CN206914635U - A kind of compound unmanned plane - Google Patents
A kind of compound unmanned plane Download PDFInfo
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- CN206914635U CN206914635U CN201720805365.0U CN201720805365U CN206914635U CN 206914635 U CN206914635 U CN 206914635U CN 201720805365 U CN201720805365 U CN 201720805365U CN 206914635 U CN206914635 U CN 206914635U
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Abstract
The utility model belongs to compound unmanned plane field, disclose a kind of compound unmanned plane, including fuselage, it is fixed on the propeller of afterbody, it is fixed on the wing of fuselage upper end, symmetrical the first link for being fixed on both sides below wing, two first link one end and the tail of falling V set in inverted V-shaped are connected to simultaneously, it is connected to the first link other end and the first rotor of the switching that can be verted in horizontal level and vertical position, it is connected to the tail of falling V center and can be verted switching and the second rotor for verting of the left and right sides in horizontal level and vertical position, first power set, second power set and the 3rd power set.The advantages of said structure causes compound unmanned plane to take into account fixed-wing unmanned plane and rotor wing unmanned aerial vehicle, and it is not interfere with each other between wing and rotor, simplify operation, the power of compound unmanned plane VTOL can be provided, and can provides power during follow-on mission, and landing is convenient, cruising time is long, flying speed is fast.
Description
Technical field
It the utility model is related to compound unmanned air vehicle technique field, more particularly to a kind of compound unmanned plane.
Background technology
Common unmanned plane type is broadly divided into fixed-wing unmanned plane and rotor wing unmanned aerial vehicle.Wherein fixed-wing unmanned plane takes off
It is required for specific runway to be slided for it with landing, and the thrust advanced or pulling force is produced by power set, by consolidates for fuselage
Determine wing and produce lift.Its flying speed is fast, voyage and cruise time length, but landing distance, it is desirable to the runway of high quality, sternly
Ghost image sound and the development for hampering fixed-wing unmanned plane.
And rotor wing unmanned aerial vehicle includes two kinds of structures of single rotor and more rotors, provided by engine or motor driving rotor
Lift, unmanned plane is drawn high aerial.Its advantage is can be remote not in smaller place VTOL, hovering, but its efficiency
Such as fixed-wing unmanned plane, power consumption is big, speed is slow, short cruising time is also the shortcomings that rotor wing unmanned aerial vehicle is present.
Disclose the compound unmanned plane of a kind of fixed-wing and more rotors composition in the prior art, have both fixed-wing unmanned plane and
The characteristic of rotor wing unmanned aerial vehicle, and the switching of wing offline mode and rotor flying pattern can be fixed at any time, but it is switching
During to fixed-wing offline mode, although electronic more rotors stopped power supply, but the shape of rotor and construction are in flight gas
Into the burden of compound unmanned plane during flying in stream, resistance is on the one hand increased, on the other hand increases manipulation difficulty, is failed two
Person is perfectly combined together.Therefore, how to design the advantages of one kind takes into account fixed-wing unmanned plane and rotor wing unmanned aerial vehicle and mutually not
The compound unmanned plane of interference, is to solve the problems, such as at present.
Utility model content
The purpose of this utility model is to provide a kind of compound unmanned plane, has taken into account fixed-wing unmanned plane and rotor wing unmanned aerial vehicle
The advantages of and do not interfere with each other.
To use following technical scheme up to this purpose, the utility model：
A kind of compound unmanned plane, including fuselage, be fixed on the propeller of afterbody, be fixed on fuselage upper end wing,
It is symmetrical to be fixed on the first link of both sides below wing while be connected to two first link one end and set in inverted V-shaped
The tail of falling V, be connected to the first link other end and can horizontal level and vertical position vert switching the first rotor, even
Be connected to the tail of falling V center and can horizontal level and vertical position vert switching and the left and right sides vert second rotation
The wing, the first power set for driving propeller rotational, the second power set for driving the first rotor rotational and the rotation of driving second
The 3rd power set that the wing rotates.
Preferably, first link is provided with the component that verts, the component that verts is used to control first rotation
The wing verts switching in horizontal level and vertical position, and second power set are arranged on vert component and first rotation
Between the wing.
Preferably, the tail of falling V verts component provided with first component and second that verts, described first verts component use
Verted switching in horizontal level and vertical position in vert component and the second rotor of control described second, described second verts component
For controlling second rotor to vert both sides to the left and right, the 3rd power set are arranged on described second and verted component and institute
State between the second rotor.
Preferably, during two first rotor rotationals, the rotation direction of two the first rotors is opposite.
Preferably, first link is elongated rod shape structure, and connect along fuselage head to caudal directions, described first
The sectional area for connecing frame tapers into.
Preferably, the tail of falling V is set relative to the symmetrical plane of two the first links in symmetrical structure.
The beneficial effects of the utility model：Passing through said structure so that compound unmanned plane has fixed wing and rotor concurrently,
The advantages of having taken into account fixed-wing unmanned plane and rotor wing unmanned aerial vehicle, and do not interfere with each other between wing and rotor, operation is simplified, both
The power of compound unmanned plane VTOL can be provided, and can provides power during follow-on mission, landing is convenient, cruising time is long,
Flying speed is fast.
Brief description of the drawings
Fig. 1 is the dimensional structure diagram of the compound unmanned plane of the utility model；
Fig. 2 is enlarged drawing at the utility model Fig. 1 I；
Fig. 3 is the view that the compound rotor of unmanned plane first of the utility model and the second rotor are horizontal；
Fig. 4 is the view that the compound rotor of unmanned plane first of the utility model and the second rotor are in vertical position.
In figure：
1st, fuselage；2nd, propeller；3rd, wing；4th, the first link；5th, the tail of falling V；6th, the first rotor；7th, the second rotor；8、
First power set；9th, the second power set；10th, the 3rd power set；11st, vert component；12nd, first verts component；13rd,
Two vert component；51st, empennage.
Embodiment
Further illustrate the technical solution of the utility model below in conjunction with the accompanying drawings and by embodiment.
The utility model provides a kind of compound unmanned plane, and as Figure 1-4, the compound unmanned plane includes fuselage 1, propeller
2nd, wing 3, the first link 4, the tail of falling V 5, the first rotor 6, the second rotor 7, the first power set 8, the second power set 9 with
And the 3rd power set 10, wherein the first power set 8, the second power set 9 and the 3rd power set 10 are all connected to control
Device (not shown) processed.
Above-mentioned propeller 2 is fixed on the afterbody of fuselage 1, and it is connected to above-mentioned first power set 8, and is filled by the first power
8 drives rotation is put, to drive compound unmanned plane during flying.Specifically, above-mentioned first power set 8 can be to be connected to controller
Motor or servomotor, and first power set 8 can set head or the afterbody of fuselage 1, it is as the present embodiment
Main power source during compound unmanned plane during flying.First power set 8 are arranged on the afterbody of fuselage 1 by the present embodiment, such as Fig. 1 institutes
Show.
End is fixed with above-mentioned wing 3 on the fuselage 1, and the wing 3 is used for when compound unmanned plane is in high-altitude flight state,
Propeller 2 is coordinated to realize the follow-on mission of compound unmanned plane together.
Above-mentioned first link 4 is provided with two, is symmetrically fixed on the above-mentioned lower section both sides of wing 3, can refer to Fig. 1, should
First link 4 is elongated rod shape structure, and gradually become along the head of fuselage 1 to caudal directions, the sectional area of first link 4
It is small, set by said structure, enable to the center of gravity of compound unmanned plane to be in and meet the position that flight requires, and then improve multiple
Close the overall performance of unmanned plane.It is, of course, understood that first link 4 can also be other structures, it disclosure satisfy that and set
Meter requires.
In the present embodiment, above-mentioned first link 4 one end big close to the head of fuselage 1 i.e. sectional area is connected with first
Rotor 6, specifically, being provided with the component 11 that verts for being connected to controller at the end of the first link 4, verting on component 11
Above-mentioned second power set 9 are fixed with, second power set 9 are connected to the first rotor 6.The above-mentioned component 11 that verts is used to control
Second power set 9 and the first rotor 6 vert switching in horizontal level and vertical position, i.e., as shown in figure 3, now the first rotation
The wing 6 is horizontal (Plane of rotation of the first rotor 6 is vertical with horizontal plane) by the control of component 11 of verting；As shown in figure 4, the
One rotor 6 is controlled in vertical position by the component 11 that verts (Plane of rotation of the first rotor 6 is parallel with horizontal plane).When the first rotation
When the wing 6 is horizontal, by adjusting the rotating speed of the first rotor 6, it can realize to compound unmanned plane VTOL and fly
The adjustment of line direction, when the first rotor 6 is in vertical position, its caused power is driven jointly with driving force caused by propeller 2
Move compound unmanned plane follow-on mission.
In the present embodiment, the above-mentioned component 11 that verts is driving structure of verting common in the art, for example, can be according to
The base that verts, linkage and the steering wheel of secondary connection or other can realize the structure that the first rotor 6 verts,
This is no longer repeated its structure.
In the present embodiment, above-mentioned second power set 9 can be motor, piston engine or turboshaft engine, and
Power is transferred to the first rotor 6 by above-mentioned motor, piston engine or turboshaft engine by gear and axle.
In the present embodiment, it is necessary to explanation, the first rotor of above-mentioned two 6 when driving rotation by the second power set 9,
The rotation directions of two the first rotors 6 on the contrary, and then the anti-twisted torque that can cancel out each other so that compound unmanned plane during flying is more flat
Surely, manipulate simpler.
The first link of above-mentioned two 4 is connected to above-mentioned V close to the small one end of the afterbody of fuselage 1 i.e. sectional area simultaneously
Tail 5, specifically, the above-mentioned tail of falling V 5 is set relative to the symmetrical plane of two the first links 4 in symmetrical structure, it is symmetrical by this
The setting of structure, it is possible to increase the flying quality of compound unmanned plane.
Fig. 1 and Fig. 2 are can refer to, the above-mentioned tail of falling V 5 includes two and tilts the empennage for being connected to two the first links 4 respectively
51, two empennages 51 are set in inverted V-shaped, are provided between two empennages 51 and are respectively connected with the first of controller and vert component 12
And second vert component 13, verted second and above-mentioned 3rd power set 10, the 3rd power set 10 are set on component 13
Drive connection has above-mentioned second rotor 7, and drives second rotor 7 to rotate.In the present embodiment, above-mentioned first component 12 that verts is used
Verted switching in horizontal level and vertical position in vert component 13, the 3rd power set 10 and the second rotor 7 of control second,
In order to realize the adjustment of the VTOL of compound unmanned plane or heading.Above-mentioned second vert component 13 be used for control the
Three power set 10 and the second rotor 7 or so vert, to realize the rotating in air of compound unmanned plane.
In the present embodiment, above-mentioned first vert component 12 and second vert component 13 structure and the structure of component 11 of verting
It is same or similar, it is driving structure of verting common in the art, therefore no longer its structure is repeated herein.
In the present embodiment, the axis of above-mentioned second rotor 7 is on the central plane of fuselage 1, and then passes through reasonable Arrangement
The position of second rotor 7, and coordinate the location arrangements of the first rotor 6, it can further improve the performance of compound unmanned plane.
Above-mentioned 3rd power set 10 are motor, and the second power set 9 can be motor, piston engine or whirlpool axle
Engine.
In the present embodiment, the pitch of above-mentioned first rotor 6 can be it is fixed, can also be by setting blade pitch control mechanism
Realize that pitch is adjustable, the blade pitch control mechanism is structure common in the art, is no longer described in detail.Above-mentioned second rotor 7
Pitch fix.
The utility model passes through said structure so that compound unmanned plane has fixed wing 3 and rotor concurrently, has taken into account fixation
The advantages of wing unmanned plane and rotor wing unmanned aerial vehicle, and do not interfere with each other between wing 3 and rotor, operation is simplified, can be provided multiple
The power of unmanned plane VTOL is closed, and can provides power during follow-on mission, and landing is convenient, cruising time is long, flying speed
It hurry up.
The utility model additionally provides a kind of control method of compound unmanned plane, specifically, it can be by the way that first be revolved
The rotor 7 of the wing 6 and second verts to vertical position, and the rotating speed by adjusting the first rotor 6 and the second rotor 7 realizes compound nothing
Man-machine VTOL or the adjustment of heading；
And revolved by the way that the first rotor 6 and the second rotor 7 are verted to horizontal level, and by propeller 2, first
The skyborne follow-on mission of compound unmanned plane is realized in the rotation of the rotor 7 of the wing 6 and second.
Wherein, when compound unmanned plane carries out VTOL, component 11 and first verted component 12 by verting first
First rotor 6 and the second rotor 7 are verted to vertical position, that is, the first rotor 6 and the second rotor 7 are verted to it
Plane of rotation is parallel with the X/Y plane shown in Fig. 1, then when needing vertical lift-off, closes the first power set 8, starts second
Power set 10 of power set 9 and the 3rd, and increase the rotating speed of the first rotor 6 and the second rotor 7, pass through the first rotor 6 and the
The lifting force of two rotors 7 goes up to the air compound unmanned plane.When needing landing, reduce the rotating speed of the first rotor 6 and the second rotor 7,
To cause compound UAV Landing.
When the change (such as prominent wind, air-flow) that external environment condition is run into lift-off or landing mission needs to adjust either certainly
When body heading needs adjustment, it can proceed as follows：
When compound unmanned plane needs the axle travel direction adjustment on the basis of X-axis (i.e. compound unmanned plane does pitch orientation adjustment)
When, on the premise of keeping two rotating speeds of the first rotor 6 constant, increase the rotating speed of the second rotor 7, now compound unmanned plane can be
Do nutation motion under the boosting function of second rotor 7, reduce the rotating speed of the second rotor 7, compound unmanned plane can then face upward motion.
When compound unmanned plane needs to adjust using Y-axis as datum axis travel direction, (i.e. compound unmanned plane is along its flight side
To doing left and right directions adjustment) when, now it is divided into two kinds of situations：
1st, when the pitch of the first rotor 6 is fixed, the rotating speed of one of them first rotor 6 and the second rotor 7 is kept not
Become, reduce the rotating speed of another the first rotor 6, compound unmanned plane can then vert to the direction of another the first rotor 6, such as subtract
The power reduction of the rotating speed of first rotor 6 in small left side, now the first rotor 6, the fuselage 1 of compound unmanned plane can then roll to the left
Turn；Reduce the rotating speed of first rotor 6 on right side, the fuselage 1 of compound unmanned plane can then vert to the right.
2nd, the first rotor 6 pitch can timing, now keep the rotating speed of two the first rotors 6 and the second rotor 7 not
Become, by the pitch for adjusting two the first rotors 6 so that it is poor that lift is produced between two the first rotors 6 so that compound unmanned plane
The direction of first rotor 6 is verted thereto.
When compound unmanned plane needs to adjust using Z axis as datum axis travel direction, (compound unmanned plane does aerial turn
To motion), now keep the rotating speed of two the first rotors 6 and the second rotor 7 constant, verted the driving of component 13 second by second
Rotor 7 verts to both sides to the left and right, and compound unmanned plane can then do aerial divertical motion.Specifically, when second component 13 that verts drives
Dynamic second rotor 7 vert to the left certain angle when, the left side lift lifting of propeller 2, compound unmanned plane does dextrorotation about the z axis
Turn in (in terms of from the direction that the afterbody of fuselage 1 points to head)；When second component 13 that verts drives the second rotor 7 to vert to the right certain angle
When spending, the right side lift lifting of propeller 2, compound unmanned plane does rotate counterclockwise about the z axis.
When above-mentioned compound unmanned plane of the present utility model carries out high-speed flight in the air, can now fly into fixed-wing
Row mode, that is, the cooperation by propeller 2, the first rotor 6, the second rotor 7 and wing 3, realize follow-on mission, specifically
, be by verting component 11 and first component 12 that verts verts the first rotor 6 and the second rotor 7 to horizontal level,
It is that X/Y plane shown in the Plane of rotation and Fig. 1 of the first rotor 6 and the second rotor 7 is perpendicular, now passes through the first power and fill
Put 8 and be used as active force, the second power set 9 and the 3rd power set 10 are used as auxiliary power so that the first rotor 6 and the second rotation
The power of the wing 7 is identical with the direction of advance of compound unmanned plane (forming fixed-wing offline mode), the first rotor 6 and the second rotor 7
Flight to compound unmanned plane provides auxiliary power so that compound unmanned plane during flying is more stable and quick, and propeller 2, the
The cooperation of one rotor 6, the second rotor 7 and wing 3, enable to the cruising time of compound unmanned plane is longer, flying speed more
It hurry up.When compound unmanned plane enters fixed-wing offline mode, its control is identical with common fixed-wing.
Obviously, above-described embodiment of the present utility model is used for the purpose of clearly illustrating the utility model example, and
It is not the restriction to embodiment of the present utility model.For those of ordinary skill in the field, in described above
On the basis of can also make other changes in different forms.There is no need and unable to give all embodiments
It is exhaustive.All made within spirit of the present utility model and principle all any modification, equivalent and improvement etc., should be included in
Within the protection domain of the utility model claims.
Claims (6)
1. a kind of compound unmanned plane, it is characterised in that including fuselage (1), be fixed on the propeller (2) of fuselage (1) afterbody, fix
Wing (3) in fuselage (1) upper end, symmetrically it is fixed on below wing (3) the first link (4) of both sides while is connected to two
Individual first link (4) one end and set in inverted V-shaped the tail of falling V (5), be connected to the first link (4) other end and can be
Horizontal level and vertical position vert switching the first rotor (6), be connected to the tail of falling V (5) center and can be in horizontal position
Put with vertical position vert switching and the left and right sides vert the second rotor (7), driving propeller (2) rotate the first power
The 3rd power that the second power set (9) and the second rotor of driving (7) that device (8), the first rotor of driving (6) rotate rotate
Device (10).
2. compound unmanned plane according to claim 1, it is characterised in that first link (4) is provided with group of verting
Part (11), the component that verts (11) are used to control first rotor (6) to vert switching in horizontal level and vertical position, institute
State the second power set (9) and be arranged on described vert between component (11) and first rotor (6).
3. compound unmanned plane according to claim 2, it is characterised in that the tail of falling V (5) is verted component provided with first
(12) verted component (13) with second, described first component (12) that verts is used to controlling described second to vert component (13) and second
Rotor (7) verts switching in horizontal level and vertical position, and described second component (13) that verts is used to control second rotor
(7) both sides are verted to the left and right, the 3rd power set (10) be arranged on described second vert component (13) and it is described second rotation
Between the wing (7).
4. compound unmanned plane according to claim 1, it is characterised in that when two first rotors (6) rotate, two
The rotation direction of first rotor (6) is opposite.
5. compound unmanned plane according to claim 1, it is characterised in that first link (4) is elongated rod shape structure,
And tapered into along fuselage (1) head to caudal directions, the sectional area of first link (4).
6. compound unmanned plane according to claim 5, it is characterised in that the tail of falling V (5) is relative to two first connections
The symmetrical plane of frame (4) is set in symmetrical structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720805365.0U CN206914635U (en) | 2017-07-05 | 2017-07-05 | A kind of compound unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720805365.0U CN206914635U (en) | 2017-07-05 | 2017-07-05 | A kind of compound unmanned plane |
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| Publication Number | Publication Date |
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| CN206914635U true CN206914635U (en) | 2018-01-23 |
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ID=61336032
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| Application Number | Title | Priority Date | Filing Date |
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| CN201720805365.0U Active CN206914635U (en) | 2017-07-05 | 2017-07-05 | A kind of compound unmanned plane |
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| CN (1) | CN206914635U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107336833A (en) * | 2017-07-05 | 2017-11-10 | 天津曙光天成科技有限公司 | A kind of compound unmanned plane and control method |
-
2017
- 2017-07-05 CN CN201720805365.0U patent/CN206914635U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107336833A (en) * | 2017-07-05 | 2017-11-10 | 天津曙光天成科技有限公司 | A kind of compound unmanned plane and control method |
| CN107336833B (en) * | 2017-07-05 | 2023-10-31 | 天津凤凰智能科技有限公司 | Composite unmanned aerial vehicle and control method |
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| TR01 | Transfer of patent right |
Effective date of registration: 20221013 Address after: Room 105, Building 9, Area B3 (formerly Area 2 of Ronghui Business Park), Enterprise Headquarters Base, Binhai-Zhongguancun Science and Technology Park, Economic and Technological Development Zone, Binhai New Area, Tianjin 300457 Patentee after: Tianjin Phoenix Intelligent Technology Co.,Ltd. Address before: Floor 1, block B, No.3, Tengfei Road, Junliang City, Dongli District, Tianjin Patentee before: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. |
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