Space flight device

Abstract

The present invention relates to a space flight device, and may comprise: a takeoff and landing part provided on the ground; a flight unit capable of taking off from and landing on the takeoff and landing part; and a supply part which is provided in the takeoff and landing part and connected to the flight unit, and which supplies energy so that the flight unit that has taken off can stay in the air. Therefore, a support part stays in space, and an aerial vehicle takes off from the support part and flies into space, and thus costs can be lower than those when directly taking off from the ground.

Description

space flight device

[0001] Cross-reference to related applications

[0002] This application claims the benefit of priority to Republic of Korea Patent Application No. 10-2024-0032687, filed March 7, 2024, the contents of which are incorporated herein by reference in their entirety.

[0003] The present invention relates to a space flight device.

[0004] A spacecraft is designed to travel in space more than 100km above the ground, and a spaceflight device is needed to go from the ground to space.

[0005] Spacecraft are launched from the ground into space by multi-stage launch vehicles. The launched spacecraft either orbit the Earth or head to another celestial body.

[0006] Spaceflight devices include, depending on their flight range, Airbus and Air Cargo satellites, space stations, lunar probes, interplanetary probes and spacecraft bound for Mars or Venus, and even interstellar spacecraft.

[0007] Sending such a spacecraft from the ground into space requires a great deal of effort and economic expense.

[0008] The present invention provides a technology for sending a spaceflight device from the ground to space at an economical cost and for efficiently supplying the energy required for spaceflight from the ground to space.

[0009] A space flight device according to one embodiment of the present invention includes a take-off and landing section installed on the ground, a flight unit capable of taking off and landing from the take-off and landing section, and a supply section installed on the take-off and landing section and connected to the flight unit, and supplying energy so that the flight unit can remain in the sky after taking off.

[0010] The above flight unit may include a landing gear capable of taking off and landing from the landing gear, and an aircraft capable of taking off and landing from the landing gear.

[0011] The above supply unit is connected to the support unit, and the support unit can take off carrying the aircraft.

[0012] The above-mentioned support unit may include a support body supporting the aircraft, a plurality of support propellants installed on the support body, and a plurality of support blade units installed on the support body.

[0013] The above-mentioned support unit may further include a support member installed in the support body to guide the cable of the supply unit into the interior of the support body.

[0014] The aircraft may include a flight body supported on the support, and a plurality of flight propulsion units installed on the flight body.

[0015] The above supply unit may include a reel unit installed in the takeoff and landing unit, and a cable wound around the reel unit and connected to the flight unit.

[0016] The cable may include at least one wire section, a first tube positioned inside the wire section and having an interior partitioned by at least one bulkhead, and a second tube positioned inside the first tube.

[0017] Materials with different properties can flow inside the first tube and the second tube.

[0018] The above reel unit may include a drum portion on which the cable is wound, a roller portion installed adjacent to the drum portion and capable of moving in up, down, left, and right directions to induce winding of the cable, and a roller driving portion that operates the roller portion.

[0019] The above roller driving unit may include a driving motor, a gear unit that can be rotated by the driving motor, a load connected to the gear unit and the roller unit, and an elastic member that provides elastic force in the vertical direction of the roller unit.

[0020] The above reel unit further includes a coupler installed in the drum portion and connected to the cable, and a power supply portion and a fuel supply portion can be connected to the coupler.

[0021] According to an embodiment of the present invention, since the support remains in space and the aircraft takes off from there and flies in space, there is an effect of reducing costs compared to taking off directly from the ground.

[0022] According to an embodiment of the present invention, energy, such as electricity or fuel, can be supplied to a support in space through a supply unit. This has the effect of enabling the support unit to remain in space.

[0023] According to an embodiment of the present invention, the support unit has the effect of landing on the ground, loading the aircraft, and then moving back and forth 50 to 60 km above the ground to perform its duties.

[0024] According to an embodiment of the present invention, a flight unit can remain in the air for a long time through a takeoff and landing section and a supply section, and can continuously supply energy from the ground, thereby reducing fuel consumption and reducing operating costs.

[0025] According to an embodiment of the present invention, by utilizing the support, energy and cost can be saved compared to when an aircraft takes off directly from the ground, and the support serves as an intermediate base, thereby providing the effect of supporting more stable space flight.

[0026] According to an embodiment of the present invention, the support unit including the support body, the propulsion unit, and the blade unit can independently stay in the air, and there is an effect of supporting takeoff and landing of the aircraft, thereby enabling more stable operation.

[0027] According to an embodiment of the present invention, by guiding a cable internally through a support member of a base, structural stability can be increased, protection from the external environment can be achieved, and the durability of the energy supply system can be improved, enabling long-term operation.

[0028] According to an embodiment of the present invention, energy can be stably supplied to a flight unit through a supply unit including a reel unit and a cable, so that the flight unit can operate continuously, thereby enabling long-term operation.

[0029] According to an embodiment of the present invention, various substances can flow independently inside the cable, thereby enabling simultaneous supply of power and fuel, thereby improving the efficiency and stability of energy supply.

[0030] According to an embodiment of the present invention, the winding of the cable can be smoothly controlled by utilizing the roller portion of the reel unit, thereby improving the reliability of the supply system, reducing cable wear, and reducing maintenance costs.

[0031] According to an embodiment of the present invention, the movement of the cable can be stably controlled through the drive motor and elastic member of the roller drive unit, thereby alleviating shock during the energy supply process and thereby increasing the durability of the system.

[0032] According to an embodiment of the present invention, power and fuel supply can be easily connected through the coupler of the reel unit, thereby improving operational convenience and enabling more flexible operation of the supply system, thereby increasing efficiency.

[0033] Figure 1 is a schematic diagram showing a space flight device according to one embodiment of the present invention.

[0034] Figure 2 is a plan view showing the support part of Figure 1.

[0035] Fig. 3 is an enlarged view showing a portion of the support part of Fig. 1.

[0036] Fig. 4 is a schematic diagram showing the bottom surface of the support part of Fig. 2.

[0037] Figure 5 is a schematic diagram showing the cable of Figure 1.

[0038] Figure 6 is a schematic diagram showing the reel unit of Figure 1.

[0039] Figure 7 is a schematic diagram showing the reel unit of Figure 6.

[0040] Fig. 8 is a cross-sectional view showing the connection part of Fig. 6.

[0041] Fig. 9 is a schematic diagram showing the joint structure of the connection part, socket, and coupler of Fig. 6.

[0042] Figure 10 is a schematic diagram showing the state in which an Earth-bound aircraft is positioned on the support of a flight unit.

[0043] Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings so that those skilled in the art can easily implement the present invention. However, the present invention may be implemented in various different forms and is not limited to the embodiments described herein. Like reference numerals designate similar parts throughout the specification.

[0044] Then, a space flight device according to one embodiment of the present invention will be described with reference to FIGS. 1 to 8.

[0045] Referring to FIGS. 1 to 9, a spaceflight device (1) according to the present embodiment includes a takeoff and landing section (10), a flight unit (20), and a supply section (30), and minimizes the cost of sending the spaceflight device from the ground to space, and supplies energy for spaceflight from the ground to space, thereby enabling the spaceflight device to remain in space. The spaceflight device (1) can transport personnel, cargo, etc. back and forth from the Earth to space, and from space to the Earth.

[0046] The landing gear (10) includes legs (11) and a base (12), and supports a flight unit (20) that is installed on the ground and is to be sent into space.

[0047] The legs (11) are composed of multiple legs. The lower ends of the legs (11) are connected to each other and fixed to the ground. The legs (11) gradually spread apart from the lower end to the upper end. The arrangement of the legs (11) can be varied depending on the design. The legs (11) are connected to the aboveground and underground spaces.

[0048] The base (12) is connected to the upper end of the legs (11). A space is formed inside the base (12). A person can move within the space inside the base (12). The base (12) is separated from the ground by the legs (11). The base (12) and the ground are connected by stairs, an elevator, an escalator, or the like. A person on the ground can move within the space inside the base (12).

[0049] The upper surface of the base (12) is flat. A take-off and landing pad is formed on the upper surface of the base (12). A reel space is formed inside the base (12).

[0050] The flight unit (20) includes a support (21) and a flight body (22), and can take off and land from the upper surface of the base (12), and can move from the ground to the Karman line and fly in space.

[0051] The support unit (21) includes a support body (211), a support propulsion unit (212), and a support blade unit (213), and can take off and land from the landing unit (10) and support an aircraft (22) in space. The support unit (21) may further include a support member (214).

[0052] The support body (211) forms the outer shape of the support part (21), and a landing pad is formed in the center of the upper surface where an aircraft (22) can take off and land. A space in which a person can move is formed inside the support body (211). The interior of the base (12) and the interior of the support body (211) are connected so that a person can move. The support body (211) is formed with a plurality of blade holes (211a) that penetrate upward and downward.

[0053] The blade section (213) includes a motor (213m) and wings (213b), which are arranged in each blade hole (211a). The wings (213b) are formed in multiple numbers and are connected to the drive shaft of the motor (213m). Instead of the motor (213m), an engine using fuel may be used. A bracket (213a) supporting the motor (213m) is installed in the blade hole (211a).

[0054] The support body (211) can take off from the landing gear (10) and fly by the propulsion force of the blade section (213). The blade section (213) can operate from the ground to a height of 10 km. The blade section (213) can be protected from external force by the periphery of the blade hole (211a).

[0055] The propeller (212) is installed in multiple places at intervals along the perimeter of the edge of the propeller body (211). The propeller (212) is outside the base (12). However, the propeller (212) may also be installed on the bottom surface of the propeller body (211). The propeller (212) has a launch vehicle structure.

[0056] When the support part (21) flies to 10 km above the ground by the blade part (213), the support propulsion unit (212) is then activated, allowing the support part (21) to fly to the Karman line of 100 km above the ground. As a result, the support part (21) can remain at the Karman line.

[0057] The support unit (21) flies from the ground to 10 km above the ground by driving the blade unit (213). From 10 km above the ground, the air density decreases, resulting in a lack of oxygen, lift, etc., and thus the support unit (21) cannot obtain power from the blade unit (213). Therefore, the support unit (21) cannot fly with the blade unit (213) alone, and therefore, from 10 km above the ground, it can fly with the help of the support propulsion unit (212) to the Karman line.

[0058] The support (214) is installed on the lower surface of the support body (211). One end of the support (214) is connected to the support body (211). The other end of the support (214) is spaced apart from the support body (211). A guide hole (214a) is formed in the support (214).

[0059] The aircraft (22) includes a flight body (221) and a flight propulsion system (222), and can take off and land on a support (21) that has flown to the Karman line and can fly in space.

[0060] The aircraft body (221) is located on the landing pad of the support member (21) and can take off and land on the landing pad. The aircraft body (221) is connected to the support member (211) on the landing pad of the support member (21). The aircraft body (221) can receive energy such as fuel and electricity from the support member (211). A space in which a person can move is formed inside the aircraft body (221).

[0061] The area of ​​the flight body (221) is smaller than the area of ​​the support body (211). Therefore, the flight body (221) can land stably on the support body (211).

[0062] A plurality of flight propulsion units (222) are installed along the perimeter of the aircraft body (221). The flight propulsion units (222) have a space launch vehicle structure. The aircraft body (22) can fly in space by the propulsive force of the flight propulsion units (222). Since the aircraft body (22) takes off and flies in space, energy consumption can be minimized compared to taking off from the ground.

[0063] The flight propulsion unit (222) does not extend beyond the support body (211). Accordingly, a flame hole (211b) is formed in the portion of the support body (211) that coincides with the flight propulsion unit (222) into which the flame emitted from the flight propulsion unit (222) flows. However, the flame hole (211b) may be omitted.

[0064] In addition, the blade section (213), the propeller (212), and the flight propulsion unit (222) that enable the flight unit (20) to fly can be used in parallel with an eco-friendly motor with low noise and a fuel-using propulsion unit. As a result, the flight performance of the flight unit (20) can be improved.

[0065] The supply unit (30) includes a reel unit (32) and a cable (31) and is installed on the takeoff and landing unit (10). The supply unit (30) supplies energy such as electricity and fuel to the flight unit (20) of the Karman line from the ground so that the flight unit (20) staying on the Karman line can continue to stay.

[0066] The cable (31) includes a wire section (311), a first tube (312), and a second tube (313), and supplies energy such as electricity, fuel, and water from the ground to the support section (21) of the Karman line.

[0067] The wire section (311) is composed of an inner wire (311a), which is a negative (-) wire, and an outer wire (311b), which is a positive (+) wire.

[0068] An internal wire (311a) is arranged inside an external wire (311b). The internal wire (311a) and the external wire (311b) are separated by a covering. The covering prevents interference between the internal wire (311a) and the external wire (311b).

[0069] The first tube (312) is arranged inside the inner wire (311a). The first tube (312) has an insulating structure. The second tube (313) is arranged inside the first tube (312). A partition wall (312a) is formed between the first tube (312) and the second tube (313). The partition wall (312a) connects the inner surface of the first tube (312) and the outer surface of the second tube (313). The partition wall (312a) is arranged along the circumferential direction of the first tube (312) and the second tube (313). Accordingly, a plurality of spaces are formed between the first tube (312) and the second tube (313).

[0070] Hydrogen may flow inside the second tube (313). However, liquefied natural gas (LNG), kerosene, or the like may also flow inside the second tube (313).

[0071] Liquid oxygen can flow through each of the multiple spaces of the first tube (312). As the internal space of the first tube (312) is divided, the cross-sectional area of ​​each space becomes narrower. As the cross-sectional area narrows, the flow rate increases according to Bernoulli's principle. The high flow rate allows liquid oxygen to be transported to a desired location in a short period of time.

[0072] However, water may flow in any one of the multiple spaces of the first tube (312). Furthermore, wastewater generated from the flight unit (20) may flow in any one space. Various substances may flow in the internal space of the second tube (313) and the multiple spaces of the first tube (312).

[0073] Energy such as electricity, fuel, and water is continuously supplied from the ground to the support (21) via a cable (31). The support (21) supplied with energy can remain continuously at the Karman line. Accordingly, the support (21) does not need to come down to the ground to supply fuel, electricity, etc., thereby minimizing the economic costs associated with the takeoff and landing of the support (21).

[0074] Cables can be made from materials such as aramid fiber, carbon fiber, carbon nanotubes (CNTs), and graphene. The cable material can be varied.

[0075] Aramid fibers are strong, lightweight, impact-resistant, flexible, and have excellent impact resistance. They are elastic like a rubber band and can absorb sudden impacts. They are also heat-resistant and stable even at high temperatures above 500℃.

[0076] Carbon fiber is 10 times stronger than steel, lighter, more durable, and does not corrode, so it is used as a structural reinforcement material. It also has excellent heat resistance, so it does not deform even at temperatures above 1000℃.

[0077] Carbon nanotubes are 100 times stronger than steel, yet lightweight. They also have better electrical and thermal conductivity than copper, are highly flexible and resilient, and are not easily broken. Furthermore, their specific gravity is four to eight times lighter than steel, allowing them to be used as electrical cables at heights exceeding 60 kilometers. Furthermore, carbon nanotubes can withstand the tensile stress caused by their own weight.

[0078] Graphene is 200 times stronger than steel, yet ultra-light, has a higher electrical conductivity than copper, is transparent and flexible, and has excellent thermal conductivity, generating less heat and providing excellent cooling.

[0079] Meanwhile, the cable (31) can be maintained connected to the support body (211) without being bent by the guide hole (214a) of the support (214).

[0080] The reel unit (32) includes a drum section (321), a roller section (322), and a roller driving section (323), and is installed on the take-off and landing section (10) and has a cable (31) wound around it.

[0081] The drum unit (321) includes a drum body (321a) and a drum driving unit (321c).

[0082] The drum body (321a) is installed in the reel space of the base (12). The drum body (321a) can rotate forward and backward. The cable (31) can be wound and unwound by the rotation of the drum body (321a). A connection portion (321b) connected to the cable (31) is formed on one side of the drum body (321a).

[0083] The drum drive unit (321c) is composed of a motor and generates rotational force. The drum drive unit (321c) is coupled to the drum body (321a). The drum body (321a) of the drum drive unit (321c) can rotate forward and backward. Accordingly, the drum drive unit (321c) generates rotational force so that the drum body (321a) can rotate in the direction in which the cable (31) is released when the flight unit (20) takes off. Conversely, the drum drive unit (321c) generates rotational force so that the drum body (321a) can rotate in the direction in which the cable (31) is wound when the flight unit (20) lands.

[0084] The roller section (322) includes a support (322a), a bar section (322b), and a roller (322c) and guides the cable (31) wound around the drum section (321) so that the cable (31) can be wound without becoming tangled.

[0085] The support (322a) is separated from the drum part (321) and protrudes vertically upward. The protruding support (322a) does not protrude upward from the base (12).

[0086] The bar member (322b) is hinge-connected to the support (322a) at one end. The bar member (322b) can move left and right based on the hinge when the cable (31) is wound around the drum body (321a). The other end of the bar member (322b) is located on the drum body (321a).

[0087] The roller (322c) is rotatably connected to the other end of the bar member (322b). The circumference of the roller (322c) is in contact with the cable (31) being wound. The cable (31) can be wound without becoming tangled by the guide of the roller (322c).

[0088] The roller drive unit (323) includes a drive motor (323a), a gear unit (323b), a load (323e), and an elastic member (323f), and operates the roller unit (322) to move.

[0089] The drive motor (323a) is linked to the drum drive unit (321c). The drive motor (323a) can operate when the drum drive unit (321c) operates.

[0090] The gear unit (323b) includes a first gear (323c) and a second gear (323d).

[0091] The first gear (323c) is coupled to the drive shaft of the drive motor (323a). The first gear (323c) may be a spur gear.

[0092] The second gear (323d) is supported on the periphery of the reel space and meshes with the first gear (323c). The second gear (323d) can rotate in the reel space. The second gear (323d) can rotate along the first gear (323c). The pitch circle diameter of the second gear (323d) is larger than the pitch circle diameter of the first gear (323c).

[0093] The rod (323e) has one end hinge-connected to the edge of the second gear (323d) and the other end hinge-connected to the bar member (322b). The rod (323e) is perpendicular to the bar member (322b). The rod (323e) can move by the rotation of the second gear (323d) to pull or push the bar member (322b). At this time, the bar member (322b) can move left and right.

[0094] The elastic member (323f) includes a first elastic body (323g) and a second elastic body (323h).

[0095] The first elastic body (323g) connects one end of the bar member (322b) and the upper side of the support (322a). The second elastic body (323h) connects the other end of the bar member (322b) and the bottom of the reel space. The first elastic body (323g) has a coil spring structure. The first elastic body (323g) and the second elastic body (323h) can provide elastic force to the bar member (322b) in different directions.

[0096] The elastic member (323f) can provide elasticity so that the bar member (322b) that has moved in the up-and-down direction can return to its original state.

[0097] The coupler (324) is detachably connected to the connection portion (321b) via a socket (321d). The socket (321d) is detachably connected to the connection portion (321b) by a screw. The coupler (324) is detachably connected by being inserted into the socket (321d).

[0098] The connection part (321b) is connected to a power supply part (not shown) and a fuel supply part (not shown) via a coupler (324).

[0099] When the drum body (321a) rotates, a rotational movement occurs between the coupler (324) and the socket (321d), so that the fuel supply part can be maintained connected to the connection part (321b) without being twisted.

[0100] A compression ring (R1) and an oil ring (R2) are coupled between the coupler (324) and the socket (321d). Accordingly, the sealing between the first tube (312) and the second tube (313) of the coupler (324) and the first tube (312) and the second tube (313) of the socket (321d) can be improved.

[0101] And, a power supply line (L1) having a negative pole and connected to the internal wire (311a) is connected to the connection part (321b), and a power supply line (L2) having a positive pole and connected to the external wire (311b) is connected. A bearing (B) is coupled between the internal wire (311a), the external wire (311b), and the power supply lines (L1, L2) to prevent the power supply lines (L1, L2) from being twisted due to the rotation of the drum body (321a). The bearing (B) and the power supply lines (L1, L2) may be connected by a slip ring (not shown) or a carbon brush, etc.

[0102] In addition, the coupler (324) is provided with an injection port (324I) that is connected to the first tube (312) and into which fuel such as LNG, kerosene, or hydrogen is injected. A supply pipe (IN) for supplying liquid oxygen can be connected to the second tube (313) of the coupler (324).

[0103] Meanwhile, the outer circumferential diameter of the cable (31) is 62 mm, and the specific gravity is 1, 1 m = 3 kg (100 km = 300 tons). In this case, the total weight of the cable (31) is 300 tons, but the actual gravity load applied to the support (21) may be approximately 20 tons due to the decrease in air density as it goes up in the sky. Accordingly, the flight and efficiency of the flight unit (20) can be improved and energy consumption can be minimized.

[0104] The following describes the operation of the spaceflight device described above.

[0105] The flight unit (20) is moored to the landing gear (10) and is connected to the support (21) via a cable (31). The aircraft (22) is coupled to the support (21). The power supply unit and the fuel supply unit are connected to the connection unit (321b) via a coupler (324). Electricity, fuel, etc. can be supplied to the support (21) via the cable (31).

[0106] The pedestal (21) can carry an aircraft (22) and take off from the takeoff and landing section (10) by driving the blade section (213) and fly to the troposphere and stratosphere. Thereafter, by operating the pedestal propulsion unit (212), the pedestal (21) can fly to the Karman line. Thus, the flight unit (20) can fly to space and stay there.

[0107] Meanwhile, when the flight unit (20) takes off, the cable (31) can be released from the drum body (321a) and moved along the support (21) by the operation of the drum drive unit (321c). By combining the connection unit (321b) and the coupler (324), the cable (31) and the fuel supply unit and the power supply unit are not tangled, and fuel and power can be continuously supplied to the support unit (21). Accordingly, the support unit (21) can continuously remain in space. The flight vehicle (22) can take off from the support unit (21) remaining in space and fly in space.

[0108] Therefore, according to the present embodiment, the support member (21) stays in space, and the aircraft (22) takes off from the support member (21) and flies in space, so that costs can be reduced compared to taking off directly from the ground.

[0109] For reference, although the above description and drawings describe the flight unit (20) of the space flight device (1) of the present invention as flying in space, the space flight device (1) of the present invention can fly on the ground. Accordingly, the flight unit (20) can fly on the ground. At this time, as illustrated in FIG. 10, an Earth-based flight vehicle (22a) can take off and land on the support member (21). The Earth-based flight vehicle (22a) can have the same structure as the space-flying flight vehicle (22). In addition, the support member (21) can transport 20 to 30 Earth-based flight vehicles (22a) at the same time. The Earth-based flight vehicle (22a) can transport personnel, cargo, etc. back and forth.

[0110] Meanwhile, when a 10,000-ton Earth-borne flying object (22a) flies at 50 to 60 km above the ground, the weight is reduced to 10,000 tons x 1 / 20,000 = 0.5 tons, and the air density is lowered, so that air resistance (friction) is reduced when the Earth-borne flying object (22a) flies, enabling it to fly 4 to 6 km in 1 second.

[0111] Therefore, the scope of the present invention should be interpreted as including the space flight device (1) being capable of flying and transporting cargo not only in space but also on Earth.

[0112] Although the preferred embodiments of the present invention have been described in detail above, the scope of the present invention is not limited thereto, and various modifications and improvements made by those skilled in the art using the basic concept of the present invention defined in the following claims also fall within the scope of the present invention.

Claims

1. Landing gear installed on the ground, A flight unit capable of taking off and landing from the above landing section and A supply unit installed on the above takeoff and landing section and connected to the above flight unit, and which supplies energy so that the above flight unit can remain in the sky after taking off. A spaceflight device including:

2. In paragraph 1, The above flight unit is A landing gear capable of taking off and landing from the above landing gear, and An aircraft capable of taking off and landing on the above-mentioned support Includes, The above supply unit is connected to the support unit, and the support unit can load the aircraft and take off. Space flight device.

3. In paragraph 2, The above support part A support body supporting the above aircraft, A plurality of propulsion units installed on the above-mentioned support body and Multiple support blade parts installed on the above support body Including Space flight device.

4. In paragraph 3, The above support part A support installed on the above-mentioned support body to guide the cable of the supply unit into the interior of the above-mentioned support body More inclusive Space flight device.

5. In paragraph 2, The above aircraft The aircraft body supported on the above support, and Multiple flight propulsion units installed on the above flight body Including Space flight device.

6. In paragraph 1, The above supply unit A reel unit installed on the above landing gear, and A cable wound on the above reel unit and connected to the above flight unit Including Space flight device.

7. In paragraph 6, The above cable is At least one wire section, A first tube located inside the above-mentioned wire section and having an interior partitioned by at least one bulkhead; and A second tube located inside the first tube Includes, Materials with different properties can flow inside the first tube and the second tube. Space flight device.

8. In paragraph 6, The above reel unit The drum portion on which the above cable is wound, A roller section installed adjacent to the drum section and capable of moving up and down and left and right and inducing winding of the cable; and Roller driving unit that operates the above roller unit Including Space flight device.

9. In paragraph 8, The above roller drive part drive motor, A gear part that can be rotated by the above driving motor, A rod connected to the above gear part and the above roller part, and An elastic member that provides elasticity in the vertical direction of the above roller portion Including Space flight device.

10. In paragraph 8, The above reel unit It further includes a coupler installed in the drum section and connected to the cable, The above coupler can be connected to a power supply unit and a fuel supply unit. Space flight device.

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