CN111332463A - Counter-rotating vertical take-off and landing unmanned aerial vehicle - Google Patents
Counter-rotating vertical take-off and landing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN111332463A CN111332463A CN202010204899.4A CN202010204899A CN111332463A CN 111332463 A CN111332463 A CN 111332463A CN 202010204899 A CN202010204899 A CN 202010204899A CN 111332463 A CN111332463 A CN 111332463A
- Authority
- CN
- China
- Prior art keywords
- rotor
- support
- unmanned aerial
- plate
- aerial vehicle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000013016 damping Methods 0.000 claims abstract description 13
- 238000009434 installation Methods 0.000 claims abstract description 6
- 230000008878 coupling Effects 0.000 claims description 15
- 238000010168 coupling process Methods 0.000 claims description 15
- 238000005859 coupling reaction Methods 0.000 claims description 15
- 230000005540 biological transmission Effects 0.000 claims description 6
- 230000002093 peripheral effect Effects 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 3
- 238000005096 rolling process Methods 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 238000005265 energy consumption Methods 0.000 abstract description 2
- 230000035939 shock Effects 0.000 description 9
- 238000010521 absorption reaction Methods 0.000 description 7
- 230000000694 effects Effects 0.000 description 7
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/38—Constructions adapted to reduce effects of aerodynamic or other external heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention relates to a contra-rotating vertical take-off and landing unmanned aerial vehicle, belonging to the technical field of unmanned aerial vehicles; the device comprises a main body bracket and a contra-rotating structure, wherein the contra-rotating structure is coaxially arranged in the main body bracket; the main body support comprises a shell support, a first fixing frame, a second fixing frame, a motor support and a damping support; the shell support comprises a circular main body, a rectifying plate and a rectifying cone; the contra-rotating structure comprises a first rotor, a first connecting shaft disc, 2 first bevel gears, 2 second bevel gears, 3 pressure ball bearings, a second connecting shaft disc, a second rotor, a third connecting shaft disc and a direct current motor; firstly, the double rotors are utilized to generate mutually offset rotating torque to keep the unmanned aerial vehicle to stably run; the outer wall surface formed by the shell and each fixing frame and the surface of the rotor blade jointly form a relatively closed airflow channel, so that the problems of low propelling efficiency and safety of the open rotor wing are solved, and the open rotor wing has the characteristics of simplicity in installation, low energy consumption, high safety and the like.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a contra-rotating vertical take-off and landing unmanned aerial vehicle.
Background
In recent years, the market of civil small unmanned aerial vehicles is rapidly developed, and as one of the small unmanned aerial vehicles, the traditional multi-rotor unmanned aerial vehicle is well known by the public. Many rotor unmanned aerial vehicle indicates the unmanned aerial vehicle that has two and above rotors, and among the prior art, many rotor unmanned aerial vehicle rotate the rotor through every epaxial motor, and then produce the lift. However, in order to overcome the unidirectional rotation torque caused by the rotation of the rotor, the conventional unmanned aerial vehicle needs to be provided with at least two rotor motors, so that the heat loss of the motors in high-speed operation is multiplied, each motor must work simultaneously and cannot break down, and otherwise, the whole unmanned aerial vehicle can crash due to the rotation torque in the single direction which cannot be balanced. On the other hand, traditional unmanned aerial vehicle has shortcomings such as low propulsion efficiency and high danger owing to the adoption of a plurality of open rotors.
Disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the invention provides a counter-rotating vertical take-off and landing unmanned aerial vehicle, which overcomes the limitation that the unmanned aerial vehicle in the prior art must use multiple motors and multiple rotors simultaneously, reduces the energy consumption of the unmanned aerial vehicle, and solves the problems of low propelling efficiency and low safety of an open rotor.
The technical scheme of the invention is as follows: the utility model provides a to changeing unmanned aerial vehicle that takes off and land perpendicularly which characterized in that: the device comprises a main body bracket and a contra-rotating structure, wherein the contra-rotating structure is coaxially arranged in the main body bracket;
the main body support comprises a shell support, a first fixing frame, a second fixing frame, a motor support and a damping support; the shell support comprises a circular main body, a rectifying plate and a rectifying cone; the rectifying cone is of a circular truncated cone structure, the top surface of the rectifying cone is provided with a bearing column, four rectifying plates which are uniformly distributed along the circumferential direction are coaxially fixed on the inner ring surface of the circular main body and form a convergent airflow channel together with the inner wall surface of the shell support, and the longitudinal section of each rectifying plate is in a wing shape; four plate-shaped support arms are uniformly distributed on the upper ring surface of the circular main body along the circumferential direction, and a plurality of damping supports are arranged on the outer ring surface of the circular main body along the circumferential direction; the first fixing frame and the second fixing frame are two semicircular arc plates positioned on the same peripheral surface and are coaxially and fixedly arranged in the middle of the four plate-shaped support arms; a bearing rod is vertically fixed on the inner arc surface of the first fixing frame; the motor support is a hollow circular plate and is coaxially fixed at the upper parts of the four plate-shaped support arms;
the contra-rotating structure comprises a first rotor, a first connecting shaft disc, 2 first bevel gears, 2 second bevel gears, 3 pressure ball bearings, a second connecting shaft disc, a second rotor, a third connecting shaft disc and a direct current motor; the direct current motor is fixed on the upper surface of the center of the motor support, the second rotor is arranged below the center of the motor support through the third coupling disc and connected with an output shaft of the direct current motor, and the blade flow channel is anticlockwise seen from top to bottom and is driven to rotate through the direct current motor; one of the first bevel gears is coaxially fixed below a rotor disc of the second rotor through the second coupling disc; the first rotor is coaxially arranged on a bearing column of the rectifying cone through the pressure ball bearing, and a blade flow passage of the first rotor is clockwise when viewed from top to bottom; the other first bevel gear is coaxially fixed above the rotor disc of the first rotor through the first connecting shaft disc, so that 2 first bevel gears are coaxially and oppositely arranged; 2 the second bevel gear respectively through pressure ball bearing coaxial and relative installation in on the bearing rod of first mount, and be located two between the first bevel gear, make 2 the second bevel gear respectively with 2 first bevel gear meshes, thereby by the second rotor drives first rotor and rotates.
The further technical scheme of the invention is as follows: the shell bracket is provided with four damping brackets; the damping support is made of composite materials and comprises a supporting rod, a fixing plate and a bent plate; the upper ends of the two support rods are arranged on the outer ring surface of the circular ring-shaped main body through the fixing plate, and the lower ends of the two support rods are fixed with the bent plate.
The further technical scheme of the invention is as follows: the middle parts of two opposite support arms on the shell support are provided with through holes for penetrating through the bearing rods of the first fixing frame to realize the positioning of the bearing rods.
The further technical scheme of the invention is as follows: a disc for mounting the direct current motor is arranged in the center of the motor support and is fixed on a ring at the outer edge of the motor support through four support rods arranged along the circumferential direction; four positioning blocks are uniformly distributed on the peripheral surface of the circular ring along the circumferential direction and are matched with positioning grooves arranged at the upper parts of the four plate-shaped support arms; the four positioning blocks are respectively positioned in the extending directions of the four supporting rods.
The further technical scheme of the invention is as follows: the pressure ball bearings are composed of rolling bodies, a retainer, inner rings and outer rings, the outer surfaces of the outer rings are in interference fit with bearing holes for mounting the pressure ball bearings, two of the pressure ball bearings are respectively mounted at the center hole of the second bevel gear and symmetrically positioned on two sides of the central axis of the first rotor, and the other pressure ball bearing is mounted in the bearing hole on the lower surface of the first rotor and matched with a bearing column of the shell support.
The further technical scheme of the invention is as follows: the first bevel gear plate consists of a conical bevel gear plate and transmission rods, and the transmission rods of the two first bevel gears are respectively inserted into blind holes formed in the shaft ends of the first connecting shaft plate and the third connecting shaft plate and are fixed through set screws; the two first bevel gears are respectively and symmetrically positioned at two axial sides of the bearing rod of the first fixing frame.
The further technical scheme of the invention is as follows: a central through hole is formed in the center of the conical bevel gear disc of the second bevel gear and used for mounting the pressure ball bearing; and the two ends of the central axis of the first rotor are symmetrically positioned at the two sides of the central axis of the first rotor respectively.
The further technical scheme of the invention is as follows: the direct current motor is a brushless direct current motor.
Advantageous effects
The invention has the beneficial effects that: according to the contra-rotating vertical take-off and landing unmanned aerial vehicle, on the basis of only using one direct current motor, the contra-rotating of the double rotors is utilized to generate mutually offset rotating torque, so that the unmanned aerial vehicle is kept to stably run. The problem of among the prior art unmanned aerial vehicle must use the restriction of many rotors of many motors simultaneously, reduced unmanned aerial vehicle in the aspect of the heat production of motor to the outer wall that casing and each mount constitute constitutes relative confined airflow channel with rotor blade surface jointly, improve open rotor propulsion efficiency and security low is solved, have characteristics such as the installation is simple, the power consumption is low, the security is high.
Drawings
FIG. 1 is an overall schematic view of a contra-rotating vertical take-off and landing unmanned aerial vehicle according to the present invention;
FIG. 2 is a schematic view of a housing support for a counter-rotating vertical take-off and landing UAV of the present invention;
FIG. 3 is a schematic view of a first fixing frame of a contra-rotating vertical take-off and landing UAV of the present invention;
FIG. 4 is a schematic view of a second fixing frame of a contra-rotating vertical take-off and landing UAV of the present invention;
FIG. 5 is a schematic diagram of a contra-rotating structure of a contra-rotating vertical take-off and landing unmanned aerial vehicle of the invention;
FIG. 6 is a front view of a contra-rotating vertical take-off and landing unmanned aerial vehicle motor support of the present invention;
FIG. 7 is a schematic view of a first rotor of a counter-rotating VTOL UAV of the present invention;
FIG. 8 is a top view of a first rotor of a counter-rotating VTOL UAV of the present invention;
FIG. 9 is a front view of a shock mount for a counter-rotating VTOL UAV of the present invention;
FIG. 10 is a side view of a shock mount for a counter-rotating VTOL UAV of the present invention;
description of reference numerals: 1. the novel motor comprises a shell support, 2, a first fixing frame, 3, a second fixing frame, 4, a first rotor, 5, a first connecting shaft disc, 6, a first bevel gear, 7, a second bevel gear, 8, a pressure ball bearing, 9, a second rotor, 10, a motor support, 11, a direct current motor, 12, a damping support, 13, a positioning groove, 14, a first threaded hole, 15, a second threaded hole, 16, a positioning through hole, 17, a rectifying plate, 18, a rectifying cone, 19, a bearing rod, 20, a second connecting shaft disc, 21, a third connecting shaft disc, 22, a third threaded hole, 23, a motor hole, 24, a bearing column and 25, wherein the shell support is provided with a bearing hole.
Detailed Description
The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
This embodiment is a contra-rotating vertical take-off and landing unmanned aerial vehicle.
Referring to fig. 1 to 10, the present embodiment is composed of a housing bracket 1, a first fixing frame 2, a second fixing frame 3, a first rotor 4, a first coupling disc 5, a first bevel gear 6, a second bevel gear 7, a pressure ball bearing 8, a second coupling disc 20, a second rotor 9, a third coupling disc 21, a motor bracket 10, a dc motor 11, and a damping bracket 12.
The shell support 1 is an integrally formed thin-wall support, four rectifying plates 17 with the section shapes of wing-shaped sections are uniformly distributed on the inner side of the bottom along the circumferential direction, and the four rectifying plates 17 are used for adjusting the outlet airflow direction passing through the counter-rotating blades to form an airflow outlet flow passage on one hand and connecting a rectifying cone 18 with the shell support 1 on the other hand; the rectifying cone 18 is in a cone frustum shape, wherein the central axis of the rectifying cone coincides with the central axis of the shell support 1, and the central axis and the inner wall surface of the shell support form a convergent airflow channel together, so that the flow velocity of outlet airflow is improved, and further the thrust is increased; the central position of its upper surface is equipped with the bearing post 24 with pressure ball bearing 8 complex, and inside cavity is in order to reduce unmanned aerial vehicle quality.
Four groups of second threaded holes 15 are uniformly distributed at the bottom of the shell support 1, corresponding through holes are uniformly distributed at corresponding positions of the shock absorption support 12, screws penetrate through the through holes of the shock absorption support 12 and are connected with the second threaded holes 15 of the shell support 1 to play a role in connecting the shock absorption support 12 with the shell support 1, and the shock absorption support 12 is made of light composite materials; four plate-shaped support arms are uniformly distributed on the upper ring surface of the circular main body of the shell support 1 along the circumferential direction, six groups of first threaded holes 14 are formed in the middle parts of the four support arms, corresponding through holes are formed in corresponding positions of the first fixing frame 2 and the second fixing frame 3, so that the bearing rod 19 of the first fixing frame 2 penetrates through the positioning through holes 16 in the two opposite support arms to play a role in positioning the first fixing frame 2, and a screw penetrates through the through holes of the first fixing frame 2 and the second fixing frame 3 and is connected with the first threaded hole 14 of the shell support 1 to play a role in connecting the first fixing frame 2 and the second fixing frame 3 with the shell support 1; four locating slots 13 are arranged at the tops of the four support arms, and the extension parts of the four ends of the motor support 10 penetrate through the locating slots 13 to play a role in connecting the motor support 10 with the shell support 1.
The first fixing frame 2 is of a semicircular thin-wall structure, three groups of through holes are uniformly distributed in the wall surface, screws penetrate through the through holes of the first fixing frame 2 and are connected with the first threaded holes 14 of the shell support 1, the effect of connecting the first fixing frame 2 with the shell support 1 is achieved, and the bearing rod 19 penetrates through the positioning through holes 16 of the shell support 1 to achieve the effect of positioning the bearing rod 19.
The second fixing frame 3 is of a semicircular thin-wall structure, three groups of through holes are uniformly distributed in the wall surface, and the through holes of the second fixing frame 3 are penetrated by screws and are connected with the first threaded holes 14 of the shell support 1, so that the effects of connecting the second fixing frame 2 and the shell support 1 are achieved.
The motor support 10 is a hollow circular thin plate structure, and four positioning blocks are extended from the outer edge of the support at equal intervals and are respectively inserted into four positioning grooves 13 at the tops of four support arms of the shell support 1. The circular ribbed slab that motor support 10 is located the outer lane plays the effect of consolidating the cross support on the one hand, hugs closely the casing support inner wall during on the other hand installation, prevents that casing support 1 from because of receiving external force to inwards warp, plays the effect of inside and outside fixed casing support 1 with first mount 2 and second mount 3 jointly. Four threaded holes corresponding to the motor holes are equidistantly formed in the center of the motor support 10 and used for fixedly mounting the direct current motor 11.
The blade flow passage of the first rotor 4 is clockwise when viewed from top to bottom, a third threaded hole 22 for fixedly connecting the first connecting shaft disk 5 is formed in the upper surface of the rotor disk, and a bearing hole 25 for fixing the pressure ball bearing 8 is formed in the center of the lower surface of the rotor disk.
The first connecting shaft disc 5 is provided with five through holes corresponding to the third threaded holes 22 of the first rotor 4 on the disc surface, and screws penetrate through the through holes on the disc surface of the first connecting shaft disc 5 and are connected with the third threaded holes 22 of the first rotor 4, so that the first connecting shaft disc 5 and the first rotor 4 are connected; the shaft end is provided with a blind hole and a fastening screw hole which are respectively used for installing and fixing the first bevel gear 6.
The first bevel gears 6 are composed of two parts of a conical bevel gear disc and a transmission rod, the transmission rods of the two first bevel gears 6 are respectively inserted into blind holes formed in the shaft ends of the first connecting shaft disc 5 and the third connecting shaft disc 21 and are fixed through set screws, and the two first bevel gears 6 are respectively symmetrically positioned on two sides of the central axis of a bearing rod 19 in the first fixing frame 2 and are meshed with the two second bevel gears 7.
A through hole for installing a pressure ball bearing 8 is formed in the center of the conical bevel gear disc of the second bevel gear 7, the central axes of the two second bevel gears 7 are superposed with the central axis of the bearing rod 19 in the first fixing frame 2, are symmetrically arranged on two sides of the central axis of the first rotor 4 respectively, and are meshed with the two first bevel gears 6.
The pressure ball bearings 8 are composed of rolling bodies, a retainer, an inner ring and an outer ring, the outer surface of the outer ring is in interference fit with bearing holes, two of the pressure ball bearings 8 are respectively arranged in the center hole of the second bevel gear 7 and symmetrically positioned on two sides of the central axis of the first rotor 4, and the other pressure ball bearing 8 is arranged in a bearing hole 25 on the lower surface of the first rotor 4 and matched with a bearing column 24 of the shell support 1.
The second coupling disc 20 is provided with five through holes corresponding to the third threaded holes on the lower surface of the second rotor 9 on the disc surface, and the through holes are used for fixedly connecting the second coupling disc 20 and the second rotor 9; the shaft end is provided with a blind hole and a fastening screw hole which are respectively used for installing and fixing the first bevel gear 6.
The blade flow passage of the second rotor 9 is counterclockwise as viewed from top to bottom, a third threaded hole 22 for fixedly connecting the second coupling plate 20 is formed in the lower surface of the rotor plate, and a third threaded hole 22 for fixedly connecting the third coupling plate 21 is also formed in the upper surface of the rotor plate.
The third shaft coupling disc 21 is provided with five through holes corresponding to third threaded holes in the upper surface of the second rotor on the disc surface, and the through holes are used for fixedly connecting the third shaft coupling disc 21 and the second rotor 9; the shaft end is provided with a blind hole and a fastening screw hole which are respectively used for installing and fixing the direct current motor 10.
The direct current motor 11 is a brushless direct current motor, four motor holes 23 corresponding to the threaded holes of the motor support 10 are respectively formed in four corners of the bottom surface of the brushless direct current motor, and are used for fixedly connecting the direct current motor 11 and the motor support 10 and providing power for the first rotor 4 and the second rotor 9.
Four through holes corresponding to the second threaded holes 15 of the shell support 1 are formed in the top of the shock absorption support 12, and screws penetrate through the through holes of the shock absorption support 12 and are connected with the second threaded holes 15 of the shell support 1 to achieve the effects of connecting the shock absorption support 12 with the shell support 1.
Installation procedure of the embodiment
Four damping supports 12 are respectively connected and fixed on the periphery of the shell support 1 through screws, the angles of the damping supports 12 are adjusted to enable the shell support 1 to be kept horizontal, and the device is placed on a horizontal workbench. The disc surface of the first connecting shaft disc 5 and the upper surface of the first rotor 4 are respectively connected by screws, the disc surface of the second connecting shaft disc 20 and the lower surface of the second rotor 9, the disc surface of the third connecting shaft disc 21 and the upper surface of the second rotor 9, and then the two first bevel gears 6 are respectively installed and fixed at the shaft ends of the first connecting shaft disc 5 and the second connecting shaft disc 20 by using set screws. The pressure ball bearing 8 is mounted to a bearing hole on the lower surface of the first rotor 4, and the connected first bevel gear 6, the first connecting shaft disk 5 and the first rotor 4 are integrally mounted to a bearing column on the upper surface of the rectifying cone 18.
Then, two pressure ball bearings 8 are respectively installed in the central holes of the two second bevel gears 7, after a bearing rod of the first fixing frame 2 penetrates through a positioning through hole 16 on one side of the shell support 1, the two assembled pressure ball bearings 8 and the two assembled second bevel gears 7 are assembled in the support, the two second bevel gears 7 are meshed with the first bevel gear 6 at the bottom, then the end part of the bearing rod 19 is inserted into the positioning through hole 16 on the other side of the shell support 1, and the first fixing frame 2 and the shell support 1 are slightly connected through screws. Then the shaft end of the third coupling disc 21 passes through the central hole of the motor bracket 10, the direct current motor 11 is installed at the shaft end of the third coupling disc 21, and the fastening screw is screwed for fixing. And then, the extending parts at the four ends of the motor support 10 are respectively inserted into the positioning grooves of the shell support 1, so that the outer surface of the outermost circle of the circular rib plate of the motor support 10 is tightly attached to the inner surface of the shell support 1, then, screws for connecting the first fixing frame 2 and the shell support 1 are screwed, and finally, the second fixing frame 3 is installed.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (8)
1. The utility model provides a to changeing unmanned aerial vehicle that takes off and land perpendicularly which characterized in that: the device comprises a main body bracket and a contra-rotating structure, wherein the contra-rotating structure is coaxially arranged in the main body bracket;
the main body support comprises a shell support, a first fixing frame, a second fixing frame, a motor support and a damping support; the shell support comprises a circular main body, a rectifying plate and a rectifying cone; the rectifying cone is of a circular truncated cone structure, the top surface of the rectifying cone is provided with a bearing column, four rectifying plates which are uniformly distributed along the circumferential direction are coaxially fixed on the inner ring surface of the circular main body and form a convergent airflow channel together with the inner wall surface of the shell support, and the longitudinal section of each rectifying plate is in a wing shape; four plate-shaped support arms are uniformly distributed on the upper ring surface of the circular main body along the circumferential direction, and a plurality of damping supports are arranged on the outer ring surface of the circular main body along the circumferential direction; the first fixing frame and the second fixing frame are two semicircular arc plates positioned on the same peripheral surface and are coaxially and fixedly arranged in the middle of the four plate-shaped support arms; a bearing rod is vertically fixed on the inner arc surface of the first fixing frame; the motor support is a hollow circular plate and is coaxially fixed at the upper parts of the four plate-shaped support arms;
the contra-rotating structure comprises a first rotor, a first connecting shaft disc, 2 first bevel gears, 2 second bevel gears, 3 pressure ball bearings, a second connecting shaft disc, a second rotor, a third connecting shaft disc and a direct current motor; the direct current motor is fixed on the upper surface of the center of the motor support, the second rotor is arranged below the center of the motor support through the third coupling disc and connected with an output shaft of the direct current motor, and the blade flow channel is anticlockwise seen from top to bottom and is driven to rotate through the direct current motor; one of the first bevel gears is coaxially fixed below a rotor disc of the second rotor through the second coupling disc; the first rotor is coaxially arranged on a bearing column of the rectifying cone through the pressure ball bearing, and a blade flow passage of the first rotor is clockwise when viewed from top to bottom; the other first bevel gear is coaxially fixed above the rotor disc of the first rotor through the first connecting shaft disc, so that 2 first bevel gears are coaxially and oppositely arranged; 2 the second bevel gear respectively through pressure ball bearing coaxial and relative installation in on the bearing rod of first mount, and be located two between the first bevel gear, make 2 the second bevel gear respectively with 2 first bevel gear meshes, thereby by the second rotor drives first rotor and rotates.
2. The unmanned aerial vehicle for counter-rotating vertical take-off and landing according to claim 1, wherein: the shell bracket is provided with four damping brackets; the damping support is made of composite materials and comprises a supporting rod, a fixing plate and a bent plate; the upper ends of the two support rods are arranged on the outer ring surface of the circular ring-shaped main body through the fixing plate, and the lower ends of the two support rods are fixed with the bent plate.
3. The unmanned aerial vehicle for counter-rotating vertical take-off and landing according to claim 1, wherein: the middle parts of two opposite support arms on the shell support are provided with through holes for penetrating through the bearing rods of the first fixing frame to realize the positioning of the bearing rods.
4. The unmanned aerial vehicle for counter-rotating vertical take-off and landing according to claim 1, wherein: a disc for mounting the direct current motor is arranged in the center of the motor support and is fixed on a ring at the outer edge of the motor support through four support rods arranged along the circumferential direction; four positioning blocks are uniformly distributed on the peripheral surface of the circular ring along the circumferential direction and are matched with positioning grooves arranged at the upper parts of the four plate-shaped support arms; the four positioning blocks are respectively positioned in the extending directions of the four supporting rods.
5. The unmanned aerial vehicle for counter-rotating vertical take-off and landing according to claim 1, wherein: the pressure ball bearings are composed of rolling bodies, a retainer, inner rings and outer rings, the outer surfaces of the outer rings are in interference fit with bearing holes for mounting the pressure ball bearings, two of the pressure ball bearings are respectively mounted at the center hole of the second bevel gear and symmetrically positioned on two sides of the central axis of the first rotor, and the other pressure ball bearing is mounted in the bearing hole on the lower surface of the first rotor and matched with a bearing column of the shell support.
6. The unmanned aerial vehicle for counter-rotating vertical take-off and landing according to claim 1, wherein: the first bevel gear plate consists of a conical bevel gear plate and transmission rods, and the transmission rods of the two first bevel gears are respectively inserted into blind holes formed in the shaft ends of the first connecting shaft plate and the third connecting shaft plate and are fixed through set screws; the two first bevel gears are respectively and symmetrically positioned at two axial sides of the bearing rod of the first fixing frame.
7. The unmanned aerial vehicle for counter-rotating vertical take-off and landing according to claim 1, wherein: a central through hole is formed in the center of the conical bevel gear disc of the second bevel gear and used for mounting the pressure ball bearing; and the two ends of the central axis of the first rotor are symmetrically positioned at the two sides of the central axis of the first rotor respectively.
8. The unmanned aerial vehicle for counter-rotating vertical take-off and landing according to claim 1, wherein: the direct current motor is a brushless direct current motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010204899.4A CN111332463A (en) | 2020-03-22 | 2020-03-22 | Counter-rotating vertical take-off and landing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010204899.4A CN111332463A (en) | 2020-03-22 | 2020-03-22 | Counter-rotating vertical take-off and landing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111332463A true CN111332463A (en) | 2020-06-26 |
Family
ID=71176507
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010204899.4A Pending CN111332463A (en) | 2020-03-22 | 2020-03-22 | Counter-rotating vertical take-off and landing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111332463A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114735218A (en) * | 2022-04-12 | 2022-07-12 | 江苏信博建设项目管理有限公司 | Three-dimensional topography mapping device based on unmanned aerial vehicle |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5351913A (en) * | 1992-06-22 | 1994-10-04 | United Technologies Corporation | Coaxial transmission/center hub subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors |
| CN201089520Y (en) * | 2007-07-19 | 2008-07-23 | 樊文炎 | Gyroscope type vertically elevating flight device |
| CN104163241A (en) * | 2014-08-12 | 2014-11-26 | 中国航空工业经济技术研究院 | Unmanned logistics helicopter |
| CN105620740A (en) * | 2016-03-09 | 2016-06-01 | 西北工业大学 | Coaxial opposite-rotating dual-rotating-wing duct type vertical take-off and landing aircraft |
| CN206664928U (en) * | 2017-04-07 | 2017-11-24 | 南昌华梦达航空科技发展有限公司 | One kind can expand the dynamic culvert type coaxial double-oar unmanned vehicle of oil |
| CN206885349U (en) * | 2017-05-09 | 2018-01-16 | 西安交通大学 | A kind of all-electric coaxial more Rotor thrust devices |
| CN110356549A (en) * | 2018-04-09 | 2019-10-22 | 南京拓步智能科技有限公司 | A kind of single duct contrarotation formula double-rotor aerobat based on controllable deflector |
-
2020
- 2020-03-22 CN CN202010204899.4A patent/CN111332463A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5351913A (en) * | 1992-06-22 | 1994-10-04 | United Technologies Corporation | Coaxial transmission/center hub subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors |
| CN201089520Y (en) * | 2007-07-19 | 2008-07-23 | 樊文炎 | Gyroscope type vertically elevating flight device |
| CN104163241A (en) * | 2014-08-12 | 2014-11-26 | 中国航空工业经济技术研究院 | Unmanned logistics helicopter |
| CN105620740A (en) * | 2016-03-09 | 2016-06-01 | 西北工业大学 | Coaxial opposite-rotating dual-rotating-wing duct type vertical take-off and landing aircraft |
| CN206664928U (en) * | 2017-04-07 | 2017-11-24 | 南昌华梦达航空科技发展有限公司 | One kind can expand the dynamic culvert type coaxial double-oar unmanned vehicle of oil |
| CN206885349U (en) * | 2017-05-09 | 2018-01-16 | 西安交通大学 | A kind of all-electric coaxial more Rotor thrust devices |
| CN110356549A (en) * | 2018-04-09 | 2019-10-22 | 南京拓步智能科技有限公司 | A kind of single duct contrarotation formula double-rotor aerobat based on controllable deflector |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114735218A (en) * | 2022-04-12 | 2022-07-12 | 江苏信博建设项目管理有限公司 | Three-dimensional topography mapping device based on unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106004287A (en) | Amphibious multifunctional vertical take-off and landing aircraft | |
| CN103910066B (en) | Twin-engined coaxial unmanned helicopter in parallel | |
| CN102490897B (en) | Multi-driving embedded rotor manned helicopter | |
| US10745124B2 (en) | Rotor systems and methods | |
| CN101898635A (en) | Duct single screw aircraft based on Magnus effect | |
| CN111332463A (en) | Counter-rotating vertical take-off and landing unmanned aerial vehicle | |
| US6837457B2 (en) | Aircraft rotor and aircraft | |
| CN214776629U (en) | Vector coaxial handheld holder integrated unmanned aerial vehicle | |
| US12098696B2 (en) | Systems and methods for interleaved synchronous propeller system | |
| JP2013519022A (en) | High efficiency, high power vertical axis wind power generator | |
| CN211685575U (en) | Special-shaped equal-strength unmanned aerial vehicle arm | |
| CN112441229A (en) | Flapping rotor wing device with upward shaft wing capable of vertically running and downward horizontally running | |
| CN103395494B (en) | Dish-shaped helicopter | |
| CN208325622U (en) | Inclining rotary mechanism and aircraft for tiltrotor aircraft | |
| CN211001888U (en) | Four rotor unmanned aerial vehicle camera linkage | |
| CN213057502U (en) | High-speed flight unmanned vehicles that VTOL | |
| CN115061487A (en) | Aircraft and attitude control method and device thereof and related equipment | |
| CN108995793A (en) | A kind of rotary wing changing is away from system | |
| CN209852594U (en) | Propeller assembly and aircraft | |
| CN209053809U (en) | To counter-rotating fan | |
| CN111120182B (en) | Empennage self-yaw type half-rotation impeller water turbine | |
| CN210479010U (en) | Adjustable high-efficiency aerodynamic propeller | |
| CN109823523A (en) | A kind of coaxial double-oar aircraft | |
| CN210761238U (en) | Coaxial wide and narrow wing propulsion device | |
| CN110683041A (en) | Disc-shaped aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20200626 |