CN110450962A - Oil electric mixed dynamic unmanned plane and its working method - Google Patents
Oil electric mixed dynamic unmanned plane and its working method Download PDFInfo
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- CN110450962A CN110450962A CN201910768216.5A CN201910768216A CN110450962A CN 110450962 A CN110450962 A CN 110450962A CN 201910768216 A CN201910768216 A CN 201910768216A CN 110450962 A CN110450962 A CN 110450962A
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- 238000000034 method Methods 0.000 title claims abstract description 11
- 230000005540 biological transmission Effects 0.000 claims abstract description 99
- 230000001360 synchronised effect Effects 0.000 claims abstract description 44
- 230000000712 assembly Effects 0.000 claims abstract description 30
- 238000000429 assembly Methods 0.000 claims abstract description 30
- 239000003921 oil Substances 0.000 description 22
- 239000000446 fuel Substances 0.000 description 15
- 230000005611 electricity Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000005265 energy consumption Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 244000273618 Sphenoclea zeylanica Species 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000012512 characterization method Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 210000004209 hair Anatomy 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000010200 validation analysis 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
- B64C27/08—Helicopters with two or more rotors
-
- 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
-
- 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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
- B64D35/06—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors the propellers or rotors being counter-rotating
-
- 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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/08—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
-
- 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
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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)
- Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)
Abstract
The present invention relates to oil electric mixed dynamic unmanned plane and its working methods, the unmanned plane includes casing, oil electric mixed dynamic structure, frame assembly and rotor assemblies, oil electric mixed dynamic structure is placed in casing, oil electric mixed dynamic structure includes active force component and secondary Power Component, active force component is connect by the first transmission component with secondary Power Component, active force component is connect by the second transmission component with frame assembly, and frame assembly is connect by third transmission component with rotor assemblies；After active force component output power, secondary Power Component work and frame assembly work are driven, frame assembly drives rotor assemblies work.The present invention realizes that cruising ability is strong, and using synchronous belt transfer mode, structure is simple, always consumes energy low.
Description
Technical field
The present invention relates to unmanned planes, more specifically refer to oil electric mixed dynamic unmanned plane and its working method.
Background technique
Referred to as " unmanned plane ", english abbreviation is " UAV " to UAV, is using radio robot and to provide for oneself
The not manned aircraft of presetting apparatus manipulation, or fully or intermittently automatically operated by car-mounted computer.
The multi-rotor unmanned aerial vehicle of commercial market at present, Duo Yichun electric motor or pure fuel engines provide power, pure
Electric motor stability is high, it is easy to operate, using wide model, but cruising ability is poor.And pure fuel engines is because of more hairs
It is poor that motivation works at the same time consistency, it is difficult to ensure that each rotor revolving speed is consistent, often influences the stabilization of unmanned plane during flying, causes one
Fixed defect, it is overall all in theoretical validation rank although having there is some novel rotor fuel oil unmanned plane structures on the market at present
Section, design is complicated, fuel engines vibratility is larger, and body design is overweight, and total energy consumption is not high, and overall performance is not good enough.
Therefore, it is necessary to design a kind of new unmanned plane, realize that cruising ability is strong, structure is simple, always consumes energy low.
Summary of the invention
It is an object of the invention to overcome the deficiencies of existing technologies, oil electric mixed dynamic unmanned plane and its work side are provided
Method.
To achieve the above object, the invention adopts the following technical scheme: oil electric mixed dynamic unmanned plane, including casing, oil
Electricity mixed power structure, frame assembly and rotor assemblies, the oil electric mixed dynamic structure are placed in the casing, the oil
Electricity mixed power structure includes that active force component and secondary Power Component, the active force component pass through the first transmission component and institute
Secondary Power Component connection is stated, the active force component is connect by the second transmission component with the frame assembly, the fuselage group
Part is connect by third transmission component with the rotor assemblies；After the active force component output power, the pair is driven
Power Component work and frame assembly work, the frame assembly driving rotor assemblies work.
Its further technical solution are as follows: first transmission component includes the first driving wheel, the first driven wheel and first
Synchronous belt, first driving wheel are connect with the active force component, and first driven wheel is connect with the secondary Power Component,
The active force component and the secondary Power Component pass through the described first synchronous band connection.
Its further technical solution are as follows: the frame assembly includes rack and fuselage transmission component, the fuselage transmission
Component is connected in the rack, and the fuselage transmission component includes driving shaft, fuselage driving wheel, the first transmission gear and
Two transmission gears, the fuselage driving wheel and first transmission gear respectively with the active axis connection, the fuselage master
Driving wheel is connect with second transmission component, and second transmission gear is engaged with first transmission gear.
Its further technical solution are as follows: be inserted with driven shaft in second transmission gear.
Its further technical solution are as follows: the frame assembly further includes tensioning spring and tensioning wheel, is set in the rack
Have sliding slot and fixed link, the sliding slot is built-in with slide bar, and the slide bar is connect with the tensioning wheel, the slide bar with it is described solid
The tensioning spring is connected between fixed pole, the tensioning wheel is abutted with second transmission component.
Its further technical solution are as follows: second transmission component includes the second driving wheel and the second synchronous belt, described
With the fuselage driving wheel by the described second synchronous band connection, the tensioning wheel supports second driving wheel with second synchronous belt
It connects.
Its further technical solution are as follows: the driving shaft and the driven shaft respectively by the third transmission component with
The rotor assemblies connection.
Its further technical solution are as follows: the rotor assemblies include left side rotor, left paddle seat, right side rotor, right paddle seat, a left side
Moving axis and right moving axis, the left side rotor are connect by left paddle seat with the rack, the right side rotor by right paddle seat with
The rack connection, the left side rotor are connect with the left moving axis, and the right side rotor is connect with the right moving axis, the left side
Moving axis and the right moving axis are connect with the third transmission component respectively.
Its further technical solution are as follows: the third transmission component includes third driving wheel, third driven wheel and third
It is connected separately with the third driving wheel on synchronous belt, the driving shaft and the driven shaft, the left moving axis and described
The third driven wheel is connected separately on right moving axis, the third driving wheel is connected with the driven wheel by third synchronous belt
It connects；The rack is equipped with limit pulley blocks, and the limit pulley blocks include the first limit pulley and the second limit pulley, institute
It states the first limit pulley and the second limit pulley is placed in the two sides of the third synchronous belt.
The present invention also provides the working methods of oil electric mixed dynamic unmanned plane, comprising:
After the active force component output power, the secondary Power Component work and the frame assembly work are driven
Make, the frame assembly driving rotor assemblies work.
Compared with the prior art, the invention has the advantages that: the present invention is by setting fuel engines as main power pack
Part, generator are used as from Power Component, are passed to the partial power of active force component from power packages using the first transmission component
Another part power of active force component is transferred to needed for meeting other power supplies of unmanned plane using the second transmission component by part
Frame assembly, then the power of frame assembly is transferred to rotor assemblies by third transmission component, it is provided for the rotation of rotor assemblies
Power realizes that cruising ability is strong, and using synchronous belt transfer mode, structure is simple, always consumes energy low.
The invention will be further described in the following with reference to the drawings and specific embodiments.
Detailed description of the invention
Technical solution in order to illustrate the embodiments of the present invention more clearly, below will be to needed in embodiment description
Attached drawing is briefly described, it should be apparent that, drawings in the following description are some embodiments of the invention, general for this field
For logical technical staff, without creative efforts, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is the schematic perspective view one for the oil electric mixed dynamic unmanned plane that the specific embodiment of the invention provides；
Fig. 2 is the partial enlargement diagram at Figure 1A；
Fig. 3 is the (removal of schematic perspective view two for the oil electric mixed dynamic unmanned plane that the specific embodiment of the invention provides
Left connecting rod and tensioning spring)；
Fig. 4 is the partial enlargement diagram at Fig. 3 B；
Fig. 5 is the schematic perspective view for the frame assembly that the specific embodiment of the invention provides；
Fig. 6 is the configuration schematic diagram (removal tensioning spring) for the frame assembly that the specific embodiment of the invention provides.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawing and specific implementation
Invention is further described in detail for mode.
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, those skilled in the art's every other implementation obtained without creative efforts
Example, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside", " up time
The orientation or positional relationship of the instructions such as needle ", " counterclockwise " is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of
The description present invention and simplified description, rather than the device or element of indication or suggestion meaning must have a particular orientation, with spy
Fixed orientation construction and operation, therefore be not considered as limiting the invention.
In addition, term " first ", " second " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Define " first " as a result, the feature of " second " can be expressed or
Implicitly include one or more of the features.In the description of the present invention, the meaning of " plurality " is two or more,
Unless otherwise specifically defined.
In the present invention unless specifically defined or limited otherwise, term " installation ", " connected ", " connection ", " fixation " etc.
Term shall be understood in a broad sense, for example, it may be connection, may be a detachable connection, or integral；It can be mechanical connection,
It is also possible to be electrically connected；It can be directly connected, can also can be inside two elements indirectly connected through an intermediary
The interaction relationship of connection or two elements.For the ordinary skill in the art, it can manage as the case may be
Solve the concrete meaning of above-mentioned term in the present invention.
In the present invention unless specifically defined or limited otherwise, fisrt feature second feature "upper" or "lower"
It may include that the first and second features directly contact, also may include that the first and second features are not direct contacts but pass through it
Between other characterisation contact.Moreover, fisrt feature includes the first spy above the second feature " above ", " above " and " above "
Sign is right above second feature and oblique upper, or is merely representative of first feature horizontal height higher than second feature.Fisrt feature exists
Second feature " under ", " lower section " and " following " include that fisrt feature is directly below and diagonally below the second feature, or is merely representative of
First feature horizontal height is less than second feature.
In the description of this specification, reference term " one embodiment ", " some embodiments ", " example ", " specifically show
The description of example " or " some examples " etc. means specific features, structure, material or spy described in conjunction with this embodiment or example
Point is included at least one embodiment or example of the invention.In the present specification, schematic expression of the above terms are not
It is interpreted as that identical embodiment or example must be directed to.Moreover, particular features, structures, materials, or characteristics described
It can be combined in any suitable manner in any one or more of the embodiments or examples.In addition, those skilled in the art can
Different embodiments or examples described in this specification to be combined.
Specific embodiment as shown in figs. 1 to 6, oil electric mixed dynamic unmanned plane provided in this embodiment, can be used in
In unmanned scene, realize that cruising ability is strong, structure is simple, always consumes energy low.
Referring to Fig. 1, the oil electric mixed dynamic unmanned plane, including casing (not shown), oil electric mixed dynamic structure,
Frame assembly and rotor assemblies, oil electric mixed dynamic structure are placed in casing, and oil electric mixed dynamic structure includes main power pack
Part 11 and secondary Power Component 12, active force component 11 are connect by the first transmission component with secondary Power Component 12, main power pack
Part 11 is connect by the second transmission component with frame assembly, and frame assembly is connect by third transmission component with rotor assemblies；It is logical
After crossing 11 output power of active force component, the secondary work of Power Component 12 and frame assembly work, frame assembly driving rotation are driven
Wing component operation.
In the present embodiment, active force component 11 includes fuel engines, includes generator from Power Component；In other realities
Example is applied, it can be other energy conversions from Power Component that above-mentioned active force component 11, which can also be other power sources,.
In the present embodiment, fuel engines is as active force, after the starting of fuel engines refuelling, the active force component
11 output shaft high speed rotation, a part drives the rotor high speed rotation of generator by the first transmission component, according to magnetic induction line
Principle exports DC voltage, powers for the other electricity systems of unmanned plane；Fuel engines another part power passes through the second transmission
Component is driven to frame assembly, and frame assembly drives the rotation of rotary-wing transmission group.
In one embodiment, Fig. 1 and Fig. 2 are please referred to, above-mentioned secondary Power Component 12 is connected to casing by mounting base 13
It is interior.
In one embodiment, referring to Fig. 2, the first above-mentioned transmission component includes the first driving wheel 41, the first driven wheel
43 and first synchronous belt 42, the first driving wheel 41 connect with active force component 11, the first driven wheel 43 and secondary Power Component 12
Connection, active force component 11 and secondary Power Component 12 are connected by the first synchronous belt 42.
Specifically, the first driving wheel 41 is connected on the output shaft of above-mentioned active force component 11, secondary Power Component 12
It is connected with the first driven wheel 43 on input shaft, the first driving wheel 41 and the first driven wheel 43 are connected using the first synchronous belt 42
Mode realizes power transmission, and the transmission using the first synchronous belt 42 is flexible, and it is larger to be suitable for unmanned machine vibration of fuel power etc.
In environment, stability is high, and structure is simple, always consumes energy low.
In one embodiment, Fig. 5 and Fig. 6 are please referred to, above-mentioned frame assembly includes rack 21 and fuselage transmission component,
Fuselage transmission component is connected in rack 21, and fuselage transmission component includes driving shaft 28, fuselage driving wheel 53, the first transmission gear
25 and second transmission gear 26, fuselage driving wheel 53 and the first transmission gear 25 connect respectively with driving shaft 28, fuselage master
Driving wheel 53 is connect with the second transmission component, and the second transmission gear 26 is engaged with the first transmission gear 25.
In addition, being inserted with driven shaft 29 in the second transmission gear 26.
Frame assembly and oil electric mixed dynamic structure pass through the second transmission component realization power transmission；It is set inside frame assembly
Gear drive group is set, which includes the first transmission gear 25 and the second transmission gear 26, the first transmission gear 25
And 26 engaged transmission of the second transmission gear, contrary, revolving speed is identical, thus drives rotor assemblies rotation, rotor assemblies packet
Include left side rotor 31 and right side rotor 34, the first transmission gear 25 and corresponding drive left side 31 He of rotor of the second transmission gear 26
Right side rotor 34 rotates, and left side rotor 31 is contrary with the rotor of right side rotor 34, offsets unmanned plane during flying torsion, improves nothing
Man-machine flight stability.
In one embodiment, referring to Fig. 2, above-mentioned frame assembly further includes tensioning spring 23 and tensioning wheel 24, machine
Frame 21 is equipped with sliding slot 211 and fixed link 242, which is fixedly connected in rack 21, and sliding slot 211 is built-in with cunning
Bar 241, slide bar 241 can slide in sliding slot 211, and slide bar 241 is connect with tensioning wheel 24, is connected between slide bar 241 and fixed link 242
It is connected to tensioning spring 23, tensioning wheel 24 is abutted with the second transmission component.
Specifically, the top and lower section of above-mentioned tensioning wheel 24 are connected separately with tensioning spring 23, second synchronous belt
52 are placed between two tensioning springs 23.One end of tensioning spring 23 is connect with slide bar 241, the other end of tensioning spring 23 and solid
Fixed pole 242 connects.
Specifically, the second transmission component includes the second driving wheel 51 and the second synchronous belt 52, the second driving wheel 51 and machine
Body driving wheel 53 is connected by the second synchronous belt 52, and tensioning wheel 24 is abutted with the second synchronous belt 52,
In addition, the second above-mentioned transmission component further includes fuselage driving wheel 53.
The frame assembly being connected with oil electric mixed dynamic structure is fixed, but when oil electric mixed dynamic arrangement works
Vibratility is larger, and when the two is mutually driven work, the second synchronous belt 52 is tensioned inconsistent, influences transmission efficiency or even vibrated
Big second synchronous belt, 52 transmission slip, causes rotor assemblies moment stall, causes certain security risk to unmanned plane during flying, therefore
Tensioning wheel 24 and tensioning spring 23, which is arranged, to be occurred to avoid the slipping phenomenon in 52 transmission process of the second synchronous belt, when second
When skidding in 52 transmission process of synchronous belt, tensioning wheel 24 can be made to slide under the action of the second synchronous belt 52, and then driven
Slide bar 241 slides, and Flexible change occurs for tensioning spring 23, and then generates elastic force, and to drive tensioning wheel 24 to reset, drive second is same
It walks band 52 to reset, improves the safety and reliability of entire unmanned plane during flying.
In one embodiment, referring to Fig. 5, above-mentioned 21 upper end of rack is connected with fuselage hatchcover 22, fuselage hatchcover 22 with
The first cavity is enclosed between rack 21, the second above-mentioned synchronous belt 52, tensioning wheel 24, tensioning spring 23, fuselage are actively
Wheel 53 is respectively placed in first cavity.
In one embodiment, Fig. 3 and Fig. 4 are please referred to, above-mentioned driving shaft 28 and driven shaft 29 are passed by third respectively
Dynamic component is connect with rotor assemblies.
The number of third transmission component is two, and driving shaft 28 is connected by one of third transmission component and rotor assemblies
It connects, driven wheel is connect by another third transmission component with rotor assemblies, and then is realized and passed through two thirds by frame assembly
Transmission component drives rotor assemblies work.
In one embodiment, Fig. 3 to Fig. 4 is please referred to, rotor assemblies include left side rotor 31, left paddle seat 32, right side rotor
34, right paddle seat 35, left moving axis 37 and right moving axis 38, left side rotor 31 are connect by left paddle seat 32 with rack 21, right side rotor
34 are connect by right paddle seat 35 with rack 21, and left side rotor 31 is connect with left moving axis 37, and right side rotor 34 is connect with right moving axis 38,
Left moving axis 37 and right moving axis 38 are connect with third transmission component respectively.
Power is driven to left side rotor 31 and right side rotor 34 by third transmission component by frame assembly respectively, with driving
Left side rotor 31 and right side rotor 34 work, and to realize the rotation of left side rotor 31 and right side rotor 34, drive unmanned plane
Flight.
Specifically, above-mentioned left paddle seat 32 is connect by left connecting rod 33 with rack 21, and above-mentioned right paddle seat 35 passes through the right side
Connecting rod 36 is connect with rack 21.
Above-mentioned left connecting rod 33 and right connecting rod 36 is hollow stem, in order to which third synchronous belt 62 places left connecting rod 33
In right connecting rod 36.
In one embodiment, above-mentioned left side rotor 31 and right side rotor 34 are symmetrical, only provide unmanned plane lift and make
With not providing unmanned plane pitching, rolling and yaw.The power of left side rotor 31 and right side rotor 34 is defeated by active force component 11
Shaft high speed rotation provides power by multiple groups toothed belt transmission.
In addition, above-mentioned rotor assemblies further include big propeller aircraft, above-mentioned left side rotor 31 is with left moving axis 37 can
Detaching structure connection, the detachable structure can be the fasteners such as bolt, and above-mentioned right side rotor 34 is removable with right moving axis 38
Structure connection is unloaded, which can be the fasteners such as bolt.Big propeller aircraft can also be using fasteners such as bolts
It is connected on left moving axis 37 and right moving axis 38, according to mission payload difference, left side rotor 31, right side rotor 34 and big rotor spiral shell
Paddle is revolved, can be replaced, revolving speed has multiple groups toothed belt transmission ratio to set, and revolving speed is different, and pulling force is of different sizes, according to the actual situation
Depending on, realize the replacement of different propellers.
In one embodiment, please refer to Fig. 3 and Fig. 4, above-mentioned third transmission component include third driving wheel 61, third from
Third driving wheel 61, left moving axis 37 are connected separately on driving wheel 63 and third synchronous belt 62, driving shaft 28 and driven shaft 29
And third driven wheel 63 is connected separately on right moving axis 38, third driving wheel 61 and driven wheel are connected by third synchronous belt 62
It connects.
The power between third driving wheel 61 and third driven wheel 63 is carried out using third synchronous belt 62 to transmit, it is opposite to connect
Bar gear drive, flexibility is preferable, runs under particularly suitable fuel engines vibration environment.
In one embodiment, Fig. 5 and Fig. 6 are please referred to, above-mentioned rack 21 is equipped with limit pulley blocks, limits pulley blocks packet
The first limit pulley 24 and the second limit pulley 27 are included, it is same that the first limit pulley 24 and the second limit pulley 27 are placed in third
Walk the two sides of band 62.Using the first limit pulley 24 and the second limit 27 limits synchronization V belt translation path of pulley, high speed is prevented
Transmission is collided with other structures part, and the second synchronous belt 52 is caused to wear and influence safety.
The first limit pulley 24 and the second limit pulley 27 are connected in rack 21 by vertical bar respectively.
Specifically, the number for limiting pulley blocks is two groups, certainly, in other embodiments, of above-mentioned limit pulley blocks
Number can be three groups or other numerical value.
In one embodiment, it referring to Fig. 4, being equipped with left limit pulley blocks in above-mentioned left paddle seat 32, is set in right paddle seat 35
There are right limit pulley blocks 39, and left limit pulley blocks abut third synchronous belt 62, and right limit pulley blocks 39 abut third
Synchronous belt 62 limits 62 drive path of third synchronous belt, prevents high-speed drive from colliding with other structures part, causes third same
It walks the abrasion of band 62 and influences safety.
In one embodiment, the second cavity is equipped in above-mentioned rack 21, which is connected to the second cavity.It is above-mentioned
Fuselage transmission component be placed in second cavity.
One fuel engines is as active force component 11, the output shaft of active force component 11 high speed rotation at work.
A part of transmission Power Component 12 of power is generator by output shaft, is the other electricity system power supplies of entire unmanned plane, output
Power another part is driven frame assembly by axis, and frame assembly is by the first transmission gear 25, the second transmission gear 26, third master
Power is transferred to rotor assemblies by driving wheel 61, third driven wheel 63 and third synchronous belt 62 respectively, be left side rotor 31 and
The rotation of right side rotor 34 provides lift, only needs a fuel engines loading capacity big, as long as fuel is abundant under theoretical case, nothing
Man-machine cruise duration will be very long, while having the advantages that structure is simple, control is simple and low energy consumption.
In addition, turning in frame assembly and left paddle seat 32, right paddle seat 35 setting limit pulley with corresponding synchronous belt
It is dynamic；It prevents from contacting with each other in corresponding synchronous belt high speed rotation with left connecting rod 33 and right connecting rod 36, influences safety.Using
Toothed belt transmission, simple structure and high transmission efficiency are driven relative to connecting rod hardness is similar to, and toothed belt transmission is flexible, is applicable in
In unmanned machine vibration of fuel power etc. compared in overall situation.
Above-mentioned oil electric mixed dynamic unmanned plane, by setting fuel engines as active force component 11, generator is made
The partial power of active force component 11 to be passed to from Power Component using the first transmission component, to meet from Power Component
Needed for other power supplies of unmanned plane, another part power of active force component 11 is transferred to fuselage group using the second transmission component
Part, then the power of frame assembly is transferred to rotor assemblies by third transmission component, it is the powered rotation of rotor assemblies, it is real
Existing cruising ability is strong, and using synchronous belt transfer mode, structure is simple, always consumes energy low.
In one embodiment, the working method of oil electric mixed dynamic unmanned plane is additionally provided, comprising:
After 11 output power of active force component, the secondary work of Power Component 12 and frame assembly work, fuselage are driven
The work of Component driver rotor assemblies.
It should be noted that it is apparent to those skilled in the art that, above-mentioned oil electric mixed dynamic nobody
The specific implementation process of the working method of machine can refer to the corresponding description in aforementioned oil electric mixed dynamic unmanned aerial vehicle example,
For convenience of description and succinctly, details are not described herein.
It is above-mentioned that technology contents of the invention are only further illustrated with embodiment, in order to which reader is easier to understand, but not
It represents embodiments of the present invention and is only limitted to this, any technology done according to the present invention extends or recreation, by of the invention
Protection.Protection scope of the present invention is subject to claims.
Claims (10)
1. oil electric mixed dynamic unmanned plane, which is characterized in that including casing, oil electric mixed dynamic structure, frame assembly and rotation
Wing component, the oil electric mixed dynamic structure are placed in the casing, and the oil electric mixed dynamic structure includes active force component
And secondary Power Component, the active force component are connect by the first transmission component with the secondary Power Component, the active force
Component is connect by the second transmission component with the frame assembly, and the frame assembly passes through third transmission component and the rotor
Component connection；After the active force component output power, the secondary Power Component work and the frame assembly are driven
Work, the frame assembly driving rotor assemblies work.
2. oil electric mixed dynamic unmanned plane according to claim 1, which is characterized in that first transmission component includes the
One driving wheel, the first driven wheel and the first synchronous belt, first driving wheel are connect with the active force component, and described first
Driven wheel is connect with the secondary Power Component, and the active force component and the secondary Power Component pass through first synchronous belt
Connection.
3. oil electric mixed dynamic unmanned plane according to claim 2, which is characterized in that the frame assembly include rack with
And fuselage transmission component, the fuselage transmission component are connected in the rack, the fuselage transmission component includes driving shaft, machine
Body driving wheel, the first transmission gear and the second transmission gear, the fuselage driving wheel and first transmission gear difference
With the active axis connection, the fuselage driving wheel is connect with second transmission component, second transmission gear with it is described
The engagement of first transmission gear.
4. oil electric mixed dynamic unmanned plane according to claim 3, which is characterized in that plugged in second transmission gear
There is driven shaft.
5. oil electric mixed dynamic unmanned plane according to claim 3 or 4, which is characterized in that the frame assembly further includes
Tensioning spring and tensioning wheel, the rack are equipped with sliding slot and fixed link, and the sliding slot is built-in with slide bar, the slide bar with
Tensioning wheel connection, is connected with the tensioning spring between the slide bar and the fixed link, the tensioning wheel and described the
Two transmission components abut.
6. oil electric mixed dynamic unmanned plane according to claim 5, which is characterized in that second transmission component includes the
Two driving wheels and the second synchronous belt, second driving wheel and the fuselage driving wheel by the described second synchronous band connection,
The tensioning wheel is abutted with second synchronous belt.
7. oil electric mixed dynamic unmanned plane according to claim 4, which is characterized in that the driving shaft and described driven
Axis is connect by the third transmission component with the rotor assemblies respectively.
8. oil electric mixed dynamic unmanned plane according to claim 7, which is characterized in that the rotor assemblies include left side spin
The wing, left paddle seat, right side rotor, right paddle seat, left moving axis and right moving axis, the left side rotor are connected by left paddle seat and the rack
It connects, the right side rotor is connect by right paddle seat with the rack, and the left side rotor is connect with the left moving axis, the right side
Rotor is connect with the right moving axis, and the left moving axis and the right moving axis are connect with the third transmission component respectively.
9. oil electric mixed dynamic unmanned plane according to claim 8, which is characterized in that the third transmission component includes the
Described is connected separately on three driving wheels, third driven wheel and third synchronous belt, the driving shaft and the driven shaft
Be connected separately with the third driven wheel on three driving wheels, the left moving axis and the right moving axis, the third driving wheel with
The driven wheel passes through the synchronous band connection of third；The rack is equipped with limit pulley blocks, and the limit pulley blocks include first
Pulley and the second limit pulley are limited, it is synchronous that the first limit pulley and the second limit pulley are placed in the third
The two sides of band.
10. the working method of oil electric mixed dynamic unmanned plane characterized by comprising
After the active force component output power, the secondary Power Component work and frame assembly work are driven,
The frame assembly driving rotor assemblies work.
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