CN106428524B - A kind of multi-rotor aerocraft with the free wing - Google Patents
A kind of multi-rotor aerocraft with the free wing Download PDFInfo
- Publication number
- CN106428524B CN106428524B CN201611062653.8A CN201611062653A CN106428524B CN 106428524 B CN106428524 B CN 106428524B CN 201611062653 A CN201611062653 A CN 201611062653A CN 106428524 B CN106428524 B CN 106428524B
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- wing
- rotor
- free
- free wing
- bracket institution
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The present invention relates to a kind of multi-rotor aerocrafts with the free wing, including rotor, rotor bracket institution, aircraft pedestal, drive wing bracket institution and driving propeller, aircraft pedestal to be equipped with free wing mechanism；Rotor bracket institution, drive wing bracket institution and free wing mechanism are fixedly connected with aircraft pedestal respectively；Rotor is set on rotor bracket institution；Driving propeller is set on drive wing bracket institution.With such a structure, in vertical movement, higher stability and lesser resistance are able to maintain.Meanwhile in flight course, lifting power is provided using the free wing, improves the efficiency that aircraft flies in the horizontal direction.
Description
Technical field
The present invention relates to aircraft field more particularly to a kind of multi-rotor aerocrafts with the free wing.
Background technique
In existing flying object, multi-rotor aerocraft has VTOL and hovering ability, while having very extensive
Application field have that structure is simple, maintenance is easy, blade lethality is small, operation compared with traditional single-rotor helicopter
The feature of safety.The effect to become more and more important is not only played in military field, also photography in the sky, agricultural plant protection, power-line patrolling,
Multiple civil fields such as traffic tour and Disaster Assessment are widely used.
But itself there is also certain defects, although common more gyroplanes efficiency in vertical movement is higher, in water
When flat movement, efficiency is lower.
Summary of the invention
The technical problem to be solved by the present invention is to design a kind of multi-rotor aerocraft of free wing, existing flight efficiency is solved
Low technical problem.
In order to solve the above technical problems, a kind of multi-rotor aerocraft with the free wing of the invention, including free wing machine
Structure, rotor, rotor bracket institution and aircraft pedestal, rotor bracket institution, free wing mechanism are fixed with aircraft pedestal respectively
Connection；Rotor is set on rotor bracket institution；Motor is fixed on rotor bracket institution；Motor is fixedly linked with rotor.
Further, pedestal is additionally provided with drive wing bracket institution and driving propeller；It is fixedly connected with aircraft pedestal；It drives
Dynamic propeller is set on drive wing bracket institution；Motor is fixed on drive wing bracket institution；Motor and driving propeller are solid
Fixed connection.Can be as needed, it voluntarily chooses whether addition drive wing bracket institution and drives propeller.
It further, include free wing wing on free wing mechanism, free cautiously bar and aseismatic mechanism；Freely cautiously in bar
Portion is equipped with electromagnetic damping mechanism；Electromagnetic damping mechanism is located in aircraft pedestal；Aseismatic mechanism includes stator terminal and rotor-end；It is anti-
The stator terminal for shaking mechanism is fixedly connected with freely thriving bar；The rotor-end of aseismatic mechanism is fixedly connected with aircraft pedestal；Freely
Thriving bar is pierced by from aircraft pedestal both ends horizontal；Free wing wing is fixedly linked with freely thriving bar.The free wing machine of aircraft
The upper counterangle, inverted diherdral and the sweepforward angle of the wing, angle of sweep can be all adjusted according to the design needs.
Further, aseismatic mechanism is electromagnetic damping mechanism or servo motor mechanism.Electromagnetic damping mechanism or servo
Motor mechanism is fixed on freely cautiously among bar, the stator of belt coil with freely cautiously bar is fixedly connected, the rotor in outside and
Aircraft pedestal is fixedly connected, and for stablizing the free wing, slows down its angles shifts rate.The free wing of two sides provides upward liter
Power, and the size of lift is in direct ratio related to the velocity magnitude that aircraft advances.
Further, free wing wing is equipped with heavy hammer mechanism；Heavy hammer mechanism is located at free wing inboard.In the free wing
The heavy hammer structure that inboard adds, weight can turn to suitable angle according to axis, change machine by changing the center of gravity of wing
The angle of attack of the wing obtains required lift.
Further, free wing mechanism and aircraft pedestal direction of advance are in 90 °.
Further, free wing wing is equipped with rudder face；Rudder face is located at the external aileron position of free wing wing.
Further, number at least one of rotor bracket institution.Can be as needed, voluntarily selection adjusts rotor timbering machine
The number of structure.
Further, drive wing bracket institution quantity is 1.Can be as needed, voluntarily selection adjusts drive wing timbering machine
The number of structure.
Further, aircraft pedestal is equipped with empennage；Empennage includes horizontal tail and vertical fin；Horizontal tail is vertical with vertical fin.It can root
According to needs, choose whether to add.
Beneficial effects of the present invention: with such a structure, vertical movement when, be able to maintain higher stability with
And lesser resistance.Meanwhile in flight course, lifting power is provided using the free wing, improves aircraft in the horizontal direction
The efficiency of upper flight.
Detailed description of the invention
A specific embodiment of the invention is furtherd elucidate with reference to the accompanying drawing.
Fig. 1 is the structural schematic diagram of the multi-rotor aerocraft with the free wing of the invention；
Fig. 2 is that the first of the invention has the structural schematic diagram of three rotor crafts of the free wing；
Fig. 3 is the structural schematic diagram of of the invention second three rotor crafts with the free wing；
Fig. 4 is the structural schematic diagram of the third three rotor craft with the free wing of the invention；
Fig. 5 is that the first of the invention has the structural schematic diagram of the quadrotor of the free wing；
Fig. 6 is the structural schematic diagram of of the invention second quadrotor with the free wing；
Fig. 7 is the structural schematic diagram of the third quadrotor with the free wing of the invention；
Fig. 8 is the structural schematic diagram of of the invention the 4th kind quadrotor with the free wing；
Fig. 9 is the structural schematic diagram of the six rotorcraft with the free wing of the invention；
Figure 10 is the structural schematic diagram of the eight-rotary wing aircraft with the free wing of the invention；
Figure 11 is the structural schematic diagram of the free wing mechanism of multi-rotor aerocraft with the free wing of the invention；
Figure 12 is the enlarged diagram in Figure 11 at A；
Figure 13 is the structural schematic diagram of the multi-rotor aerocraft aseismatic mechanism with the free wing of the invention；
Figure 14 is the enlarged diagram in Figure 13 at 2.
Drawing reference numeral explanation:
1, rotor, 2, rotor bracket institution, 3, aircraft pedestal, 4, drive wing bracket institution, 5, driving propeller, 6, from
By wing wing, 7, free thriving bar, 8, heavy hammer mechanism, 9, aileron, 10, vertical fin；11, horizontal tail, 12, aseismatic mechanism.
Specific embodiment
Embodiment 1:
In conjunction with Fig. 1,2 and Figure 11 to Figure 14, the present invention is that the first has three rotor crafts of the free wing, including freedom
Wing mechanism, rotor 1, rotor bracket institution 2, aircraft pedestal 3, drive wing bracket institution 4 and driving propeller 5, rotor bracket
Mechanism 2, drive wing bracket institution 4 and free wing mechanism are fixedly connected with aircraft pedestal 3 respectively；Rotor 1 is set to rotor branch
On frame mechanism 2；Driving propeller 5 is set on drive wing bracket institution 4；Motor is fixed on rotor bracket institution 2；Motor with
Rotor 1 is fixedly linked；Motor is fixed on drive wing bracket institution 4；Motor is fixedly connected with driving propeller 5.
The present embodiment is preferred, includes free wing wing 6 on free wing mechanism, freely thriving bar 7 and aseismatic mechanism 12；Freely
Electromagnetic damping mechanism is equipped in the middle part of thriving bar 7；Electromagnetic damping mechanism is located in aircraft pedestal 3；Aseismatic mechanism 12 includes stator
End and rotor-end；The stator terminal of electromagnetic damping mechanism is fixedly connected with freely thriving bar 7；The rotor-end of electromagnetic damping mechanism and fly
Row device pedestal 3 is fixedly connected；Freely cautiously bar 7 is pierced by from 3 both ends horizontal of aircraft pedestal；Free wing wing 6 and freedom are cautiously
Bar 7 is connected.
The present embodiment is preferred, and aseismatic mechanism 12 is electromagnetic damping mechanism or servo motor mechanism.Electromagnetic damping mechanism or
Person's servo motor mechanism is fixed on freely among cautiously bar 7, and the stator of belt coil is fixedly connected with freely thriving bar 7, outside
Rotor be fixedly connected with aircraft pedestal 3, for stablizing the free wing, slow down its angles shifts rate.The free wing of two sides mentions
For upward lift, and the size of lift is in direct ratio related to the velocity magnitude that aircraft advances.
The present embodiment is preferred, and free wing mechanism and 3 direction of advance of aircraft pedestal are in 90 °.
The present embodiment is preferred, and the number of the free wing is 1.
The present embodiment is preferred, and the number of rotor bracket institution 2 is 3.
The present embodiment is preferred, and 4 quantity of drive wing bracket institution is 1.
Embodiment 2:
In conjunction with Fig. 3 and Figure 11 to Figure 14, the present invention is a kind of three rotor crafts with the free wing, including free wing machine
Structure, rotor 1, rotor bracket institution 2, aircraft pedestal 3, drive wing bracket institution 4 and driving propeller 5, rotor bracket institution
2, drive wing bracket institution 4 and free wing mechanism are fixedly connected with aircraft pedestal 3 respectively；Rotor 1 is set to rotor timbering machine
On structure 2；Driving propeller 5 is set on drive wing bracket institution 4；Motor is fixed on rotor bracket institution 2；Motor and rotor
1 is fixedly linked；Motor is fixed on drive wing bracket institution 4；Motor is fixedly connected with driving propeller 5.
The present embodiment is preferred, includes free wing wing 6 on free wing mechanism, freely thriving bar 7 and aseismatic mechanism 12；Freely
Electromagnetic damping mechanism is equipped in the middle part of thriving bar 7；Electromagnetic damping mechanism is located in aircraft pedestal 3；Aseismatic mechanism 12 includes stator
End and rotor-end；The stator terminal of electromagnetic damping mechanism is fixedly connected with freely thriving bar 7；The rotor-end of electromagnetic damping mechanism and fly
Row device pedestal 3 is fixedly connected；Freely cautiously bar 7 is pierced by from 3 both ends horizontal of aircraft pedestal；Free wing wing 6 and freedom are cautiously
Bar 7 is connected.
The present embodiment is preferred, and free wing wing 6 is equipped with heavy hammer mechanism 8；Heavy hammer mechanism 8 is located at free 6 inside of wing wing.
The heavy hammer structure added on the inside of free wing wing 6, weight can turn to suitable angle according to axis, by the center of gravity for changing wing
Change the angle of attack of wing, obtains required lift.
The present embodiment is preferred, and free wing mechanism and 3 direction of advance of aircraft pedestal are in 90 °.
The present embodiment is preferred, and the number of the free wing is 1.
The present embodiment is preferred, and free wing wing 6 is equipped with rudder face；Rudder face is located at 9 position of external aileron of free wing wing 6.
The present embodiment is preferred, and the number of rotor bracket institution 2 is 3.
The present embodiment is preferred, and 4 quantity of drive wing bracket institution is 1.
Embodiment 3:
In conjunction with Fig. 4 and Figure 11 to Figure 14, the present invention is second of three rotor craft with the free wing, including the free wing
Mechanism, rotor 1, rotor bracket institution 2, aircraft pedestal 3, drive wing bracket institution 4 and driving propeller 5, rotor timbering machine
Structure 2, drive wing bracket institution 4 and free wing mechanism are fixedly connected with aircraft pedestal 3 respectively；Rotor 1 is set to rotor bracket
In mechanism 2；Driving propeller 5 is set on drive wing bracket institution 4；Motor is fixed on rotor bracket institution 2；Motor and rotation
The wing 1 is fixedly linked；Motor is fixed on drive wing bracket institution 4；Motor is fixedly connected with driving propeller 5.
The present embodiment is preferred, includes free wing wing 6 on free wing mechanism, freely thriving bar 7 and aseismatic mechanism 12；Freely
Electromagnetic damping mechanism is equipped in the middle part of thriving bar 7；Electromagnetic damping mechanism is located in aircraft pedestal 3；Aseismatic mechanism 12 includes stator
End and rotor-end；The stator terminal of electromagnetic damping mechanism is fixedly connected with freely thriving bar 7；The rotor-end of electromagnetic damping mechanism and fly
Row device pedestal 3 is fixedly connected；Freely cautiously bar 7 is pierced by from 3 both ends horizontal of aircraft pedestal；Free wing wing 6 and freedom are cautiously
Bar 7 is connected.
The present embodiment is preferred, and aseismatic mechanism 12 is electromagnetic damping mechanism or servo motor mechanism.Electromagnetic damping mechanism or
Person's servo motor mechanism is fixed on freely among cautiously bar 7, and the stator of belt coil is fixedly connected with freely thriving bar 7, outside
Rotor be fixedly connected with aircraft pedestal 3, for stablizing the free wing, slow down its angles shifts rate.The free wing of two sides mentions
For upward lift, and the size of lift is in direct ratio related to the velocity magnitude that aircraft advances.
The present embodiment is preferred, and free wing wing 6 is equipped with heavy hammer mechanism 8；Heavy hammer mechanism 8 is located at free 6 inside of wing wing.
The heavy hammer structure added on the inside of free wing wing 6, weight can turn to suitable angle according to axis, by the center of gravity for changing wing
Change the angle of attack of wing, obtains required lift.
The present embodiment is preferred, and free wing mechanism and 3 direction of advance of aircraft pedestal are in 90 °.
The present embodiment is preferred, and the number of the free wing is 1.
The present embodiment is preferred, and free wing wing 6 is equipped with rudder face；Rudder face is located at 9 position of external aileron of free wing wing 6.
The present embodiment is preferred, and the number of rotor bracket institution 2 is 3.
The present embodiment is preferred, and 4 quantity of drive wing bracket institution is 1.
The present embodiment is preferred, and aircraft pedestal 3 is equipped with empennage；Empennage includes horizontal tail 11 and vertical fin 10；Horizontal tail 11 and hang down
Tail 10 is vertical.
Embodiment 4:
In conjunction with Fig. 5 and Figure 11 to Figure 14, the present invention is that the first has the quadrotor of the free wing, including the free wing
Mechanism, rotor 1, rotor bracket institution 2 and aircraft pedestal 3, rotor bracket institution 2, free wing mechanism respectively with aircraft base
Seat 3 is fixedly connected；Rotor 1 is set on rotor bracket institution 2；Motor is fixed on rotor bracket institution 2；Motor and rotor 1
It is fixedly linked.
The present embodiment is preferred, includes free wing wing 6 on free wing mechanism, freely thriving bar 7 and aseismatic mechanism 12；Freely
Electromagnetic damping mechanism is equipped in the middle part of thriving bar 7；Electromagnetic damping mechanism is located in aircraft pedestal 3；Aseismatic mechanism 12 includes stator
End and rotor-end；The stator terminal of electromagnetic damping mechanism is fixedly connected with freely thriving bar 7；The rotor-end of electromagnetic damping mechanism and fly
Row device pedestal 3 is fixedly connected；Freely cautiously bar 7 is pierced by from 3 both ends horizontal of aircraft pedestal；Free wing wing 6 and freedom are cautiously
Bar 7 is connected.
The present embodiment is preferred, and aseismatic mechanism 12 is electromagnetic damping mechanism or servo motor mechanism.Electromagnetic damping mechanism or
Person's servo motor mechanism is fixed on freely among cautiously bar 7, and the stator of belt coil is fixedly connected with freely thriving bar 7, outside
Rotor be fixedly connected with aircraft pedestal 3, for stablizing the free wing, slow down its angles shifts rate.The free wing of two sides mentions
For upward lift, and the size of lift is in direct ratio related to the velocity magnitude that aircraft advances.It is a kind of with the free wing
Multi-rotor aerocraft, including free wing mechanism, rotor 1, rotor bracket institution 2 and aircraft pedestal 3, rotor bracket institution 2, from
It is fixedly connected respectively with aircraft pedestal 3 by wing mechanism；Rotor 1 is set on rotor bracket institution 2；On rotor bracket institution 2
It is fixed with motor；Motor is fixedly linked with rotor 1.
The present embodiment is preferred, and aircraft pedestal 3 is additionally provided with drive wing bracket institution 4 and driving propeller 5；With aircraft base
Seat 3 is fixedly connected；Driving propeller 5 is set on drive wing bracket institution 4；Motor is fixed on drive wing bracket institution 4；Electricity
Machine is fixedly connected with driving propeller 5.Can be as needed, it voluntarily chooses whether addition drive wing bracket institution 4 and drives spiral
Paddle 5.
The present embodiment is preferred, and free wing mechanism and 3 direction of advance of aircraft pedestal are in 90 °.
The present embodiment is preferred, and the number of the free wing is 1.
The present embodiment is preferred, and the number of rotor bracket institution 2 is 4.
The present embodiment is preferred, and aircraft pedestal 3 is equipped with empennage；Empennage includes horizontal tail 11 and vertical fin 10；Horizontal tail 11 and hang down
Tail 10 is vertical.
Embodiment 5:
In conjunction with Fig. 6 and Figure 11 to Figure 14, the present invention is second of quadrotor with the free wing, including the free wing
Mechanism, rotor 1, rotor bracket institution 2, aircraft pedestal 3, drive wing bracket institution 4 and driving propeller 5, rotor timbering machine
Structure 2, drive wing bracket institution 4 and free wing mechanism are fixedly connected with aircraft pedestal 3 respectively；Rotor 1 is set to rotor bracket
In mechanism 2；Driving propeller 5 is set on drive wing bracket institution 4；Motor is fixed on rotor bracket institution 2；Motor and rotation
The wing 1 is fixedly linked；Motor is fixed on drive wing bracket institution 4；Motor is fixedly connected with driving propeller 5.
The present embodiment is preferred, includes free wing wing 6 on free wing mechanism, freely thriving bar 7 and aseismatic mechanism 12；Freely
Electromagnetic damping mechanism is equipped in the middle part of thriving bar 7；Electromagnetic damping mechanism is located in aircraft pedestal 3；Aseismatic mechanism 12 includes stator
End and rotor-end；The stator terminal of electromagnetic damping mechanism is fixedly connected with freely thriving bar 7；The rotor-end of electromagnetic damping mechanism and fly
Row device pedestal 3 is fixedly connected；Freely cautiously bar 7 is pierced by from 3 both ends horizontal of aircraft pedestal；Free wing wing 6 and freedom are cautiously
Bar 7 is connected.
The present embodiment is preferred, and aseismatic mechanism 12 is electromagnetic damping mechanism or servo motor mechanism.Electromagnetic damping mechanism or
Person's servo motor mechanism is fixed on freely among cautiously bar 7, and the stator of belt coil is fixedly connected with freely thriving bar 7, outside
Rotor be fixedly connected with aircraft pedestal 3, for stablizing the free wing, slow down its angles shifts rate.The free wing of two sides mentions
For upward lift, and the size of lift is in direct ratio related to the velocity magnitude that aircraft advances.
The present embodiment is preferred, and free wing wing 6 is equipped with heavy hammer mechanism 8；Heavy hammer mechanism 8 is located at free 6 inside of wing wing.
The heavy hammer structure added on the inside of free wing wing 6, weight can turn to suitable angle according to axis, by the center of gravity for changing wing
Change the angle of attack of wing, obtains required lift.
The present embodiment is preferred, and free wing mechanism and 3 direction of advance of aircraft pedestal are in 90 °.
The present embodiment is preferred, and the number of the free wing most 1.
The present embodiment is preferred, and free wing wing 6 is equipped with rudder face；Rudder face is located at 9 position of external aileron of free wing wing 6.
The present embodiment is preferred, and the number of rotor bracket institution 2 is 4.
The present embodiment is preferred, and 4 quantity of drive wing bracket institution is 1.
The present embodiment is preferred, and aircraft pedestal 3 is equipped with empennage；Empennage includes horizontal tail 11 and vertical fin 10；Horizontal tail 11 and hang down
Tail 10 is vertical.
Embodiment 6:
In conjunction with Fig. 7 and Figure 11 to Figure 14, the present invention is that the third has the quadrotor of the free wing, including the free wing
Mechanism, rotor 1, rotor bracket institution 2, aircraft pedestal 3, drive wing bracket institution 4 and driving propeller 5, rotor timbering machine
Structure 2, drive wing bracket institution 4 and free wing mechanism are fixedly connected with aircraft pedestal 3 respectively；Rotor 1 is set to rotor bracket
In mechanism 2；Driving propeller 5 is set on drive wing bracket institution 4；Motor is fixed on rotor bracket institution 2；Motor and rotation
The wing 1 is fixedly linked；Motor is fixed on drive wing bracket institution 4；Motor is fixedly connected with driving propeller 5.
The present embodiment is preferred, includes free wing wing 6 on free wing mechanism, freely thriving bar 7 and aseismatic mechanism 12；Freely
Electromagnetic damping mechanism is equipped in the middle part of thriving bar 7；Electromagnetic damping mechanism is located in aircraft pedestal 3；Aseismatic mechanism 12 includes stator
End and rotor-end；The stator terminal of electromagnetic damping mechanism is fixedly connected with freely thriving bar 7；The rotor-end of electromagnetic damping mechanism and fly
Row device pedestal 3 is fixedly connected；Freely cautiously bar 7 is pierced by from 3 both ends horizontal of aircraft pedestal；Free wing wing 6 and freedom are cautiously
Bar 7 is connected.
The present embodiment is preferred, and aseismatic mechanism 12 is electromagnetic damping mechanism or servo motor mechanism.Electromagnetic damping mechanism or
Person's servo motor mechanism is fixed on freely among cautiously bar 7, and the stator of belt coil is fixedly connected with freely thriving bar 7, outside
Rotor be fixedly connected with aircraft pedestal 3, for stablizing the free wing, slow down its angles shifts rate.The free wing of two sides mentions
For upward lift, and the size of lift is in direct ratio related to the velocity magnitude that aircraft advances.
The present embodiment is preferred, and free wing wing 6 is equipped with heavy hammer mechanism 8；Heavy hammer mechanism 8 is located at free 6 inside of wing wing.
The heavy hammer structure added on the inside of free wing wing 6, weight can turn to suitable angle according to axis, by the center of gravity for changing wing
Change the angle of attack of wing, obtains required lift.
The present embodiment is preferred, and free wing mechanism and 3 direction of advance of aircraft pedestal are in 90 °.
The present embodiment is preferred, and the number of the free wing is 1.
The present embodiment is preferred, and free wing wing 6 is equipped with rudder face；Rudder face is located at 9 position of external aileron of free wing wing 6.
The present embodiment is preferred, and the number of rotor bracket institution 2 is 4.
The present embodiment is preferred, and 4 quantity of drive wing bracket institution is 1.
The present embodiment is preferred, and aircraft pedestal 3 is equipped with empennage；Empennage includes horizontal tail 11 and vertical fin 10；Horizontal tail 11 and hang down
Tail 10 is vertical.
Embodiment 7:
In conjunction with Fig. 8 and Figure 11 to Figure 14, the present invention is the 4th kind of quadrotor with the free wing, including the free wing
Mechanism, rotor 1, rotor bracket institution 2, aircraft pedestal 3, drive wing bracket institution 4 and driving propeller 5, rotor timbering machine
Structure 2, drive wing bracket institution 4 and free wing mechanism are fixedly connected with aircraft pedestal 3 respectively；Rotor 1 is set to rotor bracket
In mechanism 2；Driving propeller 5 is set on drive wing bracket institution 4；Motor is fixed on rotor bracket institution 2；Motor and rotation
The wing 1 is fixedly linked；Motor is fixed on drive wing bracket institution 4；Motor is fixedly connected with driving propeller 5.
The present embodiment is preferred, includes free wing wing 6 on free wing mechanism, freely thriving bar 7 and aseismatic mechanism 12；Freely
Electromagnetic damping mechanism is equipped in the middle part of thriving bar 7；Electromagnetic damping mechanism is located in aircraft pedestal 3；Aseismatic mechanism 12 includes stator
End and rotor-end；The stator terminal of electromagnetic damping mechanism is fixedly connected with freely thriving bar 7；The rotor-end of electromagnetic damping mechanism and fly
Row device pedestal 3 is fixedly connected；Freely cautiously bar 7 is pierced by from 3 both ends horizontal of aircraft pedestal；Free wing wing 6 and freedom are cautiously
Bar 7 is connected.
The present embodiment is preferred, and aseismatic mechanism 12 is electromagnetic damping mechanism or servo motor mechanism.Electromagnetic damping mechanism or
Person's servo motor mechanism is fixed on freely among cautiously bar 7, and the stator of belt coil is fixedly connected with freely thriving bar 7, outside
Rotor be fixedly connected with aircraft pedestal 3, for stablizing the free wing, slow down its angles shifts rate.The free wing of two sides mentions
For upward lift, and the size of lift is in direct ratio related to the velocity magnitude that aircraft advances.
The present embodiment is preferred, and free wing wing 6 is equipped with heavy hammer mechanism 8；Heavy hammer mechanism 8 is located at free 6 inside of wing wing.
The heavy hammer structure added on the inside of free wing wing 6, weight can turn to suitable angle according to axis, by the center of gravity for changing wing
Change the angle of attack of wing, obtains required lift.
The present embodiment is preferred, and free wing mechanism and 3 direction of advance of aircraft pedestal are in 90 °.
The present embodiment is preferred, and the number of the free wing is 2.
The present embodiment is preferred, and free wing wing 6 is equipped with rudder face；Rudder face is located at 9 position of external aileron of free wing wing 6.
The present embodiment is preferred, and the number of rotor bracket institution 2 is 4.
The present embodiment is preferred, and 4 quantity of drive wing bracket institution is 1.
The present embodiment is preferred, and aircraft pedestal 3 is equipped with empennage；Empennage includes horizontal tail 11 and vertical fin 10；Horizontal tail 11 and hang down
Tail 10 is vertical.
Embodiment 8:
In conjunction with Fig. 9 and Figure 11 to Figure 14, the present invention is a kind of six rotorcraft with the free wing, including free wing machine
Structure, rotor 1, rotor bracket institution 2, aircraft pedestal 3, drive wing bracket institution 4 and driving propeller 5, rotor bracket institution
2, drive wing bracket institution 4 and free wing mechanism are fixedly connected with aircraft pedestal 3 respectively；Rotor 1 is set to rotor timbering machine
On structure 2；Driving propeller 5 is set on drive wing bracket institution 4；Motor is fixed on rotor bracket institution 2；Motor and rotor
1 is fixedly linked；Motor is fixed on drive wing bracket institution 4；Motor is fixedly connected with driving propeller 5.
The present embodiment is preferred, includes free wing wing 6 on free wing mechanism, freely thriving bar 7 and aseismatic mechanism 12；Freely
Electromagnetic damping mechanism is equipped in the middle part of thriving bar 7；Electromagnetic damping mechanism is located in aircraft pedestal 3；Aseismatic mechanism 12 includes stator
End and rotor-end；The stator terminal of electromagnetic damping mechanism is fixedly connected with freely thriving bar 7；The rotor-end of electromagnetic damping mechanism and fly
Row device pedestal 3 is fixedly connected；Freely cautiously bar 7 is pierced by from 3 both ends horizontal of aircraft pedestal；Free wing wing 6 and freedom are cautiously
Bar 7 is connected.Free wing wing is equipped with the inverted diherdral of certain angle.
The present embodiment is preferred, and aseismatic mechanism 12 is electromagnetic damping mechanism or servo motor mechanism.Electromagnetic damping mechanism or
Person's servo motor mechanism is fixed on freely among cautiously bar 7, and the stator of belt coil is fixedly connected with freely thriving bar 7, outside
Rotor be fixedly connected with aircraft pedestal 3, for stablizing the free wing, slow down its angles shifts rate.The free wing of two sides mentions
For upward lift, and the size of lift is in direct ratio related to the velocity magnitude that aircraft advances.
The present embodiment is preferred, and free wing wing 6 is equipped with heavy hammer mechanism 8；Heavy hammer mechanism 8 is located at free 6 inside of wing wing.
The heavy hammer structure added on the inside of free wing wing 6, weight can turn to suitable angle according to axis, by the center of gravity for changing wing
Change the angle of attack of wing, obtains required lift.
The present embodiment is preferred, and free wing mechanism and 3 direction of advance of aircraft pedestal are in 90 °.
The present embodiment is preferred, and the number of the free wing is 1.
The present embodiment is preferred, and the number of rotor bracket institution 2 is 6.
The present embodiment is preferred, and 4 quantity of drive wing bracket institution is 1.
Embodiment 9:
In conjunction with Figure 10 and Figure 11 to Figure 14, the present invention is a kind of eight-rotary wing aircraft with the free wing, including the free wing
Mechanism, rotor 1, rotor bracket institution 2, aircraft pedestal 3, drive wing bracket institution 4 and driving propeller 5, rotor timbering machine
Structure 2, drive wing bracket institution 4 and free wing mechanism are fixedly connected with aircraft pedestal 3 respectively；Rotor 1 is set to rotor bracket
In mechanism 2；Driving propeller 5 is set on drive wing bracket institution 4；Motor is fixed on rotor bracket institution 2；Motor and rotation
The wing 1 is fixedly linked；Motor is fixed on drive wing bracket institution 4；Motor is fixedly connected with driving propeller 5.
The present embodiment is preferred, includes free wing wing 6 on free wing mechanism, freely thriving bar 7 and aseismatic mechanism 12；Freely
Electromagnetic damping mechanism is equipped in the middle part of thriving bar 7；Electromagnetic damping mechanism is located in aircraft pedestal 3；Aseismatic mechanism 12 includes stator
End and rotor-end；The stator terminal of electromagnetic damping mechanism is fixedly connected with freely thriving bar 7；The rotor-end of electromagnetic damping mechanism and fly
Row device pedestal 3 is fixedly connected；Freely cautiously bar 7 is pierced by from 3 both ends horizontal of aircraft pedestal；Free wing wing 6 and freedom are cautiously
Bar 7 is connected.
The present embodiment is preferred, and aseismatic mechanism 12 is electromagnetic damping mechanism or servo motor mechanism.Electromagnetic damping mechanism or
Person's servo motor mechanism is fixed on freely among cautiously bar 7, and the stator of belt coil is fixedly connected with freely thriving bar 7, outside
Rotor be fixedly connected with aircraft pedestal 3, for stablizing the free wing, slow down its angles shifts rate.The free wing of two sides mentions
For upward lift, and the size of lift is in direct ratio related to the velocity magnitude that aircraft advances.
The present embodiment is preferred, and free wing wing 6 is equipped with heavy hammer mechanism 8；Heavy hammer mechanism 8 is located at free 6 inside of wing wing.
The heavy hammer structure added on the inside of free wing wing 6, weight can turn to suitable angle according to axis, by the center of gravity for changing wing
Change the angle of attack of wing, obtains required lift.
Free wing mechanism and 3 direction of advance of aircraft pedestal are in 90 °.
The present embodiment is preferred, and the number of the free wing is 1.
The present embodiment is preferred, and free wing wing 6 is equipped with rudder face；Rudder face is located at 9 position of external aileron of free wing wing 6.
The present embodiment is preferred, and the number of rotor bracket institution 2 is 8.
The present embodiment is preferred, and 4 quantity of drive wing bracket institution is 1.
The present embodiment is preferred, and aircraft pedestal 3 is equipped with empennage；Empennage includes horizontal tail 11 and vertical fin 10；Horizontal tail 11 and hang down
Tail 10 is vertical.
Many details are elaborated in the above description to fully understand the present invention.But above description is only
Presently preferred embodiments of the present invention, the invention can be embodied in many other ways as described herein, therefore this
Invention is not limited by specific implementation disclosed above.Any those skilled in the art are not departing from the technology of the present invention simultaneously
In the case of aspects, all technical solution of the present invention is made using the methods and technical content of the disclosure above many possible
Changes and modifications or equivalent example modified to equivalent change.Anything that does not depart from the technical scheme of the invention, according to this
The technical spirit of invention any simple modifications, equivalents, and modifications made to the above embodiment, still fall within skill of the present invention
In the range of the protection of art scheme.
Claims (8)
1. a kind of multi-rotor aerocraft with the free wing, including free wing mechanism, rotor, rotor bracket institution and aircraft base
Seat, it is characterised in that: the rotor bracket institution, the free wing mechanism are fixedly connected with the aircraft pedestal respectively；Institute
Rotor is stated to be set on the rotor bracket institution；Motor is fixed on the rotor bracket institution；The motor and the rotation
The wing is fixedly linked；It include free wing wing on the free wing mechanism, free cautiously bar and aseismatic mechanism；The thriving bar of freedom
The aseismatic mechanism at middle part is electromagnetic damping mechanism；The electromagnetic damping mechanism is located in aircraft pedestal；The aseismatic mechanism packet
Include stator terminal and rotor-end；The stator terminal of the electromagnetic damping mechanism is fixedly connected with the thriving bar of the freedom；The electromagnetism resistance
The rotor-end of Buddhist nun mechanism is fixedly connected with the aircraft pedestal；The thriving bar of freedom is from the aircraft pedestal both ends horizontal
It is pierced by；The free wing wing is connected with the thriving bar of the freedom.
2. the multi-rotor aerocraft according to claim 1 with the free wing, it is characterised in that: the pedestal is additionally provided with drive
Dynamic wing support mechanism and driving propeller；It is fixedly connected with the aircraft pedestal；The driving propeller is set to the drive
In dynamic wing support mechanism；Motor is fixed on the drive wing bracket institution；The motor and the fixed company of the driving propeller
It connects.
3. the multi-rotor aerocraft according to claim 1 with the free wing, it is characterised in that: on the free wing wing
Equipped with heavy hammer mechanism；The heavy hammer mechanism is located at the free wing inboard.
4. the multi-rotor aerocraft according to claim 1 or 2 with the free wing, it is characterised in that: the free wing machine
Structure and the aircraft pedestal direction of advance are in 90 °.
5. the multi-rotor aerocraft according to claim 1 with the free wing, it is characterised in that: the number of the free wing
At least one.
6. the multi-rotor aerocraft according to claim 1 with the free wing, it is characterised in that: the free wing wing is set
There is rudder face；The rudder face is located at the external aileron position of free wing wing.
7. the multi-rotor aerocraft according to claim 1 with the free wing, it is characterised in that: the rotor bracket institution
Number at least one.
8. the multi-rotor aerocraft according to claim 1 with the free wing, it is characterised in that: on the aircraft pedestal
Equipped with empennage；The empennage includes horizontal tail and vertical fin；The horizontal tail is vertical with the vertical fin.
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| CN201611062653.8A CN106428524B (en) | 2016-11-25 | 2016-11-25 | A kind of multi-rotor aerocraft with the free wing |
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| CN201611062653.8A CN106428524B (en) | 2016-11-25 | 2016-11-25 | A kind of multi-rotor aerocraft with the free wing |
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| CN106428524A CN106428524A (en) | 2017-02-22 |
| CN106428524B true CN106428524B (en) | 2019-09-13 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN207943165U (en) * | 2017-10-30 | 2018-10-09 | 深圳市大疆创新科技有限公司 | A kind of unmanned vehicle and its ascending, descending frame |
| CN207809768U (en) * | 2017-11-28 | 2018-09-04 | 深圳市大疆创新科技有限公司 | A kind of unmanned vehicle |
| CN108438206B (en) * | 2018-01-31 | 2022-03-15 | 芜湖市海联机械设备有限公司 | Unmanned aerial vehicle capable of self-balancing according to wind direction |
| CN108674632B (en) * | 2018-05-03 | 2021-06-22 | 谢娟 | An aircraft for agricultural spraying of drugs |
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| CN1118591A (en) * | 1993-01-22 | 1996-03-13 | 自由翼飞机公司 | Stol/vtol free wing aircraft with articulated tail boom |
| CN101010235A (en) * | 2004-07-02 | 2007-08-01 | 塞米肯公司 | Hybrid aircraft |
| CN204895839U (en) * | 2015-07-06 | 2015-12-23 | 杨钧杰 | Light aerocraft all -moving wing |
| CN205113706U (en) * | 2015-08-12 | 2016-03-30 | 刘十一 | A vertical take-off and landing fixed-wing aircraft with automatically retractable multi-rotors |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| KR101125870B1 (en) * | 2011-07-29 | 2012-03-28 | 한국항공우주연구원 | The tiltrotor aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1118591A (en) * | 1993-01-22 | 1996-03-13 | 自由翼飞机公司 | Stol/vtol free wing aircraft with articulated tail boom |
| CN101010235A (en) * | 2004-07-02 | 2007-08-01 | 塞米肯公司 | Hybrid aircraft |
| CN204895839U (en) * | 2015-07-06 | 2015-12-23 | 杨钧杰 | Light aerocraft all -moving wing |
| CN205113706U (en) * | 2015-08-12 | 2016-03-30 | 刘十一 | A vertical take-off and landing fixed-wing aircraft with automatically retractable multi-rotors |
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| CN106428524A (en) | 2017-02-22 |
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Effective date of registration: 20190904 Address after: 211100 Jiangning economic and Technological Development Zone, Jiangsu, general Avenue, No. 37, No. Patentee after: Nanjing Dassault Aviation Technology Co. Ltd. Address before: 210000 Tianyuanju, Yadu, No. 137 Jinghuai Street, Jiangning District, Nanjing City, Jiangsu Province, 6 buildings 402 Patentee before: Nanjing Karl Aviation Technology Co., Ltd. |
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Address after: No. 588, Hong Kong Road, Haimen Economic and Technological Development Zone, Nantong City, Jiangsu Province Patentee after: Nantong Guoyi Aviation Technology Co.,Ltd. Address before: 211100 37 general road, Jiangning economic and Technological Development Zone, Nanjing, Jiangsu Patentee before: NANJING DASSAULT AVIATION TECHNOLOGY Co.,Ltd. |