection tube into a single structure, adopting a "one tube, one ejection" design. While this meets the convenience requirements of individual soldiers, it is difficult to extend its application to high-density, high-load launch scenarios. Summary of the Invention

[0004] The purpose of this invention is to provide a multi-load ejection device and method, which can realize a cold multi-load ejection device that can continuously carry out multiple loads in the same launch tube. It has a compact structure and is safe and reliable to use.

[0005] The technical solution of the present invention is: a multi-load ejection device, comprising a launch tube assembly, a projectile assembly, a projectile-stopping mechanism, and a projectile-loading mechanism disposed inside the launch tube assembly. The projectile assemblies are arranged in n units within the launch tube assembly, where n ≥ 2. The launch tube assembly includes a cylinder, a feeding frame connected to one end of the cylinder, a phase-change power device arranged circumferentially on the cylinder, and n-1 locking mechanisms disposed on the feeding frame. The projectile-stopping mechanism is disposed on the cylinder and elastically contacts the front end of the first projectile assembly. The locking mechanisms elastically contact the rear ends of the first to (n-1)th projectile assemblies. One end of the projectile-loading mechanism is connected to the cylinder, and the other end is drivenly connected to the nth projectile assembly. A power cavity is formed between the first and second projectile assemblies, and the phase-change power device is connected to the power cavity.

[0006] Preferably, the cartridge locking mechanism includes a stop block and a cartridge carrier lock. The cartridge carrier lock is mounted on the cartridge feeding frame. One end of the stop block is hinged to the cartridge carrier lock via a first rotating shaft. The other end of the stop block is provided with a one-way locking tooth that can contact the cartridge assembly. A reset member is fitted on the first rotating shaft. The reset member is used to apply force to the stop block so that the one-way locking tooth contacts n-1 cartridge assemblies. The driving force applied to the cartridge assembly by the loading mechanism is greater than the force applied to the stop block by the reset member.

[0007] Preferably, the bullet-stopping mechanism includes a base, a locking block, a locking tongue, and a driving mechanism. The base is mounted on the cylinder. One end of the locking block is hinged to the base via a second pivot, and the other end of the locking block forms a locking plate. The locking block has a locking block that contacts the bullet assembly. A first spring is connected between the locking block and the base. The first spring is located on the opposite side of the locking block. The driving mechanism is located beside the base. The power output end of the driving mechanism is connected to the locking tongue. The driving mechanism is used to drive the locking tongue to contact or move away from the locking plate.

[0008] Preferably, one end of the latch is provided with a bearing adapted to the lock plate, and the other end of the latch is provided with a mounting cavity. The power output end of the drive mechanism extends into the mounting cavity and is connected to the latch through a second spring.

[0009] Preferably, the projectile assembly includes a projectile, an adapter is fitted at the front end of the projectile, a sabot is fitted at the rear end of the projectile, the anti-ballistic mechanism contacts the front end of the adapter, and the locking mechanism contacts the rear end of the sabot.

[0010] Preferably, the adapter is provided with guide groove 1 and guide groove 2 opposite to each other, and the sabot is provided with guide groove 3 and guide groove 4 opposite to each other. Guide groove 1, guide groove 2, guide groove 3 and guide groove 4 all pass through the axial direction of the projectile assembly. The launch tube assembly is provided with two guide rails arranged opposite to each other. Guide groove 1 and guide groove 4 are adapted to one of the guide rails, and guide groove 2 and guide groove 3 are adapted to the other guide rail.

[0011] Preferably, the sabot includes a disc and two clamping plates vertically connected to the disc. The guide groove three and guide groove four are respectively disposed on the two clamping plates. A clamping hole is opened in the middle of the disc, and the projectile head of the rear projectile assembly is clamped in the clamping hole at the front end.

[0012] Preferably, the adapter includes a first retaining ring and a second and a third retaining ring connected to the same end of the first retaining ring. The second retaining ring extends horizontally from the first retaining ring, and the third retaining ring extends obliquely toward the axis of the projectile. The first retaining ring is fitted onto the projectile, and the third retaining ring is fitted onto the projectile head. The second retaining ring is in contact with the anti-ballistic mechanism. The guide groove three and guide groove four are both provided on the first and second retaining rings.

[0013] The present invention also provides a method for launching using the above-described multi-load ejection device, comprising:

[0014] Step 1: The first projectile assembly in the launch tube assembly is located in the launch position. The projectile blocking mechanism is locked to the front end of the first projectile assembly, and the projectile locking mechanism is locked to the rear end of the first to (n-1)th projectile assemblies. The rear end of the nth projectile assembly is in contact with the loading mechanism.

[0015] Step 2: Activate the phase change power device, heat the liquid carbon dioxide inside to cause it to undergo a phase change, and generate high-pressure gas in the power chamber to push the first projectile assembly to overcome the locking force of the anti-ballistic mechanism and be launched from the cylinder.

[0016] Step 3: Activate the loading mechanism, which drives n-1 projectile assemblies to overcome the locking force of the locking mechanism and move them forward, thereby pushing the second projectile assembly forward to the launch position;

[0017] Repeat the above steps until the second projectile assembly is launched, and then repeat the above steps until all projectile assemblies have been launched.

[0018] Compared with related technologies, the beneficial effects of the present invention are as follows:

[0019] I. This invention optimizes the structure of the launch tube assembly and gives it a projectile blocking mechanism, a projectile locking mechanism, and a projectile loading mechanism. It can place multiple projectile assemblies in the launch tube assembly and automatically load them, realizing continuous multi-load cold ejection in the same launch tube, and can be applied to high-density, high-load launch scenarios.

[0020] 2. The present invention provides a locking mechanism with elastic contact at the tail of the projectile assembly, which provides better recoil force, and the recoil force is buffered and supported by elastic force.

[0021] Third, this invention uses liquid-gas phase change as a power source, which has the advantages of being non-toxic and pollution-free, fire-free and safe, with low impact overload, no need for thermal protection, and safe and reliable use. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the structure of the multi-load ejection device provided by the present invention;

[0023] Figure 2This is a schematic diagram of the launch tube assembly;

[0024] Figure 3 This is a schematic diagram of the locking mechanism;

[0025] Figure 4 A schematic diagram showing the installation of the three projectile components;

[0026] Figure 5 This is a schematic diagram of the adapter's structure;

[0027] Figure 6 This is a schematic diagram of the sabot structure;

[0028] Figure 7 A schematic diagram of the internal structure of the multi-load ejection device provided by the present invention;

[0029] Figure 8 for Figure 7 A partially enlarged schematic diagram of the first projectile component;

[0030] Figure 9 for Figure 7 A partially enlarged schematic diagram of the nth projectile component;

[0031] Figure 10 This is a schematic diagram of the bullet-stopping mechanism;

[0032] Figure 11 This is a schematic diagram of the internal structure of the loading mechanism.

[0033] In the attached diagram: 1. Launch tube assembly; 10. Phase change power device; 11. Tube body; 12. Mounting base; 13. Phase change tube; 14. Logging mechanism; 141. Stop block; 1411. One-way locking tooth; 142. Spearstock lock; 143. Reset component; 144. First rotating shaft; 16. Feed frame; 17. Guide rail; 2. Projectile assembly; 20. Projectile body; 200. Power chamber; 21. Adapter; 211. First retaining ring; 212. Second retaining ring; 213. Guide groove one; 214. Guide groove two; 215. Third retaining ring; 22. Spring support; 221. Disc; 222. Guide groove three; 223. Guide groove four; 224. Clamping plate; 225. Clamping hole; 226. Rib plate; 3. Bullet-stopping mechanism; 31. Base; 32. Locking block; 321. Locking block; 322. Locking plate; 33. Lock tongue; 331. Bearing; 332. Mounting cavity; 34. Drive mechanism; 35. First spring; 36. Second spring; 37. Second rotating shaft; 4. Spring feeding mechanism; 41. Chain box; 42. Feed chain; 43. Motor; 44. Tail top; 45. Gear set. Detailed Implementation

[0034] The present invention will now be described in detail with reference to the accompanying drawings and embodiments. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other. For ease of description, the terms "upper," "lower," "left," and "right" used below only indicate that they correspond to the upper, lower, left, and right directions in the accompanying drawings and do not limit the structure.

[0035] like Figure 1 As shown, the multi-load ejection device provided in this embodiment includes a launch tube assembly 1, a projectile assembly 2, a projectile blocking mechanism 3, and a projectile loading mechanism 4.

[0036] like Figure 1 , Figure 2 As shown, the launch tube assembly 1 includes a phase change power device 10, a tube body 11, a projectile locking mechanism 14, a projectile feeding frame 16, and a guide rail 17. The front end of the tube body 11 is the launch port, and the rear end of the tube body 11 is connected to the projectile feeding frame 16. The tube body 11 is the core structure for bearing, guiding, and launching the projectiles. It is a multi-load container capable of accommodating and sequentially arranging n projectile assemblies 2; in this embodiment, n=3. The tube body 11 can be made of composite materials such as fiberglass to reduce the overall weight. The projectile feeding frame 16 provides storage support for the projectile assemblies 2. The projectile feeding frame 16 can be made of high-strength and high-rigidity titanium alloy to ensure structural reliability.

[0037] The cylindrical body 11 is equipped with a projectile-catching mechanism 3 and a phase-change power device 10. The projectile-catching mechanism 3 is located near the launch port and is used to contact the front end of the first projectile assembly 2. The phase-change power device 10 is arranged in four groups in a circular pattern. Each group has three phase-change tubes 13, which are mounted on the outer wall of the cylindrical body 11 via mounting bases 12. The phase-change power device 10 is suitable for generating high-pressure phase-change gas mixtures; the specific principle is existing technology and will not be elaborated here. The launch tube assembly 1 has two guide rails 17 inside, with one guide rail 17 being wider than the other.

[0038] The locking mechanism 14 is mounted on the feeding frame 16 and abuts against the rear ends of the first and (n-1)th projectile assemblies 2, providing recoil force during launch. Figure 2 , Figure 3As shown, the cartridge locking mechanism 14 includes a stop block 141 and a cartridge carrier lock 142. The cartridge carrier lock 142 is mounted on the feeding frame 16. One end of the stop block 141 is hinged to the cartridge carrier lock 142 via a first rotating shaft 144. The other end of the stop block 141 is provided with a one-way locking tooth 1411 that can contact the cartridge assembly 2. A reset member 143 is fitted on the first rotating shaft 144. The reset member 143 is a torsion spring. One end of the torsion spring abuts against the cartridge carrier lock 142, and the other end of the torsion spring abuts against the stop block 141. The reset member 143 is used to apply force to the stop block 141 so that the one-way locking tooth 1411 abuts against the tail of the cartridge assembly 2 to provide recoil force and achieve buffer support. The side of the one-way locking tooth 1411 facing the direction of movement of the cartridge assembly 2 is an arc surface. To avoid scratching the projectile assembly 2, a buffer pad (not shown) is provided on the outer surface of the one-way locking tooth 1411 that abuts against the sabot 22.

[0039] like Figure 4 As shown, the projectile assembly 2 includes a projectile 20, with an adapter 21 fitted at the front end of the projectile 20 and a sabot 22 fitted at the rear end of the projectile 20. Figure 2 , Figure 5 As shown, the adapter 21 includes a first retaining ring 211 and a second retaining ring 212 and a third retaining ring 215 connected to the same end of the first retaining ring 211. Figure 7 As shown, the second retaining ring 212 extends horizontally from the first retaining ring 211, and the third retaining ring 215 extends obliquely towards the axis of the projectile 20. The first retaining ring 211, the second retaining ring 212, and the third retaining ring 215 are connected to form a horizontal "Y" shape. The first retaining ring 211 is fitted onto the projectile 20, the third retaining ring 215 is fitted onto the projectile head of the projectile 20, and the second retaining ring 212 contacts the locking block 32 of the anti-ballistic mechanism 3.

[0040] like Figure 5 As shown, both the first retaining ring 211 and the second retaining ring 212 are provided with a guide groove 213 and a guide groove 214 that extend through the axial direction. The width of the guide groove 213 is greater than the width of the guide groove 214.

[0041] like Figure 4 , Figure 6As shown, the sabot 22 includes a disc 221 and two clamping plates 224 vertically connected to the disc 221. The clamping plates 224 are engaged with the tail end of the projectile 20. One clamping plate 224 has an axially penetrating guide groove 3 222, and the other clamping plate 224 has an axially penetrating guide groove 4 223. The width of the guide groove 3 222 is smaller than the width of the guide groove 4 223. A rib 226 is provided on the surface of the disc 221 away from the projectile 20, and a locking hole 225 is formed at the center of the disc 221, into which the projectile head of the rear projectile assembly 2 is engaged. A power cavity 200 is formed between the first projectile assembly 2 and the second projectile assembly 2, and the phase change power device 10 is connected to the power cavity 200. Figure 9 As shown, the one-way locking tooth 1411 abuts against the rear surface of the disc 221 of the sabot 22.

[0042] like Figure 2 , Figure 5 , Figure 6 As shown, guide groove 1 213 and guide groove 4 223 are both adapted to the guide rail 17 with a large width dimension, and guide groove 2 214 and guide groove 3 222 are both adapted to the guide rail 17 with a small width dimension.

[0043] like Figure 7 , Figure 8 , Figure 10 As shown, the projectile-stopping mechanism 3 includes a base 31, a locking block 32, a locking tongue 33, and a driving mechanism 34. The base 31 is mounted on the cylinder 11. One end of the locking block 32 is hinged to the base 31 via a second pivot 37, and the other end of the locking block 32 forms a locking plate 322. The locking block 32 has a locking block 321 that contacts the second retaining ring 212 of the projectile assembly 2. The locking block 321 has an inclined surface on the side facing the projectile assembly 2, and the bottom of the locking block 321 has an arc connected to the inclined surface. When the projectile assembly 2 is launched, the second retaining ring 212 pushes the locking block 32 into the base 31 along the inclined surface, thereby unlocking the projectile-stopping mechanism 3.

[0044] A first spring 35 is connected between the locking block 32 and the base 31. The first spring 35 is located on the opposite side of the locking block 321. The first spring 35 pushes out the locking block 32 to keep it in the locked position.

[0045] The drive mechanism 34 (optionally an electric lead screw) is located beside the base 31. The power output end of the drive mechanism 34 is connected to the latch 33, and the drive mechanism 34 is used to drive the latch 33 to contact or move away from the lock plate 322. One end of the latch 33 is provided with a bearing 331 adapted to the lock plate 322 (to better realize the sliding of the latch 33), and the other end of the latch 33 is provided with a mounting cavity 332. The power output end of the drive mechanism 34 extends into the mounting cavity 332 and is connected to the latch 33 through the second spring 36. When the drive mechanism 34 drives the latch 33 to retract, the locking force of the locking block 32 is released, and the movement of the spring assembly 2 can open the locking block 32, causing the first spring 35 to retract. When the projectile assembly 2 finishes moving, the first spring 35 returns to its original position, the locking block 32 extends from the side wall of the base 31 and the cylinder 11 into the cylinder 11, the drive mechanism 34 drives the locking tongue 33 to extend, the bearing 331 abuts against the locking plate 322 again to lock the locking block 32, and the locking block 32 abuts against the second retaining ring 212 to achieve locking.

[0046] like Figure 1 , Figure 11 As shown, the launching tube assembly 1 is equipped with a loading mechanism 4. The loading mechanism 4 includes a chain box 41, a feeding chain 42, a motor 43, a tail fin 44, and a gear set 45. One end of the chain box 41 is connected to the tube body 11, and the feeding chain 42 is disposed in the chain box 41. The motor 43 is mounted on the chain box 41, and the motor 43 is connected to the power input end of the gear set 45. The power output end of the gear set 45 is connected to the feeding chain 42. The power output end of the feeding chain 42 is connected to the tail fin 44. The tail fin 44 contacts the nth projectile assembly 2.

[0047] The rotational motion of the motor 43 is converted into linear motion of the projectile assembly 2 driven by the feed chain 42. The feed chains 42 mesh with each other, forming a rectangular cross-section. A rectangular base is provided at the power output end of each feed chain 42. This rectangular base acts on the lower surface of the tail tip 44 to push the projectile assembly 2 along the axial direction of the cylinder 11. The motor 43 can rotate in both directions. The working principle of the feed chain 42 of the loading mechanism 4 is the same as that of CN222745165U.

[0048] The loading mechanism 4 is used to drive the projectile assembly 2 to move along the guide rail 17. The guide rail 17 plays a guiding role to prevent the projectile assembly 2 from deflecting or changing its attitude during the forward movement, and to ensure the axial positioning accuracy of the projectile 20 before ejection.

[0049] The present invention also provides a method for launching using the above-described multi-load ejection device, comprising:

[0050] Step 1: The first projectile assembly 2 within the launch tube assembly 1 is positioned at the launch location. The projectile-stopping mechanism 3 is locked to the adapter 21 of the first projectile assembly 2, and the projectile-locking mechanism 14 is locked to the sabot 22 of the first and second projectile assemblies 2. The sabot 22 of the third projectile assembly 2 contacts the tail tip 44. A power chamber 200 is formed between the first and second projectile assemblies 2.

[0051] Step two: Activate the drive mechanism 34 to retract the locking tongue 33. Activate the phase change power device 10, heating the liquid carbon dioxide inside to cause a phase change and release high-pressure gas into the power chamber 200. This high-pressure gas acts on the sabot 22 of the first projectile assembly 2, pushing the first projectile assembly 2 to open the locking block 32 and launch from the cylinder 11. At this time, the one-way locking tooth 1411 provides recoil force. After the first projectile assembly 2 is launched, under the action of the first spring 35, the locking block 32 returns to its original position. Activate the drive mechanism 34 to extend the locking tongue 33, causing the bearing 331 to press the locking block 32.

[0052] Step 3: Activate the loading mechanism 4, driving the second and third projectile assemblies 2 forward. During this forward movement, the one-way locking teeth 1411 retract against the spring force of the reset member 143. Once each projectile assembly 2 is in position, under the action of the reset member 143, the one-way locking teeth 1411 extend and abut against the sabot 22 of the corresponding projectile assembly 2. At this point, the second projectile assembly 2 is pushed forward to the firing position.

[0053] Repeat the above steps until the second projectile assembly 2 is launched. Then repeat the above steps until all projectile assemblies 2 have been launched.

[0054] The above description is merely an embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural or procedural transformations made based on the content of the present invention's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of the present invention.

Claims

1. A multi-load ejection device, comprising a launch tube assembly (1) and a projectile assembly (2), characterized in that, It also includes a ballistic blocking mechanism (3) and a loading mechanism (4) located inside the launch tube assembly (1). The projectile assembly (2) has n units arranged inside the launch tube assembly (1), where n ≥ 2. The launch tube assembly (1) includes a tube body (11), a feeding frame (16) connected to one end of the tube body (11), a phase change power device (10) arranged circumferentially on the tube body (11), and n-1 locking mechanisms (14) located on the feeding frame (16). The ballistic blocking mechanism (3) is located on the tube body (11) and elastically contacts the front end of the first projectile assembly (2). The locking mechanism (14) is in elastic contact with the rear end of the first to n-1th projectile assembly (2); one end of the loading mechanism (4) is connected to the cylinder (11), and the other end of the loading mechanism (4) is driven to the nth projectile assembly (2); a power cavity (200) is formed between the first projectile assembly (2) and the second projectile assembly (2), and the phase change power device (10) is connected to the power cavity (200); the locking mechanism (14) includes a stop (141) and a cartridge lock (142), and the cartridge lock (142) is installed on the feeding frame (16).

2. The multi-load ejection device according to claim 1, characterized in that, One end of the stop block (141) is hinged to the cartridge lock (142) via the first rotating shaft (144). The other end of the stop block (141) is provided with a one-way locking tooth (1411) that can contact the projectile assembly (2). A reset member (143) is fitted on the first rotating shaft (144). The reset member (143) is used to apply force to the stop block (141) so that the one-way locking tooth (1411) contacts n-1 projectile assemblies (2). The driving force applied by the loading mechanism (4) to the projectile assembly (2) is greater than the force applied by the reset member (143) to the stop block (141).

3. The multi-load ejection device according to claim 1, characterized in that, The bullet-stopping mechanism (3) includes a base (31), a locking block (32), a locking tongue (33), and a driving mechanism (34). The base (31) is mounted on the cylinder (11). One end of the locking block (32) is hinged to the base (31) via a second pivot (37). The other end of the locking block (32) forms a locking plate (322). The locking block (32) is provided with a locking block (321) that contacts the bullet assembly (2). A first spring (35) is connected between the locking block (32) and the base (31). The first spring (35) is located on the opposite side of the locking block (321). The driving mechanism (34) is located on the side of the base (31). The power output end of the driving mechanism (34) is connected to the locking tongue (33). The driving mechanism (34) is used to drive the locking tongue (33) to contact or move away from the locking plate (322).

4. The multi-load ejection device according to claim 3, characterized in that, One end of the latch (33) is provided with a bearing (331) adapted to the lock plate (322), and the other end of the latch (33) is provided with a mounting cavity (332). The power output end of the drive mechanism (34) extends into the mounting cavity (332) and is connected to the latch (33) through a second spring (36).

5. The multi-load ejection device according to claim 1, characterized in that, The projectile assembly (2) includes a projectile (20), an adapter (21) is fitted at the front end of the projectile (20), a sabot (22) is fitted at the rear end of the projectile (20), the anti-ballistic mechanism (3) contacts the front end of the adapter (21), and the locking mechanism (14) contacts the rear end of the sabot (22).

6. The multi-load ejection device according to claim 5, characterized in that, The adapter (21) is provided with guide groove 1 (213) and guide groove 2 (214) opposite to each other, and the sabot (22) is provided with guide groove 3 (222) and guide groove 4 (223) opposite to each other. The guide groove 1 (213), guide groove 2 (214), guide groove 3 (222) and guide groove 4 (223) all pass through the axial direction of the projectile assembly (2). The launch tube assembly (1) is provided with two guide rails (17) arranged opposite to each other. The guide groove 1 (213) and guide groove 4 (223) are adapted to one of the guide rails (17), and the guide groove 2 (214) and guide groove 3 (222) are adapted to the other guide rail (17).

7. The multi-load ejection device according to claim 6, characterized in that, The sabot (22) includes a disc (221) and two clamping plates (224) vertically connected to the disc (221). The guide groove three (222) and guide groove four (223) are respectively disposed on the two clamping plates (224). A clamping hole (225) is provided in the middle of the disc (221), and the projectile head of the rear projectile assembly (2) is clamped in the clamping hole (225) at the front end.

8. The multi-load ejection device according to claim 6, characterized in that, The adapter (21) includes a first retaining ring (211) and a second retaining ring (212) and a third retaining ring (215) connected to the same end of the first retaining ring (211). The second retaining ring (212) extends horizontally from the first retaining ring (211), and the third retaining ring (215) extends obliquely toward the axis of the projectile (20). The first retaining ring (211) is fitted onto the projectile (20), and the third retaining ring (215) is fitted onto the head of the projectile (20). The second retaining ring (212) is in contact with the anti-ballistic mechanism (3). The guide groove three (222) and the guide groove four (223) are both provided on the first retaining ring (211) and the second retaining ring (212).

9. A method for launching objects using a multi-load ejection device as described in any one of claims 1-8, characterized in that, include: Step 1: The first projectile assembly (2) in the launch tube assembly (1) is located in the launch position. The anti-ballistic mechanism (3) is locked on the front end of the first projectile assembly (2), and the locking mechanism (14) is locked on the rear end of the first to n-1 projectile assemblies (2). The rear end of the nth projectile assembly (2) is in contact with the loading mechanism (4). Step 2: Start the phase change power device (10), heat the liquid carbon dioxide inside to cause it to undergo phase change and generate high pressure gas in the power chamber (200) to push the first projectile assembly (2) to overcome the locking force of the anti-ballistic mechanism (3) and be emitted from the cylinder (11); Step 3: Activate the loading mechanism (4) to drive n-1 projectile assemblies (2) to overcome the locking force of the locking mechanism (14) and move them to the front end, thereby pushing the second projectile assembly (2) forward to the launch position; Repeat the above steps until the second projectile assembly (2) is launched, and then repeat the above steps until all projectile assemblies (2) are launched.

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