CN109573006A - A kind of tilting rotor wing unmanned aerial vehicle and its wing components - Google Patents
A kind of tilting rotor wing unmanned aerial vehicle and its wing components Download PDFInfo
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- CN109573006A CN109573006A CN201910093098.2A CN201910093098A CN109573006A CN 109573006 A CN109573006 A CN 109573006A CN 201910093098 A CN201910093098 A CN 201910093098A CN 109573006 A CN109573006 A CN 109573006A
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- tilting rotor
- rotor
- unmanned aerial
- aerial vehicle
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- 230000007246 mechanism Effects 0.000 claims description 55
- 238000000034 method Methods 0.000 description 3
- 230000005611 electricity Effects 0.000 description 2
- 238000007667 floating Methods 0.000 description 2
- 238000013507 mapping Methods 0.000 description 2
- 230000000007 visual effect Effects 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 230000033001 locomotion Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/20—Vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/296—Rotors with variable spatial positions relative to the UAV body
- B64U30/297—Tilting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U60/00—Undercarriages
- B64U60/40—Undercarriages foldable or retractable
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
The present invention relates to unmanned vehicle technical fields, it discloses in a kind of tilting rotor wing unmanned aerial vehicle and its wing components, wing components are used to be installed on the fuselage of tilting rotor wing unmanned aerial vehicle, and wing components include: wing, for being installed on fuselage: tilting rotor component is installed on wing；And undercarriage, it is installed on tilting rotor component；When tilting rotor wing unmanned aerial vehicle VTOL, tilting rotor component verts relative to wing to first position, and undercarriage is unfolded relative to wing, and tilting rotor component provides the lift of VTOL for tilting rotor wing unmanned aerial vehicle；When tilting rotor wing unmanned aerial vehicle duration flight, tilting rotor component verts relative to wing to the second position, and undercarriage provides the thrust of duration flight relative to wing-folding, tilting rotor component for tilting rotor wing unmanned aerial vehicle.By the way that undercarriage is installed on tilting rotor component, it can be achieved that the undercarriage of tilting rotor wing unmanned aerial vehicle can fold.
Description
[technical field]
The present invention relates to unmanned vehicle field more particularly to a kind of tilting rotor wing unmanned aerial vehicles and its wing components.
[background technique]
Tilting rotor wing unmanned aerial vehicle is to run when one kind is taken off without sliding, the takeoff and landing of unmanned plane can be completed with original place.?
When aerial, the tilting rotor component of tilting rotor wing unmanned aerial vehicle verts with the raising of flying speed, to tilting rotor nobody
Machine more than after certain stalling speed, vert by the completion of tilting rotor component, and the outbound course and air of tilting rotor component come
Flow direction near normal, thus make tilting rotor wing unmanned aerial vehicle by wing generate buoyancy, ensure that tilting rotor wing unmanned aerial vehicle
Duration flight ability.
For light-duty tilting rotor wing unmanned aerial vehicle due to the limitation of construction weight, undercarriage is mostly fixed, therefore, tilting rotor
For unmanned plane in flight, undercarriage increases the flight resistance of tilting rotor wing unmanned aerial vehicle, further, since undercarriage can not be packed up,
Undercarriage is caused to block the visual angle of mapping camera or holder camera.
[summary of the invention]
In order to solve the above-mentioned technical problem, the embodiment of the present invention provides a kind of folding tilting rotor wing unmanned aerial vehicle of undercarriage
And its wing.
In order to solve the above-mentioned technical problem, the embodiment of the present invention the following technical schemes are provided:
On the one hand, a kind of wing components are provided, for being installed on the fuselage of tilting rotor wing unmanned aerial vehicle, the wing components packet
Include: wing, for the wing for being installed on the fuselage: tilting rotor component, the tilting rotor component is installed on the machine
The wing；And undercarriage, the undercarriage are installed on the tilting rotor component；Wherein, the tilting rotor component can be relative to
The wing verts to first position or the second position；When the tilting rotor wing unmanned aerial vehicle VTOL, the tilting rotor
Component verts relative to the wing to the first position, and the undercarriage is unfolded relative to the wing, the rotation of verting
Wing component provides the lift of VTOL for the tilting rotor wing unmanned aerial vehicle；When the tilting rotor wing unmanned aerial vehicle duration flight,
The tilting rotor component verts relative to the wing to the second position, and the undercarriage is rolled over relative to the wing
Folded, the tilting rotor component provides the thrust of duration flight for the tilting rotor wing unmanned aerial vehicle.
In some embodiments, the tilting rotor component includes rotor mechanism and mounting assembly；The mounting assembly peace
Loaded on the wing, the rotor mechanism is installed on the mounting assembly, and the rotor mechanism can be relative to the mounting assembly
It verts；The undercarriage is installed on the rotor mechanism.
In some embodiments, the wing has leading edge and rear；The prominent leading edge in one end of the mounting assembly
Or the rear；The rotor mechanism is installed on one end of the prominent leading edge of the mounting assembly or the rear.
In some embodiments, the prominent leading edge in one end of the mounting assembly, another distal process of the mounting assembly
The rear out；Two rotor mechanisms are respectively arranged in the both ends of the mounting assembly.
In some embodiments, the mounting assembly includes the first support and the second support；One end of first support
The prominent leading edge, the other end of first support are connected to each other with second support, another distal process of second support
The rear out；One in two rotor mechanisms is installed on the prominent described up-front one end of first support, and two
Another in the rotor mechanism is installed on one end of the prominent rear of second support.
In some embodiments, two undercarriages are respectively arranged in two rotor mechanisms.
In some embodiments, the rotor mechanism includes the motor cabinet being sequentially connected, rotor motor and propeller；Institute
It states motor cabinet and is installed on the mounting assembly, the undercarriage is installed on the motor cabinet, and the motor cabinet can be relative to described
Wing verts.
In some embodiments, the propeller has rotation axis, the motor cabinet, the rotor motor and described
Propeller is linearly distributed.
In some embodiments, the undercarriage includes support portion；One end of the support portion is connected to the motor cabinet,
The other end of the support portion extends towards the direction far from the propeller.
In some embodiments, the undercarriage further includes interconnecting piece, and the interconnecting piece is connected to the support portion and institute
It states between interconnecting piece.
On the other hand, a kind of tilting rotor wing unmanned aerial vehicle is provided, comprising: fuselage；And it is installed on the institute as above of the fuselage
The wing components stated.
Compared with prior art, in tilting rotor wing unmanned aerial vehicle provided in an embodiment of the present invention and its wing components, institute
Wing components are stated for being installed on the fuselage of tilting rotor wing unmanned aerial vehicle, the wing components include: wing, and the wing is for pacifying
Loaded on the fuselage: tilting rotor component, the tilting rotor component are installed on the wing；And undercarriage, it is described to rise and fall
Frame is installed on the tilting rotor component；Wherein, the tilting rotor component can vert relative to the wing to first position
Or the second position；When the tilting rotor wing unmanned aerial vehicle VTOL, the tilting rotor component verts relative to the wing
To the first position, the undercarriage be unfolded relative to the wing, the tilting rotor component for the tilting rotor without
The lift of man-machine offer VTOL；When the tilting rotor wing unmanned aerial vehicle duration flight, the tilting rotor component relative to
The wing verts to the second position, and the undercarriage is institute relative to the wing-folding, the tilting rotor component
It states tilting rotor wing unmanned aerial vehicle and the thrust of duration flight is provided.It, can by the way that the undercarriage is installed on the tilting rotor component
Realize that the undercarriage of the tilting rotor wing unmanned aerial vehicle can fold.
[Detailed description of the invention]
One or more embodiments are illustrated by corresponding attached drawing, these exemplary illustrations not structure
The restriction of pairs of embodiment, the element with same reference numbers label is expressed as similar element in attached drawing, unless there are special
It declares, composition does not limit the figure in attached drawing.
Fig. 1 is a kind of solid of the present invention tilting rotor wing unmanned aerial vehicle that wherein an embodiment provides in VTOL state
Figure；
Fig. 2 is perspective view of the tilting rotor wing unmanned aerial vehicle shown in FIG. 1 in duration flight state；
Fig. 3 is the undercarriage of tilting rotor wing unmanned aerial vehicle shown in FIG. 1 and the perspective view of tilting rotor component；
Fig. 4 is the side view of tilting rotor wing unmanned aerial vehicle shown in FIG. 1；
Fig. 5 is the side view of tilting rotor wing unmanned aerial vehicle shown in Fig. 2；
Fig. 6 is the front view of tilting rotor wing unmanned aerial vehicle shown in FIG. 1；
Fig. 7 is the front view of tilting rotor wing unmanned aerial vehicle shown in Fig. 2；
Fig. 8 is the perspective view in boost phase of tilting rotor wing unmanned aerial vehicle shown in FIG. 1.
[specific embodiment]
To facilitate the understanding of the present invention, with reference to the accompanying drawings and detailed description, the present invention is carried out in more detail
It is bright.It should be noted that be expressed " being fixed on " another element when element, it can directly on the other element or
There may be one or more elements placed in the middle therebetween.When an element is expressed " connection " another element, it be can be directly
It is connected to another element in succession or there may be one or more elements placed in the middle therebetween.Term used in this specification
"vertical", "horizontal", "left" and "right", "inner", "outside" and similar statement are for illustrative purposes only.
Unless otherwise defined, technical and scientific term all used in this specification is led with technology of the invention is belonged to
The normally understood meaning of the technical staff in domain is identical.It is specific to be intended merely to description for used term in the description of the invention
Embodiment purpose, be not intended to limitation the present invention.Term "and/or" used in this specification includes one or more
Any and all combinations of relevant listed item.
Fig. 1 and Fig. 2 are please referred to, for a kind of present invention tilting rotor wing unmanned aerial vehicle 300 that wherein an embodiment provides, including machine
Body 200 and wing components 100.Wherein, the wing components 100 are installed on the fuselage 200.
The whole fuselage 200 is in shuttle shape, includes the control electricity being made of electronic components such as MCU in the fuselage 200
Road component, the control circuit component include multiple control modules, e.g., for controlling the 300 flight appearance of tilting rotor wing unmanned aerial vehicle
It is the winged control control module of state, related airborne for the Beidou module for the tilting rotor wing unmanned aerial vehicle 300 that navigates and for handling
The data processing module etc. of environmental information acquired in equipment.
The wing components 100 include wing 10, tilting rotor component 20 and undercarriage 30.Wherein, the wing 10
It is installed on the fuselage 200, the tilting rotor component 20 is installed on the wing 10, and the undercarriage 30, which is installed on, described to incline
Switch rotor component 20, the tilting rotor component 20 can vert relative to the fuselage 10 to first position or the second position.
There are two types of state of flights, respectively VTOL state and duration flight shape for the tool of tilting rotor wing unmanned aerial vehicle 100
State.Wherein, when 100 VTOL of tilting rotor wing unmanned aerial vehicle, the tilting rotor component 20 is relative to the wing 10
It verting to the first position, the tilting rotor component 20 provides lift for 300 VTOL of tilting rotor wing unmanned aerial vehicle,
And the undercarriage 30 is unfolded relative to the fuselage, and the undercarriage 30 can support the tilting rotor wing unmanned aerial vehicle 300.When
When 300 duration flight of tilting rotor wing unmanned aerial vehicle, the rotation of tilting rotor component 20 is described to vert to the second position
Rotor assemblies 20 are that the tilting rotor wing unmanned aerial vehicle 300 provides the thrust of duration flight, and the undercarriage 30 is relative to institute
Fuselage folding is stated, the undercarriage 30 is smaller to the flight resistance of the tilting rotor wing unmanned aerial vehicle 300.
It should be noted that the tilting rotor wing unmanned aerial vehicle 300, in duration flight, the tilting rotor component 20 provides
The thrust for making the tilting rotor wing unmanned aerial vehicle 300 advance, the wing 10 crosses air, due to the configuration of the wing 10, institute
The upper lower aerofoil for stating wing 10 has pressure difference, and the wing 10 generates the lift for making 300 floating of tilting rotor wing unmanned aerial vehicle, and
And the tilting rotor component 20 provides energy consumed by thrust and is consumed less than the tilting rotor component 20 offer lift
Energy, therefore, the tilting rotor wing unmanned aerial vehicle 300 can be with duration flight.
It is worth noting that the undercarriage 30 that can be folded relative to the fuselage 200 by setting, can avoid described rise
The visual angle that frame 30 blocks mapping camera or holder camera is fallen, for another angle, reduces light during man-machine design
Learn the arrangement difficulty of equipment.Further speaking, the tilting rotor wing unmanned aerial vehicle 300 only will use undercarriage in VTOL
30, and need to fold the undercarriage 30 in duration flight, therefore, the undercarriage 30 is installed on the tilting rotor
Component 20 does not need additionally to arrange motor to the undercarriage 30, makes the cruising ability of the tilting rotor wing unmanned aerial vehicle 300 and obtains
To promoted while, the weight saving of the tilting rotor wing unmanned aerial vehicle 300.In addition, when the tilting rotor wing unmanned aerial vehicle 300 is rising
When flying the stage, since the undercarriage 30 is installed on the tilting rotor component 20, and the undercarriage 30 connects with ground
Touching, namely one is increased to the tilting rotor component 20 on the direction perpendicular to ground in the tilting rotor component 20
Kinematic constraint cannot be moved towards ground direction, make the tilting rotor component 20 can only be along the direction face-up perpendicular to ground
Movement, weakens the vibration of the tilting rotor component 20, improves the stabilization when tilting rotor wing unmanned aerial vehicle 300 takes off
Property.
The wing 10 along its extension direction L be unfolded, the wing 10 have leading edge 11, rear 12, top airfoil 13 and
Lower aerofoil 14.Wherein, the leading edge 11 and the rear 12 are opposite, and the top airfoil 13 and the lower aerofoil 14 are opposite and connect
It is connected between the leading edge 11 and the rear 12, the leading edge 11, the rear 12, the top airfoil 13 and the bottom wing
Face 14 4 is all parallel to the extension direction L of the wing 10.
The tilting rotor component 20 includes mounting assembly 21, rotor mechanism 22 and motor (not shown) of verting.It is described
Mounting assembly 21 is connected with the wing 10, and the rotor mechanism 22 is installed on the mounting assembly 21, the rotor mechanism 22
It can vert relative to the wing 10 to the first position or the second position, the motor that verts is for driving the rotation
Wing mechanism 22 verts relative to the wing 10.
When 300 VTOL of tilting rotor wing unmanned aerial vehicle, the rotor mechanism 22 verts relative to the wing 10
To the first position, the rotor mechanism 22 provides lift for 300 VTOL of tilting rotor wing unmanned aerial vehicle.
When 300 duration flight of tilting rotor wing unmanned aerial vehicle, the rotor mechanism 22 verts relative to the wing 10
To the second position, the rotor mechanism 22 provides thrust for 300 duration flight of tilting rotor wing unmanned aerial vehicle.
The whole mounting assembly 21 is in hollow tubular, before one end of the mounting assembly 21 protrudes the wing 10
Edge 11, the rear 12 of the prominent wing 10 of the other end of the mounting assembly 21.
The mounting assembly 21 includes the first support 210 and the second support 211, and one end of first support 210 is prominent
The leading edge 11 of the wing 10, the other end of first support 210 and one end of second support 211 are connected to each other, described
The rear 12 of the prominent wing 10 of the other end of second support 211.
It is understood that according to the actual situation, in a first aspect, first support 210 and second support 211
It can be with integrated setting namely the mounting assembly 21 for an entirety.In second aspect, first support 210 and described
One in second support, 211 the two can be omitted.In the third aspect, the mounting assembly 21 can be omitted namely the rotation
Wing mechanism 22 is directly mounted at the wing 10.
The quantity of the rotor mechanism 22 is two, and one in two rotor mechanisms 22 is installed on described first
Seat 210 protrudes one end of the leading edge 11 of the wing 10, another in two rotor mechanisms 22 is installed on described second
The other end of the rear 12 of the prominent wing 10 of support 211.
When 300 VTOL of tilting rotor wing unmanned aerial vehicle, two rotor mechanisms 22 are both with respect to the wing
10 vert to first position, provide vertical lift jointly by two rotor mechanisms 22 for the tilting rotor wing unmanned aerial vehicle 300
Lift.
When 300 duration flight of tilting rotor wing unmanned aerial vehicle, two rotor mechanisms 22 are both with respect to the wing
10 vert to the second position, provide duration flight jointly by two rotor mechanisms 22 for the tilting rotor wing unmanned aerial vehicle 300
Thrust.
It is understood that according to the actual situation, the quantity of the rotor mechanism 22 is not limited to two, as long as at least
Be one, only by a rotor mechanism 22 be the tilting rotor wing unmanned aerial vehicle 300 provide VTOL lift or
The thrust of person's duration flight.
Also referring to Fig. 3, each rotor mechanism 22 include a motor cabinet 220, a rotor motor 221, with
An and propeller 222.The motor cabinet 220, the rotor motor 221 and the propeller 222 are sequentially connected.The electricity
Base 220 is installed on one end of the prominent leading edge 11 of the mounting assembly 21 or one end of the prominent rear 12, described
Motor cabinet 220 can vert relative to the wing 10.
Referring to Figure 4 together to Fig. 7, the motor cabinet 220, the rotor motor 221 and the propeller 222 are in line
Property distribution, for example, the motor cabinet 220, the rotor motor 221 and the propeller 222 are along the propeller 222
Rotation axis S distribution.When the rotor mechanism 22 verts relative to the wing 10 to first position, such as Fig. 4 and Fig. 6 institute
Show, the propeller 222 is located at the side of 13 direction of top airfoil.When the rotor mechanism 22 inclines relative to the wing 10
When going to the second position, as shown in figure 5 and figure 7, the propeller 222 is located at 13 direction of the leading edge 11 or the rear
Side.
The motor that verts is installed in the mounting assembly 21, and the motor that verts is for driving the motor cabinet 221
It verts relative to the wing 10, the quantity of the motor that verts is corresponding with the quantity of the rotor mechanism 22.
It should be noted that the motor that verts can be servo motor, or steering engine, the motor that verts can be with
The motor cabinet 221 is directly driven to vert relative to the wing 10, it can also be for example, by gear set, turbine and worm mechanism etc.
Transmission mechanism drives the motor cabinet 221 to vert relative to the wing 10.
The undercarriage 30 is installed on the motor cabinet 221, the quantity of the undercarriage 221 and the rotor mechanism 22
Quantity is corresponding.
The undercarriage 30 is whole L-shaped, and the undercarriage 30 includes support portion 31 and interconnecting piece 32.The interconnecting piece 32
One end connect the motor cabinet 221, the other end of the interconnecting piece 32 connects the support portion 31, the one of the support portion 31
End is connected with the interconnecting piece 32, and the other end of the support portion 31 extends towards the direction far from the propeller 222.
When the rotor mechanism 22 verts relative to the wing 10 to the first position, as shown in Figure 4 and Figure 6,
First support portion 31 is basically perpendicular to the lower aerofoil 14, and the support portion 31 is far from the another of the propeller 222
One end is located at one end of 14 direction of lower aerofoil, so that the support portion 31 can support the tilting rotor wing unmanned aerial vehicle
300。
When the rotor mechanism 22 verts relative to the wing 10 to the second position, as shown in figure 5 and figure 7,
The support portion 31 is basically parallel to the lower aerofoil 14, and the support portion 31 is located at the one of 14 direction of lower aerofoil
Side, so that the support portion 31 is small to the flight resistance of the tilting rotor wing unmanned aerial vehicle 300.
In some embodiments of the invention, the rotor mechanism 22 inclines around the center line O relative to the wing 10
Turn, the center line O is basically perpendicular to the extension direction S of the wing 10, and the center line O is parallel to the wing 10
Top airfoil 13 or lower aerofoil 14.
In some embodiments of the invention, the support portion 31 is parallel to the rotation axis S of the propeller 222.
In some embodiments of the invention, the interconnecting piece 32 and the support portion 31 are perpendicular.
It is worth noting that the interconnecting piece 32 avoids the branch for making the support portion 31 deviate the wing 10
Interference with the wing 10 support part 31.
It is understood that according to the actual situation, the interconnecting piece 32 can be omitted namely one end of the support portion 31
Directly it is connected with the motor cabinet 221.
The tilting rotor wing unmanned aerial vehicle 300 is specific as follows when specifically used:
When 300 VTOL of tilting rotor wing unmanned aerial vehicle, as shown in Fig. 1, Fig. 4 and Fig. 6, two rotor mechanisms
22 vert both with respect to the wing 10 to the first position, and the undercarriage 30 is unfolded relative to the wing 10, and two
The rotor mechanism 22 provides the lift of VTOL jointly for the tilting rotor wing unmanned aerial vehicle 300.
When the tilting rotor wing unmanned aerial vehicle 300 rises to preset height, as shown in figure 8, being located at the rotor of the leading edge 11
Mechanism 22 first gradually verts relative to the wing 10 to the second position, and the undercarriage 30 positioned at the leading edge 11 is opposite
It is folded in the wing 10, the rotor mechanism 22 positioned at the rear 12 is maintained at described first relative to the wing 10
It sets, continues the liter that the offer of the tilting rotor wing unmanned aerial vehicle 300 holding floating is provided positioned at the rotor mechanism 22 of the rear 12
Power.
When the flying speed of the tilting rotor wing unmanned aerial vehicle 300 is more than stalling speed, positioned at the rotor of the rear 12
Mechanism 22 rapidly verts relative to the wing 10 to the second position, positioned at the rear 12 undercarriage 30 relative to
The wing 10 folds, and two rotor mechanisms 22 provide pushing away for duration flight jointly for the tilting rotor wing unmanned aerial vehicle 300
Power, as shown in Fig. 2, Fig. 5 and Fig. 7.
Compared with prior art, tilting rotor wing unmanned aerial vehicle 300 and its wing components 100 provided in an embodiment of the present invention
In, the wing components 100 are used to be installed on the fuselage 200 of tilting rotor wing unmanned aerial vehicle 300, and the wing components 100 include: machine
The wing 10, for being installed on the fuselage 200: tilting rotor component 20, the tilting rotor component 20 is installed on the wing 10
The wing 10；And undercarriage 30, the undercarriage 30 are installed on the tilting rotor component 20；Wherein, the rotation of verting
Wing component 20 can vert relative to the wing 10 to first position or the second position；When the tilting rotor wing unmanned aerial vehicle 300 hangs down
When straight landing, the tilting rotor component 20 verts relative to the wing 10 to the first position, 30 phase of undercarriage
The wing 10 is unfolded, the tilting rotor component 20 is that the tilting rotor wing unmanned aerial vehicle 300 provides the liter of VTOL
Power；When 300 duration flight of tilting rotor wing unmanned aerial vehicle, the tilting rotor component 20 relative to the wing 10 vert to
The second position, the undercarriage 30 are folded relative to the wing 10, and the tilting rotor component 20 is the rotation of verting
The thrust of the offer duration flight of wing unmanned plane 300.It, can be real by the way that the undercarriage 30 is installed on the tilting rotor component 20
The undercarriage 30 of the existing tilting rotor wing unmanned aerial vehicle 300 can fold.
Finally, it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；At this
It under the thinking of invention, can also be combined between the technical characteristic in above embodiments or different embodiment, step can be with
It is realized with random order, and there are many other variations of different aspect present invention as described above, for simplicity, they do not have
Have and is provided in details；Although the present invention is described in detail referring to the foregoing embodiments, the ordinary skill people of this field
Member is it is understood that it is still possible to modify the technical solutions described in the foregoing embodiments, or to part of skill
Art feature is equivalently replaced；And these are modified or replaceed, each reality of the present invention that it does not separate the essence of the corresponding technical solution
Apply the range of a technical solution.
Claims (11)
1. a kind of wing components, for being installed on the fuselage of tilting rotor wing unmanned aerial vehicle, which is characterized in that the wing components packet
It includes:
Wing, the wing is for being installed on the fuselage:
Tilting rotor component, the tilting rotor component are installed on the wing；And
Undercarriage, the undercarriage are installed on the tilting rotor component；
Wherein, the tilting rotor component can be verted relative to the wing to first position or the second position；
When the tilting rotor wing unmanned aerial vehicle VTOL, the tilting rotor component verts relative to the wing to described
One position, the undercarriage are unfolded relative to the wing, and the tilting rotor component provides for the tilting rotor wing unmanned aerial vehicle
The lift of VTOL；
When the tilting rotor wing unmanned aerial vehicle duration flight, the tilting rotor component verts relative to the wing to described
Two positions, the undercarriage are provided relative to the wing-folding, the tilting rotor component for the tilting rotor wing unmanned aerial vehicle
The thrust of duration flight.
2. wing components according to claim 1, which is characterized in that the tilting rotor component includes rotor mechanism and branch
Holder assembly；
The mounting assembly is installed on the wing, and the rotor mechanism is installed on the mounting assembly, and the rotor mechanism can
It verts relative to the mounting assembly；
The undercarriage is installed on the rotor mechanism.
3. wing components according to claim 2, which is characterized in that the wing has leading edge and rear；
The prominent leading edge in one end of the mounting assembly or the rear；
The rotor mechanism is installed on one end of the prominent leading edge of the mounting assembly or the rear.
4. wing components according to claim 3, which is characterized in that the prominent leading edge in one end of the mounting assembly,
The prominent rear of the other end of the mounting assembly；
Two rotor mechanisms are respectively arranged in the both ends of the mounting assembly.
5. wing components according to claim 4, which is characterized in that the mounting assembly includes the first support and second
Seat；
The prominent leading edge in one end of first support, the other end of first support are connected to each other with second support,
The prominent rear of the other end of second support；
One in two rotor mechanisms is installed on the prominent described up-front one end of first support, two rotors
Another in mechanism is installed on one end of the prominent rear of second support.
6. wing components according to claim 4 or 5, which is characterized in that two undercarriages are respectively arranged in two
The rotor mechanism.
7. according to the described in any item wing components of claim 3 to 6, which is characterized in that the rotor mechanism includes successively phase
Motor cabinet, rotor motor and propeller even；
The motor cabinet is installed on the mounting assembly, and the undercarriage is installed on the motor cabinet, and the motor cabinet can be opposite
It verts in the wing.
8. wing components according to claim 7, which is characterized in that the propeller has rotation axis, the motor
Seat, the rotor motor and the propeller are linearly distributed.
9. wing components according to claim 7 or 8, which is characterized in that the undercarriage includes support portion；
One end of the support portion is connected to the motor cabinet, and the other end of the support portion is towards the direction far from the propeller
Extend.
10. wing components according to claim 9, which is characterized in that the undercarriage further includes interconnecting piece, the connection
Portion is connected between the support portion and the interconnecting piece.
11. a kind of tilting rotor wing unmanned aerial vehicle characterized by comprising
Fuselage；And
It is installed on the wing components as described in any one of claim 1 to 10 of the fuselage.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410488452.2A CN118358751A (en) | 2019-01-30 | 2019-01-30 | Tilt rotor unmanned aerial vehicle and wing subassembly thereof |
| CN201910093098.2A CN109573006B (en) | 2019-01-30 | 2019-01-30 | Tilt rotor unmanned aerial vehicle and wing subassembly thereof |
| PCT/CN2020/070952 WO2020156078A1 (en) | 2019-01-30 | 2020-01-08 | Tiltrotor unmanned aerial vehicle and wing assembly thereof |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110667836A (en) * | 2019-11-19 | 2020-01-10 | 北京煜邦电力技术股份有限公司 | Pure electric tilt rotor unmanned aerial vehicle and control method thereof |
| WO2020156078A1 (en) * | 2019-01-30 | 2020-08-06 | 深圳市道通智能航空技术有限公司 | Tiltrotor unmanned aerial vehicle and wing assembly thereof |
| CN112644697A (en) * | 2020-12-31 | 2021-04-13 | 成都翼展展科技有限公司 | Multi-rotor aircraft |
| CN113928551A (en) * | 2021-09-18 | 2022-01-14 | 南京航空航天大学 | Novel-structure combined type unmanned helicopter in near space and flight control method thereof |
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| CN113928551A (en) * | 2021-09-18 | 2022-01-14 | 南京航空航天大学 | Novel-structure combined type unmanned helicopter in near space and flight control method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN118358751A (en) | 2024-07-19 |
| CN109573006B (en) | 2024-04-12 |
| WO2020156078A1 (en) | 2020-08-06 |
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