Metal diaphragm tank for rocket and method of making and assembling same

Abstract

The application provides a metal diaphragm storage tank for a hopper and a manufacturing and assembling method thereof, which comprises an air path shell, a liquid path shell, a metal diaphragm, a composite material winding layer and a porous plate. The air path shell is integrally formed by a connecting ring, an air path half-sphere and an air path connector and is provided with the porous plate; the liquid path shell is integrally formed by a shell flange, a liquid path half-sphere and a liquid path connector; the application solves the problems of fatigue rupture of the metal diaphragm and deformation of the flange caused by long-term storage and work of the hopper on the moon surface with great temperature change, the problem of bearing design of the thin shell caused by the offset design of the flange due to the narrow space layout of the hopper, and meets the lightweight demand of the hopper propulsion system.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of space vehicle tank, in particular, relates to a metal diaphragm tank for a leap vehicle and a manufacturing and assembling method thereof. BACKGROUND

[0002] In the field of space propulsion, propellant tank is one of the important components of attitude and orbit control power system, and its main function is to store propellant and provide propellant without air inclusion for downstream engine during work. Metal diaphragm is widely used in various space vehicles due to its long-life storage, superior transverse acceleration resistance, strong liquid sloshing resistance, lightweight and other advantages.

[0003] Limited by the thrust of the lunar exploration launch vehicle, the overall weight design of the leap vehicle needs to be extremely lightweight, and the performance indicators of the tank that affect the weight of the leap vehicle propulsion subsystem, i.e. the tank weight and discharge efficiency, have more stringent requirements. At the same time, in order to make the space layout of the leap vehicle propulsion system more compact and efficient, the tank shell flange needs to be adjusted from the previous connection ring at the equator of the shell to the weak liquid path shell, and the design requirement of the offset flange will cause a severe stress environment of the shell which may lead to shell rupture. In addition, compared with the metal diaphragm tank for deep space exploration, the leap vehicle tank needs to be stored and worked for a long time on the moon surface with large temperature difference, which will cause large deformation of the shell flange and damage the composite tank cabin, and the long storage and working time will cause fatigue rupture of the metal diaphragm. The existing metal diaphragm tank cannot solve the above problems, therefore, it is urgent to provide a metal diaphragm tank for a leap vehicle.

[0004] Further, when the metal diaphragm tank works on the moon surface with pressure, under the combined action of the propellant volume change force caused by the alternating pressure of the air cavity and the temperature of the moon surface, the metal diaphragm will produce repeated fatigue, and the existing metal diaphragm has weak fatigue resistance and cannot meet the requirements of long-term storage and work on the moon surface; the metal diaphragm tank will produce large radial deformation and damage the cabin due to large change of the environmental temperature during long-term work on the moon surface; and the flange of the traditional metal diaphragm tank is usually located near the connection ring at the equator of the shell, and the severe stress environment of the shell caused by the design requirement of the offset flange;

[0005] The related prior art: metal propellant tank for aerospace and manufacturing method thereof (patent document CN104648696A), which provides a metal propellant tank for aerospace and a manufacturing method thereof, adopts a full-metal diaphragm tank, which is heavy in quality and poor in material capacity to withstand damage caused by large radial deformation of the tank; and in the technical solution thereof, the gas path nozzle is straight, which may cause instability of the top of the metal diaphragm when the gas cavity gas speed is high, greatly affecting safety; in addition, the shell weld of this manufacturing method is more, which brings the rise of manufacturing cost and reduces the reliability of the tank, and the tank works when the gas cavity is inflated, the lunar storage brings the change of propellant saturated vapor pressure; since the technical solution disclosed in the patent document, the diaphragm has not been subjected to a special treatment process, and under the action of the above factors, the diaphragm will experience repeated movement fatigue, resulting in rupture, which ultimately affects the failure of the task.

[0006] In view of the technical problems in the prior art, the present application provides a metal diaphragm tank for a hopper and a manufacturing and assembling method thereof. SUMMARY

[0007] In view of the defects in the prior art, the present application aims to provide a metal diaphragm tank for a hopper and a manufacturing and assembling method thereof.

[0008] According to the present application, a metal diaphragm tank for a hopper is provided, comprising: a gas path shell 1, a liquid path shell 2, a metal diaphragm 3, a gas path connector 6 and a porous plate 10.

[0009] The gas path connector 6 is arranged in the gas path shell 1.

[0010] The porous plate 10 is embedded in the gas path connector 6.

[0011] The gas path shell 1 is arranged on one side of the metal diaphragm 3, and the liquid path shell 2 is arranged on the other side of the metal diaphragm 3.

[0012] Preferably, the gas path shell 1 further comprises a connecting ring 4 and a gas path hemisphere 5; a gas cavity 13 is formed between the outer periphery of the metal diaphragm 3 and the gas path shell 1.

[0013] The liquid path shell 2 comprises a shell flange 7, a liquid path hemisphere 8 and a liquid path connector 9; a liquid cavity 14 is formed between the inner periphery of the metal diaphragm 3 and the liquid path shell 2.

[0014] The connecting ring 4, the gas path hemisphere 5 and the gas path connector 6 are integrally formed; the shell flange 7, the liquid path hemisphere 8 and the liquid path connector 9 are integrally formed.

[0015] The gas path connector 6 is provided with a cylindrical groove, and the porous plate 10 is embedded in the cylindrical groove in the gas path connector 6.

[0016] The gas path connector 6 and the liquid path connector 9 are both plunger type sealed connectors, and both are provided with a hexagonal structure for easy clamping.

[0017] Preferably, the wall thickness of the gas path shell 1 is 0.7-1.0 mm.

[0018] Preferably, the inner profile of the liquid path shell 2 is mainly composed of a cylinder segment, a sphere segment and an ellipsoid segment; the radius R2 of the sphere segment is equal to the radius R1 of the metal diaphragm; the ellipsoid segment has an ellipsoid long semi-axis a = 0.9-1.4R1 and an ellipsoid short semi-axis b = 0.4-0.7R1; the wall thickness of the ellipsoid segment of the liquid path shell 2 is 0.7-1.0 mm, and the wall thickness of the rest of the shell is 1.0-1.5 mm; the wall thickness of the liquid path shell 2 above the shell flange 7 is equal and is 1.0-1.5 mm, and the transition between the shell flange 7 and the ellipsoid segment is a transition sphere to a straight line, and the wall thickness is transitioned from 1.0-1.5 mm to 0.7-1.0 mm.

[0019] Preferably, the inner profile of the metal diaphragm 3 is mainly composed of a cone segment, a transition sphere segment and a sphere segment, and the different segments are tangent to each other and smoothly connected; the wall thickness of the metal diaphragm 3 gradually increases from 1.4 to 2.0 mm, and the material used is pure aluminum.

[0020] Preferably, the metal diaphragm storage tank for the flying device further comprises a composite winding layer 1112.

[0021] The composite winding layer 1112 comprises a shell winding layer 11 and a flange annular reinforcing layer 12.

[0022] The outer side of the gas path shell 1 and the liquid path shell 2 is wound with a shell winding layer 11.

[0023] The flange annular reinforcing layer 12 is wound on the annular outer side of the shell winding layer 11.

[0024] Preferably, the shell winding layer 11 and the flange annular reinforcing layer 12 use T800 or T1000 fiber; the shell winding layer 11 has a winding layer thickness of 1-1.5 mm; the flange annular reinforcing layer 12 is annularly wound at a distance of 20-30 mm from the upper surface of the shell flange 7 to the upper surface of the shell flange 7, and the winding thickness is 4-6 mm.

[0025] Preferably, the multi-hole plate 10 is provided with holes of different hole diameters, including large holes in the middle and small holes uniformly distributed around the periphery, and the total area of the holes is not less than the flow area of the gas path connector 6; the cross section of the multi-hole plate 10 is rectangular; and the shape of the holes can be circular or elliptical.

[0026] Preferably, the application provides a manufacturing and assembly method for the metal diaphragm storage tank for the flying device provided by the application, which comprises:

[0027] Step S1: using the shell mold to form a spherical forging by die forging, and then forming the gas path shell 1 and the liquid path shell 2 by machining;

[0028] Step S2: the metal diaphragm 3 is processed by stamping and flanging of the plate material respectively by using the forming die and the flanging die, the metal diaphragm 3 is machined according to the wall thickness size requirement, and the metal diaphragm 3 is heat treated;

[0029] Step S3: using a bar to form a perforated plate 10 by machining;

[0030] Step S4: the perforated plate 10 is fixed in the cylindrical groove of the gas path connector 6 by stamping, the punching points are 6 to 12, and the punching points are uniformly arranged and kept fastened;

[0031] Step S5: the metal diaphragm 3 is flanged and welded with the connecting ring 4 on the gas path shell 1 after the installation of the perforated plate 10;

[0032] Step S6: the liquid path shell 2 and the gas path shell 1 are welded to form an inner lining shell;

[0033] Step S7: the inner lining shell is wound according to the winding procedure to form a shell winding layer 11, and then a flange ring reinforcing layer 12 is wound around the flange 7.

[0034] Preferably, in the manufacturing and assembling method of the metal diaphragm storage tank of the flying device, the heat treatment temperature of the metal diaphragm 3 after forming is 420-430 DEG C, and the heat treatment time is 4-6h; the cylindrical groove after stamping deformation ensures that the perforated plate 10 does not fall off;

[0035] The raw materials for processing the gas path shell 1, the liquid path shell 2 and the perforated plate 10 are aluminum alloy.

[0036] Compared with the prior art, the present application has the following beneficial effects:

[0037] 1. The present application improves the fatigue resistance of the metal diaphragm by improving the heat treatment parameters of the metal diaphragm, so that the metal diaphragm storage tank can be stored for more than 30 days on the moon, and the fatigue problem of the metal diaphragm in the prior art is solved; in particular, when the storage tank works, the gas cavity is inflated, the propellant saturated vapor pressure changes during storage on the moon, and the diaphragm will experience repeated movement fatigue under the action of the two, the present application sets the heat treatment temperature and time of the diaphragm in a specific range, so that the fatigue resistance of the diaphragm is improved, and the long-term storage requirement on the moon can be met.

[0038] 2、The application can make the single side radial deformation of the tank not more than 0.2% of the flange radius by adding a certain thickness flange ring reinforcement layer on the upper surface of the flange, avoiding the damage of the cabin due to the large radial deformation of the metal diaphragm tank caused by the large change of the environmental temperature.

[0039] 3、The application sets the offset flange on the weak liquid path shell, and the transition reinforcement design of the liquid path shell near the flange compensates the poor stress environment of the shell caused by the design requirement of the offset flange, and realizes the optimization of the space layout of the whole vehicle.

[0040] 4、The application improves the inner surface shape and design parameters of the liquid path shell, so that the discharge efficiency of the spherical metal diaphragm exceeds 99%, the discharge efficiency of the metal diaphragm tank is improved, and the weight of the whole vehicle is reduced.

[0041] 5、The application uses the aluminum alloy forging to forge a spherical forging, and then processes the gas path and liquid path shell, and then welds, so that the spherical shell has only one weld, and the reliability of the metal diaphragm tank is improved.

[0042] 6、The application solves the instability problem of the top of the diaphragm caused by the straight-through nozzle when rapidly inflating by setting a perforated plate on the gas path connector.

[0043] 7、The overall structure of the application solves the problems of metal diaphragm fatigue rupture and flange deformation caused by the long-term storage and work of the whole vehicle on the moon with large temperature changes, the bearing design problem of the thin-walled shell caused by the offset design of the flange due to the narrow space layout of the whole vehicle, and meets the lightweight demand of the whole vehicle propulsion system. BRIEF DESCRIPTION OF DRAWINGS

[0044] Other features, objects and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments, made with reference to the accompanying drawings:

[0045] Figure 1 A metal diaphragm tank structure for a whole vehicle provided by the application.

[0046] Figure 2 A metal diaphragm tank structure provided by the application Figure 1 A local enlarged view of P in the metal diaphragm tank structure.

[0047] Figure 3 A flange provided by the application.

[0048] Figure 4 A perforated plate structure provided by the application.

[0049] DETAILED DESCRIPTION

[0050] The application will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the application, but do not limit the application in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the application. These are within the scope of the application.

[0051] As shown in the drawings, the metal diaphragm tank for the hopper is provided, which comprises an air path shell 1, a liquid path shell 2, a metal diaphragm 3, an air path connector 6 and a porous plate 10. Figure 1 The air path shell 1 comprises a connecting ring 4 and an air path hemisphere 5; the metal diaphragm 3 and the air path shell 1 form an air cavity 13; the liquid path shell 2 comprises a shell flange 7, a liquid path hemisphere 8 and a liquid path connector 9; the metal diaphragm 3 and the liquid path shell 2 form a liquid cavity 14; the connecting ring 4, the air path hemisphere 5 and the air path connector 6 are integrally formed; the shell flange 7, the liquid path hemisphere 8 and the liquid path connector 9 are integrally formed and have no welding seam therebetween, so that the reliability is high and the production cost is low; the air path connector 6 is provided with a cylindrical groove, and the porous plate 10 is embedded in the cylindrical groove in the air path connector 6.

[0052] Further, the wall thickness of the air path shell 1 is 0.7-1.0 mm; the inner profile of the liquid path shell 2 mainly comprises a column segment, a spherical segment and an ellipsoidal segment; the radius R2 of the spherical segment is equal to the radius R1 of the metal diaphragm; the ellipsoidal length half axis a of the ellipsoidal segment is 0.9-1.4R1, and the ellipsoidal short half axis b is 0.4-0.7R1; such structure and parameter matching can significantly improve the metal diaphragm discharge efficiency to more than 99%; the wall thickness of the ellipsoidal segment of the liquid path shell 2 is 0.7-1.0 mm, and the wall thickness of the rest of the shell is 1.0-1.5 mm; the wall thickness of the part above the shell flange 7 of the liquid path shell 2 is equal and is 1.0-1.5 mm, and the transition between the shell flange 7 and the ellipsoidal segment is a transition spherical shape to a straight line shape, and the wall thickness is transitioned from 1.0-1.5 mm to 0.7-1.0 mm. The above technical features can ensure shell reinforcement without affecting fiber winding, and prevent the phenomenon of fiber arching; the shell flange 7 is arranged lower, which has better space layout for the hopper system, and the shell reinforcement technical solution of the application can ensure the mechanical strength of the position of the shell flange 7 in the mechanical environment, and prevent the weakening of the bearing capacity due to the thin wall thickness.

[0053] Further, the wall thickness of the air path shell 1 is 0.7-1.0 mm; the inner profile of the liquid path shell 2 mainly comprises a column segment, a spherical segment and an ellipsoidal segment; the radius R2 of the spherical segment is equal to the radius R1 of the metal diaphragm; the ellipsoidal length half axis a of the ellipsoidal segment is 0.9-1.4R1, and the ellipsoidal short half axis b is 0.4-0.7R1; such structure and parameter matching can significantly improve the metal diaphragm discharge efficiency to more than 99%; the wall thickness of the ellipsoidal segment of the liquid path shell 2 is 0.7-1.0 mm, and the wall thickness of the rest of the shell is 1.0-1.5 mm; the wall thickness of the part above the shell flange 7 of the liquid path shell 2 is equal and is 1.0-1.5 mm, and the transition between the shell flange 7 and the ellipsoidal segment is a transition spherical shape to a straight line shape, and the wall thickness is transitioned from 1.0-1.5 mm to 0.7-1.0 mm. The above technical features can ensure shell reinforcement without affecting fiber winding, and prevent the phenomenon of fiber arching; the shell flange 7 is arranged lower, which has better space layout for the hopper system, and the shell reinforcement technical solution of the application can ensure the mechanical strength of the position of the shell flange 7 in the mechanical environment, and prevent the weakening of the bearing capacity due to the thin wall thickness.

[0054] Further, the inner profile of the metal diaphragm 3 is mainly composed of a tapered section, a transition ball section and a ball section, and the different sections are tangent to each other and smoothly connected, the wall thickness of the metal diaphragm 3 gradually increases from 1.4 to 2.0 mm, and the material used is pure aluminum.

[0055] The metal diaphragm tank for the hopper further comprises a composite material winding layer 1112, the composite material winding layer 1112 comprises a shell winding layer 11 and a flange annular reinforcing layer 12, the outer side of the gas path shell 1 and the liquid path shell 2 is wound with the shell winding layer 11, and the flange annular reinforcing layer 12 is wound on the annular outer side of the shell winding layer 11; further, the shell winding layer 11 and the flange annular reinforcing layer 12 use fiber T800 or T1000, the winding layer thickness of the shell winding layer 11 is 1-1.5 mm, and the flange annular reinforcing layer 12 solves the technical problem that the existing tank cabin cannot withstand the damage caused by the large radial deformation of the tank due to the use of composite materials, and under the same working pressure and burst pressure indicators, the overall tank weight of the embodiment is lighter.

[0056] Further, the multi-hole plate 10 is provided with holes with different hole diameters, including large holes in the middle and small holes uniformly distributed around, and the total area of the holes is not less than the flow passage area of the gas path connector 6; the cross section of the multi-hole plate 10 is rectangular; the shape of the holes can be circular or elliptical; the gas path connector 6 and the liquid path connector 9 are both plunger type sealed connectors and are provided with a hexagonal structure for easy clamping; a plurality of threads are designed in the hexagonal structure of the gas path connector 6 for welding clamping and fixing, and the number of threads can be 6-8; the flange annular reinforcing layer 12 is annularly wound at a distance of 20-30 mm from the upper surface of the shell flange 7 to the upper surface of the shell flange 7, and the winding thickness is 4-6 mm, and the arrangement of the multi-hole plate 10 can improve the instability of the top of the metal diaphragm when the gas cavity gas velocity is high.

[0057] The application will be described in more detail below.

[0058] As shown in Figure 3 The flange corners are rounded to prevent the composite material fibers from being cut and damaged when winding over the flange; the gas path shell 1, the liquid path shell 2 and the multi-hole plate 10 are made of aluminum alloy;

[0059] The application also provides a manufacturing and assembling method of the metal diaphragm tank for the hopper, comprising:

[0060] Step S1: using a shell mold to form a spherical forging by die forging, and then forming the gas path shell 1 and the liquid path shell 2 by machining;

[0061] Step S2: the metal diaphragm 3 is processed by stamping and flanging of the plate material respectively using a forming die and a flanging die, the metal diaphragm 3 is machined according to the wall thickness size requirement, and the metal diaphragm 3 is heat treated;

[0062] Step S3: the porous plate 10 is formed by machining using a bar material;

[0063] Step S4: the porous plate 10 is fixed in the cylindrical groove of the gas path connector 6 by stamping, the punch points are 6-12 uniformly distributed, and at this time, the fastening can be maintained;

[0064] Step S5: the metal diaphragm 3 is welded with the connecting ring 4 on the gas path shell 1 after the flanging and installation of the porous plate 10;

[0065] Step S6: the liquid path shell 2 and the gas path shell 1 are welded to form an inner lining shell;

[0066] Step S7: the inner lining shell is wound according to the winding procedure to form the metal diaphragm storage tank for a hopper vehicle.

[0067] Further, in step S2, the heat treatment temperature of the formed metal diaphragm 3 is 420-430 DEG C, and the heat treatment time is 4-6 h; the cylindrical groove after stamping deformation ensures that the porous plate 10 does not fall off;

[0068] In summary, the present application provides a metal diaphragm storage tank for a hopper vehicle and a manufacturing and assembling method thereof, which comprises a gas path shell 1, a liquid path shell 2, a metal diaphragm 3, a composite material winding layer 1112 and a porous plate 10. The gas path shell 1 comprises a connecting ring 4, a gas path hemisphere 5 and a gas path connector 6 integrally formed and provided with the porous plate 10; the liquid path shell 2 comprises a shell flange 7, a liquid path hemisphere 8 and a liquid path connector 6 integrally formed; the problems of metal diaphragm fatigue rupture and flange deformation caused by long-term storage and work of the hopper vehicle on the moon surface with large temperature changes are solved, the problem of thin-walled shell bearing design caused by flange offset design due to the narrow space layout of the hopper vehicle is solved, and the lightweight demand of the hopper vehicle propulsion system is met.

[0069] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, therefore cannot be understood as a limitation on the present application.

[0070] The specific embodiments of the present application are described above. It needs to be understood that the present application is not limited to the specific embodiments described above, and various changes or modifications can be made by those skilled in the art within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be combined with each other at will without conflict.

Claims

1. A metal diaphragm storage tank for a leap vehicle, characterized in that, The utility model provides a kind of gas-liquid separation device, including: Gas path shell (1), liquid path shell (2), metal diaphragm (3), gas path connector (6) and porous plate (10); The gas path connector (6) is arranged in the gas path shell (1); The porous plate (10) is embedded in the gas path connector (6); The gas path shell (1) is arranged on one side of the metal diaphragm (3), and the liquid path shell (2) is arranged on the other side of the metal diaphragm (3); The gas path shell (1) further includes a connecting ring (4) and a gas path hemisphere (5), and a gas cavity (13) is formed between the outer periphery of the metal diaphragm (3) and the gas path shell (1); The liquid path shell (2) includes a shell flange (7), a liquid path hemisphere (8) and a liquid path connector (9), and a liquid cavity (14) is formed between the inner periphery of the metal diaphragm (3) and the liquid path shell (2); The connecting ring (4), the gas path hemisphere (5) and the gas path connector (6) are integrally formed, and the shell flange (7), the liquid path hemisphere (8) and the liquid path connector (9) are integrally formed. The gas path connector (6) is provided with a cylindrical groove, and the porous plate (10) is embedded in the cylindrical groove in the gas path connector (6); The gas path connector (6) and the liquid path connector (9) are both plunger type sealed interfaces and are provided with a hexagonal structure for easy clamping. Further comprising a composite material winding layer (1112). The composite material winding layer (1112) includes a shell winding layer (11) and a flange annular reinforcing layer (12). The gas path shell (1) and the liquid path shell (2) are both wrapped with the shell winding layer (11). The flange annular reinforcing layer (12) is wrapped on the annular outer side of the shell winding layer (11). The shell winding layer (11) and the flange annular reinforcing layer (12) use fiber T800 or T1000, and the flange annular reinforcing layer (12) is annularly wrapped at a distance of 20-30 mm from the upper surface of the shell flange (7) to the upper surface of the shell flange (7).

2. The metal diaphragm tank for a jump starter according to claim 1, wherein The wall thickness of the gas path shell (1) is 0.7-1.0 mm.

3. The metal diaphragm tank for a jump starter of claim 1, wherein, The inner profile of the liquid path shell (2) is mainly composed of a cylinder segment, a sphere segment and an ellipsoid segment, the radius R2 of the sphere segment is equal to the radius R1 of the metal diaphragm, the ellipsoid length half axis a of the ellipsoid segment is 0.9-1.4R1, and the ellipsoid short half axis b is 0.4-0.7R1, the wall thickness of the ellipsoid segment of the liquid path shell (2) is 0.7-1.0 mm, and the wall thickness of the rest of the shell is 1.0-1.5 mm, the wall thickness of the part above the shell flange (7) of the liquid path shell (2) is equal and 1.0-1.5 mm, and the wall thickness of the transition sphere from the shell flange (7) to the ellipsoid segment is 0.7-1.0 mm.

4. The metal diaphragm tank for a jump starter according to claim 3, wherein The inner profile of the metal diaphragm (3) is mainly composed of a cone segment, a transition sphere segment and a sphere segment, the different segments are tangent to each other and smoothly connected, the wall thickness of the metal diaphragm (3) gradually increases from 1.4 to 2.0 mm, and the material used is pure aluminum.

5. The metal diaphragm tank for a jump starter of claim 1, wherein, The winding layer thickness of the shell winding layer (11) is 1-1.5 mm, and the winding thickness of the flange annular reinforcing layer (12) is 4-6 mm.

6. The metal diaphragm tank for a jump starter of claim 1, wherein, The porous plate (10) is provided with holes of different sizes, including large holes in the middle and small holes uniformly distributed around the periphery, and the total area of the holes is not less than the flow area of the gas path connector (6); the cross section of the porous plate (10) is rectangular; the shape of the holes is circular or elliptical.

7. A method for manufacturing and assembling the metal diaphragm tank for the flying machine according to any one of claims 1 to 6, comprising: Step S1: using a shell mold to form a spherical forging by die forging, and then machining the gas path shell (1) and the liquid path shell (2) by machining; Step S2: the metal diaphragm (3) is processed by stamping and flanging of sheet metal respectively using a forming die and a flanging die, and the metal diaphragm (3) is machined according to the wall thickness size requirement, and the metal diaphragm (3) is heat treated; Step S3: using a bar to form a porous plate (10) by machining; Step S4: the porous plate (10) is fixed in the cylindrical groove of the gas path connector (6) by stamping, the punching points are 6 to 12, the punching points are uniformly arranged, and the fastening is kept; Step S5: weld the connecting ring (4) on the gas path shell (1) after the metal diaphragm (3) is flanged and the porous plate (10) is installed; Step S6: weld the liquid path shell (2) and the gas path shell (1) to form an inner liner shell; Step S7: wind the inner liner shell according to the winding procedure to wind the shell winding layer (11), and then wind the flange circumferential reinforcing layer (12) around the shell flange (7).

8. The method of claim 7, wherein the metal diaphragm tank is manufactured and assembled by the steps of: In step S2, the heat treatment temperature of the formed metal diaphragm (3) is 420-430℃, and the heat treatment time is 4-6h; the cylindrical groove after stamping deformation ensures that the porous plate (10) does not fall off; The raw materials for processing the gas path shell (1), the liquid path shell (2) and the porous plate (10) are aluminum alloy.

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