阅读说明：本技术 用于运载火箭中级间分离的气动分离系统 (Pneumatic separation system for interstage separation in launch vehicles ) 是由 秦春云 郭凤明 刘建 戴政 张蕾 任彦婷 杜正刚 于 2019-02-13 设计创作，主要内容包括：本申请提供了一种用于运载火箭中级间分离的气动分离系统,其包括至少一个气瓶、气源输出开关和至少一个气缸；气瓶通过充气管路连接气缸,气源输出开关设置在充气管路上,以控制充气管路的通断；在上面级箭体上设置有传力装置,传力装置与气缸中的气动推杆匹配设置；气瓶安装在分离子级箭体的前底上或级间段上；气瓶用于充入具有预设压力的压缩气体,且在气源输出开关打开时,气瓶中存储的压缩气体在经充气管路后通过气缸中的气动推杆和传力装置推动运载火箭的上面级箭体与分离子级箭体之间彼此分离。本申请有利于分离子级箭体的回收复用；能够节省试验成本；原理可靠,结构简单,通用性好。(The application provides a pneumatic separation system for interstage separation in a launch vehicle, which comprises at least one gas cylinder, a gas source output switch and at least one cylinder; the gas cylinder is connected with the cylinder through an inflation pipeline, and the gas source output switch is arranged on the inflation pipeline so as to control the on-off of the inflation pipeline; a force transmission device is arranged on the upper arrow body and is matched with a pneumatic push rod in the air cylinder; the gas cylinder is arranged on the front bottom or the stage section of the separation sub-stage arrow body; the gas cylinder is used for being filled with compressed gas with preset pressure, and when the gas source output switch is opened, the compressed gas stored in the gas cylinder pushes the upper rocket body and the separation sub-rocket body of the carrier rocket to be separated from each other through the pneumatic push rod and the force transmission device in the cylinder after passing through the gas charging pipeline. The method is beneficial to recycling of the separated sub-stage arrow body; the test cost can be saved; the principle is reliable, the structure is simple, and the universality is good.)

1. A pneumatic separation system for interstage separation in a launch vehicle is characterized by comprising at least one gas cylinder, a gas source output switch and at least one cylinder;

the gas cylinder is connected with the cylinder through an inflation pipeline, and the gas source output switch is arranged on the inflation pipeline so as to control the on-off of the inflation pipeline;

a force transmission device is arranged on the upper arrow body and is matched with a pneumatic push rod in the air cylinder; the gas cylinder is arranged on the front bottom or the stage section of the separation sub-stage arrow body;

the gas cylinder is used for filling compressed gas with preset pressure, and when the gas source output switch is opened, the compressed gas stored in the gas cylinder pushes the upper rocket body and the separation sub-rocket body of the carrier rocket to be separated from each other through the pneumatic push rod and the force transmission device in the gas cylinder after passing through the gas charging pipeline.

2. A pneumatic separation system for interstage separation in a launch vehicle according to claim 1 wherein when there is only one interstage structure of primary nozzle configuration in the upper stage rocket body of the launch vehicle, there are more than two cylinders, and more than two cylinders are distributed evenly on the interstage separation plane between the stage section and the rear short shell of the upper stage; the force transfer device is fixedly connected to the upper rocket body close to the interstage separation surface;

and a pneumatic push rod in the cylinder acts thrust on the force transmission device to realize the separation between the upper arrow body and the separation sub-arrow body.

3. A pneumatic separation system for interstage separation in a launch vehicle according to claim 1 wherein when there is only one interstage structure in a primary nozzle configuration in an upper stage rocket body of the launch vehicle, there is one cylinder disposed at an engine primary nozzle in the upper stage rocket body; the force transmission device is an engine main nozzle in the upper-stage arrow body;

and a pneumatic push rod in the cylinder acts thrust on the force transmission device to realize the separation between the upper arrow body and the separation sub-arrow body.

4. A pneumatic separation system for interstage separation in a launch vehicle according to claim 2 or 3 wherein the cylinder is fixed using a fixed support of a regular triangular platform structure when the cylinder is mounted on the front bottom of the separation sub-stage rocket body; the number of the gas cylinders is six, every two gas cylinders form one group, and two adjacent groups of the gas cylinders are uniformly arranged at intervals of 120 degrees around the axis of the carrier rocket in the flight direction.

5. A pneumatic separation system for interstage separation in a launch vehicle according to claim 2 or 3 wherein the cylinder is fixed using a fixed bracket of a regular quadrangular frustum of a prism structure when the cylinder is mounted on the stage section; the number of the gas cylinders is eight, and every two gas cylinders form a group; the gas cylinders of each group are arranged evenly at 90 DEG intervals around the axis of the direction of flight of the carrier rocket.

6. A pneumatic separation system for interstage separation in a launch vehicle according to claim 1 wherein when there are a plurality of interstage structures of primary nozzle configuration in the upper stage rocket body of the launch vehicle, the number of cylinders is set to two or more, and the two or more cylinders are evenly distributed on the interstage separation plane between the stage section and the rear short shell of the upper stage; the force transfer device is fixedly connected to the upper rocket body close to the interstage separation surface;

and a pneumatic push rod in the cylinder acts thrust on the force transmission device to realize the separation between the upper arrow body and the separation sub-arrow body.

7. A pneumatic separation system for interstage separation in a launch vehicle according to claim 6 wherein there are eight of said cylinders, four of said cylinders, one group of two of said cylinders, two adjacent groups of said cylinders for uniform placement at 90 ° intervals about the axis of the direction of flight of the launch vehicle; the four cylinders are all arranged on the stage section, each cylinder is used for being uniformly arranged around the axis of the carrier rocket in the flying direction at intervals of 90 degrees, and a group of gas cylinders are arranged between every two adjacent cylinders.

8. A pneumatic separation system for interstage separation in a launch vehicle according to claim 1, 2 or 3 wherein a cylinder pressure sensing gauge is further provided on the gas charging line connecting the cylinder with a gas source output switch, the cylinder pressure sensing gauge being used to sense the pressure of compressed gas output by the cylinder.

9. A pneumatic separation system for interstage separation in a launch vehicle according to claim 1, 2 or 3 wherein an inflation and deflation port is provided at one end of the inflation line connected to the gas cylinder, and a mechanical inflation switch is provided on the inflation line connected to the inflation and deflation port and the gas cylinder.

10. A pneumatic separation system for interstage separation in a launch vehicle according to claim 1, 2 or 3 wherein one end of said cylinder is provided with a first pressure gauge and the other end thereof is provided with a second pressure gauge; the first pressure detection meter is used for detecting the pressure of the cylinder inflation cavity, and the second pressure detection meter is used for detecting the pressure of the cylinder exhaust cavity.

Technical Field

The application belongs to the technical field of carriers, and particularly relates to a pneumatic separation system for inter-stage separation in a carrier rocket.

Background

With the continuous progress of science and technology, the launch vehicle as a vehicle is advancing from a single use stage to a plurality of repeated use stages. In order to realize repeated use of the carrier rocket, the separated sub-stage rocket bodies of the carrier rocket need to be recovered.

For the separation sublevel recovery multiplexing type carrier rocket, on the premise of ensuring the flight safety and reliability of the carrier rocket, the adverse effects on the separation sublevel structure, the attitude and the like of the carrier rocket during the whole flight mission period are reduced as much as possible. In order to avoid the impact of the interstage separation on the heat flow of the separation sub-stage, the interstage separation of the separation sub-stage recovery multiplexing type carrier rocket adopts cold separation. At present, the impulse device adopted by cold separation of domestic carrier rockets is generally a solid small rocket.

The small solid rocket is fixedly connected with the separating sub-stage rocket body, and the separating sub-stage rocket body is separated from the upper stage rocket body by reverse thrust generated by the ignition work of the small solid rocket in the separating process. However, the solid small rocket belongs to initiating explosive devices, the energy is concentrated, and the heat flow of the solid small rocket can seriously wash the separated sub-stage rocket body in the separation process, which can seriously affect the repeated use of the separated sub-stage rocket body after recovery. In addition, although the small solid rocket is generally applied to domestic carrier rockets at the present stage, the small solid rocket has the defect that the performance cannot be directly detected, and the performance of the products on the rocket can be bytestified only by increasing the production quantity of initiating explosive devices in the same batch and then extracting a sufficient quantity of products to carry out ground ignition tests. Such consumable tests are not only costly but also still do not allow direct detection of the performance of the arrow-up product. And the initiating explosive devices are all produced by professional manufacturers, so that the difficulty of reducing the cost is high.

Disclosure of Invention

To overcome, at least to some extent, the problems of the related art, the present application provides a pneumatic separation system for interstage separation in a launch vehicle.

According to an embodiment of the present application, there is provided a pneumatic separation system for inter-stage separation in a launch vehicle comprising at least one gas cylinder, a gas source output switch, and at least one gas cylinder;

the gas cylinder is connected with the cylinder through an inflation pipeline, and the gas source output switch is arranged on the inflation pipeline so as to control the on-off of the inflation pipeline;

a force transmission device is arranged on the upper arrow body and is matched with a pneumatic push rod in the air cylinder; the gas cylinder is arranged on the front bottom or the stage section of the separation sub-stage arrow body;

the gas cylinder is used for filling compressed gas with preset pressure, and when the gas source output switch is opened, the compressed gas stored in the gas cylinder pushes the upper rocket body and the separation sub-rocket body of the carrier rocket to be separated from each other through the pneumatic push rod and the force transmission device in the gas cylinder after passing through the gas charging pipeline.

In the pneumatic separation system for the interstage separation in the carrier rocket, when only one interstage structure in the upper stage rocket body of the carrier rocket has a main nozzle configuration, more than two cylinders are arranged, and the more than two cylinders are locally and uniformly distributed on the interstage separation surface between the interstage section and the rear short shell of the upper stage; the force transfer device is fixedly connected to the upper rocket body close to the interstage separation surface;

and a pneumatic push rod in the cylinder acts thrust on the force transmission device to realize the separation between the upper arrow body and the separation sub-arrow body.

In the pneumatic separation system for the interstage separation in the carrier rocket, when only one interstage structure in the configuration of the main spray pipe is arranged in the upper stage rocket body of the carrier rocket, one air cylinder is arranged, and the air cylinder is arranged at the main spray pipe of the engine in the upper stage rocket body; the force transmission device is an engine main nozzle in the upper-stage arrow body;

and a pneumatic push rod in the cylinder acts thrust on the force transmission device to realize the separation between the upper arrow body and the separation sub-arrow body.

Further, when the gas cylinder is arranged on the front bottom of the separation sub-grade arrow body, the gas cylinder is fixed by a fixing support with a regular triangular platform structure; the number of the gas cylinders is six, every two gas cylinders form one group, and two adjacent groups of the gas cylinders are uniformly arranged at intervals of 120 degrees around the axis of the carrier rocket in the flight direction.

Further, when the gas cylinder is arranged on the stage section, the cylinder is fixed by a fixing support with a regular quadrangular frustum pyramid structure; the number of the gas cylinders is eight, and every two gas cylinders form a group; the gas cylinders of each group are arranged evenly at 90 DEG intervals around the axis of the direction of flight of the carrier rocket.

In the above pneumatic separation system for interstage separation in a launch vehicle, when a plurality of interstage structures in a main nozzle configuration exist in an upper stage rocket body of the launch vehicle, the number of the cylinders is more than two, and the more than two cylinders are uniformly distributed on an interstage separation surface between a interstage section and an upper stage rear short shell; the force transfer device is fixedly connected to the upper rocket body close to the interstage separation surface;

and a pneumatic push rod in the cylinder acts thrust on the force transmission device to realize the separation between the upper arrow body and the separation sub-arrow body.

Furthermore, eight gas cylinders are arranged, four gas cylinders are arranged, every two gas cylinders form one group, and two adjacent groups of gas cylinders are uniformly arranged at intervals of 90 degrees around the axis of the carrier rocket in the flight direction; the four cylinders are all arranged on the stage section, each cylinder is used for being uniformly arranged around the axis of the carrier rocket in the flying direction at intervals of 90 degrees, and a group of gas cylinders are arranged between every two adjacent cylinders.

In the pneumatic separation system for the interstage separation of the carrier rocket, the gas cylinder pressure detection meter is further arranged on the gas charging pipeline, which is connected with the gas source output switch, and is used for detecting the pressure of the compressed gas output by the gas cylinder.

In the pneumatic separation system for the interstage separation of the carrier rocket, one end of the inflation pipeline connected with the gas cylinder is provided with the inflation and deflation port, and the inflation pipeline connected with the inflation and deflation port and the gas cylinder is provided with the mechanical inflation switch.

In the pneumatic separation system for the intermediate separation of the carrier rocket, one end of the air cylinder is provided with a first pressure detection meter, and the other end of the air cylinder is provided with a second pressure detection meter; the first pressure detection meter is used for detecting the pressure of the cylinder inflation cavity, and the second pressure detection meter is used for detecting the pressure of the cylinder exhaust cavity.

According to the above embodiments of the present application, at least the following advantages are obtained: this application is arranged in carrier rocket interstage separation's pneumatic separation system, through setting up gas cylinder, air supply output switch and cylinder, fills compressed gas in the gas cylinder, opens air supply output switch, and the gas cylinder produces thrust through the pneumatic push rod in the cylinder, for the interstage separation energy of carrying rocket, and this application can avoid the small solid rocket to ignite to erode the plume of the arrow body of separation son, is favorable to the used repeatedly of the arrow body of separation son.

The pneumatic separation system for the interstage separation in the carrier rocket can avoid the defect that the performance of initiating explosive devices cannot be directly detected, and can directly detect the performance, so that the cost of product production and ground ignition test increased for performing a side evidence test on the performance of flight test products is avoided.

The pneumatic separation system for the interstage separation in the carrier rocket has the advantages of reliable principle, simple structure and good universality, and can be applied to the separation of the fairing of the carrier rocket and the separation process of the effective load. The method can play a positive role in recycling and reusing the carrier rocket and controlling the cost of the carrier rocket.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the scope of the invention, as claimed.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of the specification of the application, illustrate embodiments of the application and together with the description, serve to explain the principles of the application.

Fig. 1 is a schematic structural diagram of a pneumatic separation system for inter-stage separation in a launch vehicle according to an embodiment of the present application.

Fig. 2 is a schematic structural diagram of a pneumatic separation system for interstage separation in a launch vehicle, provided in an embodiment of the present application, in an interstage separation structure of a gas cylinder and a pneumatic push rod in a single-cylinder state.

Fig. 3 is a schematic structural diagram of a pneumatic separation system for inter-stage separation in a launch vehicle according to an embodiment of the present application, in which gas bottles are mounted on the front bottom of a separation sub-stage rocket body in a single-cylinder state, wherein the flight direction of the launch vehicle is perpendicular to the paper.

Fig. 4 is a schematic structural diagram of a pneumatic separation system for inter-stage separation in a launch vehicle according to an embodiment of the present application, in which gas cylinders are installed in a stage section in a single-cylinder state, wherein a flight direction of the launch vehicle is perpendicular to a paper surface.

Fig. 5 is a schematic structural diagram of a pneumatic separation system for interstage separation in a launch vehicle according to an embodiment of the present application, in which a gas cylinder and a pneumatic push rod are installed in an interstage structure in a multi-cylinder state, wherein the pneumatic push rod acts on an rocket body support.

Fig. 6 is a second schematic structural view of a pneumatic separation system for interstage separation in a launch vehicle according to an embodiment of the present application, in which a gas cylinder and a pneumatic push rod are installed in an interstage structure in a multi-cylinder state, wherein the pneumatic push rod acts on an rocket body support.

Description of reference numerals:

1. a gas cylinder; 2. an air source output switch; 3. a cylinder; 31. a cylinder push rod; 4. an inflation pipeline; 5. a pipeline at the front end of the spray pipe; 6. a gas cylinder pressure detection meter; 7. an air discharge port; 8. a mechanical inflation switch; 9. an interface; 10. a first pressure detection gauge; 11. a second pressure detection gauge; 12. a force transfer device; 13. and fixing the bracket.

Detailed Description

For the purpose of promoting a clear understanding of the objects, aspects and advantages of the embodiments of the present application, reference will now be made to the accompanying drawings and detailed description, wherein like reference numerals refer to like elements throughout.

The illustrative embodiments and descriptions of the present application are provided to explain the present application and not to limit the present application. Additionally, the same or similar numbered elements/components used in the drawings and the embodiments are used to represent the same or similar parts.

As used herein, "first," "second," …, etc., are not specifically intended to mean in a sequential or chronological order, nor are they intended to limit the application, but merely to distinguish between elements or operations described in the same technical language.

With respect to directional terminology used herein, for example: up, down, left, right, front or rear, etc., are simply directions with reference to the drawings. Accordingly, the directional terminology used is intended to be illustrative and is not intended to be limiting of the present teachings.

As used herein, the terms "comprising," "including," "having," "containing," and the like are open-ended terms that mean including, but not limited to.

As used herein, "and/or" includes any and all combinations of the described items.

References to "plurality" herein include "two" and "more than two"; reference to "multiple sets" herein includes "two sets" and "more than two sets".

As used herein, the terms "substantially", "about" and the like are used to modify any slight variation in quantity or error that does not alter the nature of the variation. In general, the range of slight variations or errors that such terms modify may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. It should be understood by those skilled in the art that the aforementioned values can be adjusted according to actual needs, and are not limited thereto.

Certain words used to describe the present application are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art in describing the present application.

The pneumatic separation system for interstage separation in a launch vehicle can provide energy for interstage separation of a launch vehicle.

As shown in fig. 1, the pneumatic separation system for interstage separation in a launch vehicle provided by the present embodiment includes at least one gas cylinder 1, a gas source output switch 2, and at least one gas cylinder 3. Each gas cylinder 1 is connected with an inflation pipeline 4, and the gas cylinders 1 are connected with one end of a gas source output switch 2 through the inflation pipelines 4. The other end of the air source output switch 2 is connected with each cylinder 3 through a spray pipe front end pipeline 5.

The upper arrow body is provided with a force transmission device 12, and the force transmission device 12 is matched with a pneumatic push rod 31 in the air cylinder 3.

The gas cylinder 1 is used for being filled with compressed gas with preset pressure, and when the gas source output switch 2 is opened, the compressed gas stored in the gas cylinder 1 pushes the force transmission device through the pneumatic push rod 31 in the gas cylinder 3 after passing through the gas charging pipeline 4, so that the upper rocket body and the separation sub-rocket body of the carrier rocket are separated from each other.

Wherein, the gas cylinder 1 is arranged on the front bottom or the stage section of the separation sub-stage arrow body.

For the interstage structure having only one main nozzle configuration in the upper stage arrow body, more than two cylinders 3, i.e., a multi-cylinder state, may be used. More than two cylinders 3 are uniformly distributed on the interstage separation surface between the interstage section and the rear short shell of the upper stage. The force transfer device 12 is fixedly connected to the upper stage arrow body and is close to the stage separation surface. The pneumatic push rod 31 in the cylinder 3 acts the thrust on the force transmission device 12 to realize the separation between the upper arrow body and the separation sub-arrow body.

The force transmission device 12 is a force transmission support which is fixedly connected to the upper arrow body and is close to the interstage separation surface.

Of course, as shown in fig. 2, for the interstage structure having only one main nozzle configuration in the upper stage arrow body, it is also possible to use one cylinder 3, i.e., a single-cylinder state. The cylinder 3 is disposed at the main nozzle of the engine in the upper stage arrow body. The force transmission device 12 is specifically an engine main nozzle in the upper arrow body, and the engine main nozzle has the function equivalent to that of a force transmission support. The pneumatic push rod 31 in the cylinder 3 acts the thrust on the force transmission device 12 to realize the separation between the upper arrow body and the separation sub-arrow body.

As shown in fig. 3, when the gas cylinder 1 is mounted on the front bottom of the separation sub-arrow body, the gas cylinder 3 is fixed by a fixing bracket 13 having a regular triangular platform structure. In this embodiment, the pneumatic separation system for interstage separation in a launch vehicle comprises six gas cylinders 1, and each two gas cylinders 1 are in one group and divided into three groups. Two adjacent groups of gas cylinders 1 are arranged evenly at 120 ° intervals around the axis of the direction of flight of the launch vehicle.

As shown in fig. 4, when the gas cylinder 1 is mounted on the stage section, the cylinder 3 is fixed using a fixing bracket 13 of a regular quadrangular frustum pyramid structure. In the present embodiment, the pneumatic separation system for interstage separation in a launch vehicle comprises eight gas cylinders 1, and each two gas cylinders 1 are divided into four groups. The gas cylinders 1 of each group are intended to be arranged evenly at 90 ° intervals around the axis of the direction of flight of the launch vehicle.

As shown in fig. 5, for the inter-stage structure in which a plurality of main nozzle configurations exist in the upper stage arrow body, two or more cylinders 3, i.e., a multi-cylinder state, may be used, and the two or more cylinders 3 are uniformly distributed on the inter-stage separation plane between the inter-stage section and the rear short shell of the upper stage. The force transfer device 12 is fixedly connected to the upper stage arrow body and is close to the stage separation surface. The pneumatic push rod 31 in the cylinder 3 acts the thrust on the force transmission device 12 to realize the separation between the upper arrow body and the separation sub-arrow body.

The force transmission device 12 is a force transmission support which is fixedly connected to the upper arrow body and is close to the interstage separation surface.

As shown in fig. 6, the pneumatic separation system for interstage separation in a launch vehicle comprises eight gas cylinders 1 and four gas cylinders 3, and each two gas cylinders 1 are divided into four groups. Two adjacent groups of gas cylinders 1 are arranged evenly at 90 ° intervals around the axis of the direction of flight of the launch vehicle. Four cylinders 3 are all arranged on the stage section, each cylinder 3 is used for being uniformly arranged at intervals of 90 degrees around the axis of the flight direction of the carrier rocket, and a group of gas cylinders 1 are arranged between every two adjacent cylinders 3.

In the preparation stage of the carrier rocket taking off, compressed gas is filled into the gas bottle 1 through the air charging and discharging port 7 to reach the required pressure. The compressed gas may be one or more of compressed air, nitrogen, helium and the like.

When the carrier rocket carries out interstage separation, the air source output switch 2 is opened, the inflation cavity of the air cylinder 3 is pressurized, and the pneumatic push rod 31 pushes the force transmission device 12 on the upper stage rocket body to separate the upper stage rocket body from the separation sub-stage rocket body. When the pneumatic ram 31 reaches its stroke and stops moving, there is a relative velocity between the upper stage arrow body and the separation sub-stage arrow body. The upper arrow body and the separation sub-arrow body respectively continue to move until the interstage separation is completed, the force transmission device 12 is launched out along with the upper arrow body, and the pneumatic separation system returns to the ground along with the separation sub-arrow body.

In this embodiment, a gas cylinder pressure detection meter 6 is further arranged on the gas charging pipeline 4 connecting the gas cylinder 1 and the gas source output switch 2, and the gas cylinder pressure detection meter 6 is used for detecting the pressure of the compressed gas output by the gas cylinder 1. The pressure detected by the gas cylinder pressure detection meter 6 can be used for carrying out quantitative analysis on whether the system is normal or not. It is understood that the cylinder pressure detecting gauge 6 may be connected to the cylinder pressure monitoring apparatus through a cable.

In this embodiment, an inflation/deflation port 7 is provided at one end of the inflation line 4 connected to the gas cylinder 1. A mechanical inflation switch 8 is arranged on the inflation pipeline 4 which is connected with the inflation and deflation port 7 and the gas bottle 1. In the preparation stage of the carrier rocket taking off, the mechanical inflation switch 8 can be opened, and compressed gas is filled into the gas cylinder 1 through the inflation and deflation port 7.

In addition, a connector 9 can be arranged on an inflation pipeline 4 connected with the mechanical inflation switch 8 and the gas bottle 1, and the gas bottle 1 is connected with the rocket body pressurizing and conveying system through the connector 9, so that the gas source sharing of the pneumatic separation system and the rocket body pressurizing and conveying system for the interstage separation in the carrier rocket can be realized. When the gas bottle 1 is connected with the rocket body pressurizing and conveying system, in order to ensure the normal work of the rocket body pressurizing and conveying system, the type of compressed gas required to be filled in the gas bottle 1 can be determined according to the type of gas required by the rocket body pressurizing and conveying system.

In the present embodiment, one end of the cylinder 3 is provided with a first pressure detection gauge 10, and the other end thereof is provided with a second pressure detection gauge 11. Wherein, the first pressure detecting meter 10 is used for detecting the pressure of the air charging cavity of the cylinder 3, and the second pressure detecting meter 11 is used for detecting the pressure of the air discharging cavity of the cylinder 3. By providing the first pressure detecting gauge 10 and the second pressure detecting gauge 11, the pressure changes of the charging chamber and the exhaust chamber of the cylinder 3 can be measured, thereby detecting whether the operating state of the cylinder 3 is normal. It is understood that the first pressure detection gauge 10 and the second pressure detection gauge 11 may be connected to the cylinder 3 pressure monitoring apparatus by a cable.

It can be understood that the magnitude of the separating force can be determined according to the initial state before separation and the requirements of the separation process, so as to determine the requirements of the cylinder diameter, the charging pressure and the like of the cylinder 3, further calculate the gas consumption, and determine the volume of the required gas cylinder 1 and the initial charging pressure of the gas cylinder 1.

The gas cylinder 1 is connected with the gas charging pipeline 4 through threads, and a sealing piece is arranged at the joint of the gas cylinder and the gas charging pipeline, so that the gas cylinder has sealing performance. The cylinder 3 and the spray pipe front end pipeline 5 are in threaded connection or welded, and a sealing piece is arranged at the joint when the threaded connection is adopted, so that the sealing performance is achieved.

In the final assembly test process of the pneumatic separation system for the interstage separation in the carrier rocket, the gas cylinder 1 can be inflated before the separation surfaces are not connected, the gas source output switch 2 is opened, whether the gas cylinder 3 works normally or not is checked, and whether the system works normally or not can be quantitatively analyzed through the pressure detected by the gas cylinder pressure detection meter 6; in actual flight conditions, whether the system works normally can be judged through analysis of the telemetered pressure signals.

The utility model provides a pneumatic piece-rate system for stage separation in carrier rocket is through setting up gas cylinder pressure detection table 6, first pressure detection table 10 and second pressure detection table 11, can be in the final assembly test procedure or carrier rocket's actual flight in-process, supplementary quantitative analysis is used for whether normal work of pneumatic piece-rate system for stage separation in carrier rocket, thereby can avoid the inherent congenital defect that can't directly carry out the performance detection of initiating explosive device completely, and then can avoid increasing the product production quantity and carrying out the consumption nature side evidence experiment of spot check ignition on a large scale to the same batch product that goes on for the reliability of side evidence flight product, can show reduce cost.

The pneumatic separation system for the interstage separation in the carrier rocket is used as a separation energy source of the carrier rocket, can avoid plume scouring of the particle-level rocket body caused by solid small rocket ignition in the interstage separation process, and is favorable for reuse of the particle-level rocket body.

The pneumatic separation system for the interstage separation in the carrier rocket has the performance direct detection effect and can avoid the defect that the performance of initiating explosive devices cannot be directly detected, so that the cost of product production and ground ignition test increased for performing a bystander test on the performance of flight test products is avoided.

The pneumatic separation system for the interstage separation in the carrier rocket has the advantages of reliable principle, simple structure and good universality, and can be applied to the separation of the fairing of the carrier rocket and the separation process of the effective load. The method can play a positive role in recycling and reusing the carrier rocket and controlling the cost of the carrier rocket.

The foregoing is merely an illustrative embodiment of the present application, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principles of the present application shall fall within the protection scope of the present application.