CN112937852A - Vertical take-off and landing unmanned aerial vehicle power part structure and working method - Google Patents
Vertical take-off and landing unmanned aerial vehicle power part structure and working method Download PDFInfo
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- CN112937852A CN112937852A CN202110180999.2A CN202110180999A CN112937852A CN 112937852 A CN112937852 A CN 112937852A CN 202110180999 A CN202110180999 A CN 202110180999A CN 112937852 A CN112937852 A CN 112937852A
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- motor
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- unmanned aerial
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/80—Vertical take-off or landing, e.g. using rockets
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Control Of Motors That Do Not Use Commutators (AREA)
- Control Of Multiple Motors (AREA)
Abstract
The invention provides a power part structure of a vertical take-off and landing unmanned aerial vehicle and a working method, wherein the power part structure comprises the following steps: the device comprises a propeller, wings, a direct current brushless motor, a motor tilting base, a servo motor driving gear, a motor base driving gear and a servo motor; the screw is connected DC brushless motor upper end, DC brushless motor lower extreme is connected the motor base upper end that verts, the motor base lower extreme that verts is connected motor base drive gear, the wing side-mounting servo motor, servo motor connects servo motor drive gear, servo motor drive gear with motor base drive gear meshes. By adopting the FOC vector controller to drive the servo motor, the motion torque of the motor is stable, the noise is low, and the high-speed dynamic response is realized.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to a power part structure of a vertical take-off and landing unmanned aerial vehicle and a working method.
Background
The existing fixed-wing unmanned aerial vehicle cannot be suspended in the air, lifted off and landed, needs a longer runway when taking off and landing, has higher requirements on the lifting environment, and cannot be suspended in the air like a multi-rotor unmanned aerial vehicle. And although many rotor unmanned aerial vehicle can VTOL, can not carry out long-time flight and high-speed flight.
Publication number CN110382356A discloses an unmanned aerial vehicle's power component and unmanned aerial vehicle, wherein, power component includes: the propeller is fixedly connected with the propeller and is used for driving the propeller to rotate; the electric regulation component is electrically connected with the motor and used for controlling the motor to rotate; the electric adjusting assembly and the motor are arranged up and down, and the propeller is located above the electric adjusting assembly and the motor.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a power part structure of a vertical take-off and landing unmanned aerial vehicle and a working method.
According to the power part structure of the vertical take-off and landing unmanned aerial vehicle provided by the invention, the structure comprises: the device comprises a propeller, wings, a direct current brushless motor, a motor tilting base, a servo motor driving gear, a motor base driving gear and a servo motor;
the screw is connected DC brushless motor upper end, DC brushless motor lower extreme is connected the motor base upper end that verts, the motor base lower extreme that verts is connected motor base drive gear, the wing side-mounting servo motor, servo motor connects servo motor drive gear, servo motor drive gear with motor base drive gear meshes.
Preferably, the servo motor is a direct current brushless servo motor.
Preferably, the servo motor is connected with a FOC vector controller.
Preferably, the gear ratio of the servo motor driving gear to the motor base driving gear is 1: 2.
Preferably, the wing is of streamlined design.
Preferably, the brushless dc motor is connected to the motor tilting base through four M3 flat head screws.
Preferably, the propeller is connected with the dc brushless motor through a propeller fixing screw.
Preferably, the upper end of the motor tilting base is provided with a horizontal rod, a circular table top is arranged in the middle of the horizontal rod, and the upper surface of the circular table top is connected with the lower end of the brushless direct current motor.
Preferably, two ends of the horizontal rod extend downwards vertically to form two vertical rods, and the inner side of the lower end of each vertical rod is connected with the motor base driving gear.
The invention also provides a power part working method of the vertical take-off and landing unmanned aerial vehicle, which comprises the following steps:
step one, when the unmanned aerial vehicle takes off, the FOC vector controller drives the servo motor to work, the servo motor drives the servo motor driving gear, the servo motor drives the gear to rotate the motor base driving gear, the motor base driving gear drives the motor tilting base to tilt, the motor tilting base drives the propeller to tilt, so that the propeller tilts to be horizontal with the ground, the propeller starts to rotate, and the unmanned aerial vehicle starts to take off when the propeller reaches a certain rotating speed.
Step two: work as unmanned aerial vehicle accomplishes the lift of hanging down and takes off, when beginning high-speed flight, FOC vector controller drive servo motor work, servo motor drive gear, servo motor drive gear drive motor base drive gear rotates, motor base drive gear drive the motor base that verts, the motor base that verts drives the screw verts, makes the screw verts into and becomes vertical state with ground, and unmanned aerial vehicle obtains prorsad thrust, unmanned aerial vehicle's lift by the pressure differential of surface provides about the wing.
Step three: work as during unmanned aerial vehicle descends, FOC vector controller drive servo motor work, servo motor drive gear, servo motor drive gear drive motor base drive gear rotates, motor base drive gear drive the motor base that verts, the motor base that verts drives the screw verts, makes the screw incline turn into with ground one-tenth horizontality, the screw reduces the rotational speed, unmanned aerial vehicle descends, when unmanned aerial vehicle accomplishes and falls behind, the screw stall.
Compared with the prior art, the invention has the following beneficial effects:
1. by adopting the direct-current brushless servo motor, the starting torque can be improved, the response speed can be increased, and the torque can be output more stably.
2. By adopting the 1:2 gear set for transmission, the rotating torque can be improved, and the control precision is increased.
3. By adopting the FOC vector controller to drive the servo motor, the motion torque of the motor is stable, the noise is low, and the high-speed dynamic response is realized.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a perspective view (one) of a power part structure of a vertical take-off and landing unmanned aerial vehicle;
FIG. 2 is a front view of a power part structure of a VTOL UAV;
fig. 3 is a schematic perspective view (ii) of a power part structure of the vertical take-off and landing unmanned aerial vehicle.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1 and 2, a vertical take-off and landing unmanned aerial vehicle power part structure includes: the device comprises a propeller 1, wings 2, a direct current brushless motor 3, a motor tilting base 4, a servo motor driving gear 6, a motor base driving gear 7 and a servo motor 10; the propeller 1 is connected the 3 upper ends of direct current brushless motor, and the motor 4 upper ends of verting are connected to 3 lower extremes of direct current brushless motor, and motor base drive gear 7 is connected to 4 lower extremes of motor base that vert, 2 side-mounting servo motor 10 of wing, and servo motor drive gear 6 is connected to servo motor 10, and servo motor drive gear 6 meshes with motor base drive gear 7. The servo motor 10 is a direct current brushless servo motor, and the servo motor 10 is connected with an FOC vector controller. The gear ratio of the servo motor driving gear 6 to the motor base driving gear 7 is 1:2, and the wing 2 adopts a streamline design. The brushless DC motor 3 is connected with the motor tilting base 4 through four M3 flat head screws. The propeller 1 is connected with the brushless DC motor 3 through a propeller fixing screw 8. 4 upper ends of the motor tilting base are arranged to be horizontal rods, a circular table top is arranged in the middle of each horizontal rod, and the upper surface of the circular table top is connected with the lower end of the brushless direct current motor 3. Two vertical rods are arranged at the vertical and downward extending positions of the two ends of the horizontal rod, and the inner side of the lower end of each vertical rod is connected with a motor base driving gear 7.
As shown in fig. 3, a method for operating a power part of a vertical take-off and landing unmanned aerial vehicle comprises the following steps:
step one, when unmanned aerial vehicle takes off, FOC vector controller drive servo motor 10 work, servo motor 10 drive servo motor drive gear 6, servo motor drive gear 6 drive motor base drive gear 7 rotates, motor base drive gear 7 drive motor verts base 4, the motor verts base 4 and drives screw 1 and verts, make screw 1 incline become horizontal state with ground, screw 1 begins to rotate, unmanned aerial vehicle begins to take off when reaching certain rotational speed.
Step two: accomplish to hang down and take off when unmanned aerial vehicle, when the high-speed flight of beginning, FOC vector controller drive servo motor 10 work, servo motor 10 drive servo motor drive gear 6, servo motor drive gear 6 drive motor base drive gear 7 rotates, motor base drive gear 7 drive motor 4 that verts, the motor verts base 4 and drives screw 1 and verts, make screw 1 tilt become with ground one-tenth vertical state, unmanned aerial vehicle obtains forward thrust, unmanned aerial vehicle's lift is provided by the pressure differential of wing 2 upper and lower surfaces.
Step three: when unmanned aerial vehicle descends, FOC vector controller drive servo motor 10 work, servo motor 10 drive servo motor drive gear 6, servo motor drive gear 6 drive motor base drive gear 7 rotates, motor base drive gear 7 drive motor verts base 4, the motor verts base 4 and drives screw 1 and verts, make screw 1 incline turn into with ground one-tenth horizontality, screw 1 reduces the rotational speed, unmanned aerial vehicle descends, after unmanned aerial vehicle accomplishes and descends, screw 1 stall.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A vertical take-off and landing unmanned aerial vehicle power part structure is characterized by comprising: the aircraft comprises a propeller (1), wings (2), a direct current brushless motor (3), a motor tilting base (4), a servo motor driving gear (6), a motor base driving gear (7) and a servo motor (10);
screw (1) is connected DC brushless motor (3) upper end, DC brushless motor (3) lower extreme is connected the motor base (4) upper end that verts, the motor base (4) lower extreme that verts is connected motor base drive gear (7), wing (2) side-mounting servo motor (10), servo motor (10) are connected servo motor drive gear (6), servo motor drive gear (6) with motor base drive gear (7) meshing.
2. The vertical take-off and landing unmanned aerial vehicle power section structure of claim 1, wherein: the servo motor (10) adopts a direct-current brushless servo motor.
3. The vertical take-off and landing unmanned aerial vehicle power section structure of claim 1, wherein: the servo motor (10) is connected with an FOC vector controller.
4. The vertical take-off and landing unmanned aerial vehicle power section structure of claim 1, wherein: the gear ratio of the servo motor driving gear (6) to the motor base driving gear (7) is 1: 2.
5. The vertical take-off and landing unmanned aerial vehicle power section structure of claim 1, wherein: the wing (2) adopts a streamline design.
6. The vertical take-off and landing unmanned aerial vehicle power section structure of claim 1, wherein: the brushless DC motor (3) is connected with the motor tilting base (4) through four M3 flat head screws.
7. The vertical take-off and landing unmanned aerial vehicle power section structure of claim 1, wherein: the propeller (1) is connected with the direct current brushless motor (3) through a propeller fixing screw (8).
8. The vertical take-off and landing unmanned aerial vehicle power section structure of claim 1, wherein: the motor base (4) that verts upper end sets up to the horizon bar, set up to circular table face in the middle of the horizon bar, circular table face upper surface connection brushless DC motor (3) lower extreme.
9. The vertical take-off and landing unmanned aerial vehicle power section structure of claim 8, wherein: two vertical rods extend downwards from two ends of the horizontal rod vertically, and the inner side of the lower end of each vertical rod is connected with the motor base driving gear (7).
10. The working method of the power part structure of the vertical take-off and landing unmanned aerial vehicle as claimed in claim 1, comprising the following steps:
step one, when the unmanned aerial vehicle takes off, FOC vector controller drives servo motor (10) work, servo motor (10) drive servo motor drive gear (6), servo motor drive gear (6) drive motor base drive gear (7) rotate, motor base drive gear (7) drive motor base (4) of verting verts, motor base (4) of verting drive screw (1) verts, makes screw (1) incline become with ground one-tenth horizontality, screw (1) begin to rotate, unmanned aerial vehicle begins to take off when screw (1) reaches certain rotational speed.
Step two: work as unmanned aerial vehicle accomplishes the lift of hanging down and takes off, when beginning high-speed flight, FOC vector controller drive servo motor (10) work, servo motor (10) drive servo motor drive gear (6), servo motor drive gear (6) drive motor base drive gear (7) rotate, motor base drive gear (7) drive motor base (4) of verting verts, motor base (4) of verting drive screw (1) are verted, make screw (1) incline become with ground one-tenth vertical state, unmanned aerial vehicle obtains prorsad thrust, unmanned aerial vehicle's lift by the pressure differential of surface provides about wing (2).
Step three: work as during unmanned aerial vehicle descends, FOC vector controller drive servo motor (10) work, servo motor (10) drive servo motor drive gear (6), servo motor drive gear (6) drive motor base drive gear (7) rotate, motor base drive gear (7) drive base (4) that verts are verted to the motor, base (4) that verts are driven to the motor screw (1) verts, makes screw (1) incline become with ground one-tenth horizontality, screw (1) reduction in rotation speed, unmanned aerial vehicle descends, after unmanned aerial vehicle accomplishes to descend, screw (1) stall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110180999.2A CN112937852A (en) | 2021-02-08 | 2021-02-08 | Vertical take-off and landing unmanned aerial vehicle power part structure and working method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110180999.2A CN112937852A (en) | 2021-02-08 | 2021-02-08 | Vertical take-off and landing unmanned aerial vehicle power part structure and working method |
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| CN112937852A true CN112937852A (en) | 2021-06-11 |
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| CN202110180999.2A Pending CN112937852A (en) | 2021-02-08 | 2021-02-08 | Vertical take-off and landing unmanned aerial vehicle power part structure and working method |
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| WO2009044998A1 (en) * | 2007-10-02 | 2009-04-09 | Chaeho Lim | Taking off and landing airplane using variable rotary wings |
| CN206719540U (en) * | 2017-04-13 | 2017-12-08 | 大连云海创新科技有限公司 | Tilting rotor type VUAV based on Flying-wing |
| CN207089645U (en) * | 2017-08-04 | 2018-03-13 | 北京拓普空间科技有限公司 | A kind of energy-efficient electric power drives six rotor wing unmanned aerial vehicles |
| CN207997982U (en) * | 2018-03-15 | 2018-10-23 | 中国人民解放军国防科技大学 | Screw mechanism and VTOL fixed wing unmanned aerial vehicle vert |
| CN110382356A (en) * | 2018-04-23 | 2019-10-25 | 深圳市大疆创新科技有限公司 | The Power Component and unmanned plane of unmanned plane |
| KR20200080825A (en) * | 2018-12-27 | 2020-07-07 | 건국대학교 산학협력단 | Veryical takeoff and landing fixed wing unmanned aerial vehicle |
| CN111762316A (en) * | 2020-08-04 | 2020-10-13 | 西安电子科技大学 | Tilting component of tilting rotor unmanned aerial vehicle, tilting rotor unmanned aerial vehicle and using method |
| CN111762315A (en) * | 2020-08-04 | 2020-10-13 | 西安电子科技大学 | Tiltable rotor unmanned aerial vehicle and use method thereof |
-
2021
- 2021-02-08 CN CN202110180999.2A patent/CN112937852A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009044998A1 (en) * | 2007-10-02 | 2009-04-09 | Chaeho Lim | Taking off and landing airplane using variable rotary wings |
| CN206719540U (en) * | 2017-04-13 | 2017-12-08 | 大连云海创新科技有限公司 | Tilting rotor type VUAV based on Flying-wing |
| CN207089645U (en) * | 2017-08-04 | 2018-03-13 | 北京拓普空间科技有限公司 | A kind of energy-efficient electric power drives six rotor wing unmanned aerial vehicles |
| CN207997982U (en) * | 2018-03-15 | 2018-10-23 | 中国人民解放军国防科技大学 | Screw mechanism and VTOL fixed wing unmanned aerial vehicle vert |
| CN110382356A (en) * | 2018-04-23 | 2019-10-25 | 深圳市大疆创新科技有限公司 | The Power Component and unmanned plane of unmanned plane |
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| CN111762315A (en) * | 2020-08-04 | 2020-10-13 | 西安电子科技大学 | Tiltable rotor unmanned aerial vehicle and use method thereof |
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