JP7398331B2 - Fuel loading structure and its manufacturing method - Google Patents

Description

The present invention relates to a fuel loading structure for loading liquid fuel in an area other than the effective space in the central portion of an airframe, and a method for manufacturing the same.

An airframe (for example, an aircraft fuselage) is a hollow cylindrical structure centered on its axis, and has a frame, stringers, and a skin as structural members.
The frame is a member that extends in a circular or arc shape in the circumferential direction of the hollow cylindrical structure, and the stringer is a member that extends linearly in the axial direction of the structure.
The frame and stringers typically have an H-shaped, T-shaped, or L-shaped cross-sectional shape, intersect with each other, and are connected at intersections to form the frame of the fuselage.
The skin is an arc-shaped flat plate attached to the outer surface of the aircraft frame, and is integrated with the frame and stringers to increase the rigidity of the aircraft (for example, the fuselage), and also serves to spatially partition the inside and outside of the aircraft. has.

The above-mentioned frames, stringers, and skins have conventionally been mainly made of metal (duralumin, etc.), and rivets or welding have been used to connect them.
However, from the viewpoint of reducing the weight of aircraft, it is desired that the fuselage (fuselage and wings) be made of composite material (for example, CFRP: carbon fiber reinforced plastic).
Further, when the aircraft body is made of a composite material (CFRP), it has been proposed to use, for example, a space surrounded by a CFRP structure in a wing as a fuel tank (for example, Patent Document 1).

Japanese Patent Application Publication No. 2012-187808

When using a space surrounded by a CFRP structure in an aircraft body (for example, inside a wing) as a fuel tank, there are the following problems.
It is necessary to run piping and wiring for flight control inside the wings of an aircraft, and in the case of small aircraft, there may be a shortage of space for installing fuel tanks.
Also, installing a fuel tank inside the aircraft reduces the effective space in the center of the aircraft (space for carrying cargo and personnel).

The present invention was devised to solve the above-mentioned problems. That is, an object of the present invention is to provide a fuel loading structure and a method for manufacturing the same, which can carry the necessary fuel while minimizing the reduction in effective space in the center of the fuselage when the fuselage is constructed of composite materials. It is about providing.

According to the present invention, there is provided a fuel loading structure constituting an airframe,
a stringer extending in the axial direction of the fuselage;
A frame extending in the circumferential direction of the aircraft body,
The stringer and the frame are each hollow tubes,
an outer layer made of fiber-reinforced plastic that has a tensile strength that exceeds the in-plane stress caused by the pressure of the liquid fuel filled inside;
A fuel mounting structure is provided, which includes a liner that is in close contact with the inner surface of the outer layer and has corrosion resistance and airtightness against the liquid fuel.

Further, according to the present invention, there is provided a method for manufacturing the above-mentioned fuel loading structure, comprising:
a plurality of stringers are arranged so as to extend in the axial direction at intervals in the circumferential direction;
The plurality of frames are arranged so that at least some of the frames extend in the circumferential direction at intervals in the axial direction,
A method of manufacturing a fuel loading structure is provided, in which the stringer and the frame are heated to a temperature exceeding the melting point of a thermoplastic resin and are firmly connected to each other at intersections to form a single skeleton as a whole.

According to the configuration of the present invention, since the stringer and the frame have an outer layer made of fiber-reinforced plastic and a liner having corrosion resistance and airtightness, the fuselage can be made of a composite material and can be lightweight.

Further, the stringer and the frame are each hollow tubes, and each outer layer has a tensile strength that exceeds the in-plane stress due to the pressure of liquid fuel, and the liner (inner layer) has corrosion resistance against liquid fuel and airtightness. This makes it possible to fill the hollow tubes of the stringer and frame with liquid fuel, reducing the conventional fuel loading space.

Furthermore, since the fuel carrying structure constitutes the fuselage (for example, the fuselage of an aircraft), the necessary fuel can be loaded with minimal reduction in the effective space in the center of the fuselage, allowing for more cargo and personnel. can be mounted on an aircraft.

FIG. 1 is an overall configuration diagram of a first embodiment of a fuel loading structure. FIG. 2 is an enlarged view of a quarter circle corresponding to the lower right portion of FIG. 1(B). FIG. 3 is a perspective view of FIG. 2; It is a sectional view of a stringer. FIG. 4 is a perspective view similar to FIG. 3 of a second embodiment of the fuel loading structure.

Hereinafter, embodiments of the present invention will be described in detail based on the accompanying drawings. Note that common parts in each figure are given the same reference numerals, and redundant explanation will be omitted.

FIG. 1 is an overall configuration diagram of a first embodiment of a fuel loading structure 100 according to the present invention.
In this figure, (A) is a side view, and (B) is a sectional view taken along the line BB.

In FIG. 1, a fuel loading structure 100 is a hollow cylindrical structure that constitutes a fuselage 1 (for example, an aircraft fuselage) and surrounds an inner cargo space 2.
The fuselage 1 is, for example, the fuselage of an aircraft, but may also be the fuselage of a flying object other than an aircraft (such as an artificial satellite, a rocket, etc.).
Hereinafter, in Fig. 1(A), the central axis of the hollow cylinder is defined as the Z-axis, in Fig. 1(B), the center is defined as O, the horizontal axis passing through the center O is the X-axis, and the vertical axis passing through the center O is the Y-axis. do.
Note that the fuel loading structure 100 is not limited to a completely hollow cylindrical shape, but may be a hollow ellipse or may have a partially deformed portion.

2 is an enlarged view of a quarter circle corresponding to the lower right portion of FIG. 1(B), and FIG. 3 is a perspective view of FIG. 2.

1 to 3, a fuel loading structure 100 includes a plurality of stringers 10 and a plurality of frames 20. In FIGS.
The plurality of stringers 10 extend in the axial direction (Z-axis direction) of the fuselage 1 at intervals in the circumferential direction. Aircraft 1 is a fuselage in this example.
At least some of the frames 20 extend in the circumferential direction of the fuselage 1 with intervals in the axial direction.
Further, the stringer 10 and the frame 20 are firmly connected to each other at the intersection, and constitute a single skeleton F as a whole. The intersection of the stringer 10 and the frame 20 may be directly connected or may be connected via an intermediate member.

The fuel loading structure 100 further includes a plate-shaped skin 30 attached to the outer surface of the stringer 10.
The stringer 10, frame 20, and skin 30 described above are integrated as a whole, have the necessary rigidity as the fuselage 1 (structure), and spatially partition the inside and outside of the fuselage 1.

FIG. 4 is a cross-sectional view of the stringer 10.
The stringer 10 is a hollow tube and has an outer layer 60a and an inner layer (hereinafter referred to as liner 62a).

The outer layer 60a is made of fiber-reinforced plastic having a tensile strength that exceeds the in-plane stress caused by the pressure of the liquid fuel L filled inside. Further, the skin 30 described above is also made of the same type of fiber-reinforced plastic as the outer layer 60a of the stringer 10 and frame 20, and partially shares the load of the stringer 10 and frame 20.
The fiber-reinforced plastic (hereinafter referred to as FRP) is preferably carbon fiber-reinforced plastic (CFRP), but may also be aramid fiber-reinforced plastic or glass fiber-reinforced plastic.
Further, the carbon fiber reinforced plastic is preferably a thermoplastic flame retardant carbon fiber reinforced plastic.
Moreover, since pressurization is applied inside the fuselage 1, it is preferable that the skin 30 also be provided with a liner similar to the liner 62a to prevent internal gas from leaking to the outside.

The liquid fuel L is, for example, liquid oxygen (LOX) or liquid hydrogen (LH2). The temperature of liquid oxygen is a cryogenic temperature of about -180°C, and the temperature of liquid hydrogen is a cryogenic temperature of about -253°C. Note that this is just an example, and other fuels (eg, normal jet fuel) may be used.

The liner 62a is in close contact with the inner surface of the outer layer 60a, and has corrosion resistance against the liquid fuel L and airtightness. The liner 62a is a thermoplastic engineering plastic that has corrosion resistance against the liquid fuel L.
Engineering plastics are, for example, crystalline polymers such as nylon (PA6), polyacetal (POM), polyphenylene sulfite (PPS), polyallyletherketone (PAEK), or, for example, polycarbonate (PC), polyphenylene ether (PPE). , amorphous polymers such as polyetherimide (PEI).

In this figure, the stringer 10 further includes a surface tension member 64a.
The surface tension member 64a is located inside the liner 62a, separates gas and liquid by surface tension, and supplies only the liquid to the manifold 40 (described later). The surface tension member 64a is preferably made of porous or mesh FRP.
By having the surface tension member 64a, the internal liquid fuel L can be forcibly supplied to the engine (or the propulsion device, or the connected manifold 40) under extremely low gravity (10 ⁻⁴ G or less).

The frame 20 is a hollow tube and has an outer layer 60b (not shown) similar to the stringer 10, a liner 62b, and a surface tension member 64b.
Outer layer 60b, liner 62b, and surface tension member 64b of frame 20 are preferably the same as outer layer 60a, liner 62a, and surface tension member 64a of stringer 10, but may be different.

In this example, stringer 10 and frame 20 are rectangular tubes. The dimensions (width, height, thickness) of the rectangular tube are set so as to provide the necessary rigidity for the fuselage 1 (structure).
Note that the cross-sectional shape of the hollow tube is not limited to a rectangle, but may be a trapezoid, a hat shape, a circle, or an ellipse.

In FIG. 4, the stringer 10 has a flat flange portion 12 that is integrally attached to the outer surface (lower surface in the figure) of the outer layer 60a and extends in the width direction in the figure.
The flange portion 12 is made of the same FRP (preferably CFRP) as the outer layer 60a, and is used to facilitate connection with the skin 30.
Although it is preferable that the flange portions 12 be provided continuously over the entire length of the stringer 10, a plurality of flange portions 12 may be provided at intervals in the length direction.
Note that the frame 20 may be provided with a similar flange portion (not shown).

In FIG. 3 , the fuel loading structure 100 further includes a manifold 40 .
The manifold 40 is connected to the stringer 10 and the frame 20, and stores liquid fuel L therein.
Like the stringers 10 and frame 20, the manifold 40 preferably has an outer layer made of fiber-reinforced plastic and a liner made of engineering plastic, but may be made of metal.
Moreover, although it is preferable that the manifold 40 has a surface tension member like the stringer 10 and the frame 20, this may be omitted.
The stringer 10, frame 20, and manifold 40 collectively function as a fuel tank. That is, the manifold 40 communicates with a propulsion device (for example, an engine) of the aircraft via a piping line (not shown), and supplies liquid fuel L to the propulsion device.
When the propulsion device has a fuel cell, the liquid fuel L is liquid hydrogen.

In FIG. 3, the manifold 40 has a plurality (two in this example) of hollow annular members 42 extending in the circumferential direction of the body 1 and spaced apart in the axial direction (Z direction).
In this example, the hollow annular member 42 is an arc-shaped member obtained by dividing a hollow circular member into four parts at intervals of 90 degrees. However, the hollow annular member 42 may be an undivided, integral hollow circular member.
The cross-sectional shape of the hollow annular member 42 is preferably a rectangular tube like the stringer 10 and the frame 20, but it may also be trapezoidal, hat-shaped, circular, or elliptical.
Further, the hollow annular member 42 includes an outer layer 60c, a liner 62c, and a surface tension member 64c (not shown) similar to the stringer 10.

In FIG. 3, the frame 20 includes a plurality of circular arc parts 26a extending in the circumferential direction, an intermediate connecting part 26b that connects the end surfaces of the plurality of circular arc parts 26a, and a hollow annular member 42 that connects the extreme end of the circular arc parts 26a to each other. It has an end connecting portion 26c to be connected.
In this example, the frame 20 is a continuous tube as a whole, and both ends are hermetically fixed to a pair of axially adjacent hollow annular members 42.
The plurality of circular arc portions 26a are spaced apart from each other in the axial direction, and are preferably located parallel to each other.

It is preferable that the arc portion 26a, the intermediate connecting portion 26b, and the end connecting portion 26c be integrally formed, and that the outer layer 60b, the liner 62b, and the surface tension member 64b are seamlessly continuous.
In addition, both ends of the frame 20 are airtightly fixed to a pair of hollow annular members 42 adjacent to each other in the axial direction, and the surface tension member 64b and the space inside thereof are connected to the surface tension member 64c of the hollow annular member 42 and the space inside thereof. Continuously connected to space.
With this configuration, it is possible to fill the hollow tube of the frame 20, which is a continuous tube, with the liquid fuel L, and the liquid fuel L inside is forcibly supplied to the manifold 40 with extremely low gravity by the surface tension members 64b and 64c. can do.

Note that the frame 20 is composed of separate arc portions 26a, intermediate connection portions 26b, and end connection portions 26c, and the intermediate connection portions 26b and end connection portions 26c are used to connect the arc portions 26a, intermediate connection portions 26b, and The end connecting portions 26c may be connected and assembled.
With this configuration, the shapes of the arcuate portion 26a, the intermediate connecting portion 26b, and the end connecting portion 26c can be unified to enable mass production and reduce manufacturing costs and assembly costs.

In FIGS. 2 and 3, the fuel mounting structure 100 further includes a heat insulating member 50. As shown in FIG. The heat insulating member 50 includes an outer heat insulating member 52 provided outside the skin 30 and an inner heat insulating member 54 provided inside the frame 20 and the stringer 10 (ie, the skeleton F).
The outer heat insulating member 52 prevents heat from entering from the outside. The outer heat insulating member 52 is preferably a vacuum heat insulating layer, but may also be a cryogenic heat insulating material such as a foam heat insulating material.
The inner heat insulating member 54 is provided inside the stringer 10, frame 20, and manifold 40, and prevents heat from entering these members from the inside. The inner heat insulating member 54 is preferably a heat insulating material for extremely low temperatures, such as a foamed heat insulating material.
The heat insulating member 50 described above can reduce gasification of the liquid fuel L stored inside the stringer 10, the frame 20, and the manifold 40.

By combining the four sets of fuel loading structures 100 divided into four parts shown in FIG. 3, the fuselage 1 shown in FIG. 1 (for example, the fuselage of an aircraft) is formed.
Note that the division of the fuselage 1 is not limited to four divisions, and some or all of the divisions may be integrated without being divided.
For example, the skin 30, manifold 40, and heat insulating member 50 are preferably integrated without being divided.

FIG. 5 is a perspective view similar to FIG. 3 of a second embodiment of a fuel loading structure 100 according to the invention.
In this figure, the manifold 40 includes a plurality of hollow annular members 42 extending in the circumferential direction of the fuselage 1 and spaced apart in the axial direction, and a hollow rod-shaped member having both ends fixed to a pair of adjacent hollow annular members 42 and extending in the axial direction. It has a member 44.

In this example, the hollow annular member 42 is an arcuate member divided into four parts, but it may be an integral hollow circular member that is not divided.
Further, in this example, two hollow rod-shaped members 44 are provided for each of the quarter-divided arc-shaped members, but a plurality (2 to 4) may be provided for each undivided hollow circular member. good.
The cross-sectional shapes of the hollow annular member 42 and the hollow rod-like member 44 are preferably rectangular tubes like the stringer 10 and the frame 20, but may also be trapezoidal, hat-shaped, circular, or oval.
Further, the hollow annular member 42 and the hollow rod-like member 44 have an outer layer 60c, a liner 62c, and a surface tension member 64c similar to the stringer 10.

In this example, the frame 20 is an arc tube 27 that extends in the circumferential direction from one of a pair of circumferentially adjacent hollow rod-shaped members 44 to the other.
The plurality of arcuate tubes 27 are spaced apart in the axial direction and are preferably located parallel to each other.

By combining the four sets of fuel loading structures 100 divided into four parts shown in FIG. 5, the fuselage 1 shown in FIG. 1 (for example, the fuselage of an aircraft) is formed.
Note that the number of divisions of the fuselage 1 is not limited to four, and some or all of them may be integrated without being divided.
The other configurations are the same as those in the first embodiment.

The method for manufacturing the fuel loading structure 100 described above includes the following steps (processes) S1 to S3.
(S1) A plurality of stringers 10 are arranged so as to extend in the axial direction at intervals in the circumferential direction.
(S2) A plurality of frames 20 are arranged so that at least some of them extend in the circumferential direction at intervals in the axial direction.
(S3) The stringer 10 and frame 20 are heated to a temperature exceeding the melting point of the thermoplastic resin used in the fiber-reinforced plastic that constitutes the outer layer of the stringer 10 or frame 20 to firmly connect each other at the intersection, and the whole A single skeleton F is constructed.

Furthermore, the stringer 10 and frame 20 described above can be manufactured, for example, in the following steps T1 to T4.
(T1) A mandrel (not shown) extending in the axial direction or circumferential direction is prepared.
(T2) An airtight thermoplastic resin tape is wound around the outer peripheral surface of the mandrel around the axis of the mandrel.
(T3) A fiber prepreg tape impregnated with a thermoplastic resin used in the fiber-reinforced plastic forming the outer layer of the stringer 10 or the frame 20 is wrapped around the outer peripheral surface of the thermoplastic resin tape around the axis of the mandrel.
(T4) The stringer 10 or frame 20 is manufactured by heating the mandrel around which the thermoplastic resin tape and the fiber prepreg tape are wound to a temperature exceeding the melting point of the thermoplastic resin used in the fiber prepreg tape.
In this case, the thermoplastic resin tape constitutes the above-mentioned liner and the fiber prepreg tape constitutes the above-mentioned outer layer.

Note that when the outer layers 60a, 60b and the liners 62a, 62b are made of the same resin, the distinction between the outer layer and the liner can be eliminated, and the manufacturing process can be simplified.

Further, the surface tension members 64a, 64b may be pre-attached to the surface of the mandrel before step T1, or may be inserted inside after step T4.

Further, it is preferable to attach a plate-shaped skin 30 to the outer surface of the stringer 10 and heat the skin 30 to a temperature exceeding the melting point of the thermoplastic resin to firmly fix the skin 30 to the outer surface of the stringer 10.

The thermoplastic resin used in the fiber prepreg tape mentioned above is a thermoplastic engineering plastic.
Engineering plastics are, for example, crystalline polymers such as nylon (PA6), polyacetal (POM), polyphenylene sulfite (PPS), polyallyletherketone (PAEK), or, for example, polycarbonate (PC), polyphenylene ether (PPE). , amorphous polymers such as polyetherimide (PEI).
These resins are used alone as liner materials, but are also used as matrix resins for fiber-reinforced plastics.

The above-mentioned fiber reinforced plastic (FRP) is preferably thermoplastic FRP, but is not limited thereto, and may also include thermosetting FRP.
In addition to the methods described above, heat press molding, hybrid injection molding, automatic tape lamination molding, continuous molding, fusion bonding, fastening bonding, and the like can be applied as methods for producing thermoplastic FRP.
Furthermore, the stringer 10 and the frame 20 may be continuously molded by combining pultrusion molding and continuous molding.
In addition to the above-mentioned thermal fusion bonding method, high frequency induction fusion bonding, resistance fusion bonding, etc. can be applied as a fusion bonding method for FRP.

According to the embodiment of the present invention described above, since the stringer 10 and the frame 20 have the outer layers 60a, 60b made of fiber reinforced plastic (FRP) and the liners 62a, 62b having corrosion resistance and airtightness, the fuselage 1 can be made of composite materials to reduce weight.

Furthermore, the stringer 10 and the frame 20 are each hollow tubes, and each outer layer 60a, 60b has a tensile strength that exceeds the in-plane stress due to the pressure of the liquid fuel L, and the liner 62a, 62b (inner layer) is a liquid fuel L. It has corrosion resistance and airtightness against L. Thereby, the liquid fuel L can be filled into the hollow tubes of the stringer 10 and the frame 20, and the conventional fuel mounting space can be reduced.

Furthermore, since the fuel loading structure 100 consisting of the stringer 10 and the frame 20 surrounds the luggage space 2 inside the aircraft fuselage, the necessary fuel can be loaded while minimizing the reduction in the effective space in the central part of the aircraft fuselage 1. be able to. This allows more cargo and personnel to be loaded onto the aircraft.

Note that the present invention is not limited to the embodiments described above, and it goes without saying that various changes can be made without departing from the gist of the present invention.

F skeleton, L liquid fuel, O center, X horizontal axis, Y vertical axis, Z center axis,
1 fuselage, 2 luggage space, 10 stringer, 12 flange section,
20 frame, 26a arc part, 26b intermediate connection part,
26c end connecting portion, 27 arc tube, 30 skin,
40 manifold, 42 hollow annular member, 44 hollow rod member,
50 heat insulation member, 52 outer heat insulation member, 54 inner heat insulation member,
60a, 60b, 60c outer layer, 62a, 62b, 62c liner,
64a, 64b, 64c surface tension member, 100 fuel mounting structure

Claims (12)

A fuel loading structure that constitutes an aircraft,
a stringer extending in the axial direction of the fuselage;
a frame extending in the circumferential direction of the aircraft body;
a manifold connected to the stringer and the frame and storing liquid fuel therein ,
The stringer and the frame are each hollow tubes,
an outer layer made of fiber-reinforced plastic having a tensile strength that exceeds the in-plane stress due to the pressure of the liquid fuel filled inside ;
a liner that is in close contact with the inner surface of the outer layer and has corrosion resistance and airtightness against the liquid fuel ;
The stringer and the frame include a surface tension member located inside the liner that separates gas and liquid by surface tension and supplies only liquid to the manifold . A fuel loading structure that constitutes an aircraft,
a stringer extending in the axial direction of the fuselage;
a frame extending in the circumferential direction of the aircraft body;
a manifold connected to the stringer and the frame and storing liquid fuel therein ,
The stringer and the frame are each hollow tubes,
an outer layer made of fiber-reinforced plastic having a tensile strength that exceeds the in-plane stress due to the pressure of the liquid fuel filled inside ;
a liner that is in close contact with the inner surface of the outer layer and has corrosion resistance and airtightness against the liquid fuel ;
The manifold has a plurality of hollow annular members extending in the circumferential direction of the fuselage and spaced apart in the axial direction,
The frame includes a plurality of circular arc portions extending in the circumferential direction, an intermediate connecting portion that connects end surfaces of the plurality of circular arc portions to each other, and an end connecting portion that connects the most end portions of the circular arc portions to the hollow annular member. A fuel loading structure having : A fuel loading structure that constitutes an aircraft,
a stringer extending in the axial direction of the fuselage;
a frame extending in the circumferential direction of the aircraft body;
a manifold connected to the stringer and the frame and storing liquid fuel therein ,
The stringer and the frame are each hollow tubes,
an outer layer made of fiber-reinforced plastic having a tensile strength that exceeds the in-plane stress due to the pressure of the liquid fuel filled inside ;
a liner that is in close contact with the inner surface of the outer layer and has corrosion resistance and airtightness against the liquid fuel ;
The manifold includes a plurality of hollow annular members extending in the circumferential direction of the fuselage and spaced apart in the axial direction;
a hollow rod-shaped member having both ends fixed to a pair of adjacent hollow annular members and extending in the axial direction;
In the fuel loading structure, the frame is an arcuate tube extending in the circumferential direction from one of a pair of circumferentially adjacent hollow rod-shaped members to the other . a plate-shaped skin attached to the outer surface of the stringer;
The fuel loading structure according to any one of claims 1 to 3 , wherein the skin is made of the same type of fiber-reinforced plastic as the outer layer of the stringer and the frame, and partially shares the load of the stringer and the frame. body. The fuel loading structure according to claim 4, further comprising a heat insulating member provided inside the frame and the stringer or outside the skin. The liquid fuel is liquid oxygen or liquid hydrogen,
The liner is an engineering plastic that has corrosion resistance against the liquid fuel,
The fuel loading structure according to any one of claims 1 to 3 , wherein the fiber-reinforced plastic is carbon fiber-reinforced plastic, aramid fiber-reinforced plastic, or glass fiber-reinforced plastic. A method for manufacturing a fuel loading structure according to any one of claims 1 to 3, comprising :
a plurality of stringers are arranged so as to extend in the axial direction at intervals in the circumferential direction;
The plurality of frames are arranged so that at least some of the frames extend in the circumferential direction at intervals in the axial direction,
The stringers and the frame are heated to a temperature exceeding the melting point of the thermoplastic resin used in the fiber-reinforced plastic that constitutes the outer layer of the stringer or the frame, so that the stringers and the frame are firmly connected to each other at the intersection, so that the stringer and the frame are made into a single piece. A method for manufacturing a fuel loading structure that constitutes the skeleton of. providing the axially extending mandrel;
Wrapping an airtight thermoplastic resin tape around the outer peripheral surface of the mandrel around the axis;
Wrapping the fiber prepreg tape impregnated with the thermoplastic resin around the outer peripheral surface of the thermoplastic resin tape around the axis;
The fuel loading structure according to claim 7 , wherein the stringer or the frame is manufactured by heating the mandrel around which the thermoplastic resin tape and the fiber prepreg tape are wound to a temperature exceeding the melting point of the thermoplastic resin. manufacturing method. 8. The method for manufacturing a fuel loading structure according to claim 7 , wherein a plate-shaped skin is attached to the outer surface of the stringer, and the skin is heated to a temperature exceeding the melting point of the thermoplastic resin. The thermoplastic resin is an engineering plastic,
8. The method for manufacturing a fuel carrying structure according to claim 7 , wherein the engineering plastic is nylon, polyacetal, polyphenylene sulfite, polyallyletherketone, polycarbonate, polyphenylene ether, or etherimide. The thermoplastic resin is an engineering plastic,
9. The method for manufacturing a fuel carrying structure according to claim 8 , wherein the engineering plastic is nylon, polyacetal, polyphenylene sulfite, polyallyletherketone, polycarbonate, polyphenylene ether, or etherimide. The thermoplastic resin is an engineering plastic,
10. The method for manufacturing a fuel carrying structure according to claim 9 , wherein the engineering plastic is nylon, polyacetal, polyphenylene sulfite, polyallyletherketone, polycarbonate, polyphenylene ether, or etherimide.

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