CN211055372U - Dual-rotor unmanned aerial vehicle externally connected with motor - Google Patents
Dual-rotor unmanned aerial vehicle externally connected with motor Download PDFInfo
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- CN211055372U CN211055372U CN201821711897.9U CN201821711897U CN211055372U CN 211055372 U CN211055372 U CN 211055372U CN 201821711897 U CN201821711897 U CN 201821711897U CN 211055372 U CN211055372 U CN 211055372U
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Abstract
The utility model provides a two rotor unmanned aerial vehicle of external motor, belongs to miniature unmanned aerial vehicle equipment field. Duct I, go up screw device, duct II, lower screw device, duct III, chassis device, landing gear, battery device and motor device constitution, I lower extreme of duct fix in duct II upper end, last screw device place in duct I and duct II centre, and can the relative slip, duct II lower extreme fix in duct III upper end, lower screw device place in duct II and duct III centre, and can the relative slip, chassis device upper end fix the lower extreme at duct III, landing gear be the circumference array and distribute at the chassis device lower extreme, battery device be the symmetric distribution on duct II and chassis device outer wall, motor device be the symmetric distribution at duct II outer walls, this device has better stability and lift at the in-process of flight.
Description
Technical Field
The invention relates to a dual-rotor unmanned aerial vehicle externally connected with a motor, in particular to an unmanned aerial vehicle consisting of a duct I, an upper propeller device, a duct II, a lower propeller device, a duct III, a chassis device, a landing gear, a battery device and a motor device, and belongs to the field of micro unmanned aerial vehicle equipment.
Background
At the present stage, ducted unmanned aerial vehicle's structural design, motor, electricity are transferred, devices such as flight control ware are mainly placed inside the duct, and the aerodynamic circulation of the whole device of reduction that can be by a wide margin like this reduces the lift of whole device, and some ducted unmanned aerial vehicles in addition place devices such as motor, electricity are transferred, flight control ware on unmanned aerial vehicle's top, reduce unmanned aerial vehicle's stationarity like this.
Disclosure of Invention
Aiming at the defects, the invention provides a double-rotor unmanned aerial vehicle externally connected with a motor.
The invention is realized by the following technical scheme: the utility model provides a dual rotor unmanned aerial vehicle of external motor, is by duct I, go up screw device, duct II, lower screw device, duct III, chassis device, landing gear, battery device and motor device and constitutes, duct I lower extreme fix in duct II upper ends, last screw device place in duct I and duct II middles, and can the relative slip, duct II lower extreme fix in duct III upper end, lower screw device place in duct II and duct III middles, and can the relative slip, chassis device upper end fix the lower extreme at duct III, landing gear be the circumference array and distribute at the chassis device lower extreme, battery device be the symmetric distribution on duct II and chassis device outer wall, motor device be the symmetric distribution at duct II outer walls.
The duct I is composed of a 45-degree oblique opening, a 45-degree oblique hole, a first sliding rail and a first butt joint boss, the 45-degree oblique opening is formed in the upper end of the duct I, the 45-degree oblique hole is distributed in the middle of the duct I in a circumferential array mode, the first sliding rail is distributed at the lower end of the duct I, and the first butt joint boss is distributed on the outer side of the sliding groove in a circumferential array mode.
The upper propeller device is composed of an upper toothed ring, an upper circular sliding block, an upper propeller fixing block and an upper propeller, the upper circular sliding block is placed between a duct I and a duct II, the upper end of the upper circular sliding block is in contact with a first sliding rail and can slide relatively, the upper toothed ring is fixed on the outer side of the upper circular sliding block, the upper propeller fixing block is symmetrically fixed on the inner side of the upper circular sliding block, and two ends of the upper propeller are fixed on the upper propeller fixing block.
The duct II is composed of a second butt joint boss, a second slide rail and fixing holes, the second butt joint boss is symmetrically and evenly distributed at the upper end and the lower end of the duct II, the second butt joint boss at the upper end is in contact with the first butt joint boss, the second butt joint boss at the lower end is in contact with the duct III, the second slide rail is symmetrically distributed at the upper end and the lower end of the duct II, the lower end of the upper circular slide block is in contact with the second slide rail and can slide relatively, and the fixing holes are evenly distributed around the duct II.
Lower screw device constitute by lower ring gear, lower circular slider, lower screw fixed block and lower screw, lower circular slider place in the middle of duct II and duct III, the upper end contacts with the second slide rail, the lower extreme contacts with duct III, and can the relative slip, lower ring gear fix in the circular slider outside down, lower screw fixed block be the symmetry and fix circular slider inboard under, the lower screw both ends fix on lower screw fixed block.
The chassis device comprises a duct IV, a steering engine, a direction device and a flight controller, wherein the upper end of the duct IV is fixed at the lower end of a duct III, a third butt joint boss and a third slide rail are arranged on the duct III, the third butt joint boss is uniformly distributed at the upper end of the duct III and is in contact with a second butt joint boss at the lower end, the third slide rail is fixed at the upper end of the duct III and is in contact with the lower end of a lower circular slide block and can slide relatively, the steering engine is fixed on the outer wall of the duct IV, one end of the direction device is connected with the steering engine, the other end of the direction device is connected with the duct IV, and the flight controller is symmetrical to the steering engine and is fixed on the outer wall of the duct IV.
The direction device comprises a fixed column, a fixed plate, a flow deflector, a fixed block and a connecting column, wherein the flow deflector is distributed in a linear array mode, two ends of the flow deflector are connected with the fixed plate, one end of the fixed column is connected with the duct IV, the other end of the fixed column is connected with the fixed plate on one side, the fixed block is connected with the fixed plate on the other side, one end of the connecting column is connected with the fixed block, the connecting part is of a hexagonal structure, the other end of the connecting column is connected with the steering engine, and the connecting part.
The landing gear comprises undercarriage, elastic column and supporting leg, the undercarriage fix at IV outer wall of duct, the contact surface adopts the arc structure, supporting leg one end be connected with the undercarriage, elastic column one end be connected with the undercarriage, the other end is connected with the supporting leg.
The battery device is composed of a battery frame, a battery and an electric regulator, the battery frame is fixed on the outer wall of the duct II and the outer wall of the chassis device, the battery and the electric regulator are placed inside the battery frame, and the output end of the battery is connected with the input end of the electric regulator, the input end of the steering engine and the input end of the flight controller.
The motor device comprises a motor frame, a motor and a motor gear, wherein the motor frame is fixed on the outer wall of the duct II, the motor is fixed in the motor frame, the input end of the motor is connected with the output end of the electric regulator and the output end of the flight controller, and the motor gear is fixed at the shaft end of the motor.
The aircraft has the beneficial effects that the aircraft has better stability and lift force in the flying process, adopts multiple structure matching, and is convenient to disassemble when parts are damaged; except the propeller and the direction device, other devices are not arranged in the whole ducted device, the airflow of the whole device is increased, the flight efficiency is increased, and the ducted I adopts a 45-degree oblique opening and a 45-degree oblique hole, so that the airflow quantity can be increased, the pneumatic lift of the whole device is increased, and the working efficiency is improved; the screw adopts last screw and screw combination down, relative rotation through last screw and screw down, control unmanned aerial vehicle's balance, the moment of torsion offsets, go up screw device and screw device down and all adopt external motor, increase the stability of whole device, landing gear adopts the elasticity post, unmanned aerial vehicle can play certain elasticity helping hand when taking off, during the descending, can play the cushioning effect, improve unmanned aerial vehicle's security, the battery holder, motor holder and duct II and ground disk device contact surface, cambered surface structure all takes, can closely meet during the assembly, the stability and the security of reinforcing means.
Drawings
FIG. 1 is a schematic structural diagram of the present invention;
FIG. 2 is a schematic structural diagram of a duct I;
FIG. 3 is a schematic structural view of an upper propeller device;
FIG. 4 is a schematic structural view of duct II;
FIG. 5 is a schematic view of the lower propeller arrangement;
FIG. 6 is a schematic structural view of duct III;
FIG. 7 is a schematic structural view of a chassis device;
FIG. 8 is a schematic view of the structure of the direction device;
FIG. 9 is a schematic view of the landing gear configuration;
FIG. 10 is a schematic diagram of a battery device;
fig. 11 is a schematic structural view of the motor device.
In the figure, 1, a duct I, 2, an upper propeller device, 3, a duct II, 4, a lower propeller device, 5, a duct III, 6, a chassis device, 7, a landing gear, 8, a battery device, 9, a motor device, 101, 45-degree inclined openings, 102, 45-degree inclined holes, 103, a first slide rail, 104, a first butt joint boss, 201, an upper toothed ring, 202, an upper circular slide block, 203, an upper propeller fixing block, 204, an upper propeller, 301, a second butt joint boss, 302, a second slide rail, 303, a fixing hole, 401, a lower toothed ring, 402, a lower circular slide block, 403, a lower propeller fixing block, 404, a lower propeller, 501, a third butt joint boss, 502, a third slide rail, 601, a duct IV, 602, a steering engine, 603, a direction device, 604, a flight controller, a connecting column 6031, a fixing column 6032, a fixing plate, 6033, a deflector, 6034, a fixing block, 35, 701, a landing gear, 702. elastic column, 703, supporting leg, 801, battery frame, 802, battery, 803, electricity accent, 901, motor frame, 902, motor, 903, motor gear.
Detailed Description
The invention is realized by the following technical scheme: a dual-rotor unmanned aerial vehicle with an external motor is composed of a duct I1, an upper propeller device 2, a duct II 3, a lower propeller device 4, a duct III 5, a chassis device 6, a landing device 7, a battery device 8 and a motor device 9, the lower end of the duct I1 is fixed at the upper end of the duct II 3, the upper propeller device 2 is arranged between the duct I1 and the duct II 3, and can slide relatively, the lower end of the duct II 3 is fixed at the upper end of the duct III 5, the lower propeller device 4 is arranged between the duct II 3 and the duct III 5, and can slide relatively, the upper end of the chassis device 6 is fixed at the lower end of the duct III 5, the landing gears 7 are distributed at the lower end of the chassis device 6 in a circumferential array, the battery devices 8 are symmetrically distributed on the outer walls of the duct II 3 and the chassis device 6, and the motor devices 9 are symmetrically distributed on the outer wall of the duct II 3.
The duct I1 is composed of a 45-degree oblique opening 101, a 45-degree oblique hole 102, a first slide rail 103 and a first butt boss 104, wherein the 45-degree oblique opening 101 is arranged at the upper end of the duct I1, the 45-degree oblique hole 102 is distributed in the middle of the duct I1 in a circumferential array mode, the first slide rail 103 is distributed at the lower end of the duct I1, and the first butt boss 104 is distributed outside the slide groove 103 in a circumferential array mode.
The upper propeller device 2 is composed of an upper toothed ring 201, an upper circular sliding block 202, an upper propeller fixing block 203 and an upper propeller 204, the upper circular sliding block 202 is placed between the duct I1 and the duct II 3, the upper end of the upper circular sliding block is in contact with the first sliding rail 103 and can slide relatively, the upper toothed ring 201 is fixed on the outer side of the upper circular sliding block 202, the upper propeller fixing block 203 is symmetrically fixed on the inner side of the upper circular sliding block 202, and two ends of the upper propeller 204 are fixed on the upper propeller fixing block 203.
The duct II 3 is composed of a second butt joint boss 301, a second slide rail 302 and a fixing hole 303, the second butt joint boss 301 is symmetrically and uniformly distributed at the upper end and the lower end of the duct II 3, the second butt joint boss 301 at the upper end is in contact with the first butt joint boss 104, the second butt joint boss 301 at the lower end is in contact with the duct III 5, the second slide rail 302 is symmetrically distributed at the upper end and the lower end of the duct II 3, the lower end of the upper circular slide block 202 is in contact with the second slide rail 302 and can slide relatively, and the fixing hole 303 is uniformly distributed around the duct II 3.
The lower propeller device 4 is composed of a lower toothed ring 401, a lower circular sliding block 402, a lower propeller fixing block 403 and a lower propeller 404, the lower circular sliding block 402 is placed between a duct II 3 and a duct III 5, the upper end of the lower circular sliding block 402 is in contact with the second sliding rail 302, the lower end of the lower circular sliding block is in contact with the duct III 5 and can slide relatively, the lower toothed ring 401 is fixed on the outer side of the lower circular sliding block 402, the lower propeller fixing block 403 is symmetrically fixed on the inner side of the lower circular sliding block 402, and two ends of the lower propeller 404 are fixed on the lower propeller fixing block 403.
The chassis device 6 comprises a duct IV 601, a steering engine 602, a direction device 603 and a flight controller 604, the upper end of the duct IV 601 is fixed at the lower end of the duct III 5, a third butt-joint boss 501 and a third slide rail 502 are arranged on the duct III 5, the third butt-joint boss 501 is uniformly distributed at the upper end of the duct III 5, the third butt-joint boss 501 is in contact with a second butt-joint boss 301 at the lower end, the third slide rail 502 is fixed at the upper end of the duct III 5, the third slide rail 502 is in contact with the lower end of a lower circular slide block 402 and can slide relatively, the steering engine 602 is fixed on the outer wall of the duct IV 601, one end of the direction device 603 is connected with the steering engine 602, the other end of the direction device is connected with the duct IV 601, and the flight controller 604 is symmetrical to the steering engine 602 and fixed on the outer wall of the duct IV 601.
The direction device 603 comprises a fixed column 6031, a fixed plate 6032, a flow deflector 6033, a fixed block 6034 and a connecting column 6035, wherein the flow deflector 6033 is distributed in a linear array, two ends of the flow deflector 6033 are connected with the fixed plate 6034, one end of the fixed column 6031 is connected with a duct IV 601, the other end of the fixed column 6031 is connected with the fixed plate 6032 on one side, the fixed block 6034 is connected with the fixed plate 6032 on the other side, one end of the connecting column 6035 is connected with the fixed block 6034, and the other end of the connecting column 6035 is connected with a.
The landing gear 7 consists of a landing gear 701, an elastic column 702 and a supporting leg 703, the landing gear 701 is fixed on the outer wall of the duct IV 601, one end of the supporting leg 703 is connected with the landing gear 701, one end of the elastic column 702 is connected with the landing gear 701, and the other end of the elastic column 702 is connected with the supporting leg 703.
The battery device 8 is composed of a battery frame 801, a battery 802 and an electric regulator 803, the battery frame 801 is fixed on the outer wall of the duct II 3 and the outer wall of the chassis device 6, the battery 802 and the electric regulator 803 are placed inside the battery frame 801, and the output end of the battery 802 is connected with the input end of the electric regulator 803, the input end of the steering engine 602 and the input end of the flight controller 604.
The motor device 9 is composed of a motor frame 901, a motor 902 and a motor gear 903, the motor frame 901 is fixed on the outer wall of the duct II 3, the motor 902 is fixed in the motor frame 901, the input end of the motor 902 is connected with the output end of the electric regulator 803 and the output end of the flight controller 604, and the motor gear 903 is fixed at the shaft end of the motor 902.
The specific working mode of the invention is as follows: through outside remote controller control flight controller 604, control motor 902 rotates, ring gear 202 and lower ring gear 402 rotate in the drive, go up screw 204 and screw 404 down and operate with the rotational speed of difference, it provides lift to go up screw 204, screw 404 eliminates the reaction torque down, unmanned aerial vehicle carries out the vertical lift, flight controller 604 control steering wheel 602 rotates, it rotates to drive direction device 603, the guide vane 6033 deflects certain angle, through changing the air current direction, provide the power that gos forward for unmanned aerial vehicle.
It will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in the embodiments described above without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims.
Claims (10)
1. The utility model provides a bispin wing unmanned aerial vehicle of external motor, is duct I, goes up screw device, duct II, lower screw device, duct III, chassis device, landing gear, battery device and motor device and constitutes its characterized in that: i lower extreme of duct fix in II upper ends of duct, last screw device place in the middle of duct I and duct II, and can the relative slip, II lower extremes of duct fix in the upper end of duct III, lower screw device place in the middle of duct II and duct III, and can the relative slip, chassis device upper end fix the lower extreme at duct III, landing gear be the circumference array and distribute at the chassis device lower extreme, battery device be the symmetric distribution on duct II and chassis device outer wall, motor device be the symmetric distribution at II outer walls of duct.
2. The twin rotor drone of claim 1, with an external motor, wherein: the duct I is composed of a 45-degree oblique opening, a 45-degree oblique hole, a first sliding rail and a first butt joint boss, the 45-degree oblique opening is formed in the upper end of the duct I, the 45-degree oblique hole is distributed in the middle of the duct I in a circumferential array mode, the first sliding rail is distributed at the lower end of the duct I, and the first butt joint boss is distributed on the outer side of the sliding groove in a circumferential array mode.
3. The twin rotor drone of claim 1, with an external motor, wherein: the upper propeller device is composed of an upper toothed ring, an upper circular sliding block, an upper propeller fixing block and an upper propeller, the upper circular sliding block is placed between a duct I and a duct II, the upper end of the upper circular sliding block is in contact with a first sliding rail and can slide relatively, the upper toothed ring is fixed on the outer side of the upper circular sliding block, the upper propeller fixing block is symmetrically fixed on the inner side of the upper circular sliding block, and two ends of the upper propeller are fixed on the upper propeller fixing block.
4. The twin rotor drone of claim 1, with an external motor, wherein: the duct II is composed of a second butt joint boss, a second slide rail and fixing holes, the second butt joint boss is symmetrically and evenly distributed at the upper end and the lower end of the duct II, the second butt joint boss at the upper end is in contact with the first butt joint boss, the second butt joint boss at the lower end is in contact with the duct III, the second slide rail is symmetrically distributed at the upper end and the lower end of the duct II, the lower end of the upper circular slide block is in contact with the second slide rail and can slide relatively, and the fixing holes are evenly distributed around the duct II.
5. The twin rotor drone of claim 1, with an external motor, wherein: lower screw device constitute by lower ring gear, lower circular slider, lower screw fixed block and lower screw, lower circular slider place in the middle of duct II and duct III, the upper end contacts with the second slide rail, the lower extreme contacts with duct III, and can the relative slip, lower ring gear fix in the circular slider outside down, lower screw fixed block be the symmetry and fix circular slider inboard under, the lower screw both ends fix on lower screw fixed block.
6. The twin rotor drone of claim 1, with an external motor, wherein: the chassis device comprises a duct IV, a steering engine, a direction device and a flight controller, wherein the upper end of the duct IV is fixed at the lower end of a duct III, a third butt joint boss and a third slide rail are arranged on the duct III, the third butt joint boss is uniformly distributed at the upper end of the duct III and is in contact with a second butt joint boss at the lower end, the third slide rail is fixed at the upper end of the duct III and is in contact with the lower end of a lower circular slide block and can slide relatively, the steering engine is fixed on the outer wall of the duct IV, one end of the direction device is connected with the steering engine, the other end of the direction device is connected with the duct IV, and the flight controller is symmetrical to the steering engine and is fixed on the outer wall of the duct IV.
7. An external motor twin rotor drone according to claim 6, wherein: the direction device comprises a fixed column, a fixed plate, a flow deflector, a fixed block and a connecting column, wherein the flow deflector is distributed in a linear array mode, two ends of the flow deflector are connected with the fixed plate, one end of the fixed column is connected with the duct IV, the other end of the fixed column is connected with the fixed plate on one side, the fixed block is connected with the fixed plate on the other side, one end of the connecting column is connected with the fixed block, the connecting part is of a hexagonal structure, the other end of the connecting column is connected with the steering engine, and the connecting part.
8. The twin rotor drone of claim 1, with an external motor, wherein: the landing gear comprises undercarriage, elastic column and supporting leg, the undercarriage fix at IV outer wall of duct, the contact surface adopts the arc structure, supporting leg one end be connected with the undercarriage, elastic column one end be connected with the undercarriage, the other end is connected with the supporting leg.
9. The twin rotor drone of claim 1, with an external motor, wherein: the battery device is composed of a battery frame, a battery and an electric regulator, the battery frame is fixed on the outer wall of the duct II and the outer wall of the chassis device, the battery and the electric regulator are placed inside the battery frame, and the output end of the battery is connected with the input end of the electric regulator, the input end of the steering engine and the input end of the flight controller.
10. The twin rotor drone of claim 1, with an external motor, wherein: the motor device comprises a motor frame, a motor and a motor gear, wherein the motor frame is fixed on the outer wall of the duct II, the motor is fixed in the motor frame, the input end of the motor is connected with the output end of the electric regulator and the output end of the flight controller, and the motor gear is fixed at the shaft end of the motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821711897.9U CN211055372U (en) | 2018-10-22 | 2018-10-22 | Dual-rotor unmanned aerial vehicle externally connected with motor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821711897.9U CN211055372U (en) | 2018-10-22 | 2018-10-22 | Dual-rotor unmanned aerial vehicle externally connected with motor |
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| CN211055372U true CN211055372U (en) | 2020-07-21 |
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| CN201821711897.9U Active CN211055372U (en) | 2018-10-22 | 2018-10-22 | Dual-rotor unmanned aerial vehicle externally connected with motor |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109204805A (en) * | 2018-10-22 | 2019-01-15 | 山东建筑大学 | A kind of DCB Specimen unmanned plane of external motor |
| CN112896506A (en) * | 2021-01-28 | 2021-06-04 | 西安电子科技大学 | All-directional docking system and method based on flight array |
-
2018
- 2018-10-22 CN CN201821711897.9U patent/CN211055372U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109204805A (en) * | 2018-10-22 | 2019-01-15 | 山东建筑大学 | A kind of DCB Specimen unmanned plane of external motor |
| CN109204805B (en) * | 2018-10-22 | 2024-04-05 | 山东建筑大学 | External motor's two rotor unmanned aerial vehicle |
| CN112896506A (en) * | 2021-01-28 | 2021-06-04 | 西安电子科技大学 | All-directional docking system and method based on flight array |
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