CN106275417A - A kind of Fixed Wing AirVehicle with many rotors - Google Patents
A kind of Fixed Wing AirVehicle with many rotors Download PDFInfo
- Publication number
- CN106275417A CN106275417A CN201610818142.8A CN201610818142A CN106275417A CN 106275417 A CN106275417 A CN 106275417A CN 201610818142 A CN201610818142 A CN 201610818142A CN 106275417 A CN106275417 A CN 106275417A
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- Prior art keywords
- motor
- fuselage
- axis
- many rotors
- symmetry
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Classifications
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
Abstract
Present invention is disclosed a kind of Fixed Wing AirVehicle with many rotors, belong to aircraft field.It solve existing aircraft to be limited by landing site and the slow-footed problem of horizontal flight, it includes a fuselage, two wings, one first propulsion plant and one second propulsion plant, two wings are movably fixed to fuselage both sides respectively, and two V-shaped settings of wing, and opening is towards afterbody, first propulsion plant is in order to produce horizontal pull or horizontal thrust to aircraft, and the second propulsion plant is coupled on fuselage or described wing, and the second propulsion plant in order to produce longitudinal lift to aircraft.
Description
Technical field
The present invention relates to aircraft field, particularly to a kind of Fixed Wing AirVehicle with many rotors.
Background technology
Having fixed-wing and many rotors at the aircraft that aviation field is common, wherein, fixed-wing relies on engine to promote, and engine drives
The raw horizontal thrust being parallel to fuselage axis of movable property, makes the fixed-wing can high-speed flight aloft.But owing to engine can not produce
The raw lift being perpendicular to fuselage axis, so fixed-wing can only obtain lift by the relative motion between fixed-wing and air,
To overcome the gravity of fixed-wing, there is positive correlation, phase in the speed of related movement between the size of lift and fixed-wing and air
The biggest to movement velocity, the lift that fixed-wing is obtained is the biggest.But, fixed-wing of the prior art also exists two and lacks
Point: first, needs longer runway that fixed-wing just can be made to obtain enough horizontal velocities, so that fixed-wing obtains enough when taking off
Lift take off；Second, fixed-wing needs to keep enough flight speeds could obtain enough lift to overcome after take off
The gravity of self.
Many rotors rely on engine make the propeller of many rotors around own axes rotation, many rotors by propeller time rotational with
Air produces relative motion and obtains lift.The lift produced due to many rotors is directly driven propeller certainly then generation by engine,
The most rotors take off need not have horizontal flight speed, i.e. eliminate the reliance on runway, overcome fixed-wing and rely on relatively long runway
Shortcoming.Meanwhile, many rotors also overcome the shortcoming needing to keep enough flight speeds after fixed-wing takes off, and many rotors can hang down
Go straight up to fall, hovering, forwards, backwards left and right flight, there is the diversified advantage of flight attitude.But owing to many rotors provide
Mainly lift, the horizontal thrust being parallel to fuselage axis that many rotor wing unmanned aerial vehicles obtain is less, so horizontal flight speed is relatively
Slowly.
In sum, in prior art, aircraft or need to rely on long runway, and need to keep enough flying after taking off
Line speed；Horizontal flight speed is slower.
Summary of the invention
The main object of the present invention there is provided the aircraft of a kind of combination fixed-wing and the structure of many rotors, it solves
Existing aircraft is limited by landing site and the slow-paced defect of horizontal flight.
For reaching object above, the invention provides a kind of Fixed Wing AirVehicle with many rotors, including:
Fuselage；
Two wings, wing described in two is movably fixed to described fuselage both sides, the V-shaped setting of wing described in two respectively, and opens
Mouth is towards described afterbody；
First propulsion plant, described first propulsion plant is coupled on described fuselage, and described first propulsion plant is in order to right
Aircraft produces horizontal pull or horizontal thrust；
Second propulsion plant, described second propulsion plant is coupled on described fuselage or described wing, and described second advances
Device in order to produce longitudinal lift to aircraft.
In one embodiment, described fuselage has a plane of symmetry, and wing described in two is symmetrically arranged at described symmetry
The both sides in face.
In one embodiment, the center of gravity of described aircraft is positioned on the described plane of symmetry.
In one embodiment, wing described in two is integral type structure.
In one embodiment, described fuselage is provided with the first slot, described wing embed in described first slot with
Described fuselage connects.
In one embodiment, the wingtip of described wing is extended with winglet.
In one embodiment, wing described in two is all mutually perpendicular to the described plane of symmetry.
In one embodiment, described first propulsion plant includes first motor and first propeller, described
The output shaft of the first motor couples described first propeller；
Described second propulsion plant includes at least one second motor and at least one second propeller, described second motor
Quantity and the quantity of described second propeller equal, and the output shaft of each described second motor is all coupled with one described
Two propellers.
In one embodiment, the output shaft axis of described first motor is positioned on the described plane of symmetry, and described first electricity
The output shaft axis of machine is parallel to each other with described fuselage axis or overlaps.
In one embodiment, described first propeller is connected with described fuselage head by the first motor, and described first
Motor drives described first propeller rotation, produces described aircraft horizontal pull forward.
In one embodiment, described first motor embeds in described afterbody, and the output shaft of described first motor
With described fuselage dead in line, the output shaft of described first motor passes outside described afterbody and described first propeller coupling
Connecing, described first motor drives described first propeller rotation, and produces described aircraft horizontal thrust forward.
In one embodiment, on the downside of described fuselage head, it is provided with photoelectric nacelle, is provided with in described photoelectric nacelle and takes the photograph
As head.
In one embodiment, the output shaft axis of described second motor is mutually perpendicular to described fuselage axis, and described
The output shaft axis of the second motor is parallel to each other with the described plane of symmetry or overlaps.
In one embodiment, the quantity of described second motor is one, and described second motor is connected with described fuselage,
The output shaft axis of described second motor overlaps with the described plane of symmetry, and the output shaft axis of described second motor pass through described in fly
The center of gravity of row device.
In one embodiment, the output shaft axis of described second motor is mutually perpendicular to described fuselage axis, and described
The output shaft axis of the second motor and the angle of the described plane of symmetry are more than 0 °.
In one embodiment, between output shaft axis and the described plane of symmetry of described second motor, angle upward is
Between 8 °, or the output shaft axis of described second motor and the described plane of symmetry, angle down is 8 °.
In one embodiment, described second motor is connected with described fuselage or described wing by support, described support
Including cross bar and vertical pole, described cross bar the first end is connected with described fuselage or described wing, described cross bar is also associated with described
Vertical pole the first end, described vertical pole the second end is connected with described second motor.
In one embodiment, described cross bar and vertical pole are package assembly or integral structure.
In one embodiment, described second motor embeds inside described vertical pole the second end, the output of described second motor
Axle passes outside described vertical pole the second end, and couples with described second propeller.
In one embodiment, the first end of described cross bar is connected with described wing, described cross bar axis and described fuselage
Axis is parallel to each other, and described cross bar axis is mutually perpendicular to described vertical pole axis.
In one embodiment, the quantity of described second motor is four, and described in two of which, the second motor is arranged on institute
Stating the first side of the plane of symmetry, the second motor described in another two is arranged on the second side of the described plane of symmetry, and is arranged on described symmetry
Two described second motors of the first side, face be arranged on two described second motors of the described plane of symmetry the second side along described right
Title face is symmetrical arranged, and is wherein positioned at two described second motors of the described plane of symmetry the first side or is positioned at the described plane of symmetry the second side
Two described second motors lay respectively at the both sides of described wing.
In one embodiment, the first end of two the described cross bars being positioned at described plane of symmetry the same side is connected, or
Two the described cross bars being positioned at described plane of symmetry the same side are integral type structure.
In one embodiment, described cross bar is positioned at upside or the downside of described wing.
In one embodiment, in four described second motors at least both, in order to adjust described aircraft pitching, rolling
At least one in turning and going off course.
In one embodiment, the first end of described cross bar is connected with described fuselage, described cross bar axis and described fuselage
Axis is mutually perpendicular to, and described cross bar axis is arranged in a mutually vertical manner with described vertical pole axis.
According to preferred embodiment, the invention provides following advantage:
(1) aircraft of the present invention combines fixed-wing and the structure of many rotors, produces horizontal pull including to aircraft
Or the first propulsion plant of horizontal thrust, and multi-aircraft produces longitudinal lift and the second propulsion plant of longitudinal thrust；
(2) aircraft of the present invention has and has hovering ability as fixed-wing, to runway without relying on, and zero-speed
The degree advantage such as takeoff and anding, and have as many rotors there is higher horizontal flight speed, and there is bigger voyage
Etc. advantage.
The present invention is further illustrated below in conjunction with drawings and Examples.
Accompanying drawing explanation
Fig. 1 is the structural representation of the Fixed Wing AirVehicle with many rotors of the present invention.
Detailed description of the invention
Hereinafter describe and be used for disclosing the present invention so that those skilled in the art are capable of the present invention.Below describe in excellent
Select embodiment to be only used as citing, it may occur to persons skilled in the art that other obvious modification.Define in the following description
The ultimate principle of the present invention can apply to other embodiments, deformation program, improvement project, equivalent and the not back of the body
Other technologies scheme from the spirit and scope of the present invention.
Refering to accompanying drawing 1, it is shown that fly according to a kind of fixed-wing with many rotors described in the preferred embodiment of the present invention
Device (hereinafter referred to as aircraft), wherein said aircraft can be that piloted vehicle, push-button aircraft or distance type fly
Row device.Especially, described aircraft is one and combines fixed-wing and many rotor structures, and possesses fixed-wing and many rotors respectively
The aircraft of advantage, such as, described aircraft longitudinally can take off in the way of many rotor flyings, has runway without relying on,
Possess the advantage such as hovering ability and zero velocity takeoff and anding, and can horizontal flight in the way of fixed-wing flight, have higher
Horizontal flight speed, and there is bigger voyage.
In the present embodiment, the described Fixed Wing AirVehicle with many rotors, including fuselage 1 and two wings 2, fuselage 1 has
Having a plane of symmetry, the center of gravity of aircraft is positioned on this plane of symmetry, and wherein two wings 2 are symmetrically arranged at the both sides of the plane of symmetry,
And two wing 2 be movably fixed to fuselage 1 both sides, such as fuselage 1 both sides and be respectively arranged with the first slot, wing 2 embeds first and inserts
It is connected with fuselage 1 in groove, facilitates the installation and removal of wing 2.It addition, the two the most V-shaped settings of wing 2, and opening is towards fuselage 1
Afterbody, the angle of this opening is 120 °～140 °, it is preferable that the angle of opening is 132.30 °.Further, two wings 2 all with
The plane of symmetry is mutually perpendicular to.
In other embodiments, two wings 2 are integral type structure, and therefore, the quantity of this first slot can be one, one
Two wings 2 of body formula are connected with fuselage 1 in embedding this first slot.
In the present embodiment, the wingtip of wing 2 is extended with winglet 3, and this winglet 3 is in order to reduce wing induction resistance
Power, can be single upper winglet or upper and lower winglet etc., it is preferable that winglet 3 upwardly extends in the wingtip of wing 2, and winglet 3
And the angle between wing 2 is 105 °.
Described aircraft also includes that the first propulsion plant, the first propulsion plant include first motor and first spiral shell
Rotation oar 4, the first propeller 4 is coupled on the output shaft 5 of the first motor, and output shaft 5 axis of the first motor is positioned on the plane of symmetry,
And first output shaft 5 axis of motor parallel with fuselage 1 axis or overlap, and then make aircraft keep putting down in flight course
Weighing apparatus.
In the present embodiment, the first propeller 4 is connected with fuselage 1 head by the first motor, and the first motor drives first
Propeller 4 rotation, produces aircraft horizontal pull forward, therefore, this aircraft have as fixed-wing at high speed to
The advantage of front horizontal flight.
In other embodiments, the first propeller 4 is connected with fuselage 1 afterbody by the first motor, and the first motor is defeated
Shaft 5 and fuselage 1 dead in line, the first motor drives the first propeller 4 rotation, and produces and push away aircraft level forward
Power.The mode that this first motor is connected with fuselage 1 afterbody includes: the first motor embeds in described fuselage 1 afterbody, the first motor
Output shaft 5 passes and couples with described first propeller 4 outside fuselage 1 afterbody.It addition, be provided with photoelectric nacelle on the downside of fuselage 1 head
10, it is provided with photographic head in photoelectric nacelle 10.
Described aircraft include the second propulsion plant, the second propulsion plant include at least one second motor and at least one
Second propeller 6, the quantity of the second motor and the quantity of the second propeller 6 are equal, and the output shaft 7 of each second motor all couples
Having second propeller 6, therefore, each in multiple second propellers 6 can carry out turning independent of other the second propeller 6
Velocity modulation is whole, thus realizes the pitching of aircraft, rolling and driftage etc..Wherein, output shaft 7 axis of the second motor and fuselage 1 axle
Line is mutually perpendicular to, and output shaft 7 axis of the second motor is 0 °～10 ° with fuselage 1 plane of symmetry angle, and therefore, the second motor drives
Dynamic second propeller 6 rotation, produces aircraft longitudinal lift upwards, make aircraft have as many rotors to runway without
Rely on, possess the advantage such as hovering ability and zero velocity takeoff and anding, as preferably, output shaft 7 axis of the second motor with
The angle of fuselage 1 plane of symmetry is 0 °, and output shaft 7 axis of the i.e. second motor is parallel to each other with fuselage 1 plane of symmetry or overlaps.More excellent
Selection of land, between output shaft 7 axis and fuselage 1 plane of symmetry of the second motor, angle upward is 8 °, or the output of the second motor
Between axle 7 axis and fuselage 1 plane of symmetry, angle down is 8 °.
In the present embodiment, being provided with flight control system and power supply etc. in fuselage 1, flight control system is respectively with first
Motor and the electrical connection of the second motor, control the first motor and the work of the second motor respectively by remote controller, and power supply can be lithium battery,
And power supply is respectively the first motor, the second motor and images first-class work offer electric energy.In addition, aircraft also comprises pair
The common components such as the wing, elevator and rudder.
In the present embodiment, the quantity of the second motor and the second propeller 6 is one, and the second motor is with fuselage 1 even
Connecing, output shaft 7 axis of the second motor is positioned on fuselage 1 plane of symmetry, output shaft 7 axis of the second motor and fuselage 1 axis phase
The most vertical, and the center of gravity that output shaft 7 axis of the second motor is by aircraft.
In other embodiments, the quantity of the second motor and the second propeller 6 is more than one, wherein, and the second motor
Connecting fuselage 1 or wing 2 by support, support includes that cross bar 8 and vertical pole 9, cross bar 8 first end are connected with fuselage 1 or wing 2,
It is also associated with vertical pole 9 first end, vertical pole 9 second end and the second motor on cross bar 8 to connect.Second motor is embedded into vertical pole 9 second
End is internal, and the output shaft 6 of the second motor passes outside vertical pole 9 second end, and couples with the second propeller 5, and the second propeller 5 is permissible
It is positioned at upside or the downside of cross bar 8.
In the present embodiment, cross bar 8 and vertical pole 9 are integral type structure.
In other embodiments, cross bar 8 and vertical pole 9 are modular construction, wherein, cross bar 8 are provided with the second slot, vertical
Bar 9 first end is connected with cross bar 8 in embedding the second slot.
As preferably, the quantity of the second motor and the second propeller 6 is four, and wherein, two the second motors are arranged
In the first side of the plane of symmetry, another two the second motor is arranged on the second side of the plane of symmetry, and is arranged on the two of the plane of symmetry the first side
Individual second motor and two the second motors being arranged on the plane of symmetry the second side are symmetrical arranged along the plane of symmetry, are wherein positioned at the plane of symmetry
Two the second motors of side or be positioned at two the second motors of the plane of symmetry the second side and lay respectively at the both sides of wing 2.
In the present embodiment, the first end of cross bar 8 is connected with wing 2, and cross bar 8 axis is parallel to each other with fuselage 1 axis, and
Cross bar 8 axis is mutually perpendicular to vertical pole 9 axis, and the second propeller 6 is positioned at the upside of cross bar 8.Further, plane of symmetry the same side it is positioned at
The first end of two cross bars 8 be connected, or two cross bars 8 being positioned at plane of symmetry the same side are integral type structure.
In other embodiments, the first end of cross bar 8 is connected with fuselage 1, and cross bar 8 axis is mutually perpendicular to fuselage 1 axis,
And cross bar 8 axis is arranged in a mutually vertical manner with vertical pole 9 axis.
The method of operating of the aircraft being described below in the present embodiment:
When taking off, the first motor does not starts, the second electric motor starting, and second driven by motor the second propeller 6 rotation, for flying
Row device provides longitudinal lift upwards, and when longitudinal lift that the second propeller 6 produces is more than the gravity of the device that takes off, the device that takes off is opened
Beginning takes off.
After taking off, after aircraft flight to certain altitude, second driven by motor the second propeller 6 rotating speed keeps constant, makes
Aircraft keeps balance, then starts the first motor, first driven by motor the first propeller 4 rotation, produces the water to aircraft
Horizontal sliding power or horizontal pull, the horizontal flight speed of the device that now takes off starts to accelerate, and the device that takes off enters takeoff condition and flies to level
The transition stage of row state, when after the horizontal flight speed that the device that takes off reaches certain, closes the second motor, device entrance level of taking off
State of flight.When the device that takes off needs hovering, close the first motor, make the horizontal pull of the first propeller 4 generation or level push away
Power is zero, then starts the second motor, and second driven by motor the second propeller 6 rotation produces the longitudinal lift to aircraft, when
When lift is equal to aircraft gravity, the device that takes off is in floating state.After this, can be coordinated by least two the second motor,
The device that makes to take off realizes the actions such as pitching, rolling or driftage.
During landing, the first motor cuts out, and the second motor reduces the rotating speed of the second propeller 6, makes aircraft upwards vertical
Reducing to lift, when lift is less than the gravity of aircraft, aircraft starts landing.
Embodiment described above is merely to illustrate technological thought and the feature of the present invention, in its object is to make this area
Technical staff will appreciate that present disclosure and implement according to this, it is impossible to only limit the patent model of the present invention with the present embodiment
Enclose employing, the most all equal changes made according to disclosed spirit or modification, still fall in the scope of the claims of the present invention.
Claims (25)
1. the Fixed Wing AirVehicle with many rotors, it is characterised in that including:
Fuselage (1)；
Two wings (2), wing described in two (2) is movably fixed to described fuselage (1) both sides respectively, and wing described in two (2) is V-shaped to be set
Put, and opening is towards described fuselage (1) afterbody；
First propulsion plant, described first propulsion plant is coupled on described fuselage (1), and described first propulsion plant is in order to flying
Row device produces horizontal pull or horizontal thrust；
Second propulsion plant, described second propulsion plant is coupled on described fuselage (1) or described wing (2), and described second pushes away
Enter device in order to aircraft to be produced longitudinal lift.
2. as claimed in claim 1 with the Fixed Wing AirVehicle of many rotors, it is characterised in that described fuselage (1) has one
The plane of symmetry, wing described in two (2) is symmetrically arranged at the both sides of the described plane of symmetry.
3. as claimed in claim 2 with the Fixed Wing AirVehicle of many rotors, it is characterised in that the center of gravity position of described aircraft
On the described plane of symmetry.
4. as claimed in claim 2 with the Fixed Wing AirVehicle of many rotors, it is characterised in that wing described in two (2) is one
Body formula structure.
5. as claimed in claim 2 with the Fixed Wing AirVehicle of many rotors, it is characterised in that described fuselage (1) is upper to be arranged
The first slot, described wing (2) is had to be connected with described fuselage (1) in embedding described first slot.
6. as claimed in claim 2 with the Fixed Wing AirVehicle of many rotors, it is characterised in that the wingtip of described wing (2)
It is extended with winglet (3).
7. as claimed in claim 2 with the Fixed Wing AirVehicle of many rotors, it is characterised in that wing described in two (2) all with
The described plane of symmetry is mutually perpendicular to.
8. as claimed in claim 2 with the Fixed Wing AirVehicle of many rotors, it is characterised in that described first propulsion plant bag
Including first motor and first propeller (4), the output shaft (5) of described first motor couples described first propeller
(4)；
Described second propulsion plant includes at least one second motor and at least one second propeller (6), described second motor
Quantity and the quantity of described second propeller (6) equal, and the output shaft (7) of each described second motor is all coupled with one
Described second propeller (6).
9. as claimed in claim 8 with the Fixed Wing AirVehicle of many rotors, it is characterised in that the output of described first motor
Axle (5) axis is positioned on the described plane of symmetry, and output shaft (5) axis of described first motor is mutual with described fuselage (1) axis
Parallel or overlap.
10. as claimed in claim 9 with the Fixed Wing AirVehicle of many rotors, it is characterised in that described first propeller (4)
Being connected with described fuselage (1) head by the first motor, described first motor drives the rotation of described first propeller (4), produces
To described aircraft horizontal pull forward.
11. as claimed in claim 9 with the Fixed Wing AirVehicle of many rotors, it is characterised in that described first motor embeds
In described fuselage (1) afterbody, and the output shaft (5) of described first motor and described fuselage (1) dead in line, described first motor
Output shaft (5) pass that described fuselage (1) afterbody is outer to be coupled with described first propeller (4), described in described first motor drives
First propeller (4) rotation, and produce described aircraft horizontal thrust forward.
12. as claimed in claim 11 with the Fixed Wing AirVehicle of many rotors, it is characterised in that described fuselage (1) head
Downside is provided with photoelectric nacelle (10), and described photoelectric nacelle is provided with photographic head in (10).
13. as claimed in claim 8 with the Fixed Wing AirVehicles of many rotors, it is characterised in that described second motor defeated
Shaft (7) axis is mutually perpendicular to described fuselage (1) axis, and output shaft (7) axis of described second motor and described symmetry
Face is parallel to each other or overlaps.
14. as claimed in claim 13 with the Fixed Wing AirVehicle of many rotors, it is characterised in that the number of described second motor
Amount is one, and described second motor is connected with described fuselage (1), and output shaft (7) axis of described second motor is right with described
Title face overlaps, and the center of gravity that output shaft (7) axis of described second motor is by described aircraft.
15. as claimed in claim 8 with the Fixed Wing AirVehicles of many rotors, it is characterised in that described second motor defeated
Shaft (7) axis is mutually perpendicular to described fuselage (1) axis, and output shaft (7) axis of described second motor and described symmetry
The angle in face is more than 0 °.
16. as claimed in claim 15 with the Fixed Wing AirVehicles of many rotors, it is characterised in that described second motor defeated
Between shaft (7) axis and the described plane of symmetry, angle upward is 8 °, or output shaft (7) axis of described second motor and institute
Stating between the plane of symmetry angle down is 8 °.
17. as arbitrary in claim 13,15 or 16 as described in the Fixed Wing AirVehicle with many rotors, it is characterised in that described
Second motor is connected with described fuselage (1) or described wing (2) by support, and described support includes cross bar (8) and vertical pole (9),
Described cross bar (8) first end is connected with described fuselage (1) or described wing (2), and described cross bar is also associated with described vertical pole on (8)
(9) first ends, described vertical pole (9) second end is connected with described second motor.
18. as claimed in claim 17 with the Fixed Wing AirVehicles of many rotors, it is characterised in that described cross bar (8) and indulging
Bar (9) is package assembly or integral structure.
19. as claimed in claim 17 with the Fixed Wing AirVehicle of many rotors, it is characterised in that described second motor embeds
Inside described vertical pole (9) second end, the output shaft (7) of described second motor passes outside described vertical pole (9) second end, and with described
Second propeller (6) couples.
20. as claimed in claim 19 with the Fixed Wing AirVehicles of many rotors, it is characterised in that the of described cross bar (8)
One end is connected with described wing (2), and described cross bar (8) axis is parallel to each other with described fuselage (1) axis, and described cross bar (8)
Axis is mutually perpendicular to described vertical pole (9) axis.
21. as claimed in claim 20 with the Fixed Wing AirVehicle of many rotors, it is characterised in that the number of described second motor
Amount is four, and the second motor described in two of which is arranged on the first side of the described plane of symmetry, and described in another two, the second motor is arranged
In the second side of the described plane of symmetry, and be arranged on two described second motors of the described plane of symmetry the first side be arranged on described right
Two described second motors of the second side, title face are symmetrical arranged along the described plane of symmetry, are wherein positioned at the two of the described plane of symmetry the first side
Individual described second motor or be positioned at two described second motors of the described plane of symmetry the second side and lay respectively at the two of described wing (2)
Side.
22. as claimed in claim 21 with the Fixed Wing AirVehicle of many rotors, it is characterised in that be positioned at the described plane of symmetry same
First end of two described cross bars (8) of side is connected, or is positioned at two described cross bars (8) of described plane of symmetry the same side
For integral type structure.
23. as claimed in claim 22 with the Fixed Wing AirVehicle of many rotors, it is characterised in that described cross bar (8) is positioned at
The upside of described wing (2) or downside.
24. as claimed in claim 21 with the Fixed Wing AirVehicle of many rotors, it is characterised in that four described second motors
In at least both, in order to adjust at least one in described aircraft pitching, rolling and driftage.
25. as claimed in claim 19 with the Fixed Wing AirVehicles of many rotors, it is characterised in that the of described cross bar (8)
One end is connected with described fuselage (1), and described cross bar (8) axis is mutually perpendicular to described fuselage (1) axis, and described cross bar (8)
Axis is arranged in a mutually vertical manner with described vertical pole (9) axis.
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| CN201610818142.8A CN106275417A (en) | 2016-09-12 | 2016-09-12 | A kind of Fixed Wing AirVehicle with many rotors |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610818142.8A CN106275417A (en) | 2016-09-12 | 2016-09-12 | A kind of Fixed Wing AirVehicle with many rotors |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107054621A (en) * | 2017-03-23 | 2017-08-18 | 西安飞机工业（集团）有限责任公司 | A kind of plug-in transition beam of wing |
| CN109857132A (en) * | 2019-03-12 | 2019-06-07 | 辽宁壮龙无人机科技有限公司 | A kind of flight control assemblies and method |
| RU2785230C1 (en) * | 2018-12-19 | 2022-12-05 | ЛЕОНАРДО С.п.А. | Aircraft and method for its manufacture |
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| CN105015770A (en) * | 2015-07-29 | 2015-11-04 | 张飞 | Vertical take-off and landing aircraft with wing body blended with single duct |
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| RU2785230C1 (en) * | 2018-12-19 | 2022-12-05 | ЛЕОНАРДО С.п.А. | Aircraft and method for its manufacture |
| CN109857132A (en) * | 2019-03-12 | 2019-06-07 | 辽宁壮龙无人机科技有限公司 | A kind of flight control assemblies and method |
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