CN106892081A - Multi-rotor aerocraft - Google Patents
Multi-rotor aerocraft Download PDFInfo
- Publication number
- CN106892081A CN106892081A CN201510967067.7A CN201510967067A CN106892081A CN 106892081 A CN106892081 A CN 106892081A CN 201510967067 A CN201510967067 A CN 201510967067A CN 106892081 A CN106892081 A CN 106892081A
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- CN
- China
- Prior art keywords
- utricule
- air bag
- rotor
- rotor aerocraft
- duct
- Prior art date
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/24—Arrangement of propulsion plant
- B64B1/30—Arrangement of propellers
- B64B1/34—Arrangement of propellers of lifting propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/24—Arrangement of propulsion plant
- B64B1/30—Arrangement of propellers
- B64B1/32—Arrangement of propellers surrounding hull
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/58—Arrangements or construction of gas-bags; Filling arrangements
Abstract
A kind of multi-rotor aerocraft is disclosed, including：Air bag, the air bag include utricule and its around inner space, the profile of the air bag is flat disk like of the interior thickness more than peripheral thickness, and include multiple ducts of the upper and lower surface through air bag in the neighboring area of air bag, the side wall of the duct limits the inner space of air bag together with utricule；And many rotor systems, many rotor systems include positioned at the governor circuit box in inside air bag space, the multiple motors in the multiple duct and multiple propellers and the connecting bracket for connecting governor circuit box and the multiple motor.The multi-rotor aerocraft by the use of many rotor systems and air bag as double lift-sources, to extend the hang time and improve handling.
Description
Technical field
The present invention relates to aeronautical technology, more particularly, to multi-rotor aerocraft.
Background technology
Aerostatics is once widely used in air transport.Aerostatics refers to using the gas for being lighter than air
To provide the airborne vehicle of lift.According to operation principle, aerostatics can be divided into dirigible, captive balloon and
Fire balloon.Aerostatics include air bag, for accommodate proportion less than air gas (such as hot-air,
Hydrogen or helium), so as to obtain lift.The simple structure of aerostatics, it is with low cost, stop in the air
Stay the time long.However, the precise control of aerostatics is highly difficult.In vertical direction, aerostatics
Can be risen or fallen by charging and discharging gas control.However, in the horizontal direction, the movement of aerostatics
By natural wind or additional power set, not only translational speed is slow but also operating difficulties.
Fig. 1 a and 1b are shown respectively the top view of the air bag in the aerostatics according to prior art and cut
Face figure.The air bag includes the utricule 100 of inflation.Utricule 100 after being inflated be shaped as cylinder
Shape, circle is illustrated as in the vertical view of Fig. 1 a, and rectangle is illustrated as in the section of Fig. 1 b.
In recent years, multi-rotor aerocraft increasingly causes the concern of people.Existing many rotor flyings
Device system is main by multiple propellers, motor, electron speed regulator, master control borad, frame, lithium battery
Constituted Deng part.Using single lithium battery power supply system, realized to multiaxis using big multiplying power discharging
The driving of rotor system.By control the rotating speed of each propeller can realize all directions freely become rail and
Pose adjustment.Due to the capacity limit of lithium battery, the multi-rotor aerocraft attainable flight time is only
At 15-30 minutes or so, so as to constrain its range of application.
Therefore, it is desirable to reference to aerostatics and the advantage of multi-rotor aerocraft, develop stagnant sky for a long time
And manipulate easy aircraft.
The content of the invention
It is an object of the invention to provide it is a kind of by the use of many rotor systems and air bag as double lift-sources with
Extension hang time and the multi-rotor aerocraft of raising handling.
A kind of embodiments in accordance with the present invention, there is provided multi-rotor aerocraft, including：Air bag, it is described
Air bag include utricule and its around inner space, the profile of the air bag is interior thickness more than week
The flat disk like of side thickness, and include the upper and lower surface through air bag in the neighboring area of air bag
Multiple ducts, the side wall of the duct limits the inner space of air bag together with utricule；And many rotations
Wing system, many rotor systems are including the governor circuit box positioned inside air bag space, positioned at institute
The multiple motors in multiple ducts are stated with multiple propellers and for connecting governor circuit box and institute
State the connecting bracket of multiple motors.
Preferably, the upper and lower surface of the air bag is smooth curved surface, and upper and lower surface is smoothed
Cross.
Preferably, the profile of the air bag is the revolving body with major axis and short axle, and with short axle
As rotary middle spindle.
Preferably, the profile of the air bag is the revolution formed around rotary middle spindle with one of lower curve
Body：Ellipse, parabolic arc, hyperbolic arc, sectional curve.
Preferably, the ratio between the major axis and short axle are 2:1~5:1.
Preferably, also including the battery case positioned at the bottom of the utricule, wherein accommodating chargeable electricity
Pond and DC voltage conversion module.
Preferably, also including the photovoltaic module positioned at the top of the utricule, the photovoltaic module is
Flexible thin film photovoltaic's component.
Preferably, the photovoltaic module is conformal with the top of the utricule.
Preferably, the utricule is formed by the one kind selected from following material：High intensity reinforcing fibre cloth,
PVC film, dacron membrane, polyester fiber film.
Preferably, the multi-rotor aerocraft also includes：Respectively in the upper and lower surface of utricule
Between part protuberance lid；And for that will cover and the rigidly connected connecting rod of governor circuit box, its
In, the lid limits the short axle of air bag with the connecting rod together.
Preferably, the multi-rotor aerocraft also includes：For by the inner surface of utricule be connected branch
The connected multiple drawstrings of frame, the length of the multiple drawstring is set according to the profile of air bag, so that
Inflated condition maintains the profile of air bag.
Preferably, the duct has for the upper port of gas inflow and for gas outflow
Lower port, and upper port and lower port increase relative to the area of center section, the duct
Side wall is smooth curved surface.
Preferably, the side wall of the duct is integrally formed with the utricule, or by independent tubulose
Part limits penetrating via and is bonded together with utricule.
Preferably, the connecting bracket is hollow tubulose, and using wire from governor circuit box
Start, motor is reached through connecting bracket, for being motor with drive voltage.
Preferably, the multi-rotor aerocraft also includes：Fluid sealant, for filling the connection branch
The inner space of frame；And flange plate structure, between the connecting bracket and the utricule
Connection, wherein, the fluid sealant and the flange plate structure maintain the air-tightness of the utricule together.
Preferably, it is 4 or more to state the quantity of multiple propellers.
Preferably, the governor circuit box and the multiple connecting bracket are with the central shaft of the utricule
Zhou duicheng tuxing is formed, wherein, the multiple connecting bracket is angularly distributed in perpendicular to central shaft
Plane in.
Preferably, the equal length of the multiple connecting bracket, and be respectively mounted in end described
Multiple motors and the multiple propeller so that the central shaft of the multiple propeller and the utricule
Distance it is equal.
Preferably, the central shaft of the multiple motor and the multiple propeller respectively with the utricule
Central shaft it is parallel so that operationally produce vertical direction air-flow, formed lift.
Multi-rotor aerocraft according to the abovementioned embodiments of the present invention, using many rotor systems and air bag
As double lift-sources, to extend the hang time and improve handling.In inflated condition, air bag
Profile is flat disk like, is conducive to reducing windage and improves wind loading rating.When moving in the horizontal direction,
The shape can also reduce the energy loss of power-equipment, and improve handling.
In the periphery of air bag, duct, motor and propeller for accommodating many rotor systems are set.
Because the edge thickness of air bag is smaller, duct can meet many rotor systems needed for aerodynamics
It is required that, without particular design, you can reduce resistance of the duct to prop-blast.
The multi-rotor aerocraft can apply to the field of various needs empty and moving horizontally property stagnant for a long time
Close.For example, the multi-rotor aerocraft can carry communication equipment, it is communication for rescue and relief work
Terminal, or for carrying collecting device, for climate monitoring, data acquisition, or carry
Monitoring device, monitors for a long time for remote.
Brief description of the drawings
By description referring to the drawings to the embodiment of the present invention, it is of the invention above-mentioned and other
Objects, features and advantages will be apparent from, in the accompanying drawings：
Fig. 1 a and 1b are shown respectively the vertical view of the air bag in the aerostatics of reference examples of the invention
Figure and sectional view；
Fig. 2 a and 2b are shown respectively the air bag in multi-rotor aerocraft according to an embodiment of the invention
Top view and sectional view；And
Fig. 3 a and 3b are shown respectively the top view of multi-rotor aerocraft according to an embodiment of the invention
And sectional view.
Specific embodiment
The present invention is more fully described hereinafter with reference to accompanying drawing.In various figures, identical element
Represented using similar reference.For the sake of clarity, the various pieces in accompanying drawing are not pressed
Ratio is drawn.Furthermore, it is possible to not shown some known parts.For brevity, Ke Yi
Structure described in one width figure by being obtained after several steps.
It should be appreciated that in the structure of outlines device, being referred to as being located at separately when by one layer, a region
One layer, another region " above " or when " top ", can refer to located immediately at another layer, another
Above one region, or its between another layer, another region also comprising other layers or
Region.Also, if device overturn, this layer, region will be positioned at another layer, another
Individual region " below " or " lower section ".
If in order to describe, located immediately at another layer, another region above scenario, will to adopt herein
With " A is directly on B " or the form of presentation of " A is on B and abuts therewith ".At this
In application, " A is in B " represents that A is located in B, rather than A formation in B
In doped region.
In this application, term " intermediate structure " refers to each step in manufacture metamaterial composite structure
The general designation of the total formed in rapid, including all layers for having been formed or region.
Describe hereinafter many specific details of the invention, such as micro-structural, material, chi
Very little, handling process and technology, to be more clearly understood that the present invention.But as the technology of this area
Personnel it will be appreciated that as, the present invention can not be realized according to these specific details.
The present invention can be presented in a variety of manners, some of them example explained below.
Fig. 2 a and 2b are shown respectively the air bag in multi-rotor aerocraft according to an embodiment of the invention
Top view and sectional view, wherein the sectional view shown in Fig. 2 b is along in the top view shown in 2a
Heart line AA interceptions are obtained.
The air bag includes the utricule 200 that can be inflated.The utricule shape of inflated condition is shown in figure
Shape.As illustrated, being shaped as flat disk like in inflated condition utricule 200.The shape is favourable
In reduction windage and raising wind loading rating.When moving in the horizontal direction, the shape can also reduce dynamic
The energy loss of power equipment, and improve handling.
The thickness of the center section of air bag is more than the thickness of peripheral part, and with smooth surface
Profile.Preferably, air bag is revolving body, the revolving body have major axis on the horizontal plane and
Short axle in vertical direction, and with short axle as rotary middle spindle.The ratio between major axis and short axle are
2:1~5:1.
As an example, utricule 200 is illustrated as circle in the vertical view of Fig. 1 a, in cutting for Fig. 1 b
Face is illustrated as approximate ellipsoidal.However, the cross sectional shape not limited to this of utricule 200, can be with
It is to be selected from ellipse, or is made up of at least one of parabolic arc, hyperbolic arc, sectional curve
It is close-shaped.
At least a portion lift that air bag is used for needed for providing the stagnant sky of multi-rotor aerocraft.Air bag includes
Utricule 200 and its around inner space.Utricule 200 accommodates gas of the proportion less than air, example
Such as hydrogen or helium, to provide lift.Therefore, the material of utricule 200 should have air-tightness.
For example, utricule 200 is made up of high intensity reinforcing fibre cloth.Alternatively, if to the machinery of utricule
Intensity requirement is not high, and the material of utricule 200 can also be PVC film, dacron membrane, polyester fiber film.
Air bag can reduce windage and improve handling using flat disk like utricule.Therefore, capsule
Body can take conformal measure to maintain desired profile.Conformal measure is, for example, that multilayer drawstring is socketed
Technology.In the inner space of utricule 200, in the form of multilayer drawstring, every layer of drawstring is spaced 25mm,
The length of drawstring is set from big to small from the center section of utricule 300 to peripheral part.Multilayer drawstring
Can ensure that the profile of utricule 200 is consistent with design.
Technique for forming disk like utricule includes multiple steps.First, setting according to disk like utricule
Meter profile, by the surface segmentation of disk like utricule into multiple grid regions.Each grid includes the one of utricule
Individual surface district.The position of shape and grid according to disk like utricule, the shape of the surface district of adjacent mesh
Shape is identical or different.Then, according to the surface area topology of grid, high intensity reinforcing fibre cloth is cut,
To obtain the material piece corresponding with the surface district of grid.Then, by material piece according to surface district
Position is stitched together and is pressed, to form complete utricule surface.In pressing, pressure
Conjunction machine temperature is 120 degrees Celsius, and pressing speed is 0.5 m/min, and material must not be rocked during pressing,
In order to avoid produce fold.
In the aerostatics of the reference examples of the invention shown in Fig. 1, the utricule 100 of air bag is cylinder
Shape.Assuming that utricule 100 a diameter of 3m, 1m high, then the volume of utricule 100 is 7.069m3,
Windage is 20N under wind speed in 5m/s.Many according to an embodiment of the invention shown in Fig. 2
In rotor craft, the utricule 200 of air bag is flat disk like.Assuming that utricule 200 be shaped as reason
The elliposoidal thought, major axis is 3.45m, and short axle is 1.15m, then the volume of utricule 200 is 7.17m3,
The wind resistance 5N under the wind speed of 5m/s.As can be seen here, many rotations for implementing people's example of the invention
Rotor aircraft can be substantially reduced windage, correspondingly improve wind loading rating, reduce energy loss and change
The handling of kind horizontal direction movement.
Fig. 3 a and 3b are shown respectively the top view of multi-rotor aerocraft according to an embodiment of the invention
And sectional view, wherein the sectional view shown in Fig. 3 b along the top view shown in 3a center line AA
Interception is obtained.
The multi-rotor aerocraft includes flat disk like utricule 300.In this embodiment, utricule 300
It is the revolving body with the short axle on the major axis and vertical direction in horizontal plane.Utricule 300 exists
The vertical view of Fig. 3 a is illustrated as circle, is shown as in a cross-sectional view in Fig. 3b by hyperbolic arc group
Into substantially closed curve.The top segmental arc of hyperbolic arc corresponds to the upper surface of utricule 300, under
Portion's segmental arc corresponds to the lower surface of utricule 300.
As shown in Figure 3 b, on the periphery of utricule 300, the top segmental arc and bottom segmental arc of hyperbolic arc
Linkage section be smooth curve.That is, smoothed between the upper and lower surface of utricule 300
Cross, without producing sharp edge.The smooth edges of utricule 300 are conducive to obtaining streamlined section
Facial contour, so as to reduce windage when multi-rotor aerocraft is moved.According to interior space requirement and sky
Aerodynamics demand, can be more than, small using the action in hyperbolic arc section, and top segmental arc
In or equal to bottom segmental arc action.
In the periphery of utricule 300, peripherally equally distributed 4 ducts 340 in direction are formed.
Duct 340 extends to lower surface from the upper surface of utricule 300, forms the penetrating via of air-flow.
In the embodiment, side wall and the utricule 300 of duct 340 are integrally formed.In alternate embodiments,
Duct 340 limits penetrating via by independent tubular part respectively, and is bonded in utricule 300
Together, so as to form gas-tight seal.
The upper port and lower port of duct 340 increase relative to the area of intermediate portion, and contain
The side wall in road 340 is the smooth surface of evagination so that the sectional area of duct 340 divides from center section
Do not expand gradually to its upper port and lower port, so as to reduce the resistance that air-flow is flowed in and out.
In work, air-flow is flowed into from the upper port of duct 340, is flowed out from the lower port of duct 340.
In the core of the upper and lower surface of utricule 300, the lid 310 of protuberance is formed respectively
With 320.Further, in the inner space of utricule 300, governor circuit box 301 is set.Master control
The parts such as master control borad, electron speed regulator, signal receiver are included in circuit box.In the embodiment
In, governor circuit box 301 doubles as main support.
In a preferred embodiment, lid 310 and 320 is respectively via connecting rod 302 and 303 and master
Control circuit box 301 is rigidly connected.4 respective one end of connecting bracket 305 respectively with governor circuit
During box 301 is rigidly connected, and the respective other end extends to corresponding duct 340, for pacifying
Fill respective motor 350 and propeller 360.
Preferably, governor circuit box 301 and four organization center symmetric figures of connecting bracket 305,
For example, zhou duicheng tuxing is formed with the central shaft of utricule 300, wherein, four connecting brackets 305
Angularly it is distributed in the plane of central shaft.It is further preferred that four connecting brackets 305
Equal length, the end of four connecting brackets 305 is respectively mounted respective motor 550 and spiral
Oar 560, so as to equal with the distance of the central shaft of utricule.In motor 550 and propeller 560
Central shaft of the heart axle with utricule is parallel, so that operationally propeller 560 is produced along vertical side
To air-flow, formed lift.In other implementations, four connecting brackets 305 can also
The central shaft of utricule 300 is favoured, is not limited with the present embodiment.
Connecting bracket 305 for example passes through utricule 300 by sealing flange dish structure, for supporting electricity
Machine 350 and propeller 360.Connecting bracket 305 can be hollow tubulose, for motor
350 drive circuit is arranged in governor circuit box 301.Wire since governor circuit box 301,
Motor 350 is reached through connecting bracket 305, for providing driving voltage for motor 350.Even
The inside of support 305 is connect, after wire is placed, inner space is filled using fluid sealant.
Due to being sealed using sealant sealing and flange plate structure, the gas in utricule 300 can be avoided
Body is revealed via the inner space of connecting bracket 305 or itself and joint portion between utricule 300,
So as to maintain the air-tightness of utricule 300.
Preferably, in the inside of utricule 300, utricule 300 is connected using multiple top drawstrings 306
Upper inside surface and connecting bracket 305, using multiple bottom drawstrings 307 connection utricule 300
Lower inner surface and connecting bracket 305.The length of top drawstring 306 and bottom drawstring 307 is from capsule
The center section of body 300 is set from big to small to peripheral part.So as in inflated condition, utilize
The pulling force of drawstring maintains the surface configuration of utricule 300, to realize the conformal of utricule 300.As above
It is described, can be using the set-up mode of multilayer drawstring.Multilayer drawstring can preferably maintain large volume
The profile of air bag, and can preferably cause that the exact shape of air bag is consistent with design outline.
Preferably, battery case is installed in the bottom of utricule 300.Battery case is used to accommodate chargeable electricity
Pond and DC voltage conversion module.In battery inside, using wire connection rechargeable battery and directly
Stream voltage transformation module.The bottom of battery case facilitates chargeable by valve mechanism closure or openness
The replacing of battery and charging.In battery inside, battery case is connected to by governor circuit using wire
Box 301 so that can be powered to governor circuit box 301.
Preferably, in the top installation photovoltaic component of utricule 300.Because the top of utricule 300 is
Curved surface, therefore the flexible thin film photovoltaic component conformal with the top of utricule 300 can be installed.Using
Photovoltaic module is connected to governor circuit box 301 and/or battery case by wire so that can use photovoltaic
Component is powered to governor circuit box 301, or for being charged to the rechargeable battery of battery inside.
Preferably, shock bracket is also devised with the bottom of utricule 300, plays landing protection of taking off
Effect.Shock bracket is for example installed in the lower surface of battery case.
In working order, many rotor systems change rotor by adjusting 4 rotating speeds of motor 350
Rotating speed, so as to realize lift variation and control heading.In floating state, 4 motors 350
It is maintained at balancing speed so that the lift that rotor is produced is equal to the deadweight of aircraft.In vertical direction
When upper mobile, vertical ascent is realized by the rotating speed for increasing by 4 motors 350 simultaneously, by simultaneously
Reduce 4 rotating speeds of motor 350 and realize vertical decline.When moving in the horizontal direction, reduce edge
The rotating speed of preceding first motor of the direction of motion, increase posterior second along the direction of motion
The rotating speed of motor, while maintain other two motor balancing speed so that aircraft first occurs one
Determine the inclination of degree, then produce the thrust for travelling forward.
In the design of utricule 300, using the structure for possessing certain aerodynamic appearance.Pass through
To material, shape, size, the design of filling gas so that utricule 300 can be carried after inflation
For effective net buoyancy.Therefore, the volume V of utricule 300, surface area S, density of material D1,
Needed between the parameters such as filling gas density D2, atmospheric density D3, the weight M of whole machine miscellaneous part
Meet following relation：
M ＞ V × (D3-D2)-S × D1 ＞ 0,
The net buoyancy numerical value that i.e. utricule 300 is provided have to be larger than zero, but can not be more than removing utricule in system
The weight sum total of the miscellaneous part outside 300.
Under designing herein, the buoyancy that utricule 300 is provided is capable of the portion of effective bucking-out system miscellaneous part
Divide weight, mitigate the take-off weight of system, reduce the requirement to airscrew thrust, and then reduce work
Power consumption when making, realizes the extension of flight time.
In the multi-rotor aerocraft of above-described embodiment, not only with the gas conduct accommodated in air bag
Lift-source, and provide lift-source, and the mobile control for realizing horizontal direction using many rotor systems
System.At least a portion lift needed for providing the stagnant sky of multi-rotor aerocraft due to air bag, therefore,
Even if many rotor systems work in relatively low rotating speed, it is also possible to realize multi-rotor aerocraft hovering,
Vertically move and move horizontally.The multi-rotor aerocraft uses the combination of air bag and many rotor systems,
The energy ezpenditure of many rotor systems can be reduced, extends the hang time.Many rotor systems are many rotors
Aircraft provides the power for moving horizontally and vertically moving.
In inflated condition, the profile of air bag is flat disk like, is conducive to reducing windage and improves wind resistance
Ability.When moving in the horizontal direction, the shape can also reduce the energy loss of power-equipment, with
And improve handling.
In the periphery of air bag, duct, motor and propeller for accommodating many rotor systems are set.
Because the edge thickness of air bag is smaller, duct can meet many rotor systems needed for aerodynamics
It is required that.Used compared with the duct in the middle of air bag is arranged on, in embodiments of the invention and be arranged on gas
The duct on capsule periphery, without particular design, you can reduce resistance of the duct to prop-blast
Power.
In the above-described embodiment, many rotor systems for describing multi-rotor aerocraft include 4 spiral shells
Rotation oar.It is appreciated that many rotor systems can include more propellers, it is more complicated to realize
Flight attitude.
Embodiments of the invention are described above.But, these embodiments are used for the purpose of
Descriptive purpose, and be not intended to limit the scope of the present invention.The scope of the present invention is by appended right
It is required that and its equivalent restriction.The scope of the present invention is not departed from, those skilled in the art can make
Various alternatives and modifications, these alternatives and modifications should all fall within the scope of the present invention.
Claims (19)
1. a kind of multi-rotor aerocraft, including：
Air bag, the air bag include utricule and its around inner space, the profile of the air bag is
Interior thickness is more than the flat disk like of peripheral thickness, and includes running through gas in the neighboring area of air bag
Multiple ducts of the upper and lower surface of capsule, the side wall of the duct limits the inside of air bag together with utricule
Space；And
Many rotor systems, many rotor systems include positioned inside air bag space governor circuit box,
Multiple motors in the multiple duct are with multiple propellers and for connecting governor circuit
Multiple connecting brackets of box and the multiple motor.
2. multi-rotor aerocraft according to claim 1, wherein, the upper following table of the air bag
Face is smooth curved surface, and upper and lower surface is seamlessly transitted.
3. multi-rotor aerocraft according to claim 2, wherein, the profile of the air bag is
Revolving body with major axis and short axle, and using short axle as rotary middle spindle.
4. multi-rotor aerocraft according to claim 3, wherein, the profile of the air bag is
With the revolving body that one of lower curve is formed around rotary middle spindle：Ellipse, parabolic arc, hyperbola
Arc, sectional curve.
5. multi-rotor aerocraft according to claim 3, wherein, the major axis and short axle it
Than being 2:1~5:1.
6. multi-rotor aerocraft according to claim 1, also including positioned at the bottom of the utricule
The battery case in portion, wherein accommodating rechargeable battery and DC voltage conversion module.
7. multi-rotor aerocraft according to claim 2, also including positioned at the top of the utricule
The photovoltaic module in portion, the photovoltaic module is flexible thin film photovoltaic's component.
8. multi-rotor aerocraft according to claim 7, wherein, the photovoltaic module and institute
The top for stating utricule is conformal.
9. multi-rotor aerocraft according to claim 1, wherein, the utricule by selected from
A kind of formation of lower material：High intensity reinforcing fibre cloth, PVC film, dacron membrane, polyester fiber film.
10. multi-rotor aerocraft according to claim 1, also includes：
The lid of the protuberance of the center section of the upper and lower surface of utricule is located at respectively；And
For that will cover and the rigidly connected connecting rod of governor circuit box,
Wherein, the lid and the connecting rod limit the short axle of air bag together.
11. multi-rotor aerocrafts according to claim 1, also include：For by utricule
Multiple drawstrings that inner surface is connected with connecting bracket, the length of the multiple drawstring is according to the outer of air bag
Shape is set, so as to maintain the profile of air bag in inflated condition.
12. multi-rotor aerocrafts according to claim 1, wherein, the duct has to be used
The upper port flowed into gas and the lower port for gas outflow, and upper port and lower port
Area relative to center section increases, and the side wall of the duct is smooth curved surface.
13. multi-rotor aerocrafts according to claim 12, wherein, the side wall of the duct
It is integrally formed with the utricule, or is limited penetrating via by independent tubular part and glued with utricule
It is connected together.
14. multi-rotor aerocrafts according to claim 1, wherein, the connecting bracket is
Hollow tubulose, and using wire since governor circuit box, motor is reached through connecting bracket,
For being motor with drive voltage.
15. multi-rotor aerocrafts according to claim 14, also include：
Fluid sealant, the inner space for filling the connecting bracket；And
Flange plate structure, for the connection between the connecting bracket and the utricule,
Wherein, the fluid sealant and the flange plate structure maintain the air-tightness of the utricule together.
16. multi-rotor aerocrafts according to claim 1, wherein, the multiple propeller
Quantity be 4 or more.
17. multi-rotor aerocrafts according to claim 1, wherein, the governor circuit box
Zhou duicheng tuxing is formed with the central shaft of the utricule with the multiple connecting bracket, wherein, it is described
Multiple connecting brackets are angularly distributed in the plane of central shaft.
18. multi-rotor aerocrafts according to claim 17, wherein, the multiple connection branch
The equal length of frame, and the multiple motor and the multiple propeller are respectively mounted in end,
So that the multiple propeller is equal with the distance of the central shaft of the utricule.
19. multi-rotor aerocrafts according to claim 18, wherein, the multiple motor and
Central shaft of the central shaft of the multiple propeller respectively with the utricule is parallel, so that operationally
The air-flow of vertical direction is produced, lift is formed.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510967067.7A CN106892081A (en) | 2015-12-21 | 2015-12-21 | Multi-rotor aerocraft |
| PCT/CN2016/109139 WO2017107781A1 (en) | 2015-12-21 | 2016-12-09 | Multi-rotor air vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510967067.7A CN106892081A (en) | 2015-12-21 | 2015-12-21 | Multi-rotor aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106892081A true CN106892081A (en) | 2017-06-27 |
Family
ID=59089080
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510967067.7A Pending CN106892081A (en) | 2015-12-21 | 2015-12-21 | Multi-rotor aerocraft |
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| CN (1) | CN106892081A (en) |
| WO (1) | WO2017107781A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114148502A (en) * | 2021-12-03 | 2022-03-08 | 中国特种飞行器研究所 | Four-rotor aircraft based on floating platform |
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| CN102501967A (en) * | 2011-11-09 | 2012-06-20 | 中国科学院长春光学精密机械与物理研究所 | Multi-rotor aircraft |
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| WO2017107781A1 (en) | 2017-06-29 |
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