CN106314787A - Aircraft - Google Patents
Aircraft Download PDFInfo
- Publication number
- CN106314787A CN106314787A CN201610811579.9A CN201610811579A CN106314787A CN 106314787 A CN106314787 A CN 106314787A CN 201610811579 A CN201610811579 A CN 201610811579A CN 106314787 A CN106314787 A CN 106314787A
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- CN
- China
- Prior art keywords
- aircraft
- propeller
- metaplasm
- pair
- rudder
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8227—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising more than one rotor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8236—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft including pusher propellers
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention provides an aircraft which comprises an aircraft body, a main rotor device and a plurality of auxiliary propeller devices. The main rotor device is mounted on the aircraft body and is used for generating vertical thrust, the auxiliary propeller devices are mounted on the periphery of the aircraft body and are used for generating transverse thrust, and a plurality of pairs of aircraft turning screw propellers and a plurality of pairs of aircraft translation screw propellers are formed by the multiple auxiliary propeller devices. The aircraft has the advantages that the aircraft can be turned by the corresponding paired screw propellers formed by the multiple corresponding auxiliary propeller devices and can be subjected to translation by the corresponding paired screw propellers formed by the multiple corresponding auxiliary propeller devices, accordingly, the aircraft body can be prevented from being inclined when turning or translation actions are carried out by the aircraft, and the aircraft can assuredly stably fly; the aircraft can quickly respond to turning and translation instructions and accordingly can be flexibly and quickly controlled.
Description
Technical field
The present embodiments relate to technical field of aerospace, particularly relate to a kind of aircraft.
Background technology
Along with the development of science and technology, it is more and more extensive that multi-rotor aerocraft is applied in industry-by-industry field, therefore suffers from
Consumers in general and the favor of enterprise.Multi-rotor aerocraft structure includes four or multiple rotor being horizontally mounted, multiple biography
Sensor and control system composition.
Owing to the rotor of Multi-axis aircraft currently on the market is all horizontally mounted, so in order to realize the flat of aircraft
Move, be merely able to, by controlling the speed difference between rotor, complete the change of attitude.Such as, forward, backward, to the left, to the right
Movement and rotate clockwise and counterclockwise around axis body.But this change by controlling the speed difference between rotor
Flight attitude method makes the aircraft can not smooth flight.Such as, for quadrotor, when controlling aircraft
Need to increase the rotating speed of two rotors on the right of aircraft to the left during flight, reduce the rotating speed of two rotors in the left side.Due to four
Rotor be all be horizontally mounted so necessarily causing whole aircraft that left low right high inclination occurs, cause the rolling of whole fuselage
Dynamic.
On the one hand, rock that to cause aircraft be to be accomplished by the The Cloud Terrace that configuration requirement is high for carrying out taking photo by plane due to fuselage
Keep the steady of camera head, to ensure the quality of shooting picture.So necessarily increase configuration high-performance The Cloud Terrace to be carried
The expense come.
On the other hand, if needing to realize to realize rapidly moving to left of aircraft to be accomplished by increasing about aircraft two
The rotating speed difference of the rotor on limit, and the biggest inclination that aircraft generation will be caused bigger of rotating speed difference.Excessive inclination will be led
Cause aircraft out of hand (because control system is the detection knot of the gyroscope by the state of flight for sense aircraft
Fruit controls the safe flight of aircraft, and the range of gyroscope is limited, so being tilted beyond gyro when aircraft
During the range of instrument, control system is by losing the control to aircraft, causes potential safety hazard).Therefore, in order to ensure the safety of flight
Property, aircraft of the prior art can not respond the course changing control to aircraft timely.
Summary of the invention
The embodiment of the present invention provides a kind of aircraft, can not put down in order at least to solve the aircraft in above-mentioned technical problem
The technical problem of steady flight.
In certain embodiments, the aircraft that the present invention provides includes: aircraft body, is arranged on described aircraft body
On for produce the main rotor device of vertical thrust and be arranged on around described aircraft body for producing lateral thrust
Multiple metaplasm devices, the plurality of metaplasm device is formed with the multipair propeller turned to for aircraft and multipair for flying
The propeller of device translation.
The aircraft of the present embodiment is provided by main rotor device and promotes power to realize lifting, by being arranged on aircraft
Multiple metaplasm devices around main body provide the power of horizontal direction to realize turning to or moving horizontally of aircraft.Due to this
Embodiment is that the paired propeller formed by multiple metaplasm devices realizes turning to and translating of aircraft, so this reality
Execute the aircraft of example realizing turning to or do not have during translation motion the inclination of fuselage, thus ensure that the steady of aircraft
Flight.Simultaneously as be special metaplasm device to control turning to and moving horizontally of aircraft, so the flying of the present embodiment
Row device can respond rapidly and turns to and translate instruction so that the control to aircraft is rapid more flexibly.
In certain embodiments, the multipair propeller turned to for aircraft at least include a pair clockwise for aircraft
The propeller turned to and the propeller turned to counterclockwise for aircraft for a pair；
A pair of propeller in the propeller that aircraft turns to clockwise with the pair of for flying
The described propeller for aircraft translation in a pair of a propeller shape in the propeller that device turns to counterclockwise.
By the propeller that turns to will be used for and be used for the propeller of translation and be set at least include one in the present embodiment
The structure of public propeller has been reduced to minimum by being used for realizing the propeller that aircraft turns to and translate, thus simplifies and fly
The structure of row device, alleviates the overall weight of aircraft.On the other hand, during realizing aircraft is turned to and translated
Decrease the quantity of the propeller needing control, reduce the process to data volume, thus simplify the control to aircraft.
In certain embodiments, multiple metaplasm devices along the surrounding of described aircraft body according to the uniform cloth of predetermined space
Put.The multiple metaplasm devices being evenly arranged according to predetermined space in the present embodiment make whole aircraft that weight can be kept to distribute
On equilibrium, beneficially aircraft smooth flight.
In certain embodiments, the surrounding along described aircraft body has been evenly arranged multiple battery peace according to predetermined space
Dress seat；The adjacent metaplasm device of each two in wherein said multiple metaplasm device is both with respect at least one battery mounting base pair
Claim the left and right sides being arranged at least one battery mounting base described.
The structure of the surrounding that battery mounting base is evenly distributed in the present embodiment aircraft body makes that installs to own
Between battery mutually isolated, be conducive to quickly heat produced by battery in work process is distributed, it is to avoid heat production collection
In to the damage of battery and the damage to overall aircraft.
In certain embodiments, also include being arranged in described aircraft body the arrow being positioned at below described main rotor device
Amount rudder；Described vector rudder can rotate to change the area towards described main rotor device.
In certain embodiments, vector rudder includes:
Steering wheel and the multiple rudder blades being connected with described steering wheel, described rudder blade is the ring-type section bar of class isosceles trapezoid, described
Four angles of ring-type section bar are rounding off.
Vector rudder in the present embodiment can realize aircraft when the metaplasm device of aircraft breaks down for auxiliary
Turn to and translate, to ensure still to be capable of safe flight and the control of aircraft in the case of metaplasm device breaks down
System, adds the safety coefficient of aircraft.
In certain embodiments, metaplasm device include for connect two adjacent described battery mounting bases along first party
To extend the first linking arm,
Along be different from described first direction second direction extend the second linking arm, one end of described second linking arm with
Described first linking arm connects, and the other end is provided with the motor for driving propeller.By two along different in the present embodiment
The linking arm in direction will be used for the structure driving the motor of propeller to be arranged in aircraft body
In certain embodiments, the other end of described second linking arm is provided with two fork of class V-arrangement, in described two fork
First fork and second fork be separately installed with the first motor and the second motor for driving propeller.
In certain embodiments, propeller is coaxial double oar.
In certain embodiments, main rotor device is coaxial double-rotary wing.
In certain embodiments, the camera head being arranged in described aircraft body is also included.
In certain embodiments, aircraft body is to be formed with the ring-shaped frame of hollow space；Described main rotor device is pacified
It is contained in the described hollow centre of described ring-shaped frame.
In certain embodiments, ring-shaped frame includes the lower supporting mechanism of supporting mechanism in annular, annular and multiple battery holder；
One end of the plurality of battery holder is fixed in described annular on supporting mechanism, and the other end is fixed on supporting mechanism under described annular
On；The plurality of battery holder is uniformly distributed around described ring-shaped frame.
The present invention is a kind of aircraft being different from existing product, its simple in construction, and flight stability is safe and reliable.It
It is different from existing product in structure, mainly provides main rotor device and the vector rudder below of power, position by being positioned at center
In body surrounding from angled multiple metaplasm devices.Realize the method that aircraft redundance controls, no matter take off, landing,
Cruise can keep horizontal attitude.It is that the rotating speed of multiple metaplasm devices by being positioned at main body surrounding changes during translation
Become, make aircraft generation position change, the most also can be by tilting the vector rudder below main rotor device, change of flight device side
To.
Accompanying drawing explanation
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
In having technology to describe, the required accompanying drawing used is briefly described, it should be apparent that, the accompanying drawing in describing below is this
Some bright embodiments, for those of ordinary skill in the art, on the premise of not paying creative work, it is also possible to root
Other accompanying drawing is obtained according to these accompanying drawings.
Fig. 1 is the structural representation of an embodiment of aircraft of the present invention；
Fig. 2 is the structural representation of an embodiment of the annular frame being mounted with main rotor device of aircraft of the present invention
Figure；
Fig. 3 is the structural representation of an embodiment of the metaplasm device of aircraft of the present invention；
Fig. 4 is the structural representation of an embodiment of the mounting means of the vector rudder of aircraft of the present invention；
Fig. 5 is the structural representation of an embodiment of the vector rudder of aircraft of the present invention；
Fig. 6 is the top view of an embodiment of aircraft of the present invention.
Detailed description of the invention
For making the purpose of the embodiment of the present invention, technical scheme and advantage clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is
The a part of embodiment of the present invention rather than whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art
The every other embodiment obtained under not making creative work premise, broadly falls into the scope of protection of the invention.
It should be noted that in the case of not conflicting, the embodiment in the present invention and the feature in embodiment can phases
Combination mutually.Describe the present invention below with reference to the accompanying drawings and in conjunction with the embodiments in detail.
As it is shown in figure 1, the embodiment of the present invention provides a kind of aircraft, described aircraft includes:
Aircraft body 1；
The main rotor device 2 for producing vertical thrust being arranged in described aircraft body 1；Fly described in being arranged on
The multiple metaplasm devices 3 for producing lateral thrust around row device main body 1, the plurality of metaplasm device 3 is formed with multipair use
The propeller turned in aircraft and the multipair propeller for aircraft translation.
The flying instrument of the present embodiment is provided with promoting power to realize the main rotor device 2 of lifting and to be arranged on aircraft
The power of the offer horizontal direction around main body is to realize the multiple metaplasm devices 3 turning to or moving horizontally of aircraft.By
It is that the paired propeller formed by multiple metaplasm devices 3 realizes turning to and translating of aircraft, institute in the present embodiment
With the aircraft of the present embodiment realizing turning to or do not have during translation motion the inclination of fuselage, thus ensure that aircraft
Smooth flight.Simultaneously as be special metaplasm device to control turning to and moving horizontally of aircraft, so this enforcement
The aircraft of example can respond rapidly and turns to and translate instruction so that the control to aircraft is rapid more flexibly.
In certain embodiments, the described multipair propeller turned to for aircraft at least include a pair suitable for aircraft
Propeller that hour hands turn to and the propeller turned to counterclockwise for aircraft for a pair；
A pair of propeller in the propeller that aircraft turns to clockwise with the pair of for flying
The described propeller for aircraft translation in a pair of a propeller shape in the propeller that device turns to counterclockwise.
By the propeller that turns to will be used for and be used for the propeller of translation and be set at least include one in the present embodiment
The structure of public propeller has been reduced to minimum by being used for realizing the propeller that aircraft turns to and translate, thus simplifies and fly
The structure of row device, alleviates the overall weight of aircraft.On the other hand, during realizing aircraft is turned to and translated
Decrease the quantity of the propeller needing control, reduce the process to data volume, thus simplify the control to aircraft.
Aircraft body 1 in embodiment shown in Fig. 1 is to be formed with the ring-shaped frame 1 of hollow space, and main rotor
Device is mounted in the hollow space of described ring-shaped frame 1.But it is ring that the aircraft of the present invention is not limited to aircraft body
The aircraft of shape framework, aircraft body can be arbitrary shape, and main rotor device can be mounted in aircraft body
Either above or below.In order to more clearly highlight the inventive point of the present invention, below with aircraft body as ring frame
The embodiment of frame describes in detail.Annular frame 1 in the present embodiment can be annular can also be regular polygon
Ring-type (such as, regular pentagon, regular hexagon etc.).The aircraft of embodiment illustrated in fig. 1 also includes being arranged on annular frame
Fly control installation base plate 5, described in fly control installation base plate 5 for carrying fly control device 7.
In certain embodiments, ring-shaped frame 1 includes the lower supporting mechanism of supporting mechanism in annular, annular and multiple battery
Seat；One end of the plurality of battery holder is fixed in described annular on supporting mechanism, and the other end is fixed under described annular support
In mechanism；The plurality of battery holder is uniformly distributed around described ring-shaped frame.
Annular frame 1 in embodiment includes multiple battery holder 11, polylith annular base plate 12 and multiple substrate as shown in Figure 2
Connector 13.In the present embodiment, annular base plate 12 1 has four pieces, and every two pieces of annular base plate 12 and multiple substrate connector 13 are altogether
With constituting supporting mechanism (supporting mechanism under supporting mechanism and annular in annular).Two supporting mechanisms of the present embodiment are relative
Arrange, and substrate connector 13 position included in two supporting mechanisms is relative.One end of battery holder 11 is fixed on one
On the substrate connector 13 of supporting mechanism, the other end of battery holder 11 is fixed on the substrate connector 13 of another supporting mechanism
On, the most multiple battery holders 11, polylith annular base plate 12 and multiple substrate connector 13 just together constitute annular frame.First
Annular base plate 12, substrate connector 13 and battery holder 11 are all to be fixed by screw, each battery holder 11 of vertical direction be by
Upper and lower two screws become rigid body to be connected with annular base plate 12 and substrate connector 13, they are become by three screws the most again
Rigid body connects, and thus constitutes the three-legged structure enhanced stability of local.Annular frame in the present embodiment farthest subtracts
The light weight of self, thus ensure that and can obtain more long continuation of the journey when aircraft.Additionally, the ring frame in the present embodiment
Frame can also is that integrated, which reduces the existence connecting space between scattered connection member, it is to avoid fly
The damage that whole body is caused by the resonance being likely to result in during row, eventually affects the safety of flight.
Also including in embodiment illustrated in fig. 2 that main rotor device, described main rotor device 2 include main rotor 21, motor is installed
Seat 22 and multiple arm bar 23.Wherein main rotor device 2 is arranged in annular frame by multiple arm bars 23.Arm bar
The quantity of 23 is identical with the quantity of battery holder 11, and one end of multiple arm bar 23 is fixed on motor mount 22, another
End is fixedly mounted on battery holder 11.Multiple arm bars 23 are evenly distributed on motor mount 22 around.
The mounting means of main rotor device 2 is by the arm of force identical for four thickness length by upper and lower two motor mounts 22
Bar about 23 is clamped, then is fixed into rigid body by screw and glue, then this structure is being rigidly connected with battery holder 11.When
When main rotor 21 rotates, produced lift is sent to battery holder 11 by arm bar 23, and such battery holder 11 just becomes the main force
Bearing member.
In certain embodiments, main rotor device 2 is coaxial double-rotary wing.By providing lift by being used in the present embodiment
Power set are set to coaxial double-rotary wing and counteract the torsion that aircraft body is caused by main rotor device, thus avoid aircraft
Main body is with the rotation of main rotor device.
In certain embodiments, metaplasm device includes
For connecting first linking arm extended in a first direction of two adjacent described battery mounting bases, and
Along be different from described first direction second direction extend the second linking arm, one end of described second linking arm with
Described first linking arm connects, and the other end is provided with the motor for driving propeller.
The most in certain embodiments, metaplasm device 3 includes propeller 31, motor 32, motor mount 33, machine
Armed lever 34 (i.e., the second linking arm), mounting seat 35, it is transversely mounted bar 36 (i.e., the first linking arm).Propeller 31 with motor 32 is
Being screwed, motor mount 33 has the installing hole of corresponding motor 32 to be also that screw is fixed with motor 32.Motor mount
33 with horn bar 34 and horn bar 34 and mounting seat 35 be all after grafting fixing dead with glue, this mounting means simple and fast,
Mounting seat 35 is screwed with being transversely mounted bar 36, is transversely mounted bar 36 for the screw thread with two adjacent battery holder sidewalls
Hole carries out screw and fixes.
In certain embodiments, the other end of described second linking arm is provided with two fork of class V-arrangement, in described two fork
First fork and second fork be separately installed with the first motor and the second motor for driving propeller.
Propeller in any of the above-described embodiment is single screw or coaxial double oar.
As shown in Figure 4, aircraft also includes being arranged on the protective cover 6 bottom described annular frame 1 in certain embodiments.
By outside foreign material, (such as, earth's surface is not convex for protecting the main rotor device 2 within annular frame 1 for protective cover 6 in the present embodiment
Rise, in-flight by branch during trunk) damage, thus ensure that the safe flight of aircraft, extend service life, fall
The low cost that aircraft is safeguarded.
As shown in Figure 1 and Figure 4, aircraft also includes being arranged in described annular frame 1 with described in certain embodiments
The vector rudder 4 that main rotor device 2 is relative, described vector rudder 4 is positioned at the blowing direction side of described main rotor device 2；Described arrow
Amount rudder 4 can rotate to change the area towards described main rotor device 2.
As shown in Figure 4, vector rudder 4 includes: multiple rudder blades (such as, first rudder blade the 41, second rudder blade the 42, the 3rd rudder blade 43,
4th rudder blade 44) and include the mounting seat 45 for controlling the steering wheel that the plurality of rudder blade rotates, the center of described protective cover 6
Position is provided with fixing seat 61；Wherein, the plurality of rudder blade is connected with described steering wheel by linking arm respectively；Described vector rudder 4
It is arranged on described fixing seat 61 by described mounting seat.Multiple rudder blades are formed with the multipair rudder blade turned to for aircraft with many
To the rudder blade translated for aircraft.Described rudder blade is at least ring-type or tabular.
The present embodiment is by increasing vector rudder 4, it is ensured that the metaplasm device 3 at aircraft breaks down and cannot complete normally
Aerial mission in the case of control vector rudder 4 and proceed to fly normally or at least can be controlled by vector rudder 4
Aircraft adjustment direction safety return.Additionally, the vector rudder 4 in the present embodiment can be additionally used in counteracting main rotor device 2 to ring
The torsion that shape framework 1 causes, thus avoid annular frame 1 with the rotation of main rotor device 2.
In certain embodiments, the multipair rudder blade turned to for aircraft at least includes a pair turning clockwise for aircraft
To rudder blade and the rudder blade that turns to counterclockwise for aircraft for a pair；
A pair of rudder blade in the rudder blade that aircraft turns to clockwise is inverse for aircraft with the pair of
A rudder blade in the rudder blade that hour hands turn to forms a pair rudder blade for aircraft translation.
With reference to Fig. 4, Fig. 5, rudder blade 41 is the ring-type section bar of class isosceles trapezoid, and four angles of described ring-type section bar are round and smooth mistake
Cross.Described annular section bar is formed in one.Or rudder blade 41 be shaped as by the round and smooth bending of two panels first connection panel 411,
Second connection panel 412, two panels central plane plate 413, upper bottom surface plate 414 and the panel 415 of going to the bottom of the round and smooth bending of two panels enclose and form
Class isosceles trapezoid；Upper bottom surface plate 414 is for being connected with described aircraft body, and the two ends of described upper bottom surface plate 414 lead to respectively
Cross a piece of first connect panel 411 be connected with one end of described two panels central plane plate 413, described in go to the bottom panel 415 two ends distinguish
Connect panel 412 by a piece of second to be connected with the other end of described two panels central plane plate 413.The present embodiment sets the first rudder blade
41 and second parts between rudder blade 42 are the front of aircraft.The first rudder blade 41 and the 3rd rudder blade 43 in the present embodiment are a pair
The rudder blade turned to clockwise and/or counterclockwise for aircraft.The second rudder blade 42 and the 4th rudder blade 44 in the present embodiment are one
To the rudder blade turned to clockwise and/or counterclockwise for aircraft.First rudder blade 41 and the second rudder blade 42 be a pair for flying
The rudder blade that device moves horizontally backward, the 3rd rudder blade 43 and the 4th rudder blade 44 are the rudder moved for aircraft forward horizontal for a pair
Leaf, the first rudder blade 41 and the 4th rudder blade 44 are the rudder blade moved horizontally to the left for aircraft for a pair, the second rudder blade 42 and the 3rd
Rudder blade 43 is the rudder blade moved horizontally to the right for aircraft for a pair.
In certain embodiments, control aircraft by vector rudder and carry out different directions translation and the method that turns to is:
When aircraft is to right translation, flies to control device and control: the second rudder blade 42 rotates clockwise certain angle, the 3rd rudder blade
43 rotate counterclockwise certain angle, and the first rudder blade 41 rotates clockwise certain angle, and the 4th rudder blade 44 rotates counterclockwise certain angle
Degree, such aircraft just can level move right.Or control overall vector rudder to be tilted to the right.
When aircraft is to left, flies to control device and control: the second rudder blade 42 rotates counterclockwise certain angle, the 3rd rudder blade
43 rotate clockwise certain angle, and the first rudder blade 41 rotates counterclockwise certain angle, and the 4th rudder blade 44 rotates clockwise certain angle
Degree, such aircraft just can level be moved to the left.Or control overall vector rudder to be tilted to the left.
When aircraft translates forward, fly to control device and control: the 3rd rudder blade 43 rotates clockwise certain angle, the 4th rudder blade
44 rotate counterclockwise certain angle, and the first rudder blade 41 rotates counterclockwise certain angle, and the second rudder blade 42 rotates clockwise certain angle
Degree, such aircraft just can be with horizontal forward movement.Or control overall vector rudder to turn forward.
When aircraft translates backward, fly to control device and control: the 3rd rudder blade 43 rotates counterclockwise certain angle, the 4th rudder blade
44 rotate clockwise certain angle, and the first rudder blade 41 rotates clockwise certain angle, and the second rudder blade 42 rotates counterclockwise certain angle
Degree, such aircraft just can level be moved rearwards by.Or control overall vector rudder to tilt backwards.
When aircraft is around axle time rotational counterclockwise, fly to control device and control: first rudder blade the 41, the 3rd rudder blade the 43, second rudder blade
42 and the 4th rudder blade 44 rotate counterclockwise certain angle, such aircraft just can rotate around axle counterclockwise.
When aircraft is around axle time rotational clockwise, fly to control device and control: first rudder blade the 41, the 3rd rudder blade the 43, second rudder blade
42 and the 4th rudder blade 44 rotate clockwise certain angle, aircraft just can turn clockwise around axle.
In certain embodiments, the multipair propeller turned to for aircraft at least include a pair clockwise for aircraft
The propeller turned to and the propeller turned to counterclockwise for aircraft for a pair；
A pair of propeller in the propeller that aircraft turns to clockwise with the pair of for flying
A propeller shape in the propeller that device turns to counterclockwise is in a pair for the propeller of aircraft translation.
In certain embodiments, it is also possible to tilt to control aircraft to phase to any direction by controlling overall vector rudder
Corresponding and incline direction flies.Fly i.e., it is possible to realize aircraft by vector rudder in the translation of 360 degree of any directions.
Fig. 6 is the top view of one embodiment of aircraft of the present invention.Figure shows first to fourth metaplasm device.This reality
Executing and setting part between the first metaplasm device 21 and the second metaplasm device 22 in example is the front of aircraft.In the present embodiment
One metaplasm device 21 and the 3rd metaplasm device 23 are metaplasm device (corresponding a pair turned to clockwise for aircraft for a pair
Propeller is a pair propeller turned to clockwise for aircraft).The second metaplasm device 22 and fourth officer in the present embodiment
Oar device 24 be a pair metaplasm device turned to counterclockwise for aircraft (a pair corresponding propeller be a pair for flying
The propeller that device turns to clockwise).First metaplasm device 21 and the second metaplasm device 22 be a pair for aircraft level backward
The metaplasm device of movement, the 3rd metaplasm device 23 and the 4th metaplasm device 24 are the pair moved for aircraft forward horizontal for a pair
Oar device, the first metaplasm device 21 and the 4th metaplasm device 24 are the metaplasm device moved horizontally to the right for aircraft for a pair,
Second metaplasm device 22 and the 3rd metaplasm device 23 are the metaplasm device moved horizontally to the left for aircraft for a pair.
In certain embodiments, control aircraft by metaplasm device and carry out different directions translation and the method turned to
For:
When aircraft is to right translation, flies to control device and improve the first metaplasm device 21 and rotating speed of the 4th metaplasm device 24,
Reducing the second metaplasm device 22 and rotating speed of the 3rd metaplasm device 23, such aircraft just can level move right.
When aircraft is to left, controller improves the second metaplasm device 22 and rotating speed of the 3rd metaplasm device 23, fall
Low first metaplasm device 21 and the rotating speed of the 4th metaplasm device 24, such aircraft just can level be moved to the left.
When aircraft translates forward, controller improves the 3rd metaplasm device 23 and the rotating speed of the 4th metaplasm device 24, fall
Low first metaplasm device 21 and the speed of the second metaplasm device 22, aircraft just can be with horizontal forward movement.
When aircraft translates backward, controller improves the first metaplasm device 21 and rotating speed of the second metaplasm device 22, fall
Low 3rd metaplasm device 23 and the rotating speed of the 4th metaplasm device 24, aircraft just can level be moved rearwards by.
When aircraft is around axle time rotational counterclockwise, controller improves turning of the second metaplasm device 22 and the 4th metaplasm device 24
Speed, reduces the first metaplasm device 21 and rotating speed of the 3rd metaplasm device 23, and aircraft just can rotate around axle counterclockwise.
When aircraft is around axle time rotational clockwise, controller improves turning of the first metaplasm device 21 and the 3rd metaplasm device 23
Speed, reduces the second metaplasm device 22 and rotating speed of the 4th metaplasm device 24, and aircraft just can turn clockwise around axle.
As shown in Figure 6, the most multiple metaplasm devices along the surrounding of described ring-shaped frame according to predetermined space
Being evenly arranged, the installation direction of each of which metaplasm device is all so that the direction that propeller level is dried, and propeller
Blowing direction tangent with the concentric circular of annular frame.The present embodiment achieves turning to of aircraft by minimum metaplasm device
With move horizontally, simplify the structure of aircraft, reduce the production cost of aircraft.
In certain embodiments, the surrounding along described ring-shaped frame has been evenly arranged the installation of multiple battery according to predetermined space
Seat；The metaplasm device that each two in wherein said multiple metaplasm device is adjacent is symmetrical both with respect at least one battery mounting base
Arrange.By battery mounting base in the present embodiment and the reasonable Arrangement of metaplasm device so that whole aircraft counterweight is symmetrical, thus
Ensure that the smooth flight of aircraft.
In certain embodiments, aircraft also includes the camera head being arranged in described aircraft body.The present embodiment
In camera head can be arranged on inside or around or the optional position such as top or bottom of aircraft body.This reality
Executing the camera head in example and be can be common high definition or non-high definition camera device or VR camera head.The present embodiment
Aircraft is due to can be with smooth flight, it is possible to just can shoot in the case of the The Cloud Terrace configuring low precision low cost
High-quality video pictures, thus reduce the cost overhead of configuration high accuracy The Cloud Terrace.
Last it is noted that above example is only in order to illustrate technical scheme, it is not intended to limit；Although
With reference to previous embodiment, the present invention is described in detail, it will be understood by those within the art that: it still may be used
So that the technical scheme described in foregoing embodiments to be modified, or wherein portion of techniques feature is carried out equivalent；
And these amendment or replace, do not make appropriate technical solution essence depart from various embodiments of the present invention technical scheme spirit and
Scope.
Claims (10)
1. an aircraft, including:
Aircraft body；
The main rotor device for producing vertical thrust being arranged in described aircraft body；With
The multiple metaplasm devices for producing lateral thrust being arranged on around described aircraft body, the plurality of metaplasm device
It is formed with the multipair propeller turned to for aircraft and the multipair propeller for aircraft translation.
Aircraft the most according to claim 1, it is characterised in that the described multipair propeller turned to for aircraft is at least
Including the propeller turned to clockwise for aircraft for a pair and the propeller turned to counterclockwise for aircraft for a pair；
A pair of propeller in the propeller that aircraft turns to clockwise is inverse for aircraft with the pair of
The described propeller for aircraft translation in a pair of a propeller shape in the propeller that hour hands turn to.
Aircraft the most according to claim 1, it is characterised in that the plurality of metaplasm device is along described aircraft body
Around it is evenly arranged according to predetermined space.
Aircraft the most according to claim 1, it is characterised in that along the surrounding of described aircraft body according to predetermined space
It is evenly arranged multiple battery mounting base；The adjacent metaplasm device of each two in wherein said multiple metaplasm device both with respect to
At least one battery mounting base is arranged symmetrically in the left and right sides of at least one battery mounting base described.
Aircraft the most according to claim 1, it is characterised in that described aircraft also includes being arranged on described aircraft master
It is positioned at the vector rudder below described main rotor device on body.
Aircraft the most according to claim 5, it is characterised in that described vector rudder includes steering wheel and is connected with described steering wheel
The multiple rudder blades connect, described rudder blade is the ring-type section bar of class isosceles trapezoid, and four angles of described ring-type section bar are rounding off.
Aircraft the most according to claim 4, it is characterised in that each metaplasm device includes:
For connecting first linking arm extended in a first direction of two adjacent described battery mounting bases, and
The second linking arm extended along the second direction being different from described first direction, one end of described second linking arm is with described
First linking arm connects, and the other end is provided with the motor for driving propeller.
Aircraft the most according to claim 7, it is characterised in that the other end of described second linking arm is provided with class V-arrangement
Two fork, in described two fork first fork and second fork be separately installed with the first motor and second for driving propeller
Motor.
Aircraft the most according to claim 8 or claim 9, it is characterised in that described propeller is coaxial double oar.
10. according to the aircraft described in any one of claim 1-8, it is characterised in that during described aircraft body is for being formed
The ring-shaped frame of absolutely empty；Described main rotor device is arranged in the described hollow centre of described ring-shaped frame.
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| CN201610811579.9A CN106314787B (en) | 2016-09-08 | 2016-09-08 | Aircraft |
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| CN201610811579.9A CN106314787B (en) | 2016-09-08 | 2016-09-08 | Aircraft |
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| CN106314787B CN106314787B (en) | 2019-05-07 |
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| CN107010215A (en) * | 2017-05-31 | 2017-08-04 | 锐合防务技术（北京）有限公司 | Aircraft |
| CN108609181A (en) * | 2018-05-09 | 2018-10-02 | 重庆睿宇测绘有限责任公司 | Outdoor scene three-dimensional surveys and draws take photo by plane unmanned plane and its control method |
| JP2021037926A (en) * | 2019-08-30 | 2021-03-11 | 株式会社エアロジーラボ | Multicopter |
| JP2021062830A (en) * | 2019-10-16 | 2021-04-22 | 株式会社Ｌｉｂｅｒａｗａｒｅ | Aerial vehicle |
| CN113212746A (en) * | 2021-05-24 | 2021-08-06 | 四川迅联达智能科技有限公司 | Shift-shaft reverse-rotation dual-rotor aircraft |
| CN113636074A (en) * | 2020-05-11 | 2021-11-12 | 乌鲁木齐市达坂城海为支油风电有限公司 | Unmanned aerial vehicle aircraft capable of intelligently adjusting balance of aircraft body |
| CN115200648A (en) * | 2022-09-14 | 2022-10-18 | 四川省亚通工程咨询有限公司 | Bridge state monitoring system and method based on unmanned aerial vehicle |
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| CN115200648A (en) * | 2022-09-14 | 2022-10-18 | 四川省亚通工程咨询有限公司 | Bridge state monitoring system and method based on unmanned aerial vehicle |
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| CN106314787B (en) | 2019-05-07 |
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Effective date of registration: 20190731 Address after: 518054 Virtual University Park C505, No. 2 Sandao, Yuexing Street, Nanshan District, Shenzhen City, Guangdong Province Patentee after: Shenzhen Ruihe Aircraft Intelligent Equipment Co., Ltd. Address before: 100191 Beijing, Zhichun Road, College of International Building, No. 912,, 1 Patentee before: Sharp Defense Technology (Beijing) Co., Ltd. |
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