CN107458595A - A kind of oil electricity mixes heavily loaded multirotor helicopter - Google Patents
A kind of oil electricity mixes heavily loaded multirotor helicopter Download PDFInfo
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- CN107458595A CN107458595A CN201710791210.0A CN201710791210A CN107458595A CN 107458595 A CN107458595 A CN 107458595A CN 201710791210 A CN201710791210 A CN 201710791210A CN 107458595 A CN107458595 A CN 107458595A
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- 230000005611 electricity Effects 0.000 title claims abstract description 26
- 239000000446 fuel Substances 0.000 claims abstract description 44
- 238000010276 construction Methods 0.000 claims description 10
- 239000010977 jade Substances 0.000 claims description 3
- 238000002485 combustion reaction Methods 0.000 claims description 2
- 230000008450 motivation Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 abstract description 3
- 238000004146 energy storage Methods 0.000 abstract description 3
- 238000010248 power generation Methods 0.000 abstract description 3
- 230000002035 prolonged effect Effects 0.000 abstract description 3
- 239000003921 oil Substances 0.000 description 12
- 230000007423 decrease Effects 0.000 description 6
- 238000006243 chemical reaction Methods 0.000 description 5
- 230000009471 action Effects 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 3
- 206010034719 Personality change Diseases 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 230000003100 immobilizing effect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
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- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- B64C27/12—Rotor drives
-
- 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
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
-
- B64D27/026—
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of oil electricity to mix heavily loaded multirotor helicopter, it is made up of fuel engines module, motor, control direction small machine, battery pack, small rotor, main rotor module, frame and control system module, it employs a kind of by the main rotor offer lift of the dynamic engine driving of oil, and drive generator to give cell power generation energy storage, then small machine and small rotor wing rotation are driven come the mixed dynamic model formula of control direction by battery；The advantages of electronic multirotor helicopter moves helicopter with oil is combined, the object of larger quality, such as document, goods or people can be lifted；And capacity usage ratio is high, the activity duration of helicopter can be greatly prolonged, improves operating efficiency；Can be that helicopter is powered by power supply of battery by the power and energy of generator, support helicopter works on a period of time to implement forced landing in addition, when when motivation failure or empty.
Description
Technical field
The present invention relates to helicopter field, and in particular to a kind of oil electricity mixes heavily loaded multirotor helicopter.
Background technology
Referred to as " unmanned plane ", english abbreviation is " UAV " to UAV, using radio robot and is provided for oneself
The not manned aircraft that presetting apparatus manipulates, or fully or intermittently independently operated by car-mounted computer.
Compared with manned aircraft, unmanned plane is often more suitable for the task of those too " slow-witted, dirty or dangerous ".Nobody
Machine presses application field, can be divided into it is military with it is civilian.Military aspect, unmanned plane are divided into reconnaissance plane and target drone.Civilian aspect, unmanned plane
+ sector application, it is that unmanned plane has really just needed；At present take photo by plane, agricultural, plant protection, miniature self-timer, express transportation, disaster relief,
Observe wild animal, monitoring infectious disease, mapping, news report, electric inspection process, the disaster relief, movies-making, manufacture romance etc. field
Application, greatly expanded the purposes of unmanned plane in itself, developed country is also in actively extension sector application and development unmanned plane
Technology.
Existing unmanned plane is mostly fuel engines driving or motor driving, and the band of simple fuel engines driving carries energy
Power is eager to excel than motor driving, but less stable, and the probability that fuel engines breaks down is significantly larger than motor, but works as unmanned plane
In flight course, such as fuel engines failure, helicopter can directly fall, and cause unmanned plane and its article carried
Break, cause very big economic loss.
In addition, the handling of oil electric mixed dynamic unmanned plane of the prior art is undesirable, load capacity is also poor, and
And energy utilization rate is not also high, and equally exist potential safety hazard caused by fuel engines unmanned plane failure.
The content of the invention
The purpose of the present invention is in view of the deficienciess of the prior art, a kind of unpiloted oil electricity mixing of offer is heavily loaded more
Heligyro.
To achieve the above object, the invention provides a kind of oil electricity to mix heavily loaded multirotor helicopter, and the helicopter includes
Frame, fuel engines module, motor, multiple control direction small machines, battery pack, main rotor module and control system module；
The fuel engines module, multiple control direction small machines, battery pack and control system module are each attached to the upper of frame；
The fuel engines module top has an output shaft being vertically arranged, and the axle center of the output shaft passes vertically through
The barycenter of helicopter, the multiple control direction small machine are uniformly distributed centered on output shaft, each control direction small machine
Top is fixed with a small fine jade wing；
The motor is arranged on the top of fuel engines, and it is unidirectional to be connected with one between the rotating shaft of the output shaft and motor
Clutch, the rotating shaft are connected with main rotor module, the control system module respectively with motor, battery pack, fuel engines
Module, control direction small machine connect with control terminal.
Preferably, the main rotor module includes gear fixed mount and the DCB Specimen of coaxial construction；The gear is fixed
The outside of frame is fixed with frame；The gear fixed mount inner underside is provided with upper rotor gear, and upside is provided with lower rotor gear in it,
Its inside portion is rotatably provided with a tumbler gear, and the tumbler gear is engaged between rotor gear and lower rotor gear；
The DCB Specimen of the coaxial construction include be connected with the rotating shaft of motor upper rotor shaft, be fixed on the upper rotor shaft
On upper rotor, lower rotor shaft and the lower rotor being fixed in lower rotor shaft；The upper rotor gear and lower rotor gear difference
It is fixed in rotor shaft and lower rotor shaft；
The lower rotor shaft is hollow-core construction, and the upper rotor shaft is rotatably connected through lower rotor inside and with it.
Preferably, the main rotor module includes main rotor rotating shaft and the main rotation installed in the main rotor rotating shaft upper end
The wing, the main rotor rotating shaft lower end are connected with the rotating shaft upper end of the motor；The multiple control direction small machine direction of rotation
It is opposite with the direction of rotation of the main rotor.
Preferably, the motor has generator and motor double working modes, the pattern switching is by control system mould
Block is completed；The rotor rotary electrification of drive motor during the engine work, the electricity sent is through control system module rectification
Battery pack is charged afterwards；When engine failure, empty or the pure electric drive of needs, the voltage of the battery pack is through control
Powered after system module inversion processed to motor, the lift needed for helicopter is provided jointly with control direction small machine.
Preferably, the frame includes a bottom plate and the support frame fixed with bottom plate；The fuel engines module, electricity
Pond group and control system module are arranged on the bottom plate, and support frame as described above and the upper end of fuel engines module are fixed with installation
Frame, the end that the mounting bracket is uniformly arranged centered on having multiple rotating shafts by motor, the control direction small machine installation
In the end；The frame also includes the fixed mount being connected between mounting bracket and gear fixed mount.
Preferably, the upper rotor gear and lower rotor module and number of teeth all same；The multiple control direction
The direction of rotation of small machine includes turning clockwise and rotate counterclockwise, the controlling party to turn clockwise with rotate counterclockwise
It is arranged at intervals to small machine.
Preferably, the number of the control direction small machine is the even number more than or equal to 4.
Preferably, the upper rotor gear, lower rotor gear and tumbler gear are angular wheel.
Preferably, support frame as described above, mounting bracket, fixed mount are pipe frame structure.
Beneficial effect：The present invention drives main rotor to provide lift using oil turbine, and drive motor is to cell power generation
Energy storage, then small machine and small rotor wing rotation are driven come the mixed dynamic model formula of control direction by battery；Electronic more rotors are combined to go straight up to
The advantages of machine is with fuel power helicopter, the object of larger quality, such as document, goods or people can be lifted；And energy profit
It is high with rate, the activity duration of helicopter can be greatly prolonged, improves operating efficiency.In addition, when motivation failure or fuel oil
Can be that helicopter is powered by power supply of battery by the power and energy of generator when exhausting, support helicopter after
Continuous work is for a period of time to implement forced landing.
Brief description of the drawings
Fig. 1 is the structural representation that oil electricity provided in an embodiment of the present invention mixes heavily loaded multirotor helicopter；
Fig. 2 is the structural representation of bispin wing structure main rotor module provided in an embodiment of the present invention；
Fig. 3 is the structural representation of single rotor structure main rotor module provided in an embodiment of the present invention；
Fig. 4 is the overlooking the structure diagram that oil electricity provided in an embodiment of the present invention mixes heavily loaded multirotor helicopter；
Fig. 5 is that oil electricity provided in an embodiment of the present invention mixes heavily loaded multirotor helicopter manipulating principle figure.
Embodiment
Below in conjunction with the accompanying drawings and specific embodiment, the present invention is furture elucidated, and the present embodiment is with technical solution of the present invention
Premised under implemented, it should be understood that these embodiments are only illustrative of the invention and is not intended to limit the scope of the invention.
As shown in figure 1, the embodiment of the invention discloses a kind of oil electricity to mix heavily loaded multirotor helicopter, it include frame 2,
Fuel engines module 3, motor 8, multiple control direction small machines 7, battery pack 5, main rotor module 1 and control system module 4；
Frame 2 is as fuel engines module 3, generator 8, control direction small machine 7, battery pack 5, main rotor module 1 and control system
The fixed mechanism for module 4 of uniting.
As shown in figure 1, fuel engines module 3, multiple control direction small machines 7, battery pack 5 and control system module 4
It is each attached to the upper of frame 2；Fuel engines module 3 is arranged in the center of frame 2, and battery pack 5 and control system module 4 are divided
The sidepiece in fuel engines module 3 is not located at.
Control system module 4 is the control system of control helicopter flight state, and it controls engine 3, generator 8, electricity
The working condition of pond group 5 and control direction small machine 7, ensure the normal flight of helicopter.
Battery pack 5 can use conventional accumulators to form, and the electric energy that generator 8 is received during normal work is charged, and together
When powered to the control direction small machine 7 for being distributed in the surrounding of main rotor module 1, when fuel engines 3 failure of module, battery pack
5 to small machine 7 in addition to powering, and is also powered to the generator 8 carried out after patten transformation, allows it to drive main rotor 1 to rotate
Lift is provided.
As shown in figure 1, the top of fuel engines module 3 has an output shaft being vertically arranged, the axle center of output shaft is vertical
Through the barycenter of this helicopter, multiple control direction small machines 7 are uniformly distributed centered on the axle center of output shaft, each controlling party
The one small fine jade wing 6 is all fixed with rotating shaft to the top of small machine 7；Motor 8 is arranged on the top of fuel engines module 3, combustion
A clutch (not shown) is connected between the rotating shaft of the output shaft and motor 8 of oil turbine module 3.Fuel engines mould
The rotating shaft of the output shaft, motor of block 3 is identical with the axle center of the rotating shaft of main rotor module 1.
The clutch that the embodiment of the present invention uses is one-way clutch, when engine operates, by fuel engines module 3
Output shaft be connected with the rotating shaft coaxial line of motor 8 so that the output shaft of the rotating shaft of motor 8 and fuel engines module 3
Rotate together, when motor 8 is exports power source, throw-out-of clutch so that the rotating shaft of motor 8 and fuel engines module 3
Output shaft disconnects.Because the rotating shaft of motor 8 is connected with main rotor module 1 so that main rotor module 1 with motor 8 rotating shaft
Rotate together, there is provided one is available for Helicopter Safety to return to the basic lift to land.
The motor 8 of the embodiment of the present invention has generator and motor double working modes, and it can be used as generator use,
Also can be used as motor, control system module 4 is connected with motor 8 and battery pack 5 respectively, and the pattern switching is by control system
Module 4 is completed.The rotor rotary electrification of drive motor 8 during 3 normal work of engine, the electricity sent enter through control system module 4
Battery pack 5 is charged after row rectification；Engine 3 breaks down, empty or need pure electric drive when, the voltage of battery pack 5 warp
After control system module 4 working power is provided to motor 8.Control system module 4 can by control inverter export voltage
Frequency, and then the rotating speed of controlled motor 8, provide the lift needed for helicopter jointly with control direction small machine 7, it is straight so as to realize
Rising, decline and deflecting of the machine of liter under electronic state of flight.
Control system module 4 is connected with fuel engines module 3, and control system module is used to control fuel engines module
3 startup, stopping and rotating speed.And then realize the raising and lowering of helicopter.
Control system module 4 is connected with multiple control direction small machines 7, no matter is used as and is flown in fuel engines module 3
Power source, or motor 8, as flying power source, battery pack 5 is always that it provides working power, and control system module 4 is all
Operation, rotating speed and the stopping of multiple control direction small machines 7 are can control, can just be controlled by the rotating speed and torque that control small machine 7
The flight path of helicopter processed.
As described in Figure 1, the small quantity of rotor 6 is identical with the control quantity of small machine 7, is fixedly connected on the armature spindle of small machine 7,
Small machine 7 drives small rotor 6 to rotate when rotating, and small rotor 6 can act on a lift by the output shaft of small machine 7 and torque is arrived
On helicopter, change lift and the torque that small rotor 6 is applied on helicopter by controlling the rotation of each small machine 7, from
And reach the purpose of control helicopter attitude and heading.
Control system module 4 and control terminal (not shown) are used to send to go straight up to by wireless connection, control terminal
The control signal of machine, including the control signal such as the startup of fuel engines module 3, stopping, rising, decline, heading, the control
Signal processed is received through radio communication by control system module 4, and control system module 4 is made accordingly according to the control signal received
Output, as started or stoped fuel engines module 3, the acceleration or deceleration of fuel engines module 3, control direction small machine 7
Operation, acceleration and deceleration or stopping etc..
As shown in figure 3, the main rotor module 1 of the embodiment of the present invention can use single rotor structure, single rotor structure includes
One main rotor rotating shaft 111, the lower end of main rotor rotating shaft 111 are connected with the rotating shaft upper end of motor 8, also can be in main rotor rotating shaft
Gear is set between 111 and the rotating shaft of motor 8, and the upper end of main rotor rotating shaft 111 is provided with main rotor 112.Using this knot
During the main rotor 112 of structure, the caused reaction force when rotated of main rotor 112, body can be made to produce rotation, to make body steady
It is fixed, the direction of rotation of multiple control direction small machines 7 is arranged to the direction of rotation of main rotor 112 on the contrary, making main rotor 112
Caused reaction force is cancelled out each other with reaction force caused by multiple control direction small machines 7, and then realizes stable machine.
Alternatively embodiment, main rotor module 1 are bispin wing structure, as illustrated in fig. 1 and 2, the embodiment of the present invention
Main rotor module 1 include the DCB Specimen of gear fixed mount 16 and coaxial construction；As a kind of embodiment, gear fixed mount 16 is excellent
Elect rectangular structure as, can also use other shapes structure, the outside of gear fixed mount 16 is fixed with frame 2；Gear fixed mount 16
Interior downside is provided with upper rotor gear 15, and the upside in gear fixed mount 16 is provided with lower rotor gear 17, in gear fixed mount 16
Sidepiece be provided with a tumbler gear 14, tumbler gear 14 is arranged on the rack that the sidepiece in gear fixed mount 16 is set,
Tumbler gear 14 can freely rotate on rack, tumbler gear 14 be engaged on rotor gear 15 and lower rotor gear 17 it
Between.
As shown in Fig. 2 the DCB Specimen for the coaxial construction that the present invention uses includes the upper rotor shaft being connected with the rotating shaft of motor 8
12nd, upper rotor 11, lower rotor shaft 18 and the lower rotor 13 being fixed in lower rotor shaft 18 being fixed in rotor shaft 12；Upper rotation
Wing axle 12, the axle center of lower rotor shaft are identical with the rotating shaft core of motor 8.Upper rotor gear 15 and lower rotor gear 17 are solid respectively
It is scheduled in rotor shaft 12 and lower rotor shaft 18.The mode of above-mentioned fixation includes a variety of, such as welding, interference fit or other means
It is fixed.Lower rotor shaft 12 is hollow-core construction, and upper rotor shaft 18 is rotatably connected through the inside of lower rotor 12 and with it, the present invention
Various structures of the prior art can be taken by being rotatably connected, and such as bearing connection, will not be described here.It should be noted that
The embodiment of the present invention can also use other bispin wing structures of the prior art.
As shown in figure 1, the frame 2 of the present invention includes a bottom plate 21 and the support frame 22 fixed with bottom plate；The fuel oil hair
Motivation module 3, battery pack 5 and control system module 4 are arranged on the bottom plate, support frame as described above 22 and fuel engines module
3 upper end is fixed with mounting bracket 23, and the mounting bracket 23 has multiple ends being uniformly arranged centered on rotating shaft, control direction
Small machine 7 is arranged on the end, and frame 2 also includes the fixed mount 24 being connected between mounting bracket 23 and gear fixed mount 16.
As shown in Fig. 2 when using bispin wing structure, the stabilization of helicopter body is top rotor 11, the and of lower rotor 13
What multiple control direction small machines 7 maintained jointly, therefore, the angular speed that upper rotor 11 reversely rotates with lower rotor 13 can phase
Together, can also differ.For ease of manufacturing, preferably the angular speed that upper rotor 11 reversely rotates with lower rotor 13 is arranged to
It is identical.
Realize that rotor 11 is identical with the angular speed that lower rotor 13 reversely rotates, the embodiment of the present invention is by by upper rotor
Gear 15 and the lower modulus of rotor gear 17 and the number of teeth be all provided with being set to it is identical, when fuel engines module 3 drives upper rotor gear 15
During rotation, commutating and be driven through tumbler gear 14, the angular speed of lower rotor angular wheel 17 is identical with the upper angular speed of rotor gear 15,
But in opposite direction, thus rotor is rotated with same angular velocity, opposite direction up and down for drive.Opposite direction rotation can make me straight
The machine of liter is cancelled out each other by the reaction force of upper rotor 11 and lower rotor 13.On this condition, multiple control direction small machines 7
Direction of rotation should be not all the same, so its caused reaction force is also cancelled out each other.
For ease of control, as shown in figure 5, the number of the control direction small machine 7 of the embodiment of the present invention be preferably greater than etc.
In 4 even number, under regular flight condition, wherein half is set to turn clockwise, second half rotate counterclockwise.And it is preferred that will be inverse
Hour hands rotation is arranged at intervals with the control direction small machine 7 to turn clockwise, can so make helicopter when doing relevant action,
Fuselage can be kept stable substantially.
Upper rotor gear 15, lower rotor gear 17 and the tumbler gear 14 of the present invention can use of the prior art a variety of
The gear of shape, it is preferred to use angular wheel.Angular wheel has a long lifespan, high load capacity bearing capacity, chemically-resistant and corrosivity is strong,
Noise reduction and damping, in light weight, cost is low, is easy to shaping, the advantages that lubricity is good.
In order to mitigate the own wt of this helicopter, increase the load capacity of this helicopter, the support in frame 2 of the present invention
Frame 22, mounting bracket 23, fixed mount 24 are both preferably pipe frame structure, can also use the lighter solid construction of material or other structures.
Below using the quantity of control direction small machine as 4 embodiments, the control mode and original of helicopter of the present invention are described
Reason：
Rise：Control system module 4 controls the rotating speed of fuel engines module 3, when rotating speed postcritical, makes rotor
11st, when the rotation generation lift of lower rotor 13 and multiple control direction small machines 7 is more than the gravity of this helicopter, helicopter is
It can rise.
Tumbling action：As shown in Figures 4 and 5, during helicopter does roll action, control system module 4 controls multiple controls
The running status of direction small machine 7 processed, 62, No. 64 small rotors are made to be in halted state.No. 61 small rotor rotating speed declines, No. 63 small
Rotor rotating speed raises, then helicopter is by the torque for making it be rotated in yz planes around x-axis, thus lifts No. 63 small rotor side
Height, No. 61 small rotor side decline, and 62, No. 64 small rotor position keeps immobilizing.If raising No. 61 small rotor rotating speed, 63
Number small rotor rotating speed declines, then helicopter attitude change is also opposite.During this, main rotor rotating speed is constant or has slight drop, tool
Body numerical value and small rotor rotation speed change are related with lift size.
Flexion-extension acts：As shown in Figures 4 and 5, during helicopter does pitching motion, control system module 4 controls multiple controls
The running status of direction small machine 7 processed, 61, No. 63 small rotors are made to be in halted state.No. 62 small rotor rotating speed declines, No. 64 small
Rotor rotating speed raises, then helicopter is by the torque for making it be rotated in xz planes around y-axis, thus lifts No. 64 small rotor side
Height, No. 62 small rotor side decline, and 61, No. 63 small rotor position keeps immobilizing.If raising No. 62 small rotor rotating speed, 64
Number small rotor rotating speed declines, then helicopter attitude change is also opposite.During this, main rotor rotating speed is constant or has slight drop, tool
Body numerical value and small rotor rotation speed change are related with lift size.
Lateral deviation acts：As shown in Figures 4 and 5, during helicopter does lateral deviation action, control system module 4 controls multiple controls
The running status of direction small machine 7 processed, raise 61, No. 63 small rotor rotating speed, 62, No. 64 small rotor rotating speed declines, so straight
The machine of liter is produced around the clockwise of itself frame axis by the lateral deviation torque for making helicopter be rotated on x/y plane around z-axis direction
Rotate.If declining 61, No. 63 small rotor rotating speed, 62, No. 64 small rotor rotating speed rises, then the lateral deviation direction of motion is on the contrary, go straight up to
Machine is rotated clockwise.During this period, main rotor rotating speed has slight drop, the additional lift provided depending on small rotor
Size.
Decline：During flight, control system module 4 controls the rotating speed of fuel engines module 4, when fuel engines mould
The rotating speed of block 4 is less than critical point, rotor 11, lower rotor 13 and multiple control direction small machines 7 is rotated caused lift
Less than this helicopter gravity when, helicopter can be begun to decline.
In summary, the present invention drives main rotor to provide lift using oil turbine, and drive motor is to cell power generation
Energy storage, then small machine and small rotor wing rotation are driven come the mixed dynamic model formula of control direction by battery；Electronic more rotors are combined to go straight up to
The advantages of machine is with fuel power helicopter, the object of larger quality, such as document, goods or people can be lifted；And energy profit
It is high with rate, the activity duration of helicopter can be greatly prolonged, improves operating efficiency.In addition, when motivation failure or fuel oil
Can be that helicopter is powered by power supply of battery by the power and energy of generator when exhausting, support helicopter after
Continuous work is for a period of time to implement forced landing.
Described above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications also should
It is considered as protection scope of the present invention.
Claims (9)
1. a kind of oil electricity mixes heavily loaded multirotor helicopter, it is characterised in that：Including frame（2）, fuel engines module（3）、
Motor（8）, multiple control direction small machines（7）, battery pack（5）, main rotor module（1）With control system module（4）；The combustion
Oil turbine module（3）, multiple control direction small machines（7）, battery pack（5）With control system module（4）It is each attached to frame
（2）It is upper；
The fuel engines module（3）Top has an output shaft being vertically arranged, and the axle center of the output shaft passes vertically through
The barycenter of helicopter, the multiple control direction small machine（7）It is uniformly distributed centered on output shaft, each small electricity of control direction
Machine（7）Top is fixed with a small fine jade wing（6）；
The motor（8）It is arranged on fuel engines（3）Top, the output shaft（9）With motor（8）Rotating shaft between connect
There are an one-way clutch, the motor（8）Rotating shaft and main rotor module（1）Connection, the control system module（4）Respectively with
Motor（8）, battery pack（5）, fuel engines module（3）, control direction small machine（7）Connected with control terminal.
2. oil electricity according to claim 1 mixes heavily loaded multirotor helicopter, it is characterised in that：The main rotor module
（1）Including gear fixed mount（16）With the DCB Specimen of coaxial construction；The gear fixed mount（16）Outside and frame（2）Gu
It is fixed, the gear fixed mount（16）Inner underside is provided with upper rotor gear（15）, upside is provided with lower rotor gear in it（17）, in it
Sidepiece is rotatably provided with a tumbler gear（14）, the tumbler gear（14）It is engaged on rotor gear（15）With lower rotor gear
（17）Between；
The DCB Specimen of the coaxial construction includes and motor（8）Rotating shaft connection upper rotor shaft（12）, be fixed on the upper rotation
Wing axle（12）On upper rotor（11）, lower rotor shaft（18）Be fixed on lower rotor shaft（18）On lower rotor（13）；On described
Rotor gear（15）With lower rotor gear（17）It is separately fixed at rotor shaft（12）With lower rotor shaft（18）On；
The lower rotor shaft（12）For hollow-core construction, the upper rotor shaft（18）Rotatably connect inside through lower rotor and with it
Connect.
3. oil electricity according to claim 1 mixes heavily loaded multi-rotor unmanned aerial vehicle, it is characterised in that：The main rotor module
（1）Including main rotor rotating shaft（111）With installed in the main rotor rotating shaft（111）The main rotor of upper end（112）, the main rotor
Rotating shaft（111）Lower end and the motor（8）Rotating shaft upper end connection；The multiple control direction small machine（7）Direction of rotation with
The main rotor（112）Direction of rotation it is opposite.
4. oil electricity according to claim 1 mixes heavily loaded multirotor helicopter, it is characterised in that：The motor（8）Have
Generator and motor double working modes, the pattern switching is by control system module（4）Complete；The engine（3）Normal work
Drive motor when making（8）Rotor rotary electrification, send electricity through control system module（4）To battery pack after rectification（5）Charging；
Engine（3）When failure, empty or the pure electric drive of needs, the battery pack（5）Voltage through control system module
（4）To motor after inversion（8）Power supply, with control direction small machine（7）The common lift provided needed for helicopter.
5. oil electricity according to claim 1 mixes heavily loaded multirotor helicopter, it is characterised in that：The frame（2）Including
One bottom plate（21）With the support frame fixed with bottom plate（22）；The fuel engines module（3）, battery pack（5）And control system
Module（4）On the bottom plate, support frame as described above（22）With fuel engines module（3）Upper end be fixed with mounting bracket
（23）, the mounting bracket（23）With multiple with motor（8）Rotating shaft centered on the end that is uniformly arranged, the control direction is small
Motor（7）Installed in the end；The frame（2）Also include being connected to mounting bracket（23）With gear fixed mount（16）Between
Fixed mount（24）.
6. oil electricity according to claim 2 mixes heavily loaded multirotor helicopter, it is characterised in that：The upper rotor gear
（15）With lower rotor gear（17）Modulus and number of teeth all same；The multiple control direction small machine（7）Direction of rotation include
Turn clockwise and rotate counterclockwise, the control direction small machine to turn clockwise with rotate counterclockwise（7）It is arranged at intervals.
7. oil electricity according to claim 6 mixes heavily loaded multirotor helicopter, it is characterised in that：The small electricity of control direction
Machine（7）Number be even number more than or equal to 4.
8. oil electricity according to claim 2 mixes heavily loaded multirotor helicopter, it is characterised in that：The upper rotor gear
（15）, lower rotor gear（17）And tumbler gear（14）It is angular wheel.
9. oil electricity according to claim 4 mixes heavily loaded multirotor helicopter, it is characterised in that：Support frame as described above（22）、
Mounting bracket（23）, fixed mount（24）It is pipe frame structure.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109263979A (en) * | 2018-10-26 | 2019-01-25 | 珠海银通无人机科技有限公司 | A kind of dual redundant power aerial vehicle |
| CN110481780A (en) * | 2019-09-11 | 2019-11-22 | 北方民族大学 | Hybrid power unmanned plane and its control method with two kinds of rotors |
| GB2578083A (en) * | 2018-06-06 | 2020-04-22 | Prior Stephen | An unmanned aerial vehicle |
| CN112009695A (en) * | 2019-05-30 | 2020-12-01 | 李秋辐 | Circumferential jet engine device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105539828A (en) * | 2015-12-08 | 2016-05-04 | 陈蜀乔 | Petrol-electric hybrid multi-rotor aerial vehicle capable of self electricity generation |
| CN105644776A (en) * | 2016-03-17 | 2016-06-08 | 秦建法 | Multi-rotor unmanned helicopter |
| CN106114842A (en) * | 2016-07-27 | 2016-11-16 | 西安交通大学 | A kind of oil electricity mixing coaxial dual-rotor helicopter and using method thereof |
| CN207257981U (en) * | 2017-09-05 | 2018-04-20 | 南京荣骏科技发展有限公司 | A kind of heavily loaded multirotor helicopter of oil electricity mixing |
-
2017
- 2017-09-05 CN CN201710791210.0A patent/CN107458595A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105539828A (en) * | 2015-12-08 | 2016-05-04 | 陈蜀乔 | Petrol-electric hybrid multi-rotor aerial vehicle capable of self electricity generation |
| CN105644776A (en) * | 2016-03-17 | 2016-06-08 | 秦建法 | Multi-rotor unmanned helicopter |
| CN106114842A (en) * | 2016-07-27 | 2016-11-16 | 西安交通大学 | A kind of oil electricity mixing coaxial dual-rotor helicopter and using method thereof |
| CN207257981U (en) * | 2017-09-05 | 2018-04-20 | 南京荣骏科技发展有限公司 | A kind of heavily loaded multirotor helicopter of oil electricity mixing |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2578083A (en) * | 2018-06-06 | 2020-04-22 | Prior Stephen | An unmanned aerial vehicle |
| GB2578083B (en) * | 2018-06-06 | 2020-11-25 | Hybrid Drones Ltd | An unmanned aerial vehicle |
| CN109263979A (en) * | 2018-10-26 | 2019-01-25 | 珠海银通无人机科技有限公司 | A kind of dual redundant power aerial vehicle |
| CN112009695A (en) * | 2019-05-30 | 2020-12-01 | 李秋辐 | Circumferential jet engine device |
| CN110481780A (en) * | 2019-09-11 | 2019-11-22 | 北方民族大学 | Hybrid power unmanned plane and its control method with two kinds of rotors |
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Application publication date: 20171212 |