A multi-rotor unmanned aerial vehicle for flying on the moon surface by means of self-generated water vapor

Abstract

The present application belongs to the field of manned moon landing, and particularly relates to a multi-rotor unmanned aerial vehicle for moon flight by means of self-generated water vapor; the present application aims to provide an unmanned aerial vehicle which makes full use of the high vacuum, 127-degree high-temperature furnace environment and low-gravity acceleration environment conditions of the moon surface, and realizes the photographing exploration task by adding a water tank, an air pipe and a steam nozzle on the body of the existing unmanned aerial vehicle, self-generating water vapor instead of atmosphere, rotating the rotor of the unmanned aerial vehicle, and pushing the unmanned aerial vehicle to move in the moon surface airspace by means of the water vapor; the unmanned aerial vehicle body comprises a water tank, an air pipe and a steam nozzle, the water tank is installed on the top of the existing unmanned aerial vehicle, and pure water is contained in the internal cavity of the water tank; the steam nozzle is installed above the propeller of the existing unmanned aerial vehicle; one end of the air pipe is communicated with the internal cavity of the water tank, and the other end of the air pipe is communicated with the internal cavity of the steam nozzle; the present application is superior to the Mars helicopter scheme of the NASA of the United States.

Description

Technical Field

[0001] This invention belongs to the field of manned lunar landing, and in particular relates to a multi-rotor unmanned aerial vehicle that achieves lunar surface flight by generating its own water vapor.

[0002] The inventors clearly know that the lunar surface is a vacuum environment without an atmosphere. The innovation of this invention is to make full use of the high vacuum of the lunar surface (liquid water easily boils to generate water vapor), the high temperature furnace environment of 127 degrees Celsius (sunlight above and heat radiation from the high temperature rocks on the lunar surface below, continuously inputting heat into the liquid water), and the low gravity acceleration environment (the same mass of drone on the lunar surface has only one-sixth of the gravity on the ground). By adding a water tank, air pipe and steam nozzle to the body of the existing drone, water vapor at a certain pressure is generated to replace the atmosphere. The drone's rotor rotates, and the water vapor propels the drone to move in the air above the lunar surface, realizing the mission of exploring the surrounding area.

[0003] This innovative solution is an original invention that enables drones to fly freely in the vacuum environment of the moon, and it is superior to NASA's Mars helicopter solution. Background Technology

[0004] The present invention, "A Multi-rotor Unmanned Aerial Vehicle for Lunar Surface Flight Using Self-Generated Water Vapor," is used for environmental information collection in the area near the lunar landing site during China's lunar manned landing process. The background technology involved is as follows:

[0005] (a) Unmanned Aerial Vehicles

[0006] Unmanned vehicles, or UAVs for short, are devices operated by radio remote control equipment and onboard program control devices, or by an onboard computer that operates completely or intermittently autonomously. These include unmanned aerial vehicles, unmanned vehicles, and robot dogs.

[0007] Compared to manned aircraft, drones are often better suited for tasks that are too "dull, dirty, or dangerous." Drones can be categorized into military and civilian applications. In the civilian sector, drones combined with industry applications represent a genuine necessity. Their applications in aerial photography, agriculture, plant protection, miniature selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying, news reporting, power line inspection, film and television production, and even creating romantic moments have greatly expanded the uses of drones. Developed countries are also actively expanding industry applications and developing drone technology.

[0008] (II) China's Manned Lunar Landing Program

[0009] The China Manned Lunar Landing Program is the manned lunar landing phase of China's lunar exploration program.

[0011] The manned lunar landing project is a major scientific and technological project with high challenges, innovation and pioneering spirit.

[0012] (III) Basic data of the Moon

[0013] The Moon (English name: Moon, Latin: Luna), also known as the Moon or Taiyin, is the only natural satellite orbiting the Earth and the closest celestial body to Earth. The Moon is essentially a sphere, the fifth largest satellite in the solar system by volume, with an average radius of 1737 kilometers, a volume 1 / 49th that of Earth, and a mass 1 / 81st that of Earth. The average distance between the Earth and the Moon is 384,400 kilometers. The Moon takes 27.3 days to complete one revolution around the Earth. The Moon rotates synchronously with the same hemisphere facing the Earth, due to tidal locking. When the Moon moves in the opposite direction to the Sun, a lunar eclipse occurs.

[0014] Regarding the origin of the Moon, the dominant theory since the 1980s has been the "giant impact hypothesis," which posits that a celestial body named Theia collided with a portion of Earth's mantle during its early stages and was ejected into space. The debris then rapidly reassembled to form the Moon. The Moon does not emit its own light but reflects sunlight. Its atmosphere is extremely thin, approaching a vacuum, and contains water vapor. The lunar surface is dotted with impact craters, interspersed with dark lunar maria. Liquid water cannot exist on the lunar surface, but ice may exist within the craters at the poles. Internally, the Moon consists of a core, mantle, and crust. The lunar crust has an average thickness of 50 kilometers, with the mantle lying between the core and crust.

[0015] Lunar physical data:

[0016] Average orbital radius: 384,403 kilometers;

[0017] Orbital eccentricity: 0.0549;

[0018] Distance to perigee: 363,300 kilometers;

[0019] apogee distance: 405,696 kilometers;

[0020] Average orbital period: 27.32 days;

[0021] Average orbital speed: 1.023 km / s;

[0022] The orbital inclination angle varies between 28.58° and 18.28°;

[0023] Right ascension of the ascending node: 125.08°;

[0024] Perigee argument: 318.15°;

[0025] Average Earth-Moon distance: 384,400 kilometers;

[0026] Retrograde period at the intersection: 18.61 years;

[0027] Perigee period: 8.85 years;

[0028] Food year: 346.6 days;

[0029] Saros cycle: 18 years, 10 / 11 days;

[0030] The average inclination of the orbit relative to the ecliptic is 4°.

[0031] The average inclination of the Moon's equator to the ecliptic: 1°;

[0032] Equatorial diameter: 3476.2 kilometers;

[0033] Diameter of the poles: 3472.0 km;

[0034] Flattening: 0.0012;

[0035] Surface area: 3.79 × 10 7 square kilometers;

[0036] Volume: 2.199 × 10 10 cubic kilometers;

[0037] Mass: 7.349 × 10 22 kilogram;

[0038] Its average density is 3.350 times that of water;

[0039] Equatorial gravitational acceleration: 1.622 m / s² 2 (1 / 6 of the Earth);

[0040] Escape velocity: 2.4 km / s;

[0041] Rotation period: 27 days, 7 hours, 43 minutes, and 11.559 seconds (27.32 days, synchronous rotation);

[0042] Rotation speed: 4.6267 m / s (lunar equator);

[0043] The axis of rotation tilt varies between 3.60° and 6.69°, and its angle with the ecliptic is 1.5424°.

[0044] Albedo: 0.12;

[0045] Magnitude at full moon: -13;

[0046] Atmospheric pressure: 1.3 × 10 -10 kPa;

[0047] Surface temperature (t): -180~150℃

[0048] Maximum surface temperature: 127°C when exposed to direct sunlight;

[0049] Lowest surface temperature: -173°C during lunar night.

[0050] (iv) America's first Mars helicopter

[0051] Ingenuity is NASA's first Mars helicopter, weighing approximately 4 pounds (1.8 kg), with a fuselage about the size of a tissue box and a height of about 0.49 meters. It employs a coaxial counter-rotating rotor design, with rotors 1.2 meters in diameter made of carbon fiber and consisting of four blades. The rotors rotate at speeds exceeding 2400 revolutions per minute, far surpassing those of Earth helicopters, to generate sufficient lift in the thin Martian atmosphere (which has a density only 1% of Earth's).

[0052] The helicopter is equipped with solar panels to charge its lithium batteries for flight and to keep equipment warm during the frigid Martian nights (which can drop to -90 degrees Celsius). Its navigation and control system utilizes smartphone-grade processors such as the Qualcomm Snapdragon 801, inertial measurement units, laser altimeters, inclinometers, and cameras for navigation, enabling fully autonomous flight (due to significant communication delays between Earth and Mars). Communication relies entirely on the Perseverance rover as a relay, with a designed communication range of 100 to 1000 meters.

[0053] The Ingenuity rover was designed to fly at a maximum altitude of 3-5 meters, a maximum distance of 300 meters, a maximum horizontal speed of approximately 10 meters per second, a climb rate of approximately 3 meters per second, and a single flight time of no more than 90 seconds. The original plan was to conduct a maximum of five technology demonstration flights within 30 Martian days (approximately 31 Earth days). In the actual mission, Ingenuity far exceeded its design specifications, completing 72 flights with a total flight time exceeding 2 hours and a total distance exceeding 11.6 kilometers (7.1 miles). Its maximum altitude reached 18 meters (59 feet), and its fastest speed reached 14.5 miles per hour (6.5 meters per second). The mission duration was extended from the original 30 days to nearly 3 years (approximately 1000 Martian days). On January 18, 2024, during its 72nd flight landing, one or more rotor blades were damaged, rendering it unable to continue flying, thus ending the historic mission.

[0054] NASA is developing second-generation Mars helicopter technology for exploration missions on Mars and other planets with thin atmospheres.

[0055] (V) Harbin Institute of Technology's lunar module integrated simulation of a "ground space station"

[0056] In Heilongjiang Province, my country, a world-leading "ground space station"—the Space Environment Ground Simulation Facility—led by Harbin Institute of Technology, has been put into trial operation. This facility can comprehensively simulate various space environmental factors. Inside the lunar dust chamber is a large vacuum chamber. On the left side, an electron gun is connected to the outside to generate an electron beam, negatively charging the lunar dust. The honeycomb-shaped array on the front contains 36 deuterium lamps, which generate ultraviolet light to give the lunar dust a low-voltage positive charge. Above is a vibrating screen, primarily used to simulate the dust emission phenomenon on the lunar surface. The comprehensive lunar surface environment simulation chamber aims to simulate various environments, more closely resembling the real lunar surface environment, to study the formation mechanism of lunar dust under these conditions and its impact on spacecraft, spacesuits, and astronauts, thus making full preparations for future manned lunar landings.

[0057] (vi) Existing problems: The manned lunar landing site lacks drones for surrounding patrols.

[0059] The existing problem is that there is a lack of drones at the manned lunar landing site to quickly survey the surrounding area and obtain environmental information data. Summary of the Invention

[0060] The purpose of this invention is to provide a drone that makes full use of the high vacuum, 127-degree Celsius high-temperature furnace environment, and low gravitational acceleration of the lunar surface. By adding a water tank, air pipe, and steam nozzle to the body of an existing drone, water vapor is generated to replace the atmosphere. The drone's rotor rotates, and the water vapor propels the drone to move in the air above the lunar surface, thus achieving the mission of taking pictures and exploring.

[0061] To achieve the above objectives, the technical solution of the present invention is implemented as follows:

[0062] A multi-rotor unmanned aerial vehicle (UAV) that achieves lunar surface flight by generating its own water vapor includes a UAV body, characterized in that it further includes a water tank, an air pipe, and a steam nozzle. The water tank is installed on the top of the existing UAV, and its internal cavity is filled with pure water. The steam nozzle is installed above the propeller of the existing UAV. One end of the air pipe is connected to the internal cavity of the water tank, and the other end of the air pipe is connected to the internal cavity of the steam nozzle.

[0063] Preferably, the water tank is divided into a lower water tank and an upper cover. The upper cover is installed above the lower water tank to form a sealed cavity A, which is used to hold liquids that are easy to vaporize, such as pure water.

[0064] Preferably, the outer surface of the top cover is coated with a light-absorbing coating.

[0065] Preferably, the inner surface of the top cover extends downward with at least one heat-conducting column, the end of the heat-conducting column contacting the inner surface of the lower water tank or the end of the heat-conducting column being rigidly connected to the inner surface of the lower water tank.

[0066] Preferably, the inner cavity of the lower water tank is divided into different small water tanks by protruding ribs, which are used to fix the liquid contained therein in different areas to stabilize the flight attitude.

[0067] Preferably, the outer surface of the drain tank is coated with a heat-absorbing coating.

[0068] Preferably, the steam nozzle includes a front cover and a rear cover, the front cover being mounted on top of the rear cover to form a sealed cavity B, in which water vapor delivered from the gas pipe is temporarily stored and distributed.

[0069] Preferably, the front cover has multiple distribution holes, from which water vapor is ejected and directed toward the propeller below.

[0070] Preferably, a solenoid valve is installed at one end of the air pipe, the solenoid valve being used to control the injection and cessation of water vapor, as well as the flow rate and volume of water vapor.

[0071] This invention has one of the following advantages:

[0072] (1) The purpose of this invention is to provide a multi-rotor drone that can fly on the lunar surface by generating its own water vapor. It makes full use of the high vacuum, high temperature furnace environment of 127 degrees Celsius and low gravity acceleration environment on the lunar surface. By adding a water tank, air pipe and steam nozzle to the body of the existing drone, water vapor of a certain pressure is generated to replace the atmosphere. The rotor of the drone rotates and the water vapor propels the drone to move in the air above the lunar surface to realize the task of taking pictures and exploring the surrounding area.

[0073] (2) The cost of a single drone is low, and it can explore a larger area through a one-way flight mode that does not return.

[0074] (3) Using pure water as a medium, it vaporizes quickly and can generate water vapor at a high pressure in a short time.

[0075] (4) Multi-rotor drones are electrically powered, making it easy to charge or replace batteries, and are easy to carry and highly safe.

[0076] (5) Each UAV is small in size and light in weight, and multiple UAVs can be carried on each lunar mission.

[0077] (6) Equipped with lightweight landing gear, it can be recovered after a single long-distance flight and used as a man-made object to land on the lunar surface, marking its location and history. Attached Figure Description

[0078] Figure 1 This is a schematic diagram of the structure of the multi-rotor unmanned aerial vehicle (UAV) of the present invention, which achieves lunar surface flight by utilizing self-generated water vapor. Figure 1 (Top surface).

[0079] Figure 2 This is a schematic diagram of the structure of the multi-rotor unmanned aerial vehicle (UAV) of the present invention, which achieves lunar surface flight by utilizing self-generated water vapor. Figure 2 (ventral side).

[0080] Figure 3 This is a schematic diagram of the structure of the top cover of the water tank of the present invention.

[0081] Figure 4 This is a schematic diagram of the lower water tank structure of the water tank of the present invention.

[0082] Figure 5 This is a schematic diagram of the structure of the steam nozzle of the present invention.

[0083] Figure 6 This is a schematic diagram of the exploded structure of the steam nozzle of the present invention.

[0084] The attached figure labels are summarized as follows:

[0085] 1-Water tank; 11-Top cover; 111-Heat-conducting column; 112-Stop; 113-Connector connection port; 12-Lower water tank; 121-Protruding rib; 122-Connecting arm; 2-Air pipe; 3-Steam nozzle; 31-Front cover; 311-Distribution hole; 32-Rear cover; 33-Connector; 4-Motor and propeller. Detailed Implementation

[0086] The specific embodiments of the present invention will now be described in detail with reference to the accompanying drawings.

[0087] Example 1:

[0088] The inventors clearly know that the lunar surface is a vacuum environment without an atmosphere. The innovation of this invention is to make full use of the high vacuum of the lunar surface (where liquid water easily boils to generate water vapor), the high temperature furnace environment of 127 degrees Celsius (sunlight above and heat radiation from the high temperature rocks on the lunar surface below, continuously inputting heat into the liquid water), and the low gravitational acceleration environment (the same mass of drone on the lunar surface has only one-sixth of the gravity on the ground). By adding a water tank, air pipe and steam nozzle to the body of the existing drone, water vapor is generated to replace the atmosphere. The rotor of the drone rotates, and the water vapor propels the drone to move in the air above the lunar surface, realizing the mission of exploring the surrounding area.

[0089] The lunar physical data involved in this invention are as follows:

[0090] Maximum surface temperature: 127°C when exposed to direct sunlight;

[0091] Lowest surface temperature: -173°C during lunar night.

[0092] Equatorial gravitational acceleration: 1.622 m / s² (1 / 6 of Earth's).

[0093] (a) Lunar environmental conditions, specifically manifested as follows:

[0094] (1) Under the high vacuum environment on the lunar surface, liquid water rapidly vaporizes through evaporation and transpiration. Vaporization carries away a large amount of heat, and the liquid water condenses.

[0095] (2) The high-temperature furnace environment of 127 degrees Celsius on the lunar surface, with sunlight above and heat radiation from the high-temperature rocks on the lunar surface below, continuously inputs heat into the liquid water in the water tank, causing the liquid water to continuously vaporize.

[0096] (3) The low gravity acceleration environment makes objects of the same mass only one-sixth of the Earth's gravity. The drone becomes lighter on the lunar surface and only needs a small amount of water vapor to form 0.42% of the Earth's atmosphere for the drone to fly.

[0097] (II) Implementation Plan:

[0098] refer to Figure 1 : A schematic diagram of the structure of the multi-rotor unmanned aerial vehicle (UAV) of the present invention, which achieves lunar surface flight by utilizing self-generated water vapor. Figure 1 (Top surface).

[0099] refer to Figure 2 : A schematic diagram of the structure of the multi-rotor unmanned aerial vehicle (UAV) of the present invention, which achieves lunar surface flight by utilizing self-generated water vapor. Figure 2 (ventral side).

[0100] A multi-rotor unmanned aerial vehicle (UAV) that achieves lunar surface flight by generating its own water vapor includes a UAV body, characterized in that it further includes a water tank 1, an air pipe 2, and a steam nozzle 3. The water tank 1 is installed on the top of the existing UAV, and its internal cavity is filled with pure water. The steam nozzle 3 is installed above the propeller of the existing UAV. One end of the air pipe 2 is connected to the internal cavity of the water tank 1, and the other end of the air pipe 2 is connected to the internal cavity of the steam nozzle 3.

[0101] refer to Figure 3 : This is a schematic diagram of the structure of the upper cover of the water tank of the present invention. Multiple heat-conducting columns 111 are manufactured on the inner surface of the upper cover 11 for transferring heat from the upper cover 11. The upper cover 11 and the lower water tank 12 are connected by a stop 112 to form a sealed cavity A. Each connector is connected to the upper cover 11 through a connector connection port 113. A light-absorbing coating is applied to the outer surface of the upper cover 11 to convert absorbed light energy into heat energy, which is then transported to the liquid water through the heat-conducting columns 111, ensuring the continuous vaporization process.

[0102] refer to Figure 4 This is a schematic diagram of the lower water tank structure of the present invention. Multiple small water troughs are formed on the inner surface of the lower water trough 12 by the transverse and longitudinal ribs 121. The amount of water carried by the drone during each flight is just above the ribs 121, allowing the water to overflow and be evenly distributed among the small water troughs. These small water troughs solidify pure water within each trough to ensure stable flight. A heat-absorbing coating is applied to the outer surface of the lower water trough 12 to absorb heat radiation from lunar rocks, continuously supplying heat to the liquid water and ensuring the continuous vaporization process.

[0103] refer to Figure 5 and Figure 6 : This is a schematic diagram of the steam nozzle of the present invention. The front cover 31 and the rear cover 32 are fastened together to form a sealed cavity B. A connector 33 is connected to the top of the rear cover 32. Multiple distribution holes 311 are machined on the front cover 31, and water vapor is sprayed onto the propeller from the distribution holes 311.

[0104] Figure 6 This is a schematic diagram of the exploded structure of the steam nozzle of the present invention. The location of the distribution hole 311 is clearly shown to ensure that water vapor is sprayed as far as possible onto the outer end of the propeller.

[0105] To ensure the visual effect, red dye, or other colored dyes, can be added to the liquid water.

[0106] (III) Referencing NASA's Mars helicopter program, analyze the feasibility of this plan:

[0107] Ingenuity is NASA's first Mars helicopter, weighing approximately 4 pounds (1.8 kg), with a fuselage about the size of a tissue box and a height of about 0.49 meters. It employs a coaxial counter-rotating rotor design, with rotors 1.2 meters in diameter made of carbon fiber and consisting of four blades. The rotors rotate at speeds exceeding 2400 revolutions per minute, far surpassing those of Earth helicopters, to generate sufficient lift in the thin Martian atmosphere (which has a density only 1% of Earth's).

[0108] The helicopter is equipped with solar panels to charge its lithium batteries for flight and to keep equipment warm during the frigid Martian nights (which can drop to -90 degrees Celsius). Its navigation and control system utilizes smartphone-grade processors such as the Qualcomm Snapdragon 801, inertial measurement units, laser altimeters, inclinometers, and cameras for navigation, enabling fully autonomous flight (due to significant communication delays between Earth and Mars). Communication relies entirely on the Perseverance rover as a relay, with a designed communication range of 100 to 1000 meters.

[0109] The Ingenuity rover was designed to fly at a maximum altitude of 3-5 meters, a maximum distance of 300 meters, a maximum horizontal speed of approximately 10 meters per second, a climb rate of approximately 3 meters per second, and a single flight time of no more than 90 seconds. The original plan was to conduct a maximum of five technology demonstration flights within 30 Martian days (approximately 31 Earth days). In the actual mission, Ingenuity far exceeded its design specifications, completing 72 flights with a total flight time exceeding 2 hours and a total distance exceeding 11.6 kilometers (7.1 miles). Its maximum altitude reached 18 meters (59 feet), and its fastest speed reached 14.5 miles per hour (6.5 meters per second). The mission duration was extended from the original 30 days to nearly 3 years (approximately 1000 Martian days). On January 18, 2024, during its 72nd flight landing, one or more rotor blades were damaged, rendering it unable to continue flying, thus ending the historic mission.

[0110] Feasibility analysis of unmanned aerial vehicle (UAV) flight on the lunar surface:

[0111] (1) Assuming that the lunar surface has 1% of the Earth's atmosphere, since the gravitational acceleration on the lunar surface is less than that on Mars, NASA's first Mars helicopter can take off and land on the lunar surface.

[0112] (2) Considering that Mars has 2 / 5 of Earth's gravitational acceleration, while the Moon has only 1 / 6 of Earth's gravitational acceleration, calculations show that the Moon only needs 0.42% of Earth's atmosphere to ensure that NASA's first Mars helicopter can fly.

[0113] (3) Considering that the Mars helicopter is used in an unmanned environment, a lot of redundant mass is added, such as solar panels, tripods, insulation materials, coaxial counter-rotor drive system, etc. In contrast, our manned lunar landing has astronauts on the lunar surface, so some of the redundant mass can be omitted, and the other part of the redundant mass can be replaced by the mass of water tank, air pipe, steam nozzle and liquid water. The multi-rotor UAV of this scheme that uses self-generated water vapor to achieve lunar surface flight is very likely to fly in self-generated 0.42% water vapor.

[0114] (4) This innovative solution is an original invention that enables unmanned aerial vehicles to fly freely on the lunar surface, which is superior to NASA's Mars helicopter solution.

[0115] (iv) Other measures to ensure the feasibility of the present invention:

[0116] (1) The mass of the multi-rotor UAV that achieves lunar flight by means of self-generated water vapor of the present invention is reduced to the extreme. For example, the water tank, air pipe and steam nozzle are made of carbon fiber material in one piece, and the ribs 121 and heat conduction columns 111 are directly processed so that the heat conduction columns 111 are directly connected to the upper cover 11 and the lower water tank 12.

[0117] (2) Take advantage of the vacuum environment on the moon to increase the diameter of the propeller and not waste a single water molecule.

[0118] (3) Take advantage of the vacuum environment on the lunar surface to increase the speed of the propeller.

[0119] (4) Taking advantage of the small gravitational acceleration on the lunar surface, a double-layer propeller structure is adopted. The upper propeller is surrounded by a cylinder. Water vapor is first sprayed onto the upper propeller and then sprayed down onto the lower propeller.

[0120] (5) The multi-rotor UAV of the present invention achieves lunar surface flight by means of self-generated water vapor, and is used in one direction without returning, or with extremely reduced mass, or with increased single flight distance.

[0121] The technical principles of the present invention have been described above with reference to specific embodiments. These descriptions are merely for explaining the principles of the invention and should not be construed as limiting the scope of protection of the claims in any way. Based on this explanation, those skilled in the art can readily conceive of other specific embodiments of the invention without inventive effort, and these embodiments will all fall within the scope of protection of the claims.

Claims

1. A multi-rotor unmanned aerial vehicle (UAV) that achieves lunar surface flight by generating its own water vapor, comprising the UAV body, characterized in that, It also includes a water tank, an air pipe, and a steam nozzle. The water tank is installed on the top of the existing drone and its internal cavity is filled with purified water. The steam nozzle is installed above the propeller of the existing drone. One end of the air pipe is connected to the internal cavity of the water tank, and the other end of the air pipe is connected to the internal cavity of the steam nozzle.

2. The multi-rotor unmanned aerial vehicle (UAV) for lunar surface flight using self-generated water vapor as described in claim 1, characterized in that: The water tank is divided into a lower water tank and an upper cover. The upper cover is installed above the lower water tank to form a sealed cavity A, which is used to hold liquids that are easy to vaporize, such as pure water.

3. The multi-rotor unmanned aerial vehicle (UAV) for lunar surface flight using self-generated water vapor as described in claim 2, characterized in that, The outer surface of the top cover is coated with a light-absorbing coating or a heat-absorbing coating.

4. The multi-rotor unmanned aerial vehicle (UAV) for lunar surface flight using self-generated water vapor as described in claim 2, characterized in that, At least one heat-conducting column extends downward from the inner surface of the top cover, and the end of the heat-conducting column contacts the inner surface of the lower water tank or is rigidly connected to the inner surface of the lower water tank.

5. The multi-rotor unmanned aerial vehicle (UAV) for lunar surface flight using self-generated water vapor as described in claim 2, characterized in that, The inner cavity of the lower water tank is divided into different small water tanks by protruding ribs, which are used to fix the liquid contained therein in different areas to stabilize the flight attitude.

6. The multi-rotor unmanned aerial vehicle (UAV) for lunar surface flight using self-generated water vapor as described in claim 2, characterized in that, The outer surface of the drain tank is coated with a heat-absorbing coating.

7. The multi-rotor unmanned aerial vehicle (UAV) for lunar surface flight using self-generated water vapor as described in claim 1, characterized in that, The steam nozzle includes a front cover and a rear cover. The front cover is installed on top of the rear cover to form a sealed cavity B, in which water vapor delivered from the gas pipe is temporarily stored and distributed.

8. The multi-rotor unmanned aerial vehicle (UAV) for lunar surface flight using self-generated water vapor as described in claim 7, characterized in that, The front cover has multiple distribution holes, from which water vapor is ejected and directed toward the propeller below.

9. A multi-rotor unmanned aerial vehicle (UAV) that achieves lunar surface flight by means of self-generated water vapor according to any one of claims 1-8, characterized in that, A solenoid valve is installed at one end of the air pipe. The solenoid valve is used to control the injection and stop of water vapor, as well as to control the flow rate and volume of water vapor.

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