CN111959753A - Unmanned aerial vehicle of safe performance - Google Patents
Unmanned aerial vehicle of safe performance Download PDFInfo
- Publication number
- CN111959753A CN111959753A CN202010898879.1A CN202010898879A CN111959753A CN 111959753 A CN111959753 A CN 111959753A CN 202010898879 A CN202010898879 A CN 202010898879A CN 111959753 A CN111959753 A CN 111959753A
- Authority
- CN
- China
- Prior art keywords
- unmanned aerial
- aerial vehicle
- parachute
- cabin
- flight control
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 22
- 230000001681 protective effect Effects 0.000 claims abstract description 6
- 230000006698 induction Effects 0.000 claims description 11
- 230000000694 effects Effects 0.000 claims description 4
- 210000001015 abdomen Anatomy 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims description 3
- 230000008054 signal transmission Effects 0.000 claims description 3
- 108010066278 cabin-4 Proteins 0.000 abstract description 7
- 238000013507 mapping Methods 0.000 abstract description 3
- 239000003208 petroleum Substances 0.000 abstract description 3
- 238000007689 inspection Methods 0.000 abstract description 2
- 239000002689 soil Substances 0.000 description 2
- 238000013473 artificial intelligence Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
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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
- B64D17/00—Parachutes
- B64D17/62—Deployment
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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
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
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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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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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
- B64D47/00—Equipment not otherwise provided for
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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
- B64D47/00—Equipment not otherwise provided for
- B64D47/08—Arrangements of cameras
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention discloses an unmanned aerial vehicle with safe performance, which comprises a rack 1, a parachute cabin 3, a flight control cabin 4, a propeller 5, a protective bracket 6 and an inductance coil 13, is safe and reliable, prevents the unmanned aerial vehicle from entering a high-voltage discharge area, protects the unmanned aerial vehicle from being damaged by the unmanned aerial vehicle on electric power facilities, can automatically pop up the parachute in an uncontrolled state when a crash accident happens due to an accident, and can be widely applied to agriculture and forestry plant protection, electric power patrol, petroleum pipeline inspection, homeland surveying and mapping, artificial rainfall, aerial remote sensing, emergency rescue and relief, geological survey, safety patrol, logistics express delivery, medical rescue, ocean remote sensing, news report and the like.
Description
Technical Field
The invention belongs to the field of aircrafts, belongs to an unmanned aerial vehicle, and particularly relates to an unmanned aerial vehicle with safe performance.
Background
With the rapid development of industrial internet, big data, artificial intelligence and other emerging technologies in recent years, the unmanned aerial vehicle has wide application requirements in the fields of routing inspection, detection and the like in dangerous areas or spaces where people are inconvenient to arrive by virtue of the characteristics of high flexibility, low cost and the like. At present, unmanned aerial vehicles flying in outdoor scenes are mature in application, and can be deeply applied to a plurality of industrial scenes such as agriculture and forestry plant protection, electric power line patrol, petroleum pipeline patrol, national soil surveying and mapping, artificial rainfall, aerial remote sensing, emergency rescue and disaster relief, geological survey, safety patrol, logistics express delivery, medical rescue, ocean remote sensing, news reports and the like. Meanwhile, the power grid development is also expanded rapidly, and in the intensive construction of various outdoor high-voltage, ultrahigh-voltage and extra-high-voltage overhead lines, although the existing unmanned aerial vehicle basically has the obstacle avoidance function, the unmanned aerial vehicle is damaged by electric shock due to high-voltage discharge of a power line, even the power grid accident phenomenon is caused, and the machine and airborne goods are damaged completely due to crash accidents caused by factors such as the unmanned aerial vehicle.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle with safe performance, which can automatically avoid a line discharge range according to the voltage condition of a power grid and keep a safe distance, and can automatically pop up a parachute in an uncontrolled state when a crash accident occurs due to an accident.
The invention relates to an unmanned aerial vehicle with safe performance, which comprises a rack 1, a parachute cabin 3, a flight control cabin 4, a propeller 5, a protection bracket 6 and an inductance coil 13, and is characterized in that: the central position of the frame 1 is provided with a parachute cabin 3, the periphery of the parachute cabin 3 is provided with a flight control cabin 4, no less than two pairs of propellers 5 are arranged at the periphery of the frame 1, the outer side of each propeller 5 is connected with the frame 1 and provided with a protective bracket 6, and the top end of each protective bracket 6 is provided with an inductance coil 13;
the parachute cabin 3 is of a cylindrical structure, the top of the parachute cabin is provided with the safety cover 2, the bottom of the parachute cabin is open and is in a horn mouth shape, and a parachute connected with the frame 1 body is installed inside the parachute cabin;
the flight control cabin 4 is internally provided with a flight control system, and a main control board of the flight control system is connected with a wireless signal transmission unit, a satellite positioning unit, a motor of the propeller 5, an inductance coil 13 and airborne equipment.
The lower part of the abdomen of the rack 1 is provided with undercarriage 11, rack hanging and mounting airborne equipment and a battery cabin 12 are connected between the undercarriage 11, and the airborne equipment comprises a cloud deck 10, a high-definition camera 7, a thermal imager 8 and a gyroscope 9 which are mounted on the cloud deck 10; the battery compartment 12 is located in the lower part of the airborne equipment and has an induction coil 13 mounted at the bottom.
Drawings
The invention is described in further detail below with reference to the following figures and detailed description:
fig. 1 is a schematic view of a top view of an unmanned aerial vehicle with safe performance according to the present invention;
fig. 2 is a schematic view of a vertical structure of the unmanned aerial vehicle with safe performance.
In the figure: 1-frame, 2-safety cover, 3-parachute cabin, 4-flight control cabin, 5-propeller, 6-protective bracket, 7-high-definition camera, 8-thermal imager, 9-gyroscope, 10-tripod head, 11-undercarriage, 12-battery cabin and 13-inductance coil.
Detailed Description
The invention relates to an unmanned aerial vehicle with safe performance, which comprises a rack 1, a parachute cabin 3, a flight control cabin 4, a propeller 5, a protection bracket 6 and an inductance coil 13, and is characterized in that: the central position of the frame 1 is provided with a parachute cabin 3, the periphery of the parachute cabin 3 is provided with a flight control cabin 4, no less than two pairs of propellers 5 are arranged at the periphery of the frame 1, the outer side of each propeller 5 is connected with the frame 1 and provided with a protective bracket 6, and the top end of each protective bracket 6 is provided with an inductance coil 13;
the parachute cabin 3 is of a cylindrical structure, the top of the parachute cabin is provided with the safety cover 2, the bottom of the parachute cabin is open and is in a horn mouth shape, and a parachute connected with the frame 1 body is installed inside the parachute cabin;
a flight control system is arranged in the flight control cabin 4, and a main control board of the flight control system is connected with a wireless signal transmission unit, a satellite positioning unit, a motor of the propeller 5, an inductance coil 13 and airborne equipment;
the lower part of the abdomen of the rack 1 is provided with undercarriage 11, rack hanging and mounting airborne equipment and a battery cabin 12 are connected between the undercarriage 11, and the airborne equipment comprises a cloud deck 10, a high-definition camera 7, a thermal imager 8 and a gyroscope 9 which are mounted on the cloud deck 10; the battery compartment 12 is located in the lower part of the airborne equipment and has an induction coil 13 mounted at the bottom.
Each inductance coil 13 is respectively installed at the top end of the protection bracket 6 and the bottom of the unmanned aerial vehicle, one end of each inductance coil 13 is connected with the voltage detection unit of the main control board, the other end of each inductance coil is bonded, and when one inductance coil 13 detects voltage, the flight control system locks the unmanned aerial vehicle to move towards the direction of the corresponding inductance coil; when two or more induction coils 13 detect voltage and form potential, the flight control system controls the unmanned aerial vehicle to return along the previous action route until the induction coils 13 do not detect the voltage any more; when two or more than two inductance coils 13 detect that the voltage does not form the electric potential, the flight control system locks the unmanned aerial vehicle to move towards the direction of the inductance coil which detects the voltage.
The effect of the insurance lid 2 at 3 tops in parachute bay is when unmanned aerial vehicle breaks down, and when the stall whereabouts, the parachute is popped out to back off insurance lid 2 under the effect of atmospheric pressure, makes unmanned aerial vehicle slowly land, avoids unmanned aerial vehicle and machine-carried goods to fall and decreases.
The high-definition camera 7 and the thermal imager 8 act on the AR function of the unmanned aerial vehicle to realize accurate obstacle avoidance and cruise of a preset route; the gyroscope 9 assists the main control board to control the cloud deck 10 and the horizontal flight angle of the unmanned aerial vehicle.
The unmanned aerial vehicle with safe performance is safe and reliable, can be prevented from entering a high-voltage discharge area, can be used for protecting the unmanned aerial vehicle from damaging electric facilities, has a function of safe landing when the unmanned aerial vehicle fails, and can be widely applied to agriculture and forestry plant protection, electric power line patrol, petroleum pipeline patrol, national soil surveying and mapping, artificial rainfall, aerial remote sensing, rescue and relief work, geological survey, safety patrol, logistics express delivery, medical rescue, ocean remote sensing, news report and the like.
Claims (3)
1. A drone of safe performance, comprising: frame (1), parachute cabin (3), flight control cabin (4), screw (5), protective cradle (6), inductance coils (13), its characterized in that: the parachute cabin (3) is arranged in the center of the rack (1), the flight control cabin (4) is arranged on the periphery of the parachute cabin (3), no less than two pairs of propellers (5) are arranged on the periphery of the rack (1), the rack (1) is connected to the outer side of each propeller (5) to be provided with a protection bracket (6), and an inductance coil (13) is arranged at the top end of each protection bracket (6);
the parachute cabin (3) is of a cylindrical structure, the top of the parachute cabin is provided with a safety cover (2), the bottom of the parachute cabin is open and is in a horn mouth shape, and a parachute connected with the frame (1) body is installed inside the parachute cabin;
a flight control system is arranged in the flight control cabin (4), and a main control board of the flight control system is connected with a wireless signal transmission unit, a satellite positioning unit, a motor of the propeller (5), an inductance coil (13) and airborne equipment;
the lower part of the abdomen of the rack (1) is provided with undercarriage (11), a rack is connected between the undercarriage (11) to hang and install airborne equipment and a battery compartment (12), the airborne equipment comprises a cradle head (10), and a high-definition camera (7), a thermal imager (8) and a gyroscope (9) which are arranged on the cradle head (10); the battery compartment (12) is positioned at the lower part of the airborne equipment, and the bottom of the battery compartment is provided with an inductance coil (13).
2. A drone of safe performance according to claim 1, characterized in that: each induction coil (13) is respectively installed at the top end of the protection support (6) and the bottom of the unmanned aerial vehicle, one end of each induction coil (13) is connected with the voltage detection unit of the main control board, the other end of each induction coil is grounded, and when one induction coil (13) detects voltage, the unmanned aerial vehicle is locked by the flight control system to move towards the direction where the induction coil is located; when two or more induction coils (13) detect voltage and form potential, the flight control system controls the unmanned aerial vehicle to return along the previous action route until the induction coils (13) do not detect the voltage any more; when two or more than two inductance coils (13) detect that the voltage does not form the electric potential, the flight control system locks the unmanned aerial vehicle to move towards the direction of the inductance coil which detects the voltage.
3. A drone of safe performance according to claim 1, characterized in that: the effect of safety cover (2) at parachute bay (3) top is when unmanned aerial vehicle breaks down, and when the stall whereabouts, backs up safety cover (2) under the effect of atmospheric pressure and pops out the parachute.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010898879.1A CN111959753A (en) | 2020-08-31 | 2020-08-31 | Unmanned aerial vehicle of safe performance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010898879.1A CN111959753A (en) | 2020-08-31 | 2020-08-31 | Unmanned aerial vehicle of safe performance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111959753A true CN111959753A (en) | 2020-11-20 |
Family
ID=73400171
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010898879.1A Withdrawn CN111959753A (en) | 2020-08-31 | 2020-08-31 | Unmanned aerial vehicle of safe performance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111959753A (en) |
-
2020
- 2020-08-31 CN CN202010898879.1A patent/CN111959753A/en not_active Withdrawn
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20201120 |