CN211167475U - The separation system of the rocket compartment and the rocket - Google Patents

Abstract

The present application relates to the field of aerospace technology, and in particular, to a separation system for a rocket compartment and a rocket. Since the separation system and rocket of the rocket cabin section of the present application can avoid the use of pyrotechnic devices, the safety is high, and because the push-pull device has three layers of cylinders, it can ensure a long stroke, so it can be used in the length direction. It saves the space inside the rocket compartment occupied by the push-pull device, so you can use some space in the diameter direction of the rocket compartment, and increasing the diameter of the three-layer cylinder of the push-pull device will inevitably increase the thrust of the center tube, so that it can be Ensure that there is sufficient separation impulse between the rocket compartments. In addition, using high-pressure gas as the separation energy, the separation impulse generated by it is also relatively stable, and the separation effect is also better.

Description

The separation system of the rocket compartment and the rocket

technical field

The present application relates to the field of aerospace technology, and in particular, to a separation system for a rocket compartment and a rocket.

Background technique

During the rocket launch, the compartments need to be separated. At present, the separation of rocket compartments generally uses pyrotechnic separation energy, such as solid small rockets, pyrotechnic cylinders, or mechanical separation springs.

Among them, the solid small rocket and the fire working cylinder are all pyrotechnic devices that use gunpowder as a power source. Since the pyrotechnic device has the characteristics of extremely high safety requirements, a special storage warehouse is required to store the pyrotechnic device, and also It is necessary to install a pyrotechnic device between the rocket compartments in the workshop of the corresponding explosion-proof level. At the same time, when the pyrotechnic device is installed between the rocket compartments, supporting anti-static measures are also required. The safety of the pyrotechnic device is low, and the storage and installation environment of the pyrotechnic device used for the separation of the rocket compartment is relatively high.

Although the mechanical separation spring is relatively reliable in terms of safety, the separation impulse provided by it is small, which is not conducive to the separation between the rocket compartments. If the mechanical separation spring can ensure the separation impulse between the rocket compartments, its own The weight is necessarily heavier, which runs counter to the requirement to reduce the weight of the launch vehicle as much as possible.

Therefore, how to improve the safety of the separation system of the rocket cabins on the premise of ensuring the separation impulse between the rocket cabin sections is a technical problem that those skilled in the art need to solve urgently.

Utility model content

The present application provides a separation system for rocket cabin sections and a rocket, so as to improve the safety of the separation system for rocket cabin sections on the premise of ensuring the separation impulse between the rocket cabin sections.

In order to solve the above-mentioned technical problems, the application provides the following technical solutions:

A separation system for a rocket cabin section, comprising: a gas cylinder, a pressure conveying pipeline, an on-off valve, at least two push-pull devices, and a force-bearing device matched with each push-pull device; the gas bottle is fixed inside the rocket cabin section or on the outer wall; the pressure delivery pipeline is connected from the gas cylinder outlet to each push-flush device, and the parts of the pressure delivery pipeline leading to each push-flush device are the same as each other; the on-off valve is arranged at the gas cylinder outlet or the pressure delivery pipe On the way, the pressure gas in the control gas cylinder leads to the pressure conveying pipeline; the push-pull device includes: a base, an outer cylinder, a middle cylinder and a center cylinder with an inflatable cavity extending inward from the rear end and not passing through; the front end of the intermediate cylinder Inserted from the rear end of the outer cylinder into the through-gassing cavity of the outer cylinder, and the front end of the intermediate cylinder is in contact with the inwardly bent part of the front end of the outer cylinder; the front end of the central cylinder is inserted into the inflatable cavity of the intermediate cylinder from the rear end of the intermediate cylinder, and The front end of the center cylinder protrudes from the front end of the intermediate cylinder, and the outer surface of the center cylinder is in contact with the inwardly bent part of the front end of the intermediate cylinder; the base is fixed with the rear end of the outer cylinder; the outer cylinder of the push-pull device is fixed inside the rocket cabin section Or the outer wall, and the intermediate tube and the central tube can be protruded toward the front of the rocket cabin section, so as to apply a separation impulse to the force-receiving device fixed on the inner wall of the front stage section of the rocket cabin section.

In the above-mentioned separation system for a rocket cabin segment, preferably, the push-pull device further comprises: an end cap, and the end cap is fixed on the front end of the central cylinder extending out of the intermediate cylinder.

In the above separation system for a rocket cabin section, preferably, the front end surface of the end cap is set as a forward convex convex surface, and the portion of the force receiving device in contact with the end cap is set as an inwardly concave concave surface.

In the above-mentioned separation system for a rocket cabin segment, preferably, two nuts are threadedly connected to the part of the central cylinder extending out of the intermediate cylinder, and the two nuts are both arranged behind the end cap.

The separation system for the rocket cabin segment as described above, wherein, preferably, the number of the push-pull devices is two, the two push-pull devices are relatively fixed on the inner wall of the rocket cabin segment, and the two push-pull devices are distributed in the gas sides of the bottle.

The separation system for the rocket compartment section as described above, wherein, preferably, a vertical plate is attached and fixed on the inner wall of the rocket compartment section, and a vertical plate extending toward the interior of the rocket compartment section is vertically fixed on the side of the vertical plate facing the rear of the rocket compartment section. The bottom plate is provided with ribs between the bottom plate and the vertical plate; the bottom plate is provided with a through hole, the push-punch device is fixed on the base, and the pressure conveying pipeline passes through the through hole of the bottom plate and communicates with the push-punch device.

In the separation system of the rocket cabin as described above, preferably, the upper end of the push-pull device is fastened with a fixing hoop, and the fixing hoop is fixed to the vertical plate.

In the separation system for the rocket cabin as described above, preferably, the gas outlet of the gas cylinder is disposed toward the front of the rocket cabin.

The separation system for the rocket cabin segment as described above, preferably, further comprising: a controller; the controller is electrically connected to the on-off valve to control the opening of the on-off valve; The unlocking device is electrically connected to control the unlocking device to unlock.

A rocket, wherein the separation system of the rocket cabin section described in any one of the above is fixedly installed between two adjacent cabin sections on the rocket.

Compared with the above-mentioned background technology, the separation system of the rocket compartment provided by the utility model can avoid the use of pyrotechnic devices, so the safety is higher, and because the push-pull device has a three-layer cylinder, it can ensure a longer stroke, Therefore, the space inside the rocket compartment occupied by the push-pull device can be saved in the length direction, so some space in the diameter direction of the rocket compartment can be used, and increasing the diameter of the three-layer cylinder of the push-pull device will inevitably enhance the thrust of the center tube. , so as to ensure that there is sufficient separation impulse between the rocket compartments. In addition, using high-pressure gas as the separation energy, the separation impulse generated by it is also relatively stable, and the separation effect is also better.

Description of drawings

In order to more clearly illustrate the embodiments of the present utility model or the technical solutions in the prior art, the following briefly introduces the accompanying drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description These are just some embodiments described in the present invention, and for those of ordinary skill in the art, other drawings can also be obtained according to these drawings.

1 is a schematic diagram of a separation system for a rocket cabin section provided by an embodiment of the present application;

2 is a schematic structural diagram of a separation system for a rocket cabin section provided by an embodiment of the present application;

Fig. 3 is the fixing schematic diagram of the push-punch device provided by the embodiment of the present application;

4 is a schematic structural diagram of a push-punch device provided by an embodiment of the present application;

5 is a cross-sectional view of a push-punch device provided by an embodiment of the present application;

6 is a schematic diagram of a push-punch device according to an embodiment of the present application;

FIG. 7 is a schematic structural diagram of a force receiving device provided by an embodiment of the present application.

Detailed ways

The following describes in detail the embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals refer to the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary, and are only used to explain the present invention, but not to be construed as a limitation of the present invention.

The present application provides a separation system for a rocket cabin, as shown in Figures 1 and 2, comprising: a gas cylinder 1, a pressure delivery pipeline, an on-off valve 2, at least two push-pull devices (the push-pull device 31 and the push-pull device 31 and the push-pull device 31 and the push-pull device A punching device 32) and a force receiving device 7 (as shown in FIG. 7) matched with each pushing and punching device (that is, the number of the force receiving device 7 is the same as that of the pushing and punching device).

Wherein, the gas cylinder 1 is fixed inside the rocket cabin section 10 or on the outer wall of the rocket cabin section 10 , preferably fixed on the inner wall of the rocket cabin section 10 . Its interior is filled with high-pressure gas such as nitrogen or air, and in order to reduce the pressure loss when the pressure gas is transported in the pressure conveying pipeline connected to the gas cylinder 1, the gas outlet of the gas cylinder 1 is preferably directed toward the front of the rocket cabin section 10. The front mentioned here is the direction toward the rocket head, that is, the direction toward the rocket fairing, and the opposite rear is the direction toward the rocket tail. Of course, it can also be oriented in other directions, such as the horizontal direction. In order to facilitate the inflation of the gas cylinder 1 before the launch of the rocket, an inflation pipeline is also connected to the gas cylinder 1, and an inflation hand valve 5 is installed on the inflation pipeline (as shown in Figures 1 and 2).

The pressure delivery pipeline is connected from the gas outlet of the gas cylinder 1 to each push-pushing device. Preferably, the pressure delivery pipeline is fitted and fixed to the inner wall of the rocket cabin section 10 to ensure the fixed position of the pressure delivery pipeline. In order to ensure that the thrust of each push-pull device is the same and the reaction is synchronized, the parts of the pressure conveying pipeline leading to each push-pull device are identical to each other. .

Specifically, taking two push-pull devices (the push-pull device 31 and the push-punch device 32 ) as an example, the pressure conveying pipeline includes: a first pipeline 41 , a second pipeline 42 , a third pipeline 43 and a pipeline tee 44 ; The first pipe 41 extends from the gas outlet of the gas cylinder 1 toward the front of the rocket cabin section 10, and the first pipe 41 is communicated with the first port of the pipe tee 44; the second pipe 42 is connected with the pipe tee 44. The second port is communicated, and on the inner wall of the rocket cabin section 10, along the circumferential direction of the rocket cabin section 10, it extends to the push-pull device 31, and communicates with the push-pull device 31; the third pipe 43 and the pipe tee 44 The third port communicates and extends on the inner wall of the rocket compartment 10 along the circumferential direction of the rocket compartment 10 in a direction opposite to the second duct 42 to the push-pull device 32 and communicates with the push-pull device 32 .

The on-off valve 2 (usually can be an electric explosion valve or a solenoid valve) is arranged at the gas outlet of the gas cylinder 1 or on the pressure delivery pipeline to open or close the gas cylinder 1 and control the pressure gas in the gas cylinder 1 to lead to the pressure delivery pipe road. Specifically, when the push-flushing device 31 and the push-flushing device 32 are provided, the on-off valve 2 is connected between the gas cylinder 1 and the first pipeline 41 , or the on-off valve 2 is arranged on the first pipeline 41 . In addition, a pressure reducing valve 6 (as shown in Figure 1) can be set on the pressure delivery pipeline to reduce the high pressure gas output from the gas cylinder 1 to a predetermined pressure value, for example: reduce the pressure to 2MPa or 3MPa, to avoid direct pressure The high pressure gas output from the gas cylinder 1 causes damage to the push-flush device. The orifice plate can be installed into the pressure conveying pipeline as the pressure reducing valve 6, wherein the orifice plate is a metal sheet with a circular opening, the wall of the circular hole is at right angles to the front end of the orifice plate, and the axis of the orifice plate is connected to the pipeline during installation. The axes are concentric. On this basis, in addition, the on-off valve 2 and the pressure reducing valve 6 can also be integrated into an integrated valve for easy installation.

The push-pull device is fixed on the inner or outer wall of the rocket cabin section 10, and the push-pull device can protrude toward the front of the rocket cabin section 10 to apply separation to the force-bearing device fixed on the inner wall of the previous stage section of the rocket cabin section 10 Impulse. The front end of the rocket cabin section 10 is fixedly connected with the rear end of the previous stage section. As shown in Figure 2, the front end of the rocket cabin section 10 is extended with connecting wings, and the connecting wings are provided with connecting holes. The rear end of the first-stage cabin also extends outward with connecting wings, and the connecting wings also have corresponding connecting holes. The front end of the rocket cabin section 10 is butted with the rear end of the previous first-stage cabin section, and the two connecting wings are in contact with each other. , the two rocket cabin segments are fixedly connected by passing the unlocking device through the connecting hole. Of course, the connecting wings of the rocket cabin can also extend inward. At this time, a slot is formed on the connecting wings in front of the push-pull device, so that after the push-pull device is attached to the inner wall of the rocket cabin, the opening of the connecting wings can be opened. The groove portion protrudes forward.

Take two push-pull devices (the push-pull device 31 and the push-pull device 32) as an example. The push-pull device 31 and the push-pull device 32 are distributed on both sides of the gas cylinder 1 and fixed on the inner wall of the rocket cabin section 10. There is a relatively uniform separation force between the cabin sections, and the push-pull device 31 and the push-pull device 32 are arranged opposite each other. Specifically, the fixing method of the push-pull device and the rocket cabin section 10 is described by taking the push-pull device 31 as an example. As shown in FIG. 3 , a mounting seat 8 is fixed on the inner wall of the rocket cabin section 10 , and the mounting seat 8 includes a bottom plate 81 , ribs 82 and a vertical plate 83, the vertical plate 83 is fitted and fixed to the inner wall of the rocket cabin section 10, the bottom plate 81 and the vertical plate 83 are vertically fixed towards the rear side of the rocket cabin section 10, and the bottom plate 81 extends to the interior of the rocket cabin section 10, The rib 82 is provided between the bottom plate 81 and the vertical plate 82 . The bottom plate 81 has a through hole, the push-punch device 31 is fixed on the base 81 , and the pressure conveying pipeline passes through the through hole of the bottom plate 81 and communicates with the push-punch device 31 . In order to ensure that the position of the push-punch device does not change during operation, that is, the push-punch device moves in a predetermined direction, the mounting base 8 further includes a fixing hoop 84 , which fastens the upper end of the push-punch device 31 to the vertical plate 82 .

Taking the push-punch device 31 as an example, as shown in FIG. 4 , FIG. 5 and FIG. 6 , the push-punch device 31 includes: a base 311 , an outer cylinder 312 , a middle cylinder 313 , and a center cylinder 314 .

The outer tube 312 has an outer tube air-filled cavity that penetrates along the axial direction, and the front end of the outer tube 312 is bent inward by a predetermined distance; The front end is also bent inward by a predetermined distance; the center barrel 314 has a center barrel inflation cavity extending inward in the axial direction from the rear end of the center barrel 314 and not passing through.

The front end of the intermediate cylinder 313 is inserted into the outer cylinder inflatable cavity from the rear end of the outer cylinder 312, and the front end of the intermediate cylinder 313 is in contact with the bent part of the front end of the outer cylinder 312, and the rear end of the intermediate cylinder 313 is completely accommodated in the outer cylinder inflatable cavity . The front end of the center cylinder 314 is inserted into the inflatable cavity of the intermediate cylinder 313 from the rear end of the intermediate cylinder 313 , and the front end of the center cylinder 314 protrudes from the front end of the intermediate cylinder 313 . In contact, the rear end of the central barrel 314 is fully received into the intermediate barrel inflatable cavity.

The base 311 is fixed to the rear end of the outer cylinder 312 and closes the rear end of the outer cylinder 312 . Specifically, the front end of the base 311 is recessed inwardly with a accommodating cavity, the outer wall surface of the side wall of the accommodating cavity has an outer thread, the inner surface of the rear end of the outer cylinder 312 has an inner thread, and the outer thread of the side wall of the base 311 is connected to the rear of the outer cylinder 312 The inner threads of the ends are matched to fix the base 311 and the outer cylinder 312 . In addition, the base 311 has ventilation holes penetrating both sides, so as to communicate the inflation chambers of the outer cylinder 312 , the middle cylinder 313 and the center cylinder 314 with the pressure conveying pipeline through the ventilation holes.

In addition, in order to ensure the sealing performance of the push-punch device, a sealing ring is provided at the position where the rear end of the intermediate cylinder 313 contacts the inner wall of the outer cylinder 312, and a sealing ring is also provided at the position where the rear end of the central cylinder 314 contacts the inner wall of the intermediate cylinder. Preferably, a double-channel dynamic seal is provided at the position where the rear end of the intermediate cylinder 313 contacts the inner wall of the outer cylinder 312 and the position where the rear end of the central cylinder 314 contacts the inner wall of the intermediate cylinder. Specifically, the rear end of the intermediate cylinder 313 is bent outward by a predetermined distance, and the bent portion is in contact with the inner wall of the outer cylinder 312; the rear end of the central cylinder 314 is bent outward by a predetermined distance, and the bent portion is in contact with the intermediate cylinder The inner wall of 313 is in contact; the outwardly bent portion of the rear end of the intermediate cylinder 313 has an inward groove, and a sealing ring, preferably an O-shaped sealing ring, is arranged in the groove, so as to make the gap between the intermediate cylinder 131 and the outer cylinder 132 It has good sealing performance; the outwardly bent part of the rear end of the central cylinder 314 has an inward groove, and a sealing ring is arranged in the groove, preferably an O-shaped sealing ring, so that the central cylinder 314 and the intermediate cylinder 313 There is good sealing between them.

In order to further ensure the tightness, the part of the outer cylinder 312 in contact with the base 311 is provided with a sealing ring. The rear end of the outer cylinder 312 has a groove concave from the back to the front, and a sealing ring, preferably an O-shaped sealing ring, is arranged in the groove. the groove at the end to squeeze the sealing ring in the groove.

In addition, the end cap 317 can also be fixed on the front end of the center cylinder 314 extending out of the middle cylinder 313. Preferably, the end cap 317 is screwed to the front end of the center cylinder 314, and the end cap 317 can be screwed into the center cylinder 314 by adjusting the end cap 317. The position of the front end, so that the length of the push-punch device can be adjusted. When the push-pull device 31 is actuated, the end cap 317 is brought into contact with the force-receiving device 7 (as shown in FIG. 7 ) fixed on the inner wall of the preceding stage of the rocket compartment 10, and a separation impulse is applied to the force-receiving device. In order to ensure the centering of the contact between the end cap 317 and the force-receiving device 7, the front end surface of the end cap 317 is set as a convex surface that protrudes forward, and the part of the force-receiving device 7 in contact with the end cap 317 is set to face Concave concave surface.

4 and 5, two nuts (nut 315 and nut 316) are threadedly connected to the part of the central cylinder 314 extending out of the intermediate cylinder 313, and the nut 315 and the nut 316 are both arranged behind the end cap 317, In order to prevent loosening and adjust the height, in order to facilitate the installation and adjustment of the nut, the nut is preferably set as a hexagonal nut.

In addition, the separation system for the rocket cabin section provided by the present application also includes: a controller (not shown in the figure), which controls the opening of the on-off valve 2 to fill the push-pull device with the high-pressure gas stored in the gas cylinder 1 through the pressure conveying pipeline And after it is detected that the gas pressure in the pressure delivery pipeline and the inflatable cavity of the push-pull device reaches a predetermined value, or after the switch valve is opened for a predetermined time, the unlocking device ( For example, explosion bolts, etc.) are unlocked, and the push-pull device extends the force-bearing device fixed on the inner wall of the upper-stage rocket cabin section to apply a separation impulse, so that the two sections of the rocket can be quickly separated.

The above-mentioned predetermined time can be tested on the ground for the separation system of the above-mentioned rocket cabin, and the time is measured after the opening and closing valve is opened, and it is detected that the gas pressure in the pressure conveying pipeline and the inflatable cavity of the push-pull device reaches the required value. When the rocket is launched, stop timing, and set the recorded time as a predetermined time value in the controller, so as to control the unlocking time of the unlocking device by a predetermined time during the rocket launch.

Specifically, the time from opening the on-off valve to the change of the inlet pressure of the push-pull device is the system response time t1, and the time for the inlet air pressure of the push-pull device to reach the required value from 0 is the pressure holding time t2, then from the opening of the on-off valve to the push-pull device The time between the inlet air pressure of the punching device reaching the required value is the unlocking time t0=t1+t2, that is, the predetermined time value to be set in the controller, and the predetermined time value is preferably 500-600 ms.

Since the separation system of the rocket cabin section provided by the present application avoids the use of pyrotechnic devices, the safety is high, and because the push-pull device of the present application has three layers of cylinders, it can ensure a long stroke, so in the length direction The space inside the rocket compartment occupied by the thruster can be saved, so some space in the diameter direction of the rocket compartment can be used, and increasing the diameter of the three-layer cylinder of the thruster will inevitably increase the thrust of the center cylinder, which will also increase the thrust of the center cylinder. It can ensure that there is sufficient separation impulse between the rocket compartments. In addition, using high-pressure gas as the separation energy, the separation impulse generated by it is also relatively stable, and the separation effect is also better.

The present application also provides a rocket, the separation system of the rocket cabin section is fixedly installed between two adjacent cabin sections on the rocket, and the separation system of the rocket cabin section is used as a booster for the separation of the carrier Energy, providing a moderate separation impulse for the separation of the rocket compartment.

It will be apparent to those skilled in the art that the present invention is not limited to the details of the above-described exemplary embodiments, and that the present invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the present invention. Therefore, the embodiments are to be considered in all respects as exemplary and not restrictive, and the scope of the present invention is defined by the appended claims rather than the foregoing description, and it is therefore intended that the All changes within the meaning and range of the required equivalents are embraced within the present invention. Any reference signs in the claims shall not be construed as limiting the involved claim.

In addition, it should be understood that although this specification is described in terms of embodiments, not each embodiment only includes an independent technical solution, and this description in the specification is only for the sake of clarity, and those skilled in the art should take the specification as a whole , the technical solutions in each embodiment can also be appropriately combined to form other implementations that can be understood by those skilled in the art.

Claims (10)

1. A separation system for a rocket cabin, comprising: a gas cylinder, a pressure delivery pipeline, an on-off valve, at least two push-pull devices and a force-receiving device that cooperates with each push-pull device; The gas cylinder is fixed on the inner or outer wall of the rocket compartment; The pressure conveying pipeline is communicated from the air outlet of the gas cylinder to each push-pull device, and the parts of the pressure conveying pipeline leading to each push-pull device are identical to each other; The on-off valve is arranged at the gas outlet of the gas cylinder or on the pressure delivery pipeline, and controls the pressure gas in the gas cylinder to lead to the pressure delivery pipeline; The pushing and punching device comprises: a base, an outer cylinder, a middle cylinder and a central cylinder with an inflatable cavity extending inward from the rear end and not passing through; the front end of the intermediate cylinder is inserted into the through-penetrating outer cylinder inflatable cavity from the rear end of the outer cylinder, and The front end of the intermediate cylinder is in contact with the inwardly bent part of the front end of the outer cylinder; the front end of the central cylinder is inserted into the inflatable cavity of the intermediate cylinder from the rear end of the intermediate cylinder, and the front end of the central cylinder protrudes from the front end of the intermediate cylinder, and the outer The surface is in contact with the inwardly bent part of the front end of the intermediate cylinder; the base is fixed with the rear end of the outer cylinder; The outer cylinder of the push-pull device is fixed on the inner or outer wall of the rocket cabin, and the intermediate cylinder and the central cylinder can protrude toward the front of the rocket cabin to apply force to the force-bearing device fixed on the inner wall of the previous stage of the rocket cabin. Separate impulse. 2 . The separation system of the rocket cabin section according to claim 1 , wherein the push-pull device further comprises: an end cap, the end cap being fixed on the front end of the central cylinder extending out of the intermediate cylinder. 3 . 3 . The separation system of the rocket cabin section according to claim 2 , wherein the front end surface of the end cap is set as a convex surface that protrudes forward, and the part of the force receiving device in contact with the end cap is set as an inward concave surface. 4 . Concave. 4. The separation system of the rocket cabin section according to claim 2 or 3, characterized in that, two nuts are threadedly connected to the part of the central cylinder extending out of the intermediate cylinder, and the two nuts are both provided with the end caps. rear. 5. The separation system of the rocket cabin section according to any one of claims 1-3, wherein the number of the push-pull devices is two, and the two push-pull devices are relatively fixed on the inner wall of the rocket cabin section, and Two push-flush devices are distributed on both sides of the cylinder. 6. The separation system of the rocket cabin section according to any one of claims 1-3, wherein the inner wall of the rocket cabin section is fitted and fixed with a vertical plate, and the vertical plate facing the rear side of the rocket cabin section is vertically fixed with a vertical plate. The bottom plate extending to the interior of the rocket cabin is provided with ribs between the bottom plate and the vertical plate; the bottom plate has a through hole, the push-punch device is fixed on the base, and the pressure conveying pipeline passes through the through hole of the bottom plate and the pusher. The flushing device is connected. 7 . The separation system of the rocket compartment according to claim 6 , wherein the upper end of the push-pull device is fastened with a fixing hoop, and the fixing hoop is fixed to the vertical plate. 8 . 8 . The separation system of the rocket cabin section according to claim 1 , wherein the gas outlet of the gas cylinder is disposed toward the front of the rocket cabin section. 9 . 9 . The separation system of a rocket cabin section according to claim 1 , further comprising: a controller; the controller is electrically connected to the switch valve to control the opening of the switch valve; and the controller is connected to the fixed The unlocking devices of two adjacent rocket cabin sections are electrically connected to control the unlocking of the unlocking devices. 10. A rocket, characterized in that the separation system of the rocket cabin section according to any one of the preceding claims 1-9 is fixedly installed between two adjacent cabin sections on the rocket.

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