CN209080150U - A kind of six rotor wing unmanned aerial vehicles - Google Patents
A kind of six rotor wing unmanned aerial vehicles Download PDFInfo
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- CN209080150U CN209080150U CN201821746573.9U CN201821746573U CN209080150U CN 209080150 U CN209080150 U CN 209080150U CN 201821746573 U CN201821746573 U CN 201821746573U CN 209080150 U CN209080150 U CN 209080150U
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Abstract
The utility model discloses a kind of six rotor wing unmanned aerial vehicles, including rack and pedestal, the inner cavity of the pedestal is fixedly connected with yielding rubber, the quantity of the yielding rubber is six, the yielding rubber is fixedly connected close to the side of rack with rack, and the two sides of the base bottom are symmetrically fixed with landing gear, and the bottom of landing gear is provided through landing bar, landing bar is fixedly connected with floor-type support frame far from one end of landing gear, and the surface of floor-type support frame is provided with fluorescence coating.The utility model has the advantages that carry out night illumination using solar power generation and landing stability is good, due to using lighter material and less structure, after adding lighting device, it still is able to guarantee the quality of six rotor wing unmanned aerial vehicles in suitable range, it is operated convenient for user, improves the enjoyment of operation, and improve stability in landing, and then the practicability of six rotor wing unmanned aerial vehicles is greatly improved, the function of six rotor wing unmanned aerial vehicles has been played well.
Description
Technical field
The utility model relates to air vehicle technique field, specially a kind of six rotor wing unmanned aerial vehicles.
Background technique
Six rotor wing unmanned aerial vehicles generally use power source of six rotors as aircraft, and six rotors are in same plane,
Adjacent two rotor, a rotation counterclockwise, one rotates clockwise, and to offset reaction torque active force, six motors are symmetrically pacified
Mounted in the stent ends of aircraft, and two rotors opposite on diagonal line are oppositely oriented, square signal on the workbench among bracket
Machine, GPS positioning module etc. are picked, middle layer lets row control calculator, electric current electricity tune circuit board fly away, and aircraft electrical is installed by lower layer
Pond, flight control calculator are the brains of six rotor wing unmanned aerial vehicles, and unmanned plane utilizes automatic control system, energy in flight course
It is enough that the configuration of aircraft, flight attitude and kinematic parameter are implemented to control, it is loaded with accelerometer, gyroscope, barometer, compass
Equal sensors, it controls the revolving speed of each motor and then controls the posture of aircraft, in addition GPS or the achievable fixed point of differential GPS
Hovering, the functions such as autonomous airline operation, parking space of the frame bottom reserved space as modular component are such as taken photo by plane required
Video camera and holder, the sensor module of real-time monitoring, water sampling device etc., six rotor wing unmanned aerial vehicle biggest advantages are to upgrade empty
Between it is wide, power is sufficient, and flight stability is good.
With the development of society, the purposes of unmanned plane also all the more extensively, needs constantly in night flying, however unmanned plane
It is always a biggish problem in night flying, the existing typically no lighting system of six rotor wing unmanned aerial vehicles, because of lighting system
Power consumption is big, and volume is big, is not convenient to use, and can make troubles to user, and in landing, stability is poor, thereby reduces
The practicability of six rotor wing unmanned aerial vehicles cannot play the function of six rotor wing unmanned aerial vehicles well.
Utility model content
The purpose of this utility model is to provide a kind of six rotor wing unmanned aerial vehicles, have and carry out night photograph using solar power generation
Advantage bright and that landing stability is good, solves the problems, such as to mention in above-mentioned background technique.
To achieve the above object, the utility model provides the following technical solutions: a kind of six rotor wing unmanned aerial vehicles, including rack and
Pedestal is fixedly connected with yielding rubber between rack and pedestal, the two sides of the base bottom are symmetrically fixed with landing gear, described
The bottom of landing gear is provided through landing bar, and the landing bar is fixedly connected with floor-type support frame far from one end of landing gear,
The surface of the floor-type support frame is provided with fluorescence coating, and the landing bar is fixedly connected with first far from one end of floor-type support frame
Damping damping mat, is fixedly connected with decoupling rod at the top of the first damping damping mat, and the outer sheath of the decoupling rod is equipped with subtracting
Shake spring, be fixedly connected with the second damping damping mat at the top of the damping spring, the top of the second damping damping mat with
Landing gear is fixedly connected, and the two sides at the top of the first damping damping mat are fixedly connected to positioning column, the landing gear it is interior
Chamber is provided with limited block, and the top of limited block is through at the top of the positioning column, and location hole, institute are offered on the limited block
It states location hole to be adapted with positioning column, the inner cavity of the landing gear offers limiting slot compatible with limited block.
The two sides of the limited block all extend to the inner cavity of limiting slot and are slidably connected with the inner wall of limiting slot, the rack
Surface be provided with first flange disk, the quantity of the first flange disk is six, and the first flange disk is bolted
It is connected with second flange disk, the side of the second flange disk is fixedly connected with rotor wings frame, and the rotor wings frame is far from second flange
One end of disk is fixedly connected with protection shell, is provided with rotor at the top of the protection shell.
It is fixedly connected with electric power box at the top of the rack, is fixedly connected with solar battery at the top of the electric power box
Plate, the bottom of the electric power box cavity have been fixed by screws battery fixing seat, the top of the battery fixing seat
It is fixedly connected with battery, first through hole is offered at the top of the electric power box, the two sides of the electric power box bottom offer
Second through-hole, inverter fixing seat is fixedly connected on the left of the electric power box cavity, and the top of the inverter fixing seat is solid
Surely it is connected with inverter, the bottom of the protection shell is fixedly connected with lamp holder, and the inner cavity of the lamp holder is provided with headlamp.
Preferably, the inner cavity of the headlamp is provided with aluminium layer.
Preferably, the solar panel and battery are electrically connected, the battery respectively with inverter and illumination
Lamp is electrically connected.
Preferably, the angle between the landing gear and pedestal is 105 °.
Preferably, the landing gear and landing bar are made of hollow aluminium alloy steel pipe, and the rack and rotor wings frame are adopted
Use carbon fibre materials.
Preferably, the inner cavity of the electric power box offers cavity, and the inverter and battery are respectively positioned on the inner cavity of cavity.
Preferably, the length of the landing gear is 2/3rds of landing pole length, and the length of the landing bar is greater than machine
The height of frame.
Preferably, the quantity of the yielding rubber is six.
Compared with prior art, the beneficial effects of the utility model are as follows:
1, the utility model passes through yielding rubber, landing gear, landing bar, floor-type support frame, fluorescence coating, the first damping damping
Pad, decoupling rod, positioning column, damping spring, the second damping damping mat, electric power box, solar panel, battery, first through hole,
Inverter and headlamp are used cooperatively, six rotor wing unmanned aerial vehicle, are had and are utilized solar power generation progress night illumination and landing
The good advantage of stability, due to still being able to guarantee six after adding lighting device using lighter material and less structure
The quality of rotor wing unmanned aerial vehicle operates in suitable range convenient for user, improves the enjoyment of operation, and landing
When improve stability, and then greatly improve the practicability of six rotor wing unmanned aerial vehicles, played six rotor wing unmanned aerial vehicles well
Function；
2, the utility model is enabled to six rotor wing unmanned aerial vehicle to have the effect of fluorescence, is made by the setting of fluorescence coating
It obtains user and quickly finds six rotor wing unmanned aerial vehicle when light is bad, increase the practicability of six rotor wing unmanned aerial vehicle, pass through
Positioning column and positioning hole are used cooperatively, and can be played the role of positioning to landing bar, be avoided landing bar and the feelings shaken occur
Condition increases the stability of landing bar, and then increases the stability of six rotor wing unmanned aerial vehicle, passes through limited block and limiting slot
It is used cooperatively, limit can be played the role of to landing bar, further increase the stability of landing bar；
3, the utility model is used cooperatively by solar panel, battery, inverter and headlamp, can be using too
Sun can be carried out power generation, and then provide illumination required electric energy in night flying, brings convenience to user, passes through cavity
Setting, can further decrease the quality of six rotor wing unmanned aerial vehicle, be conducive to extend the flight duration of six rotor wing unmanned aerial vehicles, pass through
The light refraction that headlamp issues can be gone out, improve the intensity of irradiation light by the setting of aluminium layer.
Detailed description of the invention
Fig. 1 is the schematic perspective view one of the utility model；
Fig. 2 is the schematic perspective view two of the utility model；
Fig. 3 is the schematic cross-sectional view of electric power box in the utility model；
Fig. 4 is the broken section structural schematic diagram of landing gear in the utility model；
Fig. 5 is the schematic perspective view of the utility model headlamp；
Fig. 6 is the partial structurtes enlarged drawing of A point in the utility model Fig. 1.
In figure: 1, rack；2, pedestal；3, yielding rubber；4, landing gear；5, land bar；6, floor-type support frame；7, fluorescence
Layer；8, the first damping damping mat；9, decoupling rod；10, positioning column；11, damping spring；12, the second damping damping mat；13, it positions
Hole；14, limited block；15, limiting slot；16, rotor wings frame；17, shell is protected；18, rotor；19, electric power box；20, solar battery
Plate；21, battery fixing seat；22, battery；23, first through hole；24, the second through-hole；25, inverter fixing seat；26, inversion
Device；27, lamp holder；28, headlamp；29, aluminium layer；30, first flange disk；31, second flange disk；32, cavity.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
Every other embodiment obtained, fall within the protection scope of the utility model.
Six rotor wing unmanned aerial vehicles of one kind are fixedly connected between rack 1 and pedestal 2 as shown, it includes rack 1 and pedestal 2
There is yielding rubber 3, the quantity of yielding rubber 3 is six, the two sides of 2 bottom of pedestal are symmetrically fixed with landing gear 4, landing gear 4
Bottom is provided through landing bar 5, and the bar 5 that lands is fixedly connected with floor-type support frame 6, floor-type support far from one end of landing gear 4
The surface of frame 6 is provided with fluorescence coating 7, and the bar 5 that lands is fixedly connected with the first damping damping mat 8 far from one end of floor-type support frame 6,
The top of first damping damping mat 8 is fixedly connected with decoupling rod 9, and the outer sheath of decoupling rod 9 is equipped with damping spring 11, damping spring
11 top is fixedly connected with the second damping damping mat 12, and the top of the second damping damping mat 12 is fixedly connected with landing gear 4, the
The two sides at the top of one damping damping mat 8 are fixedly connected to positioning column 10, and the length of decoupling rod 9 and positioning column 10 is less than damping bullet
The natural length (i.e. length of the damping spring 11 in uncompressed state) of spring 11 makes to stay between landing gear 4 and landing bar 5 in this way
There is certain buffer length, the inner cavity of landing gear 4 is provided with limited block 14, and the top of positioning column 10 is through to the top of limited block 14
Portion offers location hole 13 on limited block 14, and location hole 13 is adapted with positioning column 10, and the inner cavity of landing gear 4 offers and limits
The position compatible limiting slot 15 of block 14.
The two sides of the limited block 14 all extend to the inner cavity of limiting slot 15 and are slidably connected with the inner wall of limiting slot 15, machine
The surface of frame 1 is provided with first flange disk 30, and the quantity of first flange disk 30 is six, and first flange disk 30 is bolted
It is connected with second flange disk 31, the side of second flange disk 31 is fixedly connected with rotor wings frame 16, and rotor wings frame 16 is far from second flange
One end of disk 31 is fixedly connected with protection shell 17, and the top of protection shell 17 is provided with rotor 18.
The top of the rack 1 is fixedly connected with electric power box 19, and the top of electric power box 19 is fixedly connected with solar battery
Plate 20, the bottom of 19 inner cavity of electric power box have been fixed by screws battery fixing seat 21, the top of battery fixing seat 21
It is fixedly connected with battery 22, the top of electric power box 19 offers first through hole 23, and the two sides of 19 bottom of electric power box offer
Second through-hole 24, inverter fixing seat 25 is fixedly connected on the left of 19 inner cavity of electric power box, and the top of inverter fixing seat 25 is solid
Surely it is connected with inverter 26, the bottom of protection shell 17 is fixedly connected with lamp holder 27, and the inner cavity of lamp holder 27 is provided with headlamp 28.
In the utility model: the inner cavity of headlamp 28 is provided with aluminium layer 29, can be by headlamp by the setting of aluminium layer 29
28 light refractions issued are gone out, and the intensity of irradiation light is improved.
In the utility model: solar panel 20 and battery 22 are electrically connected, battery 22 respectively with inverter 26
It is electrically connected with headlamp 28.
In the utility model: the angle between landing gear 4 and pedestal 2 is 105 °, make landing gear 4 from the centre of pedestal 2 to
Two sides inclination, to increase the stability of strutting system of landing gear 4.
In the utility model: landing gear 4 and landing bar 5 are made of hollow aluminium alloy steel pipe, and rack 1 and rotor wings frame 16 are equal
It is made of carbon fibre materials.
In the utility model: the inner cavity of electric power box 19 offers cavity 32, and inverter 26 and battery 22 are respectively positioned on cavity
32 inner cavity can further decrease the quality of six rotor wing unmanned aerial vehicle by the setting of cavity 32, be conducive to extend six rotors
The flight duration of unmanned plane.
In the utility model: the length of landing gear 4 is 2/3rds of landing 5 length of bar, and the length of landing bar 5 is greater than machine
The height of frame 1.
In the utility model: headlamp 28 can be rotated in the inner cavity of lamp holder 27, carry out angle and direction adjusting.
Working principle: when the utility model is used, solar power generation, generated electricity are carried out by solar panel 20
Power is stored in battery 22, and battery 22 is by electric power distribution to headlamp 28, so that headlamp 28 is illuminated, user can
With the direction of illumination of adjusting illuminating lamp 28, after adjusting, then six rotor wing unmanned aerial vehicle is flown up at night, opens headlamp
28, it can be illuminated, when landing lands, floor-type support frame 6 pushes landing bar 5 to move upwards, and landing bar 5 pushes the first damping
Damping mat 8 moves upwards, and 8 compression shock absorption spring 11 of the first damping damping mat, damping spring 11 plays the effect of damping, and first subtracts
Shake damping mat 8 drives positioning column 10 to move upwards and contact with the second damping damping mat 12, and the second damping damping mat 12, which plays, to be subtracted
The effect of shake can protect the electric elements in six rotor wing unmanned aerial vehicles, extend the service life of six rotor wing unmanned aerial vehicles, positioning column
10 play the effect of positioning, and limited block 14 and limiting slot 15 play the effect of limit, thus reached using solar power generation into
Row night illumination and the good purpose of stability of landing.
In summary: six rotor wing unmanned aerial vehicle, by yielding rubber 3, landing gear 4, landing bar 5, floor-type support frame 6, glimmering
Photosphere 7, the first damping damping mat 8, decoupling rod 9, positioning column 10, damping spring 11, the second damping damping mat 12, electric power box 19,
Solar panel 20, battery 22, first through hole 23, inverter 26 and headlamp 28 are used cooperatively, and solve existing six
The typically no lighting system of rotor wing unmanned aerial vehicle, because lighting system power consumption is big, volume is big, is not convenient to use, can to user with
It is inconvenient to come, and in landing, stability is poor, thereby reduces the practicability of six rotor wing unmanned aerial vehicles, cannot play six well
The problem of rotor wing unmanned aerial vehicle function.
It should be noted that, in this document, it is left and right be the view direction shown by each attached drawing on the basis of, be located at and see
The person of examining left-hand side is left side, is right side positioned at observer's right-hand side.In addition, such as first and second or the like relationship art
Language is only used to distinguish one entity or operation from another entity or operation, without necessarily requiring or implying this
There are any actual relationship or orders between a little entities or operation.Moreover, the terms "include", "comprise" or its
What his variant is intended to non-exclusive inclusion, so that including the process, methods of a series of elements, article or setting
Standby includes not only those elements, but also including other elements that are not explicitly listed, or further includes for this process, side
Method, article or the intrinsic element of equipment.
The electric elements occurred in the application are electrically connected with extraneous main controller and 220V alternating current, and main controller can be
Computer etc. plays the conventionally known equipment of control.
While there has been shown and described that the embodiments of the present invention, for the ordinary skill in the art,
It is understood that these embodiments can be carried out with a variety of variations in the case where not departing from the principles of the present invention and spirit, repaired
Change, replacement and variant, the scope of the utility model is defined by the appended claims and the equivalents thereof.
Claims (8)
1. a kind of six rotor wing unmanned aerial vehicles, including rack (1) and pedestal (2), it is characterised in that: the rack (1) and pedestal (2) it
Between be fixedly connected with yielding rubber (3), the two sides of pedestal (2) bottom are symmetrically fixed with landing gear (4), the landing gear
(4) bottom is provided through landing bar (5), and landing bar (5) is fixedly connected with landing branch far from the one end of landing gear (4)
The surface of support (6), the floor-type support frame (6) is provided with fluorescence coating (7), and the landing bar (5) is far from floor-type support frame (6)
One end be fixedly connected with the first damping damping mat (8), be fixedly connected with decoupling rod at the top of the first damping damping mat (8)
(9), the outer sheath of the decoupling rod (9) is equipped with damping spring (11), and the is fixedly connected at the top of the damping spring (11)
The top of two damping damping mats (12), the second damping damping mat (12) is fixedly connected with landing gear (4), first damping
Two sides at the top of damping mat (8) are fixedly connected to positioning column (10), and the inner cavity of the landing gear (4) is provided with limited block
(14), it is through to the top of limited block (14) at the top of the positioning column (10), offers location hole on the limited block (14)
(13), the location hole (13) is adapted with positioning column (10), and the inner cavity of the landing gear (4) offers and limited block (14) phase
The limiting slot (15) of adaptation；
The two sides of the limited block (14) all extend to the inner cavity of limiting slot (15) and are slidably connected with the inner wall of limiting slot (15),
The surface of the rack (1) is provided with first flange disk (30), and the quantity of the first flange disk (30) is six, and described first
Ring flange (30) has been bolted to connection second flange disk (31), and the side of the second flange disk (31) is fixedly connected with
Rotor wings frame (16), the rotor wings frame (16) is fixedly connected with protection shell (17) far from the one end of second flange disk (31), described
Rotor (18) are provided at the top of protection shell (17)；
It is fixedly connected with electric power box (19) at the top of the rack (1), is fixedly connected with the sun at the top of the electric power box (19)
Energy solar panel (20), the bottom of electric power box (19) inner cavity has been fixed by screws battery fixing seat (21), described
It is fixedly connected at the top of battery fixing seat (21) battery (22), offers first through hole at the top of the electric power box (19)
(23), the two sides of electric power box (19) bottom offer the second through-hole (24), and the left side of electric power box (19) inner cavity is solid
Surely it is connected with inverter fixing seat (25), is fixedly connected with inverter (26) at the top of the inverter fixing seat (25), it is described
The bottom of protection shell (17) is fixedly connected with lamp holder (27), and the inner cavity of the lamp holder (27) is provided with headlamp (28).
2. a kind of six rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that: the inner cavity of the headlamp (28) is arranged
There are aluminium layer (29).
3. a kind of six rotor wing unmanned aerial vehicle according to claim 2, it is characterised in that: the solar panel (20) and storage
Battery (22) is electrically connected, and the battery (22) is electrically connected with inverter (26) and headlamp (28) respectively.
4. a kind of six rotor wing unmanned aerial vehicle according to claim 3, it is characterised in that: the landing gear (4) and pedestal (2) it
Between angle be 105 °.
5. a kind of six rotor wing unmanned aerial vehicle according to claim 4, it is characterised in that: the landing gear (4) and landing bar (5)
It is made of hollow aluminium alloy steel pipe, the rack (1) and rotor wings frame (16) are all made of carbon fibre materials.
6. a kind of six rotor wing unmanned aerial vehicle according to claim 5, it is characterised in that: the inner cavity of the electric power box (19) opens up
Have cavity (32), the inverter (26) and battery (22) are respectively positioned on the inner cavity of cavity (32).
7. a kind of six rotor wing unmanned aerial vehicle according to claim 6, it is characterised in that: the length of the landing gear (4) is drop
2/3rds of bar (5) length are fallen, the length of landing bar (5) is greater than the height of rack (1).
8. a kind of six rotor wing unmanned aerial vehicle according to claim 7, it is characterised in that: the quantity of the yielding rubber (3) is
Six.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821746573.9U CN209080150U (en) | 2018-10-26 | 2018-10-26 | A kind of six rotor wing unmanned aerial vehicles |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821746573.9U CN209080150U (en) | 2018-10-26 | 2018-10-26 | A kind of six rotor wing unmanned aerial vehicles |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209080150U true CN209080150U (en) | 2019-07-09 |
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ID=67120881
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821746573.9U Active CN209080150U (en) | 2018-10-26 | 2018-10-26 | A kind of six rotor wing unmanned aerial vehicles |
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| Country | Link |
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| CN (1) | CN209080150U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109050888A (en) * | 2018-10-26 | 2018-12-21 | 常州大学怀德学院 | A kind of six rotor wing unmanned aerial vehicles |
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2018
- 2018-10-26 CN CN201821746573.9U patent/CN209080150U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109050888A (en) * | 2018-10-26 | 2018-12-21 | 常州大学怀德学院 | A kind of six rotor wing unmanned aerial vehicles |
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