CN112607018A - Platform is scattered to electrified particle of no ground connection aircraft - Google Patents
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- CN112607018A CN112607018A CN202011429887.8A CN202011429887A CN112607018A CN 112607018 A CN112607018 A CN 112607018A CN 202011429887 A CN202011429887 A CN 202011429887A CN 112607018 A CN112607018 A CN 112607018A
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- 239000002245 particle Substances 0.000 title claims abstract description 60
- 230000009471 action Effects 0.000 claims abstract description 6
- 238000012544 monitoring process Methods 0.000 claims description 8
- 238000004891 communication Methods 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 5
- 230000005684 electric field Effects 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 230000008569 process Effects 0.000 claims description 3
- 230000001276 controlling effect Effects 0.000 claims description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 2
- 230000001105 regulatory effect Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 5
- 238000009825 accumulation Methods 0.000 abstract description 4
- 238000004887 air purification Methods 0.000 abstract description 4
- 238000006555 catalytic reaction Methods 0.000 abstract description 3
- 230000004048 modification Effects 0.000 abstract description 2
- 238000012986 modification Methods 0.000 abstract description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 239000000443 aerosol Substances 0.000 description 2
- 238000009833 condensation Methods 0.000 description 2
- 230000005494 condensation Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000001737 promoting effect Effects 0.000 description 2
- 230000033228 biological regulation Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000013329 compounding Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000005686 electrostatic field Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000007935 neutral effect Effects 0.000 description 1
- 230000010287 polarization Effects 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
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- A—HUMAN NECESSITIES
- A01—AGRICULTURE; FORESTRY; ANIMAL HUSBANDRY; HUNTING; TRAPPING; FISHING
- A01G—HORTICULTURE; CULTIVATION OF VEGETABLES, FLOWERS, RICE, FRUIT, VINES, HOPS OR SEAWEED; FORESTRY; WATERING
- A01G15/00—Devices or methods for influencing weather conditions
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/16—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting
- B64D1/18—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting by spraying, e.g. insecticides
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01W—METEOROLOGY
- G01W1/00—Meteorology
- G01W1/02—Instruments for indicating weather conditions by measuring two or more variables, e.g. humidity, pressure, temperature, cloud cover or wind speed
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
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- Aviation & Aerospace Engineering (AREA)
- Environmental & Geological Engineering (AREA)
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- Pest Control & Pesticides (AREA)
- Automation & Control Theory (AREA)
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- Ecology (AREA)
- Electrostatic Spraying Apparatus (AREA)
- Elimination Of Static Electricity (AREA)
Abstract
The invention discloses a ground-free aircraft charged particle scattering platform, and belongs to the field of weather modification. The aircraft that broadcasts the charged particles needs to continuously emit charges to the outside, and if the charges are neutralized without a ground wire, the loss of electrons and the accumulation of positive charges are caused. The invention utilizes the charged particle generating module to respectively emit positive and negative charges to the outside, monitors the current flowing to the positive and negative electrodes in the charged particle generating module through the power supply control module, and adjusts the voltage of the high-voltage power supply on the premise of ensuring the power as large as possible, so that the current values of the positive and negative electrodes can be kept in dynamic balance all the time, thereby avoiding the ground wire. Because the aircraft is not limited by the grounding traction piece and the ground wire any more, the large-area charged particle scattering can be carried out in an open space, and the flexibility and the action effect of tasks such as electro-catalysis rainfall, air purification and fog dissipation are improved.
Description
Technical Field
The invention belongs to the field of artificial influence weather, and particularly relates to a charged particle scattering platform of an ungrounded aircraft.
Background
The electrocatalytic rainfall is a method for promoting the formation of rainfall by electrifying part of aerosol in the air, generating an electrostatic field to have a polarization effect on other neutral water molecule clusters, generating non-contact electric field condensation force of electrified aerosol particles on the polarized water molecule clusters, and promoting the condensation rate of the water molecule clusters to increase. According to the same principle, the air purification and fog dissipation tasks can be carried out.
However, two existing techniques for scattering charged particles, that is, scattering charged particles by using a discharge device and scattering charged particles by using diffusion or natural airflow, are fixed in one position, and have a limited range and are greatly influenced by geographical locations and natural environments; or the aerial vehicle is utilized to directly enter a cloud layer or an area needing to be scattered with the charged particles for scattering, although the charged particles can be scattered in a wider space, the charged particles can also be directly scattered to a specified position, but the aerial vehicle is often matched with a traction piece and a ground wire on the ground, and if the ground wire is not arranged, the charges generated on the aerial vehicle are accumulated, so that the charged particles cannot be scattered.
The two technologies greatly limit the range of charged particle scattering in the application of an external field, have higher requirements on ground conditions, and limit the flexibility and action effects of tasks such as electro-catalysis rainfall, air purification, fog dissipation and the like.
Disclosure of Invention
In view of the above defects or improvement needs of the prior art, the present invention provides a ground-free aircraft charged particle scattering platform, and aims to provide a platform that is flexible, independent of ground traction and ground wire, and can perform large-area charged particle scattering in an open space.
In order to achieve the above object, the present invention provides a ground-free aircraft charged particle scattering platform, comprising: the system comprises an aircraft, and a charged particle generation module, a meteorological information acquisition module, a remote communication module and a power supply control module which are carried on the aircraft;
the charged particle generation module comprises a first direct-current high-voltage power supply, a second direct-current high-voltage power supply, a positive electrode and a negative electrode; the negative end of the first direct-current high-voltage power supply is connected with the positive end of the second direct-current high-voltage power supply through a common end; the other two ends respectively form a single-electrode discharge device consisting of a positive electrode and a negative electrode, positive and negative particles are generated under the action of a direct-current high-voltage power supply, and the charged particles are scattered through the electrodes;
the meteorological information acquisition module is used for monitoring meteorological parameters of a working area where the aircraft is located in real time; the remote communication module is used for receiving the meteorological parameters acquired by the meteorological information acquisition module, communicating with the ground and controlling the flight state of the aircraft by monitoring the meteorological parameters;
and the power supply control module is used for monitoring the current flowing to the positive electrode and the negative electrode in the charged particle generation module, and adjusting the voltage or the current of the first direct-current high-voltage power supply and the voltage or the current of the second direct-current high-voltage power supply on the premise of ensuring that the power supply power is maximum within an allowable range, so that the currents of the positive electrode and the negative electrode are kept in dynamic balance, and the ground wire is avoided.
Further, the meteorological information acquisition module comprises a temperature and humidity sensor, an air pressure measuring device, a height measuring device and a charged particle concentration measuring device.
Further, one end of the telecommunications module is located on the aircraft and the other end is located on the ground.
Further, the positive electrode and the negative electrode in the charged particle generating module are made of carbon fiber.
Further, the positive and negative electrodes are arranged in a brush shape.
Furthermore, the distance between the two electrode ends of the first direct-current high-voltage power supply and the second direct-current high-voltage power supply which are not connected through the common end is 3-5 times of the electric gap of the non-uniform electric field.
Further, the specific process of the power control module adjusting the voltage or current of the first dc high-voltage power supply and the second dc high-voltage power supply is as follows:
s1, firstly increasing the voltage or current of a first high-voltage power supply; then the voltage or the current of the second high-voltage power supply is increased;
s2, if the voltage or the current of the second high-voltage power supply can be increased and the difference value of the voltage or the current of the second high-voltage power supply and the current of the first high-voltage power supply is within an allowable range, returning to execute the step S1; otherwise, restoring the voltage or the current of the first high-voltage power supply and the second high-voltage power supply to be the last regulating value;
and S3, setting the voltage or the current of the first high-voltage power supply and the second high-voltage power supply according to the maximum allowable power which can be reached in the allowable range of the corresponding current difference value.
In general, the above technical solutions contemplated by the present invention can achieve the following advantageous effects compared to the prior art.
The aircraft that broadcasts the charged particles needs to continuously emit charges to the outside, and if the charges are neutralized without a ground wire, the loss of electrons and the accumulation of positive charges are caused. The invention utilizes the charged particle generating module to respectively emit positive and negative charges to the outside, monitors the current flowing to the positive and negative electrodes in the charged particle generating module through the power supply control module, and adjusts the voltage of the high-voltage power supply on the premise of ensuring the power as large as possible, so that the current values of the positive and negative electrodes can be kept in dynamic balance all the time, thereby avoiding the ground wire. Because the aircraft is not limited by the grounding traction piece and the ground wire any more, the large-area charged particle scattering can be carried out in an open space, and the flexibility and the action effect of tasks such as electro-catalysis rainfall, air purification and fog dissipation are improved.
Drawings
FIG. 1 is a schematic view of a charged particle scattering platform of an ungrounded aircraft according to the present invention;
FIG. 2 is a schematic diagram of the topology of the internal circuit of the non-grounded aircraft charged particle scattering platform provided by the invention;
FIG. 3 is a high voltage supply voltage current regulation process provided by the present invention;
wherein 1 is a first direct current high voltage power supply, and 2 is a second direct current high voltage power supply.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
The passenger plane with electricity demand forms a circuit loop by utilizing a metal frame of the passenger plane, a ground traction wire is not needed, and the electric load on the passenger plane does not need to emit charges to the outside and keeps the charge balance all the time, so that the loss of electrons and the accumulation of positive charges are avoided. However, the aircraft spreading the charged particles needs to continuously emit charges to the outside, and if the charges are neutralized without a ground wire, the loss of electrons and the accumulation of positive charges are caused. The invention respectively sends out positive and negative charges to the outside through the charged particle generating module, and maintains the dynamic balance of sending out the positive and negative charges through the power supply control module, thereby realizing the overall charge balance.
Referring to fig. 1, an example of the present invention provides a ground-free aircraft charged particle scattering platform, including: the system comprises an aircraft, a charged particle generation module, a meteorological information acquisition module, a remote communication module and a power supply control module; all modules are carried on the aircraft;
referring to fig. 2, the charged particle generating module includes a positive electrode, a negative electrode and two dc high voltage power supplies; the negative end of the first direct-current high-voltage power supply 1 is connected with the positive end of the second direct-current high-voltage power supply 2 through a common end, the remaining two ends are respectively a positive end and a negative end and are respectively single-electrode discharge devices consisting of a positive electrode and a negative electrode, positive particles and negative particles are generated under the action of the direct-current high-voltage power supplies, and the charged particles are scattered through electrodes; the distance between the two remaining electrode ends of the direct-current high-voltage power supply is long enough, specifically 3-5 times of the electrical gap of the non-uniform electric field specified in GB16935.1-2008, so that no discharge phenomenon in the form of double electrodes is generated between the electrodes, and the compounding of positive and negative charged particles can be greatly reduced. Under the scene of electronic broadcasting, the voltage range of the direct-current high-voltage power supply is 50-150 kv.
In order to minimize the aircraft load while ensuring good electrical conductivity of the electrodes, the positive and negative electrodes in the charged particle generating module are preferably made of carbon fibers, and are preferably configured in a brush shape because brush-shaped electrodes are susceptible to point discharge. The invention is not limited to this, and it is within the scope of the invention to use electrodes of different shapes made of other materials.
The meteorological information acquisition module comprises a temperature and humidity sensor, an air pressure measuring device, a height measuring device and a charged particle concentration measuring device and is used for monitoring meteorological parameters of a working area where the aircraft is located in real time.
The one end of remote communication module is located the aircraft, and the other end is located subaerial for receive meteorological parameter that meteorological information collection module gathered, communicate with ground, control flight direction and distance etc. of aircraft through monitoring meteorological parameter.
The power supply control module monitors the current flowing to the positive electrode and the negative electrode in the charged particle generation module through the ammeter, and adjusts the voltage of the high-voltage power supply on the premise of ensuring the power as large as possible according to the current difference value, so that the current values of the positive electrode and the negative electrode can be kept in dynamic balance all the time; as shown in fig. 3, the voltage or current of the first dc high-voltage power supply 1 is increased, and then the voltage or current of the second dc high-voltage power supply 2 is increased, and if the voltage or current of the second dc high-voltage power supply 2 can be increased and the current difference is within the allowable range, the above operations are repeated; otherwise, restoring the voltage or current of the first direct-current high-voltage power supply 1 and the second direct-current high-voltage power supply 2 to be the last value; the present invention considers that the maximum power is reached when the voltage and current of the second dc high voltage power supply 2 cannot track the voltage or current of the first dc high voltage power supply 1. And setting the voltage or the current of the first direct-current high-voltage power supply 1 and the second direct-current high-voltage power supply 2 according to the maximum allowable power which can be reached in the corresponding allowable range of the current difference value.
It will be understood by those skilled in the art that the foregoing is only a preferred embodiment of the present invention, and is not intended to limit the invention, and that any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (7)
1. A non-grounded aircraft charged particle scattering platform, comprising: the system comprises an aircraft, and a charged particle generation module, a meteorological information acquisition module, a remote communication module and a power supply control module which are carried on the aircraft;
the charged particle generation module comprises a first direct-current high-voltage power supply (1), a second direct-current high-voltage power supply (2), a positive electrode and a negative electrode; the negative end of the first direct-current high-voltage power supply is connected with the positive end of the second direct-current high-voltage power supply through a common end; the other two ends respectively form a single-electrode discharge device consisting of a positive electrode and a negative electrode, positive particles and negative particles are generated under the action of the first direct-current high-voltage power supply and the second direct-current high-voltage power supply, and the charged particles are scattered through the electrodes;
the meteorological information acquisition module is used for monitoring meteorological parameters of a working area where the aircraft is located in real time; the remote communication module is used for receiving the meteorological parameters acquired by the meteorological information acquisition module, communicating with the ground and controlling the flight state of the aircraft by monitoring the meteorological parameters;
and the power supply control module is used for monitoring the current flowing to the positive electrode and the negative electrode in the charged particle generation module, and adjusting the voltage or the current of the first direct-current high-voltage power supply and the voltage or the current of the second direct-current high-voltage power supply on the premise of ensuring that the power supply power is maximum within an allowable range, so that the currents of the positive electrode and the negative electrode are kept in dynamic balance, and the ground wire is avoided.
2. The ungrounded aircraft charged particle scattering platform according to claim 1, wherein the meteorological information acquisition module comprises a temperature and humidity sensor, an air pressure measuring device, an altitude measuring device and a charged particle concentration measuring device.
3. The ungrounded aircraft charged particle scattering platform of claim 2, wherein the telecommunications module is located on the aircraft at one end and on the ground at the other end.
4. The non-grounded aircraft charged particle scattering platform according to any one of claims 1 to 3, wherein the positive and negative electrodes in the charged particle generation module are made of carbon fiber.
5. The non-grounded aircraft charged particle scattering platform as claimed in claim 4, wherein the positive and negative electrodes are configured as a brush.
6. The ungrounded aircraft charged particle scattering platform as claimed in any one of claims 1 to 5, wherein the distance between the two electrode terminals of the first DC high voltage power supply and the second DC high voltage power supply which are not connected through the common terminal is 3 to 5 times the electrical gap of the non-uniform electric field.
7. The ungrounded aircraft charged particle scattering platform of claim 6, wherein the specific process of the power control module adjusting the voltage or current of the first DC high voltage power supply and the second DC high voltage power supply is as follows:
s1, firstly increasing the voltage or current of a first high-voltage power supply; then the voltage or the current of the second high-voltage power supply is increased;
s2, if the voltage or the current of the second high-voltage power supply can be increased and the difference value of the voltage or the current of the second high-voltage power supply and the current of the first high-voltage power supply is within an allowable range, returning to execute the step S1; otherwise, restoring the voltage or the current of the first high-voltage power supply and the second high-voltage power supply to be the last regulating value;
and S3, setting the voltage or the current of the first high-voltage power supply and the second high-voltage power supply according to the maximum allowable power which can be reached in the allowable range of the corresponding current difference value.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011429887.8A CN112607018B (en) | 2020-12-07 | 2020-12-07 | Platform is scattered to electrified particle of no ground connection aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011429887.8A CN112607018B (en) | 2020-12-07 | 2020-12-07 | Platform is scattered to electrified particle of no ground connection aircraft |
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| Publication Number | Publication Date |
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| CN112607018A true CN112607018A (en) | 2021-04-06 |
| CN112607018B CN112607018B (en) | 2022-04-01 |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US20060284004A1 (en) * | 2005-06-14 | 2006-12-21 | Jones Edward B | Method of scavenging atmospheric energy, causing rainfall, and for dissipating severe weather formations using an electrostatic dirigible |
| US20120123181A1 (en) * | 2006-08-18 | 2012-05-17 | Itt Manufacturing Enterprises, Inc. | Charged Seed Cloud as a Method for Increasing Particle Collisions and for Scavenging Airborne Biological Agents and Other Contaminants |
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| US20160165813A1 (en) * | 2014-12-10 | 2016-06-16 | The Boeing Company | Systems and methods of inducing rainfall |
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2020
- 2020-12-07 CN CN202011429887.8A patent/CN112607018B/en active Active
Patent Citations (7)
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| US20060284004A1 (en) * | 2005-06-14 | 2006-12-21 | Jones Edward B | Method of scavenging atmospheric energy, causing rainfall, and for dissipating severe weather formations using an electrostatic dirigible |
| US20120123181A1 (en) * | 2006-08-18 | 2012-05-17 | Itt Manufacturing Enterprises, Inc. | Charged Seed Cloud as a Method for Increasing Particle Collisions and for Scavenging Airborne Biological Agents and Other Contaminants |
| CN104396646A (en) * | 2014-09-23 | 2015-03-11 | 石家庄虎林环保设备有限公司 | Method for eliminating haze through artificially inducing rainfall with charged water mist |
| US20160165813A1 (en) * | 2014-12-10 | 2016-06-16 | The Boeing Company | Systems and methods of inducing rainfall |
| CN109479592A (en) * | 2018-12-14 | 2019-03-19 | 黄朝 | A kind of no pylon weather regulating system |
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