CN111994255B - Individual light and small aerial survey unmanned aerial vehicle and individual light and small aerial survey unmanned aerial vehicle system - Google Patents
Individual light and small aerial survey unmanned aerial vehicle and individual light and small aerial survey unmanned aerial vehicle system Download PDFInfo
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- CN111994255B CN111994255B CN202010843818.5A CN202010843818A CN111994255B CN 111994255 B CN111994255 B CN 111994255B CN 202010843818 A CN202010843818 A CN 202010843818A CN 111994255 B CN111994255 B CN 111994255B
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/36—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
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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
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
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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
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Support Of Aerials (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention relates to an individual light and small aerial survey unmanned aerial vehicle and an individual light and small aerial survey unmanned aerial vehicle system, wherein an upper cover plate, a lower cover plate and a side plate assembly are arranged on a central circuit board to enclose a cavity for accommodating the central circuit board, a power supply assembly is arranged above the upper cover plate, so that the whole aerial survey unmanned aerial vehicle is compact in structure, the size and the wheelbase of the unmanned aerial vehicle are reduced through a large amount of structural optimization and high integration, the unmanned aerial vehicle can be completed by one person no matter in packaging, transportation or actual operation, convenience and flexibility in use are greatly improved, an air inlet is arranged on a main body of the unmanned aerial vehicle, and a radiating extension is arranged at the tail part of the main body of the unmanned aerial vehicle, so that collective overheat failure caused by the central circuit board is effectively avoided. Through the highly integrated ground station system, the complex actions of preparing a notebook computer, connecting a ground transceiver module, arranging an antenna and the like by a user are avoided, the use-and-play is realized, and the usability is greatly improved.
Description
Technical Field
The invention relates to the field of aerial survey unmanned aerial vehicles, in particular to an individual soldier light-weight small-sized aerial survey unmanned aerial vehicle and an individual soldier light-weight small-sized aerial survey unmanned aerial vehicle system.
Background
Currently, in products for performing aerial survey operation by using unmanned aerial vehicles, the unmanned aerial vehicle is mainly a full-package type large unmanned aerial vehicle. The wheelbase of the unmanned aerial vehicle is more than 1 meter, a carbon fiber integrated forming technology is generally adopted, the upper machine body is made of carbon fiber, and electronic equipment is installed in the cabin; the power arm is connected with the machine body through a rotary flange; the lower part is provided with a nacelle; landing gear is typically split on both feet. In the aspect of communication, the unmanned aerial vehicle needs a notebook computer, a remote controller, an external data transmission and an external data transmission antenna (part) to carry out ground communication.
At present, the full-package type large unmanned aerial vehicle mainly has the following defects in the field of aerial survey operation:
1. heavy work during outgoing: the size of the machine body is overlarge, the general wheelbase is 1-2 meters, the large-size machine body is heavy in transportation, loading and unloading, large-sized aviation aluminum box packages are often needed, and at least 3 people can go out for operation;
2. the operation efficiency is low: because the flight speed of the large full-package unmanned aerial vehicle can only be kept at about 5m/s, the flight range is short and the operation efficiency is low under the condition of the same flight time;
3. complicated installation: the unmanned aerial vehicle is often not foldable and adopts a detachable storage mode, so that after the unmanned aerial vehicle is taken out from a package, complex installation work is needed to start operation, the process generally needs 2-3 persons, the time is about 15 minutes, and when the unmanned aerial vehicle needs to be transferred in the task process, the unmanned aerial vehicle still needs to be detached again, and the user experience is extremely poor;
4. the communication system is complex: in the flying process of the unmanned aerial vehicle, a ground notebook computer, a remote controller, an external data transmission module and an antenna are often required to communicate with an airplane, the system is extremely complex to operate, 2-3 persons are required to cooperate to complete monitoring and communication, the notebook computer is used for communication, and the influence of the problems of poor compatibility, poor cruising performance and the like of the notebook computer is also received, so that the aerial survey operation is greatly influenced;
5. short endurance: although the unmanned aerial vehicle can carry a large-capacity battery, the weight of the unmanned aerial vehicle is large, so that the flight time is greatly influenced, and the flight time is generally about 30 minutes;
6. expensive maintenance: such unmanned aerial vehicle is because integrated into one piece, in case any damage appears, all need change, lead to after-sale cost of maintenance high, after-sale cycle is for a long time.
Disclosure of Invention
Therefore, the individual light and small aerial survey unmanned aerial vehicle and the individual light and small aerial survey unmanned aerial vehicle system are needed to be provided, and the technical problems that the existing aerial survey unmanned aerial vehicle is large in size, heavy in weight, needs multiple persons to operate in a matching mode and low in working efficiency are solved.
In order to achieve the above purpose, the inventor provides a light and small-sized aerial survey unmanned aerial vehicle for individual soldiers, which comprises a main body, a power arm assembly, a power assembly, a heat dissipation assembly and a quick-dismantling mounting structure;
the machine body comprises a central circuit board, an upper cover plate, a lower cover plate and a side plate assembly, wherein the side plate assembly is connected between the upper cover plate and the lower cover plate, and the upper cover plate, the lower cover plate and the side plate assembly enclose a cavity for accommodating the central circuit board;
the battery assembly is connected above the upper cover plate and is electrically connected with the central circuit board;
the power arm assembly comprises four power arms which are symmetrically connected to the main body of the machine body; the power arm is electrically connected with the central circuit board
The quick-release mounting structure is connected to the bottom of the lower cover plate and is used for carrying an aerial survey camera.
The heat radiation assembly comprises an air inlet and a heat radiation fan, the air inlet is arranged on the main body of the machine body, and the heat radiation fan is arranged at the tail part of the main body of the machine body.
As a preferable structure of the invention, the side plate assembly comprises 2 front side plates, 2 middle side plates, 2 rear side plates, 1 machine head side plate and 1 machine tail side plate, wherein the upper cover plate and the lower cover plate are diamond-shaped, the machine head side plate is trapezoidal and is clamped on the front side of the machine body, the machine tail side plate is clamped on the rear side of the machine body, and the 2 front side plates, the 2 middle side plates and the 2 rear side plates are clamped on two sides of the machine body.
As a preferable structure of the present invention, the air inlet is provided on the front side plate, the middle side plate and the rear side plate, and the heat radiation fan is mounted on the tail side plate.
As an optimized structure of the invention, the individual light and small aerial survey unmanned aerial vehicle further comprises a battery cover and a bolt, wherein the battery cover is connected to the upper cover plate, a front clamping position is arranged on the front side of the bottom of the battery cover, a rear clamping position is arranged on the rear side of the bottom of the battery cover, step screws are arranged on the upper cover plate, the front clamping position and the rear clamping position are matched with the step screws, bolt holes are formed in the battery cover and the upper cover plate, and the bolt is matched with the bolt holes of the bolt holes in the battery cover and the upper cover plate.
As a preferable structure of the invention, the power arm comprises a folding piece, a propeller, a motor, a landing gear and a horn, wherein the power arm is connected to the main body of the machine body through the folding piece, the motor is connected with the horn, the propeller is in transmission connection with the motor, and the landing gear is connected to the bottom of the horn.
As an optimized structure, the individual light and small aerial survey unmanned aerial vehicle further comprises an obstacle avoidance and FPV system, wherein the obstacle avoidance and FPV system is integrated on the front side of the central circuit board, an obstacle avoidance sensor of the obstacle avoidance and FPV system is arranged on the front part of the technical main body, and a camera of the obstacle avoidance and FPV system is arranged on the front side of the bottom of the lower cover plate of the body.
As an optimized structure of the invention, the individual light and small aerial survey unmanned aerial vehicle further comprises a GPS and PPK system, wherein the GPS and PPK system comprises a GPS support, a GPS and magnetic compass module, a PPK support, a PPK circuit board and a PPK antenna, the GPS support and the PPK support are respectively connected with two sides of the middle part of the upper cover plate, the GPS and magnetic compass module is connected with the GPS support, and the PPK circuit board is connected with the PPK support. The PPK antenna is connected to the PPK circuit board.
As an optimized structure of the invention, the quick-dismantling mounting structure is a quick-dismantling screw hole formed in the bottom of the lower cover plate, and the quick-dismantling screw hole is connected with the quick-dismantling plate through a short aluminum column.
In prior art, above-mentioned technical scheme a light small-size aerial survey unmanned aerial vehicle of individual soldier, the fuselage main part is formed by upper cover plate, lower apron and curb plate subassembly concatenation, and convenient dismantlement is installed on the central circuit board in upper cover plate, lower apron and curb plate subassembly enclose into a cavity that is used for holding the central circuit board, and power supply module then installs in upper cover plate top for whole aerial survey unmanned aerial vehicle structure is inseparable, through a large amount of structural optimization and high integration, reduces unmanned aerial vehicle's size and wheelbase, no matter pack, during transportation or actual operation, all can be accomplished by alone, convenience and flexibility when improving the use greatly. In the flight process, air flow can be compressed and enter the air inlet, cold air enters the inside of the machine body to cool, and the fan hot air fan discharges the hot air flow in the machine body from the rear to the unmanned aerial vehicle, so that the aim of heat dissipation is achieved. The problem that equipment is temporarily caused by overhigh temperature due to high integration of the central circuit board is effectively avoided.
The utility model provides a light small-size aerial survey unmanned aerial vehicle system of individual soldier, includes ground station system and foretell light small-size aerial survey unmanned aerial vehicle of individual soldier, ground station system and the light small-size aerial survey unmanned aerial vehicle communication connection of individual soldier.
As a preferred structure of the present invention, the ground station system includes a housing, a panel, a handle, an antenna, and an extended backpack, the panel, the handle, the antenna, and the extended backpack being integrated on the housing.
Compared with the prior art, the technical scheme provides the light and small aerial survey unmanned aerial vehicle system for the individual soldiers, and complicated actions of preparing a notebook computer, connecting a ground transceiver module, arranging an antenna and the like by a user are avoided through the highly integrated ground station system, so that the system is convenient to take and use, and the usability is greatly improved.
Drawings
FIG. 1 is a three-dimensional view of an individual light and small aerial survey unmanned aerial vehicle according to an embodiment when two power arms are retracted;
FIG. 2 is a top view of an individual light and small aerial survey unmanned aerial vehicle according to an embodiment when two power arms are retracted;
FIG. 3 is a front view of an individual light and small aerial survey unmanned aerial vehicle according to an embodiment when two power arms are stowed;
fig. 4 is a three-dimensional view of a fuselage body of the individual soldier light and small aerial survey unmanned aerial vehicle according to the embodiment;
FIG. 5 is a rear view of a fuselage body of an individual soldier light and small aerial survey unmanned aerial vehicle according to an embodiment;
fig. 6 is a schematic diagram of a power arm structure of an individual light and small aerial unmanned aerial vehicle according to an embodiment;
fig. 7 is a front view of the individual light small aerial survey unmanned aerial vehicle according to the embodiment when the quick-release mounting structure is a stability augmentation plate;
FIG. 8 is a front view of the individual light and small aerial survey unmanned aerial vehicle according to the embodiment when the quick release mounting structure is a hard hanging plate;
FIG. 9 is a three-dimensional view of a battery cover of the individual soldier light and small aerial survey unmanned aerial vehicle according to the embodiment;
FIG. 10 is a top view of a battery cover of the individual soldier light and small aerial survey unmanned aerial vehicle according to the embodiment;
FIG. 11 is a distribution view of a heat dissipation system of an individual light and small aerial unmanned aerial vehicle on a side plate assembly according to an embodiment;
FIG. 12 is a three-dimensional view of a ground station system of the individual soldier light and small aerial survey unmanned aerial vehicle system of the present embodiment;
FIG. 13 is a front view of a ground station system of the individual soldier light and small aerial survey unmanned aerial vehicle system of the present embodiment;
FIG. 14 is a top view of a ground station system of the individual soldier light and small aerial survey unmanned aerial vehicle system of the present embodiment;
fig. 15 is a rear view of a ground station system of the individual soldier light and small aerial survey unmanned aerial vehicle system of the present embodiment.
Reference numerals illustrate:
10. a main body of the main body;
11. an upper cover plate; 12. a lower cover plate; 131. a nose side plate; 132. a front side plate; 133. a middle side plate; 134. a rear side plate; 135. a tail side plate;
31. a folding member; 32. a propeller; 33. a motor; 34. landing gear; 35. a horn;
41. an obstacle avoidance sensor; 42. an FPV camera;
51. a PPK scaffold; 52. a PPK circuit board; 53. a PPK antenna; 54. a GPS bracket; 55. a GPS and magnetic compass module;
61. a stability augmentation plate; 62. a hard hanging plate; 63. a camera; 64. short aluminum columns; 65. a long aluminum column;
71. a heat radiation fan; 72. an air inlet;
81. a battery cover; 811. front clamping position; 812. back clamping; 813. a bolt hole;
91. a housing; 911. a charging port; 912. a USB data port; 913. charging indicator lights, 92, panels; 921. a rocker; 922. a button switch; 923. a power switch; 924. a photographing button; 925. a bracket; 926. a power indicator light; 93. a handle; 931. a handle bracket; 94. a tablet or a cell phone; 95. expanding a knapsack; 96. an antenna.
Detailed Description
In order to describe the technical content, constructional features, achieved objects and effects of the technical solution in detail, the following description is made in connection with the specific embodiments in conjunction with the accompanying drawings.
In the description of the present application, the terms "first," "second," and "second," are used for descriptive purposes only and are not to be construed as indicating or implying relative importance unless explicitly specified and defined otherwise; the term "plurality" means two or more, unless specified or indicated otherwise; the terms "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, integrally connected, or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the description of the present specification, it should be understood that the terms "upper," "lower," "left," "right," and the like in the embodiments of the present application are described in terms of angles shown in the drawings, and should not be construed as limiting the embodiments of the present application. In the context of this document, it will also be understood that when an element is referred to as being "on" or "under" another element, it can be directly on the other element or be indirectly on the other element through intervening elements.
Referring to fig. 1 to 12, the present embodiment relates to a light and small-sized individual unmanned aerial vehicle, as shown in fig. 1 to 3, comprising a main body 10, a central circuit board, a power arm assembly, a power assembly, an obstacle avoidance and FPV system, a GPS and PPK system, and a quick-release mounting structure.
As shown in fig. 4 and 5, the body main body 10 includes an upper cover plate 11, a lower cover plate 12, and a side plate assembly connected between the upper cover plate 11 and the lower cover plate 12, the upper cover plate 11, the lower cover plate 12, and the side plate assembly enclosing a cavity for accommodating a central circuit board; the central circuit board is connected in a cavity enclosed by the upper cover plate 11, the lower cover plate 12 and the side plate assembly, and the obstacle avoidance and FPV system and the GPS and PPK system are integrated on the central circuit board; the battery assembly is connected above the upper cover plate 11 and is electrically connected with the central circuit board; the power arm assembly comprises four power arms which are symmetrically connected to the main body 10; the power arm is connected with the center circuit board electricity, and quick detach mount structure connects in the lower apron 12 bottom, and quick detach mount structure is used for carrying aerial survey camera 64.
The main body 10 structure of the fuselage is mainly stressed and installed in the unmanned aerial vehicle, and the whole main body is in a diamond streamline structure, so that wind resistance can be effectively reduced, space is saved, and in the main body 10 structure, through quick installation, the folding structure, the power arm and landing gear 34 structure, the battery cover 81 structure, the heat dissipation system, the obstacle avoidance and FPV system, the GPS and PPK system and the quick-release mounting structure of the unmanned aerial vehicle can be integrated on the main body structure, so that the structural strength is greatly improved, and the weight is reduced. The main body 10 mainly comprises 1 upper cover plate 11, 1 lower cover plate 12, 1 central circuit board, 2 front side plates 132, 2 middle side plates 133, 2 rear side plates 134, 1 nose side plate 131, 1 tail side plate 135, and is connected with the clamping groove by screws.
Upper fuselage cover 11: the solar cell is made of carbon fiber plates, the number of the solar cell is 1, the solar cell is in the uppermost part of the whole, the nose is pointed, the tail is blunt, and the upper cover plate 11 is integrated with a GPS/PPK system installation position, a cell cover 81 structure installation position, a power arm installation position, a folding structure installation position and a barrier avoiding system installation position, and is also a cell installation position.
Lower fuselage cover 12: for carbon fiber plate material, quantity is 1, is whole bottommost, and diamond shape, aircraft nose position is more sharp, and the tail position is duller, has integrated folding structure installation position, power arm installation position, obstacle avoidance system installation position, picture transmission system installation position, quick detach mount structure installation position at lower apron 12 to when newly adding other structures, can directly provide the structure installation position at lower apron 12 newly added hole site.
A central circuit board: the electronic circuit is a PCB circuit board, the number of the electronic circuit boards is 1, and in the middle of the whole electronic circuit board, electronic modules such as flight control, GPS, PPK, power supply, 4G communication, data transmission and image transmission are integrated, so that the electronic circuit board is an electronic circuit center of an unmanned aerial vehicle. The design is in the middle part of the fuselage and highly integrated, so that the space can be effectively saved, and the stability is improved.
Front side plate 132: is made of carbon fiber material, has 2 blocks in number, is rectangular in shape and is provided with heat dissipation ventilation holes on two sides of the whole front. The 2 front side plates 132 are arranged in a triangle shape, so that the resistance can be reduced in the flying process.
Middle side plate 133: the carbon fiber composite material is made of carbon fiber materials, the number of the carbon fiber composite material is 2, and the carbon fiber composite material is arranged in a rectangular shape and is bilaterally symmetrical on two sides of the middle of the whole body.
Rear side plate 134: is made of carbon fiber material, has 2 blocks in number, is in a rectangular shape and is provided with heat dissipation ventilation holes at the rear of the whole body. The 2 rear side plates 134 are arranged in an inverted triangle, so that the wind resistance coefficient of the aircraft is kept small even when the aircraft flies upside down.
Head side plate: the integrated sensor is made of carbon fiber materials, the number of the integrated sensor is 1, and the integrated sensor is in a trapezoid shape at the forefront of the whole body, and is provided with integrated hole sites, integrated cameras, ultrasonic sensors and other sensors.
Rear side plate 134: the heat dissipation fans 71 are integrated in a carbon fiber material, 1 block in number, in a rectangular shape at the forefront of the whole.
The upper cover plate 11 and the lower cover plate 12 are connected with screws through aluminum columns, 1 central circuit board, 2 front side plates 132, 2 middle side plates 133 and 2 rear side plates 134 are formed, and 1 machine head side plate 131 and 1 machine tail side plate 135 are connected with the upper cover plate 12 and the lower cover plate 12 through clamping grooves.
For small unmanned aerial vehicle, collapsible design can promote the use convenience greatly. The folding structure is arranged on the right front arm 35 and the left rear arm 35, and the machine body is minimized by folding down by 90 degrees, and the folding structure can be rapidly arranged in a short time and is simple to operate. Through folding, unmanned aerial vehicle changes rectangular shape into, can make unmanned aerial vehicle organism reduce greatly, convenient transportation and installation.
The unmanned aerial vehicle of this embodiment adopts "X" shape power arm design, and the atress is the most even, and structural strength is the biggest. As shown in fig. 6, the power arm and landing gear 34 structure is composed of a folding member 31, a propeller 2, a motor 34, a landing gear 34 and a horn 35.
Folding member 31: the number of the folding machine is 4, and the folding machine is formed by CNC processing of aluminum alloy and is used for connecting a power arm with the machine body 10 and realizing a folding function.
Propeller 2: and 4, which are integrally formed and processed by carbon fibers, and are used for providing lifting force and are connected with the motor 34 through quick-release pieces.
Motor 34: 4, the function is to provide unmanned power, and is connected with the horn 35 and the propeller 2.
Arm 35: the number of the carbon tubes is 4, and the carbon tubes are arranged in an X-shaped cross manner and are used for transmitting power.
Landing gear 34: the number of the unmanned aerial vehicle is 4, and the unmanned aerial vehicle is formed and processed by carbon fiber integrally, and the unmanned aerial vehicle is used for supporting the unmanned aerial vehicle, and is connected with the horn 35 and the motor 34 through long bolts to form a whole. Compared with the cross landing gear 34, the design has high structural strength and does not shade the mounting.
As shown in fig. 1 to 3, the obstacle avoidance and FPV system is integrated at the unmanned aerial vehicle head position, wherein an obstacle avoidance sensor 41 (a vision camera, ultrasonic waves, millimeter wave radar, etc.) is mounted at the fuselage head, and the probe portion protrudes through the hole of the nose side plate 131; the FPV camera 42 is mounted near the nose of the lower fuselage cover 12 to provide real-time image return and adjustable camera angle. The optical pod can also be suspended here to realize the monitoring function.
As shown in fig. 1-3, the GPS/PPK system is an aircraft navigation, positioning, pointing system. On the whole, GPS and PPK distribute in the middle both sides of fuselage, and the left side is PPK, and the right side is GPS, has both saved the space, guarantees the signal mutually noninterfere again. The GPS and magnetic compass device comprises a GPS bracket 54, a GPS and magnetic compass module 55, a PPK bracket 51, a PPK circuit board 52 and a PPK antenna 53.
GPS stand 54: the GPS bracket 54 is formed by CNC processing of aluminum alloy, adopts the structure of a cylinder and a metal tray, the lower part is connected with the upper cover plate 11 of the machine body through screws, and the upper part is a circular platform, so that other modules are conveniently arranged.
GPS and magnetic compass module 55: this is unmanned aerial vehicle core sensor, with GPS receiver and magnetism compass integration as an organic whole, places on GPS support 54, can firmly fix, guarantees not influenced when aircraft wide-angle motion.
PPK holder 51: the PPK support 51 is formed by CNC (computer numerical control) processing of aluminum alloy, adopts the structure of a cylinder and a metal tray, is connected with the upper cover plate 11 of the machine body through screws at the lower part, and is a circular platform at the upper part, so that the installation and maintenance are convenient, the distance between a PPK module and an antenna can be greatly reduced, and the signal superiority of the PPK module is ensured.
PPK circuit board 52: which is firmly fixed to the PPK bracket 51 by screws, providing high-precision positioning information.
PPK antenna 53: connected to the PPK circuit board 52 by a screw for receiving signals.
The quick-dismantling mounting structure is divided into a stability augmentation plate 61 and a hard hanging plate 62.
As shown in fig. 7, the stability augmentation plate 61: the lower cover plate 12 of the machine body is provided with 4 screw holes, and 4 short aluminum columns 64 are connected through the screw holes to form 4 quick-release screw holes. The stability augmentation cradle head is connected through the 4 screw holes, namely, the installation is realized, and different cameras 64 can be mounted below the stability augmentation cradle head to realize different operation tasks.
The hard hanging plate 62 is shown in fig. 8: the lower cover plate 12 of the machine body is provided with 4 screw hole sites, 4 long aluminum columns 65 are connected through the screw hole sites, a mounting plate is arranged below the long aluminum columns 65, and different cameras 64 can be arranged above the mounting plate to realize different operation tasks. Different onboard cameras 64 are adapted by selectively mounting the stability augmentation plate 61 or the hard hanging plate 62.
The light and small-size aerial survey unmanned aerial vehicle of individual soldier of above-mentioned embodiment, fuselage main part 10 is formed by upper cover plate 11, lower apron 12 and curb plate subassembly concatenation, conveniently dismantle, keep away barrier and FPV system, GPS and PPK system integration are on central circuit board, install on the central circuit board in upper cover plate 11, lower apron 12 and curb plate subassembly enclose into a cavity that is used for holding central circuit board, power supply unit then installs in upper cover plate 11 top for whole aerial survey unmanned aerial vehicle is compact structure, through a large amount of structural optimization and high integration, reduce unmanned aerial vehicle's size and wheelbase, no matter pack, during transportation or actual operation, all can be accomplished by alone, convenience and flexibility when improving the use greatly.
Further, as shown in fig. 9 and 10, the individual light and small aerial survey unmanned aerial vehicle further comprises a battery cover 81 and a bolt, the battery cover 81 is streamline, the battery cover 81 is connected to the upper cover plate 11, a front clamping position 811 is arranged on the front side of the bottom of the battery cover 81, a rear clamping position 812 is arranged on the rear side of the bottom of the battery cover 81, a step screw is arranged on the upper cover plate 11, the front clamping position 811 and the rear clamping position 812 are matched with the step screw, a bolt hole 813 is arranged on the battery cover 81 and the upper cover plate 11, and the bolt is matched with the bolt hole 813 of the bolt hole 813 on the battery cover 81 and the upper cover plate 11.
The battery cover 81 is the most obvious appearance and structural member of the aircraft and is integrally formed by glass fiber or carbon fiber, and is used for covering the unmanned aerial vehicle battery and reducing resistance. The whole body is streamline and is perfectly matched with the upper cover plate 11. The bottom of the upper cover plate 11 is provided with a front clamping position 811 and a rear clamping position 812 which are connected and positioned by being matched with a step screw on the upper cover plate, and a bolt is used for preventing the upper cover plate from being separated. When the battery cover 81 is installed, the battery cover is only required to be attached to the upper cover plate 11 and slide from front to back until the bolt is completely buckled into the bolt hole 813; when the bolt is separated, the bolt is pulled downwards, and the bolt is pushed forwards from back to front, so that the bolt can be separated, and the bolt is convenient to assemble and disassemble.
Further, the design of the product is very critical due to the high integration of the heat dissipation system. The heat dissipation system mainly comprises an air inlet 72 and a heat dissipation fan 71. As shown in fig. 11:
air inlet 72: the air inlets 72 are distributed on the front side plate 132, the middle side plate and the rear side plate 134, in the flying process, air flow can be compressed to enter the air inlets 72, and cold air enters the inside of the machine body to cool and then is discharged, so that the purpose of heat dissipation is achieved.
A heat radiation fan 71: is mounted on the tail side plate 135 to discharge the hot air flow inside the unmanned aerial vehicle from the rear.
In other embodiments, an individual light and small aerial survey unmanned aerial vehicle system is involved, including ground station system and the aforesaid individual light and small aerial survey unmanned aerial vehicle, ground station system and individual light and small aerial survey unmanned aerial vehicle communication connection.
As shown in fig. 12 to 15, the ground station system includes a housing 91, a panel 92, a rocker 921, a knob switch 922, a handle bracket 931, a handle 93, a tablet or cellular 94 bracket 925, an antenna 96, a power switch 923, a photographing button 924, a power indicator 926, a USB data port 912, a charge indicator 913, a charge port 911, and an extended backpack 95, and the panel 92, the rocker 921, the knob switch 922, the handle bracket 931, the handle 93, the tablet or cellular 94 bracket 925, the antenna 96, the power switch 923, the photographing button 924, the power indicator 926, the USB data port 912, the charge indicator 913, the charge port 911, and the extended backpack 95 are integrated on the housing 91.
The ground station system is important equipment at the ground end of the unmanned aerial vehicle, bears key tasks such as monitoring information, remotely controlling the unmanned aerial vehicle, sending instructions and the like, and integrates functions such as a remote controller, data transmission, image transmission, ground station planning and the like. The multifunctional backpack mainly comprises a shell 91, a panel 92, a rocker 921, a button switch 922, a handle bracket 931, a handle 93, a tablet/mobile phone bracket 925, a tablet/mobile phone, an antenna 96, a power switch 923, a photographing button 924, a power indicator 926, a USB data port 912, a charging indicator 913, a charging port 911 and an expanding backpack 95.
The shell 91 is formed and processed by aluminum alloy CNC integrally, and has high structural strength and can resist general dropping. Which is the main body of the overall ground station system, inside which the electronic modules are placed.
Panel 92 is divided into carbon fiber plate material and aluminum alloy material, which are inlaid above the shell 91 and fixed by four corner screws.
The number of the rocking bars 921 is 2, the rocking bars 921 are arranged on the shell 91 in a left-right mode through screws and extend out through the panel 92, and the function of the rocking bars is to control the movement of the unmanned aerial vehicle.
A button switch 922: the number of the rockers 921 is 2, the rockers are mounted on the shell 91 left and right through screws and extend out through the panel 92, and the rockers are used for controlling the unmanned aerial vehicle to fly in a mode and return.
Handle support 931: the aluminum alloy CNC is integrally formed and processed, the number is 2, the left and right sides are mounted on the back surface of the shell 91 through screws, and the aluminum alloy CNC is used for mounting the handles 93.
Handle 93: is made of carbon fiber and is installed by embedding handle supports 931 on two sides.
Tablet/cell phone stand 925: is an aluminum alloy CNC integrally formed and is mounted on the housing 91 by screws and extends through the panel 92 for the purpose of securing the tablet/phone and for angular adjustment.
Tablet/cell phone: and installing the APP on the unmanned aerial vehicle, so as to realize unmanned aerial vehicle operation. Which is mounted on the tablet/phone holder 925 and secured by a flat clip.
Antenna 96: the number is 2, and the signal is more sensitive by being distributed left and right, and the signal is mounted on the shell 91 through the screw head.
Power switch 923: which is mounted on the panel 92 and functions to turn on/off the ground station power supply.
Photographing button 924: which is mounted on the panel 92 and functions to trigger photographing.
Power indicator 926: which is mounted on the panel 92, indicates ground station power by 4 indicator lights.
USB data port 912: mounted above the housing 91 and operative to transmit data via USB.
Charging indicator lamp 913: mounted above the housing 91, and functions to indicate a state when charged.
Charging port 911: mounted above the housing 91 and operative to use the DC header for ground station charging.
Expanding backpack 95: the aluminum alloy CNC integrated into one piece is processed, installs at the casing 91 back, and its effect is when the ground station needs to extend the function, can provide the space.
Through the highly integrated ground station system, the complex actions of preparing a notebook computer, connecting a ground transceiver module, arranging an antenna and the like by a user are avoided, the use-and-play is realized, and the usability is greatly improved.
The invention has the main beneficial effects as follows:
1. can realize the individual operation: through a large amount of structural optimization and high integration, the size of the unmanned aerial vehicle is 700mm in wheelbase, and the unmanned aerial vehicle is one of the lightest products in the current long-endurance high-precision aerial survey unmanned aerial vehicle. On this basis, no matter in packing, transportation or actual operation, can all be accomplished by alone, convenience and flexibility when improving the use greatly.
2. The operation efficiency is high: through advanced designs such as low-resistance machine head, streamline battery cover 81, overall light weight and high-strength machine body, the unmanned aerial vehicle can keep the navigation time of 60 minutes in a high-speed cruising state of 12m/s, the cruising mileage is broken through by 30 km, and compared with the traditional aerial survey unmanned aerial vehicle, the operation efficiency is improved by 5 times.
3. The installation is quick: according to the unmanned aerial vehicle, only two arms 35 are required to be folded, and only 30 seconds are required from the packaging to the task starting, so that the easiness of initial preparation is greatly improved, and the unmanned aerial vehicle has obvious advantages in situations such as task transition.
4. High ease of use: through the highly integrated ground station system, the complex actions of preparing a notebook computer, connecting a ground transceiver module, arranging an antenna and the like by a user are avoided, the use-and-play is realized, and the usability is greatly improved.
5. Stable and reliable: through the design of the X-shaped power arm, the integration of a large amount of structural reinforcement and an electronic circuit, the unmanned aerial vehicle can realize all-weather high-strength operation, and can still keep flight safety in severe environments such as strong wind.
6. After-sale maintenance is convenient: according to the unmanned aerial vehicle, the base materials are easy to obtain, and through the modularized design, once a problem occurs and replacement or maintenance is needed, only the module is needed to be replaced, so that the after-sale cost is greatly reduced.
7. The expanding function is rich: through quick detach mounting structure design, 4 limit dispersion type undercarriage 34 designs, can convenient and fast change the mount, and fuselage lower part space and field of vision are wide, can not produce undercarriage 34 and shelter from scheduling problem, realize "a tractor serves several purposes", greatly increased unmanned aerial vehicle's expansion function.
It should be noted that, although the foregoing embodiments have been described herein, the scope of the present invention is not limited thereby. Therefore, based on the innovative concepts of the present invention, alterations and modifications to the embodiments described herein, or equivalent structures or equivalent flow transformations made by the present description and drawings, apply the above technical solutions directly or indirectly to other relevant technical fields, all of which are included in the scope of protection of the present patent.
Claims (9)
1. An individual soldier's light small-size aerial survey unmanned aerial vehicle, its characterized in that: the power arm comprises a main body, a power arm assembly, a power assembly, a heat dissipation assembly and a quick-dismantling mounting structure;
the machine body comprises a central circuit board, an upper cover plate, a lower cover plate and a side plate assembly, wherein the side plate assembly is connected between the upper cover plate and the lower cover plate, and the upper cover plate, the lower cover plate and the side plate assembly enclose a cavity for accommodating the central circuit board;
the battery assembly is connected above the upper cover plate and is electrically connected with the central circuit board;
the power arm assembly comprises four power arms which are symmetrically connected to the main body of the machine body, and the power arms are electrically connected with the central circuit board;
the quick-release mounting structure is connected to the bottom of the lower cover plate and is used for carrying an aerial survey camera;
the heat radiation assembly comprises an air inlet and a heat radiation fan, the air inlet is arranged on the main body of the machine body, and the heat radiation fan is arranged at the tail part of the main body of the machine body;
the central circuit board is in the middle of the whole body, the central circuit board is in a diamond shape, the upper cover plate and the lower cover plate are in diamond shapes, and the side plate assembly is matched with the shapes of the upper cover plate and the lower cover plate;
the side plate assembly comprises two front side plates, two middle side plates, two rear side plates, a machine head side plate and a machine tail side plate;
the two front side plates are arranged in a triangle shape, and are provided with radiating air holes at two sides of the front of the whole body;
the two middle side plates are arranged symmetrically left and right at the two sides of the middle of the whole body;
the two rear side plates are arranged at the rear of the whole body and are provided with radiating air holes, and the two rear side plates are arranged in an inverted triangle;
one nose side plate is arranged at the forefront of the whole body, and is trapezoid-shaped and provided with an integrated hole site;
the tail side plate is arranged at the rearmost part of the whole body, is rectangular and integrates a cooling fan;
the air inlets are distributed on the front side plate, the middle side plate and the rear side plate, the cooling fans are arranged on the tail side plate, and hot air flow in the unmanned aerial vehicle is discharged out of the unmanned aerial vehicle from the rear;
the individual light and small aerial survey unmanned aerial vehicle further comprises a battery cover matched with the upper cover plate in shape, the battery cover is streamline, and the battery cover is connected to the upper cover plate.
2. The individual light and small aerial survey unmanned aerial vehicle of claim 1, wherein: the aircraft nose curb plate joint is in fuselage main part front side, the tail curb plate joint is in fuselage main part rear side, curb plate and 2 rear side plate joint are in fuselage main part both sides in 2 preceding curb plates, 2.
3. The individual light and small aerial survey unmanned aerial vehicle of claim 1, wherein: the light small aerial survey unmanned aerial vehicle of individual soldier still includes the bolt, battery cover bottom front side is equipped with preceding screens, battery cover bottom rear side is equipped with back screens, be equipped with step screw on the upper cover plate, preceding screens and back screens and step screw looks adaptation, be equipped with the bolt hole on battery cover and the upper cover plate, the bolt is with the bolt hole looks adaptation of bolt hole on battery cover and the upper cover plate.
4. The individual light and small aerial survey unmanned aerial vehicle of claim 1, wherein: the power arm comprises a folding piece, a propeller, a motor, a landing gear and a horn, wherein the power arm is connected to the main body of the machine body through the folding piece, the motor is connected with the horn, the propeller is connected with the motor in a transmission manner, and the landing gear is connected to the bottom of the horn.
5. The individual light and small aerial survey unmanned aerial vehicle of claim 1, wherein: the individual soldier light and small aerial survey unmanned aerial vehicle further comprises an obstacle avoidance and FPV system, the obstacle avoidance and FPV system is integrated on the front side of the central circuit board, an obstacle avoidance sensor of the obstacle avoidance and FPV system is arranged on the front portion of the technical main body, and a camera of the obstacle avoidance and FPV system is arranged on the front side of the bottom of the lower cover plate of the body.
6. The individual light and small aerial survey unmanned aerial vehicle of claim 1, wherein: the single-soldier light and small aerial survey unmanned aerial vehicle further comprises a GPS and PPK system, the GPS and PPK system comprises a GPS support, a GPS and magnetic compass module, a PPK support, a PPK circuit board and PPK antennas, the GPS support and the PPK support are respectively connected to two sides of the middle of the upper cover plate, the GPS and the magnetic compass module are connected to the GPS support, the PPK circuit board is connected to the PPK support, and the PPK antennas are connected to the PPK circuit board.
7. The individual light and small aerial survey unmanned aerial vehicle of claim 1, wherein: the quick detach mounting structure is the quick detach screw hole for increasing steady board, lower apron bottom is equipped with, increase steady board and connect on the quick detach screw hole through short aluminium post.
8. An individual soldier's light small-size aerial survey unmanned aerial vehicle system, its characterized in that: an individual light and small aerial survey drone comprising a ground station system and any one of claims 1 to 7, the ground station system being in communication connection with the individual light and small aerial survey drone.
9. The individual light and small aerial survey unmanned aerial vehicle system of claim 8, wherein: the ground station system comprises a shell, a panel, a handle, an antenna and an extended backpack, wherein the panel, the handle, the antenna and the extended backpack are integrated on the shell.
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