KR102664437B1 - Lightweight Space Launch Vehicle Fuselage Structure and Design Method of the Same - Google Patents

Abstract

The present invention relates to a space launch vehicle for transporting a payload from the ground to space orbit or outer space. More specifically, the fuselage of the space launch vehicle and the propellant tank accommodated inside the fuselage are manufactured using carbon fiber-reinforced composite materials. It relates to a composite ultra-light space launch vehicle fuselage and its manufacturing method.

Description

Ultralight space launch vehicle fuselage and manufacturing method thereof {Lightweight Space Launch Vehicle Fuselage Structure and Design Method of the Same}

The present invention relates to a space launch vehicle for transporting a payload from the ground to space orbit or outer space. More specifically, the fuselage of the space launch vehicle and the propellant tank accommodated inside the fuselage are manufactured using carbon fiber-reinforced composite materials. This relates to a reinforced composite ultra-light space launch vehicle fuselage and its manufacturing method.

A space launch vehicle is a rocket that leaves the Earth with a payload and lifts it to a designated location in space orbit. It refers to a propulsion engine using action and reaction or an aircraft propelled by this rocket engine.

A space launch vehicle consists of an engine that generates propulsion, a propellant tank that stores propellant, avionics equipment for attitude control and communication, a payload transported to orbit, and a fairing that protects the payload until it reaches orbit. Among them, the propellant tank accounts for more than half of the total structural weight excluding the engine. Most propellant tanks are manufactured by processing and welding metal materials such as aluminum or stainless steel.

Most existing propellant tanks are manufactured in a monocoque structure. This is because the monocoque consists of only a thin shell structure without a frame structure, making it a structure optimized for weight reduction. Balloon tanks are the most extreme of these. They maintain their shape only by internal pressurization, but have the advantage of being very light.

Considering only weight, a sphere with the lightest weight in a given volume is ideal, but due to limitations in slenderness ratio considering the required propellant capacity and aerodynamic performance of the launch vehicle, the main propellant tank is generally manufactured in the form of a long cylinder. Propellant tanks for engine systems using turbopumps store propellants at a pressure of about 5 bar or lower. In this case, the internal pressure is relatively low, so the weight can be reduced by reducing the wall thickness of the tank. On the other hand, propellant tanks for pressurized cycle engines store their interior at a high pressure of about 10 to 20 bar, so the wall thickness of the tank increases accordingly, resulting in an increase in weight.

The propellant tank of a space launch vehicle basically has a separate type in which the outer wall that forms the structure of the fuselage and the tank in which the propellant is stored are separated, and an integrated type in which the tank itself forms the structure of the fuselage. In the case of an integrated method in which the tank itself is manufactured as a fuselage rather than a method in which the fuselage structure and the tank are manufactured separately, the propellant tank can be made lighter because the tank's internal pressure can play a role in supporting the load.

In addition, the structural cost increases as the projectile becomes smaller, so it is very important to reduce the weight of the projectile tank in small projectiles.

Therefore, there is a need to develop technology to reduce the weight of propellant tanks, which account for a large proportion of the components of space launch vehicles.

Korean Patent Publication No. 10-2023-0029274 (published on March 3, 2023)

The present invention was developed to solve the above problems, and its purpose is to reduce the weight of the fuselage structure including the propellant tank in a small space launch vehicle.

To this end, the purpose of the present invention is to provide a propellant tank including a cylinder made of fiber-reinforced composite material, and an upper and lower dome inserted into the cylinder to form a fuselage-integrated tank.

The fuselage of an ultra-light space launch vehicle according to an embodiment of the present invention is a fuselage of a space launch vehicle in which a space for accommodating fuel or oxidizer is formed inside, and a space for accommodating fuel or oxidizer is formed inside, and both longitudinal sides are open. formed cylinder; and an upper dome and a lower dome respectively coupled to both sides of the cylinder, and is configured as an integrated fuselage type that serves as a tank filled with fuel or oxidizer and forms the outer surface of the fuselage.

In addition, the cylinder, upper dome, and lower dome are made of a laminate structure in which multiple layers of fiber-reinforced composite prepreg are laminated.

Additionally, the upper dome and lower dome are inserted into the interior of the cylinder and coupled to each other.

In addition, the upper dome and the lower dome are adhesively coupled to the inner surface of the cylinder, and the upper dome and lower dome further include a joint extending longitudinally along a radial outer circumference, and a radial outer portion of the joint is formed. The side surface comes into contact with the inner surface of the cylinder and is joined through an adhesive member.

In addition, the upper dome and the lower dome are formed with a first open hole for the inflow and outflow of fuel or oxidant, and a boss made of a fiber-reinforced composite material or a metal material is coupled to the first open hole.

In addition, the boss is formed with a second open hole for the inflow and outflow of fuel or oxidant, and a boss cap made of a fiber-reinforced composite or metal material is coupled to the second open hole.

Additionally, the radial outer circumference of the boss is coupled to the circumference of the first open hole, and the outer surface is coupled to the inner surface of the first open hole.

Additionally, the length (H) of the joint is calculated through Equation 1 below.

(Formula 1)

: 접착제의 전단강도, k : 접착강도에 대한 안전율D: inner diameter of cylinder, P: required internal pressure of fuselage,

: Shear strength of adhesive, k: Safety factor for adhesive strength

In addition, the upper dome or lower dome is formed in the shape of an oval or tori sphere dome, and the ratio of the major axis to the minor axis is 1: 0.3 to 1: 0.7.

In addition, the cylinder is provided with a baffle on its inner surface that protrudes radially inward, and the baffle is formed in a 'ㄷ' shape.

In addition, the baffle includes a bottom plate and a pair of side plates extending in the longitudinal direction on both sides in the width direction of the bottom plate, and the bottom plate is formed with a bent surface bent upward or downward on the inner or outer side in the radial direction, The side plate has a joining surface bent from the radial outer side to the circumferential inner or outer side.

Additionally, the boss is composed of a dome coupling portion formed on the radial outer side and coupled to the dome, and a cap coupling portion formed on the radial inner side and coupled to the boss cap.

In addition, the dome coupling portion includes an adhesive surface formed for adhesive bonding with the dome in a certain area from the radial outer end to the inside; It includes a first bolting coupling portion for bolting with the dome on the radial inner side of the adhesive surface and a first seal groove formed between the adhesive surface and the first bolting coupling portion and into which a seal is inserted, and the cap coupling portion , a second bolting coupling portion for bolting the boss cap to the outer radial direction; And on the radial inner side of the second bolting joint, it includes a second seal groove into which the second seal is inserted.

Additionally, an insulating material is provided on the outside of the upper dome or lower dome for insulation.

An ultra-light space launch vehicle fuselage according to another embodiment of the present invention includes an oxidizing agent tank containing an oxidizing agent and made of the ultra-light space launch vehicle fuselage of the above-mentioned embodiment; A fuel tank made of the ultra-light space launch vehicle fuselage of the embodiment, which is coupled to the lower side of the oxidizer tank and accommodates fuel; and an oxidizing agent transfer pipe penetrating the fuel tank to transport the oxidizing agent to the lower side of the fuel tank.

In addition, the ultra-light space launch vehicle fuselage further includes a ring joint provided between the lower side of the oxidizer tank and an end of the upper cylinder of the fuel tank and connecting the oxidizer tank and the fuel tank.

A method of manufacturing an ultra-light space launch vehicle fuselage according to an embodiment of the present invention includes forming a cylinder using a fiber-reinforced composite material; Forming a dome using a fiber-reinforced composite material; Adhering a baffle to the cylinder; Adhering a boss to the dome; and gluing the dome to the cylinder.

In addition, the steps of forming a cylinder using a fiber-reinforced composite material and forming a dome using a fiber-reinforced composite material, or bonding a baffle to the cylinder and bonding a boss to the dome, are performed sequentially, in reverse order, or simultaneously.

A method of manufacturing an ultra-light space launch vehicle fuselage according to another embodiment of the present invention includes a first step of forming a cylinder using a fiber-reinforced composite material; A second step of forming the upper dome using a fiber-reinforced composite material; A third step of forming the lower dome using fiber-reinforced composite material; A fourth step of processing the baffle using fiber-reinforced composite or metal material; A fifth step of processing the boss using fiber-reinforced composite or metal material; A sixth step of adhering the baffle to the cylinder; A seventh step of adhering bosses to the upper and lower domes; An eighth step of adhering the upper dome to one side of the cylinder; and a ninth step of adhering the lower dome to the other side of the cylinder.

Additionally, the first to fifth steps, the sixth step and the seventh step, or the eighth step and the ninth step are performed sequentially, in reverse order, randomly, or simultaneously.

The carbon composite ultra-light space launch vehicle fuselage and manufacturing method of the present invention according to the above configuration have the effect of reducing the weight by 30% to 40% compared to aluminum alloy by applying carbon fiber composite material with superior specific strength than aluminum alloy.

In addition, a dome to form a tank is inserted inside the cylinder of the fuselage made of fiber-reinforced composite material and integrated by injecting cryogenic adhesive, so the propellant tank and fuselage do not need to be manufactured and joined separately, but share the same cylinder structure, minimizing weight. There is an effect that can be done.

In particular, since the dome and cylinder are manufactured separately and then glued together, the manufacturing process for the launch vehicle fuselage, including the tank, is minimized, thereby reducing manufacturing costs and time.

1 is an exploded perspective view of the space launch vehicle fuselage according to an embodiment of the present invention.
Figure 2 is a cross-sectional perspective view of the space launch vehicle fuselage according to an embodiment of the present invention.
Figure 3 is a cross-sectional side view of the space launch vehicle fuselage according to an embodiment of the present invention.
Figure 4 is a projection perspective view of the body portion according to an embodiment of the present invention
Figure 5 is a front view of the body portion according to an embodiment of the present invention
6 is a perspective view of a baffle according to an embodiment of the present invention.
Figure 7 is a perspective view of the boss portion according to an embodiment of the present invention
Figure 8 is a cross-sectional perspective view of the boss portion according to an embodiment of the present invention
Figure 9 is a cross-sectional perspective view of the space launch vehicle fuselage including a fuel tank and an oxidizer tank according to an embodiment of the present invention.
Figure 10 is a cross-sectional side view of the space launch vehicle fuselage including a fuel tank and an oxidizer tank according to an embodiment of the present invention.
Figure 11 is a flow chart showing a method of manufacturing a space launch vehicle fuselage according to an embodiment of the present invention.

Hereinafter, an embodiment of the present invention described above will be described in detail with reference to the drawings.

Figure 1 shows an exploded perspective view of the space launch vehicle fuselage 1000 (hereinafter referred to as 'fuselage') according to an embodiment of the present invention. As shown, the fuselage 1000 includes a cylinder 100 in which a space is formed to be filled with fuel, and both longitudinal sides are open, an upper dome 200 that seals one open surface of the cylinder 100, and A lower dome 300 that seals the other open surface of the cylinder 100, a first boss 400 and a lower dome ( It is coupled to the inside of the open surface of 300) and includes a second boss 500 for connection with the transfer pipe. In addition, a first boss cap 610 is provided on the outside of the first boss 400 to seal the open surface of the first boss 400, and on the outside of the second boss 500, a first boss cap 610 is provided. A second boss cap 620 is provided to seal the open surface. Additionally, a vortex prevention baffle 700 is coupled to the inside of the second boss 500. As the fuselage 1000 consumes propellant and the water level gradually decreases, a vortex-like vortex is generated inside the fuselage 1000 at some point. Since air bubbles can be sucked into the engine due to the vortex, the vortex within the fuselage 1000 A vortex prevention baffle 700 having a radial partition structure may be provided to suppress the occurrence of .

The cylinder 100 functions as a tank filled with fuel or oxidant inside and is composed of an integrated fuselage that forms the outer surface of the fuselage.

At this time, a first joint 210 for bonding to the cylinder 100 is formed around the upper dome 200, so that the first joint 210 of the upper dome 200 and one inner surface of the cylinder 100 are joined. can be combined In addition, a second joint 310 is formed around the lower dome 300 for connection to the cylinder 100, so that the second joint 310 of the lower dome 300 and the other inner surface of the cylinder 100 are joined. can be combined An injection space for adhesive injection may be formed between the cylinder and the dome, and the radial thickness of the injection space may be within 2 mm.

At this time, the length of the first or second joints 210 and 310 may be determined according to the load or internal pressure conditions required for the fuselage 1000.

, 접착강도에 대한 안전율을 k 라고 정의 할 때, 아래 수식 1을 통해 최소 제1 또는 제2 접합부(210, 310)의 최소길이 H를 결정할 수 있다.The inner diameter of the cylinder 100 is D, the internal pressure of the fuselage 1000 is P, the length of the first or second joints 210 and 310 is H, and the shear strength of the adhesive is

, when defining the safety factor for adhesive strength as k, the minimum length H of the minimum first or second joint (210, 310) can be determined through Equation 1 below.

At this time, the actual H can be designed to have an appropriate safety factor by selecting an appropriate value of k = 1.2 or more based on the above minimum H.

Additionally, the upper dome 200 and lower dome 300 may be formed in the form of an oval or tori-spherical dome to increase the volumetric efficiency of the fuselage 1000 in order to reduce the overall length of the projectile fuselage 1000. At this time, the ratio of the long axis to the short axis of the ellipse can be manufactured to range from 1:0.3 to 1:0.7. If it is less than the above range, a lot of stress is concentrated locally on the upper and lower domes (200, 300), so there is a problem that the thickness must be thicker to improve the strength of the composite, and if it exceeds the above range, the same volume cannot be formed. For this reason, a problem may arise in that the length of the fuselage 1000 becomes longer.

Meanwhile, the cylinder 100, the upper dome 200, and the lower dome 300 may be made of a fiber-reinforced composite material to reduce weight while maintaining a certain strength. For example, the cylinder 100, the upper dome 200, and the lower dome 300 may be formed of a laminate structure composed of multiple layers of composite prepreg.

Figure 2 shows a cross-sectional perspective view of the space launch vehicle body 1000 according to an embodiment of the present invention, and Figure 3 shows a cross-sectional side view of the space launch vehicle body 1000 according to an embodiment of the present invention. there is. Additionally, FIG. 4 shows a projected perspective view of the cylinder 100 according to an embodiment of the present invention, and FIG. 5 shows a front view of the cylinder 100 according to an embodiment of the present invention.

As shown, the cylinder 100, the upper dome 200, and the lower dome 300 may be made of a fiber-reinforced composite material, and an insulating material 800 may be provided on the outside of the upper dome 200 for insulation. .

As another example, the insulation material 800 may also be provided in the lower dome 300. That is, depending on the configuration of the system, the insulation material 800 may be attached to the upper dome 200, the lower dome 300, or both, if necessary. Referring to FIG. 9, when the lower dome is located in the space between two tanks, the insulation material can be deleted because no particularly temperature-sensitive devices are installed, and since temperature-sensitive equipment is installed at the top and bottom, each insulation material can be provided. You can.

Additionally, the first and second bosses 400 and 500 and the first and second boss caps 610 and 620 may be made of a fiber-reinforced composite material or a metal material.

Meanwhile, a baffle 900 may be provided on the inner surface of the cylinder 100, which is shaped like a 'ㄷ' and has an opening formed on the upper side. A plurality of baffles 900 may be spaced apart at equal intervals along the circumferential direction of the cylinder 100 and may be spaced apart along the longitudinal direction. The baffle 900 may be provided to attenuate the shaking of the fluid filled within the launch vehicle during its operating environment and launch. That is, it is provided to prevent shaking of the fuel filled inside the fuselage 1000 and ensure stability when propulsion of the fuselage 1000. The baffle 900 may be adhesively bonded to the inner surface of the cylinder 100 using a cryogenic adhesive.)

When the baffle 900 is opened downward, the height of the bottom plate 910 that holds the water surface of the baffle 900 located at the bottom increases accordingly. Therefore, it is preferable that the baffle 900 is opened upward and attached so that the adhesive portion is located on the upper side. In addition, a load is applied to the baffle 900 as the fluid sloshes around, and it is structurally safer to have two adhesive surfaces on the left and right sides rather than one adhesive surface, and it is easier to manufacture by forming adhesive surfaces on both left and right ends during manufacturing. Therefore, the baffle 900 can be configured in a ‘ㄷ’ shape.

Figure 6 shows a perspective view of a baffle 900 according to an embodiment of the present invention. As shown, the baffle 900 includes a bottom plate 910 and a pair of side plates 920 extending upward from both sides of the bottom plate 910 in the width direction. The bottom plate 910 has a first bent surface 911 bent downward from the radial outer side, and a second bent surface 912 bent upward from the radial inner side. The first and second bent surfaces 911 and 912 may be formed as a reinforcing structure to increase rigidity as the bottom plate 910 is formed thin. The first and second bent surfaces 911 and 912 may be bent in opposite directions with respect to the bottom plate 910.

The side plate 920 has a coupling surface 921 bent from the radial outer side to the circumferential inner side.

7 shows a perspective view of the first boss 400 or the second boss 500 according to an embodiment of the present invention, and FIG. 8 shows a first boss 400 according to an embodiment of the present invention. Alternatively, a cross-sectional perspective view of the second boss 500 is shown.

Since the first boss 400 and the second boss 500 have the same shape except for a different coupling position, the detailed configuration of the first boss 400 will be described below.

The first and second bosses 400 and 500 may be configured to form a fluid entrance of the fuselage 1000, and may be coupled to the inside of the dome using adhesives, bolts, and airtight seals. You can.

More specifically, the first boss 400 includes a dome coupling portion 410 coupled to the upper dome 200, and a cap coupling portion 420 coupled to the first boss cap 610 and having a fluid flow hole 450. It can be divided into: The first boss 400 is formed in the shape of a thick disk, and a dome coupling portion 410 is formed on the radial outer side, and a cap coupling portion 420 is formed on the radial inner side.

The dome coupling portion 410 has an adhesive surface 411 formed for adhesive bonding with the dome in a certain area from the radial outer end to the inner side, and an adhesive surface 411 for bolting bonding with the dome is formed on the radial inner side of the adhesive surface 411. 1 Bolting coupling portion 412 is formed. Additionally, a first seal groove 415 into which a first seal (not shown) is inserted may be formed between the adhesive surface 411 and the first bolting coupling portion 412. The first seal groove 415 may be recessed inward from the outer surface of the first boss 400. The first seal may be provided to improve the sealing force between the boss and the dome.

The cap coupling portion 420 may be formed on the radial inner side of the dome coupling portion 410 and may protrude outward in the thickness direction. The cap coupling portion 420 may have a second bolting coupling portion 421 formed on the outer side in the radial direction for bolting coupling with the boss cap. Additionally, a second seal groove 425 into which a second seal (not shown) is inserted may be formed on the radial inner side of the second bolting coupling portion 421. The second seal groove 425 may be recessed inward from the outer surface of the first boss 400. The second seal may be provided to improve the sealing force between the boss and the boss cap.

The first and second seals have an inner diameter larger than the PCD of the bolt for bolting the dome and the cylinder, and can be used in numbers of 1 to 3.

When multiple seals are arranged, seals with different diameters can be applied by arranging them in a concentric structure so that they do not overlap. The first and second seal grooves may also be formed to match the number of seals.

Figure 9 shows a cross-sectional perspective view of the space launch vehicle fuselage 2000 including a fuel tank and an oxidizer tank according to an embodiment of the present invention, and Figure 10 shows a fuel tank and an oxidizer tank according to an embodiment of the present invention. A cross-sectional side view of the space launch vehicle fuselage 2000 including the tank is shown.

As shown, the space launch vehicle fuselage 2000 includes an oxidizer tank 2100 that accommodates an oxidizer and a fuel tank 2200 that accommodates fuel. The oxidizer tank 2100 and the fuel tank 2200 may be made of the space launch vehicle body 1000 described above.

Therefore, the space launch vehicle fuselage 2000 can be constructed by combining the oxidizer tank 2100 and the fuel tank 2200, which are manufactured using the above-described fuselage 1000, in the longitudinal direction.

The oxidizer tank 2100 and the fuel tank 2200 may each be made of one body 1000, and a ring joint 2500 is provided between the lower side of the oxidizer tank 2100 and the end of the upper cylinder of the fuel tank 2200. It can be combined using .

At this time, an oxidizing agent transfer pipe 2300 may be provided inside the fuel tank 2200 to transfer the oxidizing agent from the oxidizing agent tank 2100 to the combustion chamber located on the lower side of the fuselage 2000.

Additionally, a work window 2400 through which the interior can be viewed may be provided on the cylinder located at the connection between the oxidizer tank 2100 and the fuel tank 2200.

Figure 11 shows a flow chart showing a method of manufacturing a space launch vehicle fuselage according to an embodiment of the present invention.

Referring to FIG. 11, the method of manufacturing a space launch vehicle fuselage according to an embodiment of the present invention includes first forming a cylinder using a fiber-reinforced composite material (S11), and forming an upper dome using a fiber-reinforced composite material. (S12) and the step (S13) of forming the lower dome using a fiber-reinforced composite material. Additionally, a step of processing a baffle using a metal material (S21) and a step of processing the first and second bosses using a metal material (S22) are performed.

Steps S11, S12, S13, S21, and S22 may be performed sequentially, in reverse order, randomly, or simultaneously.

In addition, a step (S15) of inspecting whether the cylinder and dome have been molded to appropriate standards may be further included.

Next, the steps of adhering the baffle to the cylinder (S31), adhering the first boss to the upper dome (S32), and adhering the second boss to the lower dome (S33) are performed.

Steps S31, S32, and S33 may be performed sequentially, in reverse order, randomly, or simultaneously.

Next, the step of adhering the upper dome to one side of the cylinder (S41) and the step of adhering the lower dome to the other side of the cylinder (S42) are performed.

Steps S41 and S42 may be performed sequentially or in reverse order.

Finally, a step (S50) is performed to inspect the bonding and connection state of the fuselage consisting of the cylinder and dome assembly.

The technical idea of the present invention should not be interpreted as limited to the above-described embodiments. Not only is the scope of application diverse, but various modifications can be made at the level of those skilled in the art without departing from the gist of the present invention as claimed in the claims. Therefore, such improvements and changes fall within the scope of protection of the present invention as long as they are obvious to those skilled in the art.

1000, 2000: Space launch vehicle fuselage
100: cylinder
200: upper dome
300: lower dome
400: 1st boss
410: Dome joint
411: Adhesive side
412: first bolting joint
415: first seal groove
420: cap coupling part
421: Second bolting joint
425: second seal groove
450: fluid flow hole
500: 2nd boss
610: 1st boss cap
620: 2nd boss cap
700 ; Vortex prevention baffle
800: insulation material
900: Baffle
910: Bottom plate
911: first bending surface
912: second bending surface
920: side plate
921: mating surface
2100: Oxidizer tank
2200: fuel tank
2300: Oxidizing agent transfer pipe
2400: Task window
2500: Ring joint

Claims (20)

In the fuselage of a space launch vehicle formed with a space inside to accommodate fuel or oxidizer,
A cylinder having a space inside for accommodating fuel or oxidizer and having both longitudinal sides open; and
Comprising an upper dome and a lower dome respectively coupled to both sides of the cylinder,
It is composed of an integrated fuselage type that serves as a tank filled with fuel or oxidizer inside and forms the outer surface of the fuselage,
The upper dome and the lower dome are adhesively coupled to the inner surface of the cylinder and further include a joint extending longitudinally along a radial outer circumference, and the radial outer surface of the joint is adhered to the inner surface of the cylinder. Combined through absence,
An ultra-light space launch vehicle fuselage where the length (H) of the joint is calculated using Equation 1 below so that the joint has a length minimized.

According to clause 1,
The cylinder, upper dome and lower dome are,
An ultra-light space launch vehicle fuselage made of a laminate structure made of multiple layers of fiber-reinforced composite prepreg.
According to clause 1,
The upper dome and lower dome are,
An ultra-light space launch vehicle fuselage that is inserted and coupled to the interior of the cylinder.
delete According to clause 1,
The upper dome and lower dome are,
An ultra-light space launch vehicle fuselage in which a first open hole is formed for the inflow and outflow of fuel or oxidant, and a boss made of fiber-reinforced composite or metal is coupled to the first open hole.
According to clause 5,
The boss is formed with a second open hole for the inflow and outflow of fuel or oxidant, and a boss cap made of fiber-reinforced composite or metal is coupled to the second open hole.
According to clause 5,
The boss said,
An ultra-light space launch vehicle body whose radial outer circumference is coupled to the circumference of the first open hole, and whose outer surface is coupled to the inner surface of the first open hole.
delete According to clause 1,
The upper dome or lower dome,
It is made in the form of an oval or toric dome,
An ultra-light space launch vehicle fuselage, characterized in that the ratio of the major axis to the minor axis is 1: 0.3 to 1: 0.7.
According to clause 1,
The cylinder is,
A baffle protruding radially inward is provided on the inner surface,
The baffle is,
An ultra-light space launch vehicle fuselage consisting of a 'ㄷ' shape.
According to clause 10,
The baffle is,
It includes a bottom plate and a pair of side plates extending in the longitudinal direction on both sides of the bottom plate in the width direction,
The bottom plate is formed with a curved surface bent upward or downward on the inside or outside in the radial direction,
The side plate is an ultra-light space launch vehicle fuselage in which a coupling surface is formed that is bent from the radial outer side to the circumferential inner or outer side.
According to clause 6,
The boss said,
An ultra-light space launch vehicle body composed of a dome coupling portion formed on the radial outer side and coupled to the upper dome or the lower dome, and a cap coupling portion formed on the radial inner side and coupled to the boss cap.
According to clause 12,
The dome joint is,
An adhesive surface formed for adhesive bonding with the dome in a certain area from the radial outer end to the inner side;
A first bolting coupling portion for bolting coupling with the dome on the radial inner side of the adhesive surface, and
It is formed between the adhesive surface and the first bolting joint, and includes a first seal groove into which the seal is inserted,
The cap coupling part,
A second bolting coupling portion for bolting the boss cap to the outer radial direction; and
The ultra-light space launch vehicle fuselage includes a second seal groove into which the second seal is inserted, on the radial inner side of the second bolting coupling portion.
According to clause 1,
Outside the upper dome,
Ultra-light space launch vehicle fuselage equipped with insulation material for insulation.
An oxidizing agent tank, which includes a cylinder that accommodates an oxidizing agent and is open on both sides in the longitudinal direction, an upper dome and a lower dome respectively coupled to both sides of the cylinder, and is integrally formed with the fuselage, which serves as a tank and forms the outer surface of the fuselage;
It is coupled to the lower side of the oxidizer tank, and includes a cylinder that accommodates fuel and has both longitudinal sides open, and an upper dome and a lower dome that are coupled to both sides of the cylinder, and serves as a tank and at the same time forms an outer surface of the fuselage. A fuel tank formed integrally with the fuselage;
an oxidizing agent transfer pipe whose upper side is connected to the oxidizing agent tank and whose lower side penetrates the fuel tank to transport the oxidizing agent to the lower side of the fuel tank; and
It is provided between the lower side of the oxidizer tank and the end of the upper cylinder of the fuel tank, and includes a ring joint connecting the oxidizer tank and the fuel tank to form a space between the oxidizer tank and the fuel tank,
An ultra-light space launch vehicle fuselage where the upper side of the oxidizing agent transfer pipe is exposed to the space.
According to clause 15,
The ultra-light space launch vehicle fuselage is,
a ring joint provided between the lower side of the oxidizing agent tank and an end of the upper cylinder of the fuel tank to connect the oxidizing agent tank and the fuel tank;
Ultralight space launch vehicle fuselage, further comprising:
In the method of manufacturing the ultra-light space launch vehicle fuselage of claim 1 or 15,
Forming a cylinder using a fiber-reinforced composite material;
Forming a dome using a fiber-reinforced composite material;
Adhering a baffle to the cylinder;
Adhering a boss to the dome; and
Adhering the dome to the cylinder;
Method for manufacturing an ultra-light space launch vehicle fuselage, including.
According to clause 17,
The step of forming a cylinder using the fiber-reinforced composite material and the step of forming a dome using the fiber-reinforced composite material, or the step of adhering a baffle to the cylinder and the step of adhering a boss to the dome,
A method of manufacturing an ultralight space launch vehicle fuselage, performed sequentially, in reverse order, or simultaneously.
In the method of manufacturing the ultra-light space launch vehicle fuselage of claim 1 or 15,
A first step of forming a cylinder using a fiber-reinforced composite material;
A second step of forming the upper dome using a fiber-reinforced composite material;
A third step of forming the lower dome using fiber-reinforced composite material;
A fourth step of processing the baffle using fiber-reinforced composite or metal material;
A fifth step of processing the boss using fiber-reinforced composite or metal material;
A sixth step of adhering the baffle to the cylinder;
A seventh step of adhering bosses to the upper and lower domes;
An eighth step of adhering the upper dome to one side of the cylinder; and
A ninth step of adhering the lower dome to the other side of the cylinder;
Method for manufacturing an ultra-light space launch vehicle fuselage, including.
According to clause 19,
The first to fifth steps, the sixth step and the seventh step, or the eighth step and the ninth step,
A method of manufacturing an ultralight space launch vehicle fuselage that is carried out sequentially, in reverse order, randomly, or simultaneously.