阅读说明：本技术 用于运载火箭中整流罩的气动分离系统 (Aerodynamic separation system for fairing in launch vehicle ) 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整流罩的气动分离系统,气动分离系统安装在整流罩上,整流罩采用整体拔罩方式、两个半罩分瓣平抛方式或两个半罩分瓣旋抛方式与箭体分离；气动分离系统包括至少一个气瓶、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；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推动整流罩与箭体之间彼此分离。本申请能够为整流罩分离提供能源,有利于整流罩的回收复用；能够直接进行性能检测,节省成本；原理可靠、结构简单、通用性好。(The application provides a pneumatic separation system for a fairing in a carrier rocket, wherein the pneumatic separation system is arranged on the fairing, and the fairing is separated from an rocket body in an integral hood-pulling mode, a two-half-hood split flat-throwing mode or a two-half-hood split rotary-throwing mode; the pneumatic separation system 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; the gas cylinder is used for being filled with compressed gas with preset pressure, and when the gas source output switch is turned on, the compressed gas stored in the gas cylinder pushes the fairing and the arrow body to be separated from each other through the pneumatic push rod in the cylinder after passing through the gas charging pipeline. The energy can be provided for the separation of the fairing, and the recovery and reuse of the fairing are facilitated; performance detection can be directly carried out, and cost is saved; the principle is reliable, the structure is simple, and the universality is good.)

1. A pneumatic separation system for a fairing in a carrier rocket is characterized in that the pneumatic separation system is arranged on the fairing, and the fairing is separated from a rocket body in an integral hood-pulling mode, a two-half-hood split flat-throwing mode or a two-half-hood split rotary-throwing mode;

the pneumatic separation system 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;

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 passes through the inflation pipeline and then pushes the fairing and the arrow body to be separated from each other through the pneumatic push rod in the cylinder.

2. The system of claim 1, wherein the air supply output switch is an electronically controlled switch that is connected to an external control device via a control signal line.

3. The pneumatic separation system for fairings in a launch vehicle of claim 1, wherein a cylinder pressure gauge is further disposed on said inflation line connecting said cylinder with said gas source output switch, said cylinder pressure gauge being configured to measure the pressure of compressed gas output by said cylinder.

4. The pneumatic separation system for fairings in a launch vehicle of claim 1, wherein an inflation and deflation port is provided at one end of said inflation line connected to said gas cylinder, and a mechanical inflation switch is provided on said inflation line connected to said inflation and deflation port and said gas cylinder.

5. The system of claim 4, wherein the mechanical inflation switch is connected to an interface on the inflation line of a gas cylinder, and the gas cylinder is connected to a rocket body pressurized transportation system through the interface.

6. The pneumatic separation system for fairings in a launch vehicle according to any of claims 1-5, wherein said cylinder is provided with a first pressure gauge at one end and a second pressure gauge at the other end; 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.

7. The aerodynamic separation system for fairings in a launch vehicle according to any of claims 1 to 5, wherein when said fairings are separated from the rocket bodies in an integral pull-out manner, two or more of said cylinders are disposed on the lateral separation surfaces of the fairings, and a force transmission support is provided at the front end of the last rocket body of said launch vehicle; after the separation surface of the fairing is unlocked, the fairing is separated from the arrow body under the action of the pneumatic push rod and the force transmission support.

8. The system according to any one of claims 1 to 5, wherein when the fairing is separated from the rocket body in a split flat projectile mode with two half-shrouds, each half-shroud is provided with a set of said pneumatic separation system, the mounting axis of said cylinder is perpendicular to the longitudinal separation plane of said fairing, said pneumatic push rod is directed towards the other half-shroud, and the other half-shroud is provided with a force transmission support; after the separation surface of the fairing is unlocked, the two half shrouds are translated along the direction vertical to the separation surface of the fairing under the action of the pneumatic push rod and the force transmission support, and finally separated from the arrow body.

9. The system of any one of claims 1-5, wherein when the fairing is separated from the rocket body in a split and spin-throwing manner by two half-cowls, each half-cowls is provided with a set of the pneumatic separation system, the installation axis of the cylinder is perpendicular to the transverse separation plane of the fairing, the pneumatic push rod points to the front end of the last rocket body of the launch rocket, and the front end of the last rocket body of the launch rocket is provided with a force transmission support; after the separation surface of the fairing is unlocked, the two half shrouds rotate along respective rotating shafts under the action of the pneumatic push rod and the force transmission support, and are finally separated from the arrow body.

10. A pneumatic separation system for fairings in a launch vehicle according to any of claims 1 to 5, wherein the compressed gas charged into said gas cylinders is one or more of compressed air, nitrogen, helium and hydrogen.

Technical Field

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

Background

The fairing is located at the forward most end of the launch vehicle and most missiles (collectively referred to as the launch vehicle) and is subjected to high velocity scour by the flight currents to provide a good in-hood environment for the payload. Fairings are widely used in vehicles as important components for protecting payloads and maintaining the aerodynamic shape of rocket bodies. When the vehicle is free from the atmospheric environment, the fairing is no longer functional and needs to be separated from the vehicle body.

Currently, separation of fairings in launch vehicles typically employs cold separation. The impulse device adopted by cold separation of domestic carrier rockets is generally a solid small rocket. The small solid rocket is fixedly connected to the fairing, and the fairing is separated from the carrier rocket body by reverse thrust generated by ignition work of the small solid rocket in the separation process.

However, the small solid rocket belongs to initiating explosive devices, the energy is concentrated, and the heat flow of the small solid rocket seriously scours the fairing in the separation process, which seriously influences the reuse of the fairing 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 fairings in a launch vehicle.

According to an embodiment of the present application, there is provided a pneumatic separation system for fairings in a launch vehicle, the pneumatic separation system being mounted on the fairings, the fairings being separated from an rocket body in an overall pull-out manner, a two-half-cowl split flat throw manner, or a two-half-cowl split rotary throw manner;

the pneumatic separation system 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;

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 passes through the inflation pipeline and then pushes the fairing and the arrow body to be separated from each other through the pneumatic push rod in the cylinder.

In the pneumatic separation system for the fairing in the carrier rocket, the air source output switch is an electric control switch and is connected with external control equipment through a control signal line.

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

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

Furthermore, the mechanical inflation switch is connected with the gas cylinder, a connector is arranged on the inflation pipeline, and the gas cylinder is connected with the rocket body pressurizing and conveying system through the connector.

In the pneumatic separation system for the fairing in 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.

In the pneumatic separation system for the fairing in the carrier rocket, when the fairing is separated from the rocket body in an integral hood pulling mode, more than two cylinders are arranged on the transverse separation surface of the fairing, and the front end of the last-stage rocket body of the carrier rocket is provided with a force transmission support; after the separation surface of the fairing is unlocked, the fairing is separated from the arrow body under the action of the pneumatic push rod and the force transmission support.

In the pneumatic separation system for the fairing in the carrier rocket, when the fairing is separated from the rocket body in a split flat throwing mode of two half shrouds, each half shroud is provided with one set of the pneumatic separation system, the installation axis of the cylinder is vertical to the longitudinal separation surface of the fairing, the pneumatic push rod points to the other half shroud, and the other half shroud is provided with a force transmission support; after the separation surface of the fairing is unlocked, the two half shrouds are translated along the direction vertical to the separation surface of the fairing under the action of the pneumatic push rod and the force transmission support, and finally separated from the arrow body.

In the pneumatic separation system for the fairing in the carrier rocket, when the fairing is separated from the rocket body in a split rotary throwing mode by two half shrouds, each half shroud is provided with one set of the pneumatic separation system, the installation axis of the air cylinder is perpendicular to the transverse separation surface of the fairing, the pneumatic push rod points to the front end of the last-stage rocket body of the carrier rocket, and the front end of the last-stage rocket body of the carrier rocket is provided with a force transmission support; after the separation surface of the fairing is unlocked, the two half shrouds rotate along respective rotating shafts under the action of the pneumatic push rod and the force transmission support, and are finally separated from the arrow body.

In the pneumatic separation system for the fairing in the carrier rocket, the compressed gas filled in the gas cylinder is one or more of compressed air, nitrogen, helium and hydrogen.

According to the above embodiments of the present application, at least the following advantages are obtained: the method is used for the pneumatic separation system of the fairing in the carrier rocket, and the fairing is separated from the rocket body in an integral hood pulling mode, a two-half-hood split flat throwing mode or a two-half-hood split rotary throwing mode by arranging the pneumatic separation system on the fairing; and set up gas cylinder, air supply output switch and cylinder among the pneumatic separation system, fill compressed gas in the gas cylinder, open air supply output switch, the gas cylinder produces thrust through the pneumatic push rod in the cylinder, provides the energy for the separation of radome fairing and arrow body, this application is arranged in the disengaging process of radome fairing and arrow body, can avoid among the prior art the little rocket of solid to ignite and erode the radome fairing, is favorable to the used repeatedly of radome fairing.

The pneumatic separation system for the fairing 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, thereby avoiding the cost of product production and ground ignition test increased for performing side evidence test on the performance of flight test products.

The pneumatic separation system for the fairing in the carrier rocket has the advantages of reliable principle, simple structure and good universality, and can be applied to the interstage separation and effective load separation process of the carrier rocket. 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 a fairing in a launch vehicle according to an embodiment of the present application.

Fig. 2 is a schematic structural distribution diagram of a pneumatic separation system for fairings in a launch vehicle according to an embodiment of the present application when the fairings are separated by flat throwing.

Fig. 3 is one of the top views of a portion of the structure of fig. 2.

Fig. 4 is a second top view of a portion of the structure shown in fig. 2.

Fig. 5 is a schematic view of a state of fairing horizontal projectile separation under the action of a pneumatic push rod in the pneumatic separation system for fairings in a launch vehicle provided in the embodiment of the application.

Fig. 6 is a schematic structural distribution diagram of a aerodynamic separation system for fairings in a launch vehicle when the fairings are subjected to rotational separation, provided by the embodiment of the application.

Fig. 7 is a top view of a portion of the structure of fig. 6.

Fig. 8 is a schematic view of a state of fairing spin-throw separation under the action of a pneumatic push rod in the pneumatic separation system for fairings in a launch vehicle provided in the embodiment of the present application.

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 transmission support;

20. a fairing.

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.

When the aerodynamic separation system for the fairing in the carrier rocket is used for fairing separation, energy is provided for fairing separation. The pneumatic separation system is arranged on the fairing, and the fairing is separated from the rocket body in an integral hood pulling mode, a two-half-hood split flat throwing mode or a two-half-hood split rotary throwing mode.

As shown in fig. 1, the pneumatic separation system for cowling in a launch vehicle provided by the embodiment of the present application includes at least one gas cylinder 1, a gas source output switch 2, and at least one cylinder 3. The cylinders 3 are disposed on the lateral parting surfaces of the cowling 20.

Wherein, each gas cylinder 1 is connected with an inflation pipeline 4, and the gas cylinder 1 is connected with one end of a gas source output switch 2 through the inflation pipeline 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. A pneumatic push rod 31 in the cylinder 3 cooperates with the force-transmitting support 12.

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 fairing 20 of the carrier rocket and the rocket body to be separated from each other through the pneumatic push rod 31 in the cylinder 3 after passing through the charging pipeline 4.

Specifically, the air source output switch 2 is an electrically controlled switch, and is connected with external control equipment through a control signal line. In the flight process of the carrier rocket, when pneumatic separation impulse is needed to be provided for the rocket body, the external control equipment sends a control signal to the air source output switch 2 to control the opening of the air source output switch 2, and the air bottle 1 punches an inflation cavity of the air cylinder 3 through the air source output switch 2 and the pipeline 5 at the front end of the spray pipe.

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 air source sharing of the pneumatic separation system of the fairing and the rocket body pressurizing and conveying system 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 fairing 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 radome fairing 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 the pneumatic piece-rate system of radome fairing 20 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 test of spot check ignition on a large scale with batch product that goes on for the reliability of side evidence flight product, can show reduce cost.

When the fairing 20 is separated from the rocket body in an integral hood pulling mode, the pneumatic separation system is installed on the fairing 20, and the force transmission support is installed at the front end of the last rocket body of the carrier rocket. Two or more cylinders 3 are provided on the transversely split surfaces of the cowl 20.

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.

And when the separation signal is received, the separation surface of the fairing 20 is unlocked, and when the fairing 20 is separated from the rocket body in the carrier rocket, 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 support 12 to separate the fairing 20 from the rocket body. When the pneumatic ram 31 reaches its stroke and stops moving, there is a relative velocity between the cowling 20 and the arrow. The fairing 20 and the arrow body continue to move respectively until separation is completed, the force transmission support 12 is launched out along with the arrow body, and the pneumatic separation system returns to the ground along with the fairing 20.

To ensure that the separated fairing 20 does not collide with the rocket body, a time-delay ignition side-push rocket is mounted on the fairing 20 to push the debris of the fairing 20 away from the rocket body running trajectory.

As shown in fig. 2 to 5, when the fairing 20 is separated from the rocket body by adopting a split flat-throw mode of two half shrouds, a set of pneumatic separation system needs to be installed on each half shroud, the installation axis of the cylinder 3 is perpendicular to the longitudinal separation surface of the fairing 20, the pneumatic push rod 31 points to the other half shroud, and the force transmission support is arranged on the other half shroud. After the separation signal is received and the separation surface of the fairing 20 is unlocked, the two half-shrouds are translated along the direction vertical to the separation surface of the fairing 20 under the action of the pneumatic push rod 31, and finally separated from the arrow body.

As shown in fig. 6-8, when the fairing 20 is separated from the rocket body by adopting a two-half-shroud split rotary throwing mode, a set of pneumatic separation system needs to be installed on each half shroud, the installation axis of the cylinder 3 is perpendicular to the transverse separation surface of the fairing 20, the pneumatic push rod 31 points to the front end of the last-stage rocket body of the carrier rocket, and the force transmission support is arranged at the front end of the last-stage rocket body of the carrier rocket. After the separation signal is received and the separation surface of the fairing 20 is unlocked, the two half-shrouds rotate along respective rotating shafts under the action of the pneumatic push rod 31, and finally are separated from the arrow body after unhooking.

The principle of the pneumatic separation system for the fairing in the carrier rocket is reliable, the performance of each component has detectability, the product cost is low, the recovery and the repeated use of the fairing 20 are facilitated, and the cost is reduced.

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.