CN111516906A - Flight method and flight device - Google Patents
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/105—Space science
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/105—Space science
- B64G1/1064—Space science specifically adapted for interplanetary, solar or interstellar exploration
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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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
Technical Field
The invention belongs to the technical field of flight, and particularly relates to a flight method and a flight device.
Background
Unlike the earth, where dense atmospheres exist, some stars have no atmosphere or a rarefied atmosphere, such as the moon, the spark, etc., and therefore, exploration and investigation of these stars is very challenging.
Taking lunar exploration as an example, the landing and returning of the moon at present mainly depend on the rocket principle, namely, the aircraft carries reaction substances, and medium impulse is generated through chemical reaction to overcome gravitational constraint. However, it is difficult to use rocket fuel in a lunar environment for a long time due to the limited amount of rocket fuel. Other propulsion means, such as electric propulsion, plasma propulsion, etc., still require large auxiliary energy, structural and medium consumption, which makes it more difficult to solve the flight problem. Therefore, the detection of the moon after landing is mainly realized by electrically driving the wheel driving device, namely, by driving the wheel to rotate by vehicle-mounted electric power, so as to realize the movement on the moon 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, and particularly when complex terrain is encountered, the electric driving wheel device is prone to accidents. In addition, the electric driving wheel device for steep or high landform cannot be observed and sampled nearby. Detection of other stars, such as mars, faces similar dilemma.
Disclosure of Invention
In view of the technical current situation, the invention provides a novel flying method which is suitable for various environments, including the environment without atmosphere or with thin atmosphere and cannot fly by means of atmospheric buoyancy, so that the flying method can be realized on extraterrestrial celestial bodies (extraterrestrial bodies for short) such as moon, mars and the like, thereby breaking through the barrier of the surface morphology of the celestial bodies on scientific investigation and expanding the detection and development capability of human beings on the celestial bodies.
The technical scheme provided by the invention is as follows: a flight 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 a momentum conservation effect and overcomes the gravity of a planet to drive a load to take off.
The planet may be the earth in which the atmosphere exists, or may be an extraterrestrial planet in which the atmosphere is sparse, such as the moon, a spark, or the like.
The medium is a medium on the surface of the planet, and comprises a solid medium, such as soil, gravel, rocks and other abundant resources on the planet, and also comprises a fluid medium, such as water resources on the planet.
The manner of acquiring the medium is not limited, and includes one or a combination of several of a medium acquiring unit, such as a mechanical gripper, a belt winder, an inhalation duct, and the like.
The medium accelerating unit is not limited, and may be a device that converts electric energy into mechanical motion, for example, a driving unit such as a motor and a motor, and a rotating unit such as a blade and an impeller, and under the action of electric power, the driving unit works to drive the rotating unit to rotate, and conveys the medium to the rotating unit, and the medium is accelerated by the rotating unit and then thrown out; the medium may be an electromagnetic device, for example, the medium may be polarized and then input into the electromagnetic device, and the medium may be accelerated by the electromagnetic field and then leave the electromagnetic device.
When the medium accelerating unit works, the power supply mode is not limited, and one or more of a generator, a storage battery, a remote energy transmission power supply, an onboard nuclear power supply and the like can be adopted.
The generator includes but is not limited to a fuel-based generator, which may be a fuel-powered internal combustion engine on earth, with oxygen taken from the atmosphere; on the moon may be a rocket engine like arrangement using a fuel mixed with an oxidant such as kerosene and oxygen, etc. The generator has the advantages that the power can be expanded according to needs, and heavy-load flight is realized. Solar energy is an available resource on the earth, moon, mars, and other stars, and therefore, in the present invention, the generator may convert solar energy into electric energy as a power supply unit. As one implementation, a solar panel is provided on the flying apparatus, which can receive solar energy and convert it into electrical energy.
The accumulator may be charged by a power station, for example, a solar star station or other type of power station.
The storage battery can be charged through a power station, the power station comprises a solar power station or other types of power stations, and solar charging can be carried out through a solar sailboard arranged on the flight device.
Remote energy delivery power supplies transmit energy remotely, such as electromagnetic waves, including microwaves, light energy, etc., and then convert it to electrical energy.
The onboard nuclear power source can provide power for a long time.
In the flight process, the medium is continuously consumed, and as an implementation mode, the aircraft lands before the medium is exhausted, and then takes off after the medium is loaded.
The method by which the medium is conveyed to the medium accelerating unit is not limited, and may be carried by free fall, by transmission such as a belt, or by vibration, or the like.
When the medium accelerating unit includes a driving unit and a rotating unit, the rotating unit is preferably made of a lightweight material in order to reduce impact wear. As a further preference, the surface of the rotating unit is provided with a wear resistant coating, such as a diamond coating or the like. In addition, the rotating unit is subjected to a stress lower than its ultimate yield stress when rotating at high speed.
The magnitude of the reaction force determines the magnitude of the load mass capable of takeoff. The magnitude 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) at which the medium is thrown. That is, the magnitude of the reaction force can be controlled by controlling the diameter (m) of the rotating unit, the rotational speed (rpm), and the mass flow rate (Kg/s) at which the medium is thrown, and thus the load mass that can take off is controlled, as other conditions are constant. When the mass flow rate of the medium thrown out is constant and other conditions are constant, the reaction force is in direct proportion to the diameter (m) and the rotating speed (rpm) of the rotating unit.
For example, the following table shows the reaction force achieved using a high speed motor to drive the blades when the medium is lunar soil and the ultimate mass for takeoff at the moon.
As can be seen from the above table, when the mass flow thrown out of the lunar soil is set to 0.1Kg/s, and an impeller with a diameter of 100 mm is used, at a rotation speed of 75000rpm, the speed of the lunar soil throwing out is 392.7m/s, and a reaction force of about 39N can be achieved. The gravitational constant of the moon is about 1/6 of the earth, so the reaction force can drive the load mass for taking off to be about 24 Kg. Under the same condition, the impeller with the diameter of 200 mm is used, and the 48 Kg-level load takeoff can be realized; with an impeller of 400 mm diameter, a load takeoff of the order of 96Kg can be achieved. The high-speed motor can drive the blades to achieve the rotating speed of 10000-600000rpm, so that the load mass for taking off can be driven to be large.
The invention also provides a flight device, which comprises a power supply, a medium accelerating unit and a medium storage unit;
when the flying device is in a working state, the power supply supplies power to the medium accelerating unit, the medium accelerating unit works, the medium is conveyed from the medium storage unit to the medium accelerating unit and is separated from the medium accelerating unit after the medium accelerating unit is accelerated, and the generated reaction force overcomes the gravity of a planet and drives the flying device to take off.
Preferably, the flying device further comprises an ejection unit, and the medium is separated from the medium acceleration unit after passing through the ejection unit. Preferably, the ejection unit includes a first ejection unit and a second ejection unit, the medium is accelerated and then separated from the medium acceleration unit by the first ejection unit, the generated reaction force is used to overcome the gravitational force of the planet, and the medium is separated from the medium acceleration unit by the second ejection unit, and the generated reaction force is used to control the flight direction. More preferably, the first ejection unit is provided at the bottom of the flying device, and the second ejection unit is provided at a side surface of the flying device.
The power supply can be a generator or a storage battery.
The generator includes but is not limited to a fuel-based generator, which may be a fuel-powered internal combustion engine on earth, with oxygen taken from the atmosphere; on the moon may be a rocket engine like arrangement using a fuel mixed with an oxidant such as kerosene and oxygen, etc. The generator has the advantages that the power can be expanded according to needs, and heavy-load flight is realized. Solar energy is an available resource on the earth, moon, mars, and other stars, and therefore, in the present invention, the generator may convert solar energy into electric energy as a power supply unit. As one implementation, a solar panel is provided on the flying apparatus, which can receive solar energy and convert it into electrical energy.
The storage battery can be charged by solar energy, for example, solar energy can be charged by a planet solar power station, or solar energy can be charged by a solar sailboard arranged on the flying device.
Preferably, the flying device further comprises a detector for the purposes of detection, investigation, research and the like.
Preferably, the flying device further comprises a communicator for communicating.
Preferably, the flying device further comprises a central controller for coordinating and controlling the whole flying device.
The invention provides a novel flying method, which is particularly suitable for environments without atmosphere or with very thin atmosphere, so that the flying by means of atmospheric buoyancy cannot be carried out, for example, the flying of outer stars such as moon, mars and the like. The medium existing on the planet is utilized, the medium is separated from the medium accelerating unit after being accelerated by the medium accelerating unit and returns to the planet again, the reaction force is generated by the momentum conservation effect to overcome the gravity of the planet, so that the flying purpose is skillfully realized, the barrier of the ground morphology of the planet on scientific investigation is broken through, and the detection, investigation and development capabilities of human beings on the planet such as moon, mars and the like can be expanded.
Drawings
Fig. 1 is a schematic structural diagram of a lunar surface flying apparatus in embodiment 1 of the present invention.
Fig. 2 is a schematic structural diagram of a lunar surface flying device in embodiment 2 of the present invention.
Fig. 3 is a schematic structural diagram of a lunar surface flying device in embodiment 3 of the present invention.
Fig. 4 is a schematic structural diagram of a lunar surface flying apparatus in embodiment 4 of the present invention.
Fig. 5 is a schematic structural diagram of a lunar surface flying apparatus in embodiment 5 of the present invention.
Fig. 6 is a schematic structural diagram of a lunar surface flying apparatus in embodiment 6 of the present invention.
Detailed Description
The present invention is described in further detail below with reference to examples, which are intended to facilitate the understanding of the present invention without limiting it in any way.
The reference numerals in fig. 1-6 are: 1. an aircraft body; 2. a solar sailboard; 3. a detector A; 4. a detector B; 5. a communicator; 6. a nozzle; 7. a first nozzle; 8. lunar soil; 9. a solar power station; 10. lunar soil grabbing and filtering devices; 11. a power source; 12. a high-speed motor; 13. an impeller; 14. a lunar soil storage container; 15. a central processing unit; 16. a power generation device; 17. a second nozzle; 19. and supporting the wheels.
Example 1:
a lunar surface flying device, as shown in figure 1, comprises a flying body 1, wherein the flying body 1 comprises a power supply 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 to drive the impeller 13 to rotate at a high speed, the lunar soil 8 falls from the lunar soil storage container 14 to the impeller 13, is accelerated by the high-speed rotating impeller 13 and is thrown out through the nozzle 6, and the generated reaction force overcomes the lunar gravity to drive the flying device to take off at the lunar surface.
The flying apparatus also includes a detector a3 and a detector B4 for conducting detection studies.
The flying device further comprises a communicator 5 for communicating.
The flying apparatus further comprises a central controller 15 for coordinating the control of the entire flying apparatus.
In this embodiment, lunar soil 8 is captured by lunar soil capture and filtration device 10 from outside the flying device into lunar soil storage container 14. The lunar soil in the lunar soil storage container 14 is 30Kg, the mass flow rate of the lunar soil 8 thrown out is 0.1Kg/s, 300-second flight can be realized, and the flight time can meet certain scientific detection and engineering requirements. Before the lunar soil 8 is exhausted, the flight device realizes soft landing, and the lunar soil 8 is loaded by using the lunar soil grabbing and filtering device 10 and then continues to take off.
Example 2:
a lunar surface flying device, as shown in FIG. 2, comprises a flying body 1, wherein the flying body 1 comprises a power supply 11, a high-speed motor 12, an impeller 13 and a lunar soil storage container 14.
When the flying device works, the power supply 11 supplies power to the high-speed motor, the high-speed motor 12 works to drive the impeller 13 to rotate at a high speed, the lunar soil 8 falls from the lunar soil storage container 14 to the impeller 13, is accelerated by the high-speed rotating impeller 13 and is thrown out through the nozzle 6, and the generated reaction force overcomes the lunar gravity to drive the flying device to take off at the lunar surface.
In this embodiment, the power source 11 is a storage battery, and the onboard storage battery can be charged quickly through the lunar solar power station 9 when necessary.
In addition, in this embodiment, lunar soil 8 is captured by lunar soil capture and filtration device 10 from outside the flying device into lunar soil storage container 14. Before the lunar soil 8 is exhausted, the flight device realizes soft landing, and the lunar soil 8 is loaded by using the lunar soil grabbing and filtering device 10 and then continues to take off.
The flying apparatus also includes a detector a3 and a detector B4 for conducting detection studies.
The flying device further comprises a communicator 5 for communicating.
The flying apparatus further comprises a central controller 15 for coordinating the control of the entire flying apparatus.
Example 3:
in this embodiment, the configuration of the lunar rover is substantially the same as that of embodiment 2, except that the solar power station 9 is replaced with a solar panel 2, and the solar panel 2 is provided on the rover, so that the rover charges the battery 11 through the solar panel 2 when the power is insufficient.
In this embodiment, the flying method of the flying device is the same as that of embodiment 1.
Example 4:
in this embodiment, a lunar surface flying device, as shown in fig. 4, includes a flying body 1, and the flying body 1 includes a high-speed motor, an impeller, and a lunar soil storage container.
Two solar sailboards 2 are arranged on the side face of the flying main body 1, and can be installed on the upper portion of the aircraft to provide electric energy for the high-speed motor by utilizing the convenience that no atmospheric resistance exists on the moon.
When the solar sailboard 2 works, the high-speed motor provides electric energy for the high-speed motor, the high-speed motor works to drive the impeller to rotate at a high speed, lunar soil 8 falls to the impeller from a lunar soil storage container, is accelerated by the high-speed rotating impeller and is thrown out through the first nozzle 6 and the second nozzle 7, the first nozzle 6 is arranged on the side face of the flying body 1, the reaction force after the lunar soil is thrown out is used for controlling the flying direction, the second nozzle 7 is arranged on the bottom face of the flying body 1, and the reaction force after the lunar soil is thrown out is used for overcoming the gravity of the moon.
In this embodiment, the flying device further includes a support wheel 9 disposed on the side of the flying body 1 for maintaining the attitude of the flying device and realizing the buffering of take-off and landing.
In addition, in the embodiment, before the lunar soil 8 is exhausted, the flight device realizes soft landing, and takes off after the lunar soil 8 is loaded.
The flying apparatus also includes a detector a3 and a detector B4 for conducting detection studies.
The flying device further comprises a communicator 5 for communicating.
The flying device further comprises a central controller 15 for coordinating and controlling a series of actions of the flying device, including take-off, detection, timely landing replenishment and the like.
Example 5:
in this embodiment, the structure of the lunar surface flying device is substantially the same as that of embodiment 4, except that the solar sailboard 2 is installed on the top of the flying body and vertically placed as shown in fig. 5, taking advantage of the convenience of no atmospheric resistance on the moon.
In this embodiment, the flying method of the flying device is the same as that of embodiment 4.
Example 6:
in this embodiment, the structure of the lunar surface flying device is substantially the same as that of embodiment 4, except that the solar sailboard 2 is replaced by a power generation device 16 arranged inside the flying body 1, as shown in fig. 6, the power generation device 16 may be a generator, a storage battery, a remote energy transmission power supply or an onboard nuclear power supply, and provides electric energy for a high-speed motor.
Example 7:
a mars flying device, its structure is similar to figure 1, includes the flight main part, and the flight main part includes power, high-speed motor, blade and soil storage container.
When the device is in a working state, the power supply supplies power to the high-speed motor, the high-speed motor works to drive the blades to rotate at a high speed, the mars soil falls to the blades from the soil storage container, is accelerated by the blades rotating at the high speed and is thrown out through the nozzle, and the generated reaction force overcomes the attraction of mars and drives the flying device to take off on the mars surface.
The flying apparatus also includes a detector a3 and a detector B4 for conducting detection studies.
The flying device further comprises a communicator 5 for communicating.
The flying apparatus further comprises a central controller 15 for coordinating the control of the entire flying apparatus.
In this embodiment, the mars soil is grabbed into the soil storage container by the soil grabbing and filtering device from the flight device exterior. Before the soil is exhausted, the flying device realizes soft landing, utilizes the soil grabbing and filtering device to load the soil, and then continues to take off.
The embodiments described above are intended to illustrate the technical solutions of the present invention in detail, and it should be understood that the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the present invention, and any modification, supplement or similar substitution made within the scope of the principles of the present invention should be included in the protection scope of the present invention.
Claims (23)
1. A flight method is characterized in that: adopting 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 a momentum conservation effect and overcomes the gravity of a planet to drive a load to take off.
2. The flying method of claim 1 wherein: the planet is a free or rarefied planet.
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 of claim 1 wherein: the medium accelerating unit comprises a driving unit and a rotating unit, under the action of electric power, the driving unit works to drive the rotating unit to rotate, the medium is conveyed to the rotating unit, and the medium is thrown out after being accelerated by the rotating unit.
5. The flying method according to claim 4 wherein: the drive unit is an electric motor or an electric machine;
preferably, the rotating unit is a blade or an impeller.
6. The flying method of claim 1 wherein: the medium accelerating unit is an electromagnetic device, polarizes the medium, inputs the polarized medium into the electromagnetic device, and accelerates the medium under the action of an electromagnetic field and then leaves the electromagnetic device.
7. The flying method of claim 1 wherein: one or more of a generator, a storage battery, a remote energy transmission power supply and an onboard nuclear energy power supply are adopted to supply power for the medium accelerating unit.
8. The flying method of claim 1 wherein: solar energy is converted into electric energy by utilizing a solar station on the planet, and the electric energy is used for supplying power for the driving unit.
9. The flying method of claim 1 wherein: the medium is conveyed to the medium accelerating unit through transmission, vibration transmission or free falling body.
10. The flying method of claim 1 wherein: landing before the medium is exhausted, and taking off after the medium is loaded.
11. A method as claimed in any one of claims 1 to 10, wherein: the medium accelerating unit consists of a driving unit and a rotating unit, and the load mass of the takeoff is controlled by controlling the diameter and the rotating speed of the rotating unit and the mass flow rate of the thrown medium.
12. A flight device is characterized in that: comprises a power supply, a medium accelerating unit and a medium storage unit;
when the flying device is in a working state, the power supply supplies power to the medium accelerating unit, the medium accelerating unit works, the medium is conveyed from the medium storage unit to the medium accelerating unit and is separated from the medium accelerating unit after the medium accelerating unit is accelerated, and the generated reaction force overcomes the gravity of a planet and drives the flying device to take off.
13. The heeling apparatus of claim 12, wherein: the device also comprises a spraying unit, and the medium is separated from the medium accelerating unit after passing through the spraying unit.
14. The heeling apparatus of claim 12, wherein: the ejection unit comprises a first ejection unit and a second ejection unit, the medium is accelerated and then separated from the medium acceleration unit through the first ejection unit, the generated reaction force is used for overcoming the gravitational force of the planet, the medium is separated from the medium acceleration unit through the second ejection unit, and the generated reaction force is used for controlling the flight direction.
15. The heeling apparatus of claim 14, wherein: the first spraying unit is arranged at the bottom of the flying device, and the second spraying unit is arranged on the side face of the flying device.
16. The heeling apparatus of claim 12, wherein: the power source is a generator or a battery.
17. The heeling apparatus of claim 16, wherein: the generator converts solar energy into electrical energy.
18. The heeling apparatus of claim 16, wherein: a solar sail panel is provided on the flying device, which receives solar energy and converts it into electrical energy.
19. The heeling apparatus of claim 16, wherein: the storage battery is charged by solar energy;
preferably, the solar energy is charged by a planet solar power station or a solar sailboard arranged on the flying device.
20. The heeling apparatus of claim 12, wherein: the flying apparatus further comprises a detector.
21. The heeling apparatus of claim 12, wherein: the flying device also includes a communicator.
22. The heeling apparatus of claim 12, wherein: the flying apparatus further comprises a central controller.
23. A flying device according to any one of claims 12 to 22 wherein: the planet is a non-atmospheric or a rarefied planet.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910107849.1A CN111516906A (en) | 2019-02-02 | 2019-02-02 | Flight method and flight device |
| PCT/CN2019/085930 WO2020155458A1 (en) | 2019-02-02 | 2019-05-08 | Flying method and flying device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910107849.1A CN111516906A (en) | 2019-02-02 | 2019-02-02 | Flight method and flight device |
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| CN111516906A true CN111516906A (en) | 2020-08-11 |
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| CN201910107849.1A Pending CN111516906A (en) | 2019-02-02 | 2019-02-02 | Flight method and flight device |
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| CN (1) | CN111516906A (en) |
| WO (1) | WO2020155458A1 (en) |
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