阅读说明：本技术 固体火箭发动机壳体、固体火箭发动机及其制作方法 (Solid rocket engine shell, solid rocket engine and manufacturing method thereof ) 是由 武丹 陈文杰 周睿 司学龙 钟志文 张志强 于 2020-06-09 设计创作，主要内容包括：本申请涉及一种固体火箭发动机壳体、固体火箭发动机及其制作方法,固体火箭发动机壳体包括缠绕层、绝热结构、多个光纤和多个传感器,绝热结构内具有用于收容推进剂药柱的装药空间,且绝热结构上开设有沿该绝热结构周向延伸的光路通道；缠绕层缠绕于绝热结构外。多个光纤沿绝热结构的外圆周方向间隔布置,光纤与绝热结构粘接在一起,光纤包括引出端和嵌入端,引出端伸出绝热结构外,嵌入端沿绝热结构的母线方向延伸至嵌设于光路通道内,并伸入装药空间内；光纤的嵌入端连接有传感器,传感器用于监测所述推进剂药柱(装药界面或者药柱内部)。固体火箭发动机包括固体火箭发动机壳体和填充于装药空间内的推进剂药柱。(The solid rocket engine shell comprises a winding layer, a heat insulation structure, a plurality of optical fibers and a plurality of sensors, wherein a charge space for accommodating propellant grains is arranged in the heat insulation structure, and the heat insulation structure is provided with a light path channel extending along the circumferential direction of the heat insulation structure; the winding layer is wound outside the heat insulation structure. The optical fibers are arranged at intervals along the outer circumference direction of the heat insulation structure, the optical fibers are bonded with the heat insulation structure, each optical fiber comprises a leading-out end and an embedded end, the leading-out ends extend out of the heat insulation structure, and the embedded ends extend into the light path channel along the bus direction of the heat insulation structure and extend into the powder charging space; the embedded end of the optical fiber is connected with a sensor which is used for monitoring the propellant grain (a charging interface or the inside of the grain). The solid rocket engine comprises a solid rocket engine shell and a propellant grain filled in a charging space.)

1. A solid rocket engine casing, comprising:

the propellant powder column packaging structure comprises a heat insulation structure (1), wherein a powder charging space (10) for accommodating a propellant powder column (2) is formed in the heat insulation structure (1), and a light path channel (3) extending along the circumferential direction of the heat insulation structure (1) is formed in the heat insulation structure (1);

a plurality of optical fibers (4), wherein the optical fibers (4) are arranged at intervals along the outer circumferential direction of the heat insulation structure (1), the optical fibers (4) comprise an outgoing end (40) and an embedded end (41), the outgoing end (40) extends out of the heat insulation structure (1), and the embedded end (41) extends along the generatrix direction of the heat insulation structure (1) to be embedded in the light path channel (3) and extend into the powder charging space (10);

a plurality of sensors (5), the sensors (5) being connected to the embedded ends (41) of the optical fibers (4), the sensors (5) being for monitoring the propellant grains (2);

a winding layer (6) wound outside the insulating structure (1).

2. A solid rocket engine casing according to claim 1, wherein said heat insulating structure (1) comprises a column section (11) and a front head section (12) and a rear head section (13) connected to the two ends of said column section (11), respectively; the light path channel (3) is formed by end faces of the column section (11) and the front head sealing section (12) which are connected with each other, and the embedded end (41) extends to be embedded in the light path channel (3) along the bus direction of the front head sealing section (12); and/or, light path passageway (3) by column section (11) with back sealing head section (13) interconnect's terminal surface forms, embedding end (41) are followed the generating line direction of back sealing head section (13) extends to the embedding and locates in light path passageway (3).

3. A solid rocket engine housing as claimed in claim 2, wherein when said light path channel (3) is formed by the end faces of said column section (11) and said front head section (12) being connected to each other, said front head section (12) comprises a first section (120) and a second section (121) being connected to each other, said second section (121) being connected to said column section (11), and the upper surface of said second section (121) being disposed obliquely downward to guide said embedded end (41) into said light path channel (3).

4. A solid rocket engine housing as claimed in claim 3, wherein said column section (11) comprises a third section (110) and a fourth section (111) connected to each other, said fourth section (111) having a thickness gradually decreasing from an end close to said third section (110) towards an end remote from said third section (110) to abut on said second section (121).

5. The solid rocket engine housing according to claim 3, wherein the angle of inclination of said second segment (121) is α, 0< α ≦ 30 °.

6. A manufacturing method of a solid rocket engine shell is characterized by comprising the following steps:

providing a plurality of optical fibers (4), the optical fibers (4) comprising a pigtail end (40) and an embedded end (41);

assembling a heat insulation structure (1) on a winding core mold (7), wherein a charge space (10) for accommodating a propellant grain (2) is arranged in the heat insulation structure (1), and a light path channel (3) extending along the circumferential direction of the heat insulation structure (1) is arranged on the heat insulation structure (1);

arranging all the optical fibers (4) at intervals along the outer circumferential direction of the heat insulation structure (1), extending the leading-out ends (40) of the optical fibers (4) out of the heat insulation structure (1), and extending the embedded ends (41) into the light path channel (3) and the charge space (10) along the generatrix direction of the heat insulation structure (1);

winding outside the heat insulation structure (1) to form a winding layer (6);

detecting whether all the optical fibers (4) are alive or not, and connecting a sensor (5) at the embedded end (41) of the alive optical fibers (4) to monitor the propellant grains (2).

7. A method of manufacturing a solid rocket engine casing according to claim 6, wherein said insulating structure (1) comprises a column section (11) and a front head seal section (12) and a rear head seal section (13) respectively connected to both ends of said column section (11); the light path channel (3) is formed by the end faces of the column section (11) and the front sealing head section (12) which are connected with each other;

the method for assembling the heat insulation structure (1) on the winding core mould (7) specifically comprises the following steps:

preparing the front sealing head section and the rear sealing head section by adopting a compression molding manner;

the front head sealing section (12) and the rear head sealing section (13) are assembled on the winding core mould (7) at intervals along the axial direction of the winding core mould (7);

arranging all the optical fibers (4) at intervals along the outer circumferential direction of the front head sealing section (12), extending the leading-out ends (40) of the optical fibers (4) out of the front head sealing section (12), and extending the embedded ends (41) into the charge space (10) along the bus direction of the front head sealing section (12);

laying a heat insulation segment on a winding core mould (7) between the front head sealing section (12) and the rear head sealing section (13) to form the column section (11);

the front head section (12), the column section (11) and the rear head section (13) together form the heat insulating structure (1).

8. Method for manufacturing a solid-rocket motor casing according to claim 6, wherein monitoring all the optical fibers (4) for survival comprises the following steps:

connecting an optical fiber jumper at the leading-out end (40) of the optical fiber (4);

connecting a laser pen with the optical fiber jumper to communicate the optical fiber (4);

if the embedded end (41) of the optical fiber (4) is bright, judging that the optical fiber (4) is alive; otherwise, judging that the optical fiber (4) is not alive;

and repeating the steps to monitor whether all the optical fibers (4) are alive or not.

9. A solid rocket engine, comprising:

the propellant powder column packaging structure comprises a heat insulation structure (1), wherein a powder charging space (10) for accommodating a propellant powder column (2) is formed in the heat insulation structure (1), and a light path channel (3) extending along the circumferential direction of the heat insulation structure (1) is formed in the heat insulation structure (1);

a propellant grain (2) filled in the charge space (10);

a plurality of optical fibers (4), wherein the optical fibers (4) are arranged at intervals along the outer circumferential direction of the heat insulation structure (1), the optical fibers (4) comprise an outgoing end (40) and an embedded end (41), the outgoing end (40) extends out of the heat insulation structure (1), and the embedded end (41) extends along the generatrix direction of the heat insulation structure (1) to be embedded in the light path channel (3) and extend into the propellant grain (2);

a plurality of sensors (5), the sensors (5) being connected to the embedded ends (41) of the optical fibers (4), the sensors (5) being for monitoring the propellant grains (2);

a winding layer (6) wound outside the insulating structure (1).

10. A manufacturing method of a solid rocket engine is characterized by comprising the following steps:

providing a plurality of optical fibers (4), the optical fibers (4) comprising a pigtail end (40) and an embedded end (41);

assembling a heat insulation structure (1) on a winding core mold (7), wherein a charge space (10) for accommodating a propellant grain (2) is arranged in the heat insulation structure (1), and a light path channel (3) extending along the circumferential direction of the heat insulation structure (1) is arranged on the heat insulation structure (1);

arranging all the optical fibers (4) at intervals along the outer circumferential direction of the heat insulation structure (1), extending the leading-out ends (40) of the optical fibers (4) out of the heat insulation structure (1), and extending the embedded ends (41) into the light path channel (3) and the charge space (10) along the generatrix direction of the heat insulation structure (1);

winding outside the heat insulation structure (1) to form a winding layer (6);

monitoring whether all the optical fibers (4) are alive or not, and connecting a sensor (5) at the embedded end (41) of the alive optical fibers (4);

removing the winding core mould (7);

and spraying a lining layer and pouring the propellant grain (2) in the charging space (10) so as to enable the sensor (5) to extend into the propellant grain (2) and monitor the propellant grain (2).

Technical Field

The application relates to the technical field of solid rocket engines, in particular to a solid rocket engine shell, a solid rocket engine and a manufacturing method thereof.

Background

The prior rocket engine is a common power device for various missile weapons and aerospace vehicles, and the defects of inclusion, pores, layering, interface debonding and the like are easily formed when the engine propellant is cast and molded due to the relatively poor process stability of the composite material. And due to the reasons of temperature, vibration, collision and the like, the defects tend to be expanded continuously in the processes of storage, transportation and use of the engine, if the defects are not monitored and controlled, the problems of 'super' combustion surface and the like of the solid rocket engine during working can be caused, so that the solid rocket engine is greatly threatened, the reliability and the safety of the solid rocket engine are obviously influenced, and serious even serious safety accidents can be caused.

Disclosure of Invention

The embodiment of the application provides a solid rocket engine shell, a solid rocket engine and a manufacturing method thereof, and aims to solve the problems that monitoring of the interior of the solid rocket engine is delayed and real-time in-situ monitoring and early warning cannot be carried out in the related technology.

In a first aspect, there is provided a solid rocket engine casing comprising:

the heat insulation structure is internally provided with a powder charging space for accommodating propellant grains, and the heat insulation structure is provided with a light path channel extending along the circumferential direction of the heat insulation structure;

the optical fibers are arranged at intervals along the outer circumferential direction of the heat insulation structure and comprise leading-out ends and embedded ends, the leading-out ends extend out of the heat insulation structure, and the embedded ends extend into the light path channel along the generatrix direction of the heat insulation structure and extend into the powder charging space;

the embedded ends of the optical fibers are connected with the sensors, and the sensors are used for monitoring the propellant grains;

a wrap layer wrapped around the insulation structure.

In some embodiments, the insulating structure comprises a column section and a front and a rear head seal section connected to the two ends of the column section, respectively; the light path channel is formed by end faces of the column section and the front end socket section which are connected with each other, and the embedded end extends to be embedded in the light path channel along the bus direction of the front end socket section; and/or, the light path channel is formed by the end surfaces of the column section and the rear head sealing section which are connected with each other, and the embedded end extends to be embedded in the light path channel along the bus direction of the rear head sealing section.

In some embodiments, when the optical channel is formed by end faces of the column section and the front sealing head section, the front sealing head section includes a first section and a second section connected to each other, the second section is connected to the column section, and an upper surface of the second section is disposed obliquely downward to guide the embedded end into the optical channel.

In some embodiments, the column section includes a third section and a fourth section connected to each other, and a thickness of the fourth section gradually decreases from an end close to the third section to an end far from the third section so as to abut on the second section.

In some embodiments, the tilt angle of the second segment is α, 0< α ≦ 30.

In a second aspect, a method of making a solid rocket engine casing is provided, comprising the steps of:

providing a plurality of optical fibers, the optical fibers including a pigtail end and an embedded end;

assembling a heat insulation structure on a winding core mold, wherein a charge space for accommodating propellant grains is arranged in the heat insulation structure, and the heat insulation structure is provided with a light path channel extending along the circumferential direction of the heat insulation structure;

arranging all the optical fibers at intervals along the outer circumferential direction of the heat insulation structure, extending leading-out ends of the optical fibers out of the heat insulation structure, and extending embedded ends into the light path channel along the bus direction of the heat insulation structure and extending into the charge space;

winding outside the heat insulation structure to form a winding layer;

and detecting whether all the optical fibers are alive or not, and connecting a sensor at the embedded end of the alive optical fibers to monitor the propellant grain.

In some embodiments, the insulating structure comprises a column section and a front and a rear head seal section connected to the two ends of the column section, respectively; the light path channel is formed by end faces of the column section and the front seal head section which are connected with each other;

the method for assembling the heat insulation structure on the winding core mold specifically comprises the following steps:

preparing the front sealing head section and the rear sealing head section by adopting a compression molding manner;

assembling the front head sealing section and the rear head sealing section on the winding core mould at intervals along the axial direction of the winding core mould;

arranging all the optical fibers at intervals along the outer circumferential direction of the front head sealing section, extending the leading-out ends of the optical fibers out of the front head sealing section, and extending the embedded ends into the charging space along the bus direction of the front head sealing section;

paving a heat insulation segment on the winding core mold between the front head sealing section and the rear head sealing section to form the column section;

the front head seal segment, the column segment, and the rear head seal segment collectively form the insulating structure.

In some embodiments, monitoring whether all of the optical fibers are alive comprises:

connecting an optical fiber jumper at the leading-out end of the optical fiber;

connecting a laser pen with the optical fiber jumper to communicate the optical fiber;

if the embedded end of the optical fiber is bright, judging that the optical fiber is alive; otherwise, judging that the optical fiber is not alive;

and repeating the steps to monitor whether all the optical fibers are alive or not.

In a third aspect, there is provided a solid rocket engine comprising:

the heat insulation structure is internally provided with a powder charging space for accommodating propellant grains, and the heat insulation structure is provided with a light path channel extending along the circumferential direction of the heat insulation structure;

a propellant grain filled in the charge space;

the optical fibers are arranged at intervals along the outer circumferential direction of the heat insulation structure and comprise leading-out ends and embedded ends, the leading-out ends extend out of the heat insulation structure, and the embedded ends extend into the light path channel along the generatrix direction of the heat insulation structure and extend into the propellant grain;

the embedded ends of the optical fibers are connected with the sensors, and the sensors are used for monitoring the propellant grains;

a wrap layer wrapped around the insulation structure.

In a fourth aspect, a method for manufacturing a solid rocket engine is provided, which comprises the following steps:

providing a plurality of optical fibers, the optical fibers including a pigtail end and an embedded end;

assembling a heat insulation structure on a winding core mold, wherein a charge space for accommodating propellant grains is arranged in the heat insulation structure, and the heat insulation structure is provided with a light path channel extending along the circumferential direction of the heat insulation structure;

arranging all the optical fibers at intervals along the outer circumferential direction of the heat insulation structure, extending leading-out ends of the optical fibers out of the heat insulation structure, and extending embedded ends into the light path channel along the bus direction of the heat insulation structure and extending into the charge space;

winding outside the heat insulation structure to form a winding layer;

monitoring whether all the optical fibers survive or not, and connecting a sensor at the embedded end of the surviving optical fibers;

removing the winding core mold;

and spraying a lining layer and pouring a propellant grain in the charging space so as to enable the sensor to extend into the propellant grain and monitor the propellant grain.

The beneficial effect that technical scheme that this application provided brought includes: the optical fiber and the sensor are pre-embedded in the heat insulation structure of the engine to realize in-situ monitoring of the interior of the engine, and the optical fiber is small in diameter (0.25mm), so that an integrated structure is formed after the optical fiber and the heat insulation structure are cured and molded in the process of introducing the optical fiber into the heat insulation structure of the engine, and defects of the heat insulation structure cannot be caused. And can realize on-line, real-time, initiative monitoring and control to the propellant grain inside the heat insulating structure, find and confirm the debonding of propellant grain and heat insulating structure connecting interface in time, the position and degree of the internal crackle of propellant grain, injury, and monitor the expansion of the damaged area, not only can strengthen the engine state prediction ability effectively, reduce the difficulty of engine inspection and trouble discrimination, promote engine life and reliability, still benefit the discovery of the early problem of propellant grain, thus take the remedial measure in time, in order to avoid the emergence of major accident, guarantee the safety and stability of the solid rocket engine.

The embodiment of the application provides a solid rocket engine shell, a solid rocket engine and a manufacturing method thereof, since the optical fiber and the sensor are pre-embedded in the heat insulation structure of the engine, the in-situ monitoring of the interior of the engine is realized, therefore, the method can realize the online, real-time and active monitoring and control of the propellant grain in the heat insulation structure, timely find and determine the debonding of the propellant grain and the connection interface of the heat insulation structure, the position and the degree of cracks and damages in the propellant grain, and monitors the expansion of the damaged area, not only can effectively enhance the engine state prediction capability, reduce the difficulty of engine inspection and fault discrimination, improve the service life and reliability of the engine, but also is beneficial to the discovery of early problems of propellant grains, therefore, remedial measures are taken in time to avoid major accidents and ensure the safety and stability of the solid rocket engine.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

FIG. 1 is a schematic structural view of a solid rocket engine casing provided in an embodiment of the present application;

FIG. 2 is a schematic structural diagram of a solid rocket engine provided in an embodiment of the present application;

FIG. 3 is a schematic diagram of an embedded state of an optical fiber according to an embodiment of the present disclosure;

fig. 4 is a schematic view illustrating an installation state of a column section according to an embodiment of the present disclosure;

fig. 5 is a schematic view illustrating an installation state of a winding layer according to an embodiment of the present application.

In the figure: 1. an insulating structure; 10. a charge space; 11. a column section; 110. a third stage; 111. a fourth stage; 12. a front seal head section; 120. a first stage; 121. a second stage; 13. a rear head sealing section; 2. a propellant grain; 3. an optical path channel; 4. an optical fiber; 40. leading out the terminal; 41. an embedded end; 5. a sensor; 6. a winding layer; 7. and winding the core mold.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.