阅读说明：本技术 一种用于航天器复合材料压力容器的复合法兰及其制作方法 (Composite flange for spacecraft composite material pressure vessel and manufacturing method thereof ) 是由 朱文杰 施华 乔艳伟 赵和明 黄立钠 景育 沈俊 于 2020-12-16 设计创作，主要内容包括：本发明提供了一种用于航天器复合材料压力容器的复合法兰及其制作方法,包括复合材料壳体、复合材料对接平台以及安装法兰,复合材料对接平台缠绕固定在复合材料壳体的外表面,安装法兰安装在复合材料对接平台背离复合材料壳体的一侧,且安装法兰与复合材料对接平台之间填充有定距丝和粘接剂层,安装法兰背离复合材料平台的一侧还缠绕有用于将安装法兰固定在复合材料对接平台上的纤维缠绕收紧层。通过缠绕固化于复合材料壳体上的复合材料对接平台和纤维缠绕收紧层配合,将安装法兰固定安装在复合材料壳体的外表面,从而使安装法兰能够安装在复合材料压力容器外表面的任意纬度上,且结构简单,有助于提高复合材料压力容器的使用范围。(The invention provides a composite flange for a composite material pressure vessel of a spacecraft and a manufacturing method thereof, and the composite flange comprises a composite material shell, a composite material butt joint platform and a mounting flange, wherein the composite material butt joint platform is wound and fixed on the outer surface of the composite material shell, the mounting flange is arranged on one side of the composite material butt joint platform, which is far away from the composite material shell, distance wires and an adhesive layer are filled between the mounting flange and the composite material butt joint platform, and a fiber winding tightening layer for fixing the mounting flange on the composite material butt joint platform is also wound on one side of the mounting flange, which is far away from the composite material. The composite material butt joint platform and the fiber winding tightening layer which are wound and cured on the composite material shell are matched, and the mounting flange is fixedly mounted on the outer surface of the composite material shell, so that the mounting flange can be mounted on any latitude of the outer surface of the composite material pressure container, the structure is simple, and the application range of the composite material pressure container is favorably improved.)

1. The utility model provides a composite flange for spacecraft combined material pressure vessel, a serial communication port, including combined material casing (1), combined material butt joint platform (2) and mounting flange (3), combined material butt joint platform (2) winding is fixed at the surface of combined material casing (1), one side that combined material butt joint platform (2) deviates from combined material casing (1) is installed in mounting flange (3), just it has distance silk (4) and adhesive layer (5) to fill between mounting flange (3) and combined material butt joint platform (2), one side that mounting flange (3) deviate from the combined material platform still twines and is used for fixing mounting flange (3) the fibre winding on combined material butt joint platform (2) and tightens up layer (6).

2. A composite flange for a composite spacecraft pressure vessel according to claim 1, wherein the composite shell (1) comprises a metal liner (11) and a composite fibre layer (12) wound around the outer surface of the metal liner (11), the composite shell (1) comprises a thin-walled spherical or cylindrical structure, and the ratio of the thickness to the diameter of the composite shell (1) is less than 0.004.

3. A composite flange for a composite spacecraft pressure vessel as claimed in claim 1, wherein said mounting flange (3) is circular, said mounting flange (3) having a U-shaped channel (33) formed therein, said U-shaped channel (33) being disposed in plurality on said mounting flange (3) at equal intervals around the central axis of said mounting flange (3).

4. The composite flange for the composite material pressure vessel of the spacecraft as claimed in claim 1, wherein the mounting flange (3) comprises a vertical portion (31) and a horizontal portion (32), the horizontal portion (32) is fixedly arranged in the middle of the vertical portion (31), the side wall of the vertical portion (31) departing from the horizontal portion (32) is arranged opposite to the outer surface of the composite material docking platform (2), and the horizontal portion (32) is vertically provided with mounting holes (321).

5. A composite flange for a composite spacecraft pressure vessel according to claim 4, characterised in that the fibre-wound tightening layer (6) is wound on the side wall of the vertical portion (31) facing away from the composite docking platform (2), and that the fibre-wound tightening layer (6) is wound with one layer on the vertical portion (31) on both the upper and lower sides of the horizontal portion (32).

6. A composite flange for a composite spacecraft pressure vessel as claimed in claim 1, wherein the gap between the composite docking platform (2) and the mounting flange (3) is less than 1mm, the wires (4) have a diameter of between 0.2mm and 0.5mm, and the wires (4) are evenly filled with at least four wires between the composite docking platform (2) and the mounting flange (3).

7. A composite flange for a composite spacecraft pressure vessel according to claim 1, characterised in that the composite material in both the composite shell (1) and the composite docking platform (2) is a fibre composite or epoxy composite.

8. A composite flange for a composite spacecraft pressure vessel as claimed in claim 1, wherein the thickness of the fibre hoop tie layer (6) is between 1mm and 3 mm.

9. A manufacturing method of a composite flange for a composite material pressure vessel of a spacecraft is characterized by comprising the following steps:

s1, winding a fiber composite material or an epoxy composite material on the outer surface of the metal lining (11) through a wet winding process, and curing to form a composite fiber layer (12);

s2, manufacturing a blank of the composite material butt-joint platform (2) at any specified latitude position on the outer surface of the composite material shell (1) by a wet winding process, a curing method and the like;

s3, machining a butt joint surface matched with the mounting flange (3) on the solidified blank of the composite material butt joint platform (2) by a machining method, and ensuring the diameter and the roundness of the outer side of the composite material butt joint platform (2) by machining;

s4, coating the mounting flange (3) with an adhesive, sleeving the mounting flange on the composite material butt joint platform (2), and controlling a gap between circumferential butt joint surfaces of the mounting flange (3) and the composite material butt joint platform (2) through the distance wires (4) in the sleeving process so as to ensure that the adhesive layer (5) is uniformly filled;

s5, after the mounting flange (3) is bonded with the composite material butt joint platform (2), hoop winding of fiber winding tightening layers (6) is conducted on the upper side and the lower side of the outer surface of the mounting flange (3).

Technical Field

The invention relates to the technical field of installation of composite material pressure vessels of spacecrafts, in particular to a composite flange for a composite material pressure vessel of a spacecraft and a manufacturing method thereof.

Background

With the development of aerospace technology, people have higher and higher requirements on spacecrafts. A large number of pressure containers are adopted in the existing spacecraft to store various liquids and gases, the pressure containers are key parts determining the performance and safety of the spacecraft, and the light, reliable and safe composite material pressure container has important significance for reducing the structural quality, improving the performance of the spacecraft, guaranteeing the launching safety, reducing the launching cost and the like.

With the development and wide application of carbon fiber, PBO and other organic high-performance fibers, most of the gas cylinders for the attitude and orbit control power systems of the spacecraft adopt composite material gas cylinders, and the storage tanks for the attitude and orbit control power systems of the spacecraft gradually adopt composite material structures. At present, the fiber winding composite material pressure container needs to adopt a smooth metal lining to meet the requirement of fiber winding, so that a convex flange cannot be manufactured for installation like an all-metal container.

The prior publication No. CN204186699U discloses a fixed mounting device for a glass fiber reinforced plastic pressure vessel in a reverse osmosis water treatment system, which comprises a base and a strap, wherein the base and the strap are integrally formed by injection molding, one end of the strap is integrated with the base, the other end of the strap is a free end, the strap and the base are fastened and connected with the base through a fastener, and the strap and the base can surround the periphery of the glass fiber reinforced plastic pressure vessel and tightly hoop the glass fiber reinforced plastic pressure vessel.

The inventor believes that the mounting system for the band fastening of the prior art is complex and has specific requirements on the structure of the pressure vessel, resulting in great limitations in the use of composite pressure vessels and in the need for improvement.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide a composite flange for a composite material pressure vessel of a spacecraft and a manufacturing method thereof.

The composite flange for the composite material pressure vessel of the spacecraft comprises a composite material shell, a composite material butt joint platform and a mounting flange, wherein the composite material butt joint platform is wound and fixed on the outer surface of the composite material shell, the mounting flange is mounted on one side, away from the composite material shell, of the composite material butt joint platform, distance wires and an adhesive layer are filled between the mounting flange and the composite material butt joint platform, and a fiber winding tightening layer used for fixing the mounting flange on the composite material butt joint platform is further wound on one side, away from the composite material platform, of the mounting flange.

Preferably, the composite shell comprises a metal lining and a composite fiber layer wound on the outer surface of the metal lining, the composite shell comprises a thin-walled spherical structure or a cylindrical structure, and the ratio of the thickness to the diameter of the composite shell is less than 0.004.

Preferably, the mounting flange is circular, a U-shaped groove is formed in the mounting flange, and a plurality of U-shaped grooves are formed in the mounting flange at equal intervals around the central axis of the mounting flange.

Preferably, the mounting flange includes vertical portion and horizontal part, the fixed middle part that sets up at vertical portion of horizontal part, the lateral wall that vertical portion deviates from the horizontal part is relative with the surface of combined material butt joint platform and is set up, just the mounting hole has been seted up perpendicularly on the horizontal part.

Preferably, the fiber winding tightening layer is wound on the side wall of the vertical part, which is far away from the composite material butt joint platform, and the fiber winding tightening layer is wound on the vertical parts of the upper side and the lower side of the horizontal part.

Preferably, the clearance between the composite material butt joint platform and the mounting flange is smaller than 1mm, the diameter of the distance wires is 0.2mm-0.5mm, and at least four distance wires are uniformly filled between the composite material butt joint platform and the mounting flange.

Preferably, the composite material in both the composite shell and the composite docking platform is a fiber composite or an epoxy composite.

Preferably, the thickness of the fiber-wrapped tightening layer is between 1mm and 3 mm.

The invention provides a composite flange for a composite material pressure vessel of a spacecraft and a manufacturing method thereof, wherein the composite flange comprises the following steps:

s1, winding the fiber composite material or the epoxy composite material on the outer surface of the metal lining through a wet winding process, and curing to form a composite fiber layer;

s2, manufacturing a composite material butt-joint platform blank at any specified latitude position on the outer surface of the composite material shell by a wet winding process, a curing method and the like;

s3, machining a butt joint surface matched with the mounting flange on the solidified composite material butt joint platform blank by a machining method, and ensuring the diameter and the roundness of the outer side of the composite material butt joint platform by machining;

s4, coating the mounting flange with an adhesive, sleeving the mounting flange on a composite material butt joint platform, and controlling a gap between circumferential abutting surfaces of the mounting flange and the composite material butt joint platform through the distance wires in the sleeving process so as to ensure that the adhesive layer is uniformly filled;

and S5, after the mounting flange is bonded with the composite material butt joint platform, performing hoop winding manufacture of fiber winding tightening layers on the upper side and the lower side of the outer surface of the mounting flange.

Compared with the prior art, the invention has the following beneficial effects:

1. according to the invention, the composite material butt joint platform and the fiber winding tightening layer which are wound and cured on the composite material shell are matched, and the mounting flange is fixedly mounted on the outer surface of the composite material shell, so that the mounting flange can be mounted on any latitude of the outer surface of the composite material pressure container, the structure is simple, and the application range of the composite material pressure container is favorably improved;

2. the U-shaped groove and the fiber winding tightening layer are matched for use, so that the fit clearance between the composite material butt joint platform and the mounting flange is reduced, and the fit tightness and reliability of the mounting flange and the composite material butt joint platform are improved;

3. the invention ensures the concentricity of the composite material butt-joint platform and the mounting flange by applying the distance wires, and is beneficial to improving the uniformity of adhesive filling.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a schematic view of the overall structure of a composite flange embodying the present invention;

FIG. 2 is a schematic cross-sectional view of the overall structure of a composite flange embodying the present invention;

fig. 3 is a side view schematically showing the overall structure of the composite flange according to the present invention.

Reference numerals: 1. a composite shell; 11. a metal liner; 12. a composite fiber layer; 2. a composite docking platform; 3. installing a flange; 31. a vertical portion; 32. a horizontal portion; 321. mounting holes; 33. a U-shaped groove; 4. a distance wire; 5. an adhesive layer; 6. and the fiber is wound to tighten the layer.

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

As shown in fig. 1, the composite flange for a composite pressure vessel of a spacecraft provided by the invention comprises a composite shell 1, a composite docking platform 2 and a mounting flange 3. The composite material butt joint platform 2 is wound and fixed on the outer surface of the composite material shell 1, the mounting flange 3 is mounted on one side, departing from the composite material shell 1, of the composite material butt joint platform 2, and distance wires 4 and an adhesive layer 5 are filled between the mounting flange 3 and the composite material butt joint platform 2. And a fiber winding tightening layer 6 for fixing the mounting flange 3 on the composite material butt joint platform 2 is also wound on one side of the mounting flange 3, which is far away from the composite material platform. And the composite materials in the composite material shell 1 and the composite material butt joint platform 2 are both fiber composite materials or epoxy composite materials.

Through the matching of the composite material butt joint platform 2 and the fiber winding tightening layer 6, the mounting flange 3 is fixedly mounted at any latitude on the outer surface of the composite material pressure container, and the application range of the composite material pressure container is enlarged.

As shown in fig. 2, the composite shell 1 includes a metal liner 11 and a composite fiber layer 12 wound on the outer surface of the metal liner 11, the composite shell 1 is a thin-walled spherical structure or a cylindrical structure, and the ratio of the thickness to the diameter of the composite shell 1 is less than 0.004. The composite material butt joint platform 2 is wound on a designated position of the outer surface of the composite material shell 1 through a wet winding process and is cured. The composite material docking platform 2 is annular, the diameter and the roundness of the outer side of the composite material docking platform 2 are guaranteed through machining, and the side wall of the composite material docking platform 2, which deviates from the composite material shell 1, is a smooth plane.

The mounting flange 3 is of a whole-circle thin-wall circular structure, the mounting flange 3 comprises a vertical part 31 and a horizontal part 32, the horizontal part 32 is integrally formed in the middle of the vertical part 31 in the vertical direction, the thickness of the horizontal part 32 is 6mm-9mm, a mounting hole 321 is vertically formed in one side, away from the vertical part 31, of the horizontal part 32, the thickness of the vertical part 31 gradually increases from the end part, away from the horizontal part 32, to the side, close to the horizontal part 32, of the vertical part 31, and the thickness of the vertical part 31 is 0.5mm-1 mm.

As shown in fig. 2 and 3, the side wall of the vertical portion 31 facing away from the horizontal portion 32 is adhesively secured to the outer side wall of the composite docking platform 2. The vertical portion 31 of the mounting flange 3 is provided with a U-shaped groove 33, the width of the U-shaped groove 33 is about 2mm, the length of the U-shaped groove 33 is about 15mm, and the U-shaped groove 33 is arranged on the upper side and the lower side of the vertical portion 31 at equal intervals around the central axis of the mounting flange 3. On the one hand, the weight of the mounting flange 3 is reduced, on the other hand, the deformation amount of the mounting flange 3 is increased, and the fitting rate of the mounting flange 3 and the composite material butt joint platform 2 is improved.

As shown in fig. 2, the distance wires 4 and the adhesive layer 5 are filled between the composite material docking platform 2 and the mounting flange 3, the gap between the composite material docking platform 2 and the mounting flange 3 is less than 1mm, the diameter of the distance wires 4 is between 0.2mm and 0.5mm, and at least four distance wires 4 are arranged between the composite material docking platform 2 and the mounting flange 3. The number of distance wires 4 is determined according to the diameter of the pressure vessel, and the larger the diameter of the pressure vessel is, the larger the number of distance wires 4 is. In the sleeving process, the gap between the composite material butt-joint platform 2 and the circumferential butt-joint surface of the mounting flange 3 is controlled by the distance wires 4, so that the adhesive layer 5 between the composite material butt-joint platform and the mounting flange is ensured to be uniformly filled.

The fiber winding tightening layer 6 is wound on the side wall of the vertical part 31 departing from the composite material butt joint platform 2, and the fiber winding tightening layer 6 is wound on the vertical part 31 of the upper side and the lower side of the horizontal part 32. The two fiber winding tightening layers 6 are matched to stably fix the mounting flange 3 on the composite material butt-joint platform 2, and provide tightening force to ensure the relative position and pressing force in the bonding process of the mounting flange 3 and the composite material butt-joint platform 2. And the thickness of the two fiber winding tightening layers 6 is between 1mm and 3 mm.

The invention provides a method for manufacturing a composite flange for a composite material pressure vessel of a spacecraft, which comprises the following steps:

s1, winding the fiber composite material or the epoxy composite material on the outer surface of the metal lining 11 by a wet winding process, and curing to form the composite fiber layer 12.

And S2, manufacturing a blank of the composite material butt-joint platform 2 at any specified latitude position on the outer surface of the composite material shell 1 by a wet winding process, a curing method and the like.

And S3, machining a butt joint surface matched with the mounting flange 3 on the solidified composite material butt joint platform 2 blank by a machining method, and ensuring the diameter and the roundness of the outer side of the composite material butt joint platform 2 by machining.

S4, coating the adhesive on the mounting flange 3, sleeving the mounting flange on the composite material butt-joint platform 2, and controlling the gap between the mounting flange 3 and the circumferential butt-joint surface of the composite material butt-joint platform 2 through the distance wires 4 in the sleeving process, so as to ensure that the adhesive layer 5 is uniformly filled.

S5, after the mounting flange 3 and the composite material butt joint platform 2 are bonded, the circumferential winding manufacture of the fiber winding tightening layers 6 is carried out on the upper side and the lower side of the outer surface of the mounting flange 3.

The working principle is as follows:

during working, a worker firstly winds the outer surface of the metal lining 11 through a wet winding process to manufacture the composite fiber layer 12, then manufactures a blank of the composite material butt-joint platform 2 at a specified position of the outer surface of the composite material shell 1 through the wet winding process, then manufactures the composite material butt-joint platform 2 through machining, then coats the inner ring of the mounting flange 3 with an adhesive, fixedly bonds the mounting flange 3 on the composite material butt-joint platform 2, adjusts the distance between the composite material butt-joint platform 2 and the mounting flange 3 through the distance wires 4, and finally manufactures the upper side and the lower side of the outer surface of the mounting flange 3 through circumferential winding of the fiber winding layer tightening layers 6, so that the mounting flange 3 is stably fixed on the composite material butt-joint platform 2.

In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.