CN104859859B - Aerodynamic optimization hybrid multirotor - Google Patents
Aerodynamic optimization hybrid multirotor Download PDFInfo
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- CN104859859B CN104859859B CN201510250011.XA CN201510250011A CN104859859B CN 104859859 B CN104859859 B CN 104859859B CN 201510250011 A CN201510250011 A CN 201510250011A CN 104859859 B CN104859859 B CN 104859859B
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Abstract
The invention provides an aerodynamic optimization hybrid multirotor, comprising a fuselage, at least one undercarriage, a fuel engine, an installation platform, power rotors, a power-driven rotor mechanism and an aerodynamic optimization mechanism, wherein the fuselage is provided with an upper surface, a lower surface and a first cavity; the undercarriage is fixed to the lower surface of the fuselage; the installation platform is semi-enclosed and is fixed to the lower surface of the fuselage and used for installing the fuel engine, and a second cavity connected with the first cavity is formed; the power rotors are used for being driven by the fuel engine to rotate to enable the multirotor to fly, arranged on the output shaft of the fuel engine and positioned in the first cavity or the second cavity; the power-driven rotor mechanism is used for receiving a far-end first control signal to adjust the flight attitude of the multirotor; the aerodynamic optimization mechanism is used for receiving a far-end second control signal to eliminate reverse twist during the flight of the multirotor and arranged on the outer wall of the installation platform. By implementing the aerodynamic optimization hybrid multirotor, the fuel engine and the power rotors are adopted, the aerodynamic optimization hybrid multirotor has the characteristics of simple structure, stable flight, easy operation and the like, and the carrying capacity, the battery life, the cruising speed, the size and the structure are greatly improved.
Description
Technical field
The present invention relates to multi-rotor aerocraft field, more particularly to a kind of aerodynamic optimization oil electricity mixing multi-rotor aerocraft.
Background technology
Multi-rotor aerocraft (Multirotor) is a kind of aircraft for being capable of VTOL, has at least three on its fuselage
A motor is equipped with individual rotor shaft, and each rotor shaft and one drives rotation to form the rotor of thrust by aforementioned motor, and
Various flare maneuvers can be realized by changing the rotating speed between different rotors.Due to multi-rotor aerocraft have simple structure,
Flight stability, the low feature of easily operated, easy to carry, safety hazard, therefore it is widely used in domestic and international every field
In.
In prior art, multi-rotor aerocraft includes electronic multi-rotor aerocraft and hybrid power Multi-axis aircraft.With biography
System helicopter is compared, the comparative maturity that existing electronic multi-rotor aerocraft has developed, although it has simple structure, symmetrical rotation
Total distance between the wing is fixed, and the blade of each rotor is shorter, while the linear velocity of blade end is slow, so as to touch
Impulsive force is little when hitting, be hardly damaged and with more the advantages of safety, it can be difficult to doing big, main reason is that existing electronic
Multi-rotor aerocraft great majority are using lithium polymer battery as power source.Due to the energy density of power source it is much low
In bio-fuel, therefore the cruising time of electronic multi-rotor aerocraft is short, and particularly electronic multi-rotor aerocraft reaches a set pattern
After mould, its battery weight accounts for take-off weight rising more notable than meeting, so as to there are a series of insoluble problems, such as payload
Increase, the increase of airborne period etc..
Although existing hybrid power Multi-axis aircraft can solve the problems referred to above that electronic multi-rotor aerocraft occurs,
It is, when the fuel engines on hybrid power Multi-axis aircraft drives power rotor rotational, to form larger anti-twisted.It is theoretical
For upper, hybrid power Multi-axis aircraft can be anti-twisted to overcome by changing the speed discrepancy of brshless DC motor thereon, protects
Keep steady qualitative, but the size difference due to power rotor thereon with pose adjustment rotor therebetween is larger, the air of generation
Counteracting force is difficult to overcome anti-twisted purpose in actual applications not on the same order of magnitude.
Aforementioned two kinds of existing multi-rotor aerocrafts typically adopt in design symmetrical structure so that existing many rotors fly
Row device has in all directions essentially identical flying quality, although with higher fast reserve, but overall pneumatic property
Can not be optimum, and the lift for providing is limited so that resistance during cruise is greatly increased, be unfavorable for being lifted cruising time with
And cruising speed, especially more project in the case where blowing, lack higher wind resistance.
The content of the invention
Embodiment of the present invention technical problem to be solved is, there is provided a kind of many rotor flyings of aerodynamic optimization oil electricity mixing
Device, using fuel engines and electronic rotor, not only with simple structure, flight stability, it is easily operated the features such as, also carrying
It is greatly improved in weight, cruising time, cruising speed, size and structure.
In order to solve above-mentioned technical problem, a kind of many rotor flyings of aerodynamic optimization oil electricity mixing are embodiments provided
Device, the multi-rotor aerocraft includes：
One fuselage, the fuselage includes upper surface, lower surface and through the first of the upper surface and the lower surface
Cavity；
An at least undercarriage, the undercarriage is mutually fixed with the fuselage lower surface；
One fuel engines；
One is semi-enclosed and for installing the mounting platform of the fuel engines, under the mounting platform and the fuselage
Surface is mutually fixed, and it is formed with the second cavity that opening is connected towards first cavity and with first cavity；
One is rotated by fuel engines driving and is produced the power rotation that thrust realizes the multi-rotor aerocraft flight
The wing, the power rotor is arranged on the output shaft of the fuel engines, and positioned at second cavity or first chamber
In vivo；
At least one is used to receive the control signal of distal end first to adjust the electronic rotation of the multi-rotor aerocraft flight attitude
Wing mechanism；And
At least one is used to receiving the control signal of distal end second anti-twisted pneumatic during the multi-rotor aerocraft flight to eliminate
Optimization mechanism, the aerodynamic optimization mechanism is arranged on the outer wall of the mounting platform；
Wherein, the aerodynamic optimization mechanism includes hinge, slip-stream rudder, connecting rod and slip-stream steering wheel；Wherein,
The hinge at least one, one end of each hinge is both secured on the outer wall of the mounting platform, the other end
Mutually fix with the first face of the slip-stream rudder；
The slip-stream rudder can be installed on the outer wall of the mounting platform by what the hinge was rotated, its second face and institute
The one end for stating connecting rod is mutually fixed；
The slip-stream steering wheel is fixed on the outer wall of the mounting platform, and it includes that what is be connected with the connecting rod other end turns
Motion rocker arm；
When rocking arm rotation is rotated described in the slip-stream servo driving, the slip-stream rudder is controlled around described by the connecting rod
Hinge is rotated toward and away from the slip-stream steering wheel.
Wherein, the aerodynamic optimization mechanism also includes fixed rocking arm, one end of the fixed rocking arm and the slip-stream rudder
Second face is mutually fixed, and the other end is mutually fixed with one end of the connecting rod.
Wherein, it is described by connecting rod control when rotation rocking arm is rotated clockwise described in the slip-stream servo driving
Slip-stream rudder is rotated around the hinge towards the slip-stream steering wheel；Rotate counterclockwise when rocking arm is rotated described in the slip-stream servo driving
When, the slip-stream rudder is controlled by the connecting rod and is rotated away from the slip-stream steering wheel around the hinge；Or
When rotation rocking arm is rotated clockwise described in the slip-stream servo driving, the slip-stream rudder is controlled by the connecting rod
Rotate away from the slip-stream steering wheel around the hinge；When rotation rocking arm is rotated counterclockwise described in the slip-stream servo driving, lead to
Cross the connecting rod control slip-stream rudder to rotate towards the slip-stream steering wheel around the hinge.
Wherein, the multi-rotor aerocraft also includes multiple table support bars, and one end of each table support bar is and institute
The lower surface for stating fuselage is mutually fixed, and the other end is mutually fixed with the outer wall of the mounting platform, and each table support bar
Slip-stream steering wheel described in one is equipped with lateral wall, and is connected with slip-stream rudder described in corresponding by the hinge.
Wherein, the electronic rotor mechanism includes brshless DC motor and is installed on the brshless DC motor output shaft
Pose adjustment rotor.
Wherein, the multi-rotor aerocraft also includes two bracing frames, and the fuselage also includes first side and the second side
Face；Wherein,
Described two bracing frames are parallel to each other after being individually fixed in the first side and the second side, and each
Bracing frame axially extends respectively to both sides along the fuselage first side and formed outside the fuselage two for installing institute
State the installation position of brshless DC motor.
Wherein, each bracing frame is mutually fixed by screw with the fuselage.
Wherein, the fuselage also includes the 3rd side；Wherein, the fuselage thickness from the 3rd side along described
One side axis is gradually decreased away from the 3rd side surface direction motion, and the upper surface and lower surface of the fuselage are all formed as
Curved surface with certain radian, and the curved surface radian of the upper surface is more than the curved surface radian of the lower surface.
Wherein, the output shaft of the fuel engines is perpendicular with the central axis of the fuselage.
Implement the embodiment of the present invention, have the advantages that：
1st, in embodiments of the present invention, because multi-rotor aerocraft provides main flying power using fuel engines,
Therefore carry ability and the cruising time of multi-rotor aerocraft are considerably increased；
2nd, in embodiments of the present invention, because multi-rotor aerocraft is designed on the basis of fuel engines using slip-stream rudder,
It is so as to solve the anti-twisted problem produced when fuel engines works therefore simple with control, multi-rotor aerocraft is flown
The characteristics of performance impact is little；
3rd, in embodiments of the present invention, because multi-rotor aerocraft has setting angle difference using fuselage and rotor plane
Design, that is, design that there is fuselage thickness difference to change and upper and lower surface is the curved surface with different radians so that many rotors fly
Journey middle fuselage is flown over before row device in flat-hand position, there is less aerodynamic drag in cruise, while fuselage generation is certain
Aerodynamic lift, can effectively lift aircraft entirety cruising time and cruising speed；
4th, in embodiments of the present invention, because multi-rotor aerocraft is using oil electricity mixed design, occur in fuel engines
During failure, multi-rotor aerocraft still can be controlled by electronic rotor mechanism and is force-landed safely.
Description of the drawings
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
The accompanying drawing to be used needed for having technology description is briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, without having to pay creative labor, according to
These accompanying drawings obtain other accompanying drawings and still fall within scope of the invention.
Fig. 1 is aerodynamic optimization provided in an embodiment of the present invention oil electricity mixing multi-rotor aerocraft dimensional structure diagram；
Fig. 2 is the top perspective structural representation of Fig. 1；
Fig. 3 is A point partial enlarged drawings in Fig. 1；
Fig. 4 is B point partial enlarged drawings in Fig. 3；
Fig. 5 is the part plan structural representation of Fig. 2；
Fig. 6 is the signal of the aerodynamic optimization oil electricity mixing application scenarios of multi-rotor aerocraft one provided in an embodiment of the present invention
Figure；
Fig. 7 is the signal of aerodynamic optimization oil electricity mixing multi-rotor aerocraft Another Application scene provided in an embodiment of the present invention
Figure；
In figure：1- fuselages, 11- upper surfaces, 12- lower surfaces, the cavitys of 13- first, 14- first sides, 15- second sides,
The sides of 16- the 3rd, 2- undercarriages, 3- fuel engines, 4- mounting platforms, the cavitys of 41- second, 5- power rotors, the electronic rotations of 6-
Wing mechanism, 61- brshless DC motors, 62- pose adjustment rotors, 7- aerodynamic optimizations mechanism, 71- hinges, 72- slip-stream rudders, 721-
First face, the faces of 722- second, 73- connecting rods, 74- slip-stream steering wheels, 741- rotation rocking arms, 75- fixation rocking arms, 8- table support bars,
9- bracing frames, the installation position of 91- brshless DC motors.
Specific embodiment
To make the object, technical solutions and advantages of the present invention clearer, the present invention is made into one below in conjunction with accompanying drawing
Step ground is described in detail.
As shown in Figures 1 to 5, it is many rotor flyings of a kind of aerodynamic optimization oil electricity mixing of proposition in the embodiment of the present invention
Device, multi-rotor aerocraft includes：
One fuselage 1, fuselage 1 includes upper surface 11, lower surface 12 and through upper surface 11 and the first chamber of lower surface 12
Body 13；Wherein, fuselage 1 is formed using carbon fibre material processing and fabricating；
An at least undercarriage 2, undercarriage 2 is mutually fixed with the lower surface 12 of fuselage 1；
One fuel engines 3；
One is semi-enclosed and for installing the mounting platform 4 of fuel engines 3, mounting platform 4 and the phase of 1 lower surface of fuselage 12
Fixed, it is formed with opening the first cavity 13 of direction and the second cavity 41 being connected with the first cavity 13；
One driven by fuel engines 3 rotate and produce thrust realize multi-rotor aerocraft fly power rotor 5, power
Rotor 5 is arranged on the output shaft of fuel engines 3, and in the second cavity 41 or the first cavity 13；
At least one is used to receive the control signal of distal end first to adjust the electronic gyroplane of multi-rotor aerocraft flight attitude
Structure 6；And
At least one is used to receive the control signal of distal end second to eliminate aerodynamic optimization anti-twisted during multi-rotor aerocraft flight
Mechanism 7, aerodynamic optimization mechanism 7 is arranged on the outer wall of mounting platform 4.
It should be noted that fuselage 1 in should also be provided with flight control system, fuel oil box, throttle steering wheel, power supply unit,
For receiving the data transceiving unit and various sensors of Far end control signal so that multi-rotor aerocraft flight is used.First
Control signal and the second control signal will send into flight control system by data transceiving unit so that flight control system according to
Different control signals exports different control instructions, including fuel engines 3 starts or out code, electronic rotor mechanism 6
Speed adjust instruction, the startup of aerodynamic optimization mechanism 7, close and the instruction such as torsion direction change.
It should be noted that aerodynamic optimization mechanism 7 will be controlled according to the direction of rotation of power rotor 5 so that this is pneumatic excellent
Change mechanism 7 to be formed and the reverse torsion of power rotor 5, so as to reach anti-twisted purpose is eliminated, such as in the side counterclockwise of power rotor 5
When rotation, then control aerodynamic optimization mechanism 7 and form anticlockwise torsion.
It is understood that the output shaft of fuel engines 3 should be perpendicular with the central axis of fuselage 1 so that power revolves
The centerline axis parallel of the wing 5 and fuselage 1, so as to produce aerodynamic lift.In order to reduce air drag, install flat using semi-enclosed
Platform 4, can effectively lift aircraft entirety cruising time and cruising speed.
In embodiments of the present invention, aerodynamic optimization mechanism 7 includes hinge 71, slip-stream rudder 72, connecting rod 73 and slip-stream steering wheel
74；Wherein,
Hinge 71 at least one, one end of each hinge 71 is both secured on the outer wall of mounting platform 4, the other end with
First face 721 of slip-stream rudder 72 is mutually fixed；
Slip-stream rudder 72 can pass through being installed on the outer wall of mounting platform 4 of rotating of hinge 71, its second face 722 and connecting rod 73
One end mutually fix；
Slip-stream steering wheel 74 is fixed on the outer wall of mounting platform 4, and it includes the rotation rocking arm being connected with the other end of connecting rod 73
741；
When slip-stream steering wheel 74 drives rotates the rotation of rocking arm 741, slip-stream rudder 72 is controlled around the direction of hinge 71 by connecting rod 73
Or rotate away from slip-stream steering wheel 74.
Can be divided to two kinds of directions clockwise and anticlockwise, therefore slip-stream because slip-stream steering wheel 74 drives to rotate rocking arm 741 and rotate
The rotation direction of rudder 72 is also corresponding two kinds, specific as follows：
(1) when slip-stream steering wheel 74 drives rotation rocking arm 741 to rotate clockwise, slip-stream rudder 72 is controlled by connecting rod 73 and is wrapped
Page 71 is rotated towards slip-stream steering wheel 74；When slip-stream steering wheel 74 drives rotation rocking arm 741 to rotate counterclockwise, controlled by connecting rod 73
Slip-stream rudder 72 is rotated around hinge 71 away from slip-stream steering wheel 74；
(2) when slip-stream steering wheel 74 drives rotation rocking arm 741 to rotate clockwise, slip-stream rudder 72 is controlled by connecting rod 73 and is wrapped
Page 71 is rotated away from slip-stream steering wheel 74；When slip-stream steering wheel 74 drives rotation rocking arm 741 to rotate counterclockwise, controlled by connecting rod 73
Slip-stream rudder 72 is rotated around hinge 71 towards slip-stream steering wheel 74.
In order to strengthen the fixing connected between the second face 722 of slip-stream rudder 72 and connecting rod 73, therefore aerodynamic optimization mechanism 7
Also include that fixed rocking arm 75, one end of fixed rocking arm 75 are mutually fixed with the second face 722 of slip-stream rudder 72, the other end and connecting rod 73
One end is mutually fixed.
In one embodiment, hinge 71, slip-stream rudder 72, connecting rod 73, slip-stream steering wheel 74 and fixed rocking arm 75 all pass through
Glue is fixed.
The torsion that power rotor 5 is produced is eliminated in order to further improve, therefore multi-rotor aerocraft also includes multiple putting down
Platform support bar 8, one end of each table support bar 8 is mutually fixed with the lower surface 12 of fuselage 1, the other end with mounting platform 4
Outer wall mutually fix, and a slip-stream steering wheel 74 is equipped with the lateral wall of each table support bar 8, and by hinge 71 with it is corresponding
A slip-stream rudder 72 be connected, so that slip-stream rudder 72 is distributed on different platform support bar 8, increases the air of slip-stream rudder 72
Resistance.
The embodiment of the present invention, when fuel engines 3 breaks down, can still pass through electronic rotor using oil electricity mixed design
To control, multi-rotor aerocraft is safe to force-land for mechanism 6, therefore electronic rotor mechanism 6 includes brshless DC motor 61 and is installed on nothing
Pose adjustment rotor 62 on the output shaft of brushless motor 61, so that brushless dc is controlled by the first control signal
The rotating speed of the adjustment pose adjustment of machine 61 rotor 62, so as to reach the purpose that multi-rotor aerocraft force-lands safely.
Generally, multi-rotor aerocraft installs electronic rotor mechanism 6 using two bracing frames 9, and two bracing frames 9 are solid respectively
It is scheduled on two relative sides of fuselage 2 or end face, in symmetrical structure design, therefore multi-rotor aerocraft is also including two
Support 9, fuselage 1 also includes first side 14 and second side 15；Wherein, two bracing frames 9 are individually fixed in the first of fuselage 1
It is parallel to each other after on side 14 and second side 15, and each bracing frame 9 is axial respectively to both sides along 1 first side of fuselage 14
Extend and two installation positions 91 for being used to install brshless DC motor 61 are formed outside fuselage 1.Wherein, each bracing frame 9 leads to
Cross screw mutually to fix with fuselage 1.
In embodiments of the present invention, by the pneumatic design theory of introducing conventional aircraft, can be by the profile design of fuselage 1
Half elliptic is substantially presented, and using Fixed Wing AirVehicle wing configuration design, now fuselage 1 is also including the 3rd side 16；Its
In, the thickness of fuselage 1 is moved away from the direction of the 3rd side 16 along the axis of first side 14 from the 3rd side 16 and gradually decreased so that
Fuselage has thickness difference, and the upper surface 11 and lower surface 12 of fuselage 1 are all formed as the curved surface with certain radian, and upper surface
Curved surface radian of the 11 curved surface radian more than lower surface 12.In fuselage 1 and air relative motion, the air of upper surface 11 is flow through
The distance passed by within the same time is more remote than the distance for flowing through the air of lower surface 12, thus upper surface 11 air it is relative
Speed is faster than the air of lower surface 12, and understands " pressure and fluid that fluid is produced to the material of surrounding according to handkerchief slave profit theorem
Relative velocity be inversely proportional to ", therefore 1 upper surface of fuselage 11 produce pressure be less than 1 lower surface of fuselage 12 generation pressure, from
And fuselage 1 can be made to produce certain lift, and it is certain motor-driven to be able to ensure that multi-rotor aerocraft has in different directions
Ability, can improve the precision of spot hover.
The operation principle of aerodynamic optimization provided in an embodiment of the present invention oil electricity mixing multi-rotor aerocraft is：Many rotor flyings
(such as the arrow a directions of motion in Fig. 5) during device power 5 rotate counterclockwise of rotor, then multi-rotor aerocraft body can be made to produce up time
The torsion (such as the arrow b directions of motion in Fig. 5) in pin direction, in order to overcome this torsion to pass through flight control system to aerodynamic optimization machine
Structure 7 sends instruction, makes the control slip-stream of slip-stream steering wheel 74 rudder 72 unify to be deflected (such as the arrow b directions of motion in Fig. 5) to same direction,
So that air current flow direction produces deflection (such as the arrow b directions of motion in Fig. 5), then a corresponding opposite direction can be produced (such as
The arrow a directions of motion in Fig. 5) thrust；Now, counteracting multi-rotor aerocraft is reached by the opposite direction thrust of air-flow generation to move
The torsion purpose that power rotor 5 is produced；
During multi-rotor aerocraft landing, as shown in fig. 6, the rotating speed of adjustment pose adjustment rotor 61 is consistent, attitude is made
The Plane of rotation of rotor 61 and plane-parallel are adjusted, now multi-rotor aerocraft fuselage 1 keeps certain angle of attack, sent out by fuel oil
Motivation 3 drives the Spin Control multi-rotor aerocraft landing of power rotor 5；
During flying before multi-rotor aerocraft, as shown in fig. 7, pose adjustment of the adjustment away from the side 16 of fuselage 1 the 3rd
The rotating speed of rotor 61 is raised, and now, the lift produced by pose adjustment rotor 61 away from the 3rd side 16 is more than towards the 3rd side
Lift produced by the pose adjustment rotor 61 in face 16, so that multi-rotor aerocraft produces the trend bowed, by each
Individual pose adjustment rotor 61 produces the horizontal component of lift to make multi-rotor aerocraft forward flight.Due to multi-rotor aerocraft machine
The angle of attack of body 1 reduces, and the horizontal aerodynamic drag for making multi-rotor aerocraft direction of advance reduces so as in a forward direction with most
Excellent aeroperformance, while fuselage 1 can also produce certain lift to reach the lifting of multi-rotor aerocraft cruising speed；
In the same manner, correspondence multi-rotor aerocraft is retreated or journey is flown in side, flies over journey before its principle and multi-rotor aerocraft similar
Seemingly, here is not repeated one by one.
Implement the embodiment of the present invention, have the advantages that：
1st, in embodiments of the present invention, because multi-rotor aerocraft provides main flying power using fuel engines,
Therefore carry ability and the cruising time of multi-rotor aerocraft are considerably increased；
2nd, in embodiments of the present invention, because multi-rotor aerocraft is designed on the basis of fuel engines using slip-stream rudder,
It is so as to solve the anti-twisted problem produced when fuel engines works therefore simple with control, multi-rotor aerocraft is flown
The characteristics of performance impact is little；
3rd, in embodiments of the present invention, because multi-rotor aerocraft has setting angle difference using fuselage and rotor plane
Design, that is, design that there is fuselage thickness difference to change and upper and lower surface is the curved surface with different radians so that many rotors fly
Journey middle fuselage is flown over before row device in flat-hand position, there is less aerodynamic drag in cruise, while fuselage generation is certain
Aerodynamic lift, can effectively lift aircraft entirety cruising time and cruising speed；
4th, in embodiments of the present invention, because multi-rotor aerocraft is using oil electricity mixed design, occur in fuel engines
During failure, multi-rotor aerocraft still can be controlled by electronic rotor mechanism and is force-landed safely.
Above disclosed is only a kind of preferred embodiment of the invention, can not limit the power of the present invention with this certainly
Sharp scope, therefore the equivalent variations made according to the claims in the present invention, still belong to the scope that the present invention is covered.
Claims (9)
1. a kind of aerodynamic optimization oil electricity mixes multi-rotor aerocraft, it is characterised in that the multi-rotor aerocraft includes：
One fuselage (1), the fuselage (1) is including upper surface (11), lower surface (12) and through the upper surface (11) and institute
State first cavity (13) of lower surface (12)；
An at least undercarriage (2), the undercarriage (2) is mutually fixed with the fuselage (1) lower surface (12)；
One fuel engines (3)；
One is semi-enclosed and for installing the mounting platform (4) of the fuel engines (3), the mounting platform (4) with it is described
Fuselage (1) lower surface (12) is mutually fixed, its be formed with opening towards first cavity (13) and with first cavity (13)
The second cavity (41) being connected；
One is rotated by the fuel engines (3) driving and is produced the power rotor that thrust realizes the multi-rotor aerocraft flight
(5), the power rotor (5) is arranged on the output shaft of the fuel engines (3), and positioned at second cavity (41) or
In first cavity (13)；
At least one is used to receive the control signal of distal end first to adjust the electronic gyroplane of the multi-rotor aerocraft flight attitude
Structure (6)；And
At least one is used to receive the control signal of distal end second to eliminate aerodynamic optimization anti-twisted during the multi-rotor aerocraft flight
Mechanism (7), the aerodynamic optimization mechanism (7) is arranged on the outer wall of the mounting platform (4)；
Wherein, the aerodynamic optimization mechanism (7) includes hinge (71), slip-stream rudder (72), connecting rod (73) and slip-stream steering wheel (74)；
Wherein,
The hinge (71) at least one, one end of each hinge (71) is both secured on the outer wall of the mounting platform (4),
The other end is mutually fixed with first face (721) of the slip-stream rudder (72)；
The slip-stream rudder (72) can be installed on the mounting platform (4) outer wall by what the hinge (71) was rotated, and it second
Face (722) is mutually fixed with one end of the connecting rod (73)；
The slip-stream steering wheel (74) is fixed on the outer wall of the mounting platform (4), and it includes and the connecting rod (73) other end
Connected rotation rocking arm (741)；
When the slip-stream steering wheel (74) drives rotation rocking arm (741) to rotate, the cunning is controlled by the connecting rod (73)
Stream rudder (72) is rotated around the hinge (71) toward and away from the slip-stream steering wheel (74).
2. multi-rotor aerocraft as claimed in claim 1, it is characterised in that the aerodynamic optimization mechanism (7) also includes fixing
Rocking arm (75), one end of the fixed rocking arm (75) are mutually fixed with second face (722) of the slip-stream rudder (72), the other end and institute
The one end for stating connecting rod (73) is mutually fixed.
3. multi-rotor aerocraft as claimed in claim 2, it is characterised in that when the slip-stream steering wheel (74) drives the rotation
When rocking arm (741) is rotated clockwise, the slip-stream rudder (72) is controlled around the hinge (71) towards institute by the connecting rod (73)
State slip-stream steering wheel (74) rotation；When the slip-stream steering wheel (74) drives rotation rocking arm (741) to rotate counterclockwise, by institute
State connecting rod (73) the control slip-stream rudder (72) to rotate away from the slip-stream steering wheel (74) around the hinge (71)；Or
When the slip-stream steering wheel (74) drives rotation rocking arm (741) to rotate clockwise, controlled by the connecting rod (73)
The slip-stream rudder (72) rotates around the hinge (71) away from the slip-stream steering wheel (74)；When the slip-stream steering wheel (74) drives institute
Rotation rocking arm (741) is stated when rotating counterclockwise, the slip-stream rudder (72) is controlled around the hinge (71) by the connecting rod (73)
Rotate towards the slip-stream steering wheel (74).
4. multi-rotor aerocraft as claimed in claim 3, it is characterised in that the multi-rotor aerocraft also includes multiple platforms
Support bar (8), one end of each table support bar (8) is mutually fixed with the lower surface (12) of the fuselage (1), the other end with
The outer wall of the mounting platform (4) is mutually fixed, and is equipped with slip-stream rudder described on each table support bar (8) lateral wall
Machine (74), and be connected with slip-stream rudder (72) described in corresponding by the hinge (71).
5. multi-rotor aerocraft as claimed in claim 4, it is characterised in that the electronic rotor mechanism (6) is including brushless straight
Stream motor (61) and the pose adjustment rotor (62) being installed on the brshless DC motor (61) output shaft.
6. multi-rotor aerocraft as claimed in claim 5, it is characterised in that the multi-rotor aerocraft is also including two supports
Frame (9), the fuselage (1) also includes first side (14) and second side (15)；Wherein,
Described two bracing frames (9) are mutually flat after being individually fixed in the first side (14) and the second side (15)
OK, and each bracing frame (9) axially extends the fuselage (1) to both sides respectively along the fuselage (1) first side (14)
Outside form two and be used to that the installation positions (91) of the brshless DC motor (61) to be installed.
7. multi-rotor aerocraft as claimed in claim 6, it is characterised in that each bracing frame (9) by screw with
The fuselage (1) is mutually fixed.
8. multi-rotor aerocraft as claimed in claim 7, it is characterised in that the fuselage (1) also includes the 3rd side (16)；
Wherein, fuselage (1) thickness deviates from the 3rd side from the 3rd side (16) along the first side (14) axis
The motion of face (16) direction is gradually decreased, and the upper surface (11) and lower surface (12) of the fuselage (1) is all formed as with certain
The curved surface of radian, and the curved surface radian of the upper surface (11) is more than the curved surface radian of the lower surface (12).
9. multi-rotor aerocraft as claimed in claim 8, it is characterised in that the output shaft of the fuel engines (3) and institute
The central axis for stating fuselage (1) is perpendicular.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510250011.XA CN104859859B (en) | 2015-05-18 | 2015-05-18 | Aerodynamic optimization hybrid multirotor |
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| CN105129079B (en) * | 2015-09-29 | 2017-08-25 | 郝建新 | A kind of long endurance Multi-axis aircraft of hybrid power |
| CN105539828A (en) * | 2015-12-08 | 2016-05-04 | 陈蜀乔 | Petrol-electric hybrid multi-rotor aerial vehicle capable of self electricity generation |
| CN206900666U (en) * | 2017-06-19 | 2018-01-19 | 张万民 | A kind of oil electric mixed dynamic multiaxis rotary wind type unmanned plane |
| CN110654534A (en) * | 2018-06-29 | 2020-01-07 | 中光电智能机器人股份有限公司 | Rotorcraft |
| CN108773481A (en) * | 2018-07-02 | 2018-11-09 | 广州天翔航空科技有限公司 | Electronic Manned Flying System |
| CN109466756A (en) * | 2018-12-06 | 2019-03-15 | 酷黑科技（北京）有限公司 | A kind of multi-rotor aerocraft |
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| CN103359284A (en) * | 2013-06-29 | 2013-10-23 | 天津大学 | Petrol-electric hybrid four-rotor unmanned aerial vehicle |
| CN203714176U (en) * | 2014-02-10 | 2014-07-16 | 安徽省华云高科技有限责任公司 | Hybrid power multi-rotor type aircraft |
| CN104260875B (en) * | 2014-09-19 | 2016-05-04 | 苏州天益航空科技有限公司 | The resistance to crash feature of agricultural plant protection unmanned plane |
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