CN212047876U - Single-shaft double-propeller unmanned aerial vehicle - Google Patents
Single-shaft double-propeller unmanned aerial vehicle Download PDFInfo
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- CN212047876U CN212047876U CN202020178710.4U CN202020178710U CN212047876U CN 212047876 U CN212047876 U CN 212047876U CN 202020178710 U CN202020178710 U CN 202020178710U CN 212047876 U CN212047876 U CN 212047876U
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Abstract
The utility model provides a single-shaft double-propeller unmanned aerial vehicle, which comprises a shock-absorbing base and a coaxial double-propeller device arranged on the shock-absorbing base; the coaxial double-paddle device comprises a main shaft, and an inclined control disc assembly, a steering paddle seat, a moving cone, a power motor assembly and a power paddle seat which are coaxially mounted along the main shaft from bottom to top in sequence; a steering paddle component is arranged on the steering paddle seat, and a power paddle component is arranged on the power paddle seat; the double-rotating structure brushless motor is linked with the power paddle seat and the moving cone through the self-locking gear, and the moving cone is rotationally connected with the steering paddle seat; the base is provided with double servo motors, a power supply and a mounting hole, the main shaft is inserted in the mounting hole, and the power motor and the steering motor are respectively and electrically connected with the power supply; the double servo motors are connected with the control panel through a fisheye universal joint and a threaded pull rod, and the tilting disk assembly comprises an X-direction tilting disk and a Y-direction tilting disk which are used for controlling the variable pitch of the lower rotor. The embodiment of the utility model provides a simplify unmanned vehicles's structure, improved structure space's utilization ratio.
Description
Technical Field
The utility model belongs to the technical field of the unmanned air vehicle technique and specifically relates to a unipolar bispin oar unmanned aerial vehicle's small-size coaxial double-oar aircraft is related to.
Background
A coaxial double-propeller power mechanism adopted in the aviation technology is divided into an upper propeller layer and a lower propeller layer, and torsional moments generated by the two propellers rotating in different horizontal directions are mutually offset through the reverse rotation of the upper propeller layer and the lower propeller layer. Compared with a single-propeller power mechanism, the coaxial double-propeller power mechanism does not need to be provided with a tail propeller to counteract the problem that the single propeller generates unidirectional torque, is superior to the single-propeller power mechanism in space utilization rate, uses the lift force of two pairs of coaxial rotors 12% higher than that of the rotors with single rotor/tail propeller layout, has symmetrical aerodynamic characteristics and good maneuverability, and is more beneficial to attitude control of an aircraft, so that the coaxial double-propeller power mechanism is widely applied as a helicopter power system.
In the prior art, the inventor researches a coaxial double-paddle power mechanism, an inner control disc and an outer control disc are connected with an upper inclined disc and a lower inclined disc through a joint bearing, the upper inclined disc and the lower inclined disc are respectively connected with two variable pitch rods to control the blade pitch of an upper layer of rotor wing and a lower layer of rotor wing, and a sleeve shaft drives an upper rotor wing and a lower rotor wing which rotate reversely, so that the aircraft can fly forwards in an inclined mode and turn. The mechanism is extremely complex and high in assembly difficulty, and meanwhile, because the upper and lower pairs of contrarotating rotors are driven by the sleeve shaft, the requirement on the strength, rigidity and precision of the sleeve shaft is very high, so that the processing and manufacturing difficulty is very high, and the mechanism is often applied to large-scale aviation carriers. And coaxial double-oar power unit controls down oar displacement through steering gear control tilting tray down, and steering gear control goes up oar displacement must be earlier through controlling tilting tray down, and rethread link mechanism transmits the action to tilting tray, just can realize the control to the oar pitch of going up. Therefore, the structure of the coaxial double-paddle power mechanism is still to be improved.
SUMMERY OF THE UTILITY MODEL
The utility model provides a unipolar bispin oar unmanned aerial vehicle to solve the technical problem that current coaxial double-oar power unit structure is complicated, the embodiment of the utility model provides a can simplify unmanned vehicles's structure, improve structure space's utilization ratio.
In order to solve the technical problem, an embodiment of the utility model provides a single-shaft double-propeller unmanned aerial vehicle, which comprises a shock absorbing base and a coaxial double-propeller device installed on the shock absorbing base;
the coaxial double-paddle device comprises a main shaft, and an inclined control disc assembly, a steering paddle seat, a moving cone, a power motor assembly and a power paddle seat which are coaxially arranged along the main shaft from bottom to top in sequence;
the tilt control disc assembly comprises a control disc, a tilt disc assembly and a ball bearing arranged on the tilt disc assembly, and the ball bearing is connected with the steering paddle seat through a pull rod;
the steering paddle seat is provided with a steering paddle component, and the power paddle seat is provided with a power paddle component;
the power motor assembly comprises a double-rotating structure brushless motor and a self-locking gear, the double-rotating structure brushless motor is linked with the power paddle seat and the moving cone through the self-locking gear, and the moving cone is rotationally connected with the steering paddle seat;
the shock absorption base is provided with double servo motors, a power supply and a mounting hole, the main shaft is inserted into the mounting hole, and the power motor assembly and the double servo motors are respectively and electrically connected with the power supply;
two servo motor pass through fisheye universal joint and screw thread pull rod with the control panel is connected, the swash plate subassembly is including X to the swash plate and the Y to the swash plate that are used for controlling down the rotor displacement, X to the swash plate with Y is located to the swash plate on the control panel.
Preferably, the steering paddle assembly comprises a first steering paddle clamp, a second steering paddle clamp, a first steering paddle and a second steering paddle;
the first steering oar is hinged to one end of the steering oar seat through the first steering oar clamp, and the second steering oar is hinged to the other end of the steering oar seat through the second steering oar clamp.
As a preferred scheme, the power paddle component comprises a first power paddle clamp, a second power paddle clamp, a first power paddle and a second power paddle;
the first power paddle is hinged to one end of the power paddle seat through the first power paddle clamp, and the second power paddle is hinged to the other end of the power paddle seat through the second power paddle clamp.
As a preferred scheme, the shock-absorbing low seat comprises a base and an avionic cabin, wherein the base is connected with the avionic cabin through a plurality of shock-absorbing balls; the power supply is a battery, and the battery is arranged in the avionic cabin; the double servo motors are arranged between the avionics cabin and the base.
Preferably, the base and the spindle are fixed by screws.
Preferably, the power motor assembly further comprises a motor cover, and the double-rotation-structure brushless motor and the self-locking gear are mounted in the motor cover.
Compared with the prior art, the utility model discloses beneficial effect lies in:
(1) the upper and lower rotors are driven to rotate through the layout of the double longitudinal brushless motors, and the electronic speed regulator realizes the consistency of the upper and lower differential speeds, so that the upper and lower rotors can be synchronously started, and the mutual collision of the upper and lower rotors is avoided.
(2) Double longitudinal brushless motors are selected for use by the double-rotating-structure brushless motor, the power paddle seat above the linkage of the self-locking gear and the moving cone below the self-locking gear are arranged, the linkage gear is self-locked by reverse torque when the upper rotor wing and the lower rotor wing rotate, and the double-rotating-structure brushless motor has the advantage that mutual abrasion between the linkage gear and the power paddle seat and between the moving cones can be prevented when the rotor wings are locked.
(3) Two servo motor pass through the fisheye universal joint and are connected with the control panel by the screw rod, set up two sets of swash plates X, Y on the control panel, through the rotor displacement under the swash plate control, realize that the aircraft turns to and the translation, this design benefit lies in only using single swash plate control to turn to the base slope and realize down the rotor displacement, and rotor displacement about the link mechanism control that does not need to be complicated has reduced the complete machine height, has improved structure space's utilization ratio.
(4) Through setting up the base of moving away to avoid possible earthquakes, with coaxial double-oar power unit and avionics storehouse separation, vibrations when effectively reducing the power unit operation are conducted to flight control system, make avionics storehouse focus down all the time, are favorable to the aircraft to fly steadily.
Drawings
Fig. 1 is a schematic structural diagram of a single-shaft double-propeller unmanned aerial vehicle in an embodiment of the present invention;
fig. 2 is an exploded view of a single-shaft double-propeller unmanned aerial vehicle in an embodiment of the present invention;
fig. 3 is an exploded view of a single-shaft double-propeller unmanned aerial vehicle in an embodiment of the present invention;
wherein the reference numbers in the drawings of the specification are as follows:
1. a main shaft;
2. a power paddle seat; 21. a first powered paddle clamp; 22. a second powered paddle clamp; 23. a first powered paddle; 24. A second powered paddle;
3. a steering paddle mount; 31. a first steering paddle clamp; 32. a second steering paddle clamp; 33. a first steering paddle; 34. A second steering paddle;
4. a brushless motor with a double-rotation structure; 41. a motor cover; 42. a self-locking gear;
5. moving a cone; 51. a control panel; 52. an X-direction tilting disk; 53. a Y-direction tilting disk;
6. a fisheye gimbal; 61. a threaded pull rod;
7. a shock absorbing base; 71. a shock absorbing ball; 72. a dual servo motor; 73. an avionic cabin; 74. a battery.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
Referring to fig. 1 to 3, an embodiment of the present invention provides a single-shaft double-propeller unmanned aerial vehicle, which includes a shock absorbing base 7 and a coaxial double-propeller device installed on the shock absorbing base 7;
the coaxial double-oar device comprises a main shaft 1, and an inclined control disc assembly, a steering oar seat 3, a moving cone 5, a power motor assembly and a power oar seat 2 which are coaxially arranged along the main shaft 1 from bottom to top in sequence;
the tilting control disc assembly comprises a control disc 51, a tilting disc assembly and a ball bearing arranged on the tilting disc assembly, and the ball bearing is connected with the steering paddle seat 3 through a pull rod;
a steering paddle component is arranged on the steering paddle seat 3, and a power paddle component is arranged on the power paddle seat 2;
the power motor assembly comprises a double-rotation structure brushless motor 4 and a self-locking gear 42, the double-rotation structure brushless motor 4 is linked with the power paddle base 2 and the moving cone 5 through the self-locking gear 42, and the moving cone 5 is rotationally connected with the steering paddle base 3;
the shock absorption base 7 is provided with double servo motors, a power supply and a mounting hole, the main shaft 1 is inserted into the mounting hole, and the power motor assembly and the double servo motors are respectively and electrically connected with the power supply;
the servo motor is connected with the control panel 51 through a fish-eye universal joint 6 and a threaded pull rod 61, the tilting disk assembly comprises an X-direction tilting disk 52 and a Y-direction tilting disk 53 which are used for controlling the variable pitch of the lower rotor, and the X-direction tilting disk 52 and the Y-direction tilting disk 53 are arranged on the control panel 51.
In one possible design, the steering paddle assembly comprises a first steering paddle clip 31, a second steering paddle clip 32, a first steering paddle 33, a second steering paddle 34;
the first steering paddle 33 is hinged to one end of the steering paddle mount 3 by a first steering paddle clip 31, and the second steering paddle 34 is hinged to the other end of the steering paddle mount 3 by a second steering paddle clip 32.
In one possible design, the powered paddle assembly comprises a first powered paddle clip 21, a second powered paddle clip 22, a first powered paddle 23, a second powered paddle 24;
the first power paddle 23 is hinged on one end of the power paddle base 2 through the first power paddle clamp 21, and the second power paddle 24 is hinged on the other end of the power paddle base 2 through the second power paddle clamp 22.
In one possible design, the shock absorbing base 7 comprises a base and an avionics cabin 73, and the base is connected with the avionics cabin 73 through a plurality of shock absorbing balls 71; the power supply is a battery 74 (a lithium battery can be adopted), and the battery 74 is arranged in the avionics cabin 73; the servo motor is installed between the avionic bay 73 and the base.
In one possible design, the base is fixed to the spindle 1 by screws.
In a possible design, the power motor assembly further comprises a motor cover 41, and the double-rotation structure brushless motor 4 and the self-locking gear 42 are installed in the motor cover 41.
An object of the utility model is to provide a simple structure, the assembly is easy, flight is steady, the coaxial double-oar unmanned vehicles of collapsible paddle adopts the modularization equipment method, has simplified coaxial double-oar unmanned aerial vehicle's structure, and the reliability is high, and the assembly is easy, and the assembling process is as follows:
install tilt control dish 51 subassembly, turn to oar seat 3, move awl 5, power motor module, power oar seat 2 on unmanned aerial vehicle's hollow main shaft 1 from bottom to top along the axial in proper order, wherein the ball bearing that sets up on pull rod and the tilting disk between tilting disk subassembly and the steering oar seat 3 is connected to form transmission coupling mechanism in order to drive the control inclination of steering oar seat 3, realize down the oar displacement.
Further, the hollow spindle 1 is inserted into the hole of the shock absorbing base 7 and fixed.
Two screw holes are arranged in front of and behind the shock absorbing base 7 and used for installing and locking a fixing screw of the hollow main shaft 1.
To sum up, the embodiment of the utility model provides a pair of unipolar double-screw unmanned aerial vehicle is coaxial double-screw aircraft, and its beneficial effect lies in:
(1) the upper and lower rotors are driven to rotate through the layout of the double longitudinal brushless motors, and the electronic speed regulator realizes the consistency of the upper and lower differential speeds, so that the upper and lower rotors can be synchronously started, and the mutual collision of the upper and lower rotors is avoided.
(2) Double-rotor structure brushless motor 4 chooses for use double longitudinal brushless motor, and through setting up the power oar seat 2 of self-locking gear 42 linkage top and the dynamic cone 5 of below, reverse moment realizes linkage gear self-locking when rotor rotates from top to bottom, and the benefit of this design lies in can preventing when the rotor stalling that linkage gear and power oar seat 2, dynamic cone 5 wear each other.
(3) Two servo motor 72 are connected with control panel 51 by the screw rod through fisheye universal joint 6, set up two sets of swash plates X, Y on the control panel 51, through the rotor displacement under the swash plate control, realize that the aircraft turns to and the translation, this design benefit lies in only using single swash plate control to turn to the base slope and realize down the rotor displacement, and rotor displacement about the link mechanism control that does not need to be complicated, the whole height has been reduced, the utilization ratio of structure space has been improved.
(4) Through setting up base 7 of moving away to avoid possible earthquakes, with coaxial double-oar power unit and avionics storehouse 73 separation, vibrations when effectively reducing the power unit operation are conducted to flight control system, make avionics storehouse 73 focus down all the time, are favorable to the aircraft to fly steadily.
The foregoing is a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of improvements and decorations can be made without departing from the principle of the present invention, and these improvements and decorations are also considered as the protection scope of the present invention.
Claims (6)
1. A single-shaft double-propeller unmanned aerial vehicle is characterized by comprising a shock absorption base and a coaxial double-propeller device arranged on the shock absorption base;
the coaxial double-paddle device comprises a main shaft, and an inclined control disc assembly, a steering paddle seat, a moving cone, a power motor assembly and a power paddle seat which are coaxially arranged along the main shaft from bottom to top in sequence;
the tilt control disc assembly comprises a control disc, a tilt disc assembly and a ball bearing arranged on the tilt disc assembly, and the ball bearing is connected with the steering paddle seat through a pull rod;
the steering paddle seat is provided with a steering paddle component, and the power paddle seat is provided with a power paddle component;
the power motor assembly comprises a double-rotating structure brushless motor and a self-locking gear, the double-rotating structure brushless motor is linked with the power paddle seat and the moving cone through the self-locking gear, and the moving cone is rotationally connected with the steering paddle seat;
the shock absorption base is provided with double servo motors, a power supply and a mounting hole, the main shaft is inserted into the mounting hole, and the power motor assembly and the double servo motors are respectively and electrically connected with the power supply;
two servo motor pass through fisheye universal joint and screw thread pull rod with the control panel is connected, the swash plate subassembly is including X to the swash plate and the Y to the swash plate that are used for controlling down the rotor displacement, X to the swash plate with Y is located to the swash plate on the control panel.
2. The single-shaft, twin-propeller unmanned aerial vehicle of claim 1, wherein the steering paddle assembly comprises a first steering paddle clip, a second steering paddle clip, a first steering paddle, a second steering paddle;
the first steering oar is hinged to one end of the steering oar seat through the first steering oar clamp, and the second steering oar is hinged to the other end of the steering oar seat through the second steering oar clamp.
3. The single-shaft, twin-propeller unmanned aerial vehicle of claim 1, wherein the powered paddle assembly comprises a first powered paddle clip, a second powered paddle clip, a first powered paddle, a second powered paddle;
the first power paddle is hinged to one end of the power paddle seat through the first power paddle clamp, and the second power paddle is hinged to the other end of the power paddle seat through the second power paddle clamp.
4. The single-shaft double-propeller unmanned aerial vehicle of claim 1, wherein the shock absorbing base comprises a base and an avionic bay, the base being connected to the avionic bay by a plurality of shock absorbing balls; the power supply is a battery, and the battery is arranged in the avionic cabin; the double servo motors are arranged between the avionics cabin and the base.
5. The single-shaft, twin-propeller drone of claim 4, wherein the base is fixed to the main shaft by screws.
6. The single-shaft, twin-propeller unmanned aerial vehicle of claim 1 wherein the power motor assembly further comprises a motor cover, the dual-rotor brushless motor, the self-locking gear being mounted within the motor cover.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020178710.4U CN212047876U (en) | 2020-02-17 | 2020-02-17 | Single-shaft double-propeller unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202020178710.4U CN212047876U (en) | 2020-02-17 | 2020-02-17 | Single-shaft double-propeller unmanned aerial vehicle |
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| CN212047876U true CN212047876U (en) | 2020-12-01 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112498686A (en) * | 2020-12-23 | 2021-03-16 | 航天神舟飞行器有限公司 | Micro-miniature coaxial double-propeller unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112498686A (en) * | 2020-12-23 | 2021-03-16 | 航天神舟飞行器有限公司 | Micro-miniature coaxial double-propeller unmanned aerial vehicle |
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