CN111516906A - Flight method and flight device - Google Patents

Abstract

The invention discloses a flight method and a flight device. The method adopts a medium on the surface of a planet and a medium accelerating unit; under the action of electric power, the medium accelerating unit works to convey the medium to the medium accelerating unit, the medium is separated from the medium accelerating unit after the medium accelerating unit is accelerated, and a counterforce is generated due to momentum conservation and overcomes the gravity of a planet to drive a load to take off. The method is novel and unique, is particularly suitable for environments without atmosphere or with very thin atmosphere, so that the environment cannot fly by means of atmospheric buoyancy, such as the flying of moon, mars and the like, breaks through the barrier of ground morphology to scientific investigation, and can expand the detection, investigation and development capabilities of human beings on the celestial bodies such as the moon, the mars and the like.

Description

A flight method and a flight device

technical field

The invention belongs to the field of flight technology, and in particular relates to a flight method and a flight device.

Background technique

Different from the earth with a dense atmosphere, some planets have no atmosphere or thin atmosphere on the surface, such as the moon, Mars, etc., so the exploration and investigation of these planets is very challenging.

Taking lunar exploration as an example, the current landing and return of the moon mainly rely on the principle of rockets, that is, the reaction material is brought by the aircraft, and the medium impulse is generated through chemical reaction to overcome the gravitational constraint. But due to the limited rocket fuel, it is difficult to use rocket fuel in the lunar environment for a long time. Other means of propulsion, such as electric propulsion, plasma propulsion, etc., still require large auxiliary energy, structure and medium consumption, and are more difficult to solve the flight problem. Therefore, the lunar exploration after landing is mainly realized by the electric drive wheel device, that is, the wheel rotation is driven by the on-board electric power to realize the movement on the lunar surface. However, due to the soft lunar soil in many areas on the lunar surface, the lunar surface movement needs to overcome a large resistance, especially when encountering complex landforms, the electric drive wheel device is prone to accidents. In addition, the electric drive wheel device for steep or high terrain cannot be observed and sampled nearby. Exploration of other planets such as Mars faces a similar dilemma.

SUMMARY OF THE INVENTION

In view of the above-mentioned technical status, the present invention provides a new method of flying, which is suitable for various environments, including environments without atmosphere or thin atmosphere and cannot fly by means of atmospheric buoyancy, so it can be realized in the moon, Mars and other planets other than the earth ( Alien planets for short), so as to break through the obstacles of planetary surface morphology to scientific investigation, and expand human's ability to detect and develop planets.

The technical solution provided by the present invention is as follows: a flight method adopts the medium on the surface of the planet and the medium acceleration unit; under the action of electricity, the medium acceleration unit works, and the medium is transported to the medium acceleration unit, and the medium is separated from the medium after the medium acceleration unit is accelerated. The acceleration unit generates a reaction force due to the momentum conservation effect, which overcomes the gravitational force of the planet and drives the load to take off.

The planet may be the Earth with an atmosphere, or may be an alien planet without an atmosphere, or an alien planet with a thin atmosphere, such as the moon, Mars, and the like.

The medium is the medium on the surface of the planet, including solid medium, such as soil, gravel, rock and other sufficient resources on the planet, and also includes fluid medium, such as water resources on the planet.

The manner of acquiring the medium is not limited, including a medium acquiring unit, such as one or a combination of a mechanical gripper, a belt reel, a suction pipe, and the like.

The medium acceleration unit is not limited, and can be a device that converts electrical energy into mechanical motion. For example, a driving unit such as a motor and a motor is composed of a rotating unit such as a blade and an impeller. Under the action of electricity, the driving unit works to drive the rotating unit to rotate and convey When the medium is placed on the rotating unit, the medium is thrown out after being accelerated by the rotating unit; it can also be an electromagnetic device. For example, the medium is polarized and then input into the electromagnetic device, and the medium is accelerated under the action of the electromagnetic field and then leaves the electromagnetic device.

When the medium acceleration unit is working, the power supply mode is not limited, and one or more of a generator, a battery, a remote energy transmission power source, an airborne nuclear power source, and the like can be used.

The generators include but are not limited to fuel generators. On Earth, they can be fuel-fired internal combustion engines, and oxygen is taken from the atmosphere; on the moon, they can be configured like rocket engines, using fuel and oxidant, such as kerosene mixed with oxygen. The advantage of the generator is that the power can be expanded as needed, enabling heavy-duty flight. Solar energy is an available resource on planets such as the earth, the moon, and Mars, so in the present invention, the generator can convert the solar energy into electrical energy as a power supply unit. As an implementation manner, a solar panel is arranged on the flying device, and the solar panel can receive solar energy and convert it into electrical energy.

The battery can be charged by a power station, for example, a planetary solar power station or other types of power stations.

The storage battery can be charged by a power station, and the power station includes a solar power station or other types of power stations, and can also be charged by solar energy through a solar sail panel arranged on the flying device.

The remote energy transmission power supply transmits energy remotely, such as electromagnetic wave long-distance energy transmission, including microwave, light energy, etc., and then converts it into electrical energy.

The onboard nuclear power supply can provide power for a long time.

During the flight, the medium is continuously consumed, as one implementation, landing before the medium is exhausted, and then taking off after loading the medium.

The method for the medium to be transported to the medium acceleration unit is not limited, and it can be by free fall, by transmission, such as conveyor belt, or by vibration.

When the medium acceleration unit includes a driving unit and a rotating unit, in order to reduce impact wear, the rotating unit preferably uses a lightweight material. As a further preference, a wear-resistant coating, such as a diamond coating, is provided on the surface of the rotating unit. In addition, the stress experienced by the rotating unit during high-speed rotation is lower than its ultimate yield stress.

The size of the reaction force determines the size of the load mass that can be taken off. The size of the reaction force is related to parameters such as the diameter (m) of the rotating unit, the rotational speed (rpm) and the mass flow rate (Kg/s) of the medium being thrown out. That is, other conditions are fixed, by controlling the diameter (m), rotational speed (rpm) of the rotating unit and the mass flow rate (Kg/s) of the medium thrown out, the magnitude of the reaction force can be controlled, thereby controlling the load mass that can be taken off. When the mass flow rate of the medium thrown out is constant, and other conditions are constant, the reaction force is proportional to the diameter (m) and rotation speed (rpm) of the rotating unit.

For example, the following table shows the reaction force achieved by the use of high-speed motor-driven blades when the medium is lunar soil and the limit mass for take-off on the moon.

As can be seen from the above table, when the mass flow of the lunar soil is set to be 0.1Kg/s, and the impeller with a diameter of 100 mm is used, at 75000rpm, the speed of the lunar soil is 392.7m/s, which can be A reaction force of about 39N is achieved. The gravitational constant of the moon is about 1/6 of that of the earth, so the load mass that can be driven by this reaction force is about 24Kg. Under the same conditions, using an impeller with a diameter of 200 mm, a load of 48Kg can be taken off; using an impeller with a diameter of 400 mm, a load of 96Kg can be taken off. The high-speed motor can drive the blades to achieve a rotational speed of 10,000-600,000rpm, so the load that can drive the take-off is very large.

The present invention also provides a flying device, comprising a power supply, a medium acceleration unit and a medium storage unit;

In the working state, the power supply supplies power to the medium acceleration unit, the medium acceleration unit works, the medium is transported from the medium storage unit to the medium acceleration unit, and after the medium acceleration unit is accelerated, it is separated from the medium acceleration unit, and the generated reaction force overcomes the gravitational force of the planet and drives the flight device. take off.

Preferably, the flying device further includes an ejection unit, and the medium is separated from the medium acceleration unit after passing through the ejection unit. As a further preference, the ejection unit includes a first ejection unit and a second ejection unit. After the medium is accelerated, the medium is separated from the medium acceleration unit through the first ejection unit, and the generated reaction force is used to overcome the gravitational force of the planet. After the ejection unit is separated from the medium acceleration unit, the generated reaction force is used to control the flight direction. As a further preference, the first ejection unit is arranged on the bottom of the flying device, and the second ejection unit is arranged on the side of the flying device.

The power source can be a generator or a battery.

The generators include but are not limited to fuel generators. On Earth, they can be fuel-fired internal combustion engines, and oxygen is taken from the atmosphere; on the moon, they can be configured like rocket engines, using fuel and oxidant, such as kerosene mixed with oxygen. The advantage of the generator is that the power can be expanded as needed, enabling heavy-duty flight. Solar energy is an available resource on planets such as the earth, the moon, and Mars, so in the present invention, the generator can convert the solar energy into electrical energy as a power supply unit. As an implementation manner, a solar panel is arranged on the flying device, and the solar panel can receive solar energy and convert it into electrical energy.

The storage battery can be charged by solar energy, for example, it can be charged by solar energy by means of a planetary solar power station, and it can also be charged by solar energy by means of a solar panel installed on the flying device.

Preferably, the flying device further includes a detector, which is used for detection, investigation, research and other purposes.

Preferably, the flying device further includes a communicator for communicating with each other.

Preferably, the flying device further includes a central controller for coordinating and controlling the entire flying device.

The invention provides a new flight method, which is especially suitable for the environment where there is no atmosphere or the atmosphere is very thin, so the flight cannot be carried out by means of atmospheric buoyancy, for example, the flight on the moon, Mars and other alien planets. The invention utilizes the medium existing on the planet, the medium is accelerated by the medium acceleration unit and then returns to the planet after being separated from the medium acceleration unit, and the reaction force generated by the momentum conservation effect overcomes the planet's gravitational force to skillfully achieve the purpose of flight, breaking through the ground shape of the planet Obstacles to scientific investigation can expand human's ability to detect, investigate, and explore planets such as the moon and Mars.

Description of drawings

FIG. 1 is a schematic structural diagram of a lunar flight device in Embodiment 1 of the present invention.

FIG. 2 is a schematic structural diagram of a lunar flight device in Embodiment 2 of the present invention.

3 is a schematic structural diagram of a lunar flight device in Embodiment 3 of the present invention.

4 is a schematic structural diagram of a lunar flight device in Embodiment 4 of the present invention.

FIG. 5 is a schematic structural diagram of a lunar flight device in Embodiment 5 of the present invention.

6 is a schematic structural diagram of a lunar flight device in Embodiment 6 of the present invention.

Detailed ways

The present invention will be described in further detail below with reference to the examples. It should be noted that the following examples are intended to facilitate the understanding of the present invention, but do not have any limiting effect on it.

The reference signs in Figures 1-6 are: 1. Aircraft body; 2. Solar panel; 3. Probe A; 4. Probe B; 5. Communicator; 6. Nozzle; 7. First nozzle; 8 , lunar soil; 9, solar power station; 10, lunar soil grabbing and filtering device; 11, power supply; 12, high-speed motor; 13, impeller; 14, lunar soil storage container; 15, central processing unit; 16, power generation device; 17. The second nozzle; 19. The support wheel.

Example 1:

A lunar flight device, as shown in FIG. 1 , includes a flight body 1 , and the flight body 1 includes a power source 16 , a high-speed motor 12 , an impeller 13 and a lunar soil storage container 14 .

In the working state, the power supply 16 supplies power to the high-speed motor 12, the high-speed motor 12 works, and drives the impeller 13 to rotate at a high speed. , the generated reaction force overcomes the gravitational force of the moon and drives the flying device to take off on the lunar surface.

The flying device also includes probe A3 and probe B 4 for conducting detection research.

The flying device also includes a communicator 5 for communicating.

The flying device also includes a central controller 15 for coordinating control of the entire flying device.

In this embodiment, the lunar soil 8 is grabbed into the lunar soil storage container 14 by the lunar soil grabbing and filtering device 10 from outside the flight device. The lunar soil in the lunar soil storage container 14 is 30Kg, and the mass flow rate of the lunar soil 8 thrown out is 0.1Kg/s, which can achieve a flight of 300 seconds. Such a flight time can meet certain scientific detection and engineering requirements. Before the lunar soil 8 is exhausted, the flying device achieves a soft landing, uses the lunar soil grabbing and filtering device 10 to load the lunar soil 8, and then continues to take off.

Example 2:

A lunar flight device, as shown in FIG. 2 , includes a flight body 1 , and the flight body 1 includes a power source 11 , a high-speed motor 12 , an impeller 13 and a lunar soil storage container 14 .

In the working state, the power supply 11 supplies power to the high-speed motor, the high-speed motor 12 works, and the impeller 13 is driven to rotate at a high speed. The generated reaction force overcomes the gravitational force of the moon and drives the flying device to take off on the lunar surface.

In this embodiment, the power source 11 is a battery, and the on-board battery can be quickly charged by the lunar solar power station 9 when necessary.

In addition, in this embodiment, the lunar soil 8 is grasped into the lunar soil storage container 14 by the lunar soil grabbing and filtering device 10 from the outside of the flying device. Before the lunar soil 8 is exhausted, the flying device achieves a soft landing, uses the lunar soil grabbing and filtering device 10 to load the lunar soil 8, and then continues to take off.

The flying device also includes probe A3 and probe B 4 for conducting detection research.

The flying device also includes a communicator 5 for communicating.

The flying device also includes a central controller 15 for coordinating control of the entire flying device.

Example 3:

In this embodiment, the structure of the lunar flight device is basically the same as that of the second embodiment, the difference is that the solar power station 9 is replaced by a solar panel 2, and the solar panel 2 is arranged on the flight device. Therefore, when the power is insufficient, the flight The device charges the battery 11 through the solar panel 2 .

In this embodiment, the flying method of the flying device is the same as that of the first embodiment.

Example 4:

In this embodiment, a lunar flight device, as shown in FIG. 4 , includes a flight body 1 , and the flight body 1 includes a high-speed motor, an impeller and a lunar soil storage container.

Two solar panels 2 are arranged on the side of the flying main body 1, and the solar panels 2 can be installed on the upper part of the aircraft by taking advantage of the convenience of no atmospheric resistance on the moon to provide electric power for the high-speed motor.

In the working state, the solar panel 2 provides electrical energy for the high-speed motor, the high-speed motor works, and drives the impeller to rotate at a high speed. The lunar soil 8 falls from the lunar soil storage container to the impeller, and is accelerated by the high-speed rotating impeller. The nozzle 7 is thrown out, the first nozzle 6 is arranged on the side of the flying body 1, the reaction force after the lunar soil is thrown out is used to control the flight direction, the second nozzle 7 is arranged on the bottom surface of the flying body 1, and after the lunar soil is thrown out The reaction force is used to overcome the lunar gravity.

In this embodiment, the flying device further includes a support wheel 9, which is arranged on the side of the flying body 1, and is used to maintain the attitude of the flying device and realize buffering for take-off and landing.

In addition, in this embodiment, before the lunar soil 8 is exhausted, the flying device achieves a soft landing, and takes off after loading the lunar soil 8 .

The flying device also includes probe A3 and probe B 4 for conducting detection research.

The flying device also includes a communicator 5 for communicating.

The flying device also includes a central controller 15 for coordinating and controlling a series of actions of the flying device, including take-off, detection, timely landing and replenishment, and the like.

Example 5:

In this embodiment, the structure of the lunar flight device is basically the same as that of Embodiment 4. The difference is that there is no atmospheric resistance on the moon. As shown in FIG. place.

In this embodiment, the flying method of the flying device is the same as that of the fourth embodiment.

Example 6:

In this embodiment, the structure of the lunar flight device is basically the same as that of the fourth embodiment, the difference is that the solar panel 2 is replaced by a power generation device 16 arranged inside the flight body 1 , as shown in FIG. 6 , the power generation device 16 can be It is a generator, battery, remote energy delivery power source or onboard nuclear power source that provides power to high-speed motors.

Example 7:

A Mars flight device, the structure of which is similar to that in Figure 1, includes a flight body, and the flight body includes a power source, a high-speed motor, blades and a soil storage container.

In the working state, the power supply supplies power to the high-speed motor, the high-speed motor works, and drives the blades to rotate at a high speed. The Martian soil falls from the soil storage container to the blades, and is accelerated by the high-speed rotating blades. Drive the flying device to take off on the surface of Mars.

The flying device also includes probe A3 and probe B 4 for conducting detection research.

The flying device also includes a communicator 5 for communicating.

The flying device also includes a central controller 15 for coordinating control of the entire flying device.

In this embodiment, the Martian soil is grabbed into the soil storage container from the outside of the flight device by the soil grabbing and filtering device. Before the soil is exhausted, the flying device achieves a soft landing, uses the soil grabbing and filtering device to load the soil, and then continues to take off.

The above embodiments describe the technical solutions of the present invention in detail. It should be understood that the above are only specific embodiments of the present invention and are not intended to limit the present invention. Anything done within the scope of the principles of the present invention Any modifications, additions or substitutions in similar manners, etc., shall be included within the protection scope of the present invention.

Claims (23)

1. a flight method, it is characterized in that: adopt the medium and medium acceleration unit of planetary surface; Under the action of electricity, the medium acceleration unit works, and the medium is transported to the medium acceleration unit. After the medium acceleration unit is accelerated, the medium leaves the medium acceleration unit. Due to the momentum conservation effect, a reaction force is generated, which overcomes the gravitational force of the planet and drives the load to take off. 2 . The flight method according to claim 1 , wherein the planet is a planet with no atmosphere or a thin atmosphere. 3 . 3. The flying method of claim 1, wherein the medium is a solid medium or a fluid medium; Preferably, the solid medium is one or more of soil, gravel, and rock; Preferably, the fluid medium is water. 4. The flying method according to claim 1, wherein the medium acceleration unit comprises a drive unit and a rotation unit, and under the action of electricity, the drive unit works, drives the rotation unit to rotate, conveys the medium to the rotation unit, and the medium It is thrown out after being accelerated by the rotating unit. 5. The flying method of claim 4, wherein the drive unit is an electric motor or an electric motor; Preferably, the rotating unit is a blade or an impeller. 6 . The flying method according to claim 1 , wherein the medium acceleration unit is an electromagnetic device, and the medium is polarized and input into the electromagnetic device, and the medium is accelerated under the action of the electromagnetic field and then leaves the electromagnetic device. 7 . 7. The flight method of claim 1, wherein one or more of a generator, a battery, a remote energy transmission power source, and an airborne nuclear power source are used to power the medium acceleration unit. 8 . The flying method according to claim 1 , wherein the solar energy station on the planet is used to convert the solar energy into electric energy to supply power for the drive unit. 9 . 9 . The flying method according to claim 1 , wherein the medium is conveyed to the medium acceleration unit through transmission transmission, vibration transmission or free fall. 10 . 10. The flying method according to claim 1, characterized in that: landing before the medium is exhausted, and taking off after loading the medium. 11. The flying method according to any one of claims 1 to 10, wherein the medium acceleration unit is composed of a driving unit and a rotating unit, and the medium is thrown out by controlling the diameter of the rotating unit, the rotational speed and the speed of the medium thrown out. The mass flow rate controls the take-off load mass. 12. A flying device, characterized in that it comprises a power supply, a medium acceleration unit and a medium storage unit; In the working state, the power supply supplies power to the medium acceleration unit, the medium acceleration unit works, the medium is transported from the medium storage unit to the medium acceleration unit, and after the medium acceleration unit is accelerated, it is separated from the medium acceleration unit, and the generated reaction force overcomes the gravitational force of the planet and drives the flight device. take off. 13 . The flying device according to claim 12 , further comprising an ejection unit, and the medium is separated from the medium acceleration unit after passing through the ejection unit. 14 . 14. The flying device of claim 12, wherein the ejection unit comprises a first ejection unit and a second ejection unit, and after the medium is accelerated, the first ejection unit is separated from the medium acceleration unit to generate The reaction force is used to overcome the gravitational force of the planet, and after passing through the second ejection unit, it is separated from the medium acceleration unit, and the generated reaction force is used to control the flight direction. 15. The flying device according to claim 14, wherein the first ejecting unit is arranged on the bottom of the flying device, and the second ejecting unit is arranged on the side of the flying device. 16. The flying device of claim 12, wherein the power source is a generator or a battery. 17. The flying device of claim 16, wherein the generator converts solar energy into electrical energy. 18. The flying device according to claim 16, characterized in that: a solar sail board is arranged on the flying device, and the solar sail board receives solar energy and converts it into electrical energy. 19. The flying device of claim 16, wherein the battery is charged by solar energy; Preferably, solar charging is performed through a planetary solar power station, or solar energy charging is performed through a solar panel installed on the flying device. 20. The flying device of claim 12, wherein the flying device further comprises a detector. 21. The flying device of claim 12, wherein the flying device further comprises a communicator. 22. The flying device of claim 12, wherein the flying device further comprises a central controller. 23. The flying device according to any one of claims 12 to 22, wherein the planet is a planet with no atmosphere or a thin atmosphere.

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