CN205998126U - A kind of unmanned plane during flying system - Google Patents
A kind of unmanned plane during flying system Download PDFInfo
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- CN205998126U CN205998126U CN201620690690.2U CN201620690690U CN205998126U CN 205998126 U CN205998126 U CN 205998126U CN 201620690690 U CN201620690690 U CN 201620690690U CN 205998126 U CN205998126 U CN 205998126U
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Abstract
The utility model is related to and unmanned air vehicle technique field, more particularly to a kind of unmanned plane during flying system.A kind of unmanned plane during flying system, including：The variable rotor flight device in fixed-wing flight instruments and direction of rotation, and the control system of be connected respectively wing flight instruments and rotor flight device, the control system according to fly and the situation control fixed-wing flight instruments that rises and falls and the variable rotor flight device in direction of rotation operation and closing.The flight system combined by the variable rotor flight device in fixed-wing flight instruments and direction of rotation, have the advantage of fixed-wing and two kinds of flight instrumentses of rotor concurrently, so that rotor flight device can provide the power that unmanned plane rises and falls, the power of unmanned plane horizontal flight can be provided again, and landing convenience, cruising time length, flying speed are fast.
Description
Technical field
The utility model is related to unmanned air vehicle technique field, more particularly to a kind of unmanned plane during flying system.
Background technology
The common type of airplane in unmanned plane field is mainly fixed-wing and gyroplane at present.
Wherein fixed wing aircraft, produces the thrust or pulling force that advances mainly by power set, is produced by the fixing wing of fuselage
Raw lift.Its flying speed is fast, and voyage and cruise time are long, but landing distance, it is desirable to high-quality runway, have a strong impact on and
Hamper the development of fixed wing aircraft.
And gyroplane includes single rotor and many rotors, it is to provide lift by engine or motor-driven rotor, nobody
Machine draws high aerial.Its advantage is can be in less place VTOL, hovering, but its efficiency can not show a candle to fixed wing aircraft
Wing, power consumption is big, speed is slow, cruising time short be also exist shortcoming.
Existing technology also discloses the composite aircraft of a kind of fixed-wing and electronic many rotor compositions, has both fixed-wing and flies
Machine and the characteristic of gyroplane, but which is when fixed-wing offline mode is switched to, and although electronic many rotors stopped power supply, but
It is that shape and the construction of rotor has become the burden of unmanned plane during flying in flight airflow, resistance is on the one hand increased, on the other hand
Manipulation difficulty is increased, fails perfectly to be combined together the two.
Looking for always and can have fixed wing aircraft and gyroplane advantage concurrently and mutually not do for the technical staff of this aviation field
The aircraft that disturbs.
Utility model content
The purpose of this utility model is to propose unmanned plane during flying system, can by fixed-wing flight instruments and direction of rotation
The rotor flight device of change, solves prior art fixed-wing flight instruments and rotor flight device when rotor flight device has concurrently
Become the problem of resistance in normal flight, have the advantage of fixed-wing and two kinds of flight instrumentses of rotor concurrently, when landing convenience, continuation of the journey
Between long, flying speed fast.
For reaching this purpose, the utility model is employed the following technical solutions：
A kind of unmanned plane during flying system, including：The variable rotor flight device in fixed-wing flight instruments and direction of rotation, with
And the control system of be connected respectively wing flight instruments and rotor flight device, the control system is according to flying and rise and fall
The operation of the variable rotor flight device in situation control fixed-wing flight instruments and direction of rotation and closing.
One of preferred version as the technical program, the rotor flight device include to be arranged at wing and/or fuselage
On outrigger shaft, the verting at least one end for being rotatably coupled to the outrigger shaft component and be connected to the component that verts
The electronic rotor mechanism of outer end, the electronic rotor mechanism is horizontal by the angle for setting to join under the drive of the component that verts
Close taking off, land and flying for unmanned plane.
One of preferred version as the technical program, the outrigger shaft have two, and two outrigger shafts are longitudinally asymmetric
It is arranged on wing or fuselage, is connected on different outrigger shafts and the angle of inclination in longitudinally asymmetric electronic rotor mechanism and height
Degree difference is all consistent.
One of preferred version as the technical program, the two ends of the outrigger shaft are respectively connected with the component that verts, and are connected to
Former and later two components that vert of same outrigger shaft are horizontal by different angles with the flight for coordinating unmanned plane or situation of rising and falling.
One of preferred version as the technical program, the outrigger shaft have one, and the outrigger shaft is arranged in fuselage
On axis, the outrigger shaft and fuselage axis parallel or perpendicular with fuselage axis.
One of preferred version as the technical program, the two ends of the outrigger shaft are all connected with the component that verts, and two electronic
Rotor mechanism respectively according to unmanned plane rise and fall or flight condition horizontal by set difference in height and set angle；And work as
During the perpendicular setting in outrigger shaft and fuselage axis, two component angles of inclination of verting are consistent.
One of preferred version as the technical program, the electronic rotor mechanism with unmanned plane center of gravity as basic point, symmetrically
Distribution.
One of preferred version as the technical program, during unmanned plane horizontal flight, vert component and electronic rotor mechanism
Vertical connect, and the component that verts of front side verts downwards 90 °, and the component that verts of rear side verts 90 ° upwards, the front side electronic
The electronic rotor mechanism of rotor mechanism and rear side has the difference in height for setting.
One of preferred version as the technical program, the adjustable length of the component that verts and/or the electronic rotor
The chord of mechanism is adjustable, is verted component and the demand of electronic rotor mechanism rotation space with coordinating, and electronic rotor mechanism it
Between difference in height setting.
One of preferred version as the technical program, the fixed-wing flight instruments include fuselage, wing and power dress
Put, the power set installed in head or fuselage afterbody, the electronic rotor mechanism can be fix pitch can also be can
Size mixing away from.
Beneficial effect：The flight system combined by the variable rotor flight device in fixed-wing flight instruments and direction of rotation
System, has the advantage of fixed-wing and two kinds of flight instrumentses of rotor concurrently so that what rotor flight device can provide that unmanned plane rises and falls moves
Power, can provide the power of unmanned plane horizontal flight again, and landing convenience, cruising time length, flying speed are fast.
Description of the drawings
Fig. 1 is the structural representation one of the unmanned plane during flying system that the utility model embodiment 1 is provided；
Fig. 2 is the structural representation two of the unmanned plane during flying system that the utility model embodiment 1 is provided.
In figure：
1st, outrigger shaft；2nd, vert component；3rd, wing；4th, electronic rotor mechanism；5th, fuselage.
Specific embodiment
The technical solution of the utility model is further illustrated below in conjunction with the accompanying drawings and by specific embodiment.
Embodiment 1
A kind of unmanned plane during flying system, as shown in Figure 1-2, including：The variable rotation in fixed-wing flight instruments and direction of rotation
Wing flight instruments, and the control system of be connected respectively wing flight instruments and rotor flight device, the rotor flying dress
Put the outrigger shaft 1 on including being arranged at wing and/or fuselage, be rotatably coupled to the inclining of at least one end of the outrigger shaft 1
Turn component 2 and the electronic rotor mechanism 4 of 2 outer end of component of verting is connected to, the electronic rotor mechanism 4 is in the component that verts
Horizontal by the angle for setting to coordinate taking off, land and flying for unmanned plane under 2 drive.The component 2 that verts turn
Dynamic driving electric rotor mechanism 4 is converted between horizontal plane and the two directions of vertical plane, when the electronic rotor mechanism 4 is in water
Rotation with surface, realizes the fast lifting of unmanned plane；When the electronic rotor mechanism 4 is rotated in perpendicular, the electricity
Dynamic rotor mechanism 4 rotates driven air-flow and promotes unmanned plane to fly forward or backward；When electronic rotor mechanism 4 turns in inclined-plane
When dynamic, electronic rotor mechanism 4 rotates driven air-flow and promotes unmanned plane banking motion, for coordinating unmanned plane to turn, dive,
Climb or situation that air-flow is complicated；The electronic rotor mechanism 4 is with unmanned plane center of gravity as basic point, symmetrical, to ensure nobody
The accuracy of the stability and flight path of machine operation.The fixed-wing flight instruments includes fuselage 5, wing 3 and power set,
The power set are installed in head or fuselage afterbody.The control system flies according to the situation control fixed-wing for flying and rise and fall
Luggage puts the operation of the rotor flight device variable with direction of rotation and closing.
When being embodied as, the outrigger shaft 1 has two, and two outrigger shafts 1 are longitudinally asymmetric to be arranged on wing 3 or fuselage
On 5, it is connected on different outrigger shafts 1 and the angle of inclination in longitudinally asymmetric electronic rotor mechanism 4 and difference in height all keeps one
Cause.To keep the balance of unmanned plane during flying.The outer end for verting component 2 is connected with electronic rotor mechanism 4, the electronic rotation
The length direction of the rotary shaft of wing mechanism 4 and the component 2 that verts is perpendicular, the Plane of rotation of the rotor of the electronic rotor mechanism 4
Parallel with the component 2 that verts.
Each described outrigger shaft 1 only can be connected with electronic rotor mechanism 4 in one end, it is also possible to which two ends are respectively connected with group of verting
Part 2.In actual applications, it is also possible to flight according to unmanned plane, when rising and falling and dive, climbing, by control system so that even
Former and later two components 2 that vert of same outrigger shaft 1 are connected to horizontal by different angles to coordinate the requirement of unmanned plane.
When the two ends of each outrigger shaft 1 are respectively connected with the component 2 and in unmanned plane level flight condition of verting, vert
Component 2 is vertical with electronic rotor mechanism 4 to be connected, and the component 2 that verts of front side verts downwards 90 °, rear side vert component 2 upwards
90 ° are verted, the electronic rotor mechanism of the front side and the electronic rotor mechanism of rear side equidistantly can also have the height for setting
Degree is poor.
When the electronic rotor mechanism 4 rotate in the horizontal plane realize unmanned plane and take off vertically when, increase rotating speed or adjustment
Pitch causes unmanned plane to go up to the air, and can hover in the air or all around fly；When the electronic rotor mechanism 4 in the horizontal plane
When unmanned plane vertical landing is realized in rotation, reduce rotating speed or adjustment pitch causes unmanned plane slowly to land.
Embodiment 2
As different from Example 1, the outrigger shaft 1 has one, and the outrigger shaft 1 is arranged on fuselage axis, institute
Outrigger shaft 1 is stated with fuselage axis parallel or perpendicular with fuselage axis.
Only being connected with the two ends of vert component 2, or the outrigger shaft 1 and all connect in one end of the outrigger shaft 1
The component 2 that verts is connect, when the only one end of the outrigger shaft 1 is connected with and component 2 is verted, the component 2 that verts can be when unmanned plane rises and falls
With plane-parallel, with driving electric rotor mechanism 4 and plane-parallel；Can also incline described in unmanned plane horizontal flight
Turn lower turn of 2 clockwise direction of component to turn in 1 lower section of outrigger shaft or upwards in the top of outrigger shaft 1, driving electric rotor mechanism 4 exists
Rotation in perpendicular, is that unmanned plane horizontal direction provides horizontal thrust；Tilt component 2 can also dive, climb in unmanned plane
Or when running into side airflow, horizontal by the angle for setting, to strengthen the stationarity of unmanned plane during flying.
When the two ends of the outrigger shaft 1 are all connected with electronic rotor mechanism 4, outrigger shaft 1 both can be set along fuselage axis
Put, it is also possible to the perpendicular setting in fuselage axis, when outrigger shaft 1 along fuselage axis arrange and unmanned plane be in state of flight
When, the component 2 that verts verts, and component 2 is vertical with electronic rotor mechanism 4 to be connected, and the component 2 that verts of front side verts downwards
90 °, the component 2 that verts of rear side verts 90 ° upwards, and the electronic rotor mechanism of the front side and the electronic rotor mechanism of rear side have
The difference in height of setting；When unmanned plane is in and rises and falls state, the component 2 that verts is parallel with horizontal plane, two electronic rotors
Component 2 is in same level；Can also according to the flight of unmanned plane, rise and fall and dive, climb when, made by control system
Former and later two components 2 that vert of same outrigger shaft 1 must be connected to horizontal by different angles to coordinate the requirement of unmanned plane.
When the perpendicular setting in outrigger shaft 1 and fuselage axis, two 2 angles of inclination of component of verting are consistent, to protect
Hold the balance of unmanned plane during flying.Vert described in two the rising and falling or flight condition and horizontal plane according to unmanned plane respectively of component 2
In the angle for setting.
Embodiment 3
From unlike embodiment 1 and embodiment 2, the adjustable length of the component 2 that verts, with coordinate vert component 2 with
The demand of 4 rotation space of electronic rotor mechanism, and the setting of the difference in height between electronic rotor mechanism 4.
Or the chord of the electronic rotor mechanism 4 is adjustable, to coordinate the component 2 that verts to rotate sky with electronic rotor mechanism 4
Between demand.
When being embodied as, the quantity of the outrigger shaft 1 including but not limited to 1 in embodiment 1, and in embodiment 2
Two, or three even more many, the setting of outrigger shaft 1 and the position of installation can also be fuselage 5 and/or wing 3,
The mode of operation reference implementation example 1 and embodiment 2 of its vert component 2 and electronic rotor mechanism 4 or by embodiment 1 and embodiment 2
Combine,.
In sum, the flight system for being combined by the variable rotor flight device in fixed-wing flight instruments and direction of rotation
System, has the advantage of fixed-wing and two kinds of flight instrumentses of rotor concurrently so that what rotor flight device can provide that unmanned plane rises and falls moves
Power, can provide the power of unmanned plane horizontal flight again, and landing convenience, cruising time length, flying speed are fast.
Know-why of the present utility model is described above in association with specific embodiment.These descriptions are intended merely to explain this reality
With new principle, and the restriction that can not be construed to by any way to the utility model protection domain.Based on explanation herein,
Those skilled in the art associates other specific embodiments of the present utility model by need not paying performing creative labour,
These modes are fallen within protection domain of the present utility model.
Claims (10)
1. a kind of unmanned plane during flying system, it is characterised in that include：The variable rotor in fixed-wing flight instruments and direction of rotation flies
Luggage is put, and the control system of be connected respectively wing flight instruments and rotor flight device, and the control system is according to winged
The operation of the variable rotor flight device in row and the situation control fixed-wing flight instruments for rising and falling and direction of rotation and closing.
2. unmanned plane during flying system according to claim 1, it is characterised in that the rotor flight device includes to be arranged at
Outrigger shaft (1) on wing and/or fuselage, be rotatably coupled to the outrigger shaft (1) at least one end the component that verts (2)
And the electronic rotor mechanism (4) of component (2) outer end of verting described in being connected to, electronic rotor mechanism (4) are in the component that verts
(2) horizontal by the angle for setting to coordinate taking off, land and flying for unmanned plane under drive.
3. unmanned plane during flying system according to claim 2, it is characterised in that outrigger shaft (1) has two, two institutes
State that outrigger shaft (1) is longitudinally asymmetric to be arranged on wing (3) or fuselage (5), be connected to different outrigger shafts (1) upper and in longitudinally asymmetric
The angle of inclination of electronic rotor mechanism (4) and difference in height be all consistent.
4. unmanned plane during flying system according to claim 3, it is characterised in that the two ends of outrigger shaft (1) are all connected with
Have the component that verts (2), be connected to former and later two components that vert (2) of same outrigger shaft (1) horizontal by different angles with
Coordinate the flight of unmanned plane or situation of rising and falling.
5. unmanned plane during flying system according to claim 2, it is characterised in that outrigger shaft (1) has, described prolongs
Stretch axle (1) to be arranged on fuselage axis, outrigger shaft (1) and fuselage axis parallel or perpendicular with fuselage axis.
6. unmanned plane during flying system according to claim 5, it is characterised in that the two ends of outrigger shaft (1) are all connected with
Vert component (2), two electronic rotor mechanism (4) respectively according to unmanned plane rise and fall or flight condition horizontal by set
Difference in height and the angle for setting；And when the perpendicular setting in outrigger shaft (1) and fuselage axis, two components that vert (2) incline
Angle is consistent.
7. the unmanned plane during flying system according to any one of claim 2-6, it is characterised in that the electronic rotor mechanism
(4) with unmanned plane center of gravity as basic point, symmetrical.
8. unmanned plane during flying system according to claim 3, it is characterised in that during unmanned plane horizontal flight, vert component
(2) vertical with electronic rotor mechanism (4) be connected, and the component that verts (2) of front side verts downwards 90 °, the component that verts (2) of rear side
90 ° are verted upwards, and the electronic rotor mechanism (4) of the front side and the electronic rotor mechanism (4) of rear side have the difference in height for setting.
9. the unmanned plane during flying system according to any one of claim 2-6, it is characterised in that the component that verts (2)
The chord of adjustable length and/or the electronic rotor mechanism (4) is adjustable, to coordinate vert component (2) and electronic rotor mechanism (4)
The setting of the difference in height between the demand of rotation space, and electronic rotor mechanism (4).
10. unmanned plane during flying system according to claim 2, it is characterised in that the fixed-wing flight instruments includes machine
Body (5), wing (3) and power set, the power set are installed in head or fuselage afterbody, electronic rotor mechanism (4)
Can be that to fix pitch can also be adjustable pitch.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620690690.2U CN205998126U (en) | 2016-06-30 | 2016-06-30 | A kind of unmanned plane during flying system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620690690.2U CN205998126U (en) | 2016-06-30 | 2016-06-30 | A kind of unmanned plane during flying system |
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| Publication Number | Publication Date |
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| CN205998126U true CN205998126U (en) | 2017-03-08 |
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| CN201620690690.2U Active CN205998126U (en) | 2016-06-30 | 2016-06-30 | A kind of unmanned plane during flying system |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043696A (en) * | 2016-06-30 | 2016-10-26 | 天津曙光天成科技有限公司 | Flying system for unmanned aerial vehicle |
| CN107972859A (en) * | 2017-12-11 | 2018-05-01 | 王美航 | A kind of two-way aircraft |
| WO2019109215A1 (en) * | 2017-12-04 | 2019-06-13 | 深圳市大疆创新科技有限公司 | Power device, unmanned aerial vehicle, and flight control method |
| CN111152919A (en) * | 2020-01-08 | 2020-05-15 | 北京建筑大学 | Control method of unmanned aerial vehicle capable of taking off and landing vertically |
| WO2022229201A1 (en) * | 2021-04-26 | 2022-11-03 | Wingcopter GmbH | Vertical takeoff aircraft |
-
2016
- 2016-06-30 CN CN201620690690.2U patent/CN205998126U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043696A (en) * | 2016-06-30 | 2016-10-26 | 天津曙光天成科技有限公司 | Flying system for unmanned aerial vehicle |
| WO2019109215A1 (en) * | 2017-12-04 | 2019-06-13 | 深圳市大疆创新科技有限公司 | Power device, unmanned aerial vehicle, and flight control method |
| CN107972859A (en) * | 2017-12-11 | 2018-05-01 | 王美航 | A kind of two-way aircraft |
| CN111152919A (en) * | 2020-01-08 | 2020-05-15 | 北京建筑大学 | Control method of unmanned aerial vehicle capable of taking off and landing vertically |
| CN111152919B (en) * | 2020-01-08 | 2021-06-15 | 北京建筑大学 | Control method of unmanned aerial vehicle capable of taking off and landing vertically |
| WO2022229201A1 (en) * | 2021-04-26 | 2022-11-03 | Wingcopter GmbH | Vertical takeoff aircraft |
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20221012 Address after: 300457 No. 105, Building 9, Zone B3 (formerly Zone 2 of Ronghui Business Park), Binhai Zhongguancun Science and Technology Park, Tianjin Economic and Technological Development Zone, Binhai New Area, Tianjin 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. |