CN109250096A - A kind of aircraft of more rotors in conjunction with fixed-wing - Google Patents
A kind of aircraft of more rotors in conjunction with fixed-wing Download PDFInfo
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- CN109250096A CN109250096A CN201811274759.3A CN201811274759A CN109250096A CN 109250096 A CN109250096 A CN 109250096A CN 201811274759 A CN201811274759 A CN 201811274759A CN 109250096 A CN109250096 A CN 109250096A
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- heel row
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- 230000007246 mechanism Effects 0.000 claims abstract description 38
- 238000004064 recycling Methods 0.000 claims abstract description 12
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 18
- 238000004146 energy storage Methods 0.000 claims description 16
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 13
- 238000004134 energy conservation Methods 0.000 claims description 9
- 230000002146 bilateral effect Effects 0.000 claims description 5
- 239000002828 fuel tank Substances 0.000 claims description 5
- 239000003921 oil Substances 0.000 claims description 4
- 239000010705 motor oil Substances 0.000 claims description 3
- 239000000295 fuel oil Substances 0.000 claims 1
- 230000008859 change Effects 0.000 abstract description 3
- 230000001133 acceleration Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 description 9
- 230000008569 process Effects 0.000 description 6
- 239000007787 solid Substances 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000005183 dynamical system Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Classifications
-
- 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
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- 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
- B64C27/30—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of aircraft of more rotors in conjunction with fixed-wing.Including fuselage, fixed-wing and rotor are provided with front-seat rotor, heel row rotor and wing tip rotor on fixed-wing；Front-seat rotor passes through the corresponding inclining rotary mechanism being arranged on fixed-wing respectively with heel row rotor and connects with fixed-wing, change the tilt angle of corresponding front-seat rotor or heel row rotor, by the inclining rotary mechanism of control so as to the VTOL, acceleration flight, quick pose adjustment etc. for realizing aircraft；The wing tip rotor that fixed-wing wing tip is arranged in can remove wing tip circulation while providing lift, improve flight efficiency；In inclining rotary mechanism position, corresponding fixed-wing is internally provided with recycling space, it can be by inclining rotary mechanism folding storage corresponding to front-seat rotor and heel row rotor and its two kinds of rotors into recycling space, allow aircraft that wing flight is fixed, it avoids when not needing rapid flight, rotor stalling, generating air drag influences flight.
Description
Technical field
The present invention relates to aviation aircraft technical field, more particularly to a kind of more rotors are in conjunction with fixed-wing
Aircraft.
Background technique
Currently, the Fixed Wing AirVehicle common in aviation field, thinks highly of due to generating lift balance flight mainly by wing
Amount, dynamical system are mainly used to overcome aircraft flight resistance, therefore can allow fixation much smaller than the power of aircraft weight
Rotor aircraft lifts off, and for flying speed than very fast, voyage and cruise time are also longer, but landing distance, it is desirable that high-quality
The runway of amount seriously affects and hampers Fixed Wing AirVehicle in the application of remote no special machine Performance Area.And common rotor
Aircraft can solve the narrow and small place VTOL the problem of, when needing to tilt aircraft, as long as reducing on heading
The revolving speed of paddle, the revolving speed for increasing the paddle of symmetric position can be flown by lift difference to specified direction, but direct and dynamical system
The connected rotor efficiency of system can not show a candle to the wing of Fixed Wing AirVehicle, therefore power consumption is big, and cruising ability is poor, and people start to grind thus
Send out to have concurrently the aircraft of Fixed Wing AirVehicle and rotor craft advantage a kind of.
But the structure of verting that most of rotors and the aircraft of fixed-wing combination have, during verting, high speed turns
Dynamic blade will generate larger component on winged different directions putting down with aircraft, cause attitude of flight vehicle unstable, while very
In flat winged state, the motor of rotor is stalled and is not verted multi-aircraft, and the rotor thus stalled in flat fly can generate larger
Air drag, influence air mileage and flying speed.
Therefore, how to realize and can improve the steady of aircraft flight of more rotors in conjunction with fixed-wing while VTOL
The problem of qualitative, flying speed and cruising ability are those skilled in the art's urgent need to resolve.
Summary of the invention
In view of this, the aircraft the present invention provides a kind of more rotors in conjunction with fixed-wing.
To achieve the goals above, the present invention adopts the following technical scheme:
The aircraft of a kind of more rotors in conjunction with fixed-wing, comprising: fuselage, the fixed-wing positioned at the fuselage two sides, feature
It is: is provided with flight control system on the fuselage；Rotor is provided with outside the fixed-wing；The rotor includes being arranged
Front-seat rotor on front side of the fixed-wing, the heel row rotor being arranged on rear side of the fixed-wing and it is arranged in the fixed-wing
The wing tip rotor of wing tip；The fixed-wing is internally provided with four recycling spaces；It is respectively arranged in four recycling spaces
Inclining rotary mechanism；Two inclining rotary mechanisms positioned at the fixed-wing front row are separately connected the front-seat rotor；Positioned at described solid
Two inclining rotary mechanisms for determining wing heel row are separately connected the heel row rotor；The inclining rotary mechanism and the flight control system
It is connected.
Preferably, the quantity of the front-seat rotor is two, and is distributed by center line bilateral symmetry of the fuselage axis；
The quantity of the heel row rotor is two, and is distributed by center line bilateral symmetry of the fuselage axis, symmetrical so that flying
Uniform force when row device flight, makes its flight stability.
Preferably, two front-seat rotors include left side front row rotor and right side front row rotor, two heel row rotations
The wing includes left side heel row rotor and right side heel row rotor, and left side front row rotor and the left side heel row rotor are relative to fixation
Symmetrical before and after wing horizontal center line axis, right side front row rotor and the right side heel row rotor are also relative to fixed-wing water
It is symmetrical before and after flat central axis.
Preferably, the heel row rotor wing rotation of the front-seat rotor corresponding thereto is contrary, two opposite institutes
The torque that wing tip rotor wing rotation is contrary, and the opposite rotor of the revolving speed same direction can cancel out each other to the fuselage is stated, is made
Aircraft smooth flight.
Preferably, the wing tip rotor for being set to wing tip is parallel to the fixed-wing Plane Rotation, at this time wing tip rotor
Be rotated in the lateral stability that can increase aircraft while longitudinal lift is provided, also can reduce induced drag.
Preferably, the inclining rotary mechanism includes verting pedestal, steering engine and to be connected to pedestal and the steering engine of verting
Between link mechanism.
Preferably, the front-seat rotor and the heel row rotor are provided with motor, and the motor and the flight control
System, which is connected, controls the revolving speed of the front-seat rotor and the heel row rotor, and the motor is mounted on described accordingly vert
On pedestal, rugged construction is reliable, while having the flexibility verted.
Preferably, the steering engine is verted by the pedestal that verts described in link mechanism control, thus described in completing
Front-seat rotor and heel row rotor wide-angle are verted.
Preferably, the aircraft flight is divided into rotor flying mode, rotor offline mode and fixation in conjunction with fixed-wing
Wing offline mode, is substantially be applied in combination mode of the rotor with the fixed-wing, and rotor flying mode is used for aircraft
VTOL process, the limitation of landing process aircraft using area can be substantially reduced；Rotor flight mould in conjunction with fixed-wing
Formula is used for accelerating flight on level process, and flying speed can be improved, and increases flying distance；Wing tip when fixed-wing offline mode
Rotor keeps working condition, and main function is to remove wing tip circulation, flight resistance is reduced, to reach the mesh of energy conservation continuation of the journey
, the front row rotor and the heel row rotor stop rotating and are recycled in the recycling space under this operating mode.
Preferably, the aircraft is oil electric mixed dynamic system, including engine, fuel tank, generator, energy-storage battery
And energy conservation module, the fuel tank are connected with the engine, are the engine oil to generate power, the hair
The input shaft of motor is connected with the output shaft of the engine, and the output shaft of the generator is connected with energy-storage battery, described
The power of the engine is converted to electric energy and is stored in the energy-storage battery by generator, and the energy conservation module is the same as described
Engine is connected with the energy-storage battery, controls the energy flow direction management of aircraft, and the energy-storage battery hangs down for aircraft
The energy supply of high-power output during straight landing, the as described rotor energy supply, the power that the engine generates can be described solid
Determine the wing and inclining rotary mechanism energy supply.
It can be seen via above technical scheme that compared with prior art, the present disclosure provides a kind of more rotors and admittedly
The aircraft for determining wing combination, may be implemented the VTOL of aircraft, break the limitation that Fixed Wing AirVehicle uses orographic condition,
More rotors improve the stability of aircraft, flying speed simultaneously, so that its flying distance is longer.Oily electricity hybrid power supply can mention
The flight time of high aircraft, oil machine can generate electricity and supply rotor motor and energy-storage battery.The setting of more rotors can help to fly
Device carries out quick course line adjustment, aircraft onward impulse can be provided, so that aircraft is more flexible.It is arranged on fixed-wing
Space is recycled, when so that wing offline mode is fixed in aircraft, rotor and its inclining rotary mechanism can be recycled, it will not be to aircraft
Flight causes resistance.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
The embodiment of invention for those of ordinary skill in the art without creative efforts, can also basis
The attached drawing of offer obtains other attached drawings.
Fig. 1 attached drawing is Flight Vehicle Structure schematic diagram provided by the invention；
Fig. 2 attached drawing is inclining rotary mechanism structural schematic diagram provided by the invention.
In Fig. 1:
1 it is fuselage, 2 be fixed-wing, 3 be front-seat rotor, 31 be the front-seat rotor in left side, 32 be the front-seat rotor in right side, 4 is heel row rotation
The wing, 41 be left side heel row rotor, 42 be right side heel row rotor, 5 be wing tip rotor, 6 be inclining rotary mechanism.
In Fig. 2:
2 be fixed-wing, 61 be steering engine, 62 be link mechanism, 63 for vert pedestal, 7 be motor, 8 be rotor, 9 be recycling space.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
The embodiment of the invention discloses a kind of aircraft of more rotors in conjunction with fixed-wing, comprising: fuselage 1 is located at fuselage 1
The fixed-wing 2 of two sides, it is characterised in that: be provided with flight control system on fuselage 1；Rotor 8 is provided with outside fixed-wing 2；Rotation
The wing 8 includes the front-seat rotor 3 that 1 front side of fixed-wing is arranged in, the heel row rotor 4 that 1 rear side of fixed-wing is arranged in and setting solid
Determine the wing tip rotor 5 of 1 wing tip of the wing；Fixed-wing 2 is internally provided with four recycling spaces 9；It is respectively arranged in four recycling spaces 9
Inclining rotary mechanism 6；Two inclining rotary mechanisms 6 front-seat positioned at fixed-wing 2 are separately connected front-seat rotor 3；Positioned at the two of 2 heel row of fixed-wing
A inclining rotary mechanism 6 is separately connected heel row rotor 4；Inclining rotary mechanism 6 is connected with flight control system.
In order to advanced optimize above scheme, the quantity of front-seat rotor 3 is two, and using 1 axis of fuselage as a center line left side
It is right symmetrical；The quantity of heel row rotor 4 is two, and is distributed by center line bilateral symmetry of 1 axis of fuselage.
In order to advanced optimize above scheme, two front-seat rotors 3 include left side front row rotor 31 and right side front row rotor
32, two heel row rotors 4 include left side heel row rotor 41 and right side heel row rotor 42, and left side front row rotor 31 and left side heel row are revolved
The wing 41 is relative to symmetrical, right side front row rotor 32 and right side heel row rotor 42 also phase before and after 2 horizontal center line axis of fixed-wing
For symmetrical before and after fixed-wing 2 horizontal center line axis, the symmetrical mode of rotor makes aircraft uniform force, can be with
Smooth flight.
In order to advanced optimize above scheme, 4 direction of rotation of heel row rotor of front-seat rotor 3 corresponding thereto is on the contrary, two
A opposite 5 direction of rotation of wing tip rotor on the contrary, the opposite rotor of the revolving speed same direction can cancel out each other rotor wing rotation to flying
Torsional forces caused by row device allows aircraft steadily to suspend and rectilinear flight.
In order to advanced optimize above scheme, the wing tip rotor 5 for being set to wing tip is parallel to 2 Plane Rotation of fixed-wing, the wing
Sharp rotor 5 can increase the lateral stability of aircraft, remove wing tip circulation, reduce induced drag, to improve efficiency.
In order to advanced optimize above scheme, inclining rotary mechanism 6 includes verting pedestal 63, steering engine 61 and to be connected to bottom of verting
Link mechanism 62 between seat 63 and steering engine 61.
In order to advanced optimize above scheme, front-seat rotor 3 is provided with motor 7, motor 7 and flight with heel row rotor 4
Control system, which is connected, controls the revolving speed of front-seat rotor 3 and heel row rotor 4, and motor 7 is mounted on to vert on pedestal 63 accordingly.
In order to advanced optimize above scheme, steering engine 61 controls the pedestal 63 that verts by link mechanism 62 and verts, from
And the front-seat rotor 3 of completion and 4 wide-angle of heel row rotor are verted, passing through steering engine 61 controls 8 tilt angle of rotor, realizes course-and-bearing
Adjustment, since rotor 8 is driven by motor 9, so carrying out course line adjustment, so that aircraft is swift in response, posture using rotor 8
Change more flexible.
In order to advanced optimize above scheme, aircraft flight is divided into rotor flying mode, rotor and flies in conjunction with fixed-wing
Row mode and fixed-wing offline mode, be substantially rotor 8 and fixed-wing 2 is applied in combination mode, and rotor flying mode is used for
The VTOL process of aircraft can substantially reduce the limitation of landing process aircraft using area；Rotor is in conjunction with fixed-wing
Offline mode is used for accelerating flight on level process, and front-seat rotor 3 and heel row rotor 4 certain angle that verts make rotor wing rotation be winged
Row device provides the power of flight forward, improves flying speed, increases flying distance；Wing tip rotor 5 is protected when fixed-wing offline mode
Working condition is held, main function is to remove wing tip circulation, flight resistance is reduced, to achieve the purpose that energy conservation continuation of the journey, this work
Front-seat rotor 3 and heel row rotor 4 stop rotating under operation mode, and blade folds, and steering engine is connected inclining rotary mechanism by link mechanism
Be recycled in recycling space 9 together with motor rotor thereon, avoid rotor 8 stop working generated in aircraft flight it is empty
Atmidometer mainly provides lift and forward power by fixed-wing 2.
In order to advanced optimize above scheme, aircraft is oil electric mixed dynamic system, including engine, fuel tank, hair
Motor, energy-storage battery and energy conservation module, fuel tank are connected with engine, are engine oil to generate power, power generation
The input shaft of machine is connected with the output shaft of engine, and the output shaft of generator is connected with energy-storage battery, and generator is by engine
Power be converted to electric energy and be stored in energy-storage battery, energy conservation module is connected with engine with energy-storage battery, and control flies
The energy of row device flows to management, and energy-storage battery is used for the energy supply of high-power output during aircraft vertical landing, as rotor 8
Energy supply, the power that engine generates can energize for fixed-wing 2 and inclining rotary mechanism 6, and energy conservation module controls energy flow direction management
The energy can be more saved, effectively extension hours underway.
Embodiment 1
It is at this time rotor flying mode when aircraft carries out vertical raising, flight control system passes through steering engine controls connecting rod mechanism
So that the pedestal that verts verts, front-seat rotor is enabled to be located on the horizontal plane above fixed-wing, heel row rotor is located at below fixed-wing
Horizontal plane, drives rotor motor at this time, and front-seat rotor, heel row rotor and wing tip rotor can rotate to be aircraft simultaneously and provide liter
Power, more rotors provide lift and aircraft are made to be climbed to demand height, and keep rotor revolving speed constant, can keep
Aircraft hovering, and stability is high, aircraft vertical raising is applicable to narrow spatial operation.
Embodiment 2
It at this time can be rotor offline mode in conjunction with fixed-wing when aircraft navigates by water, flight control system is controlled by steering engine
The link mechanism pedestal that vert verts, and enables front-seat rotor vert to the heading of fuselage, Plane of rotation is perpendicular to fixed-wing
Plane, heel row rotor vert to fuselage empennage direction, and for Plane of rotation vertically with fixed-wing horizontal plane, wing tip rotor direction is constant,
It is at this time rotor offline mode in conjunction with fixed-wing, front-seat rotor provides the power of flight forward with heel row rotor for aircraft,
Wing tip circulation when the wing tip rotor of fixed-wing two sides can remove aircraft flight simultaneously, reduces its flight resistance, solid simultaneously
Determine the wing and be similarly aircraft to provide the power of lift and ahead running, therefore is integrally improved the flying speed of aircraft, it can
Quickly to arrive at designated place.
When rerouting, rotor revolving speed is controlled by flight control system, if left side front row rotor revolves clockwise
Turn, rotor rotates counterclockwise behind left side, and right side front row rotor rotates counterclockwise, and right side heel row rotor rotates clockwise, if at this time
Think so that aircraft deflection of flight to the left, then reduce the motor speed of rotor clockwise, increase the motor speed of rotor counterclockwise
, similarly to the right deflection of flight when, increase the motor speed of rotor clockwise, reduce the motor speed of rotor counterclockwise,
The realization that such control mode deflects aircraft course line is more simple, while the mode of energy-storage battery control motor speed makes
Must flying, it is more rapid to change.
When aircraft enters fixed-wing offline mode, front-seat rotor is controlled by flight control system and is stopped with heel row rotor
Rotation stop is dynamic, while the blade of rotor being folded, then to vert pedestal together with rotor one by steering engine controls connecting rod mechanism
With being recycled in recycling space, the pulling force that fixed-wing mainly provides lift at this time and flight is advanced, wing tip rotor is mainly removed
Wing tip circulation reduces air drag, while can also provide lift.
Embodiment 3
It is at this time rotor flying mode, flight control system to vert by steering engine controls connecting rod mechanism when aircraft lands
Pedestal verts, and enables front-seat rotor be restored on the horizontal plane above fixed-wing, heel row rotor is restored to the level below fixed-wing
Face, rotor provides lift at this time, and aircraft can hover, and reduces rotor motor revolving speed later, aircraft is hung down
It lands vertically and falls.
A kind of aircraft of more rotors in conjunction with fixed-wing, combine gyroplane can VTOL the advantages of and fixed-wing fly
The high advantage of row device flight efficiency, so that aircraft takeoff place is no longer restricted, while the more steady, distance to go that flies is shown
It writes and improves.Increase rotor inclining rotary mechanism on aircraft and store the recycling space of rotor and inclining rotary mechanism, so that carry-on
Rotor can need to carry out according to flight angle adjustment, and rotor can rotate to be aircraft by the certain angle that verts and provide advance
Power, improve the flying speed of aircraft, so that aircraft is in identical hours underway, the distance of navigation is farther, can be fast
The arrival of speed carries out the tasks such as prospecting shooting more at a distance can pack up rotor, effectively avoid when wing flight is only fixed
In energy-saving mode, rotor do not work and causes flight resistance to aircraft；Wing tip rotor is set in fixed-wing wing tip simultaneously, it can
To remove wing tip circulation, flight efficiency is improved, so that aircraft flight is apart from farther, raising flying speed；Increased rotor is set
It sets so that when aircraft flight is more steady, shooting picture is needed when if being monitored prospecting, aircraft can hover,
Simultaneously as stability enhances, so the picture of shooting is more clear stabilization, improve work efficiency.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.For device disclosed in embodiment
For, since it is corresponded to the methods disclosed in the examples, so being described relatively simple, related place is said referring to method part
It is bright.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be readily apparent to those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, of the invention
It is not intended to be limited to the embodiments shown herein, and is to fit to and the principles and novel features disclosed herein phase one
The widest scope of cause.
Claims (10)
1. a kind of aircraft of more rotors in conjunction with fixed-wing, comprising: fuselage (1) is located at the fixed-wing of the fuselage (1) two sides
(2), it is characterised in that: be provided with flight control system on the fuselage (1)；Rotor is provided with outside the fixed-wing (2)
(8)；The rotor (8) includes the front-seat rotor (3) being arranged on front side of the fixed-wing (1), is arranged in the fixed-wing (1)
The wing tip rotor (5) of the heel row rotor (4) of rear side and setting in the fixed-wing (1) wing tip；It is set inside the fixed-wing (2)
Space (9) are recycled there are four setting；Inclining rotary mechanism (6) are respectively arranged in four recycling spaces (9)；Positioned at the fixed-wing
(2) two front-seat inclining rotary mechanisms (6) are separately connected the front-seat rotor (3)；Positioned at the two of the fixed-wing (2) heel row
A inclining rotary mechanism (6) is separately connected the heel row rotor (4)；The inclining rotary mechanism (6) and the flight control system phase
Even.
2. a kind of aircraft of the more rotors according to claim 1 in conjunction with fixed-wing, which is characterized in that the front-seat rotation
The quantity of the wing (3) is two, and is distributed by center line bilateral symmetry of the fuselage (1) axis；The number of the heel row rotor (4)
Amount is two, and is distributed by center line bilateral symmetry of the fuselage (1) axis.
3. a kind of aircraft of the more rotors according to claim 2 in conjunction with fixed-wing, which is characterized in that before two described
Row rotor (3) includes left side front row rotor (31) and right side front row rotor (32), after two heel row rotors (4) include left side
Arrange rotor (41) and right side heel row rotor (42), left side front row rotor (31) and the left side heel row rotor (41) relative to
It is symmetrical before and after fixed-wing (2) horizontal center line axis, right side front row rotor (32) and the right side heel row rotor
(42) also relative to symmetrical before and after the fixed-wing (2) horizontal center line axis.
4. a kind of aircraft of the more rotors according to claim 3 in conjunction with fixed-wing, which is characterized in that the front-seat rotation
Heel row rotor (4) direction of rotation of the wing (3) corresponding thereto is on the contrary, two opposite wing tip rotor (5) rotation sides
To opposite.
5. a kind of aircraft of the more rotors according to claim 4 in conjunction with fixed-wing, which is characterized in that the wing tip rotation
The wing (5) is parallel to the fixed-wing (2) Plane Rotation.
6. a kind of aircraft of the more rotors according to claim 1 in conjunction with fixed-wing, which is characterized in that the machine that verts
Structure (6) includes verting pedestal (63), steering engine (61) and to be connected to described vert between pedestal (63) and the steering engine (61)
Link mechanism (62).
7. a kind of aircraft of the more rotors according to claim 6 in conjunction with fixed-wing, which is characterized in that the front-seat rotation
The wing (3) and the heel row rotor (4) are provided with motor (7), and the motor (7) is connected control with the flight control system
The revolving speed of front row rotor (3) and the heel row rotor (4), the motor (7) are mounted on the corresponding pedestal that verts
(63) on.
8. a kind of aircraft of the more rotors according to claim 7 in conjunction with fixed-wing, which is characterized in that the steering engine
(61) it is verted by the pedestal (63) that verts described in the link mechanism (62) control, to complete the front-seat rotor (3)
It verts with heel row rotor (4) wide-angle.
9. a kind of aircraft of the more rotors according to claim 1 in conjunction with fixed-wing, which is characterized in that the aircraft
Flight is divided into rotor flying mode, rotor offline mode and fixed-wing offline mode in conjunction with fixed-wing.
10. a kind of aircraft of the more rotors according to claim 1 in conjunction with fixed-wing, which is characterized in that the flight
Device is oil electric mixed dynamic system, including engine, fuel tank, generator, energy-storage battery and energy conservation module, the fuel oil
Case is connected with the engine, is the engine oil to generate power, the input shaft of the generator starts with described
The output shaft of machine is connected, and the output shaft of the generator is connected with energy-storage battery, and the generator is moved the engine
Power is converted to electric energy and is stored in the energy-storage battery, and the energy conservation module is equal with the engine and the energy-storage battery
It is connected, controls the energy flow direction management of aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274759.3A CN109250096A (en) | 2018-10-30 | 2018-10-30 | A kind of aircraft of more rotors in conjunction with fixed-wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274759.3A CN109250096A (en) | 2018-10-30 | 2018-10-30 | A kind of aircraft of more rotors in conjunction with fixed-wing |
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| Publication Number | Publication Date |
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| CN109250096A true CN109250096A (en) | 2019-01-22 |
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| CN201811274759.3A Withdrawn CN109250096A (en) | 2018-10-30 | 2018-10-30 | A kind of aircraft of more rotors in conjunction with fixed-wing |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111137446A (en) * | 2019-12-26 | 2020-05-12 | 中国空气动力研究与发展中心 | Pneumatic layout of multi-rotor vertical take-off and landing unmanned aerial vehicle with stalling function |
| CN113895612A (en) * | 2021-09-08 | 2022-01-07 | 武汉思众空间信息科技有限公司 | Aircraft and using method thereof |
| CN114430725A (en) * | 2019-05-21 | 2022-05-03 | 杰欧比飞行有限公司 | Vertical take-off and landing aircraft using fixed pitch rotors to simulate rigid wing aerodynamics |
| CN115686043A (en) * | 2022-10-28 | 2023-02-03 | 南京航空航天大学 | Fixed-wing aircraft and air docking method of rotor aircraft |
-
2018
- 2018-10-30 CN CN201811274759.3A patent/CN109250096A/en not_active Withdrawn
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114430725A (en) * | 2019-05-21 | 2022-05-03 | 杰欧比飞行有限公司 | Vertical take-off and landing aircraft using fixed pitch rotors to simulate rigid wing aerodynamics |
| CN111137446A (en) * | 2019-12-26 | 2020-05-12 | 中国空气动力研究与发展中心 | Pneumatic layout of multi-rotor vertical take-off and landing unmanned aerial vehicle with stalling function |
| CN113895612A (en) * | 2021-09-08 | 2022-01-07 | 武汉思众空间信息科技有限公司 | Aircraft and using method thereof |
| CN113895612B (en) * | 2021-09-08 | 2023-08-01 | 武汉思众空间信息科技有限公司 | Aircraft and application method thereof |
| CN115686043A (en) * | 2022-10-28 | 2023-02-03 | 南京航空航天大学 | Fixed-wing aircraft and air docking method of rotor aircraft |
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