CN207644636U - Abnormity verts multi-rotor aerocraft - Google Patents
Abnormity verts multi-rotor aerocraft Download PDFInfo
- Publication number
- CN207644636U CN207644636U CN201721722064.8U CN201721722064U CN207644636U CN 207644636 U CN207644636 U CN 207644636U CN 201721722064 U CN201721722064 U CN 201721722064U CN 207644636 U CN207644636 U CN 207644636U
- Authority
- CN
- China
- Prior art keywords
- rotor
- abnormity
- verts
- rotor aerocraft
- horn
- 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.)
- Expired - Fee Related
Links
Landscapes
- Toys (AREA)
Abstract
The utility model discloses a kind of abnormity and verts multi-rotor aerocraft, including undercarriage, the horn of four radial settings and the rotor assemblies that are arranged on horn.Hollow central plate is provided in aircraft center.Central plate inner circular space diametrical position is provided with a carbon fiber central tube, and central tube centre position is fixedly connected with reversed coaxial double-rotary wing component.There are many offline mode configurations for the utility model flying instrument.When disabling Central Power System, aircraft is no different with conventional quadrotor, and mobility performance is also substantially close；When enabling Central Power System, aircraft can be exported by adjusting each rotor power and rotor work inclination angle so that aircraft body keeps horizontal and realizes preceding fly simultaneously（Reach similar uniaxial holder effect）, or fly posture before reaching best by the coordination control of two dynamical systems, realize high-speed horizontal flight.
Description
Technical field
The utility model belongs to vehicle technology field, verts multi-rotor aerocraft more particularly to a kind of abnormity.
Background technology
The advantages of traditional multi-rotor aerocraft is can to carry out more accurately steadily hovering, convenient for carrying out shooting, launching
Article etc. is higher to positioning accuracy request, and the slower flight work that even hovering requires for a long time is proposed to aircraft；But its phase
It is also fairly obvious compared with the defect of Fixed Wing AirVehicle.First, more rotors due to dynamic structure characteristic determine, capacity usage ratio compared with
Low, hovering time and cruising ability critical constraints can not often carry out the aerial work of long range, and that time-consuming is aerial
Operation then needs repeatedly to interrupt, and landing replaces battery and takes off again；Second, it is horizontal high speed can be carried out different from Fixed Wing AirVehicle
Motor-driven, the max level speed of multi-rotor aerocraft is often below 100km/h（Aim at passing through except machine for racing design）, this is right
It is greatly to limit for the multi-rotor aerocraft partly taken photo by plane with transport applications, and in terms of military scouting, flying speed
It is limited to mean not only to be difficult to achieve the purpose that rapid reconnaissance, but also be also easier to exposure and be found.Third, multi-rotor aerocraft
Be not belonging to self-stabilization structure as helicopter, it is in the horizontal direction it is motor-driven fully rely on verting for body, this makes part
There is the aerial work task of stability requirement not completed by aircraft itself directly workbench, such as takes photo by plane and flown with more rotors
Row device generally requires to install additional multi-spindle machining holder below its body to carry capture apparatus, ensures the motor-driven of aircraft when flight
Action and body shake etc. do not interfere with finding a view for capture apparatus.
Invention content
The utility model aim is the defect for existing multi-rotor aerocraft, and providing one kind, can to improve tradition more
The horizontal maneuverability of rotor craft improves voyage limitation within the identical hang time；Make multi-rotor aerocraft in horizontal attitude
Under have before the abnormity of winged ability vert multi-rotor aerocraft.
The utility model to achieve the above object, adopts the following technical scheme that：
Abnormity verts multi-rotor aerocraft, including undercarriage, more radial settings horn and be arranged in the horn
On rotor assemblies, it is characterised in that：The aircraft center is provided with vector propulsion device.
It is further characterized by：The vector propulsion device is the reversed coaxial double-rotary wing component that can be pivoted.
Further：The aircraft center is provided with hollow central plate, and the horn is connected to the center
Plate outer ledge；The reversed coaxial double-rotary wing component is arranged in central plate inner circular space.
Preferably：Central plate inner circular space diametrical position is provided with a central tube, the central tube both ends
It is connected on two steering engines, the steering engine is fixedly connected on the central plate；The reversed coaxial double-rotary wing component is solid
Surely it is connected to the central tube centre position.
The central tube is carbon fiber pipe.
The horn quantity is four, and a set of rotor assemblies are fixedly connected on every horn.
The rotor assemblies include motor and the rotor by motor driving rotation.
The rotor assemblies axle center is mutually parallel.
It is provided with power battery and flight controller on the central plate.
The power battery and flight controller are separately fixed at the central plate both sides.
The beneficial effects of the utility model：
There are many offline mode configurations for the utility model flying instrument.When disabling Central Power System, aircraft with often
Rule quadrotor is no different, and mobility performance is also substantially close；When enabling Central Power System, aircraft can pass through tune
Whole each rotor power output and rotor work inclination angle so that aircraft body keeps horizontal and realizes preceding fly simultaneously（Reach class
Like uniaxial holder effect）, or fly posture before reaching best by the coordination control of two dynamical systems, it realizes that high speed is horizontal and flies
Row.
Description of the drawings
Fig. 1 is the utility model structure diagram.
Specific implementation mode
A kind of abnormity verts multi-rotor aerocraft as shown in Figure 1, includes 2 and of horn of 1, four radial setting of undercarriage
Rotor assemblies on horn 2 are set, and rotor assemblies include motor 3 and the rotor 4 by the driving rotation of motor 3.In aircraft
Heart position is provided with hollow central plate 5.Horn 2 is connected to 5 outer ledge of central plate.5 inner circular space diameter of central plate
Position is provided with a carbon fiber central tube 6, and 6 both ends of central tube are connected to two steering engines（It is not shown in figure）On, steering engine
It is fixedly connected on central plate 6.6 centre position of central tube is fixedly connected with reversed coaxial double-rotary wing component 7.Pass through servos control
Reversed 7 working face inclination angle of coaxial double-rotary wing component, realizes that vector promotes.It is provided with power battery on central plate 6 and flight controls
Device（It is not shown in figure）.Power battery and flight controller are separately fixed at 6 both sides of central plate.
Its essence is by one, the center border circular areas of common four-axle aircraft for the utility model（Its radius is slightly larger than rotor
Structure radius）It empties and places a pair of coaxial double-rotary wing component reversely rotated wherein（It rotates backward to cancel out each other certainly
The torsional moment of body）.The load such as power battery, flight controller will be fixed to the both sides of central plate, and four axis of aircraft
Still remain unchanged.
There are many offline mode configurations for flying instrument.When disabling Central Power System, aircraft flies with conventional quadrotor
Row device is no different, and mobility performance is also substantially close；When enabling Central Power System, aircraft can be dynamic by adjusting each rotor
Power exports and rotor work inclination angle so that aircraft body keeps horizontal and realizes preceding fly simultaneously（Reach similar uniaxial holder
Effect）, or fly posture before reaching best by the coordination control of two dynamical systems, realize high-speed horizontal flight.When reversed total
When axis DCB Specimen component operation face level, there is top load performance.It is even erected when reversed coaxial double-rotary wing component operation face tilts
Directly there is high maneuverability energy.Under high maneuver model, other conventional more rotors of the more same dynamical system of horizontal flight speed
Aircraft is significantly increased.
Basic principles, main features, and advantages of the present invention has been shown and described above.One's own profession
The technical staff of industry is it should be appreciated that the present utility model is not limited to the above embodiments, described in above embodiments and description
Only the principles of the present invention, on the premise of not departing from the spirit and scope of the utility model the utility model also have respectively
Kind changes and improvements, these changes and improvements are both fallen in claimed the scope of the utility model.The requires of the utility model
Protection domain defined by appended claims and its equivalent.
Claims (9)
- The multi-rotor aerocraft 1. abnormity verts, including undercarriage, more radial settings horn and be arranged on the horn Rotor assemblies, it is characterised in that：The aircraft center is provided with vector propulsion device；The vector propulsion device is The reversed coaxial double-rotary wing component that can be pivoted.
- The multi-rotor aerocraft 2. abnormity according to claim 1 verts, it is characterised in that：The aircraft centre bit installs It is equipped with hollow central plate, the horn is connected to the central plate outer ledge；The reversed coaxial double-rotary wing component setting In central plate inner circular space.
- The multi-rotor aerocraft 3. abnormity according to claim 2 verts, it is characterised in that：The central plate inner circular is empty Between diametrical position be provided with a central tube, the central tube both ends are connected on two steering engines, and the steering engine, which is fixed, to be connected It is connected on the central plate；The reversed coaxial double-rotary wing component is fixedly connected on the central tube centre position.
- The multi-rotor aerocraft 4. abnormity according to claim 3 verts, it is characterised in that：The central tube is carbon fiber Pipe.
- 5. being verted multi-rotor aerocraft according to claim 1-4 any one of them abnormity, it is characterised in that：The horn quantity It is four, a set of rotor assemblies is fixedly connected on every horn.
- 6. being verted multi-rotor aerocraft according to claim 1-4 any one of them abnormity, it is characterised in that：The rotor assemblies The rotor rotated including motor and by motor driving.
- 7. being verted multi-rotor aerocraft according to claim 1-4 any one of them abnormity, it is characterised in that：The rotor assemblies Axle center is mutually parallel.
- The multi-rotor aerocraft 8. abnormity according to claim 2 or 3 verts, it is characterised in that：It is arranged on the central plate Dynamic battery and flight controller.
- The multi-rotor aerocraft 9. abnormity according to claim 8 verts, it is characterised in that：The power battery and flight are controlled Device processed is separately fixed at the central plate both sides.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721722064.8U CN207644636U (en) | 2017-12-12 | 2017-12-12 | Abnormity verts multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721722064.8U CN207644636U (en) | 2017-12-12 | 2017-12-12 | Abnormity verts multi-rotor aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207644636U true CN207644636U (en) | 2018-07-24 |
Family
ID=62880329
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721722064.8U Expired - Fee Related CN207644636U (en) | 2017-12-12 | 2017-12-12 | Abnormity verts multi-rotor aerocraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207644636U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110329497A (en) * | 2019-06-28 | 2019-10-15 | 西安交通大学 | The multi-rotor unmanned aerial vehicle and its control method of a kind of paddle face variable-angle |
| WO2024098486A1 (en) * | 2022-11-11 | 2024-05-16 | 北京航天长征飞行器研究所 | Flying hoverboard main structure |
-
2017
- 2017-12-12 CN CN201721722064.8U patent/CN207644636U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110329497A (en) * | 2019-06-28 | 2019-10-15 | 西安交通大学 | The multi-rotor unmanned aerial vehicle and its control method of a kind of paddle face variable-angle |
| WO2024098486A1 (en) * | 2022-11-11 | 2024-05-16 | 北京航天长征飞行器研究所 | Flying hoverboard main structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP6158459B2 (en) | Multicopter | |
| CN107042884A (en) | A kind of tilting rotor wing unmanned aerial vehicle | |
| CN105775117B (en) | A kind of helicopter of VTOL horizontal flight and its application | |
| CN204822069U (en) | Four rotor unmanned aerial vehicle configurations of duct | |
| CN205327411U (en) | Composite wing aircraft | |
| RU2456209C1 (en) | Converter plane | |
| CN106218887A (en) | A kind of vertically taking off and landing flyer of distributed-power device layout | |
| CN108639328A (en) | A kind of New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone | |
| CN109606674A (en) | Tail sitting posture vertical take-off and landing drone and its control system and control method | |
| CN109263932A (en) | A kind of multi-rotor aerocraft being vertically moved up or down | |
| CN207644636U (en) | Abnormity verts multi-rotor aerocraft | |
| CN106477033A (en) | High speed hybrid multi-rotor aerocraft | |
| CN107042883B (en) | A kind of double duct unmanned aerial vehicles that secondary transmission engine lap siding can generate electricity with loading | |
| CN105398565A (en) | Rear wing modification mechanism for flying wing aircraft | |
| CN105711830B (en) | A kind of two axial vector balancing flap tiltrotor aircrafts | |
| CN103950537A (en) | Control method and device of variable pitch aircraft | |
| CN105151296A (en) | Multi-axis manned aircraft | |
| CN107140208A (en) | STOL top load multiaxis fans wing unmanned plane | |
| CN108438215A (en) | It is a kind of to have the vector four-axle aircraft for keeping organism level ability | |
| CN107097949A (en) | A kind of VTOL fixed-wing unmanned plane | |
| CN206552261U (en) | A kind of tilting rotor wing unmanned aerial vehicle | |
| CN103863561A (en) | Vertical take-off and landing unmanned aerial vehicle with foldable aerofoils | |
| CN103693195B (en) | A kind of minute vehicle | |
| CN206719540U (en) | Tilting rotor type VUAV based on Flying-wing | |
| CN205931250U (en) | Four rotor crafts of variable pitch based on single driving system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180724 Termination date: 20201212 |