CN220448159U - Fuselage bearing type single-rotor unmanned aerial vehicle - Google Patents
Fuselage bearing type single-rotor unmanned aerial vehicle Download PDFInfo
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- CN220448159U CN220448159U CN202321661503.4U CN202321661503U CN220448159U CN 220448159 U CN220448159 U CN 220448159U CN 202321661503 U CN202321661503 U CN 202321661503U CN 220448159 U CN220448159 U CN 220448159U
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Abstract
The utility model discloses a fuselage bearing type single-rotor unmanned aerial vehicle, which comprises an integral bearing type fuselage, wherein a ducted fan, a steering engine and a rudder blade are arranged in the integral bearing type fuselage, the steering engine is connected with the rudder blade through a synchronous belt wheel set, the integral bearing type fuselage is in the shape of a hollow cylindrical barrel, a bearing platform is arranged in the integral bearing type fuselage, the steering engine is arranged on the bearing platform, and a power bracket, a battery pack, a speed regulator and a horizontal gyroscope are also arranged on the bearing platform, and the battery pack supplies power for the steering engine, the speed regulator and the horizontal gyroscope. According to the unmanned aerial vehicle, the unmanned aerial vehicle has the advantages that the unmanned aerial vehicle has the outside leakage of parts, the rudder blade provides larger control force, the flight efficiency is higher, the reliability is better, the safety is higher, the unmanned aerial vehicle is not easy to be interfered by external environments, and the integrity of the unmanned aerial vehicle can be better maintained after the unmanned aerial vehicle is subjected to flight accidents such as impact, falling and the like.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicles, and relates to a fuselage bearing type single-rotor unmanned aerial vehicle.
Background
Unmanned aerial vehicles ("UAVs") are unmanned aerial vehicles that are operated using radio remote control equipment and self-contained programmed control devices.
At present, most unmanned aerial vehicle is many rotors, generally is even rotor, but needs a plurality of blades and motor like this, and though control is nimble, organism is stable, operating threshold is low, but a large amount of energy need be dissipated to a plurality of rotors, and the noise is big, and the structure is complicated, and the machine volume is great, and the rotor is general all exposed outside, and the danger is great, and the viability is poor.
Traditional single rotor unmanned aerial vehicle is single rotor long tail boom take unmanned aerial vehicle of tail rotor, also called helicopter unmanned aerial vehicle, and the helicopter for short relies on the tail rotor on the tail boom to balance the rotation that leads to because main rotor is rotatory, and its structure is complicated, and the energy consumption is big, and the rotor exposes outside equally, and the danger is big, and the viability is poor.
Compared with a common rotor unmanned aerial vehicle, the duct fan type single rotor unmanned aerial vehicle has the advantages that the propeller is arranged inside the duct, the lift force generated during working is larger, the pneumatic effect is better, meanwhile, the duct fan is not easy to damage, the reliability and the anti-interference capability of the unmanned aerial vehicle are improved, and good safety is achieved. However, the design configuration is that the ducted fan is used as an unmanned aerial vehicle main body to control the leakage of parts such as rudder blades, battery packs, electronic speed regulators and the like, so that potential safety hazards are brought. The steering engine is directly connected with the rudder page and is positioned below the ducted fan, the steering engine occupies part of the space at the lower part of the ducted fan, the rudder page area is reduced, and the control force is reduced. The steering engine is directly connected with the rudder page, and a speed reducing mechanism is not arranged, so that high requirements are provided for the torque provided by the steering engine. The tail part has no rectifying structure, the tail flow field is chaotic and is easy to be interfered by an external flow field, and the anti-interference capability, the control capability, the reliability and the safety of the tail part can be further improved.
Disclosure of Invention
The utility model aims to provide a fuselage bearing type single-rotor unmanned aerial vehicle, which has no part leakage, and rudder pages provide larger control force and higher flight efficiency.
The technical scheme includes that the fuselage bearing type single-rotor unmanned aerial vehicle comprises an integral bearing type fuselage, a ducted fan, a steering engine and rudder blades are arranged in the integral bearing type fuselage, the steering engine is connected with the rudder blades through a synchronous belt wheel set, the integral bearing type fuselage is in a hollow cylindrical barrel shape, a bearing platform is arranged in the integral bearing type fuselage, the steering engine is arranged on the bearing platform, a power bracket, a battery pack, a speed regulator and a horizontal gyroscope are further arranged on the bearing platform, and the battery pack supplies power for the steering engine, the speed regulator and the horizontal gyroscope.
The present utility model is also characterized in that,
the synchronous pulley group comprises a large synchronous pulley and a small synchronous pulley which are connected through a synchronous belt, the small synchronous pulley is connected with a steering engine through a threaded shaft, the large synchronous pulley is connected with a rudder blade shaft of a rudder blade, and the large synchronous pulley is arranged below the bearing platform.
The transmission ratio of the large synchronous wheel to the small synchronous wheel in the synchronous belt wheel group is 1:3.
The speed regulating meter is an electronic speed regulating meter and is respectively connected with the ducted fan and the steering engine through the electric connector.
The bearing platform is fixedly provided with a speed regulator bracket, and the speed regulator is fixedly adhered to the speed regulator bracket through glue.
The bearing platform is fixedly provided with a battery compartment, and the battery pack is clamped in the battery compartment.
The rudder blade is of a three-layer blade superposition structure.
The integrated bearing type rudder blade comprises a rudder blade and is characterized in that a guide plate is arranged at the lower part of the integrated bearing type rudder blade, the guide plate is a cylinder body with a small diameter and a large diameter, the side wall of the guide plate is a smooth curved surface with radian, a cross body positioned on the central shaft of the guide plate is arranged in the guide plate, and the center of the cross body is connected with the rudder blade shaft of the rudder blade.
The beneficial effects of the utility model are as follows:
compared with the existing unmanned aerial vehicle, the unmanned aerial vehicle with the single rotor wing bearing type unmanned aerial vehicle provided by the utility model has the advantages that the unmanned aerial vehicle has the advantages that the control force is larger, the flying efficiency is higher, the reliability is better, the safety is higher, the unmanned aerial vehicle is not easy to be interfered by external environment, the integrity of the engine body can be better maintained after the unmanned aerial vehicle is subjected to flying accidents such as impact, falling and the like, the structure is simple and reliable, the manufacturing cost is low, and the unmanned aerial vehicle has stronger market competition advantages.
Drawings
FIG. 1 is an isometric view of a fuselage-carrying single-rotor unmanned aerial vehicle of the present utility model;
FIG. 2 is a top view of the fuselage-carrying single-rotor unmanned aerial vehicle of the present utility model;
FIG. 3 is a bottom view of the fuselage-carrying single-rotor unmanned aerial vehicle of the present utility model;
fig. 4 is a schematic structural view of rudder blades in the fuselage-carrying single-rotor unmanned aerial vehicle of the present utility model;
FIG. 5 is a schematic view of the power bracket in the fuselage-carrying single-rotor unmanned aerial vehicle of the present utility model;
fig. 6 is a schematic view of a part of a synchronous pulley set in a fuselage-carrying single-rotor unmanned aerial vehicle according to the present utility model;
fig. 7 is a schematic structural view of a deflector in a fuselage-carrying single-rotor unmanned aerial vehicle according to the present utility model.
In the figure, 1. An integral bearing type fuselage; 2. a ducted fan; 3. rudder blade; 4. a load-bearing platform; 5. steering engine; 6. a battery pack; 7. an electronic speed regulator; 8. a horizontal gyroscope; 9. a small synchronizing wheel; 10. a large synchronizing wheel; 11. a rudder blade shaft; 12. a deflector; 13. a power bracket; 14. a battery compartment; 15. a synchronous belt.
Detailed Description
The utility model will be described in detail below with reference to the drawings and the detailed description.
Example 1
The embodiment provides a fuselage bears single rotor unmanned aerial vehicle, as shown in fig. 1-3, including integrative bearing type fuselage 1, be provided with duct fan 2 in the integrative bearing type fuselage 1, steering wheel 5 and rudder blade 3 all are provided with four, and steering wheel 5 and rudder blade 3 one-to-one, four rudder blade 3 are central symmetry setting, rudder blade 3 is three-layer blade stack structure, steering wheel 5 is connected with rudder blade 3 through the hold-in gear group, integrative bearing type fuselage 1 is hollow cylinder barrel shape, be provided with loading platform 4 in the integrative bearing type fuselage 1, steering wheel 5 passes through the bolt setting on loading platform 4, and still be provided with power bracket 13 on the loading platform 4, group battery 6, the speed regulator 7, horizontal gyroscope 8, group battery 6 is steering wheel 5, speed regulator 7, horizontal gyroscope 8 power supply.
As shown in fig. 4, the rudder blade 3 has a large size, adopts a three-layer flow guiding design, reduces the weight, improves the utilization rate of a flow field, and improves the control performance of the rudder blade 3 compared with a common rudder blade.
The power bracket 13 is fixedly connected with the bearing platform 4 and the integrated bearing type machine body 1 respectively, as shown in fig. 5, the power bracket adopts a hollow special-shaped design, and reduces the material consumption while ensuring the structural strength and the stress area, thereby achieving the purposes of weight reduction and cost reduction.
The bearing platform 4 is fixedly provided with a speed regulator bracket and a battery bin 14, the battery pack 6 is clamped in the battery bin 14, the speed regulator 7 is fixedly adhered to the speed regulator bracket through glue, the speed regulator 7 is an electronic speed regulator, the speed regulator 7 is respectively connected with the ducted fan 2 and the steering engine 5 through an electric connector, a BEC module on the electronic speed regulator can supply three-gear adjustable power supplies of 5.2V/6V/7.4V to the single-rotor unmanned aerial vehicle, the power supply problem of four steering engines on the single-rotor unmanned aerial vehicle is solved, and other steering engines are not required to be designed; meanwhile, the electronic speed regulator receives PWM wave signals output by the flight control unit to control the brushless motor in the ducted fan, so that the problem of a driving power supply of the motor on the single-rotor unmanned aerial vehicle is solved.
Example 2
The embodiment provides a fuselage bears formula single rotor unmanned aerial vehicle, on the basis of embodiment 1, as shown in fig. 6, the hold-in range wheelset includes big synchronizing wheel 10 and little synchronizing wheel 9 that hold-in range 15 connects, and little synchronizing wheel 9 passes through the screw shaft to be connected with steering wheel 5, and big synchronizing wheel 10 is connected with rudder blade shaft 11 of rudder blade 3, and rudder blade 3 passes through the bolt to be installed on rudder blade shaft 11, and big synchronizing wheel 10 sets up in loading platform 4 below.
The transmission ratio of the large synchronizing wheel 10 and the small synchronizing wheel 9 in the synchronizing belt wheel set is 1:3, the maximum deflection angle of the steering engine 5 is 300 degrees (+/-150 degrees), the maximum deflection angle of the rudder blade 3 is 100 degrees (+/-50 degrees), a space is reserved for the rudder blade 3 through the upper arrangement of the steering engine 5, the size of the rudder blade 3 is increased, the control force is improved, the speed and the moment are increased through the synchronizing belt wheel, the rotation synchronism of the rudder blade 3 and the steering engine 5 is ensured, the control force is prevented from exceeding the control direction of the steering engine 5, the steering engine 5 drives the rudder blade 3 to deflect for a certain angle, the air flow generated by the ducted fan 2 is reflected, the machine body is stabilized, the posture of the machine body is controlled, and the flying in any direction is realized.
Example 3
The embodiment provides a fuselage bears formula single rotor unmanned aerial vehicle, on the basis of embodiment 2, integrative formula fuselage 1 lower part is provided with guide plate 12, as shown in fig. 7, guide plate 12 is the barrel that the diameter is little big-end-up, and guide plate 12 lateral wall is smooth curved surface that has the radian, the diffusion, stable duct fan washes down the air current, make afterbody atress even, the cooperation jumbo size rudder page, further improve rudder blade's control force, promote control performance, be provided with the cross body that is located guide plate center pin in the guide plate 12, cross body center is connected with rudder blade axle 11 of rudder blade 3, provide central mounting point for rudder blade axle 11.
When the fuselage bearing type single-rotor unmanned aerial vehicle works, the ducted fan 2 rotates at a high speed to provide power, air is downwards escort to generate lift force to lift the fuselage, meanwhile, the steering engine 5 drives the rudder blade 3 to rotate, the rudder blade 3 reflects the downward washing air flow generated by the ducted fan 2 to offset the torque generated by the rotation of the ducted fan 2, the flying gesture of the unmanned aerial vehicle is also controlled by the rudder blade 3, the steering engine 5 drives the rudder blade 3 to rotate for a certain angle, and the rudder blade 3 reflects the tail air flow generated by the ducted fan 2 to control the fuselage gesture angle, so that the front, back, left and right flying of the unmanned aerial vehicle is realized.
According to the fuselage bearing type single-rotor unmanned aerial vehicle, the fuselage is a hollow cylindrical barrel, the bearing platform 4 is arranged in the middle of the fuselage, the axis of the ducted fan 2 coincides with the axis of the fuselage, the ducted fan penetrates through the bearing platform 4 and is connected with the fuselage through the power bracket 13, the four rudder blades 3 are installed in the fuselage below the bearing platform 4 and are connected with the steering engine 5 through the synchronous belt wheel group, and the fuselage bearing type single-rotor unmanned aerial vehicle has the characteristics of compact structure, high load, low cost, easiness in operation, high safety, high reliability, difficulty in damage and the like, reduces the probability of unmanned aerial vehicle injury and unmanned aerial vehicle flight accidents, and has stronger market competitiveness compared with the existing unmanned aerial vehicle.
Claims (8)
1. Fuselage bears formula single rotor unmanned aerial vehicle, including integrative formula fuselage (1) that bears, be provided with duct fan (2), steering wheel (5) and rudder blade (3) in integrative formula fuselage (1), its characterized in that, steering wheel (5) are connected with rudder blade (3) through the hold-in gear wheelset, integrative formula fuselage (1) are hollow cylinder barrel shape, be provided with loading platform (4) in integrative formula fuselage (1), steering wheel (5) set up on loading platform (4), just still be provided with power bracket (13), group battery (6), speedometer (7), horizontal gyroscope (8) on loading platform (4), group battery (6) are steering wheel (5), speedometer (7), horizontal gyroscope (8) power supply.
2. The fuselage-carrying single-rotor unmanned aerial vehicle according to claim 1, wherein the synchronous pulley group comprises a large synchronous pulley (10) and a small synchronous pulley (9) which are connected by a synchronous belt (15), the small synchronous pulley (9) is connected with the steering engine (5) through a threaded shaft, the large synchronous pulley (10) is connected with a rudder blade shaft (11) of the rudder blade (3), and the large synchronous pulley (10) is arranged below the carrying platform (4).
3. The fuselage-carrying single-rotor unmanned aerial vehicle according to claim 2, wherein the transmission ratio of the large synchronizing wheel (10) to the small synchronizing wheel (9) in the synchronizing wheel set is 1:3.
4. The fuselage-carrying single-rotor unmanned aerial vehicle according to claim 1, wherein the speed regulator (7) is an electronic speed regulator, and the speed regulator (7) is respectively connected with the ducted fan (2) and the steering engine (5) through electrical connectors.
5. The fuselage-carrying single-rotor unmanned aerial vehicle according to claim 1, wherein the carrying platform (4) is fixed with a speed regulator bracket, and the speed regulator (7) is adhered and fixed on the speed regulator bracket by glue.
6. The fuselage-carrying single-rotor unmanned aerial vehicle according to claim 1, wherein the carrying platform (4) is fixed with a battery compartment (14), and the battery pack (6) is clamped in the battery compartment (14).
7. The fuselage-carrying single-rotor unmanned aerial vehicle according to claim 1, wherein the rudder blade (3) is of a three-layer blade-superimposed structure.
8. The fuselage-carried single-rotor unmanned aerial vehicle according to claim 1, wherein the lower part of the fuselage (1) is provided with a deflector (12), the deflector (12) is a cylinder with a smaller diameter at the top and a larger diameter at the bottom, the side wall of the guide plate (12) is a smooth curved surface with radian, a cross body positioned on the central shaft of the guide plate is arranged in the guide plate (12), and the center of the cross body is connected with a rudder blade shaft (11) of the rudder blade (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321661503.4U CN220448159U (en) | 2023-06-28 | 2023-06-28 | Fuselage bearing type single-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321661503.4U CN220448159U (en) | 2023-06-28 | 2023-06-28 | Fuselage bearing type single-rotor unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN220448159U true CN220448159U (en) | 2024-02-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321661503.4U Active CN220448159U (en) | 2023-06-28 | 2023-06-28 | Fuselage bearing type single-rotor unmanned aerial vehicle |
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| Country | Link |
|---|---|
| CN (1) | CN220448159U (en) |
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2023
- 2023-06-28 CN CN202321661503.4U patent/CN220448159U/en active Active
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