Rocket separation cylinder

Abstract

The utility model relates to the technical field of aerospace rocket separation, in particular to a rocket separation cylinder, which is characterized by comprising a cylinder barrel, the piston rod is arranged in the cylinder barrel and can do relative linear motion in the cylinder barrel; the cover body assembly comprises a first end cover, a middle cover body and a second end cover which are coaxially arranged, the first end cover and the second end cover are fixed to the two ends of the cylinder barrel respectively, the middle cover body partitions the cylinder barrel, and the piston rod penetrates through the centers of the first end cover, the middle cover body and the second end cover in the axis direction; the buffering mechanism comprises a limiting block, a connecting rod and a buffering block, one face of the second end cover is fixed to the first-stage rocket body housing, the top end of the piston rod extends out of the first end cover and makes contact with the second-stage rocket body housing, and after the piston rod moves to the preset stroke, the second-stage rocket body is disengaged. And the rocket separation air cylinder is arranged, so that the manufacturing cost of the aerospace industry is reduced, and the environment-friendly benefit is achieved while the stable separation action is ensured.

Description

Technical Field

[0001] The utility model relates to the technical field of aerospace rocket separation, in particular to a rocket separation cylinder. Background Art

[0002] After the rocket is launched, as the fuel in the first stage is exhausted, it needs to separate from the second stage, and after separation, the first stage falls back to the ground;

[0003] In the related art, the first-stage arrow body and the second-stage arrow body are separated from each other by disconnecting the connecting rod of the first-stage arrow body and the second-stage arrow body through gunpowder explosion.

[0004] However, in the above-mentioned separation method, gunpowder has certain instability and danger. If an accident occurs during operation or transportation, it may cause a serious accident. In addition, gunpowder is a military product, and its procurement and use are subject to strict control and restrictions, resulting in long delivery time and high cost. In addition, gunpowder is a disposable consumable. During the rocket separation process, gunpowder cannot be recycled after burning, which is contrary to the concept of sustainable development advocated by the modern aerospace industry. At the same time, the strong impact force generated by the explosion may damage other parts of the rocket, especially nearby sensitive equipment. This impact may not only affect the structural integrity of the rocket, but also interfere with the subsequent movement trajectory of the secondary rocket body. Utility Model Content

[0005] In view of at least one of the above technical problems, the utility model provides a rocket separation cylinder, which adopts the addition of a rocket separation cylinder device to achieve the separation between rocket stages.

[0006] According to a first aspect of the utility model, a rocket separation cylinder is provided, comprising:

[0007] Cylinder barrel;

[0008] A piston rod is disposed in the cylinder and can perform relative linear motion in the cylinder;

[0009] A cover assembly comprises a first end cover, an intermediate cover and a second end cover which are coaxially arranged, wherein the first end cover and the second end cover are respectively fixed to the two ends of the cylinder barrel, the intermediate cover body separates the cylinder barrel, the first end cover and the intermediate cover body seal the cylinder barrel to form a short cavity, wherein there is compressible gas in the short cavity, the intermediate cover body and the second end cover seal the cylinder barrel to form a long cavity, and the piston rod passes through the centers of the first end cover, the intermediate cover body and the second end cover along the axial direction;

[0010] The buffer mechanism comprises a limit block, a connecting rod and a buffer block, wherein the connecting rod is arranged between the intermediate cover body and the piston rod so as to be capable of relatively linear motion, one end of the connecting rod is fixed to the limit block, the limit block is arranged in the long cavity, and the other end of the connecting rod is fixed to the buffer block, the buffer block is arranged in the short cavity;

[0011] Among them, one side of the second end cover is fixed to the first-stage arrow body cover, the top end of the piston rod extends out of the first end cover and contacts the second-stage arrow body cover, and when the piston rod moves to a predetermined stroke, the second-stage arrow body is detached.

[0012] In some embodiments of the present invention, the buffer mechanism further includes a buffer spring, one end of the buffer spring is fixed to the buffer block, and the other end of the buffer spring is fixed to the first end cover.

[0013] In some embodiments of the present utility model, the inner diameter of the middle cover body is larger than the outer diameter of the piston rod, and the connecting rod is a hollow structure and is sleeved on the piston rod.

[0014] In some embodiments of the present invention, the cover body assembly also includes multiple tie rods, the outer diameters of the first end cover, the middle cover body and the second end cover are larger than the outer diameters of the cylinder, and a plurality of connecting holes are arranged at the outer edges of the first end cover, the middle cover body and the second end cover, and the connecting holes and the tie rods are connected and fixed to the cylinder and the cover body assembly through interference fit.

[0015] In some embodiments of the present invention, the cover assembly further comprises a plurality of struts, one end of each strut is connected to the cover shell of the first-stage arrow body, and the other end of each strut is connected to the first end cover.

[0016] In some embodiments of the utility model, a plurality of mounting holes are further provided on the second end cover, and the rocket separation cylinder is fixed to the first-stage rocket body cover through the mounting holes.

[0017] In some embodiments of the utility model, a piston adapted to the cross-section of the long cavity is provided on the bottom end of the piston rod, and a connecting component is provided on the top end of the piston rod, and the connecting component is used to contact with the secondary arrow body.

[0018] In some embodiments of the present invention, the middle cover body and the second end cover are provided with a plurality of reserved openings.

[0019] In some embodiments of the present invention, the reserved opening includes an exhaust port on the middle cover body and a vent port on the second end cover.

[0020] In some embodiments of the present invention, a pressure sensor and a temperature sensor are also included.

[0021] The beneficial effects of the utility model are as follows: the utility model avoids the safety risks caused by gunpowder explosion and improves the safety during the application process by adopting cylinders instead of traditional gunpowder to achieve separation between rocket stages; the cylinder system can provide precise control to ensure the smoothness of the separation action; the manufacturing cost of the cylinder is much lower than that of gunpowder, and the use of cylinders reduces production costs and can better adapt to social needs; the application of cylinders can also be reused, which has significant economic benefits and is more environmentally friendly. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0023] Figure 1 This is a schematic diagram of the structure of the rocket separation cylinder in the embodiment of the utility model;

[0024] Figure 2 This is a schematic diagram of the structure of the buffer mechanism in the embodiment of the utility model when it is not squeezed;

[0025] Figure 3 This is a schematic diagram of the structure of the buffer mechanism when it is squeezed in the embodiment of the utility model;

[0026] Figure 4 This is a schematic diagram of the structure of the first end cover in the embodiment of the utility model;

[0027] Figure 5 This is a schematic diagram of the structure of the middle cover body in the embodiment of the utility model;

[0028] Figure 6 It is a schematic structural diagram of the second end cover in an embodiment of the utility model. DETAILED DESCRIPTION

[0029] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments.

[0030] It should be noted that when an element is referred to as being "fixed to" another element, it may be directly on the other element or there may be a central element. When an element is considered to be "connected to" another element, it may be directly connected to the other element or there may be a central element at the same time. The terms "vertical", "horizontal", "left", "right" and similar expressions used herein are for illustrative purposes only and do not represent the only implementation method.

[0031] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art in the technical field of the present invention. The terms used in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. The term "and / or" used herein includes any and all combinations of one or more related listed items.

[0032] like Figures 1 to 6 The rocket separation cylinder shown includes: a cylinder barrel 1, a piston rod 2, a cover assembly 3 and a buffer mechanism 4. The piston rod 2 is arranged in the cylinder barrel 1 and can make relative linear motion in the cylinder barrel 1; the cover assembly 3 includes a first end cover 31, an intermediate cover body 32 and a second end cover 33 arranged coaxially, the first end cover 31 and the second end cover 33 are respectively fixed to the two ends of the cylinder barrel 1, the intermediate cover body 32 separates the cylinder barrel 1, the first end cover 31 and the intermediate cover body 32 seal the cylinder barrel 1 to form a short chamber 3A, there is compressible gas 3A1 in the short chamber 3A, the intermediate cover body 32 and the second end cover 33 seal the cylinder barrel 1 to form a long chamber 3B, the piston rod 2 passes through the center of the first end cover 31, the intermediate cover body 32 and the second end cover 33 along the axial direction; the buffer mechanism 4 includes a limit block 41, a connecting rod 42 and a buffer block 43, the connecting rod 42 is a hollow tube and is sleeved on the piston rod 2. The connecting rod 42 can be arranged between the middle cover body 32 and the piston rod 2 to make relative linear motion and can slide axially relative to the piston rod 2. One end of the connecting rod 42 is fixed to the limit block 41, and the limit block 41 is arranged in the long cavity 3B. The other end of the connecting rod 42 is fixed to the buffer block 43, and the buffer block 43 is arranged in the short cavity 3A. The other end of the buffer block 43 is fixed to the buffer spring 44, and the other end of the buffer spring 44 is fixed to the first end cover 31. Among them, one side of the second end cover 33 is fixed to the first-stage arrow body cover, and the top end of the piston rod 2 extends out of the first end cover 31 and contacts with the second-stage arrow body cover. When the piston rod 2 moves to a predetermined stroke, the second-stage arrow body is detached. Figure 1As shown, the cylinder 1, the piston rod 2 and the cover assembly 3 form a closed cylinder structure, and the middle cover 32 separates the entire cylinder 1 into two independent spaces. The setting of the middle cover 32 limits the movement of the piston 21, and prevents the piston rod 2 from being separated from the cylinder 1 due to the impact of the piston rod 2 moving too fast; a short cavity 3A is formed between the first end cover 31 and the middle cover 32, and a long cavity 3B is formed between the middle cover 32 and the second end cover 33. The limit block 41 connected to one end of the connecting rod 42 in the buffer mechanism 4 is set in the long cavity 3B and is adapted to the cross section of the long cavity 3B, and the buffer block 43 connected to the other end of the connecting rod 42 is set in the short cavity 3A and is adapted to the cross section of the short cavity 3A. In the initial state, the second end cover 33 fixes the bottom of the cylinder 1 to the primary arrow body cover, the piston rod 2 has a zero stroke, the top of the piston rod 2 extends out of the first end cover 31 and the top of the piston rod 2 contacts the secondary arrow body cover; gas is quickly introduced into the side of the second end cover 33 in the long cavity 3B, and air pressure is generated in the long cavity 3B at this time, and the gas pushes the piston rod 2 to quickly move in a straight line in the direction of the secondary arrow body. While the piston rod 2 moves, the gas is squeezed out from the side of the middle cover 32 in the long cavity 3B. When the piston rod 2 moves, the piston rod 2 will push the secondary arrow body cover to separate the secondary arrow body from the primary arrow body, and the separated secondary arrow body will continue to move along a predetermined trajectory; in this process, when the piston rod 2 approaches the end of its stroke, the limit block 41 in the buffer mechanism 4 will resist the piston 21 to prevent excessive movement of the piston rod 2. Figure 2 and Figure 3 As shown, in the initial state, please refer to Figure 2 The buffer mechanism 4 is affected by the buffer spring 44. At this time, one end of the buffer block 43 contacts the middle cover 32. When the piston rod 2 moves, the kinetic energy F2 of the piston rod 2 will first push the limit block 41 to move toward the secondary arrow body. Please refer to Figure 3When the stop block 41 contacts the middle cover 32, the middle cover 32 restricts the stop block 41 from moving further, and the piston rod 2 moves to the end of the stroke. At this time, the buffer block 43 in the buffer mechanism 4 squeezes the buffer spring 44, and the compressible gas 3A1 in the short chamber 3A is further compressed. Under the influence of the compressible gas 3A1 and the buffer spring 44, a thrust F1 is generated to act on the buffer block 43. Since the stop block 41 connected to the buffer block 43 abuts the piston 21, the movement of the piston rod 2 is slowed down to avoid the damage to the rocket separation cylinder caused by the violent impact after the excessive movement of the piston rod 2. When F1 is equal to F2, the piston rod 2 stops moving. When F1 is greater than F2, the buffer spring 44 will gradually return to its original state and push the buffer mechanism 4 to reset. After the piston rod 2 moves, the piston rod 2 will push the secondary rocket body cover to separate the secondary rocket body from the primary rocket body. After separation, the secondary rocket body will continue to move according to the predetermined trajectory. In some embodiments of the present invention, after the separation is completed, the piston rod 2 will be partially retracted in the cylinder 1, and the buffer mechanism 4 will continue to play a role for a period of time to ensure the stability and safety of the cylinder. Figures 1 to 3The inner diameter of the middle cover body 32 is larger than the outer diameter of the piston rod 2, providing sufficient space to accommodate the connecting rod 42, and the connecting rod 42 can make a linear motion in the gap space between the middle cover body 32 and the piston rod 2; the middle cover body 32 is also provided with an exhaust channel, and the setting of the exhaust channel allows the gas in the long cavity 3B to be quickly discharged. If the gas is not discharged in time, back pressure will be generated, slowing down the movement speed of the piston rod 2. During this process, the limit block 41 can prevent the piston rod 2 from directly hitting the middle cover body 32, reducing the vibration and impact of the system. When the buffer mechanism 4 gradually reduces the speed of the piston rod 2 to zero, the entire system ends smoothly; the buffer sleeve is usually made of elastic materials, such as polyurethane, rubber or other polymer materials, which have good energy absorption and impact resistance; the spring types include helical compression springs, disc springs, etc. The helical spring has good compression characteristics, while the disc spring can provide higher elasticity. The type should be selected according to the actual application scenario and needs, and the same is true for the material of the buffer spring 44. The utility model integrates the cylinder 1, piston rod 2, cover assembly 3 and buffer mechanism 4 in a limited space and realizes a mechanically reliable separation mechanism. The separation of the primary and secondary rocket bodies is realized through the extension of the piston rod 2, ensuring that the rocket bodies of each level are separated according to the predetermined plan; the buffer mechanism 4 arranged at the middle cover 32 provides buffering when the piston rod 2 moves to the end point, avoiding the structural damage caused by the violent impact of the piston rod 2, extending the service life of the cylinder while also protecting other components of the rocket; the utility model has a simple structure, and the modular design of the components makes maintenance and overhaul more convenient, which helps to reduce production and maintenance costs. It should also be noted here that in some embodiments of the utility model, in order to reduce the weight of the rocket, the piston rod 2 and the cover assembly 3 are made of aluminum alloy, and the cylinder 1 is made of carbon fiber. Compared with a cylinder made of all-steel, this material selection significantly reduces the weight.

[0033] Specifically, the buffer mechanism 4 further includes a buffer spring 44, one end of which is fixed to the buffer block 43, and the other end of which is fixed to the first end cover 31. Figure 2 and Figure 3 As shown, the length of the short cavity 3A is limited by the length of the buffer spring 44. The buffer spring 44 has a natural length when not under stress, and the length of the short cavity 3A is determined by this natural length; of course, the buffer spring 44 will shorten to a minimum length when it is compressed under stress, and the length of the short cavity 3A cannot be less than this minimum length to prevent the buffer spring 44 from being over-compressed and causing failure or damage. In some embodiments of the present invention, the length of the short cavity 3A is adjusted according to the requirements of the usage scenario, thereby adjusting the compression amount of the buffer spring 44, which can optimize the buffering effect and system response. In addition, the length of the long cavity 3B is limited by the required pressure and the cylinder diameter. As Figure 1As shown, the length of the long cavity 3B in the cylinder determines the movement stroke of the piston rod 2, and further determines the size of the pressure required when the cylinder is separated; in addition, the larger the diameter of the cylinder, the larger the force area. Under the same force, a larger diameter requires a longer length to disperse the force and prevent structural overload. Higher pressure and larger diameter will lead to greater internal force and structural stress, so the length of the long cavity 3B needs to be limited in combination to ensure the structural strength and stability during separation.

[0034] Furthermore, the inner diameter of the middle cover body 32 is larger than the outer diameter of the piston rod 2, and the connecting rod 42 is a hollow structure and is sleeved on the piston rod 2. This structure allows the connecting rod 42 to perform relative linear motion between the middle cover body 32 and the piston rod 2, which will not be described in detail here.

[0035] In some embodiments of the present invention, the cover assembly 3 further includes a plurality of tie rods 34, the outer diameters of the first end cover 31, the middle cover 32 and the second end cover 33 are larger than the outer diameter of the cylinder 1, and a plurality of connecting holes 3a are provided at the outer edges of the first end cover 31, the middle cover 32 and the second end cover 33, and the connecting holes 3a and the tie rods 34 are connected and fixed to the cylinder 1 and the cover assembly 3 by interference fit. Figure 1 As shown, multiple tie rods 34 are arranged in parallel along the length direction of the cylinder 1 and pass through the connection holes 3a of the first end cover 31, the middle cover 32 and the second end cover 33. The tie rods 34 tightly connect the cylinder 1 and the cover assembly 3 together, providing additional structural strength to prevent the assembly from being separated or deformed due to internal pressure or external force. Figures 4 to 6 , the number of connecting holes 3a provided on the first end cover 31, the middle cover body 32 and the second end cover 33 is consistent and the positions of the connecting holes 3a are evenly distributed, so as to ensure uniform force on each part. It should be understood that the connecting hole 3a and the pull rod 34 are assembled in an interference fit manner. By controlling the size difference between the connecting hole 3a and the pull rod 34, the two are tightly combined to achieve a reliable connection, thereby ensuring the stable operation of the system under high pressure and high stress conditions. It should be noted here that the pull rod 34 is made of steel. After passing through the connecting hole 3a, it is usually fixed with a nut or other fasteners. In order to prevent the nut from loosening, anti-loosening measures such as anti-loosening washers and locking nuts can be used. This structural design is easy to assemble and maintain and has high structural strength. The additional support provided by the pull rod 34 helps to improve the overall stability and reliability of the system.

[0036] Furthermore, the cover assembly 3 further includes a plurality of support rods 35, one end of the support rods 35 is connected to the cover of the first stage arrow body, and the other end of the support rods 35 is connected to the first end cover 31. Please continue to refer to Figure 1The support rod 35 is made of steel with high rigidity and durability. One end of the support rod 35 is fixed to the cover of the first-stage arrow body by bolts, welding or other mechanical connection methods. In order to ensure the firmness of the connection, the support rod 35 is parallel to the surface of the arrow body or at a certain angle to evenly distribute the stress. This connection method ensures that the support rod 35 can withstand the load from the arrow body structure and avoid deformation or damage to the mechanism during separation; the other end of the support rod 35 is mechanically connected to the first end cover 31 to withstand the impact and load during separation. It should be noted here that in this embodiment, the role of the support rod 35 in the separation process is not only to provide additional support, but also to prevent relative displacement between the cylinder 1 and the cover.

[0037] Preferably, the second end cover 33 is also provided with a plurality of mounting holes 3b, through which the rocket separation cylinder is fixed to the first stage rocket body casing. Figure 6 The mounting holes 3b are evenly distributed on the outer edge of the second end cover 33 to ensure uniform distribution of stress. The number and position of the mounting holes 3b are determined according to the structural requirements and mechanical analysis to provide sufficient fixing points to withstand the impact force and vibration during separation. The diameter and shape of the mounting holes 3b are designed according to the specifications of the matching fasteners. The second end cover 33 can be fixed to the first-stage rocket body cover through the mounting holes 3b by bolts, or by pins or snaps. In the utility model, the mounting holes 3b and the corresponding connectors ensure a stable connection between the second end cover 33 and the first-stage rocket body cover, so that the rocket separation cylinder remains in a predetermined position throughout the flight, ensuring overall stability.

[0038] Furthermore, a piston 21 adapted to the cross section of the long cavity 3B is provided at the bottom end of the piston rod 2, and a connecting component 22 is provided at the top end of the piston rod 2, and the connecting component 22 is used to contact the secondary arrow body. Please continue to refer to Figure 1, the piston 21 is sleeved at the bottom of the piston rod 2, and the piston 21 can be fixed to the piston rod 2 through structures such as grooves. During the rocket separation or other movement, the piston rod 2 will drive the piston 21 to move at high speed. When the piston 21 approaches the middle cover 32, the movement of the piston rod 2 is limited by the stop block 41, thereby slowing down the movement speed of the piston rod 2; since the piston 21 is adapted to the cross section of the long cavity 3B, it can play a sealing role in the long cavity 3B; in addition, the piston 21 is made of high temperature resistant and wear-resistant elastic materials, such as fluororubber, polytetrafluoroethylene, etc., and the specific material is determined according to the working environment, pressure, etc. On the other hand, the connecting component 22 is used to connect the piston rod 2 with the secondary rocket body, transmit the driving force during separation, and make the secondary rocket body separate from the primary rocket body. In this embodiment, the connecting component 22 is made of aluminum alloy to withstand sufficient strength and durability. In addition to the flange connection form in this embodiment, the connecting component 22 can also be a connecting ring, a quick connector, etc. The connecting component 22 only contacts with the secondary rocket body and is not completely connected, which is conducive to the rapid completion of the separation action. In this embodiment, the design of the connecting component 22 on the piston rod 2 ensures the reliability of the rocket under actual flight conditions, and guarantees the success rate of the mission and the safety of the system.

[0039] In some embodiments of the present invention, the middle cover 32 and the second end cover 33 are provided with a plurality of reserved openings 3c. Figure 5 and Figure 6 When using high-cost materials, the setting of the reserved opening 3c can save the materials required for manufacturing, reduce the manufacturing cost, and reduce the weight of the entire system; the setting of the reserved opening 3c can help dissipate heat, prevent local overheating, and help protect sensitive equipment and components; the setting of the reserved opening 3c can also adjust the center of gravity and mass distribution of the entire system to optimize the flight stability and control performance.

[0040] On the basis of the above embodiment, the reserved opening 3c includes an exhaust port 3c1 on the middle cover 32 and a vent 3c2 on the second end cover 33. The exhaust port 3c1 on the middle cover 32 and the vent 3c2 on the second end cover 33 can help balance the gas pressure difference inside the long cavity 3B, and prevent the long cavity 3B or the cylinder from being damaged due to excessive pressure. In the space environment, the outside is in a vacuum state. If there is no vent 3c2, when the gas inside the system is released, it may cause a vacuum effect, causing excessive structural stress or even rupture. The vent 3c2 can alleviate this problem and prevent structural damage; the exhaust port 3c1 on the middle cover 32 can discharge excess gas during rocket separation or other operations, which helps to reduce internal gas accumulation and reduce internal pressure. The exhaust port 3c1 can also be used as a safety pressure relief port to avoid dangerous situations caused by excessive gas accumulation inside the equipment. Through the setting of the exhaust port 3c1 and the vent 3c2, it can prevent the internal gas pressure from generating excessive thrust or pull on the structure, and prevent the equipment structure from being deformed or damaged.

[0041] In some embodiments of the present invention, a pressure sensor 6 and a temperature sensor 5 are also included. Figure 5 and Figure 6 , the pressure sensor 6 can monitor the pressure changes inside the device in real time. By monitoring the pressure, the working state of the system can be judged to ensure operation within a safe pressure range; the temperature sensor 5 can monitor the temperature changes inside the system in real time, which is very important for protecting temperature-sensitive equipment and preventing overheating or overcooling. The setting of the pressure sensor 6 and the temperature sensor 5 can detect the pressure and temperature inside the device in real time, so as to analyze the problems caused by the device according to the temperature and pressure curves after the test. For example, when the piston rod 2 is not extended quickly enough, analyzing whether the pressure of the device has increased can tell whether the exhaust area of ​​the middle cover body 32 is too small, making the exhaust speed too slow, generating back pressure, and causing the piston rod 2 to extend at a speed that does not reach the target; analyzing the pressure rise speed of the device can tell whether the gas source flow is too small, the pressure inside the device is too slow to build up, and the piston rod 22 speed does not meet the standard.

[0042] Those skilled in the art should understand that the present invention is not limited by the above embodiments. The above embodiments and the description are only for explaining the principle of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which are within the scope of the present invention. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A rocket separation cylinder, characterized in that: include: Cylinder barrel; A piston rod is disposed in the cylinder and can perform relative linear motion in the cylinder; A cover assembly comprises a first end cover, an intermediate cover and a second end cover which are coaxially arranged, wherein the first end cover and the second end cover are respectively fixed to the two ends of the cylinder barrel, the intermediate cover body separates the cylinder barrel, the first end cover and the intermediate cover body seal the cylinder barrel to form a short cavity, wherein there is compressible gas in the short cavity, the intermediate cover body and the second end cover seal the cylinder barrel to form a long cavity, and the piston rod passes through the centers of the first end cover, the intermediate cover body and the second end cover along the axial direction; The buffer mechanism comprises a limit block, a connecting rod and a buffer block, wherein the connecting rod is arranged between the intermediate cover body and the piston rod so as to be capable of relatively linear motion, one end of the connecting rod is fixed to the limit block, the limit block is arranged in the long cavity, and the other end of the connecting rod is fixed to the buffer block, the buffer block is arranged in the short cavity; Among them, one side of the second end cover is fixed to the first-stage arrow body cover, the top end of the piston rod extends out of the first end cover and contacts the second-stage arrow body cover, and when the piston rod moves to a predetermined stroke, the second-stage arrow body is detached.

2. The rocket separation cylinder according to claim 1, characterized in that: The buffer mechanism further includes a buffer spring, one end of which is fixed to the buffer block, and the other end of which is fixed to the first end cover.

3. The rocket separation cylinder according to claim 1, characterized in that: The inner diameter of the middle cover body is larger than the outer diameter of the piston rod, and the connecting rod is a hollow structure and is sleeved on the piston rod.

4. The rocket separation cylinder according to claim 1, characterized in that: The cover body assembly also includes multiple tie rods. The outer diameters of the first end cover, the middle cover body, and the second end cover are larger than the outer diameters of the cylinder barrel, and a plurality of connecting holes are arranged at the outer edges of the first end cover, the middle cover body, and the second end cover. The connecting holes and the tie rods connect and fix the cylinder barrel and the cover body assembly through interference fit.

5. The rocket separation cylinder according to claim 1, characterized in that: The cover assembly also includes a plurality of struts, one end of each strut is connected to the cover shell of the first-stage arrow body, and the other end of each strut is connected to the first end cover.

6. The rocket separation cylinder according to claim 5, characterized in that: The second end cover is also provided with a plurality of mounting holes, through which the rocket separation cylinder is fixed to the first-stage rocket body cover.

7. The rocket separation cylinder according to claim 1, characterized in that: A piston adapted to the cross-section of the long cavity is arranged on the bottom end of the piston rod, and a connecting component is arranged on the top end of the piston rod, and the connecting component is used to contact with the secondary arrow body.

8. The rocket separation cylinder according to claim 1, characterized in that: The middle cover body and the second end cover are provided with a plurality of reserved openings.

9. The rocket separation cylinder according to claim 8, characterized in that: The reserved openings include an exhaust port on the middle cover body and a vent port on the second end cover.

10. The rocket separation cylinder according to claim 1, characterized in that: Also includes pressure sensors and temperature sensors.

Images