CN209757510U - tilt rotor unmanned aerial vehicle and wing assembly thereof - Google Patents
tilt rotor unmanned aerial vehicle and wing assembly thereof Download PDFInfo
- Publication number
- CN209757510U CN209757510U CN201920180302.XU CN201920180302U CN209757510U CN 209757510 U CN209757510 U CN 209757510U CN 201920180302 U CN201920180302 U CN 201920180302U CN 209757510 U CN209757510 U CN 209757510U
- Authority
- CN
- China
- Prior art keywords
- wing
- assembly
- rotor
- aerial vehicle
- unmanned aerial
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000007246 mechanism Effects 0.000 claims description 55
- 230000001133 acceleration Effects 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000001174 ascending effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- DMBHHRLKUKUOEG-UHFFFAOYSA-N diphenylamine Chemical compound C=1C=CC=CC=1NC1=CC=CC=C1 DMBHHRLKUKUOEG-UHFFFAOYSA-N 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Landscapes
- Toys (AREA)
Abstract
The utility model relates to an unmanned vehicles technical field discloses a rotor unmanned aerial vehicle verts and wing assembly thereof, and the wing assembly is arranged in installing in rotor unmanned aerial vehicle's that verts fuselage, and the wing assembly includes: a wing for mounting to a fuselage: a tiltrotor assembly mounted to the wing; and a landing gear mounted to the tiltrotor assembly; when the tilt rotor unmanned aerial vehicle vertically takes off and lands, the tilt rotor assembly tilts relative to the wing to a first position, the undercarriage expands relative to the wing, and the tilt rotor assembly provides the lift force for the tilt rotor unmanned aerial vehicle to vertically take off and land; when rotor unmanned aerial vehicle that verts continues a journey the flight, the rotor subassembly that verts to the second position for the wing, and the undercarriage is folding for the wing, and the rotor subassembly that verts provides the thrust of continuation of a journey flight for rotor unmanned aerial vehicle that verts. Through installing the undercarriage in the rotor subassembly that verts, the undercarriage that can realize rotor unmanned aerial vehicle that verts can be folded.
Description
[ technical field ] A method for producing a semiconductor device
The utility model relates to an unmanned vehicles field especially relates to a rotor unmanned aerial vehicle verts and wing subassembly thereof.
[ background of the invention ]
Rotor unmanned aerial vehicle verts need not the race when one kind takes off, can accomplish unmanned aerial vehicle's taking off and descending in situ. When aerial, rotor unmanned aerial vehicle's that verts rotor subassembly verts along with flying speed's improvement, treat that rotor unmanned aerial vehicle that verts surpass certain stall speed after, the rotor subassembly that verts accomplishes and verts, the output direction of the rotor subassembly that verts is approximately perpendicular with the air incoming flow direction to make rotor unmanned aerial vehicle that verts produce buoyancy through the wing, guaranteed rotor unmanned aerial vehicle's that verts continuation of the journey flight ability.
Light-duty rotor unmanned aerial vehicle that verts is because the restriction of structure weight, and the undercarriage is mostly fixed, consequently, rotor unmanned aerial vehicle that verts when flying, and the undercarriage has increased rotor unmanned aerial vehicle's that verts flight resistance, in addition, because the undercarriage can't be packed up, leads to the undercarriage to shelter from the visual angle of survey and drawing camera or cloud platform camera.
[ summary of the invention ]
In order to solve the technical problem, the embodiment of the utility model provides a folding rotor unmanned aerial vehicle that verts of undercarriage and wing thereof is provided.
In order to solve the technical problem, an embodiment of the utility model provides a following technical scheme:
On the one hand, a wing assembly is provided for install in tiltrotor unmanned aerial vehicle's fuselage, the wing assembly includes: a wing for mounting to the fuselage: a tiltrotor assembly mounted to the wing; and a landing gear mounted to the tiltrotor assembly; wherein the tiltrotor assembly is tiltable relative to the wing to a first position or a second position; when the tilt rotor unmanned aerial vehicle vertically takes off and lands, the tilt rotor assembly tilts relative to the wing to the first position, the undercarriage expands relative to the wing, and the tilt rotor assembly provides the lift force for the tilt rotor unmanned aerial vehicle to vertically take off and land; work as when tilting rotor unmanned aerial vehicle duration flight, the rotor subassembly that verts for the wing verts extremely the second position, the undercarriage for the wing is folding, the rotor subassembly that verts does tilting unmanned aerial vehicle provides the thrust of duration flight.
In some embodiments, the tiltrotor assembly includes a rotor mechanism and a mount assembly; said mast assembly being mounted to said wing, said rotor mechanism being mounted to said mast assembly, said rotor mechanism being tiltable relative to said mast assembly; the landing gear is mounted to the rotor mechanism.
In some embodiments, the airfoil has a leading edge and a trailing edge; one end of the support assembly protrudes out of the front edge or the rear edge; the rotor mechanism is mounted at one end of the support assembly protruding from the leading edge or the trailing edge.
In some embodiments, one end of the standoff assembly protrudes beyond the leading edge and the other end of the standoff assembly protrudes beyond the trailing edge; two rotor mechanisms are respectively arranged at two ends of the support component.
In some embodiments, the mount assembly comprises a first mount and a second mount; one end of the first support protrudes out of the front edge, the other end of the first support is butted with the second support, and the other end of the second support protrudes out of the rear edge; one of the two rotor mechanisms is mounted on one end of the first support protruding out of the leading edge, and the other of the two rotor mechanisms is mounted on one end of the second support protruding out of the trailing edge.
In some embodiments, two of the landing gears are mounted to two of the rotor mechanisms, respectively.
in some embodiments, the rotor mechanism comprises a motor base, a rotor motor and a propeller which are connected in sequence; the motor mount is mounted to the carrier assembly, the landing gear is mounted to the motor mount, and the motor mount is tiltable relative to the wing.
In some embodiments, the propeller has an axis of rotation, and the motor mount, the rotor motor, and the propeller are linearly distributed.
In some embodiments, the landing gear includes a support portion; one end of the supporting part is connected to the motor base, and the other end of the supporting part extends towards the direction far away from the propeller.
In some embodiments, the landing gear further comprises a connecting portion connected between the support portion and the connecting portion.
In another aspect, a tilt rotor unmanned aerial vehicle is provided, comprising: a body; and a wing assembly as described above mounted to the fuselage.
Compared with the prior art, the embodiment of the utility model provides an among the rotor unmanned aerial vehicle verts and the wing subassembly thereof, the wing subassembly is arranged in installing in rotor unmanned aerial vehicle's that verts fuselage, the wing subassembly includes: a wing for mounting to the fuselage: a tiltrotor assembly mounted to the wing; and a landing gear mounted to the tiltrotor assembly; wherein the tiltrotor assembly is tiltable relative to the wing to a first position or a second position; when the tilt rotor unmanned aerial vehicle vertically takes off and lands, the tilt rotor assembly tilts relative to the wing to the first position, the undercarriage expands relative to the wing, and the tilt rotor assembly provides the lift force for the tilt rotor unmanned aerial vehicle to vertically take off and land; work as when tilting rotor unmanned aerial vehicle duration flight, the rotor subassembly that verts for the wing verts extremely the second position, the undercarriage for the wing is folding, the rotor subassembly that verts does tilting unmanned aerial vehicle provides the thrust of duration flight. Through inciting somebody to action the undercarriage install in the rotor subassembly that verts can be realized rotor unmanned aerial vehicle's undercarriage that verts can fold.
[ description of the drawings ]
one or more embodiments are illustrated in drawings corresponding to, and not limiting to, the embodiments, in which elements having the same reference number designation may be represented as similar elements, unless specifically noted, the drawings in the figures are not to scale.
Fig. 1 is a perspective view of a tilt rotor unmanned aerial vehicle in a vertical take-off and landing state according to an embodiment of the present invention;
fig. 2 is a perspective view of the tilt rotor drone shown in fig. 1 in a continuous flight state;
fig. 3 is a perspective view of the landing gear and tilt rotor assembly of the tilt rotor drone shown in fig. 1;
Fig. 4 is a side view of the tilt rotor drone shown in fig. 1;
fig. 5 is a side view of the tilt rotor drone shown in fig. 2;
Fig. 6 is a front view of the tilt rotor drone shown in fig. 1;
Fig. 7 is a front view of the tilt rotor drone shown in fig. 2;
Fig. 8 is a perspective view of the tilt rotor drone shown in fig. 1 during an acceleration phase.
[ detailed description ] embodiments
in order to facilitate understanding of the present invention, the present invention will be described in more detail with reference to the accompanying drawings and embodiments. It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may be present. The terms "vertical," "horizontal," "left," "right," "inner," "outer," and the like as used herein are for descriptive purposes only.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
Referring to fig. 1 and fig. 2, a tilt rotor unmanned aerial vehicle 300 according to an embodiment of the present invention includes a fuselage 200 and a wing assembly 100. Wherein the wing assembly 100 is mounted to the fuselage 200.
Fuselage 200 is whole to be fusiformis, include the control circuit subassembly that comprises electronic components such as MCU in the fuselage 200, this control circuit subassembly includes a plurality of control module, if, is used for control tilt rotor unmanned aerial vehicle 300 flight attitude fly control module, be used for the navigation tilt rotor unmanned aerial vehicle 300's big dipper module and be used for handling the data processing module etc. of the environmental information that relevant airborne equipment obtained.
the wing assembly 100 includes a wing 10, a tiltrotor assembly 20, and a landing gear 30. Wherein wing 10 is installed in fuselage 200, tiltrotor assembly 20 is installed in wing 10, landing gear 30 is installed in tiltrotor assembly 20, tiltrotor assembly 20 is tiltable to a first position or a second position relative to fuselage 10.
Tilt rotor unmanned aerial vehicle 100 has two flight states, be VTOL state and continuation of the journey flight state respectively. Wherein, when tilt rotor unmanned aerial vehicle 100 VTOL, tilt rotor assembly 20 for wing 10 tilts extremely first position, tilt rotor assembly 20 does tilt rotor unmanned aerial vehicle 300 VTOL provides lift, and undercarriage 30 for the fuselage expandes, undercarriage 30 can support tilt rotor unmanned aerial vehicle 300. Work as when tilting rotor unmanned aerial vehicle 300 duration flight, tilting rotor subassembly 20 is rotatory extremely the second position, tilting rotor subassembly 20 does tilting rotor unmanned aerial vehicle 300 provides the thrust of duration flight, and undercarriage 30 for the fuselage is folding, undercarriage 30 is right tilting rotor unmanned aerial vehicle 300's flight resistance is less.
It should be noted that, tilt rotor unmanned aerial vehicle 300 is when endurance flight, tilt rotor assembly 20 provides the messenger tilt rotor unmanned aerial vehicle 300 advances's thrust, wing 10 crosses the air, because the configuration of wing 10, the upper and lower airfoil of wing 10 has pressure differential, wing 10 produces and makes tilt rotor unmanned aerial vehicle 300 floats the lift of sky, and tilt rotor assembly 20 provides the energy that thrust consumed is less than tilt rotor assembly 20 provides the energy that lift consumed, consequently, tilt rotor unmanned aerial vehicle 300 can endurance flight.
It should be noted that, by providing the landing gear 30 that can be folded with respect to the body 200, the landing gear 30 can be prevented from obstructing the view angle of the surveying camera or the pan-tilt camera, and from another perspective, the difficulty of arranging the optical devices in the man-machine design process is reduced. Further, tilt rotor unmanned aerial vehicle 300 only can use undercarriage 30 when VTOL, and need make when continuation of the journey flight undercarriage 30 is folding, consequently, will undercarriage 30 install in tilt rotor subassembly 20 need not additionally give undercarriage 30 arranges the motor, makes tilt rotor unmanned aerial vehicle 300's duration and the time that obtains the promotion, tilt rotor unmanned aerial vehicle 300's weight reduction. Furthermore, when tilt rotor unmanned aerial vehicle 300 is at the stage of taking off, because undercarriage 30 install in on tilt rotor subassembly 20, and undercarriage 30 and ground contact, also be in tilt rotor subassembly 20 gives in the direction on perpendicular to ground tilt rotor subassembly 20 has increased a motion constraint, can not move towards ground direction promptly, makes tilt rotor subassembly 20 can only follow the ascending direction motion on perpendicular to ground, has weakened tilt rotor subassembly 20's vibrations have improved stability when tilt rotor unmanned aerial vehicle 300 takes off.
The wing 10 is deployed in its direction of extension L, the wing 10 having a leading edge 11, a trailing edge 12, an upper airfoil surface 13 and a lower airfoil surface 14. Wherein the leading edge 11 and the trailing edge 12 are opposite, the upper airfoil surface 13 and the lower airfoil surface 14 are opposite and are connected between the leading edge 11 and the trailing edge 12, and the leading edge 11, the trailing edge 12, the upper airfoil surface 13 and the lower airfoil surface 14 are all parallel to the extending direction L of the wing 10.
Tilt rotor assembly 20 includes a mount assembly 21, a rotor mechanism 22, and a tilt motor (not shown). Support assembly 21 with wing 10 links to each other, rotor mechanism 22 install in support assembly 21, rotor mechanism 22 can tilt to first position or the second position for wing 10, the tilt motor is used for driving rotor mechanism 22 tilts for wing 10.
when tilt rotor unmanned aerial vehicle 300 VTOL, rotor mechanism 22 for wing 10 tilts extremely first position, rotor mechanism 22 does tilt rotor unmanned aerial vehicle 300 VTOL provides lift.
When 300 flight that continues of rotor unmanned aerial vehicle that verts, rotor mechanism 22 for wing 10 verts extremely the second position, rotor mechanism 22 does 300 flight that continues of rotor unmanned aerial vehicle that verts provides thrust.
the support assembly 21 is hollow and cylindrical as a whole, one end of the support assembly 21 protrudes out of the leading edge 11 of the wing 10, and the other end of the support assembly 21 protrudes out of the trailing edge 12 of the wing 10.
The support assembly 21 comprises a first support 210 and a second support 211, one end of the first support 210 protrudes from the leading edge 11 of the wing 10, the other end of the first support 210 is butted against one end of the second support 211, and the other end of the second support 211 protrudes from the trailing edge 12 of the wing 10.
It is understood that, according to the practical situation, in the first aspect, the first support 210 and the second support 211 may be integrally provided, that is, the support assembly 21 is an integral body. In the second aspect, one of the first and second holders 210 and 211 may be omitted. In a third aspect, the mount assembly 21 may be omitted, i.e. the rotor mechanism 22 is mounted directly to the wing 10.
the number of the rotor mechanisms 22 is two, one of the two rotor mechanisms 22 is installed at one end of the first support 210 protruding from the leading edge 11 of the wing 10, and the other of the two rotor mechanisms 22 is installed at the other end of the second support 211 protruding from the trailing edge 12 of the wing 10.
when tilting rotor unmanned aerial vehicle 300 VTOL, two rotor mechanism 22 all relative to wing 10 verts to the first position, by two rotor mechanism 22 does jointly tilt rotor unmanned aerial vehicle 300 provides the lift of vertical lift.
work as when tilting rotor unmanned aerial vehicle 300 duration flight, two rotor mechanism 22 homogeneous phase is relative wing 10 verts to the second position, by two rotor mechanism 22 does jointly tilt rotor unmanned aerial vehicle 300 provides the thrust of duration flight.
It is understood that, according to practical conditions, the number of the rotor mechanisms 22 is not limited to two, and at least one rotor mechanism 22 is provided for providing the tilt rotor drone 300 with the lift force of vertical take-off and landing or the thrust force of endurance flight.
Referring also to fig. 3, each of the rotor mechanisms 22 includes a motor base 220, a rotor motor 221, and a propeller 222. The motor base 220, the rotor motor 221, and the propeller 222 are connected in sequence. The motor mount 220 is mounted on one end of the support assembly 21 protruding from the leading edge 11 or protruding from one end of the trailing edge 12, and the motor mount 220 can be tilted with respect to the wing 10.
referring to fig. 4 to 7, the motor base 220, the rotor motor 221, and the propeller 222 are linearly arranged, for example, the motor base 220, the rotor motor 221, and the propeller 222 are arranged along the rotation axis S of the propeller 222. When the rotor mechanism 22 is tilted to a first position relative to the wing 10, as shown in fig. 4 and 6, the propeller 222 is located on the side of the upper airfoil surface 13 facing. When the rotor mechanism 22 is tilted to a second position relative to the wing 10, as shown in fig. 5 and 7, the propeller 222 is located on the side toward which the leading edge 11 or the trailing edge 13 faces.
The motor that verts install in support subassembly 21, the motor that verts is used for the drive the motor cabinet 221 for wing 10 verts, the quantity of the motor that verts with the quantity of rotor mechanism 22 corresponds.
The tilting motor may be a servo motor or a steering engine, and the tilting motor may directly drive the motor base 221 to tilt relative to the wing 10, or may drive the motor base 221 to tilt relative to the wing 10 through a transmission mechanism such as a gear set or a worm gear mechanism.
The landing gears 30 are mounted to the motor base 221, and the number of the landing gears 221 corresponds to the number of the rotor mechanisms 22.
The landing gear 30 is L-shaped as a whole, and the landing gear 30 includes a support portion 31 and a connecting portion 32. One end of the connecting portion 32 is connected to the motor base 221, the other end of the connecting portion 32 is connected to the supporting portion 31, one end of the supporting portion 31 is connected to the connecting portion 32, and the other end of the supporting portion 31 extends in a direction away from the propeller 222.
When the rotor mechanism 22 is tilted to the first position relative to the wing 10, as shown in fig. 4 and 6, the first support portion 31 is substantially perpendicular to the lower wing surface 14, and the other end of the support portion 31 away from the propeller 222 is located at the end of the lower wing surface 14 facing the lower wing surface, so that the support portion 31 can support the tilt rotor drone 300.
When the rotor mechanism 22 is tilted to the second position relative to the wing 10, as shown in fig. 5 and 7, the strut 31 is substantially parallel to the lower wing surface 14, and the strut 31 is located on the side of the lower wing surface 14 facing, so that the flight resistance of the strut 31 to the tilt-rotor drone 300 is small.
In some embodiments of the present invention, the rotor mechanism 22 is tilted with respect to the wing 10 about the center line O, the center line O is substantially perpendicular to the extending direction S of the wing 10, and the center line O is parallel to the upper airfoil surface 13 or the lower airfoil surface 14 of the wing 10.
In some embodiments of the present invention, the support portion 31 is parallel to the rotation axis S of the propeller 222.
in some embodiments of the present invention, the connecting portion 32 is perpendicular to the supporting portion 31.
It is worth mentioning that the connecting portion 32 is used to offset the supporting portion 31 from the wing 10, so as to avoid the interference between the supporting portion 31 and the wing 10.
It is understood that, according to practical circumstances, the connecting portion 32 may be omitted, that is, one end of the supporting portion 31 is directly connected to the motor base 221.
tilt rotor unmanned aerial vehicle 300 is when specifically using, specifically as follows:
when tilting rotor unmanned aerial vehicle 300 VTOL, as shown in FIG. 1, FIG. 4 and FIG. 6, two rotor mechanism 22 all for wing 10 tilts extremely the first position, undercarriage 30 for wing 10 expandes, two rotor mechanism 22 does jointly tilt rotor unmanned aerial vehicle 300 provides the lift of VTOL.
When the tilt rotor drone 300 is raised to a preset height, as shown in fig. 8, the rotor mechanism 22 at the leading edge 11 is gradually tilted to the second position relative to the wing 10, the landing gear 30 at the leading edge 11 is folded relative to the wing 10, the rotor mechanism 22 at the trailing edge 12 is maintained at the first position relative to the wing 10, and the rotor mechanism 22 at the trailing edge 12 continues to provide lift to the tilt rotor drone 300 to maintain the air.
When the flight speed of the tilt rotor drone 300 exceeds the stall speed, the rotor mechanism 22 at the trailing edge 12 rapidly tilts relative to the wing 10 to the second position, the landing gear 30 at the trailing edge 12 folds relative to the wing 10, and the two rotor mechanisms 22 together provide the thrust of the endurance flight for the tilt rotor drone 300, as shown in fig. 2, 5 and 7.
compared with the prior art, the embodiment of the utility model provides an among tilt rotor unmanned aerial vehicle 300 and wing subassembly 100 thereof, wing subassembly 100 is arranged in installing in the fuselage 200 of tilt rotor unmanned aerial vehicle 300, wing subassembly 100 includes: a wing 10, the wing 10 for mounting to the fuselage 200: a tiltrotor assembly 20, said tiltrotor assembly 20 being mounted to said wing 10; and a landing gear 30, said landing gear 30 being mounted to said tiltrotor assembly 20; wherein the tiltrotor rotor assembly 20 is tiltable relative to the wing 10 to a first position or a second position; when the tilt rotor drone 300 is vertically takeoff and landing, the tilt rotor assembly 20 tilts relative to the wing 10 to the first position, the landing gear 30 is deployed relative to the wing 10, and the tilt rotor assembly 20 provides the tilt rotor drone 300 with vertical takeoff and landing lift; when tilt rotor unmanned aerial vehicle 300 continues to fly, tilt rotor assembly 20 for wing 10 tilts extremely the second position, undercarriage 30 for wing 10 is folded, tilt rotor assembly 20 does tilt rotor unmanned aerial vehicle 300 provides the thrust of continuation of the journey flight. By mounting the landing gear 30 in the tilt rotor assembly 20, it is possible to realize that the landing gear 30 of the tilt rotor drone 300 can be folded.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit it; within the idea of the invention, also technical features in the above embodiments or in different embodiments can be combined, steps can be implemented in any order, and there are many other variations of the different aspects of the invention as described above, which are not provided in detail for the sake of brevity; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention.
Claims (11)
1. the utility model provides a wing assembly for install in rotor unmanned aerial vehicle's fuselage that verts, a serial communication port, wing assembly includes:
A wing for mounting to the fuselage:
A tiltrotor assembly mounted to the wing; and
an undercarriage mounted to the tiltrotor assembly;
Wherein the tiltrotor assembly is tiltable relative to the wing to a first position or a second position;
When the tilt rotor unmanned aerial vehicle vertically takes off and lands, the tilt rotor assembly tilts relative to the wing to the first position, the undercarriage expands relative to the wing, and the tilt rotor assembly provides the lift force for the tilt rotor unmanned aerial vehicle to vertically take off and land;
Work as when tilting rotor unmanned aerial vehicle duration flight, the rotor subassembly that verts for the wing verts extremely the second position, the undercarriage for the wing is folding, the rotor subassembly that verts does tilting unmanned aerial vehicle provides the thrust of duration flight.
2. The wing assembly of claim 1, wherein the tiltrotor assembly includes a rotor mechanism and a mount assembly;
Said mast assembly being mounted to said wing, said rotor mechanism being mounted to said mast assembly, said rotor mechanism being tiltable relative to said mast assembly;
The landing gear is mounted to the rotor mechanism.
3. The wing assembly of claim 2, wherein the wing has a leading edge and a trailing edge;
One end of the support assembly protrudes out of the front edge or the rear edge;
The rotor mechanism is mounted at one end of the support assembly protruding from the leading edge or the trailing edge.
4. the wing assembly of claim 3, wherein one end of the strut assembly protrudes beyond the leading edge and the other end of the strut assembly protrudes beyond the trailing edge;
Two rotor mechanisms are respectively arranged at two ends of the support component.
5. The wing assembly of claim 4, wherein the mount assembly includes a first mount and a second mount;
One end of the first support protrudes out of the front edge, the other end of the first support is butted with the second support, and the other end of the second support protrudes out of the rear edge;
One of the two rotor mechanisms is mounted on one end of the first support protruding out of the leading edge, and the other of the two rotor mechanisms is mounted on one end of the second support protruding out of the trailing edge.
6. the wing assembly of claim 4, wherein two of the landing gears are mounted to two of the rotor mechanisms, respectively.
7. The wing assembly of any of claims 3 to 5, wherein the rotor mechanism comprises a motor mount, a rotor motor, and a propeller connected in series;
The motor mount is mounted to the carrier assembly, the landing gear is mounted to the motor mount, and the motor mount is tiltable relative to the wing.
8. The wing assembly of claim 7, wherein the propellers have an axis of rotation, and the motor mounts, the rotor motors, and the propellers are linearly distributed.
9. The wing assembly of claim 7, wherein the landing gear includes a support portion;
One end of the supporting part is connected to the motor base, and the other end of the supporting part extends towards the direction far away from the propeller.
10. the wing assembly of claim 9, wherein the landing gear further comprises a connection portion connected between the support portion and the connection portion.
11. The utility model provides a rotor unmanned aerial vehicle verts which characterized in that includes:
A body; and
A wing assembly as claimed in any one of claims 1 to 10 mounted to the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920180302.XU CN209757510U (en) | 2019-01-30 | 2019-01-30 | tilt rotor unmanned aerial vehicle and wing assembly thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920180302.XU CN209757510U (en) | 2019-01-30 | 2019-01-30 | tilt rotor unmanned aerial vehicle and wing assembly thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209757510U true CN209757510U (en) | 2019-12-10 |
Family
ID=68751324
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920180302.XU Active CN209757510U (en) | 2019-01-30 | 2019-01-30 | tilt rotor unmanned aerial vehicle and wing assembly thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209757510U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109573006A (en) * | 2019-01-30 | 2019-04-05 | 深圳市道通智能航空技术有限公司 | A kind of tilting rotor wing unmanned aerial vehicle and its wing components |
-
2019
- 2019-01-30 CN CN201920180302.XU patent/CN209757510U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109573006A (en) * | 2019-01-30 | 2019-04-05 | 深圳市道通智能航空技术有限公司 | A kind of tilting rotor wing unmanned aerial vehicle and its wing components |
| 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 |
| CN109573006B (en) * | 2019-01-30 | 2024-04-12 | 深圳市道通智能航空技术股份有限公司 | Tilt rotor unmanned aerial vehicle and wing subassembly thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10144509B2 (en) | High performance VTOL aircraft | |
| CN109573006B (en) | Tilt rotor unmanned aerial vehicle and wing subassembly thereof | |
| CN205707297U (en) | Fixed-wing unmanned plane | |
| US4678141A (en) | Aircraft launcher and retriever | |
| JP6731604B2 (en) | High-speed drones and other aircraft | |
| CN103950537B (en) | The control method of displacement aircraft and control setup | |
| WO2016028358A2 (en) | High Performance VTOL Aircraft | |
| WO2015099603A1 (en) | An unmanned aerial vehicle | |
| CN113165736B (en) | Manned flying object | |
| CN107444606B (en) | Novel aircraft and aircraft system | |
| JP7244084B2 (en) | Electronic parts and aircraft equipped with such electronic parts | |
| CN209757510U (en) | tilt rotor unmanned aerial vehicle and wing assembly thereof | |
| CN114793429A (en) | take-off and landing system | |
| CN213735508U (en) | Tandem wing tilt rotor aircraft | |
| CN114206723B (en) | Flying object and flying method of flying object | |
| EP3736213A1 (en) | Hybrid unmanned aerial vehicle | |
| CN217864732U (en) | Rhombic composite wing aircraft | |
| CN217864733U (en) | Compact rhombic composite wing aircraft | |
| KR20180033011A (en) | Drone having multi-function legs working as wings | |
| US11760475B2 (en) | Articulated tiltrotor | |
| CN212890923U (en) | Vertical take-off and landing fixed-wing tiltrotor aircraft | |
| CN104229130A (en) | Four-rotor wing unmanned aerial vehicle with pneumatic structure | |
| CN214084750U (en) | Unmanned plane | |
| WO2021157343A1 (en) | Vertical takeoff and landing aircraft | |
| CN108545182A (en) | A kind of VTOL fixed-wing unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 518055 Guangdong city of Shenzhen province Nanshan District Xili Street Xueyuan Road No. 1001 Chi Yuen Building 9 layer B1 Patentee after: Shenzhen daotong intelligent Aviation Technology Co.,Ltd. Address before: 518055 Guangdong city of Shenzhen province Nanshan District Xili Street Xueyuan Road No. 1001 Chi Yuen Building 9 layer B1 Patentee before: AUTEL ROBOTICS Co.,Ltd. |