A liner-banded pressure vessel winding design and forming method

Abstract

The application provides a winding design and forming method of a pressure container with a lining belt lateral flange, and aims at the design and forming requirements of a non-equal-pole-hole ellipsoidal pressure container with a lining belt lateral flange. The design method and simulation strategy of the application can solve the problems of hole expansion winding and linear design of the non-equal-pole-hole ellipsoidal container, so that the weight reduction and fiber accumulation at the head part are reduced. When winding, the fiber is more easily slid along the conical surface to the flange root through a conical auxiliary tool, and the fiber gasket reinforcement can be carried out on the stress concentration part of the flange opening according to the finite element simulation result. Through the stepped layer design, the influence of the high convex area of the welding seam on the winding fiber overhead can be reduced, and the stability of the pressure container is improved.

Description

Technical Field

[0001] This invention belongs to the field of composite material design and molding technology, and in particular, it is a design and molding method for a spiral wound pressure vessel with an inner lining and a side flange. Background Technology

[0002] With the increasing diversity of aerospace missions, some spacecraft, due to special installation requirements, have shells with integrated lateral flanges on the surface, ellipsoidal ends, and varying opening diameters, consisting of sections without cylinders or with extremely small cylinders. Furthermore, they face extremely stringent requirements regarding weight and outer diameter. Due to the complex geometry and the interference and stress concentration from the lateral flanges on the liner, the strength and linear design of these pressure vessels are more complex, and the winding process is more difficult.

[0003] To ensure structural strength, relevant organizations proposed a spiral winding method for non-equipotential pressure vessels, fixing the lateral flanges through adhesive bonding and circumferential winding. However, in practice, on the one hand, obstacle-avoidance winding and local reinforcement methods for the lateral flange structure with an inner liner were not considered; on the other hand, transition and optimization were not made for the high-protrusion area of ​​the weld.

[0004] Patent CN 113111517 A, entitled "Design Method of Non-Isopolar Pore Fiber-Wound Pressure Vessel," describes a design method for a non-isopolar pore fiber-wound pressure vessel. It employs orthotropic carbon fiber winding to create a variable stiffness structure at the end cap. However, this patent uses an integral winding design, does not employ a hole-expanding winding method for weight reduction, and has not been verified using appropriate finite element simulation.

[0005] Patent CN 112664820 A, entitled "A Composite Flange for Spacecraft Composite Material Pressure Vessels and Its Manufacturing Method," provides a composite flange for spacecraft composite material pressure vessels and its manufacturing method. By using a composite material docking platform wound and cured onto a composite material shell and a fiber-wound tightening layer, the mounting flange is fixedly installed on the outer surface of the composite material shell, allowing the mounting flange to be installed at any latitude on the outer surface of the composite material pressure vessel. However, in this patent, the mounting flange and the metal liner are separate components, installed after the composite material shell has cured. This requires secondary processing of the wound shell and may cause assembly deviations. Summary of the Invention

[0006] The purpose of this invention is to provide a design and molding method for a spiral wound pressure vessel with an inner lining and a side flange, so as to achieve continuous and stable fiber winding molding of this type of structure.

[0007] The technical solution to achieve the purpose of this invention is as follows:

[0008] A method for spiral wound design of a pressure vessel with an inner liner and a side flange, comprising the following steps:

[0009] Step 1: Design the enlarged envelope circle winding. First, wind evenly distributed fibers within the minimum polar hole range of the lower and upper end caps to meet the strength requirements near the opening ends of the lower and upper end caps. This is the first winding layer. Calculate the latitudinal resistance of the fibers in each latitudinal direction of this first winding layer.

[0010] Step 2: Calculate the magnitude of the latitudinal internal force at each latitude of the open shell and compare it with the corresponding fiber resistance. Take the point where the fiber latitudinal resistance and latitudinal internal force of the two end caps are equal as the new pole hole. Wind the uniformly distributed fibers within the new winding starting range as the second winding layer, and calculate the latitudinal resistance of the fibers at each latitude of the second winding layer.

[0011] Step 3: Calculate the latitudinal internal force of the open shell formed by the new pole hole at each latitude and compare it with the corresponding fiber resistance. Take the place where the corresponding fiber resistance of the two end caps is equal to the corresponding latitudinal internal force as the new pole hole. Wind the uniformly distributed fiber within the new winding starting range as the third winding layer.

[0012] Step 4: Continue in this manner, adding more winding layers until near the equator. The entire shell is wrapped with n layers of fiber, and the resultant force of the latitudinal fiber resistance provided by each winding layer at each latitude is greater than the latitudinal internal force of the corresponding open shell.

[0013] Step 5: Using the non-geodetic winding formula, and assuming the slip coefficient is determined, calculate the winding angles for stable winding of each winding layer in the upper and lower hemispheres of the non-equipolar hole.

[0014] Step 6: Calculate the thickness of each winding layer;

[0015] Step 7: Draw a 3D model of the pressure vessel and import it into the simulation software. The metal liner is divided into solid elements, and the composite layer is divided into shell elements. According to the winding angle and the thickness of the winding layer, assign the winding angle and thickness of each winding layer of the composite element at the same latitude, and input the mechanical property parameters of the composite material. Use fabric to reinforce the stress concentration area of ​​the winding layer opening of the integrated lateral flange interference. Add a layer of composite fabric to the stress concentration area around the flange that exceeds the allowable stress range each time, and then continuously add fabric to the dangerous areas in the feedback results to meet the overall mechanical performance requirements.

[0016] A method for spiral winding of a pressure vessel with an inner liner and a side flange, used for forming the spiral winding layer of an ellipsoidal pressure vessel, includes the following steps:

[0017] Step 8: Based on the design line, write the NC code for the winding machine in CADWIND software and run it for trial operation to eliminate the risk of interference and collision;

[0018] Step 9: Fix the metal liner onto the three-jaw chuck of the winding machine using the spigot clamping fixture;

[0019] Step 10: Install the tapered auxiliary tooling on the outside of the integrated side flange;

[0020] Step 11: Roughen and clean the surface of the metal lining;

[0021] Step 12: Test run the NC code of each winding layer with dry fiber without glue to ensure that the origin is accurate and that there is no slippage.

[0022] Step 13: Apply adhesive film to the surface of the metal lining;

[0023] Step 14: Dry the carbon fiber, install it onto the winding machine and thread it with yarn;

[0024] Step 15: Reinforce with integrated lateral flange hole periphery fiber cloth gasket;

[0025] Step 16: Measure the height h of weld 11 relative to the shell surface. w If it is lower than the thickness t of a single layer of fiber fabric w If the value is greater than t, no compensation will be made; if the value is greater than t, no compensation will be made. w Then compensate [h] w / t w A layer of transition fabric is applied, and a reinforcing fabric is added to the top layer of the weld. The layers of fabric are transitioned in a gradient manner and then coated with adhesive.

[0026] Step 17: Wet-process expansion and winding molding. After the yarn is impregnated with resin and fixed, the winding program is run to sequentially wind n layers of fiber designed by the container winding layer design method. A spiral winding method is adopted, and the diameter of the polar holes in the winding layer increases sequentially until it reaches near the equator. Finally, 2n fiber accumulation rings appear at each polar hole on the entire surface of the pressure vessel.

[0027] Step 18: After the winding is completed, wrap the release cloth around the surface of the part, pre-extract the bag, and absorb the resin-rich winding layer.

[0028] Step 19: Remove the vacuum bag and conical auxiliary tooling, and wipe the unwound surface of the metal liner clean;

[0029] Step 20: Dry and cure the wound part, and remove the nozzle clamping fixture.

[0030] The significant advantages of this invention compared to existing technologies are:

[0031] 1) The enlarged winding layer and linear trajectory of non-equipolar ellipsoidal pressure vessels can be designed and verified through corresponding simulation methods to solve the problems of enlarged winding and linear design of non-equipolar ellipsoidal vessels, so as to achieve weight reduction and slow down fiber accumulation at the end cap.

[0032] 2) The tapered auxiliary tooling makes it easier for the fiber to slide down the tapered surface to the root of the flange, ensuring the continuous and stable fiber winding process, and the fiber gaskets are used to reinforce the stress concentration areas of the flange opening.

[0033] 3) The impact of the high-protrusion area of ​​the weld on the fiber winding is reduced by step-laying, and the weak area of ​​the weld is reinforced. Attached Figure Description

[0034] Figure 1 This is a schematic diagram of a metal liner structure with side flanges.

[0035] Figure 2 A schematic diagram illustrating the assignment of finite element simulation attributes to composite materials at various latitudes.

[0036] Figure 3 This is a schematic diagram of the assembly of the liner and the winding assembly.

[0037] Figure 4 This is a schematic diagram of adhesive film being applied to the surface of a metal lining.

[0038] Figure 5 A schematic diagram of the principle of the flange obstacle avoidance winding conical auxiliary tooling.

[0039] Figure 6 This is a schematic diagram of lateral flange reinforcement.

[0040] Figure 7 This is a schematic diagram of weld transition and reinforcement.

[0041] Figure 8 A schematic diagram of the distribution of each polar hole in the expansion winding and a cross-section of the shell at the equator. Detailed Implementation

[0042] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0043] Combination Figure 1 A typical non-equipolar orifice ellipsoidal metal liner 1 with a side flange mainly includes an equatorial straight section 12, an integrated side flange 13, a lower connector 14, an upper connector 15, an upper hemisphere 16, and a lower hemisphere 17. The equatorial straight section 12 is welded between the upper hemisphere 16 and the lower hemisphere 17, forming the main body of the ellipsoidal metal liner 1; the upper connector 15 is welded to the upper hemisphere 16, and the lower connector 14 is welded to the lower hemisphere 17, with the corresponding welding position being a circumferential weld 11; multiple integrated side flanges 13 are provided on the equatorial straight section 12. The design method of the winding layer of a non-equipolar orifice ellipsoidal pressure vessel with a liner and a side flange according to this embodiment includes the following steps:

[0044] Step 1: Test the tensile strength of the fiber multifilament; prepare NOL ring specimens and wound plate parts, and test the mechanical properties under tension, compression and shear.

[0045] Step 2: Calculate the latitudinal resistance T of the fiber winding layer on the ellipsoidal surface of the metal liner 1 with a minor semi-axis length of a and a major semi-axis length of b, using the following formula:

[0046]

[0047] Where M is the number of yarn bundles; W is the amount of fiber advance perpendicular to the fiber direction on the equator (during winding, the fiber advances W in the direction perpendicular to the current position each time to fully wind the entire container lining), W = W0 / sinα, W0 is the fiber yarn width; F is the single fiber resistance, which is the tensile strength of the selected carbon fiber; r is the radius of the latitude circle at any point on the ellipsoid; r0 is the radius of the envelope latitude circle; and α represents the winding angle.

[0048] f(x) is the position function of the fiber strength utilization coefficient:

[0049]

[0050] Where f1 is the strength utilization coefficient of the fiber at the pole pores; and f2 is the strength utilization coefficient of the fiber at the equator.

[0051] Step 3: Calculate the zonal internal force N when the ellipsoidal shell is subjected to internal pressure:

[0052]

[0053] P c This refers to the magnitude of the internal pressure borne by the ellipsoidal shell.

[0054] Step 4: Design the enlarged-hole envelope winding. First, wind uniformly distributed fibers within the minimum polar hole range of the lower end cap 14 and upper end cap 15 to meet the strength requirements near the opening ends of the lower end cap 14 and upper end cap 15, as the first winding layer c1, and calculate the latitudinal resistance T1 of each latitudinal fiber of the first winding layer c1.

[0055] Step 5: Calculate the magnitude of the latitudinal internal force N1 at each latitude of the open shell and compare it with the corresponding fiber resistance T1. Take the T1=N1 position of the two end caps as the new pole hole, and wind uniformly distributed fibers within the new winding starting range as the second winding layer c2. Calculate the latitudinal resistance T2 of the fibers at each latitude of the second winding layer c2.

[0056] Step 6: Calculate the latitudinal internal force N2 of the open shell formed by the new pole hole at each latitude, and compare it with the corresponding fiber resistance T1+T2. Take the T1+T2=N2 position of the two end caps as the new pole hole, and wind the uniformly distributed fiber within the new winding starting range as the third winding layer c3.

[0057] Step 7: Continue this process, adding more winding layers until near the equator, until the entire shell is wrapped with n layers of fiber, and the nth winding layer c n In each latitude, the resultant force of the latitudinal fiber resistance provided by each winding layer is greater than the latitudinal internal force of the corresponding open shell, i.e. The number of winding layers and the starting position of the enlarged hole winding are obtained to meet the overall structural strength index. T represents the resultant resistance of the weft fibers from layer 1 to layer n. i N represents the weft fiber resistance of the winding layer obtained in the i-th layer. n This represents the latitudinal internal force of the open shell corresponding to the nth layer.

[0058] Step 8: Using the non-geodetic winding formula, and assuming the slip coefficient λ is determined, calculate the winding angles for stable winding of each winding layer 2 in the upper hemisphere 16 and lower hemisphere 17 of the non-equipolar hole. The winding angles are obtained by the following formula:

[0059]

[0060] Where z represents the coordinate of the inner lining axis of the core mold.

[0061] Based on the changes in the winding angle of each winding layer 2 in the upper hemisphere 16 and lower hemisphere 17, the linear shape of the non-equipolar holes on both sides is smoothly and continuously transitioned in the equatorial straight section 12. For the metal liner 1 that does not meet the smooth transition requirement in the equatorial straight section 12, the dwell angle can be increased to ensure that the fibers cover the polar holes.

[0062] Step 9: Calculate the thickness t of each winding layer. f The thickness of the winding layer 2 is t f The following formula is used to calculate:

[0063]

[0064] Where t0 is the thickness of a single layer of the wound fiber at the equatorial straight section 12.

[0065] Step 10: Draw the 3D model of the pressure vessel and import it into the simulation software ABAQUS. The metal liner 1 is meshed using solid elements, and the composite layer 2 is meshed using shell elements. Based on the calculation results of the winding layer 2 in Steps 7 and 9, assign the winding angle and thickness of each winding layer to the composite element 21 at the same latitude, and input the mechanical property parameters of the composite material obtained in Step 1. Submit the calculation to verify the design results of the winding layer 2, and use fabric to reinforce the stress concentration area of ​​the winding layer opening interfering with the integrated lateral flange 13. Combined with... Figure 2 Based on the finite element simulation results, a layer of composite material fabric is added to the stress concentration area around the flange that exceeds the allowable stress range each time. Then, the fabric is continuously superimposed on the dangerous areas in the feedback results to meet the overall mechanical performance requirements.

[0066] The present invention also provides a method for forming an ellipsoidal pressure vessel winding layer with a lateral flange liner, comprising the following steps:

[0067] Step 11: Based on the design line, write the NC code for the winding machine in CADWIND software and run it on a trial basis to eliminate the risk of interference and collision.

[0068] Step 12: Weigh the metal liner 1 by weight m1.

[0069] Step 13: Apply silicone grease to the inside of the upper nozzle clamping fixture 4 and the lower nozzle clamping fixture 5, assemble them on the metal inner liner 1, and fix them on the three-jaw chuck of the winding machine.

[0070] Step 14, Combining Figure 3 , Figure 5 A tapered auxiliary tooling 3 is installed on the outside of the integrated side flange 13. The tapered auxiliary tooling 3 is fixed to the integrated side flange 13 using a set screw 31. A layer of adhesive release cloth is circumferentially pasted onto the cylindrical section of the tapered auxiliary tooling housing 32 to prevent adhesive from seeping into the set screw holes of the tapered auxiliary tooling 3. The tapered auxiliary tooling 3 is fitted onto the outside of the integrated side flange 13. The tapered auxiliary tooling 3 has a cylindrical cavity with a radius of x and a height of y. The internal cavity dimensions x and y are determined by the maximum envelope range of the integrated side flange 13. The outer diameter of the tapered auxiliary tooling 3 should be as small as possible to reduce the deflection of the wound fiber 8 and to allow space for tightening the set screw 31. The maximum wall thickness of the cylindrical section of the tapered auxiliary tooling must meet the requirement of 2mm ≤ t1 ≤ 5mm. The radius r of the cylindrical section of the tooling... f =x+t1; The shortest distance from the conical surface to the cavity in the vertical direction must ensure the rigidity requirement of the tooling, satisfying t2≥1mm; h3 is the distance from the center axis of the set screw to the bottom of the conical auxiliary tooling 3, taken from the middle of the internal flange clamping surface; h1 and h2 are the heights of the conical and cylindrical sections, respectively, guaranteed by the cone angle θ, generally θ is around 80°, which can ensure that the wound fiber 2 slides smoothly along the conical surface, satisfying:

[0071]

[0072] Step 15: Pre-treat the surface of the ellipsoidal metal liner 1:

[0073] The surface of the metal liner 1 is sanded with 180-grit sandpaper rings, alternating longitudinally until it becomes rough, and then the surface is cleaned with acetone or alcohol.

[0074] The protrusions in weld 11 were ground smooth, and the recessed areas were filled with resin. After the resin cured, the surface was ground smooth again, and then the surface was cleaned with acetone or alcohol.

[0075] Step 16: Locate the origin of the coordinate system. Run the NC code of each winding layer obtained in step 11 several times using dry fiber without adhesive impregnation to ensure that the origin is accurate and that no slippage occurs.

[0076] Step 17: Cut the J313 adhesive film into long strips and evenly paste it onto the surface of the metal lining 1, ensuring no obvious wrinkles are formed. The longitudinal adhesive film 61 in the upper hemisphere and the longitudinal adhesive film 62 in the lower hemisphere are arranged radially, while the circumferential adhesive film 63 at the equator is arranged circumferentially. Figure 4 As shown.

[0077] Step 18: Clean the winding machine, prepare CR06E epoxy resin with a resin component to curing agent component mass ratio of 100:33, stir evenly, degas under vacuum, and pour into the glue tank. Dry the HF40S carbon fiber, install and thread the yarn.

[0078] Step 19: Cut the carbon fiber fabric into long strips, and combine... Figure 6 According to the simulation results of the finite element model, fiber woven fabric is used to reinforce the area around the 13 holes of the integrated side flange by using fiber cloth gaskets. The overlap area 72 of the flange reinforcement fabric 71 is about 5mm, and glue is applied.

[0079] Step 19, Combining Figure 7 Measure the distance h between weld 11 and the surface of the shell. w If it is lower than the thickness t of a single layer of fiber woven fabric w If the value is greater than t, no compensation will be made; if the value is greater than t, no compensation will be made. w Then compensate [h] w / t w A layer of transition fabric 73 is added, and a reinforcing fabric 74 is added to the top layer of the weld. The layers of fabric are transitioned in a gradient manner, with a staggered length l. w It is about 5mm thick and coated with glue. [·] is the rounding symbol.

[0080] Step 20: Wet winding and expanding process. After the yarn is impregnated with resin and fixed, run the winding program shown in Step 4 to wind the c1~c1~c2~c3~c4~c5~c6~c7 ...7~ n Layered fibers. A helical winding method is used, with the diameter of the polar holes increasing sequentially until near the equator. Combined Figure 8 At this point in the equatorial region, the tank cross-section consists of, in sequence, a metal liner 1, an epoxy film 6, transition and reinforcing fabric 7, and various winding layers 2. Ultimately, 2n fiber accumulation rings 22 appear on the entire pressure vessel surface of the tank. During the winding process, excess resin is scraped off from the surface of the winding layer 2, and the remaining resin and fiber levels are constantly monitored and replenished as needed.

[0081] Step 21: After winding, wrap the CVP-230PA66 release cloth around the surface of the part, pre-extract the bag for 30 minutes to absorb the resin-rich wrapping layer.

[0082] Step 22: Remove the vacuum bag and conical auxiliary tool 3, and wipe the unwound surface of the metal liner 1 clean with acetone or alcohol.

[0083] Step 23: Place the wound part into a rotatable curing oven. During the heating and cooling stages, the temperature is controlled by air at a rate of no more than 2℃ / min. During the heat preservation stage, the heat preservation time and temperature are based on the hysteresis couple. After heat preservation at 120℃ for 2 hours, raise the temperature to 150℃ and heat preservation for another 6 hours. After heat preservation, cool with the oven. Open the oven door after the temperature reaches 60℃.

[0084] Step 24: Remove the upper nozzle clamping fixture 4 and the lower nozzle clamping fixture 5, remove surface burrs, and polish.

[0085] Step 25: Perform the corresponding parameter tests:

[0086] Measure the weight m2 of the pressure vessel after winding. From the weight m1 before winding obtained in step 14, the weight of the winding layer m = m1 - m2 is obtained.

[0087] Measure the maximum diameter at point 12 on the equatorial straight section of the pressure vessel after winding.

[0088] Conduct a water pressure test.

Claims

1. A method for designing the winding of a pressure vessel with an inner lining and a side flange, characterized in that, Includes the following steps: Step 1: Design the enlarged envelope circle winding. First, wind evenly distributed fibers within the minimum polar hole range of the lower and upper end caps to meet the strength requirements near the opening ends of the lower and upper end caps. This is the first winding layer. Calculate the latitudinal resistance of the fibers in each latitudinal direction of this first winding layer. Step 2: Calculate the magnitude of the latitudinal internal force at each latitude of the open shell and compare it with the corresponding fiber resistance. The point where the fiber latitudinal resistance and latitudinal internal force on both end caps are equal in magnitude is designated as a new pole hole. Within this new winding starting range, evenly distributed fibers are wound as the second winding layer. The latitudinal resistance of the fibers at each latitude of the second winding layer is then calculated using the following formula: Where T is the fiber weft resistance, M is the number of spools of yarn; W is the fiber's forward movement perpendicular to the fiber direction on the equator; F is the single fiber resistance, which is the tensile strength of the selected carbon fiber; r is the radius of the latitudinal circle at any point on the ellipsoid; r0 is the radius of the enveloping latitudinal circle; f(x) is the position function of the fiber strength utilization coefficient; a is the length of the minor semi-axis of the metal liner; b is the length of the major semi-axis of the metal liner. Step 3: Calculate the latitudinal internal forces of the open shell formed by the new pole hole at each latitude and compare them with the corresponding fiber resistance. The point where the corresponding fiber resistance and the corresponding latitudinal internal force of the two end caps are equal in magnitude is taken as the new pole hole. Wind uniformly distributed fibers within the new winding starting range as the third winding layer. The magnitude of the latitudinal internal forces of the open shell at each latitude is calculated using the following formula: Where N is the magnitude of the latitudinal internal force; r is the radius of the latitudinal circle at any point on the ellipsoid; r0 is the radius of the enclosing latitudinal circle; a is the length of the minor semi-axis of the metal liner; b is the length of the major semi-axis of the metal liner; P c The magnitude of the internal pressure borne by the ellipsoidal shell; Step 4: Continue in this manner, adding more winding layers until near the equator. The entire shell is wrapped with n layers of fiber, and the resultant force of the latitudinal fiber resistance provided by each winding layer at each latitude is greater than the latitudinal internal force of the corresponding open shell. Step 5: Using the non-geodetic winding formula, and assuming the slip coefficient is determined, calculate the winding angles for stable winding of each winding layer in the upper and lower hemispheres of the non-equipolar hole. Step 6: Calculate the thickness of each winding layer; Step 7: Draw a 3D model of the pressure vessel and import it into the simulation software. The metal liner is divided into solid elements, and the composite layer is divided into shell elements. According to the winding angle and the thickness of the winding layer, assign the winding angle and thickness of each winding layer of the composite element at the same latitude, and input the mechanical property parameters of the composite material. Use fabric to reinforce the stress concentration area of ​​the winding layer opening of the integrated lateral flange interference. Add a layer of composite fabric to the stress concentration area around the flange that exceeds the allowable stress range each time, and then continuously add fabric to the dangerous areas in the feedback results to meet the overall mechanical performance requirements.

2. The pressure vessel winding design method with lateral flange as described in claim 1, characterized in that, The position function of the fiber strength utilization coefficient is: Where f1 is the strength utilization coefficient of the fiber at the pole pores; and f2 is the strength utilization coefficient of the fiber at the equator.

3. The pressure vessel winding design method with lateral flange as described in claim 1, characterized in that, The winding angle is calculated using the following formula: in Indicates the coordinates of the inner lining axis of the core mold; λ is the winding angle; λ is the slip coefficient; r is the radius of the latitude circle at any point on the ellipsoid.

4. The pressure vessel winding design method with lateral flange as described in claim 1, characterized in that, Wrapping layer thickness t f The following formula is used to calculate: Where r is the radius of the latitude circle at any point on the ellipsoid; r0 is the radius of the enveloping latitude circle; a is the length of the minor semi-axis of the metal lining; and W0 is the width of the fiber yarn.

5. The pressure vessel winding design method with lateral flange as described in claim 1, characterized in that, The forming of the winding layer for an ellipsoidal pressure vessel includes the following steps: Step 8: Based on the design line, write the NC code for the winding machine in CADWIND software and run it for trial operation to eliminate the risk of interference and collision; Step 9: Fix the metal liner onto the three-jaw chuck of the winding machine using the spigot clamping fixture; Step 10: Install the tapered auxiliary tooling on the outside of the integrated side flange; Step 11: Roughen and clean the surface of the metal lining; Step 12: Test run the NC code of each winding layer with dry fiber without glue to ensure that the origin is accurate and that there is no slippage. Step 13: Apply adhesive film to the surface of the metal lining; Step 14: Dry the carbon fiber, install it onto the winding machine and thread it; Step 15: Reinforce with integrated lateral flange hole periphery fiber cloth gasket; Step 16: Measure the distance h between the weld and the shell surface. w If it is lower than the thickness t of a single layer of fiber fabric w If the value is greater than t, no compensation will be made; if the value is greater than t, no compensation will be made. w Then compensate [h] w / t w A layer of transition fabric is applied, and a reinforcing fabric is added to the top layer of the weld. The layers of fabric are transitioned in a gradient manner and then coated with adhesive. Step 17: Wet-process expansion and winding molding. After the yarn is impregnated with glue and fixed, the winding program is run to wind the n layers of fiber designed by the container winding layer design method in sequence. The spiral winding method is adopted, and the diameter of the polar hole of the winding layer increases sequentially until it reaches the vicinity of the equator. Finally, 2n fiber accumulation rings appear on the entire surface of the pressure vessel. Step 18: After the winding is completed, wrap the release cloth around the surface of the part, pre-extract the bag, and absorb the resin-rich winding layer. Step 19: Remove the vacuum bag and conical auxiliary tooling, and wipe the unwound surface of the metal liner clean. Step 20: Dry and cure the wound part, and remove the nozzle clamping fixture.

6. The pressure vessel winding design method with lateral flange as described in claim 5, characterized in that, Before molding, the weight of the metal liner must be weighed. After molding, the weight of the pressure vessel after winding is measured to obtain the weight of the winding layer. The maximum diameter of the equatorial straight section of the pressure vessel after winding is also measured.

7. The pressure vessel winding design method with lateral flange as described in claim 5, characterized in that, The conical auxiliary tooling satisfies: Where h1 and h2 are the heights of the conical and cylindrical segments, respectively; θ is the cone angle; x and y are the cavity radius and height, respectively; r f t1 is the radius of the cylindrical segment; t2 is the maximum wall thickness of the cylindrical segment; t3 is the shortest distance from the conical surface to the cavity in the vertical direction.

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