Spacecraft multi-stage cylinder type ejection separation mechanism

Abstract

The application discloses a spacecraft multistage cylinder type ejection separation mechanism, which comprises a high-pressure gas cylinder, a flow control valve, a multistage piston cylinder, a baffle, a connecting mechanism and a multistage baffle transmission device; the flow control valve is installed in a gas passage; the connecting mechanism comprises two oppositely arranged clamping hooks and an elastic member; the bottom end of the clamping hook is fixedly connected to the top of the upper piston cylinder through a shear pin or an explosive bolt; the baffle corresponds to the clamping hook one by one and is used for limiting the clamping hook; the inner side wall of the baffle is attached to the outer side wall of the upper piston cylinder, and the bottom support at the bottom end supports the bottom end of the upper piston cylinder; in the vertical direction, the length of the baffle is greater than the length of the upper piston cylinder and has a length difference; the multistage baffle transmission device is used for limiting the maximum rising height of the baffle. The ejection separation mechanism can increase the distance between a spacecraft and a carrier during a separation process without changing the minimum distance before the spacecraft and the carrier are separated.

Description

A multi-stage cylinder ejection separation mechanism for spacecraft Technical Field

[0001] This invention relates to the field of ejection separation technology, and more specifically to a multi-stage cylinder-type ejection separation mechanism for spacecraft. Background Technology

[0002] The separation process of parallel launch vehicles is a crucial factor affecting the success of space launches. The separation process mainly involves the spacecraft, the launch vehicle, and the separation device. Specifically, the separation device first disconnects the connection between the spacecraft and the launch vehicle and provides them with a certain initial velocity through its own power. Under the velocity provided by the separation device, the launch vehicle and the spacecraft are separated by the combined effects of gravity, aerodynamic forces, etc. After reaching a specific position, the launch vehicle and the spacecraft independently carry out subsequent movements.

[0003] The most common parallel launch vehicle design currently references the US Space Shuttle, which uses a launch vehicle to carry the spacecraft and ultimately separate them. Common separation and connection mechanisms include explosive bolt connections, mechanical fastening, and electromagnetic fastening. The Space Shuttle used explosive bolt connections, where, at the moment of separation, the explosive bolts, through the force generated by the explosion, give both components an initial velocity, allowing them to separate under this initial velocity.

[0004] During the separation process of parallel launch vehicles, it is crucial to ensure that they do not collide. Secondly, after complete separation, each vehicle must maintain stability to ensure normal subsequent motion. If the separation velocity is inappropriate, they may collide before engine ignition or the velocity may not guarantee stability, potentially leading to the failure of the space launch mission. The minimum distance H between the spacecraft and launch vehicle using explosive bolts as a separation device is related to the choice of explosive bolts. With a constant distance between them, an inappropriate angular velocity after separation can cause a collision.

[0005] Explosive bolts limit the minimum distance between spacecraft and launch vehicles, and a small gap between them reduces the safety of parallel launch vehicle separation. Therefore, it is important to improve the safety of parallel launch vehicle separation. Summary of the Invention

[0006] This invention provides a multi-stage cylinder-type ejection separation mechanism for spacecraft. This ejection separation mechanism can increase the axial distance between the spacecraft and the launch vehicle during the separation process without changing the minimum distance before separation, thereby increasing the safety of the separation process.

[0007] The present invention adopts the following specific technical solution:

[0008] A multi-stage cylinder ejection separation mechanism for spacecraft is used for interstage separation of launch vehicle and spacecraft. The ejection separation mechanism includes a high-pressure gas cylinder, a flow control valve, a multi-stage piston cylinder, a baffle, a connecting mechanism, and a multi-stage baffle transmission device.

[0009] The multi-stage piston cylinder includes an upper piston cylinder, a lower piston cylinder located outside the upper piston cylinder, and at least one intermediate piston cylinder slidably connected between the upper piston cylinder and the lower piston cylinder; the lower piston cylinder is fixedly connected to the gas passage.

[0010] The high-pressure gas cylinder and the gas passage are both fixedly installed on the carrier; the high-pressure gas cylinder stores high-pressure gas and is connected to the lower piston cylinder through the gas passage, which is used to drive the multi-stage piston cylinder to extend vertically upward; the flow control valve is installed in the gas passage;

[0011] The connecting mechanism includes two hooks arranged opposite each other in the horizontal direction, and an elastic element compressed between the two hooks;

[0012] The bottom end of the hook is fixedly connected to the top of the upper piston cylinder by a shear pin or an explosion bolt, and the top end is used to engage with the slot of the spacecraft.

[0013] The baffle corresponds one-to-one with the hook and is used to limit the hook when the spacecraft is connected to the launch vehicle, thereby keeping the hook in the slot; the inner side wall of the baffle is attached to the outer side wall of the upper piston cylinder, and a bottom support is provided at the bottom end, which supports the bottom end of the upper piston cylinder and lifts the upper piston cylinder upward; in the vertical direction, the length of the baffle is greater than the length of the upper piston cylinder and there is a length difference;

[0014] The multi-stage baffle transmission device corresponds one-to-one with the baffle and can slide in the vertical direction. One end is slidably connected to the corresponding baffle, and the other end is fixedly connected to the gas channel to limit the maximum rising height of the baffle.

[0015] The maximum rising height of the upper piston cylinder is greater than the sum of the maximum rising height of the baffle and the length difference.

[0016] Furthermore, the intermediate piston cylinder is provided with a vent hole.

[0017] Furthermore, it also includes a recovery device installed within the multi-stage piston cylinder;

[0018] The upper end of the recovery device is fixedly connected to the upper piston cylinder, and the lower end is fixedly connected to the lower piston cylinder, which is used to restore the multi-stage piston cylinder to its contracted state after the gas is released.

[0019] Furthermore, both the recycling device and the elastic element are springs.

[0020] Furthermore, the multi-stage piston cylinder includes two intermediate piston cylinders, namely a first intermediate piston cylinder and a second intermediate piston cylinder.

[0021] Furthermore, the multi-stage baffle transmission device includes a first baffle transmission device, a second baffle transmission device, and a third baffle transmission device that are slidably connected in sequence.

[0022] The first section of the baffle transmission device is slidably connected to the baffle;

[0023] The third baffle transmission device is fixedly connected to the gas channel.

[0024] Furthermore, the baffle, the first baffle transmission device, the second baffle transmission device, and the third baffle transmission device are all arc-shaped plates that match the outer surface shape of the multi-stage piston cylinder.

[0025] Furthermore, it also includes a baffle buffer device disposed in the first baffle transmission device, the second baffle transmission device, and the third baffle transmission device;

[0026] The baffle buffer device is used to buffer collisions between the baffle transmission devices and between the baffle and the first section of the baffle transmission device.

[0027] Furthermore, it also includes piston cylinder buffer devices disposed at the top of each of the intermediate piston cylinders and the lower piston cylinder, the piston cylinder buffer devices being used to buffer collisions between the individual piston cylinders.

[0028] Beneficial effects:

[0029] 1. The multi-stage cylinder ejection and separation mechanism of the present invention is installed between the spacecraft and the launch vehicle. The spacecraft is ejected and separated from the launch vehicle by the extension of the multi-stage piston cylinder. The baffle on the outside of the hook keeps the hook in the spacecraft's slot, ensuring the stability of the spacecraft before separation from the launch vehicle. The multi-stage baffle transmission device installed between the baffle and the gas channel limits the maximum rising height of the baffle and also has a buffering effect on the baffle during the extension of the multi-stage piston cylinder. By controlling the difference in rising height between the upper piston cylinder and the baffle, the restriction of the baffle on the hook is released, and the separation of the spacecraft and the launch vehicle is achieved by the failure of the connecting mechanism. The distance between the spacecraft and the launch vehicle can be increased during the process of the multi-stage piston cylinder from the initial retracted state to the final extended state, thereby improving the separation safety.

[0030] 2. The multi-stage cylinder ejection separation mechanism for spacecraft of the present invention can control the state of high-pressure gas flowing into the multi-stage piston cylinder through a high-pressure gas cylinder and a flow control valve, thereby changing the acceleration, velocity, and other states during the movement of the multi-stage piston cylinder. The distance coordination between each piston cylinder and the multi-stage baffle transmission device can change the relative positional relationship between the baffle and the upper piston cylinder, thereby controlling the start failure time of the connecting mechanism. Under different multi-stage piston cylinder movement states and relative positions of the connecting mechanism, the spacecraft's movement state is different. Therefore, the spacecraft's movement state during separation can be changed by controlling the coordination between the high-pressure gas cylinder and the flow control valve, as well as the relative positional relationship between the multi-stage piston cylinder and the multi-stage baffle transmission device.

[0031] Therefore, the aforementioned ejection separation mechanism can increase the distance between the spacecraft and the launch vehicle during the separation process without changing the minimum distance before separation, thereby increasing the safety of the separation process. Attached Figure Description

[0032] Figure 1 is a schematic diagram of the ejection separation mechanism of the present invention connecting the spacecraft and the launch vehicle;

[0033] Figure 2 is a schematic diagram of the overall structure of the ejection separation mechanism of the present invention;

[0034] Figure 3 is a schematic diagram of the principle structure of the multi-stage piston cylinder, baffle, and multi-stage baffle transmission device in Figure 2.

[0035] Figure 4 is a schematic diagram of the multi-stage piston cylinder when the ejection separation mechanism completes ejection;

[0036] Figure 5 is a schematic diagram showing the relative positions of the multi-stage piston cylinder, spacecraft, connecting mechanism, and baffle when the ejection separation mechanism completes ejection.

[0037] Among them, 1-spacecraft, 2-launcher, 3-ejection separation mechanism, 4-hook, 5-high-pressure gas cylinder, 6-elastic element, 7-baffle, 8-gas passage, 9-recovery device, 10-upper piston cylinder, 11-first intermediate piston cylinder, 12-second intermediate piston cylinder, 13-lower piston cylinder, 14-piston cylinder buffer device, 15-base support, 16-first section baffle transmission device, 17-second section baffle transmission device, 18-third section baffle transmission device, 19-baffle buffer device, 20-fixed structure, 21-vent hole, 22-flow control valve, 23-limiting protrusion, 24-limiting block Detailed Implementation

[0038] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0039] As shown in Figure 1, the parallel launch vehicle includes a launch vehicle 2, a spacecraft 1 connected to the top of the launch vehicle 2, and a multi-stage cylinder-type ejection separation mechanism 3 for spacecraft 1 that connects spacecraft 1 to the launch vehicle 2. In this embodiment of the invention, the multi-stage cylinder-type ejection separation mechanism 3 for spacecraft 1 is used for connecting the launch vehicle 2 and spacecraft 1 and for inter-stage separation. Before spacecraft 1 separates from the launch vehicle 2, the ejection separation mechanism 3 serves as a fixed connection. The multi-stage cylinder-type ejection separation mechanism 3 for spacecraft 1 provided in this embodiment of the invention aims to increase the safety of separation by increasing the distance between spacecraft 1 and launch vehicle 2. The multi-stage cylinder-type ejection separation mechanism 3 for spacecraft 1 will be described in detail below.

[0040] The ejection separation mechanism 3 includes a high-pressure gas cylinder 5, a flow control valve 22, a multi-stage piston cylinder, a baffle 7, a connecting mechanism, and a multi-stage baffle transmission device.

[0041] The multi-stage piston cylinder includes an upper piston cylinder 10, a lower piston cylinder 13 located outside the upper piston cylinder 10, and at least one intermediate piston cylinder slidably connected between the upper piston cylinder 10 and the lower piston cylinder 13; the lower piston cylinder 13 is fixedly connected to the gas passage 8; in this embodiment, a four-stage piston cylinder is used as an example for description, but the multi-stage piston cylinder is not limited to a four-stage piston cylinder, and can also be a three-stage piston cylinder, a five-stage piston cylinder, etc., as shown in Figures 4 and 5. The multi-stage piston cylinder includes an upper piston cylinder 10 at the top, a lower piston cylinder 13 outside the upper piston cylinder 10, and two intermediate piston cylinders slidably connected between the upper piston cylinder 10 and the lower piston cylinder 13, the two intermediate piston cylinders being a first intermediate piston cylinder 11 and a second intermediate piston cylinder 12, respectively.

[0042] Both the high-pressure gas cylinder 5 and the gas channel 8 are fixedly installed on the launch vehicle 2 and can be fixed to the launch vehicle 2 by welding, bolts or other connection methods. The high-pressure gas cylinder 5 stores high-pressure gas and is connected to the lower piston cylinder 13 through the gas channel 8. The lower piston cylinder 13 is fixedly connected to the gas channel 8 through the fixed connection structure 20. It is used to drive the multi-stage piston cylinder to extend vertically upward through the high-pressure gas. That is, under the action of the high-pressure gas, the multi-stage piston cylinder extends from the launch vehicle 2 toward the spacecraft 1, thereby driving the spacecraft 1 away from the launch vehicle 2. A flow control valve 22 is installed in the gas channel 8. The flow control valve 22 is used to control the opening and closing of the gas channel 8 and the flow rate of the high-pressure gas. That is, the flow control valve 22 is used to control the release of gas from the high-pressure gas cylinder 5.

[0043] As shown in Figures 2 and 5, the connecting mechanism includes two hooks 4 arranged opposite each other in the horizontal direction, and an elastic element 6 compressed between the two hooks 4; the elastic element 6 can be a spring; the bottom end of the hook 4 is fixedly connected to the top of the upper piston cylinder 10 by a shear pin or an explosion bolt, and the top end is used to engage with the slot of the spacecraft 1; the slot can be a cuboid slot or other shapes; the hooks 4 and the slot are in a concave-convex fit, so that the spacecraft 1 is fixedly connected to the top of the launch vehicle 2 by engaging the hooks 4 in the slot; as shown in Figure 2, the spacecraft 1 can be installed on the top of the launch vehicle 2 by two connecting mechanisms arranged at intervals. The connecting mechanisms in Figure 2 are only schematic and do not limit the specific number and distribution of the connecting mechanisms.

[0044] As shown in Figures 2 and 3, the baffle 7 corresponds one-to-one with the hook 4 and is used to limit the hook 4 when the spacecraft 1 is connected to the launch vehicle 2, thereby keeping the hook 4 in the slot. The inner wall of the baffle 7 is attached to the outer wall of the upper piston cylinder 10, and a bottom support 15 is provided at the bottom end. The bottom support 15 supports the bottom end of the upper piston cylinder 10 and lifts the upper piston cylinder 10 up under the action of high pressure gas. In the vertical direction, the length of the baffle 7 is greater than the length of the upper piston cylinder 10 and there is a length difference. Since the length of the baffle 7 is greater than the length of the upper piston cylinder 10, when the spacecraft 1 is fixedly connected to the launch vehicle 2, the top of the baffle 7 exceeds the top of the upper piston cylinder 10 and is limited to the outside of the hook 4 to prevent the hook 4 from falling out of the slot.

[0045] As shown in Figures 2 and 3, the multi-stage baffle transmission device corresponds one-to-one with the baffle 7 and can slide vertically. One end is slidably connected to the corresponding baffle 7, and the other end is fixedly connected to the gas channel 8 to limit the maximum rising height of the baffle 7. On both sides of each multi-stage piston cylinder, there is a baffle 7 for controlling the hook 4 and a multi-stage baffle transmission device for controlling the rising height of the baffle 7. The positions of the baffle 7 and the hook 4 correspond, and the positions of the multi-stage baffle transmission device correspond to the baffle 7. A multi-stage baffle transmission device is connected between each baffle 7 and the carrier 2. In this embodiment, a three-stage baffle transmission device is used as an example for explanation, but the multi-stage baffle transmission... The actuator is not limited to a three-stage baffle transmission device. A multi-stage baffle transmission device includes a first baffle transmission device 16, a second baffle transmission device 17, and a third baffle transmission device 18 that are slidably connected in sequence. The first baffle transmission device 16 is slidably connected to the baffle 7, the second baffle transmission device 17 is slidably connected to the first baffle transmission device 16, and the third baffle transmission device 18 is slidably connected to the second baffle transmission device 17. The third baffle transmission device 18 is fixedly connected to the gas channel 8 through a fixed connection structure 20. When the baffle 7 rises, it will sequentially drive the first baffle transmission device 16, the second baffle transmission device 17, and the third baffle transmission device 18 to rise.

[0046] The maximum rising height of the upper piston cylinder 10 is greater than the sum of the maximum rising height and the length difference of the baffle 7.

[0047] The aforementioned multi-stage cylinder ejection and separation mechanism 3 of spacecraft 1 is installed between spacecraft 1 and launch vehicle 2. The ejection and separation of spacecraft 1 from launch vehicle 2 is achieved through the extension of multi-stage piston cylinders. The baffle 7 on the outside of the hook 4 keeps the hook 4 in the slot of spacecraft 1, ensuring the stability of spacecraft 1 before separation from launch vehicle 2. The multi-stage baffle transmission device installed between the baffle 7 and the gas channel 8 has the effect of limiting the maximum rising height of the baffle 7 and buffering the baffle 7 during the extension of the multi-stage piston cylinder. By controlling the difference in rising height between the upper piston cylinder 10 and the baffle 7, the restriction of the hook 4 by the baffle 7 is released, and the separation of spacecraft 1 and launch vehicle 2 is achieved by the failure of the connecting mechanism. The multi-stage piston cylinder can increase the distance between spacecraft 1 and launch vehicle 2 during the process from the initial retracted state to the final extended state, thereby improving the separation safety.

[0048] The multi-stage cylinder ejection separation mechanism 3 of the aforementioned spacecraft 1 can control the state of the high-pressure gas flowing into the multi-stage piston cylinder through the high-pressure gas cylinder 5 and the flow control valve 22, thereby changing the acceleration, velocity, and other states during the movement of the multi-stage piston cylinder. The distance coordination between each section of the piston cylinder and the multi-stage baffle transmission device can change the relative positional relationship between the baffle 7 and the upper piston cylinder 10, thereby controlling the start failure time of the connecting mechanism. Under different multi-stage piston cylinder movement states and relative positions of the connecting mechanism, the movement state of the spacecraft 1 is different. Therefore, the movement state of the spacecraft 1 during separation can be changed by controlling the coordination between the high-pressure gas cylinder 5 and the flow control valve 22, as well as the relative positional relationship between the multi-stage piston cylinder and the multi-stage baffle transmission device.

[0049] Therefore, the aforementioned ejection separation mechanism 3 can increase the distance between spacecraft 1 and launch vehicle 2 during the separation process without changing the minimum distance before separation, thereby increasing the safety of the separation process.

[0050] In one specific embodiment, the ejection separation mechanism 3 further includes a recovery device 9 installed in a multi-stage piston cylinder; the recovery device 9 can be a spring; the intermediate piston cylinder can also be provided with a vent hole 21; the upper end of the recovery device 9 is fixedly connected to the upper piston cylinder 10, and the lower end is fixedly connected to the lower piston cylinder 13, for restoring the multi-stage piston cylinder to a contracted state after venting.

[0051] Because a recovery device 9 such as a spring is installed in the multi-stage piston cylinder, and a vent 21 is provided on the intermediate piston cylinder, after the ejection separation of the spacecraft 1 is completed, the vent 21 can cause the multi-stage piston cylinder to retract, and at the same time, the recovery device 9 can restore the multi-stage piston cylinder to its initial state, which is conducive to maintaining the aerodynamic characteristics of the launch vehicle 2.

[0052] As shown in Figure 3, the baffle 7, the first baffle transmission device 16, the second baffle transmission device 17, and the third baffle transmission device 18 are all arc-shaped plates that match the outer surface shape of the multi-stage piston cylinder. Both the baffle 7 and the first baffle transmission device 16 have an integral limiting protrusion 23 at their bottom ends on the side away from the multi-stage piston cylinder. The first baffle transmission device 16, the second baffle transmission device 17, and the third baffle transmission device 18 each have an integral limiting block 24 at their top ends on the side facing the multi-stage piston cylinder. The limiting block 24 is used to block the corresponding limiting protrusion 23 to achieve a sliding connection. That is, the limiting protrusion 23 of the first baffle transmission device 16... The stop block 24 is used to block the limiting protrusion 23 of the baffle 7 when the baffle 7 rises, thereby limiting the rising height of the baffle 7. The limiting block 24 of the second baffle transmission device 17 is used to cooperate with the limiting protrusion 23 of the first baffle transmission device 16 to limit the rising height of the first baffle transmission device 16. The limiting block 24 of the third baffle transmission device 18 is used to limit the top of the second baffle transmission device 17 to limit the rising distance of the second baffle transmission device 17. Thus, the maximum rising height of the baffle 7 is limited by the first baffle transmission device 16, the second baffle transmission device 17 and the third baffle transmission device 18.

[0053] The multi-stage baffle transmission device can guide the rise of the baffle 7, and the maximum rise height of the baffle 7 can be limited by the movable distance of the multi-stage baffle transmission device. When the multi-stage piston cylinder rises and the highest point exceeds the height of the baffle 7, the hook 4 gradually gets off the baffle 7 under the lifting action of the multi-stage piston cylinder, which facilitates the hook 4 to disengage from the slot. This enables the spacecraft 1 to separate from the launch vehicle 2 with an increased separation distance, thus improving the safety of separation and ejection.

[0054] As shown in Figure 3, the ejection separation mechanism 3 further includes baffle buffer devices 19 disposed on each limiting block 24, and piston cylinder buffer devices 14 disposed on the top of each intermediate piston cylinder and lower piston cylinder 13; the baffle buffer devices 19 are fixedly connected to the limiting blocks 24; the piston cylinder buffer devices 14 are fixedly connected to the intermediate piston cylinder and lower piston cylinder 13; the baffle buffer devices 19 are used to buffer the collisions between each baffle transmission device and between the baffle 7 and the first baffle transmission device 16; the piston cylinder buffer devices 14 are used to buffer the collisions between each piston cylinder.

[0055] By adding the baffle buffer device 19 and the piston cylinder buffer device 14, the collisions between the multi-stage piston cylinders can be buffered when they extend and the baffle transmission devices slide, thereby reducing the collision force between the piston cylinders and the baffle transmission devices, preventing damage, and extending service life.

[0056] The operation of the above-mentioned ejection separation mechanism 3 is as follows:

[0057] In the first step, when the spacecraft 1 and the launch vehicle 2 separate, the high-pressure gas cylinder 5 is controlled to start releasing gas through the flow control valve 22. After the high-pressure gas passes through the gas channel 8, it first acts on the bottom support 15 of the baffle 7, causing the baffle 7 and the upper piston cylinder 10 to move upward together.

[0058] In the second step, the upper piston cylinder 10 and the baffle 7 move upward together, sequentially driving the first baffle transmission device 16, the first intermediate piston cylinder 11, the second baffle transmission device 17, and the second intermediate piston cylinder 12 to move upward until the second intermediate piston cylinder 12 collides with the lower piston cylinder 13 fixed to the carrier 2, and the second baffle transmission device 17 collides with the third baffle transmission device 18 fixed to the carrier 2. The piston cylinder buffer device 14 of the multi-stage piston cylinder and the baffle buffer device 19 of the multi-stage baffle transmission device both buffer the vibration generated by the collision.

[0059] In the third step, since each piston cylinder and baffle transmission device has a maximum movement distance, the control function of the baffle 7 on the hook 4 will fail during the collision between the second intermediate piston cylinder 12 and the lower piston cylinder 13 fixed to the carrier 2, and the second baffle transmission device 17 and the third baffle transmission device 18 fixed to the carrier 2. Under the thrust of the elastic element 6, the hook 4 will lose its engagement with the spacecraft 1, thus completing the separation, as shown in Figure 5.

[0060] In the fourth step, the second intermediate piston cylinder 12 has a vent hole 21. When the spacecraft 1 is about to separate from the hook 4, the vent hole is opened to release air, which reduces the pressure inside the multi-stage piston cylinder. Under the pulling force of the recovery device 9 and the reduced pressure, the multi-stage piston cylinder is pulled back for recovery.

[0061] Obviously, those skilled in the art can make various modifications and variations to the embodiments of the present invention without departing from the spirit and scope of the invention. Therefore, if these modifications and variations fall within the scope of the claims of the present invention and their equivalents, the present invention also intends to include these modifications and variations.

Claims

1. A multi-stage cylinder-type ejection separation mechanism for spacecraft, used for inter-stage separation of a launch vehicle and a spacecraft, characterized in that, The system includes a high-pressure gas cylinder, a flow control valve, a multi-stage piston cylinder, baffles, a connecting mechanism, and a multi-stage baffle transmission device. The multi-stage piston cylinder includes an upper piston cylinder, a lower piston cylinder located outside the upper piston cylinder, and at least one intermediate piston cylinder slidably connected between the upper and lower piston cylinders. The lower piston cylinder is fixedly connected to a gas channel. Both the high-pressure gas cylinder and the gas channel are fixedly installed on the launch vehicle. The high-pressure gas cylinder stores high-pressure gas and communicates with the lower piston cylinder through the gas channel, driving the multi-stage piston cylinder to extend vertically upwards. The flow control valve is installed in the gas channel. The connecting mechanism includes two hooks arranged horizontally opposite each other and an elastic element compressed between the two hooks. The bottom end of each hook is fixedly connected to the top of the upper piston cylinder by a shear pin or an explosive bolt, and the top end is used to engage with a slot on the spacecraft. The baffles correspond one-to-one with the hooks and limit the hooks when the spacecraft is connected to the launch vehicle. The hook is held within the slot; the inner wall of the baffle is fitted against the outer wall of the upper piston cylinder, and a base support is provided at the bottom end, which supports the bottom end of the upper piston cylinder and lifts it upward; in the vertical direction, the length of the baffle is greater than the length of the upper piston cylinder and there is a length difference; the multi-stage baffle transmission device corresponds one-to-one with the baffle and can slide in the vertical direction, one end of which is slidably connected to the corresponding baffle, and the other end is fixedly connected to the gas channel, which is used to limit the maximum rising height of the baffle; the maximum rising height of the upper piston cylinder is greater than the sum of the maximum rising height of the baffle and the length difference; the multi-stage piston cylinder includes two intermediate piston cylinders, which are a first intermediate piston cylinder and a second intermediate piston cylinder; the multi-stage baffle transmission device includes a first section baffle transmission device, a second section baffle transmission device, and a third section baffle transmission device that are slidably connected in sequence; the first section baffle transmission device is slidably connected to the baffle; the third section baffle transmission device is fixedly connected to the gas channel.

2. The multi-stage cylinder-type ejection separation mechanism as described in claim 1, characterized in that, The intermediate piston cylinder is provided with a vent hole.

3. The multi-stage cylinder-type ejection separation mechanism as described in claim 2, characterized in that, It also includes a recovery device installed inside the multi-stage piston cylinder; the upper end of the recovery device is fixedly connected to the upper piston cylinder and the lower end is fixedly connected to the lower piston cylinder, used to restore the multi-stage piston cylinder to a contracted state after the gas is released.

4. The multi-stage cylinder-type ejection separation mechanism as described in claim 3, characterized in that, Both the recycling device and the elastic element are springs.

5. The multi-stage cylinder-type ejection separation mechanism as described in claim 1, characterized in that, The baffle, the first baffle transmission device, the second baffle transmission device, and the third baffle transmission device are all arc-shaped plates that match the outer surface shape of the multi-stage piston cylinder.

6. The multi-stage cylinder-type ejection separation mechanism as described in claim 5, characterized in that, It also includes baffle buffer devices disposed in the first baffle transmission device, the second baffle transmission device and the third baffle transmission device; the baffle buffer devices are used to buffer collisions between the baffle transmission devices and between the baffle and the first baffle transmission device.

7. The multi-stage cylinder-type ejection separation mechanism as described in claim 1, characterized in that, It also includes piston cylinder buffer devices disposed at the top of each of the intermediate piston cylinders and the lower piston cylinder, the piston cylinder buffer devices being used to buffer collisions between the individual piston cylinders.

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