CN108408035A - A kind of high continuation of the journey multi-rotor unmanned aerial vehicle - Google Patents
A kind of high continuation of the journey multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN108408035A CN108408035A CN201810168651.XA CN201810168651A CN108408035A CN 108408035 A CN108408035 A CN 108408035A CN 201810168651 A CN201810168651 A CN 201810168651A CN 108408035 A CN108408035 A CN 108408035A
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- China
- Prior art keywords
- electric welding
- fuselage
- plate
- gear
- connecting rod
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Classifications
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- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C17/00—Aircraft stabilisation not otherwise provided for
-
- 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
- B64U2201/00—UAVs characterised by their flight controls
Abstract
The invention discloses a kind of high continuation of the journey multi-rotor unmanned aerial vehicles, its structure includes fuselage, balancing device, wing, motor, blade, holder, camera, undercarriage, balancing device is set to fuselage interior, balancing device is electrically connected with fuselage, wing is in be equally spaced with external fuselage and be connected by electric welding, motor is connected with wing by electric welding, blade is installed in motor top and is electrically connected with fuselage, holder is set to fuselage lower surface, holder is electrically connected with fuselage, camera is installed on holder surface and is electrically connected with fuselage, undercarriage is set to fuselage lower surface in symmetrical, undercarriage is connected with fuselage by electric welding.When unmanned plane is in high wind, power source mechanism can start the present invention automatically, by equipped with balancing device adjust the folding and unfolding and vibrations of unmanned plane wing, the rated wind velocity and equilibrant force of unmanned plane improved with this, effectively enhance the flying quality of unmanned plane.
Description
Technical field
The present invention is a kind of high continuation of the journey multi-rotor unmanned aerial vehicle, belongs to airmanship field.
Background technology
Unmanned plane abbreviation UAV (Unmanned Aerial Vehicle), refer to be not loaded with operating personnel can with autonomous flight or
The aircraft of remote driving.
Multi-rotor unmanned aerial vehicle is a kind of tool there are three and the above rotor shaft special pilotless helicopter.It passes through
Motor rotation on each axis, drives rotor, to generate a liter thrust.Rotor always away from fixation, rather than general helicopter
It is variable like that.By changing the relative rotation speed between different rotors, thus it is possible to vary the size of uniaxial propulsive force, to control flight
The running orbit of device.
But the prior art exists when unmanned plane flight in the air, and rated wind velocity is susceptible to unmanned plane crash phenomenon,
It remains to be further improved.
Invention content
In view of the deficienciess of the prior art, it is an object of the present invention to provide a kind of high continuation of the journey multi-rotor unmanned aerial vehicle, to solve
The prior art exists when unmanned plane flight in the air, and rated wind velocity is susceptible to unmanned plane crash phenomenon, needs further
Improved defect.
To achieve the goals above, the present invention is to realize by the following technical solutions：A kind of more rotors of high continuation of the journey without
Man-machine, structure includes fuselage, balancing device, wing, motor, blade, holder, camera, undercarriage, and the balancing device is set
In fuselage interior, the balancing device is electrically connected with fuselage, and the wing is in be equally spaced with external fuselage and by being welded phase
Connection, the motor are connected with wing by electric welding, and the blade is installed in motor top and is electrically connected with fuselage, the cloud
Platform is set to fuselage lower surface, and the holder is electrically connected with fuselage, and the camera is installed on holder surface and is electrically connected with fuselage,
The undercarriage is set to fuselage lower surface in symmetrical, and the undercarriage is connected with fuselage by electric welding, the balancing device
It is made of power source mechanism, main drive gear, damping, transmission mechanism, auxiliary power mechanism, regulating mechanism, the power
Source mechanism installation and lower part in fuselage, the main drive gear is set to above power source mechanism and is connected by engagement, described
Damping is set to above main drive gear and positioned at middle and upper part in fuselage, and the damping is connected with main drive gear swing
It connects, the transmission mechanism is set to main drive gear both sides in symmetrical, and the transmission mechanism is nibbled with main drive gear by gear
Conjunction is connected, and the auxiliary power mechanism is connect with transmission mechanism by being movably connected, and the regulating mechanism is set to auxiliary power machine
It is connected above structure and by transmission, the regulating mechanism is connect with wing by being movably connected.
Further, power source mechanism is by mounting bracket, sensor, mounting base, driving motor, electric connection socket, electric wire, rotation
Bar, bevel gear set are at above mounting bracket, the mounting base is set to fuselage interior and on sensor for the sensor installation
Side, the mounting base are connected with fuselage by electric welding, and the driving motor is installed on mounting base upper surface, the electric connection socket
Set on driving motor right lateral surface, the electric connection socket is connected with driving motor by bolt spiral, the electric connection socket with
Sensor is connected by electric wire, and the swingle is set to driving motor upper surface, and the swingle passes through electricity with driving motor
Weldering is connected, and the helical gear is set to swingle upper end face, and the helical gear is connected with swingle by electric welding.
Further, the main drive gear by bevel gear, head rod, rotating disk, the second connecting rod, transmission rope,
Movable block, supporting rod, arc gear wheel board group are set to helical gear rear at, the bevel gear and are connected by engagement, and described the
One connecting rod is set in the middle part of bevel gear front surface, and the head rod is vertically connected by electric welding with bevel gear and is connect, the rotation
Turntable is set to above bevel gear, and second connecting rod is set in the middle part of rotating disk front surface, second connecting rod and rotating disk
It is vertically connected and is connect by electric welding, the bevel gear is connected with rotating disk by being driven rope drive, and the movable block is rectangular
And it is set to the second connecting rod front-end surface, the movable block is connected with the second connecting rod by electric welding, and the supporting rod runs through
Movable block is in symmetry shape, and the supporting rod is connected with movable block by electric welding, and the arc-shaped gear wheel plate is equipped with two and is in pair
Shape is claimed to be set to supporting rod both ends, the arc-shaped gear wheel plate is connected with supporting rod by electric welding.
Further, the damping is by concave pad, limiting plate, hollow frame, motion bar, jacking block, first axle bar, fixed
Position plate, the first spring, top plate, chamber composition, the chamber are set to fuselage internal upper part, and the concave pad is set in chamber in upper wall
Portion, the concave pad remaining chamber room are connected by electric welding, and the limiting plate is set to concave in symmetry shape and pads both sides, the limiting plate
It is connected by electric welding with concave pad, middle part in chamber is welded in the hollow frame and is located at immediately below concave pad, the activity
Bar is connected with hollow frame by first axle bar, and the jacking block is set to motion bar rear surface, and the jacking block is logical with motion bar
It crosses electric welding to be connected, the jacking block is connected with arc-shaped gear wheel plate by pushing, and the positioning plate is set to hollow frame in symmetry shape
The left and right sides, the positioning plate are connected with hollow frame by electric welding, and the top plate is set to chamber interior, the top in symmetry shape
Plate is connected with chamber by electric welding, and the top plate is connected with positioning plate by the first spring.
Further, the transmission mechanism is by cluster gear, upper connecting rod, connecting plate, spring rope, inflator, push plate, lower connection
Bar, connecting tube composition, the upper connecting rod are set to gear plate upper surface, and the upper connecting rod is connected with gear plate by electric welding
It connects, the connecting plate is set to upper connecting rod upper end face and is located at chamber interior, and the connecting plate is with connecting rod by being welded phase
Connection, spring rope one end is connected in upper wall electric welding in chamber and the other end is connected with the electric welding of connecting plate upper surface, institute
It states inflator and is set to fuselage lower inner wall, the inflator is connected with fuselage by electric welding, and the push plate is set to inside inflator, described to push away
Plate is connected with inflator by fitting, and described lower connecting rod one end is set to push plate upper surface and electric welding is connected, the lower connection
The bar other end be set to cluster gear lower surface and by electric welding be connected, the connecting tube be set to inflator lower-left side surface and with auxiliary
Actuating unit electric welding is connected, and the connecting tube is connected with inflator by electric welding.
Further, the auxiliary power mechanism is by air bag seat, fixed frame, air bag, the first shaft, the first fixed plate,
Two springs form, and the fixed frame is set to air bag seat upper surface, and the fixed frame is connected with air bag seat by electric welding, the gas
It is top that capsule, which is set to air bag seat, and the air bag is integrated with air bag seat, and first shaft lower end is set in fixed frame
Portion, first fixed plate are set to the first shaft rear surface, and first fixed plate is connected with the first shaft by electric welding,
The second spring is equipped with two and one end and is connected by being welded with fixed frame lower surface, the second spring other end and the
One fixed plate upper surface is connected by electric welding.
Further, the regulating mechanism by disk, the second shaft, set block, second hinge bar, the first strut, second
Bar, sleeve, the second fixed plate, third spring composition, second shaft are set on the right side of disk front surface, second shaft with
Disk is connected by electric welding in horizontal direction, and first strut is connected with set block by second hinge bar, second shaft
The other end is connected with the first strut lower front surface by hinge, and second strut is horizontal to be set to the first strut upper end
Left side and it is connected by hinge, second fixed plate is set to the second strut right lateral surface and is located at sleeve inner, tells the
Two fixed plates are connected with the second strut by electric welding, and the third spring is set to sleeve inner, the third spring and sleeve
It is connected by electric welding.
Further, cluster gear is connected with arc-shaped gear wheel plate by engaging.
Advantageous effect
Operation signal is passed to unmanned plane by a kind of high continuation of the journey multi-rotor unmanned aerial vehicle of the present invention, earth station, and blade passes through electricity
Machine carries out rotation and unmanned plane is driven to fly upwards, and the scene taken by camera is transmitted to earth station by holder, works as nothing
Man-machine when encountering high wind situation in flight course, power source mechanism then starts automatically so that balancing device running, is carried with this
The wind resistance of high unmanned plane, driving motor receive the power source of sensor so that and helical gear starts to rotate in its effect, with
The bevel gear of helical gear engagement rotates with it, and drives rotating disk to be rotated by transmission rope, and damping is then in main transmission
Start the whole machine balancing that unmanned plane is adjusted with this under the rotation of mechanism, cluster gear carries out interval under the action of arc-shaped gear wheel plate
Property move up and down, air bag then under the inflation of inflator and air-extraction function expand, shrink, the first shaft being connect with disk is in gas
Moved up and down under the action of capsule, drive disk to carry out half and rotate, disk it is clockwise, rotate counterclockwise lower pulling machine
The wing so that wing carries out intermittent folding and unfolding at runtime, and wind resistance is improved with this；Conversely, driving motor is in sensor
Power source is lost under effect, helical gear stops operating, and the bevel gear engaged therewith is also simultaneously stopped rotation, passes through with it
The rotating disk that transmission rope is connected then stops operating, and transmission mechanism restores just under the interaction of arc-shaped gear wheel plate and spring rope
Beginning state, regulating mechanism inflator, second spring interaction under restPose.
A kind of high continuation of the journey multi-rotor unmanned aerial vehicle of the present invention, when unmanned plane is in high wind, power source mechanism can open automatically
It is dynamic, by equipped with balancing device adjust the folding and unfolding and vibrations of unmanned plane wing, the rated wind velocity of unmanned plane is improved with this
And equilibrant force, effectively enhance the flying quality of unmanned plane.
Description of the drawings
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon：
Fig. 1 is a kind of structural schematic diagram of high continuation of the journey multi-rotor unmanned aerial vehicle of the present invention.
Fig. 2 is a kind of structural schematic diagram of balancing device of the present invention.
Fig. 3 is a kind of detailed construction schematic diagram of balancing device of the present invention.
Fig. 4 is a kind of operating diagram of balancing device of the present invention.
In figure：Fuselage -1, balancing device -2, wing -3, motor -4, blade -5, holder -6, camera -7, undercarriage -8,
Power source mechanism -20, main drive gear -21, damping -22, transmission mechanism -23, auxiliary power mechanism -24, regulating mechanism -
25, mounting bracket -201, sensor -202, mounting base -203, driving motor -204, electric connection socket -205, electric wire -206, rotation
Bar -207, helical gear -208, bevel gear -210, head rod -211, rotating disk -212, the second connecting rod -213, transmission rope -
214, movable block -215, supporting rod -216, arc-shaped gear wheel plate -217, concave pad -220, limiting plate -221, hollow frame -222, work
Lever -223, jacking block -224, first axle bar -225, positioning plate -226, the first spring -227, top plate -228, chamber -229, tooth
Take turns block -230, upper connecting rod -231, connecting plate -232, spring rope -233, inflator -234, push plate -235, lower connecting rod -236,
Connecting tube -237, air bag seat -240, fixed frame -241, air bag -242, the first shaft -243, the first fixed plate -244, the second bullet
Spring -245, disk -250, the second shaft -251, set block -252, second hinge bar -253, the first strut -254, the second strut -
255, sleeve -256, the second fixed plate -257, third spring -258.
Specific implementation mode
To make the technical means, the creative features, the aims and the efficiencies achieved by the present invention be easy to understand, with reference to
Specific implementation mode, the present invention is further explained.
- Fig. 4 is please referred to Fig.1, the present invention provides a kind of high continuation of the journey multi-rotor unmanned aerial vehicle technical solution：Its structure includes fuselage
1, balancing device 2, wing 3, motor 4, blade 5, holder 6, camera 7, undercarriage 8, the balancing device 2 are set in fuselage 1
Portion, the balancing device 2 are electrically connected with fuselage 1, and the wing 3 is connected in being equally spaced with outside fuselage 1 and by electric welding,
The motor 4 is connected with wing 3 by electric welding, and the blade 5 is installed in 4 top of motor and is electrically connected with fuselage 1, the cloud
Platform 6 is set to 1 lower surface of fuselage, and the holder 6 is electrically connected with fuselage 1, and the camera 7 is installed on 6 surface of holder and and fuselage
1 electrical connection, the undercarriage 8 are set to 1 lower surface of fuselage in symmetrical, and the undercarriage 8 is connected with fuselage 1 by electric welding,
The balancing device 2 is by power source mechanism 20, main drive gear 21, damping 22, transmission mechanism 23, auxiliary power mechanism
24, regulating mechanism 25 forms, and the installation of power source mechanism 20 and lower part in fuselage 1, the main drive gear 21 are set to power
It is connected above source mechanism 20 and by engagement, the damping 22 is set to 21 top of main drive gear and in fuselage 1
Middle and upper part, the damping 22 are connected with the swing of main drive gear 21, and the transmission mechanism 23 is set to main biography in symmetrical
21 both sides of motivation structure, the transmission mechanism 23, which is engaged with main drive gear 21 by gear, to be connected, the auxiliary power mechanism
24 are connect with transmission mechanism 23 by being movably connected, and the regulating mechanism 25 is set to 24 top of auxiliary power mechanism and passes through transmission
It is connected, the regulating mechanism 25 is connect with wing by being movably connected, and the power source mechanism 20 is by mounting bracket 201, sensor
202, mounting base 203, driving motor 204, electric connection socket 205, electric wire 206, swingle 207, helical gear 208 form, the biography
Sensor 202 is installed with above mounting bracket 201, and the mounting base 203 is set to 1 inside of fuselage and positioned at 202 top of sensor, described
Mounting base 203 is connected with fuselage 1 by electric welding, and the driving motor 204 is installed on 203 upper surface of mounting base, described to be electrically connected
Joint chair 205 is set to 204 right lateral surface of driving motor, and the electric connection socket 205 is connected with driving motor 204 by bolt spiral
It connects, the electric connection socket 205 is connected with sensor 202 by electric wire 206, and the swingle 207 is set on driving motor 204
Surface, the swingle 207 are connected with driving motor 204 by electric welding, and the helical gear 208 is set to 207 upper end of swingle
Surface, the helical gear 208 are connected with swingle 207 by electric welding, and the main drive gear 21 is by bevel gear 210, first
Connecting rod 211, rotating disk 212, the second connecting rod 213, transmission rope 214, movable block 215, supporting rod 216, arc-shaped gear wheel plate 217
Composition, the bevel gear 210 are set to 208 rear of helical gear and are connected by engagement, and the head rod 211 is set to umbrella tooth
It takes turns in the middle part of 210 front surfaces, the head rod 211 is vertically connected by electric welding with bevel gear 210 and is connect, the rotating disk 212
Above bevel gear 210, second connecting rod 213 is set in the middle part of 212 front surface of rotating disk, second connecting rod 213
It is vertically connected and is connect by electric welding with rotating disk 212, the bevel gear 210 is connected with rotating disk 212 by the transmission of transmission rope 214
It connects, the movable block 215 is rectangular and is set to 213 front-end surface of the second connecting rod, the movable block 215 and the second connecting rod
213 are connected by electric welding, and the supporting rod 216 is in symmetry shape, the supporting rod 216 and movable block 215 through movable block 215
It is connected by electric welding, the arc-shaped gear wheel plate 217 is set is set to 216 both ends of supporting rod, the arc there are two and in symmetry shape
Gear plate 217 and supporting rod 216 are connected by electric welding, and the damping 22 is by concave pad 220, limiting plate 221, hollow
Frame 222, motion bar 223, jacking block 224, first axle bar 225, positioning plate 226, the first spring 227, top plate 228,229 groups of chamber
At the chamber 209 is set to 1 internal upper part of fuselage, and the concave pad 220 is set in chamber 209 in the middle part of upper wall, the concave pad
220 remaining chamber rooms 209 are connected by electric welding, and the limiting plate 221 is set to concave in symmetry shape and pads 220 both sides, the limiting plate
221 are connected with concave pad 220 by electric welding, and middle part in chamber 229 is welded in the hollow frame 222 and is located at concave pad 220
Underface, the motion bar 223 are connected with hollow frame 222 by first axle bar 225, and the jacking block 224 is set to motion bar
223 rear surfaces, the jacking block 224 are connected with motion bar 223 by electric welding, and the jacking block 224 is logical with arc-shaped gear wheel plate 217
It crosses promotion to be connected, the positioning plate 226 is set to 222 left and right sides of hollow frame, the positioning plate 226 and hollow frame in symmetry shape
222 are connected by electric welding, and the top plate 228 is set in symmetry shape inside chamber 229, and the top plate 228 passes through with chamber 229
Electric welding is connected, and the top plate 228 is connected with positioning plate 226 by the first spring 227, and the transmission mechanism 23 is by cluster gear
230, upper connecting rod 231, connecting plate 232, spring rope 233, inflator 234, push plate 235, lower connecting rod 236,237 groups of connecting tube
At the upper connecting rod 231 is set to 230 upper surface of gear plate, and the upper connecting rod 231 is connected with gear plate 230 by electric welding
Connect, the connecting plate 232 is set to 231 upper end face of upper connecting rod and inside the chamber 229, the connecting plate 232 with connect
Bar 231 is connected by electric welding, and described 233 one end of spring rope is connected and the other end and connection in upper wall electric welding in chamber 229
The electric welding of 232 upper surface of plate is connected, and the inflator 234 is set to 1 lower inner wall of fuselage, and the inflator 234 passes through electric welding with fuselage 1
It is connected, the push plate 235 is set to inside inflator 234, and the push plate 235 is connected with inflator 234 by fitting, under described
236 one end of connecting rod is set to 235 upper surface of push plate and electric welding is connected, and 236 other end of the lower connecting rod is set to cluster gear 230
Lower surface and be connected by electric welding, the connecting tube 237 be set to 234 lower-left side surface of inflator and with the electricity of auxiliary power mechanism 24
Weldering is connected, and the connecting tube 237 and inflator 234 are connected by electric welding, the auxiliary power mechanism 24 by air bag seat 240,
Fixed frame 241, air bag 242, the first shaft 243, the first fixed plate 244, second spring 245 form, and the fixed frame 241 is set to
240 upper surface of air bag seat, the fixed frame 241 are connected with air bag seat 240 by electric welding, and the air bag 242 is set to air bag seat
240 be top, and the air bag 242 is integrated with air bag seat 240, and 243 lower end of the first shaft is set to fixed frame 241
Inside, first fixed plate 244 are set to 243 rear surface of the first shaft, first fixed plate, 244 and first shaft 243
It is connected by electric welding, the second spring 245 is equipped with two and one end is connected with 241 lower surface of fixed frame by electric welding,
245 other end of the second spring is connected with 244 upper surface of the first fixed plate by electric welding, and the regulating mechanism 25 is by disk
250, the second shaft 251, set block 252, second hinge bar 253, the first strut 254, the second strut 255, sleeve 256, second are solid
Fixed board 257, third spring 258 form, and second shaft 251 is set on the right side of 250 front surface of disk, second shaft 251
It is connect in horizontal direction with disk 250 by being welded, first strut 254 is connected with set block 252 by second hinge bar 253
It connects, 251 other end of the second shaft is connected with 254 lower front surface of the first strut by hinge, second strut 255
Horizontal to be set on the left of 254 upper end of the first strut and be connected by hinge, second fixed plate 257 is set to the second strut
255 right lateral surfaces and inside the sleeve 256, tell that the second fixed plate 257 is connected with the second strut 255 by being welded, institute
Third spring 258 is stated inside sleeve 256, the third spring 258 is connected with sleeve 256 by electric welding, the gear
Block 230 is connected with arc-shaped gear wheel plate 217 by engaging.
Balancing device described in this patent is mainly used for improving the wind resistance of unmanned plane and mitigate caused by flight
Vibrations.
It is carrying out in use, operation signal is passed to unmanned plane by earth station, blade 5 carries out rotation drive by motor 4
Unmanned plane flies upwards, and the scene taken by camera 7 is transmitted to earth station by holder 6, when unmanned plane was flying
When encountering high wind situation in journey, power source mechanism 20 is then automatic to be started so that balancing device 2 operates, and unmanned plane is improved with this
Wind resistance, driving motor 204 receive the power source of sensor 202 so that and helical gear 208 starts to rotate in its effect, with
The bevel gear 210 that helical gear 208 engages rotates with it, and drives rotating disk 212 to be rotated by transmission rope 214, damping machine
Structure 22 then starts the whole machine balancing that unmanned plane is adjusted with this under the rotation of main drive gear 21, and cluster gear 230 is in arc-shaped gear
Carried out under the action of wheel plate 217 it is intermittent move up and down, air bag 242 then under the inflation of inflator 234 and air-extraction function expansion,
It shrinks, the first shaft 243 being connect with disk 250 is moved up and down under the action of air bag 242, and disk 250 is driven to carry out
Half rotates, 25 disk 250 it is clockwise, rotate counterclockwise lower pulling wing 3 so that wing 3 carries out intermittence at runtime
Folding and unfolding, wind resistance is improved with this；Conversely, driving motor 204 loses power source, helical teeth under the action of sensor 202
Wheel 208 stops operating, the bevel gear 210 engaged therewith is also simultaneously stopped rotation, is connected by transmission rope 214 with it
Rotating disk 212 then stops operating, and transmission mechanism 23 restores initial under the interaction of arc-shaped gear wheel plate 217 and spring rope 233
State, regulating mechanism 25 inflator 234, second spring 245 interaction under restPose.
The present invention solves the prior art when unmanned plane flight in the air, rated wind velocity, is susceptible to unmanned plane crash
Phenomenon remains to be further improved, and the present invention is combined with each other by above-mentioned component when unmanned plane is in high wind, power source machine
Structure can start automatically, by equipped with balancing device adjust the folding and unfolding and vibrations of unmanned plane wing, unmanned plane is improved with this
Rated wind velocity and equilibrant force, effectively enhance the flying quality of unmanned plane.
The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention, for this field skill
For art personnel, it is clear that invention is not limited to the details of the above exemplary embodiments, and without departing substantially from the present invention spirit or
In the case of essential characteristic, the present invention can be realized in other specific forms.Therefore, in all respects, should all incite somebody to action
Embodiment regards exemplary as, and is non-limiting, the scope of the present invention by appended claims rather than on state
Bright restriction, it is intended that including all changes that come within the meaning and range of equivalency of the claims in the present invention
It is interior.Any reference signs in the claims should not be construed as limiting the involved claims.
In addition, it should be understood that although this specification is described in terms of embodiments, but not each embodiment is only wrapped
Containing an independent technical solution, this description of the specification is merely for the sake of clarity, and those skilled in the art should
It considers the specification as a whole, the technical solutions in the various embodiments may also be suitably combined, forms those skilled in the art
The other embodiment being appreciated that.
Claims (8)
1. a kind of high continuation of the journey multi-rotor unmanned aerial vehicle, structure includes fuselage (1), balancing device (2), wing (3), motor (4), paddle
Leaf (5), holder (6), camera (7), undercarriage (8), it is characterised in that：
The balancing device (2) is set to fuselage (1) inside, and the balancing device (2) is electrically connected with fuselage (1), the wing (3)
In being equally spaced external with fuselage (1) and being connected by electric welding, the motor (4) is connected with wing (3) by electric welding, institute
It states blade (5) to be installed in motor (4) top and be electrically connected with fuselage (1), the holder (6) is set to fuselage (1) lower surface, described
Holder (6) is electrically connected with fuselage (1), and the camera (7) is installed on holder (6) surface and is electrically connected with fuselage (1), described
It falls frame (8) and is set to fuselage (1) lower surface in symmetrical, the undercarriage (8) is connected with fuselage (1) by electric welding；
The balancing device (2) by power source mechanism (20), main drive gear (21), damping (22), transmission mechanism (23),
Auxiliary power mechanism (24), regulating mechanism (25) composition, power source mechanism (20) installation and fuselage (1) interior lower part, it is described
Main drive gear (21) is set to above power source mechanism (20) and is connected by engagement, and the damping (22) is set to main biography
Above motivation structure (21) and it is located at fuselage (1) interior middle and upper part, the damping (22) is connected with main drive gear (21) swing
It connects, the transmission mechanism (23) is set to main drive gear (21) both sides, the transmission mechanism (23) and main transmission machine in symmetrical
Structure (21) is connected by gear engagement, and the auxiliary power mechanism (24) is connect with transmission mechanism (23) by being movably connected, institute
Regulating mechanism (25) is stated above auxiliary power mechanism (24) and is connected by transmission, the regulating mechanism (25) and wing
It is connect by being movably connected.
2. a kind of high continuation of the journey multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：The power source mechanism (20)
By mounting bracket (201), sensor (202), mounting base (203), driving motor (204), electric connection socket (205), electric wire (206),
Swingle (207), helical gear (208) composition, sensor (202) installation and mounting bracket (201) top, the mounting base
(203) it is set to fuselage (1) inside and above sensor (202), the mounting base (203) passes through with fuselage (1) is welded phase
Connection, the driving motor (204) are installed on mounting base (203) upper surface, and the electric connection socket (205) is set to driving motor
(204) right lateral surface, the electric connection socket (205) are connected with driving motor (204) by bolt spiral, the electric connection socket
(205) it is connected by electric wire (206) with sensor (202), the swingle (207) is set to driving motor (204) upper surface,
The swingle (207) is connected with driving motor (204) by electric welding, and the helical gear (208) is set on swingle (207)
End surfaces, the helical gear (208) are connected with swingle (207) by electric welding.
3. a kind of high continuation of the journey multi-rotor unmanned aerial vehicle according to claim 1 or 2, it is characterised in that：The main drive gear
(21) by bevel gear (210), head rod (211), rotating disk (212), the second connecting rod (213), transmission rope (214), work
Motion block (215), supporting rod (216), arc-shaped gear wheel plate (217) composition, the bevel gear (210) are set to helical gear (208) rear
And be connected by engagement, the head rod (211) is set in the middle part of bevel gear (210) front surface, the head rod
(211) it is vertically connected and is connect by electric welding with bevel gear (210), the rotating disk (212) is set to above bevel gear (210), described
Second connecting rod (213) is set in the middle part of rotating disk (212) front surface, and second connecting rod (213) passes through with rotating disk (212)
Electric welding, which is vertically connected, to be connect, and the bevel gear (210) is connected with rotating disk (212) by transmission rope (214) transmission, the activity
Block (215) is rectangular and is set to the second connecting rod (213) front-end surface, the movable block (215) and the second connecting rod (213)
It is connected by electric welding, the supporting rod (216) is in symmetry shape, the supporting rod (216) and movable block through movable block (215)
(215) it is connected by electric welding, the arc-shaped gear wheel plate (217) sets is set to supporting rod (216) both ends there are two and in symmetry shape,
The arc-shaped gear wheel plate (217) is connected with supporting rod (216) by electric welding.
4. a kind of high continuation of the journey multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：The damping (22) by
Concave pad (220), hollow frame (222), motion bar (223), jacking block (224), first axle bar (225), is determined limiting plate (221)
Position plate (226), the first spring (227), top plate (228), chamber (229) composition, the chamber (209) be set to fuselage (1) on
Portion, the concave pad (220) are set in the middle part of the interior upper wall of chamber (209), and concave pad (220) the remaining chamber room (209) passes through electric welding
It is connected, the limiting plate (221) is set to concave pad (220) both sides, the limiting plate (221) and concave pad in symmetry shape
(220) it is connected by electric welding, under middle part in chamber (229) is welded in the hollow frame (222) and is located at concave pad (220) just
Side, the motion bar (223) are connected with hollow frame (222) by first axle bar (225), and the jacking block (224), which is set to, to be lived
Lever (223) rear surface, the jacking block (224) are connected with motion bar (223) by electric welding, the jacking block (224) and arc
Shape gear plate (217) is connected by pushing, and the positioning plate (226) is set in symmetry shape at left and right sides of hollow frame (222), institute
It states positioning plate (226) with hollow frame (222) to be connected by electric welding, the top plate (228) is set in symmetry shape in chamber (229)
Portion, the top plate (228) are connected with chamber (229) by electric welding, and the top plate (228) passes through first with positioning plate (226)
Spring (227) is connected.
5. a kind of high continuation of the journey multi-rotor unmanned aerial vehicle according to claim 1 or 4, it is characterised in that：The transmission mechanism
(23) by cluster gear (230), upper connecting rod (231), connecting plate (232), spring rope (233), inflator (234), push plate (235),
Lower connecting rod (236), connecting tube (237) composition, the upper connecting rod (231) are set to gear plate (230) upper surface, the upper company
Extension bar (231) is connected with gear plate (230) by electric welding, and the connecting plate (232) is set to upper connecting rod (231) upper end face
And it is internal positioned at chamber (229), the connecting plate (232) is connected with connecting rod (231) by electric welding, the spring rope
(233) one end is connected in the interior upper wall electric welding of chamber (229) and the other end is connected with the electric welding of connecting plate (232) upper surface, institute
It states inflator (234) and is set to fuselage (1) lower inner wall, the inflator (234) is connected with fuselage (1) by electric welding, the push plate
(235) it is set to inflator (234) inside, the push plate (235) is connected with inflator (234) by fitting, the lower connecting rod
(236) one end is set to push plate (235) upper surface and electric welding is connected, and lower connecting rod (236) other end is set to cluster gear
(230) lower surface and it is connected by electric welding, the connecting tube (237) is set to inflator (234) lower-left side surface and dynamic with auxiliary
Force mechanisms (24) electric welding is connected, and the connecting tube (237) is connected with inflator (234) by electric welding.
6. a kind of high continuation of the journey multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：The auxiliary power mechanism
(24) by air bag seat (240), fixed frame (241), air bag (242), the first shaft (243), the first fixed plate (244), the second bullet
Spring (245) forms, and the fixed frame (241) is set to air bag seat (240) upper surface, the fixed frame (241) and air bag seat (240)
It is connected by electric welding, it is top, the air bag (242) and air bag seat (240) that the air bag (242), which is set to air bag seat (240),
It is integrated, the first shaft (243) lower end is set to fixed frame (241) inside, and first fixed plate (244) is set to
First shaft (243) rear surface, first fixed plate (244) and the first shaft (243) are connected by electric welding, and described the
Two springs (245) are equipped with two and one end is connected with fixed frame (241) lower surface by electric welding, the second spring (245)
The other end is connected with the first fixed plate (244) upper surface by electric welding.
7. a kind of high continuation of the journey multi-rotor unmanned aerial vehicle according to claim 1 or 6, it is characterised in that：The regulating mechanism
(25) by disk (250), the second shaft (251), set block (252), second hinge bar (253), the first strut (254), second
Bar (255), sleeve (256), the second fixed plate (257), third spring (258) composition, second shaft (251) are set to disk
(250) on the right side of front surface, second shaft (251) is connect by being welded in horizontal direction with disk (250), first strut
(254) it is connected by second hinge bar (253) with set block (252), the second shaft (251) other end and the first strut
(254) lower front surface is connected by hinge, and second strut (255) is horizontal to be set to the first strut (254) upper end
Left side and it is connected by hinge, second fixed plate (257) is set to the second strut (255) right lateral surface and is located at sleeve
(256) internal, tell that the second fixed plate (257) is connected with the second strut (255) by electric welding, the third spring (258)
Internal set on sleeve (256), the third spring (258) is connected with sleeve (256) by electric welding.
8. a kind of high continuation of the journey multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：The cluster gear (230) with
Arc-shaped gear wheel plate (217) is connected by engagement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810168651.XA CN108408035A (en) | 2018-02-28 | 2018-02-28 | A kind of high continuation of the journey multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810168651.XA CN108408035A (en) | 2018-02-28 | 2018-02-28 | A kind of high continuation of the journey multi-rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108408035A true CN108408035A (en) | 2018-08-17 |
Family
ID=63129487
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810168651.XA Withdrawn CN108408035A (en) | 2018-02-28 | 2018-02-28 | A kind of high continuation of the journey multi-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108408035A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229351A (en) * | 2018-09-11 | 2019-01-18 | 林荣东 | A kind of quadrotor drone using the self-holding weighing apparatus of additional rotor double infection |
| CN111717405A (en) * | 2020-06-23 | 2020-09-29 | 长沙航华电子科技有限公司 | Buoyancy auxiliary lifting device for unmanned aerial vehicle |
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| CN105416577A (en) * | 2015-12-09 | 2016-03-23 | 施恒锦 | Multi-rotor unmanned aerial vehicle |
| CN205854465U (en) * | 2016-08-03 | 2017-01-04 | 泛洲科技（北京）有限公司 | A kind of low windage unmanned plane |
| CN205971831U (en) * | 2016-08-22 | 2017-02-22 | 深圳一电航空技术有限公司 | Six unmanned aerial vehicle |
| CN206031770U (en) * | 2016-08-29 | 2017-03-22 | 江苏工程职业技术学院 | Anti -wind type cube unmanned aerial vehicle device |
| CN106525375A (en) * | 2016-10-21 | 2017-03-22 | 国网山东省电力公司电力科学研究院 | Self-adaptation system for detecting anti-wind capability of unmanned plane |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105416577A (en) * | 2015-12-09 | 2016-03-23 | 施恒锦 | Multi-rotor unmanned aerial vehicle |
| CN205854465U (en) * | 2016-08-03 | 2017-01-04 | 泛洲科技（北京）有限公司 | A kind of low windage unmanned plane |
| CN205971831U (en) * | 2016-08-22 | 2017-02-22 | 深圳一电航空技术有限公司 | Six unmanned aerial vehicle |
| CN206031770U (en) * | 2016-08-29 | 2017-03-22 | 江苏工程职业技术学院 | Anti -wind type cube unmanned aerial vehicle device |
| CN106525375A (en) * | 2016-10-21 | 2017-03-22 | 国网山东省电力公司电力科学研究院 | Self-adaptation system for detecting anti-wind capability of unmanned plane |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109229351A (en) * | 2018-09-11 | 2019-01-18 | 林荣东 | A kind of quadrotor drone using the self-holding weighing apparatus of additional rotor double infection |
| CN111717405A (en) * | 2020-06-23 | 2020-09-29 | 长沙航华电子科技有限公司 | Buoyancy auxiliary lifting device for unmanned aerial vehicle |
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Application publication date: 20180817 |