CN208181413U - A kind of steady damping multi-rotor unmanned aerial vehicle fuselage box - Google Patents
A kind of steady damping multi-rotor unmanned aerial vehicle fuselage box Download PDFInfo
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- CN208181413U CN208181413U CN201820711336.2U CN201820711336U CN208181413U CN 208181413 U CN208181413 U CN 208181413U CN 201820711336 U CN201820711336 U CN 201820711336U CN 208181413 U CN208181413 U CN 208181413U
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- fuselage
- body housing
- frame
- aerial vehicle
- unmanned aerial
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Abstract
The utility model relates to multi-rotor unmanned aerial vehicle technical fields, specifically, it is related to a kind of steady damping multi-rotor unmanned aerial vehicle fuselage box, body housing including polygon, fuselage load box and battery frame have been sequentially arranged in the body housing, the body housing upper end is additionally provided with upper flap, so, in the application, when multi-rotor unmanned aerial vehicle landing, the vibration absorption unit that support rod bottom is equipped with can be mediated according to road conditions, when having protrusion under the vibration absorption unit at this, vibration absorption unit stress herein is larger, amount of spring compression is got higher, when vibration absorption unit at this has recessed behaviour, vibration absorption unit stress herein is smaller, damping block can stretch out one section of groove compensated at this compared with other positions more, so that multi-rotor unmanned aerial vehicle is steadily stablized in descent, it can be suitable for complex road condition.
Description
Technical field:
The utility model relates to multi-rotor unmanned aerial vehicle technical fields, and in particular, to a kind of steady more rotors of damping nobody
Machine fuselage box.
Background technique:
Multi-rotor unmanned aerial vehicle is that there are two rotary wing aircrafts more than rotor shaft for a kind of tool.By the motor of each shaft end
Rotation drives rotor to generate lifting power.The angle of rotor is fixed variable like that rather than helicopter.By changing not
It can change the torque of propulsive force with the relative velocity between rotor, to control the running track of aircraft.Due to more rotors
Fairly simple stabilization, currently practiced Multi-axis aircraft external form is much smaller with respect to for aircraft, thus is suitble to amateurish use.Because
Multi-axis aircraft is easy to manufacture and controls, so being commonly used to production model and remotely-piloted vehicle.It common are four axis, six axis, eight
Axis aircraft.Its small in size, light-weight therefore easy to carry, the various adverse circumstances that can be not easily accessible easily into people.Hair
By now, the aerial missions such as film of taking photo by plane finds a view, monitors in real time, landform is explored have can be performed in Multi-axis aircraft for exhibition.
With the development of electronic multi-rotor unmanned aerial vehicle, the application field of multi-rotor unmanned aerial vehicle is more and more wider, the ruler of unmanned plane
Very little and weight is also stepped up, and the performance requirement unmanned plane overall structure rigidity of multi-rotor unmanned aerial vehicle flight control computer is good at present
Good, in order to meet rigidity requirement, current most of multi-rotor unmanned aerial vehicle fuselages use circular layout mode, use shell in structure
The mode of whole load uses carbon fibre composite on material more.
It has been observed that most of electronic multi-rotor unmanned aerial vehicle fuselages use circular layout type at present, used in structure outer
The mode of shell entirety load uses carbon fibre composite on material more.This master-plan has the disadvantage in that
1, power battery shape is Cubic at this stage, places space utilization rate not in ball or circular arc type fuselage
It is high.
2, due to fuselage interior space utilization rate bottom, cause airborne equipment installation dispersion, need many cables to equipment into
Row connection, increases the weight of cable.
3, fuselage is by the way of shell entirety load, and in order to ensure stiffness of fuselage, body shell is very thick, increases structure
Weight.
4, it in order to install airborne equipment, needs to beat mounting hole on fuselage cover, destroys shell load path, reduce
Structural strength.
5, round fuselage soaks that area is excessive, is easy the interference by prominent wind, reduces the safety of aircraft.
6, part type in order to mitigate weight use thin skin structure type.In order to avoid bring due to covering is thin
Stiffness of fuselage reduces, and is glued carbon fiber sheet as structure-bearing part in fuselage interior, increases full machine producting process difficulty.
7, multi-rotor unmanned aerial vehicle is in descent, and since landing place road conditions are different, there are in more rotor descents
Larger in the presence of shaking, there are when broken terrain at landing place, multi-rotor unmanned aerial vehicle even presence is turned on one's side
Situation.
Utility model content:
The utility model overcomes the deficiencies of existing technologies, and provides a kind of steady damping multi-rotor unmanned aerial vehicle fuselage box.
Technical problem to be solved in the utility model is implemented with the following technical solutions: a kind of steady more rotors of damping without
Man-machine fuselage box, the body housing including polygon have been sequentially arranged fuselage load box and battery frame, the machine in the body housing
Body shell upper end is additionally provided with upper flap, and the body housing bottom end is additionally provided with carry plate, and the open slot that carry plate two sides are equipped with is used
In arrangement undercarriage；The undercarriage includes fixing end, and the fixing end is connected firmly in body housing bottom end, and fixing end lower end is hinged
There is connecting rod, the connecting rod is pierced by via open slot, and the one end of connecting rod far from fixing end is also horizontal to be equipped with support rod；It is described
Support rod bottom face arranged for interval has several vibration absorption units, and the vibration absorption unit includes accommodating of the arranged for interval on support rod
Chamber, the accommodating cavity is interior to be equipped with damping block, is additionally provided with spring in accommodating cavity, the spring one end is pressed on accommodating cavity bottom end, bullet
The spring other end is pressed on damping block.
Preferably, the body housing is hexagonal structure, and body housing includes fuselage frame and covering, and the covering is coated on
Fuselage outer frame surface, the inwardly protruding formation carrier strip in fuselage frame lower end, the carrier strip is two, and the symmetrical cloth of carrier strip
It sets in fuselage frame bottom two sides, each carrier strip one end close to each other is additionally provided with flange, and the fuselage load box is equipped with
Connecting plate stick on flange.
Preferably, the frame of the fuselage load box generally hexagon shape, fuselage load box are integrally embedded in body housing
Interior, fuselage load box side wall corresponding with the carrier strip bottom end is equipped with and the lower fixed strip of carrier strip cooperation, the connection
Lower fixed strip side close to each other is arranged in plate, and fuselage load box upper end and lower fixed strip opposite position are additionally provided with fixation
Item, fixed item and battery frame lower end connect firmly.
Preferably, fuselage frame side, which is additionally provided with, engraves hole for reducing own wt.
Preferably, integrally hexagonal frame structure, battery frame upper end are additionally provided with embedded in battery frame one end the battery frame
Rectangular bearing frame, on rectangular bearing frame between upper fixed strip corresponding section and upper fixed strip via carbon pipe and hexagonal cup head
Screw connects firmly, and through-hole is additionally provided on the battery frame side wall, the corresponding arrangement of the through-hole on the through-hole and fuselage shell side wall, described
Rectangular bearing frame upper end is additionally provided with partition, and the rectangular space that each partition and fuselage shell side wall are enclosed is for installing electricity
Pond.
Preferably, a gram horse button is additionally provided on the lateral wall of the body housing upper end, the upper flap is buckled in via a gram horse buckle
Body housing upper end.
Compared with prior art, the application has the beneficial effect that
1, in the application, when multi-rotor unmanned aerial vehicle landing, vibration absorption unit that support rod bottom is equipped with can according to road conditions into
Row is reconciled, and when having protrusion under the vibration absorption unit at this, vibration absorption unit stress herein is larger, and amount of spring compression is got higher, when this
When the vibration absorption unit at place has recessed behaviour, vibration absorption unit stress herein is smaller, and damping block can stretch out one section compared with other positions more
The groove at this is compensated, so that multi-rotor unmanned aerial vehicle is steadily stablized in descent, complex road condition can be suitable for；
2, in the application, hexagon has effectively contained power battery, improves inner space utilization rate；
3, in the application, the design of unmanned aerial vehicle body box makes primary load bearing component be reduced to covering, fuselage load box, battery
Frame, three parts are successively nested to be glued, and compared to more traditional fuselage interior frame structure, is greatly simplified mounting process, is dropped
Low production cost；
4, in the application, since the body volume of hexagon reduces, fuselage interior equipment centralized arrangement is below battery frame
Fuselage load box in, therefore can effectively shorten the overall length of fuselage interior cable, alleviate weight；
5, in the application, the boxlike load-carrying construction and small fuselage being made of fuselage frame and covering soak area can
It is effective to mitigate construction weight.Actual weight measurement structure is shown: using the multi-rotor unmanned aerial vehicle of boxlike load-carrying construction, 1.2
In the case where rice wheelbase, it is capable of multi-rotor unmanned aerial vehicle construction weight of the fuselage of ratio by the way of shell entirety load and mitigates three
/ mono-, it is shown in Table 1.
6, in the application, in the case where accommodating the battery of same volume, the fuselage of hexagon compares round fuselage, soaks
Area reduces 29.7%, reduces interference of the prominent wind to flight attitude, sees Fig. 8；
Detailed description of the invention:
FIG. 1 is a schematic structural view of the utility model；
Fig. 2 is Fig. 1 structural front view；
Fig. 3 is Fig. 2A-location A cross-sectional view；
Fig. 4 is body housing structural schematic diagram；
Fig. 5 is fuselage load case structure schematic diagram；
Fig. 6 is battery frame structural schematic diagram；
Fig. 7 is the application assembling schematic diagram；
Fig. 8 is round body housing and hexagon body housing and battery frame structural schematic diagram；
Fig. 9 is the utility model vibration absorption unit structural schematic diagram；
In figure: 10~body housing；11~fuselage frame；12~carrier strip；13~flange；14~gram horse button；20~fuselage is held
Power box；21~lower fixed strip；22~connecting plate；23~go up fixed strip；30~battery frame；31~rectangular bearing frame；32~carbon pipe；
40~upper flap；50~carry plate；51~open slot；60~undercarriage；61~fixing end；62~connecting rod；63~support rod；
64~vibration absorption unit；65~accommodating cavity；66~damping block；67~spring.
Specific embodiment:
In order to be easy to understand the technical means, creative features, achievement of purpose, and effectiveness of the utility model, under
Face combination is specifically illustrating and embodiment, furthers elucidate the utility model.
Embodiment 1:
As shown in Fig. 1~3 and Fig. 7 and 9, a kind of steady damping multi-rotor unmanned aerial vehicle fuselage box, the fuselage including polygon
Shell 10 has been sequentially arranged fuselage load box 20 and battery frame 30 in body housing 10, and 10 upper end of body housing is additionally provided with upper flap 40, machine
10 bottom end of body shell is additionally provided with carry plate 50, and the open slot 51 that 50 two sides of carry plate are equipped with is for arranging undercarriage 60；Undercarriage 60
Including fixing end 61, fixing end 61 is connected firmly in 10 bottom end of body housing, and 61 lower end of fixing end is hinged with connecting rod 62, and connecting rod 62 passes through
It is pierced by by open slot 51, the one end of connecting rod 62 far from fixing end 61 is also horizontal to be equipped with support rod 63；Between 63 bottom face of support rod
Every being disposed with several vibration absorption units 64, vibration absorption unit 64 includes accommodating cavity 65 of the arranged for interval on support rod 63, accommodating cavity 65
It is interior to be equipped with damping block 66, it is additionally provided with spring 67 in accommodating cavity 65,67 one end of spring is pressed on 65 bottom end of accommodating cavity, and spring 67 is another
End is pressed on damping block 66.
In the prior art, multi-rotor unmanned aerial vehicle is in descent, and since landing place road conditions are different, there are more rotors drops
It is larger to there is vibration during falling, there are when broken terrain at landing place, multi-rotor unmanned aerial vehicle even has hair
The case where raw rollover.In the application, when multi-rotor unmanned aerial vehicle landing, the vibration absorption unit 64 that 63 bottom of support rod is equipped with can basis
Road conditions are mediated, and when having protrusion under the vibration absorption unit 64 at this, 64 stress of vibration absorption unit herein is larger, and spring 67 compresses
Quantitative change is high, and when the vibration absorption unit 64 at this divides into fluted, 64 stress of vibration absorption unit herein is smaller, and damping block 66 can be compared with it
He stretches out one section of groove compensated at this in position more, so that multi-rotor unmanned aerial vehicle is steadily stablized in descent, energy
Enough it is suitable for complex road condition.
As shown in figure 4, body housing 10 is hexagonal structure, body housing 10 includes fuselage frame 11 and covering, and covering is coated on
11 outer surface of fuselage frame, the inwardly protruding formation carrier strip 12 in 11 lower end of fuselage frame, carrier strip 12 is two, and carrier strip 12 is symmetrical
11 two sides of the bottom of fuselage frame are arranged in, each carrier strip 12 one end close to each other is additionally provided with flange 13, sets on fuselage load box 20
Some connecting plates 22 stick on flange 13, in this way, the boxlike load-carrying construction and small machine that are made of fuselage frame 11 and covering
Body, which soaks area, can effectively mitigate construction weight, and actual weight measurement structure is shown: using more rotations of boxlike load-carrying construction
Wing unmanned plane is capable of multi-rotor unmanned aerial vehicle of the fuselage of ratio by the way of shell entirety load in the case where 1.2 meters of wheelbases
Construction weight mitigates one third, is shown in Table 1.
As shown in figure 5, the frame of the generally hexagon shape of fuselage load box 20, fuselage load box 20 is whole to be embedded in fuselage
In shell 10, the lower fixed strip 21 that 20 side wall corresponding with carrier strip 12 bottom end of fuselage load box is equipped with and carrier strip 12 cooperates,
Lower fixed strip 21 side close to each other, 20 upper end of fuselage load box and lower 21 opposite position of fixed strip is arranged in connecting plate 22
It is additionally provided with fixed strip 23, upper fixed strip 23 and 30 lower end of battery frame connect firmly, and 11 side of fuselage frame is additionally provided with for reducing itself
Weight engraves hole, in this way, since the body volume of hexagon reduces, fuselage interior equipment centralized arrangement is in battery in the application
It in the fuselage load box 20 of 30 lower section of frame, therefore can effectively shorten the overall length of fuselage interior cable, alleviate weight.
As shown in fig. 6, the whole hexagonal frame structure of battery frame 30,30 upper end of battery frame is additionally provided with embedded in battery frame 30
The rectangular bearing frame 31 of one end, on rectangular bearing frame 31 between upper 23 corresponding section of fixed strip and upper fixed strip 23 via carbon
Pipe 32 and hexagonal hexagonal socket head cap screw connect firmly, and through-hole, the through-hole pair on 10 side wall of through-hole and body housing are additionally provided on 30 side wall of battery frame
It should arrange, rectangular 31 upper end of bearing frame is additionally provided with partition, and the rectangular space that each partition is enclosed with 10 side wall of body housing is used for
Battery is installed and improves inner space utilization rate in this way, hexagon has effectively contained power battery.
Embodiment 2:
As shown in Figure 1, the present embodiment structure and the structure of embodiment one are essentially identical, something in common is repeated no more, different
Place is: a gram horse button 14 is additionally provided on 10 upper end lateral wall of body housing, upper flap 40 is buckled in body housing via a gram horse button 14
10 upper ends, it is so easier for installation.
The measurement comparison of 1 1.2m unmanned plane construction weight of table
The characteristics of basic principles and main features and the utility model of the utility model have been shown and described above.Current row
The technical staff of industry is described in above embodiments and description it should be appreciated that the present utility model is not limited to the above embodiments
Only illustrate the principles of the present invention, on the premise of not departing from the spirit and scope of the utility model, the utility model is also
It will have various changes and improvements, these changes and improvements are both fallen in the range of claimed invention.This is practical new
The claimed range of type is defined by the appending claims and its equivalent thereof.
Claims (6)
1. a kind of steady damping multi-rotor unmanned aerial vehicle fuselage box, which is characterized in that the body housing (10) including polygon, the machine
It is sequentially arranged fuselage load box (20) and battery frame (30) in body shell (10), body housing (10) upper end is additionally provided with upper flap
(40)；
Body housing (10) bottom end is additionally provided with carry plate (50), and the open slot (51) that carry plate (50) two sides are equipped with is used for
It arranges undercarriage (60)；
The undercarriage (60) includes fixing end (61), and the fixing end (61) connects firmly in body housing (10) bottom end, fixing end
(61) lower end is hinged with connecting rod (62), and the connecting rod (62) is pierced by via open slot (51), and connecting rod (62) is far from fixed
Hold the one end of (61) is also horizontal to be equipped with support rod (63)；
Support rod (63) the bottom face arranged for interval has several vibration absorption units (64), and the vibration absorption unit (64) includes interval cloth
The accommodating cavity (65) on support rod (63) is set, damping block (66) is equipped in the accommodating cavity (65), is also set in accommodating cavity (65)
Have spring (67), described spring (67) one end is pressed on accommodating cavity (65) bottom end, and spring (67) other end is pressed on damping block
(66) on.
2. steady damping multi-rotor unmanned aerial vehicle fuselage box according to claim 1, which is characterized in that the body housing
It (10) is hexagonal structure, body housing (10) includes fuselage frame (11) and covering, and the covering is coated on fuselage frame (11) appearance
Face, the inwardly protruding formation carrier strip (12) in fuselage frame (11) lower end, the carrier strip (12) is two, and carrier strip (12)
Fuselage frame (11) two sides of the bottom are arranged symmetrically in, each carrier strip (12) one end close to each other is additionally provided with flange (13), institute
The connecting plate (22) that fuselage load box (20) is equipped with is stated to stick on flange (13).
3. steady damping multi-rotor unmanned aerial vehicle fuselage box according to claim 2, which is characterized in that the fuselage load box
(20) generally the frame of hexagon shape, fuselage load box (20) are integrally embedded in body housing (10), the fuselage load box
(20) the lower fixed strip (21) that side wall corresponding with carrier strip (12) bottom end is equipped with and carrier strip (12) cooperates, the connecting plate
(22) side close to each other in lower fixed strip (21), fuselage load box (20) upper end position corresponding with lower fixed strip (21) are set
It sets and is additionally provided with fixed strip (23), fixed item (23) and battery frame (30) lower end connect firmly.
4. steady damping multi-rotor unmanned aerial vehicle fuselage box according to claim 3, which is characterized in that the fuselage frame (11)
Side, which is additionally provided with, engraves hole for reducing own wt.
5. steady damping multi-rotor unmanned aerial vehicle fuselage box according to claim 3, which is characterized in that the battery frame (30)
Whole hexagonal frame structure, battery frame (30) upper end are additionally provided with the rectangular bearing frame (31) embedded in battery frame (30) one end,
On rectangular bearing frame (31) between upper fixed strip (23) corresponding section and upper fixed strip (23) via carbon pipe (32) and hexagonal
Hexagonal socket head cap screw connects firmly, and through-hole, the through-hole on the through-hole and body housing (10) side wall are additionally provided on battery frame (30) side wall
Corresponding arrangement, rectangular bearing frame (31) upper end are additionally provided with partition, and each partition is enclosed with body housing (10) side wall
Rectangular space for installing battery.
6. steady damping multi-rotor unmanned aerial vehicle fuselage box according to claim 1, which is characterized in that the body housing (10)
A gram horse button (14) is additionally provided on the lateral wall of upper end, the upper flap (40) is buckled on body housing (10) via a gram horse button (14)
End.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820711336.2U CN208181413U (en) | 2018-05-14 | 2018-05-14 | A kind of steady damping multi-rotor unmanned aerial vehicle fuselage box |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820711336.2U CN208181413U (en) | 2018-05-14 | 2018-05-14 | A kind of steady damping multi-rotor unmanned aerial vehicle fuselage box |
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| Publication Number | Publication Date |
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| CN208181413U true CN208181413U (en) | 2018-12-04 |
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ID=64430309
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| CN201820711336.2U Active CN208181413U (en) | 2018-05-14 | 2018-05-14 | A kind of steady damping multi-rotor unmanned aerial vehicle fuselage box |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI747718B (en) * | 2020-12-14 | 2021-11-21 | 大陸商廣州昂寶電子有限公司 | Displacement compensation method and equipment and speed compensation method and equipment |
-
2018
- 2018-05-14 CN CN201820711336.2U patent/CN208181413U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI747718B (en) * | 2020-12-14 | 2021-11-21 | 大陸商廣州昂寶電子有限公司 | Displacement compensation method and equipment and speed compensation method and equipment |
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