RU2791892C1 - Device and method for flying on the moon - Google Patents

Abstract

FIELD: space technology.

SUBSTANCE: group of inventions relates to thrust means and methods for movement in extraterrestrial space. For flying over the Moon surface, a medium from the Moon surface (fine regolith fractions) and a medium acceleration module are used. The medium is supplied to the medium acceleration module powered with solar batteries or a nuclear power plant. The accelerated medium is rejected from the module, creating jet thrust for lifting of a vehicle over the Moon and its horizontal movements.

EFFECT: overcoming obstacles related to morphology and surface relief of the Moon, thereby expanding human capabilities of studying and exploring the Moon.

11 cl, 6 dwg, 1 tbl

Description

Technical field

The present invention relates to the field of aviation technology, and more specifically relates to a method for flying on the moon and a device for flying on the moon.

Background of the invention

Unlike the Earth, which has a dense atmosphere, there is no atmosphere on the surface of the Moon, which makes it impossible to fly on the Moon using the buoyancy of the atmosphere.

At present, landing on the moon and returning from the moon mainly depend on the principle of the rocket, that is, the aircraft itself carries reactive materials, and as a result of the chemical reactions of the reactive materials, an impulse of the environment is created to overcome the limitation in the form of gravity. However, due to the limited amount of propellant in the lunar environment, it is difficult to use propellant for a long time. In addition, other propulsion methods such as electric propulsion, plasma propulsion, etc. require a large auxiliary use of energy, structure and environment, thus solving the problem of flight is even more difficult. Therefore, the exploration of the moon after landing is mainly carried out by means of an electrically driven wheeled movable device in which the wheel is driven by an on-board power supply to realize movement on the surface of the moon.

However, due to the softness of the ground in many areas on the lunar surface (i.e., lunar soil), relatively greater resistance must be overcome when moving across the lunar surface, especially when encountering complex landforms, while an electrically powered wheeled mobile device is prone to hit accidents. In addition, under conditions of steep and high terrain, the electrically driven wheeled movable device cannot perform nearby observations and measurements. Because of this, the exploration and study of the moon faces great difficulties.

The essence of the invention

In light of the above technical object, the present invention proposes a lunar flight method by which lunar flight can be realized, thereby overcoming obstacles due to the morphology of the lunar surface for scientific research and enhancing human ability to explore and explore the moon.

According to one aspect, the present invention provides a method for flying on the Moon, which uses a medium located on the Moon and a medium acceleration module. The method includes: using a power source, transferring the medium to the medium acceleration module, accelerating the medium by the medium acceleration module and ejecting the medium from the medium acceleration module, in this case, according to the momentum conservation law, an opposing force is created, and the opposing force overcomes the lunar force of attraction and lifts the load.

The environment includes solid media, such as soil, gravel, rock, which are abundantly present on a natural satellite, and fluid media, such as water resources, found on the Moon.

The method for obtaining the medium is not limited. The media may be obtained using a media acquisition unit, and the media acquisition unit may be, for example, a combination of one or more of a mechanical gripper, a belt retractor, a suction pipe, etc.

The environment acceleration module is not limited. The media acceleration module may be a device that converts electrical energy into mechanical motion, such as a device consisting of a drive unit (eg motor, etc.) and a rotating unit (eg blades, impellers, etc.). The drive unit drives the rotary unit to rotate using the power supply, the medium is transferred to the rotary unit, and the medium is accelerated by the rotary unit and thrown out. The medium acceleration module may also be an electromagnetic device. For example, the medium is magnetized and then introduced into the electromagnetic device, and the medium is accelerated and ejected from the electromagnetic device using the electromagnetic field.

When the media acceleration unit is in operation, the power supply method is not limited, and one or more of a generator, a storage battery, a power source with remote power transmission, a built-in nuclear battery, etc. can be used.

The generator includes, but is not limited to, a fuel generator. On Earth, this could be a liquid-fueled internal combustion engine that draws oxygen from the atmosphere; on the Moon, this may be a configuration similar to a rocket engine, using fuel and an oxidizer, such as a mixture of kerosene and oxygen. The advantage of the generator is that, if necessary, you can increase the power to ensure flight with a heavy load. Solar energy is an available resource on the Moon, so the generator can use solar energy and convert it into electrical energy as a power supply unit in the present invention. In one implementation, a solar panel is provided on a flight device and the solar panel can receive solar energy and convert it into electrical energy.

The storage battery can be charged using a power station, for example, it can be charged using a solar power station on the Moon or other types of power stations.

The battery can be charged using a power plant, while the power plant includes a solar power plant or other types of power plants and can be charged using a solar panel provided on the flight device.

A remote power supply transmits energy remotely, such as electromagnetic waves transmit energy (including microwave energy, light energy, etc.) over a long distance, and then converts it into electrical energy.

The built-in nuclear battery can provide electricity for a long time.

During the flight, the medium is continuously consumed. In one implementation, the method further comprises: planting before the medium is used up; and take off again after a fresh boot of the environment.

The method for transferring the medium to the media acceleration unit is not limited, and the method may be free fall, transport (eg, transport on a conveyor belt), or vibration.

When the media acceleration module comprises a driving unit and a rotating unit, lightweight materials are preferably used in the rotating unit in order to reduce impact wear. Preferably, a wear resistant coating such as diamond coating is provided on the surface of the rotating block. In addition, the load experienced by the rotating block during high-speed rotation is lower than its tensile strength.

The magnitude of the opposing force determines the amount of mass of cargo that can take off. The magnitude of the counteracting force is related to such parameters as the diameter (m) and rotation speed (rpm) of the rotating block, and the mass flow rate (kg/s) of the ejected medium, etc. That is, under constant other conditions, the magnitude of the counteracting force can be determined by determining the diameter (m) and rotation speed (rpm) of the rotating unit and the mass flow rate (kg/s) of the ejected medium, thereby determining the mass of the load that can take off. When the mass flow rate of the ejected medium is constant and other conditions are constant, the reaction force is proportional to the diameter (m) and rotation speed (rpm) of the rotating block.

For example, the following table shows the counterforce achieved by driving the paddles with a high-speed motor and the maximum mass for takeoff on the Moon.

Rotary block diameter (m) Turntable rotation speed (rpm) Ejection velocity of lunar soil (m/s) Mass flow rate of ejected lunar soil (kg/s) Reaction force (N) Maximum mass for takeoff on the moon (kg) 0.10 36000 188.50 0.10 18.85 11.54 0.10 75000 392.70 0.10 39.27 24.04 0.20 36000 376.99 0.10 37.70 23.08 0.20 75000 785.40 0.10 78.54 48.09 0.40 36000 753.98 0.10 75.40 46.16 0.40 75000 1570.80 0.10 157.08 96.17

From the table above, it can be seen that with a mass flow rate of ejected lunar soil of 0.1 kg / s, using a 100 mm impeller with a rotation speed of 75,000 rpm, an ejection speed of lunar soil of 392.7 m / s, there is an opposing force of approximately 39 N Since the Moon's gravity constant is approximately 1/6 of Earth's, the weight that the opposing force can lift is approximately 24 kg. Under the same conditions, using an impeller with a diameter of 200 mm, 48 kg of cargo is lifted, and using an impeller with a diameter of 400 mm, 96 kg of cargo is lifted. Because the high speed motor can drive the blade to reach 10,000-600,000 rpm, the weight that can be lifted is very large.

According to another aspect, the present invention provides a device for flying on the moon, comprising a power source, a medium acceleration module, and a medium storage unit.

In the working state, the power supply supplies power to the media acceleration module, the media is transferred from the media storage unit to the media acceleration module and accelerated by the media acceleration module, and is ejected from the media acceleration module to generate a counter force, and the counter force overcomes the lunar force of attraction, and the device for flying on the moon takes off.

Preferably, the lunar flight device further comprises an ejection unit, and the medium is ejected from the media acceleration module through the ejection unit. More preferably, the ejection block comprises a first ejection block and a second ejection block, wherein the reaction force generated by the medium accelerated and ejected through the first ejection block overcomes the lunar force of attraction, and the reaction force created by the medium ejected through the second ejection block controls the direction of flight. devices for flights on the moon. More preferably, the first ejection block is located on the underside of the lunar flight device and the second ejection block is located on the side of the lunar flight device.

The power source may be a generator or a battery.

The generator includes, but is not limited to, a rocket engine using a propellant and an oxidizer. The advantage of the generator is that, if necessary, you can increase the power to ensure flight with a heavy load. Solar energy is an available resource on the Moon, so the generator can use solar energy and convert it into electrical energy as a power supply unit in the present invention. In one implementation, a solar panel is provided on a lunar mission device and the solar panel can receive solar energy and convert it to electrical energy.

The storage battery can be charged by solar energy, for example, can be charged using a solar power plant on the Moon, or can be charged using a solar panel provided on the device for flying on the Moon.

Preferably, the lunar flight device further comprises a detector for detection, study, exploration, and other purposes.

Preferably, the lunar flight device further comprises a transceiver for communication.

Preferably, the lunar flight device further comprises a control device for coordinating and controlling the entire lunar flight device.

The present invention provides a new way to fly on the moon. Since there is no atmosphere on the Moon, it is impossible to fly using the buoyancy of the atmosphere. The present invention uses the environment existing on the moon, which is ejected from the environment acceleration module after being accelerated by the environment acceleration module, and returns to the moon again, while, according to the law of conservation of momentum, creating a counter force to overcome the lunar gravity force, reaching the goal of flight, thus overcoming obstacles associated with the morphology of the surface of the Moon, for scientific research and expanding human capabilities to study, explore and explore the Moon.

Brief description of graphic materials

Fig. 1 is a schematic view of the structure of the moon flight apparatus according to Embodiment 1 of the present invention.

Fig. 2 is a schematic view of the structure of the moon flight apparatus according to Embodiment 2 of the present invention.

Fig. 3 is a schematic view of the structure of the moon flight apparatus according to Embodiment 3 of the present invention.

Fig. 4 is a schematic view of the structure of the moon flight apparatus according to Embodiment 4 of the present invention.

Fig. 5 is a schematic view of the structure of the moon flight apparatus according to Embodiment 5 of the present invention.

Fig. 6 is a schematic view of the structure of the moon flight apparatus according to Embodiment 6 of the present invention.

Detailed description of embodiments

The present invention will be further described in detail below in conjunction with the embodiments. It should be noted that the following embodiments are intended to facilitate understanding of the present invention without any limiting effect.

Reference numbers in figures 1-6 mean the following:

1: aircraft body; 2: solar panel; 3: detector A; 4: detector B; 5: transceiver; 6: nozzle; 7: first nozzle; 8: lunar soil; 9: solar power plant; 10: device for capturing and filtering lunar soil; 11: power supply; 12: high speed motor; 13: impeller; 14: container for storing lunar soil; 15: central processing unit; 16: power generation device; 17: second nozzle; 19: support wheel.

Embodiment 1:

As shown in FIG. 1, the lunar flight apparatus includes an aircraft body 1, and the aircraft body 1 comprises a power source 16, a high-speed motor 12, an impeller 13, and a container 14 for storing lunar soil.

In operation, the power supply 16 supplies power to the high speed motor 12, the high speed motor 12 drives the impeller 13 to rotate at high speed. The lunar soil 8 falls from the lunar soil storage container 14 onto the impeller 13, is accelerated by the high-speed rotating impeller 13, and is ejected through the nozzle 6, and the counter force generated overcomes the lunar gravity force and lifts the flight device above the lunar surface.

The flight device further comprises detector A 3 and detector B 4 for detection and investigation.

The flight device further comprises a transceiver 5 for communication.

The flight device further comprises a central control device 15 for coordinating and controlling the entire flight device.

In this embodiment, lunar soil 8 is collected into the lunar soil storage container 14 from outside the flight device via the lunar soil capture and filtration device 10 . The amount of lunar soil in the lunar soil storage container 14 is 30 kg, the mass flow rate of the ejected lunar soil 8 is 0.1 kg/s, and a flight of 300 seconds can be realized, which can meet some requirements for scientific research and technical support.

Before the lunar soil 8 is exhausted, the flight device performs a soft landing, loads the lunar soil 8 through the lunar soil capture and filter device 10, and then takes off again.

Embodiment 2:

As shown in FIG. 2, the lunar flight apparatus includes an aircraft body 1, and the aircraft body 1 comprises a power source 11, a high-speed motor 12, an impeller 13, and a container 14 for storing lunar soil.

In operation, the power supply 11 supplies power to the high speed motor 12, the high speed motor 12 drives the impeller 13 to rotate at high speed. The lunar soil 8 falls from the lunar soil storage container 14 onto the impeller 13, is accelerated by the high-speed rotating impeller 13, and is ejected through the nozzle 6, and the counter force generated overcomes the lunar gravity force and lifts the flight device above the lunar surface.

In this embodiment, the power source 11 is a battery, and the onboard battery can be quickly charged by the lunar solar power station 9 when needed.

In addition, in this embodiment, the lunar soil 8 is collected into the lunar soil storage container 14 from the outside of the flight device by means of the lunar soil capture and filtration device 10 . Before the lunar soil 8 is exhausted, the flight device performs a soft landing, loads the lunar soil 8 through the lunar soil capture and filter device 10, and then takes off again.

The flight device further comprises detector A 3 and detector B 4 for detection and investigation.

The flight device further comprises a transceiver 5 for communication.

The flight device further comprises a central control device 15 for coordinating and controlling the entire flight device.

Embodiment 3:

In this embodiment, the structure of the moon flight device is basically the same as that of Embodiment 2, except that the solar power station 9 is replaced by the solar panel 2, and the solar panel 2 is located on the flight device, thus when the power is not enough, the flight device charges the battery 11 through the solar panel 2.

In this embodiment, the flight method of the flight device is the same as in Embodiment 1.

Embodiment 4:

In this embodiment, as shown in FIG. 4, the lunar mission apparatus includes an aircraft body 1, and the aircraft body 1 comprises a high-speed engine, an impeller, and a lunar soil storage container.

Two solar panels 2 are located on both sides of the body 1 of the aircraft. Since there is no atmospheric drag on the Moon, solar panels can be mounted on top of the aircraft to provide electrical power to a high-speed engine.

In working condition, the solar panel 2 supplies power to the high-speed motor, the high-speed motor drives the impeller to rotate at high speed. The lunar soil 8 falls from the lunar soil storage container onto the impeller, is accelerated by the high-speed rotating impeller, and is ejected through the first nozzle 7 and the second nozzle 17. ground, used to control the direction of flight; the second nozzle 17 is located on the lower surface of the body 1 of the aircraft, while the counter force generated by the ejected lunar soil is used to overcome the lunar force of gravity.

In this embodiment, the flight device further comprises a support wheel 19, which is located on the side of the body 1 of the aircraft, serving to maintain the angular orientation of the flight device and shock absorption during takeoff and landing.

Further, in this embodiment, before the lunar soil 8 is exhausted, the flight apparatus performs a soft landing, loads the lunar soil 8, and then takes off again.

The flight device further comprises detector A 3 and detector B 4 for detection and investigation.

The flight device further comprises a transceiver 5 for communication.

The flight device further comprises a central control device 15 for coordinating and controlling the sequence of actions of the flight device, including takeoff, acquisition, timely landing, resupply, etc.

Embodiment 5:

In this embodiment, the structure of the device for flying on the Moon is basically the same as in Embodiment 4, except that since there is no atmospheric drag on the Moon, the solar panel 2 is installed on the upper side of the aircraft body and is vertically, as shown in FIG. 5.

In this embodiment, the flight method of the flight apparatus is the same as in Embodiment 4.

Embodiment 6:

In this embodiment, the structure of the moon flight device is basically the same as in Embodiment 4, except that the solar panel 2 is replaced by a power generation device 16 located inside the aircraft body 1, as shown in FIG. 6, the power generation device 16 may be a generator, a storage battery, a power source with remote power transfer, or a built-in nuclear battery to provide electrical power to a high-speed engine.

In the above embodiments, the technical solutions of the present invention are described in detail. It should be understood that the embodiments are only specific embodiments of the present invention and are not intended to limit the present invention. Any modifications, additions or similar substitutions within the spirit of the present invention shall be included within the scope of the present invention.

Claims (23)

1. Device for flights on the moon, containing: power supply, environment acceleration module, media storage unit and means for transferring the medium from the medium storage unit to the medium acceleration module, at the same time, the power supply provides power supply to the medium acceleration module, which ensures the acceleration of the medium and its ejection outside from the acceleration module, the medium acceleration module contains a rotating block and a drive block for bringing the rotating block into rotation using a power source, the medium transfer means ensures the transfer of the medium into the rotating unit by means of its transportation on a conveyor belt, vibration or free fall, the rotating block is made in the form of a blade or an impeller, and the medium is lunar soil. 2. The device for flying on the moon according to claim 1, characterized in that it additionally contains an ejection block, and the medium is ejected from the medium acceleration module through the ejection block. 3. The device for flying on the moon according to claim 2, characterized in that the ejection block contains the first ejection block and the second ejection block, while the opposing force created by the medium accelerated and ejected through the first ejection block overcomes the lunar force of attraction, and the opposing force the force generated by the medium ejected through the second ejection block controls the flight direction of the lunar flight device. 4. The lunar flight device according to claim 3, characterized in that the first ejection unit is located on the underside of the lunar flight device and the second ejection block is located on the side of the lunar flight device. 5. A device for flying on the moon according to claim 1, characterized in that the power source is a generator or a battery, while the generator converts solar energy into electrical energy, the battery is charged by solar energy, the battery is charged using a solar power station on the moon or by using a solar panel provided on the lunar flight device, wherein the solar panel is located on the lunar flight device, and the solar panel receives solar energy and converts the received solar energy into electrical energy. 6. Device for flights on the moon according to claim 1, characterized in that the device for flights further comprises one or more of the following means: a transceiver and a control device. 7. The method of flying on the moon, which uses the environment located on the moon and the device according to any one of paragraphs. 1-6, including: transfer of the medium in the form of lunar soil to the medium acceleration module, acceleration of the medium by the medium acceleration module and ejection of the medium from the medium acceleration module, at the same time, the rotating block in the form of blades or impeller is brought into rotation using a drive block and a power source, and the medium is transferred to the rotating block by its transportation on a conveyor belt, vibration or free fall. 8. The method of flying on the moon according to claim 7, characterized in that the power source is one or more of the following means: a generator, a storage battery, a power source with remote power transfer, and a built-in nuclear battery. 9. The method of flying on the moon according to claim 7, characterized in that the power source is a solar power plant on the moon, converting solar energy into electrical energy to supply power to the drive unit. 10. The method of flying on the moon according to claim 7, characterized in that the method further includes: planting before the medium is used up, and taking off again after a fresh boot of the environment. 11. The method of flight on the Moon according to claim 7, characterized in that the diameter and speed of rotation of the rotating unit and the mass flow rate of the ejected medium are determined depending on the takeoff mass.

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