阅读说明：本技术 一种缠绕式法兰底座及其制作方法 (Winding type flange base and manufacturing method thereof ) 是由 赵积鹏 于斌 马天驹 顾森东 刘志栋 杨震春 张建军 张海 杨文博 李玉峰 张涛 于 2021-08-17 设计创作，主要内容包括：本申请涉及复合材料气瓶技术领域,具体而言,涉及一种缠绕式法兰底座及其制作方法,所述缠绕式法兰底座包括依次连接的筒段缠绕区、应力补强区、封头渐变壁厚区、底座安装区以及底座约束区,其中：筒段缠绕区与复合气瓶筒段的复合层外层缠绕固定；应力补强区的壁厚大于2倍的基础壁厚；封头渐变壁厚区设置有均匀的减重孔；底座安装区沿圆周方向设置有均匀的螺纹孔；底座约束区与复合气瓶的挂丝台配合连接。本发明提供的缠绕式法兰底座具有轻质高强、抗动力学载荷能力强、可靠性高、安全性高的特点,主要用于固定缠绕复合气瓶,使大容积、大重量、高长径比、轻质高强、携带超重工质的复合气瓶能够与卫星新型桁架式承力结构完美装配对接。(The application relates to the technical field of composite material gas cylinders, particularly, relates to a wound flange base and a manufacturing method thereof, the wound flange base comprises a barrel section winding area, a stress reinforcement area, a seal head gradual-change wall thickness area, a base installation area and a base restraint area which are sequentially connected, wherein: the cylinder section winding area is fixedly wound with the outer layer of the composite cylinder section of the composite gas cylinder; the wall thickness of the stress reinforcing area is more than 2 times of the wall thickness of the foundation; the gradual change wall thickness area of the end socket is provided with uniform lightening holes; the base mounting area is provided with uniform threaded holes along the circumferential direction; the base restraint area is connected with a wire hanging table of the composite gas cylinder in a matching way. The winding type flange base provided by the invention has the characteristics of light weight, high strength, strong dynamic load resistance, high reliability and high safety, and is mainly used for fixing and winding the composite gas cylinder, so that the composite gas cylinder with large volume, heavy weight, high length-diameter ratio, light weight, high strength and overweight working media can be perfectly assembled and butted with a novel truss type bearing structure of a satellite.)

1. The utility model provides a wound form flange base, the structure is head base area section of thick bamboo, its characterized in that, including section of thick bamboo winding district, stress reinforcement district, head gradual change wall thickness district, pedestal mounting district and the base restraint district that connects gradually, wherein:

the cylinder section winding area is fixedly wound with the outer layer of the composite cylinder section of the composite gas cylinder;

the wall thickness of the stress reinforcing area is more than 2 times of the wall thickness of the foundation;

the gradual change wall thickness area of the end socket is provided with uniform lightening holes;

the base mounting area is provided with uniform threaded holes along the circumferential direction;

and the base constraint area is connected with the wire hanging table of the composite gas cylinder in a matching way.

2. The wound flange pedestal of claim 1, wherein the drum section winding area is of a gradually-increased thickness structure, and stress relief grooves are uniformly formed in the axial direction.

3. The wound flange mount of claim 1, wherein the drum section winding area is provided with resin circumferential fixing grooves at equal intervals in a circumferential direction.

4. The wound flange mount of claim 1, wherein the winding fixture employs a wet winding process of a variable angle near hoop winding pattern.

5. The wound flange base of claim 1, wherein the composite gas cylinder is an iso-tension head cylindrical structure.

6. The wound flange base of claim 5, wherein the upper seal head convex cylinder at the sealing end of the composite gas cylinder is connected with a truss type bearing structure supporting plate.

7. The wrap flange mount of claim 6, wherein the mount mounting area is connected to a docking ring of the truss-like catenary structure.

8. The wound flange base of claim 5, wherein the composite gas cylinder has an outer diameter of 800mm or less, a length of 2500mm or less, and a propellant storage weight of 500kg or less.

9. A method of making the wrap flange mount of claims 1-8, comprising the steps of:

step 1: hot stamping by adopting a TC4 titanium alloy plate clamping plate to complete the forming of the seal head band barrel section blank of the winding type flange base;

step 2: machining the inner surface and the outer surface of the winding type flange base by adopting a turning process;

and step 3: finishing the processing of a stress relief groove in a winding area of a cylinder section of the winding type flange base by adopting a numerical control milling process;

and 4, step 4: finishing the machining of lightening holes in the gradual-change wall thickness area of the end socket of the wound flange base by adopting a numerical control milling process;

and 5: and finishing the processing of the threaded hole of the mounting area of the winding type flange base by adopting a drilling and tapping process.

Technical Field

The application relates to the technical field of composite material gas cylinders, in particular to a winding type flange base and a manufacturing method thereof.

Background

The truss type bearing structure has the advantages of light weight, high strength, high structural efficiency, high space utilization efficiency, high natural frequency and the like, and becomes the first choice of a novel large satellite platform bearing structure. The novel large-scale satellite platform adopts a truss type bearing structure to replace a traditional bearing cylinder type bearing structure, an electric propulsion subsystem of the satellite platform needs to carry a larger amount of high-pressure xenon propellant in 10-15 years and longer service life, so that the composite gas cylinder structure develops towards the directions of large volume, heavy weight, high length-diameter ratio and light weight and high strength, the weight of the propellant carried by the composite gas cylinder develops towards hundreds of kilograms of electric propulsion high-pressure xenon from about ten kilograms of chemical propulsion pressurization high-pressure helium, the dynamics transmission characteristic of the novel truss structure, the structural characteristics of the composite gas cylinder under the novel platform, the carried ultra-large weight of the high-pressure xenon and the like all improve the greater technical requirements on the installation interface of the composite gas cylinder.

The existing installation butt joint mode of the composite gas cylinder generally adopts a metal flange structure formed by screwing a metal lining of the traditional composite gas cylinder, but the flange structure is only suitable for the installation of the traditional bearing cylinder, has the defects of heavy weight, large torque and stress concentration, and does not have a good solution at present for the assembly connection problem of the composite gas cylinder with large volume, heavy weight, high length-diameter ratio, light weight and high strength and carrying an overweight working medium and a novel truss type bearing structure of a satellite.

Disclosure of Invention

The main purpose of the application is to provide a winding type flange base and a manufacturing method thereof, and the problem of assembly connection of a composite gas cylinder with a heavy working medium and a novel truss type bearing structure of a satellite, wherein the composite gas cylinder is large in volume, heavy in weight, high in length-diameter ratio, light in weight and high in strength.

In order to realize above-mentioned purpose, this application provides a wound form flange base, and the structure is head base area section of thick bamboo, including the section of thick bamboo winding district that connects gradually, stress reinforcement district, head gradual change wall thickness district, base installation district and the base restraint district, wherein: the cylinder section winding area is fixedly wound with the outer layer of the composite cylinder section of the composite gas cylinder; the wall thickness of the stress reinforcing area is more than 2 times of the wall thickness of the foundation; the gradual change wall thickness area of the end socket is provided with uniform lightening holes; the base mounting area is provided with uniform threaded holes along the circumferential direction; the base restraint area is connected with a wire hanging table of the composite gas cylinder in a matching way.

Furthermore, the winding area of the cylinder section is of a gradually-changed thickening structure, and stress release grooves are uniformly formed in the axial direction.

Furthermore, resin annular fixing grooves are formed in the cylinder section winding area at equal intervals along the annular direction.

Furthermore, the winding and fixing adopt a wet winding process of variable-angle near-annular winding line type.

Furthermore, the composite gas cylinder is of an equal-tension end socket cylindrical structure.

Furthermore, the convex cylinder of the upper end socket of the sealing end of the composite gas cylinder is connected with the truss type bearing structure supporting plate.

Further, the base installation area is connected with a butt-joint ring of the truss type bearing structure.

Furthermore, the outer diameter of the composite gas cylinder is less than or equal to phi 800mm, the length of the composite gas cylinder is less than or equal to 2500mm, and the weight of the stored propellant is less than or equal to 500 kg.

The application also provides a method for manufacturing the winding type flange base, which comprises the following steps: step 1: hot stamping by adopting a TC4 titanium alloy plate clamping plate to complete the forming of the seal head band barrel section blank of the winding type flange base; step 2: machining the inner surface and the outer surface of the winding type flange base by adopting a turning process; and step 3: finishing the processing of a stress relief groove in a winding area of a cylinder section of the winding type flange base by adopting a numerical control milling process; and 4, step 4: finishing the machining of lightening holes in the gradual-change wall thickness area of the end socket of the wound flange base by adopting a numerical control milling process; and 5: and finishing the processing of the threaded hole of the mounting area of the winding type flange base by adopting a drilling and tapping process.

The winding type flange base and the manufacturing method thereof provided by the invention have the following beneficial effects:

1. the winding type flange base provided by the invention has the characteristics of light weight, high strength, strong dynamic load resistance, high reliability and high safety, and is mainly used for fixing and winding the composite gas cylinder, so that the composite gas cylinder with large volume, heavy weight, high length-diameter ratio, light weight, high strength and overweight working media can be perfectly assembled and butted with a novel truss type bearing structure of a satellite.

2. Through set up stress release groove and resin hoop fixed slot in section of thick bamboo winding district, improved the stress-strain harmony of wound form flange base section of thick bamboo district and combined material gas cylinder, also improved the fixed radial and axial tension in section of thick bamboo winding district.

3. The winding type flange base is in direct contact with the truss type bearing structure butt joint ring face and is fixedly connected through the bolts, fixed rigidity full restraint is achieved, in addition, X, Y radial restraint of the protruding cylinder of the upper end socket of the sealing end of the composite gas cylinder and the truss type bearing structure supporting plate is achieved, assembly connection of the composite gas cylinder and the novel truss type bearing structure of the satellite is achieved, and reliability and safety of mechanical connection are greatly improved.

4. Replace traditional metal inside lining connection metal flange structure through wound form flange base, eliminated local stress concentration, the structural stress level has reduced 70%, and factor of safety improves 3 doubly, and mounting structure weight has reduced 20%.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this application, serve to provide a further understanding of the application and to enable other features, objects, and advantages of the application to be more apparent. The drawings and their description illustrate the embodiments of the invention and do not limit it. In the drawings:

FIG. 1 is a schematic view of a wrap around flange mount provided in accordance with an embodiment of the present application;

FIG. 2 is a schematic diagram of a composite gas cylinder and a truss-type force-bearing structure according to an embodiment of the application;

in the figure: 1-cylinder section winding area, 11-stress release groove, 2-stress reinforcing area, 3-end enclosure gradual wall thickness changing area, 31-lightening hole, 4-base installation area, 5-base constraint area, 6-composite gas cylinder, 61-wire hanging table, 62-upper end enclosure, 7-truss type bearing structure, 71-butt ring and 72-support plate.

Detailed Description

In order to make the technical solutions better understood by those skilled in the art, 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 only partial 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.

As shown in fig. 1, the application provides a wound form flange base, and the structure is head base area section, including section of thick bamboo winding district 1, the stress reinforcement district 2 that connects gradually, head gradual change wall thickness district 3, base installation district 4 and base restraint district 5 that connect gradually, wherein: the cylinder section winding area 1 is fixedly wound with the outer layer of the composite layer of the cylinder section of the composite gas cylinder 6; the wall thickness of the stress reinforcing area 2 is more than 2 times of the wall thickness of the foundation; the end socket gradually-changed wall thickness area 3 is provided with uniform lightening holes 31; the base mounting area 4 is provided with uniform threaded holes along the circumferential direction; the base restraint area 5 is connected with a wire hanging table 61 of the composite gas cylinder 6 in a matching way.

Specifically, the winding type flange base that this application embodiment provided mainly used fixed winding place compound gas cylinder 6 of big volume, heavy weight, high draw ratio, light weight height-strength, carrying overweight working medium, fixes compound gas cylinder 6 and assembles the butt joint with the novel truss-like load-carrying structure 7 of satellite to for the satellite platform electric propulsion provides required propellant gas. The winding type flange base material is preferably TC4 titanium alloy, the whole structure comprises a cylinder section and a base, wherein the cylinder section winding area 1 is mainly used for winding and fixing the outer layer of a cylinder section composite layer close to the lower end socket of the gas port end of the composite gas cylinder 6, so that the composite gas cylinder 6 can be stably wound and fixed on the flange base, and is assembled and butted with the truss type bearing structure 7. Stress reinforcement district 2 mainly sets up the outer wall at 6 bottles of compound gas cylinder and low head juncture, because there are complicated stresses such as moment of flexure, moment of torsion in bottle and head juncture, adopts the reinforcement structure can improve the reliability of flange base, and the wall thickness is preferred to adopt basic wall thickness 2.5 times wall thickness to carry out the reinforcement to stress reinforcement district 2 adopts gradual change structure with basic wall thickness transition district. The end socket gradually-changing wall thickness area 3 is arranged on the outer side of the end socket of the composite bottle, the gradually-changing wall thickness design is adopted, and the uniform lightening holes 31 are formed, so that the weight of the flange base can be reduced to the maximum extent under the condition that the requirements on strength and rigidity are met. The base installation area 4 is mainly used for being connected with the butt joint ring 71 of the truss type bearing structure 7, 8 uniformly distributed M8 internal threads are preferably processed in the circumferential direction of phi of 100mm in the base installation area 4, and the base installation area is fixedly connected with the butt joint ring 71 through bolts, so that rigid full restraint is realized. Base restraint district 5 mainly used retrains the radial of compound gas cylinder 6, connects the cooperation with the string silk platform 61 of 6 gas port end low heads of compound gas cylinder, realizes the radial restraint of X, Y two directions of compound gas cylinder 6 string silk platform 61, satisfies the requirement that 6 pressure variation head extending structure of compound gas cylinder changes.

Further, the winding area 1 of the cylinder section is of a gradually-changing thickening structure, and stress release grooves 11 are uniformly formed in the axial direction. In the embodiment of the application, the number of the stress release grooves 11 uniformly distributed in the cylinder section winding area 1 is preferably 48, and the stress release grooves 11 are mainly used for improving the stress-strain coordination between the cylinder section winding area 1 and the cylinder section of the composite gas cylinder 6 and improving the radial tension of the cylinder section winding area 1.

Further, the cylinder section winding area 1 is provided with resin annular fixing grooves at equal intervals along the annular direction. In the embodiment of the present application, the number of the resin ring fixing grooves provided in the drum segment winding area 1 is preferably 3, and the resin ring fixing grooves are mainly used for improving the axial tension of the drum segment winding area 1.

Furthermore, the winding and fixing adopt a wet winding process of variable-angle near-annular winding line type. In the embodiment of the application, the cylinder section winding area 1 and the composite layer outer layer of the cylinder section of the composite gas cylinder 6 are preferably wound and fixed by a wet winding process of a 26-degree variable-angle near-ring winding line type, and the flange base and the composite gas cylinder 6 are stably wound together, wherein the overall winding tension of the cylinder section winding area 1 is not less than 3 times of the dynamic load strength of the composite gas cylinder 6, the height of the cylinder section winding area 1 is preferably 130mm, and the thickness of the winding layer is preferably 4.2 mm.

Further, the composite gas cylinder 6 is of an equal-tension end socket cylindrical structure. The composite gas cylinder 6 is preferably a gas cylinder with sealing heads at the upper part and the lower part, the cylinder body is of a cylindrical structure, the composite gas cylinder is preferably an ultra-thin-wall titanium lining high-strength carbon fiber winding composite material gas cylinder, the lining is preferably made of TA1 pure titanium, the wall thickness of the lining foundation is preferably 0.8mm, the composite layer is preferably made of T800S carbon fiber, and the wet winding process is adopted to form a circumferential and spiral alternate winding line type.

Further, the convex cylinder of the upper end socket 62 at the sealing end of the composite gas cylinder 6 is connected with the support plate 72 of the truss type force bearing structure 7. The protruding cylinder of the upper end socket 62 at the sealing end of the composite gas cylinder 6 and X, Y directions of the support plate 72 of the truss-type bearing structure 7 are radially constrained, so that the upper end socket 62 of the composite gas cylinder 6 can be stably fixed on the support plate 72 of the truss-type bearing structure 7.

Further, the base installation area 4 is connected with the butt-joint ring 71 of the truss-type force-bearing structure 7. The base installation area 4 is fixedly connected with the butt joint ring 71 of the truss type bearing structure 7 through bolts, so that the lower seal head of the composite gas cylinder 6 can be stably fixed on the butt joint ring 71 of the truss type bearing structure 7, and the composite gas cylinder 6 is fixedly assembled and connected with the novel truss type bearing structure 7 of the satellite.

Furthermore, the outer diameter of the composite gas cylinder 6 is less than or equal to phi 800mm, the length is less than or equal to 2500mm, and the weight of the stored propellant is less than or equal to 500 kg. In the present embodiment, the outside diameter of the composite gas cylinder 6 is preferably 344mm, the length thereof is preferably 1700mm, and the stored propellant weight is preferably 180 kg.

The embodiment of the application also provides a method for manufacturing the winding type flange base, which comprises the following steps: step 1: hot stamping by adopting a TC4 titanium alloy plate clamping plate to complete the forming of the seal head band barrel section blank of the winding type flange base; step 2: machining the inner surface and the outer surface of the winding type flange base by adopting a turning process; and step 3: finishing the processing of the stress relief groove 11 of the winding area 1 of the winding type flange base barrel section by adopting a numerical control milling process; and 4, step 4: finishing the machining of the lightening holes 31 of the gradual wall thickness changing area 3 of the end socket of the wound flange base by adopting a numerical control milling process; and 5: and (4) finishing the processing of the threaded hole of the mounting area 4 of the winding type flange base by adopting a drilling and tapping process.

The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.