CN117141756B - Small-size many ducts unmanned aerial vehicle of quick deployment - Google Patents
Small-size many ducts unmanned aerial vehicle of quick deployment Download PDFInfo
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- CN117141756B CN117141756B CN202311435486.7A CN202311435486A CN117141756B CN 117141756 B CN117141756 B CN 117141756B CN 202311435486 A CN202311435486 A CN 202311435486A CN 117141756 B CN117141756 B CN 117141756B
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- 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 description 22
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 8
- 238000013461 design Methods 0.000 description 6
- 230000008901 benefit Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 230000000903 blocking effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 238000005192 partition Methods 0.000 description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
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Classifications
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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
- B64U10/13—Flying platforms
- B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/26—Ducted or shrouded rotors
Abstract
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a small multi-duct unmanned aerial vehicle capable of being deployed quickly. The technical proposal is as follows: the utility model provides a small-size many ducts unmanned aerial vehicle of quick deployment, includes the water conservancy diversion module, and the water conservancy diversion module is equipped with two at least ducts, installs the duct fan in the duct, is connected with the part assembly module on the water conservancy diversion module, and the part assembly module is connected in the region between the air outlet of a plurality of ducts on the water conservancy diversion module. The invention provides a small multi-duct unmanned aerial vehicle which is used for gun barrel mode emission and controls the gesture and heading of the unmanned aerial vehicle through the rotating speed of a motor.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a small multi-duct unmanned aerial vehicle capable of being deployed quickly.
Background
The ducted unmanned aerial vehicle is one of unmanned aerial vehicles, and due to the fact that the ducted design is adopted, the radius of the propeller inside the duct and the size of the whole ducted unmanned aerial vehicle are small, the ducted unmanned aerial vehicle is compact in structure, high in safety and low in pneumatic noise, the existing ducted unmanned aerial vehicle mainly adopts a single large-sized duct as a power source, takes off in a vertical take-off and landing mode, can carry various small sensors to achieve various functions, and has wide application prospects in the fields of civil use, military use, scientific research and the like.
Closest to the present application proposal: the first is a coaxial ducted unmanned aerial vehicle, and the second is a single-rotor ducted unmanned aerial vehicle.
The coaxial ducted unmanned aerial vehicle adopts a coaxial double-rotor structure to carry out gesture and course control, torque generated by rotation of the propellers is offset by adopting coaxial double-rotor constant-speed contra-rotation, two power systems are needed or the contra-rotation of the double-rotor is realized through a complex transmission mechanism, deflection of a machine body is realized through torque difference of the two rotors, and gesture and course control is completed. The coaxial double-rotor structure has the characteristics of compact structure and high power efficiency, so that the coaxial double-rotor structure has a wide application range. However, due to the unique layout and appearance of the ducted coaxial double-rotor unmanned aerial vehicle, the ducted coaxial double-rotor unmanned aerial vehicle has complex dynamics characteristics of high uncertainty, strong coupling and strong nonlinearity, and the difficulty of unmanned aerial vehicle flight dynamics modeling and flight control system design of a complete configuration is increased.
The single-rotor ducted unmanned aerial vehicle adopts a structure of a single rotor wing and an adjustable stable wing plate to control the gesture and the course, a plurality of fixed flow guide wing plates are arranged at the outlet of the tail part of the duct of the ducted unmanned aerial vehicle, the fixed flow guide wing plates are designed into a certain special wing shape or are arranged into a certain angle, and certain torque is generated when airflow passes through the flow guide wing plates so as to balance the reactive torque of the single rotor wing. Meanwhile, a group of controllable guide plates are arranged at the tail parts of the fixed guide wing plates, the guide plates are controlled in groups, and each group is provided with a steering engine drive for changing the direction of air flow so as to control the flight attitude and heading of the ducted unmanned aerial vehicle.
Disclosure of Invention
In order to solve the problems in the prior art, the invention aims to provide a small multi-duct unmanned aerial vehicle which is used for gun barrel type launching and controls the gesture and heading of the unmanned aerial vehicle through the rotating speed of a motor.
The technical scheme adopted by the invention is as follows:
the utility model provides a small-size many ducts unmanned aerial vehicle of quick deployment, includes the water conservancy diversion module, and the water conservancy diversion module is equipped with two at least ducts, installs the duct fan in the duct, is connected with the part assembly module on the water conservancy diversion module, and the part assembly module is connected in the region between the air outlet of a plurality of ducts on the water conservancy diversion module.
The ducted fan is directly connected with the diversion module, so that an unmanned aerial vehicle frame is omitted. The component assembly module is used for installing components such as batteries, flight controls, receivers, power management boards, GPS and the like. The component assembly module is connected to the flow guide module in the area between the air outlets of the ducts, the component assembly module is reasonably arranged, and the influence of the component assembly module on the ducts is avoided. The ducted fan, the flow guiding module and the component assembling module are compactly arranged, so that the unmanned aerial vehicle can be arranged in a gun barrel with limited space and can be launched in a gun barrel mode.
The invention comprises at least two ducted fans, and the gesture and the course of the unmanned aerial vehicle can be adjusted by controlling the rotating speeds of motors of a plurality of ducted fans. When the rotational speeds of the motors of the plurality of ducted fans are different, the lift force provided by each ducted fan is different, and the unmanned aerial vehicle can realize the adjustment of the gesture and the route. Compared with a mode that the single-rotor ducted unmanned aerial vehicle performs gesture control through the adjustable flow guide wing plates at the tail part of the duct, the gesture control mode is simpler.
As a preferable mode of the present invention, in a direction from top to bottom, the plurality of ducts are curved in a direction away from each other, and an air outlet area of the duct is equal to an air inlet area of the duct. The plurality of ducts are bent towards the direction deviating from each other, so that the area of the area between the air outlets of the plurality of ducts on the flow guiding module is increased, the component assembly module is convenient to arrange, and the blocking of the component assembly module to the air outlets of the ducts is avoided. The air outlet area of the duct is equal to the air inlet area of the duct, so that air is ensured not to be compressed and expanded in the flow guiding module.
The ducts are bent in the direction away from each other, and air enters the bent duct after passing through the duct fan and is sprayed out obliquely downwards through the air outlet of the duct. When air passes through the air outlet of the duct, the air-assisted unmanned aerial vehicle can provide upward lifting force and lateral force. When the unmanned aerial vehicle stably hovers, four lateral forces can offset each other. When the posture or heading adjustment is required, the component of the lateral force in the horizontal direction assists the posture and heading adjustment, so that the deflection force required to be provided by changing the rotation speed of the motor is reduced.
As the preferable scheme of the invention, the air outlet of the duct is flat, and the size of the lower end of the diversion module is further contracted, so that the unmanned aerial vehicle can be smoothly installed in the gun barrel. And when the air outlet of the duct is flat, the area of the air outlet of the duct is ensured to be the same as the area of the air inlet of the duct.
As a preferable scheme of the invention, the circumference surface of the ducted fan is provided with a fixed block, the diversion module is provided with a fixed groove, and the fixed block is clamped in the fixed groove. The fixed block on the duct fan is arranged in the fixed groove of the flow guiding module, so that the condition that the duct fan rotates can not occur when the motor rotates is ensured.
As a preferable scheme of the invention, the flow guide module is connected with a fixed plate, a channel hole is arranged on the fixed plate, the ducted fan penetrates through the channel hole, and the fixed plate limits the upper side of the fixed block. After the ducted fan is installed in the duct, the fixing plate and the flow guide module are installed, and the fixing plate can limit the fixing block to prevent the ducted fan from moving up and down.
As a preferred embodiment of the invention, the lower section of the component assembly module is shrunk inwards in the top-to-bottom direction. The air can present the diffusion state after flowing out from the air outlet of duct, and the part assembly module of lower section shrink can reduce the influence to the air current, guarantees lift to the maximum extent. The shrinkage size is unmanned aerial vehicle's battery can vertically place in the bottom central authorities of part assembly module just, both guarantees unmanned aerial vehicle's balance, also can guarantee space utilization's rationality.
As a preferable scheme of the invention, a battery, a power management board, a GPS, a flight control and a receiver are arranged in the component assembly module, a motor of the ducted fan is electrically connected with an electric regulator, the electric regulator and the flight control are both electrically connected with the power management board, the GPS and the receiver are both electrically connected with the flight control, and the power management board is electrically connected with the battery.
As a preferable scheme of the invention, a plurality of layers of diaphragm plates are arranged in the component assembly module, a battery is arranged at the lower side of the lowermost diaphragm plate, a flight control and a receiver are arranged on the lowermost diaphragm plate, a power management plate and a GPS (global positioning system) are arranged on the second layer of diaphragm plate from bottom to top, and holes for wiring to pass through are formed in the diaphragm plates. The partition plate can be used for conveniently installing all the components, and the components are reasonably arranged in the component assembly module.
As a preferable scheme of the invention, one side of the component assembly module is provided with a sliding plate, the sliding plate is provided with an antenna port and a lead port, an antenna of the receiver extends out of the antenna port, and a wiring of the power management board and a wiring of the battery are respectively connected after extending out of the lead port. The antenna of the receiver extends out of the antenna port, so that the receiver can be ensured to successfully receive the signal of the remote controller. The wiring of the power management board and the wiring of the battery are respectively connected after extending out of the leading-out port, so that the battery can be conveniently plugged and unplugged, and a switch is arranged or charged.
As a preferable scheme of the invention, the flow guide module is provided with wiring holes, the wiring holes are positioned among the plurality of ducts, and wiring of a motor of the duct fan passes through the wiring holes. The wiring of the motor of the duct fan is arranged to the wiring hole, so that the wiring of the motor is prevented from being arranged in disorder or affecting the duct.
The beneficial effects of the invention are as follows:
1. the ducted fan is directly connected with the diversion module, so that an unmanned aerial vehicle frame is omitted. The component assembly module is used for installing components such as batteries, flight controls, receivers, power management boards, GPS and the like. The component assembly module is connected to the flow guide module in the area between the air outlets of the ducts, the component assembly module is reasonably arranged, and the influence of the component assembly module on the ducts is avoided. The ducted fan, the flow guiding module and the component assembling module are compactly arranged, so that the unmanned aerial vehicle can be arranged in a gun barrel with limited space and can be launched in a gun barrel mode.
2. The invention comprises at least two ducted fans, and the gesture and the course of the unmanned aerial vehicle can be adjusted by controlling the rotating speeds of motors of a plurality of ducted fans. When the rotational speeds of the motors of the plurality of ducted fans are different, the lift force provided by each ducted fan is different, and the unmanned aerial vehicle can realize the adjustment of the gesture and the route. Compared with a mode that the single-rotor ducted unmanned aerial vehicle performs gesture control through the adjustable flow guide wing plates at the tail part of the duct, the gesture control mode is simpler.
3. The ducts are bent in the direction away from each other, and air enters the bent duct after passing through the duct fan and is sprayed out obliquely downwards through the air outlet of the duct. When air passes through the air outlet of the duct, the air-assisted unmanned aerial vehicle can provide upward lifting force and lateral force. When the gesture or the course is required to be adjusted, the component of the lateral force in the horizontal direction can assist in adjusting the gesture and the course, so that the deflection force required to be provided by changing the rotating speed of the motor is reduced, and the unmanned aerial vehicle is more convenient to control.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is an exploded view of the present invention;
FIG. 3 is a schematic view of a first direction of the flow guiding module;
FIG. 4 is a schematic view of a second direction of the flow guiding module;
FIG. 5 is a front view of a single duct;
FIG. 6 is a bottom view of a single duct;
FIG. 7 is a schematic diagram of a ducted fan;
FIG. 8 is a schematic structural view of a fixing plate;
FIG. 9 is an exploded view of the component assembly module;
fig. 10 is a partial structural view of the component mounting module.
In the figure: 1-a diversion module; 2-ducted fans; 3-part assembly module; 4-a fixing plate; 5-battery; 6-flight control; 11-duct; 12-an air inlet; 13-an air outlet; 14-a fixed groove; 15-wiring holes; 21-a fixed block; 31-connecting blocks; 32-diaphragm plates; 33-mounting slots; 34-a sliding groove; 35-a sliding plate; 41-a channel hole; 42-a primary and secondary screw; 351-antenna ports; 352-lead wire port.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention. It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other.
Aiming at the existing single-duct unmanned aerial vehicle with a complex structure, the invention designs the multi-duct unmanned aerial vehicle which has a simple structure and adopts a gun barrel mode for emission, so that the unmanned aerial vehicle has the advantage of rapid deployment in an emergency, and meanwhile, the problems of short shaft distance, small carrying capacity and the like of the unmanned aerial vehicle are solved through the designed flow guide module 1, so that the unmanned aerial vehicle can have good control capacity and loading capacity.
As shown in fig. 1 and 2, the fast-deployment small multi-duct unmanned aerial vehicle of the present embodiment includes a flow guiding module 1, the flow guiding module 1 is provided with at least two ducts 11, a duct fan 2 is installed in the duct 11, a component assembling module 3 is connected to the flow guiding module 1, and the component assembling module 3 is connected to an area between air outlets 13 of the plurality of ducts 11 on the flow guiding module 1.
The unmanned aerial vehicle adopts the gun barrel mode to launch, so the shape of the unmanned aerial vehicle needs to be adapted to the slender shape of the gun barrel, and the diameter of the common gun barrel is not very large, so the whole diameter of the unmanned aerial vehicle is designed to be 220mm. The unmanned plane adopts a four-rotor layout, and four ducted fans 2 with central symmetry are needed. Considering the overall weight of the unmanned aerial vehicle, a ducted fan 2 with a diameter of 73mm was used. While four ducted fans 2 with the diameter of 220mm are installed on the unmanned aerial vehicle, the wheelbase between each ducted fan 2 becomes short, which is unfavorable for the control of the unmanned aerial vehicle, and components such as a battery 5, a flight control 6, a receiver, a GPS and the like are also required to be installed below the ducted fans 2. In order to solve the problem, the invention designs a diversion module 1, which can provide an assembly space for the lower part and can provide power required by flight. To simplify the design, the unmanned frame is eliminated and the ducted fan 2 is directly fixed to the diversion module 1.
The ducted fan 2 is directly connected with the diversion module 1, and an unmanned aerial vehicle frame is omitted. The component mounting module 3 is used to mount components of a battery 5, a flight control 6, a receiver, a power management board, GPS, etc. The component assembly module 3 is connected to the flow guiding module 1 in the area between the air outlets 13 of the plurality of ducts 11, the component assembly module 3 is reasonably arranged, and the influence of the component assembly module 3 on the ducts 11 is avoided. The ducted fan 2, the flow guiding module 1 and the component assembling module 3 are compactly arranged, so that the unmanned aerial vehicle can be installed in a gun barrel with limited space and can be launched in a gun barrel mode.
The invention comprises at least two ducted fans 2, and the gesture and heading of the unmanned aerial vehicle can be adjusted by controlling the rotating speeds of motors of a plurality of ducted fans 2. When the rotational speeds of the motors of the plurality of ducted fans 2 are different, the lift force provided by each ducted fan 2 is different, and the unmanned aerial vehicle can adjust the gesture and the route.
Compared with a coaxial duct 11 unmanned aerial vehicle, the unmanned aerial vehicle has the advantages that the structure is simpler, the unmanned aerial vehicle frame is removed in the design, and the integrated duct 11 flow guiding module 1 and the component assembling module 3 enable the unmanned aerial vehicle to be simpler in structure and low in failure rate.
Compared with a single-rotor duct 11 unmanned aerial vehicle, the attitude control method is simpler. The single-rotor duct 11 unmanned aerial vehicle performs attitude control through an adjustable flow guide wing plate at the tail part of the duct 11, and an additional control chain is required to be installed to control the flow guide wing plate; the unmanned aerial vehicle directly adopts the rotating speed of the motor to control the gesture of the unmanned aerial vehicle, and the control is simpler.
Further, as shown in fig. 3 to 6, the plurality of ducts 11 are curved in a direction away from each other in the top-down direction, and the area of the air outlet 13 of the duct 11 is equal to the area of the air inlet 12 of the duct 11. The plurality of ducts 11 are bent towards the direction deviating from each other, so that the area of the area between the air outlets 13 of the plurality of ducts 11 on the diversion module 1 is increased, the component assembly module 3 is convenient to arrange, and the blocking of the component assembly module 3 to the air outlets 13 of the ducts 11 is avoided. The area of the air outlet 13 of the duct 11 is equal to the area of the air inlet 12 of the duct 11, so that air is ensured not to be compressed and expanded in the diversion module 1.
The ducts 11 are curved in the direction away from each other, and air enters the curved duct 11 after passing through the duct fan 2 and is ejected downwards in an inclined manner through the air outlet 13 of the duct 11. When air passes through the air outlet 13 of the duct 11, the air can provide a lateral force in addition to an upward lifting force for the unmanned aerial vehicle. When the unmanned aerial vehicle stably hovers, four lateral forces can offset each other. When the posture or heading adjustment is required, the component of the lateral force in the horizontal direction assists the posture and heading adjustment, so that the deflection force required to be provided by changing the rotation speed of the motor is reduced.
And the air outlet 13 of the duct 11 is flat, so that the size of the lower end of the diversion module 1 is further contracted, and the unmanned aerial vehicle can be smoothly installed in the gun barrel. And when the air outlet 13 of the duct 11 is flat, the area of the air outlet is ensured to be the same as the area of the air inlet 12 of the duct 11.
As shown in fig. 3, 7 and 8, in order to accurately limit the ducted fan 2, a fixing block 21 is disposed on the circumferential surface of the ducted fan 2, a fixing groove 14 is disposed on the flow guiding module 1, and the fixing block 21 is engaged in the fixing groove 14. The fixed block 21 on the ducted fan 2 is arranged in the fixed groove 14 of the diversion module 1, so that the ducted fan 2 can not rotate when the motor rotates.
The flow guiding module 1 is connected with a fixed plate 4, the fixed plate 4 is provided with a channel hole 41, the ducted fan 2 passes through the channel hole 41, and the fixed plate 4 limits the upper side of the fixed block 21. After the ducted fan 2 is installed in the duct 11, the fixing plate 4 and the flow guiding module 1 are installed, and the fixing plate 4 can limit the fixing block 21 to prevent the ducted fan 2 from moving up and down.
Specifically, two fixing grooves 14 are designed for each ducted fan 2 above the diversion module 1, and two fixing blocks 21 are arranged on the circumferential surface of the ducted fan 2, and the fixing blocks 21 are embedded into the fixing grooves 14, so that the situation that the ducted fan 2 does not rotate when the unmanned aerial vehicle flies is ensured. In order to prevent the ducted fan 2 from moving up and down, it is also necessary to fix the ducted fan by using a fixing plate 4, and four passage holes 41 are formed in the fixing plate 4 corresponding to the four ducted fans 2. The diameters of the four channel holes 41 are larger than those of the ducted fans 2, the two fixing blocks 21 extend to the area outside the channel holes 41, the fixing plate 4 penetrates through the four ducted fans 2 and is fixed through the snap screws 42 and the flow guide modules 1, and then the fixing plate 4 can limit the fixing blocks 21.
As shown in fig. 1, the lower section of the component mounting module 3 is contracted inward in the top-down direction. The air can be in a diffusion state after flowing out from the air outlet 13 of the duct 11, and the component assembly module 3 with the contracted lower section can reduce the influence on the air flow and ensure the lifting force to the greatest extent. The shrinkage size is unmanned aerial vehicle's battery 5 can vertically place in the bottom central authorities of part assembly module 3 just, both guarantees unmanned aerial vehicle's balance, also can guarantee space utilization's rationality.
The battery 5, the power management board, the GPS, the flight control 6 (flight controller) and the receiver are arranged in the component assembly module 3, the motor of the ducted fan 2 is electrically connected with the electric regulator (electronic speed regulator), the electric regulator and the flight control 6 are electrically connected with the power management board, the GPS and the receiver are electrically connected with the flight control 6, and the power management board is electrically connected with the battery 5. The flight control 6 is PX4 flight control 6. The main function of the component assembly module 3 is to ensure that the other components than the ducted fan 2 are well assembled together. The unmanned aerial vehicle's power source is battery 5, and stable flight is gone out and is gone out the accuse 6, and safe flight is gone out and is gone out the remote controller, and the receiver receives the remote controller signal, and GPS is used for the location, and these parts all need to install in part assembly module 3, still need to guarantee the rationality of installing between them simultaneously, the good space of utilization as far as possible.
As shown in fig. 9 and 10, connecting blocks 31 are provided at four corners of the component mounting module 3 in combination with the lower free area of the flow guiding module 1, and the connecting blocks 31 are connected to the flow guiding module 1 by screws. A plurality of layers of diaphragm plates 32 are arranged in the component assembly module 3, a battery 5 is arranged on the lower side of the diaphragm plate 32 at the lowest position, a flight control 6 and a receiver are arranged on the diaphragm plate 32 at the lowest position, a power management plate and a GPS are arranged on the diaphragm plate 32 at the second layer from bottom to top, and holes for wiring to pass through are formed in the diaphragm plate 32. The partition plate can facilitate the installation of each component, and ensure that each component is reasonably arranged in the component assembly module 3.
Specifically, to fix the battery 5, a mounting groove 33 having the same size as the battery 5 needs to be designed in the bottom of the component assembly module 3, so as to ensure the stability of the battery 5 during the flying process. The upper half of the component mounting module 3 is designed in the shape of a square, and for more orderly mounting, a layered manner is used, three sliding grooves 34 are respectively designed on both sides of the component mounting module 3, and the diaphragm 32 is inserted into the sliding grooves 34.
Meanwhile, one surface is removed in the upper half of the component assembly module 3, and a sliding plate 35 which can slide up and down is used instead, so that the disassembly and the assembly are convenient. The slide plate 35 is provided with an antenna port 351 and a lead port 352, and an antenna of the receiver extends from the antenna port 351, and a wiring of the power management plate and a wiring of the battery 5 are connected after extending from the lead port, respectively. The antenna of the receiver extends out of the antenna port 351, so that the receiver can successfully receive the signal of the remote controller. The wiring of the power management board and the wiring of the battery 5 are respectively connected after extending out of the lead-out port, so that the battery 5 is convenient to plug, set a switch or charge.
As shown in fig. 3 and fig. 4, the upper end and the lower section of the diversion module 1 are respectively provided with a wiring hole 15, the wiring holes 15 are positioned among the plurality of ducts 11, and the wiring of the motor of the duct fan 2 passes through the wiring holes 15 at the upper end of the diversion module 1. The motors of the ducted fans 2 use brushless motors, and each motor has three wires connected with an electric regulator. The wiring of the motor of the ducted fan 2 is arranged to the wiring holes 15, so that the wiring of the motor is prevented from being arranged in disorder or affecting the duct 11. The electric regulator can be installed in the gaps among the four ducts 11 of the diversion module 1, and at this time, the wiring between the electric regulator and the power management board passes through the wiring hole 15 at the lower end of the diversion module 1. Or, the electric motor is installed in the component assembly module 3, and at this time, the wiring between the motor and the electric motor sequentially passes through the wiring hole 15 at the upper end of the diversion module 1 and the wiring hole 15 at the lower end of the diversion module 1.
The method for installing the unmanned aerial vehicle comprises the following steps:
as shown in fig. 1 and 2, the unmanned aerial vehicle is required to be assembled in a certain order, because the unmanned aerial vehicle of the present invention is a four-rotor unmanned aerial vehicle, the motor rotation direction of the ducted fan 2 is specific, the motor rotation directions of the ducted fans 2 at the upper right and lower left corners are counterclockwise, the motor rotation directions of the ducted fans 2 at the upper left and lower right corners are clockwise, and the motor rotation direction can be changed by adjusting any two wires among three wires of the brushless electric motor. Before the unmanned aerial vehicle assembly is completed, the motor rotation direction needs to be debugged, and in order to facilitate debugging, the unmanned aerial vehicle assembly needs to be carried out from two sides respectively. One side is provided with a duct fan 2 which is arranged on the diversion module 1 by a fixing plate 4 and is connected with an electric motor; the other side is to install the unmanned aerial vehicle's part into the part assembly module 3, then connect the electricity to transfer signal line and power cord to the power management board, finally carry out the test of motor direction of rotation, carry out the unmanned aerial vehicle that the final equipment was got to two parts again after the test was accomplished.
Assembling the upper half part of the unmanned aerial vehicle: firstly, mounting a fixed block 21 on a ducted fan 2 into a fixed groove 14 of a diversion module 1, so as to ensure that the ducted fan 2 does not rotate when a motor rotates; the wiring of the motor of the ducted fan 2 is then passed through the wiring hole 15. The 4 ducted fans 2 were installed as described above. In the second step, the fixing plate 4 is connected with the diversion module 1, each channel hole 41 on the fixing plate 4 corresponds to one ducted fan 2, the fixing plate 4 contacts with the fixing block 21, and the fixing plate 4 is fixed on the diversion module 1 by using the snap screws 42 with the same height as the fixing block 21. And thirdly, connecting the motor wire by using an electric wire adjusting device, thus completing the assembly of the upper half part of the unmanned aerial vehicle.
Assembling the lower half part of the unmanned aerial vehicle: the assembly of unmanned aerial vehicle latter half relates to the part more, and the part has the assembly order, and the order is to the equipment that will influence whole unmanned aerial vehicle. First, one end of the battery 5 of the unmanned aerial vehicle, which is not provided with a power plug, needs to be vertically placed into the mounting groove 33 in the component assembly module 3, so that the unmanned aerial vehicle can be conveniently electrified and the battery 5 can be conveniently charged. In the second step, a diaphragm plate 32 is inserted into a sliding groove 34 at the lowest part of the component assembly module 3, the flight control 6 and the receiver are mounted on the diaphragm plate 32, and meanwhile, necessary power lines and data lines are connected on the flight control 6, so that the subsequent assembly is facilitated. Third, a single diaphragm plate 32 is inserted into the middle sliding groove 34, and a power management board and a GPS are installed in the diaphragm plate 32. The power interface of the power management board needs to face the sliding board 35 side of the component assembly module 3, so as to be convenient for connection with the battery 5. The GPS wiring needs to be connected to the flight control 6 through the gap between the diaphragms 32, and then the data and power lines between the flight control 6 and the power management board are connected. And fourthly, inserting a diaphragm plate 32 into the uppermost sliding groove 34, connecting an electric modulation signal wire with a power wire through an interface on the diaphragm plate 32 and a power management board of the second layer, and powering on to determine the rotation direction of the motor. And completing the wiring of 4 electric switches according to the steps.
Finally, the diversion module 1 and the component assembly module 3 are installed together by using screws, so that the whole unmanned aerial vehicle can be obtained.
In order to verify the performance of the designed unmanned aerial vehicle in all aspects, the fixing plate 4, the flow guiding module 1 and the component assembling module 3 are printed through 3D. In order to reduce the weight of the unmanned aerial vehicle, the resin material is adopted for printing, the thickness of the model is 2mm, and the ducted fan 2 directly purchases the existing product. The maximum thrust of each ducted fan 2 was 2.5kg, the unmanned aerial vehicle used 4500 milliampere hour lithium battery 5, and the total weight of the unmanned aerial vehicle was 3.0kg. Through practical tests, the thrust of each ducted fan 2 after passing through the diversion module 1 is 1.5kg, and the total thrust of the practical four ducts 11 is still 6kg, so that the unmanned aerial vehicle can fly normally.
The invention is not limited to the above-described alternative embodiments, and any person who may derive other various forms of products in the light of the present invention, however, any changes in shape or structure thereof, all falling within the technical solutions defined in the scope of the claims of the present invention, fall within the scope of protection of the present invention.
Claims (8)
1. A small-size many ducts unmanned aerial vehicle of quick deployment, its characterized in that: the air conditioner comprises a flow guide module (1), wherein the flow guide module (1) is provided with at least two ducts (11), a duct fan (2) is arranged in each duct (11), a component assembly module (3) is connected to the flow guide module (1), and the component assembly module (3) is connected to an area between air outlets (13) of a plurality of ducts (11) on the flow guide module (1); in the direction from top to bottom, the plurality of ducts (11) are bent in the direction away from each other, and the area of an air outlet (13) of the duct (11) is equal to the area of an air inlet (12) of the duct (11); the air outlet (13) of the duct (11) is flat.
2. The rapidly deployed mini-multi-duct drone of claim 1, wherein: the ducted fan is characterized in that a fixing block (21) is arranged on the circumferential surface of the ducted fan (2), a fixing groove (14) is formed in the flow guiding module (1), and the fixing block (21) is clamped in the fixing groove (14).
3. The rapidly deployed mini-multi-duct drone of claim 2, wherein: the air guide device is characterized in that the air guide module (1) is connected with a fixing plate (4), a channel hole (41) is formed in the fixing plate (4), the ducted fan (2) penetrates through the channel hole (41), and the fixing plate (4) limits the upper side of the fixing block (21).
4. The rapidly deployed mini-multi-duct drone of claim 1, wherein: in the top-down direction, the lower section of the component mounting module (3) is contracted inwards.
5. The rapidly deployed mini-multi-duct drone of claim 1, wherein: the intelligent bypass fan is characterized in that a battery (5), a power management board, a GPS (global positioning system), a flight control device (6) and a receiver are installed in the component assembly module (3), a motor of the bypass fan (2) is electrically connected with an electric regulator, the electric regulator and the flight control device (6) are electrically connected with the power management board, the GPS and the receiver are electrically connected with the flight control device (6), and the power management board is electrically connected with the battery (5).
6. The rapidly deployed mini-multi-duct drone of claim 5, wherein: a plurality of layers of diaphragm plates (32) are arranged in the component assembly module (3), a battery (5) is arranged at the lower side of the diaphragm plate (32) at the lowest position, a flight control (6) and a receiver are arranged on the diaphragm plate (32) at the lowest position, a power management plate and a GPS (global positioning system) are arranged on the diaphragm plate (32) at the second layer from bottom to top, and holes for wiring to pass through are formed in the diaphragm plate (32).
7. The rapidly deployed mini-multi-duct drone of claim 5, wherein: one side of the component assembly module (3) is provided with a sliding plate (35), an antenna port (351) and a lead port (352) are arranged on the sliding plate (35), an antenna of the receiver extends out of the antenna port (351), and a wiring of the power management plate and a wiring of the battery (5) are respectively connected after extending out of the lead port.
8. The rapidly deployed mini-multi-duct drone of claim 1, wherein: the air guide module (1) is provided with a wiring hole (15), the wiring hole (15) is positioned among the plurality of ducts (11), and wiring of a motor of the duct fan (2) passes through the wiring hole (15).
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