CN109677599A - DCB Specimen unmanned plane dynamical system - Google Patents
DCB Specimen unmanned plane dynamical system Download PDFInfo
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- CN109677599A CN109677599A CN201910135253.2A CN201910135253A CN109677599A CN 109677599 A CN109677599 A CN 109677599A CN 201910135253 A CN201910135253 A CN 201910135253A CN 109677599 A CN109677599 A CN 109677599A
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- 238000005183 dynamical system Methods 0.000 title claims abstract description 21
- 230000005540 biological transmission Effects 0.000 claims abstract description 53
- 230000007246 mechanism Effects 0.000 claims abstract description 51
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 9
- 230000008878 coupling Effects 0.000 claims description 8
- 238000010168 coupling process Methods 0.000 claims description 8
- 238000005859 coupling reaction Methods 0.000 claims description 8
- 241000274582 Pycnanthus angolensis Species 0.000 claims description 7
- 239000011087 paperboard Substances 0.000 claims description 7
- 230000007704 transition Effects 0.000 claims description 6
- 229910000831 Steel Inorganic materials 0.000 claims description 2
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- 230000015556 catabolic process Effects 0.000 abstract description 5
- 238000010304 firing Methods 0.000 abstract description 2
- 239000003921 oil Substances 0.000 description 26
- 238000007789 sealing Methods 0.000 description 11
- 230000017525 heat dissipation Effects 0.000 description 8
- 230000000694 effects Effects 0.000 description 7
- 238000010586 diagram Methods 0.000 description 6
- 230000008901 benefit Effects 0.000 description 5
- 230000006870 function Effects 0.000 description 4
- 230000013011 mating Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 3
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- 230000007812 deficiency Effects 0.000 description 2
- 239000000428 dust Substances 0.000 description 2
- 210000003746 feather Anatomy 0.000 description 2
- 239000002828 fuel tank Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000010687 lubricating oil Substances 0.000 description 2
- 239000000123 paper Substances 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 206010000369 Accident Diseases 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Details Of Gearings (AREA)
Abstract
The invention discloses a kind of DCB Specimen unmanned plane dynamical system, including two power take-off mechanisms, the synchronizing shaft and helicopter deceleration device being sequentially connected with the power take-off mechanism.The present invention realizes two engines by pulley transmission mechanism or one group and vehicle deceleration mechanism and output speed reducer structure and vehicle, improves the gross output of system, two engines can be worked at the same time, can also be worked independently.When two simultaneous firings, if a wherein engine breakdown, it can disengage with transmission system and connect, and be continued to drive transmission system work by another engine.Since the probability that two engines break down simultaneously is much smaller than the probability of an engine breakdown, the reliability of system is thus substantially increased.
Description
Technical field
The invention belongs to air vehicle technique fields, and in particular to a kind of DCB Specimen unmanned plane dynamical system.
Background technique
Currently, multi-rotor unmanned aerial vehicle on the market is mainly fixed pitch electric drive, due to battery energy density much
It lower than fuel oil, is limited by battery, the more gyroplanes of fixed pitch motor driven are mainly used for camera shooting of taking photo by plane, and cruise duration is short, institute
Can load-carrying it is light-weight, be unable to satisfy the other kinds of demand of civilian unmanned plane, such as: high-altitude rescue people fire fighting, pesticide spraying,
Small space transports weight etc..
With technology progress, there is feather oil and move quadrotor drone, breaches load-carrying and cruise duration
Limitation, but it is mainly pulley drive, monomotor setting, this biography that currently used feather oil, which moves quadrotor drone,
Dynamic type, low efficiency, flight stability are poor, and are arranged for monomotor, once engine breaks down, rotor can not rotate,
Aircraft accident will be will cause.
For this status, needs to propose that a kind of new double hair oil move unmanned plane, keep rotor wing unmanned aerial vehicle operation more flat
Surely, more efficient, and if engine break down, have ready conditions and carry out the continuation of the journey of short time, guarantee unmanned plane stable landing.
Chinese patent CN107010229A discloses a kind of double hair oil and moves unmanned plane, including rack, is uniformly distributed circumferentially
Multiple rotors, two engines for driving multiple edges of a wing to rotate simultaneously, for by two engines outputs
Power coupling after distribution to multiple rotors transmission system, solved on partial extent multi-rotor unmanned aerial vehicle load-carrying and
The problems such as continuation of the journey, low efficiency and poor flight stability.
But the dependence and skiving wheel that two engines carry out and when machine is simple are coupled, due to two engines
Start asynchronous and inconsistent revolving speed reason, serious impact can be caused to transmission system, and lead to reality output function
Rate decline.And there is also stress concentrations for rotor shaft, the deficiencies of being easily deformed.
Summary of the invention
It is an object of the invention to overcome the deficiencies of the prior art and provide a kind of DCB Specimen unmanned plane dynamical system, this pairs
The advantages of rotor wing unmanned aerial vehicle dynamical system has principle simple and easy to do, high reliablity.
The present invention is achieved by the following technical solutions:
A kind of DCB Specimen unmanned plane dynamical system, including two power take-off mechanisms are passed with the power take-off mechanism
The synchronizing shaft and helicopter deceleration device of dynamic connection；
The helicopter deceleration device includes main box, the rotor that can run through the main box up and down with the relative rotation
Axis, the fixed bevel gear being set in the rotor shaft, and the conical tooth shaft cooperated with the bevel gear, the main tank
Body includes main frame and the lower boxboard for being fixed at the main frame bottom, is provided with use or more in the rotor shaft
The lower flange of the limit bevel gear, the centre bore top of the bevel gear and the rotor shaft are interference fitted, middle part
With the rotor shaft spline fitted, lower part and the rotor shaft transition fit, the power end of the conical tooth shaft with it is synchronous
Axis correspondence is fixedly connected by shaft coupling.
Driving wheel, the power take-off mechanism and the biography are provided with by freewheel clutch on the synchronizing shaft
The transmission connection of driving wheel belt.
Including simultaneously vehicle deceleration mechanism and output speed reducer structure, two power take-off mechanisms are symmetrically disposed in and vehicle
Deceleration mechanism two sides；
Described and vehicle deceleration mechanism includes under casing body, can be rotatably set among the rod-shaped or tubular under casing body and passes
Dynamic portion, the base cone gear being fixedly connected with the intermediate transmission portion and two symmetrically arranged two conical tooth shafts, it is described
The cone increment of conical tooth shaft and the base cone gear engaged transmission, the under casing body is extended simultaneously in the shaft end of the conical tooth shaft
It is connect by freewheel clutch with the pto shaft drive of the power take-off mechanism.
The intermediate transmission portion is provided with upper limit ring above vertical steel bracket axis, is determined by the upper cover plate of the under casing body
The upper limit bearing of position is mutually pushed up with the upper limit ring to be held, between the bottom end in the intermediate transmission portion and the lower plate of under casing body
It is provided with lower limit bearing.
The under casing body further includes the support tube being fixedly connected with the upper cover plate, the intermediate transmission portion to branch
It is pierced by support cylinder and bearing is set in its top.
The output speed reducer structure includes cabinet, through the cabinet and in the defeated of the rotatable cooperation of cabinet
Shaft, described and vehicle deceleration mechanism intermediate transmission portion go deep into being sequentially connected in the cabinet and with the output shaft.
The lower flange top be formed with upper limit mechanism cooperation upper flange, the upper limit mechanism include with
The top board that the main frame is fixedly connected, and top board and convex intermarginal bearing are set.
It further include the small box being fixedly connected with the main frame side, the input shaft and the small box can
Rotatable engagement, the small box positioning relatively described by former and later two bearings of the shaft of the conical tooth shaft, the small box
Oil sealing is provided between the shaft of conical tooth shaft.
It further include being set in the support tube that outside the rotor shaft and bottom end is fixedly connected with the main frame, it is described
Support tube at the top of be rotatably connected with the rotor shaft by bearing.
The bevel gear of the helicopter deceleration device and the crossed axis angle of conical tooth shaft are 80 ° -90 °.
The advantages and benefits of the present invention are:
The present invention realizes two engines by pulley transmission mechanism or one group and vehicle deceleration mechanism and output speed reducer structure
And vehicle, improve the gross output of system, two engines can be worked at the same time, can also be worked independently.Start when two
When machine works at the same time, if a wherein engine breakdown, it can disengage with transmission system and connect, and be started by another
Machine continues to drive transmission system work.Since event occurs for much smaller than one engine of probability that two engines break down simultaneously
The probability of barrier thus substantially increases the reliability of system.The present invention increases between engine and simultaneously vehicle deceleration mechanism
Yielding coupling and freewheel clutch reduce impact and vibration, coordinate the rotation of two engines.Rotor shaft of the invention with
The transmission of bevel gear is made of splined connection, cylindrical interference mating part and cylindrical surface transition fit part three parts,
Its distribution of force is effectively improved, using identical bevel gear and rotor shaft, torque and moment of flexure can be made by difference
Connection structure bear, the stress for reducing rotor shaft is concentrated, and improves the rigidity of bevel gear, makes the face of bevel gear
More preferably.It realizes the transfer function of movement and power, and can have different crossed axis angles, it is axially distinct that rotor may be implemented
Direction inclination.
Detailed description of the invention
The structure schematic top plan view of Fig. 1 DCB Specimen unmanned plane dynamical system of the present invention.
Fig. 2 is the schematic structural cross-sectional view of DCB Specimen unmanned plane dynamical system of the present invention.
Fig. 3 is the partial enlargement diagram of DCB Specimen unmanned plane dynamical system of the present invention.
Fig. 4 is a kind of schematic diagram of helicopter deceleration device of the present invention.
Fig. 5 is the schematic diagram that a kind of helicopter deceleration device of the present invention is overlooked.
Fig. 6 show a kind of present invention looks up structural representation of helicopter deceleration device.
Fig. 7 show the force analysis figure of helicopter deceleration device of the invention.
Fig. 8 is inventive belt formula drive mechanism schematic diagram.
Fig. 9 is the schematic diagram for the connection type that a kind of helicopter deceleration device rotor shaft of the present invention is in tilted layout.
It for those of ordinary skill in the art, without creative efforts, can be according to above attached
Figure obtains other relevant drawings.
Specific embodiment
In order to enable those skilled in the art to better understand the solution of the present invention, combined with specific embodiments below furtherly
Bright technical solution of the present invention.
Embodiment one
DCB Specimen unmanned plane dynamical system of the invention include two power take-off mechanisms 1, extend transversely through DCB Specimen nobody
The synchronizing shaft and helicopter deceleration device of prow tail being sequentially connected with the power take-off mechanism；The power output
Mechanism is rotation power outputting mechanism, such as piston engine, turboshaft engine, motor.
The helicopter deceleration device includes main box 81, can run through the main box 81 up and down with the relative rotation
Rotor shaft 82, the fixed bevel gear 83 being set in the rotor shaft, and the conical tooth shaft 84 cooperated with the bevel gear；
The power end of the conical tooth shaft is corresponding with synchronizing shaft to be fixedly connected, and is such as fixedly connected by diaphragm coupling each for compensating
The installation error in direction.
Wherein, the main box includes main frame and the lower boxboard for being fixed at the main frame bottom, institute
The lower flange 821 to bevel gear described in upper limit, the centre bore top of the bevel gear are provided in the rotor shaft stated
Cooperate with the rotor shaft cylindrical interference, middle part and the rotor shaft spline fitted, lower part and the rotor shaft mistake
Cross cooperation.The input shaft (namely conical tooth shaft) of retarder and the mode of external connection include but is not limited to key connection or spline
Connection.Come passing movement and power using bevel-gear sett, tooth system can be the tapered tooth of Gleason system, be also possible to crin shellfish
The rotation direction of lattice equal-depth teeth, bevel gear can be left or right rotation according to the difference of input shaft direction of rotation.
Wherein, the lower flange top is formed with the upper flange 822 cooperated with upper limit mechanism, the upper limit machine
Structure includes the top board 812 being fixedly connected with the main frame, and top board and convex intermarginal bearing is arranged in.It is described
Lower boxboard 811 and rotor between centers bearing 813 is provided with below the bevel gear, the lower boxboard and rotor between centers are in described
Oil sealing 814 is provided with below bearing.The lower boxboard is lower convex type structure to assemble the bearing and oil sealing, is not being increased
Under the premise of big main box volume, increase the locating effect to rotor shaft.Main box constitutes fuel tank and radiates to guarantee to be driven,
Multiple heat dissipation fins are provided on the outer wall of the main box to improve heat dissipation effect.Oil is provided on the main frame
Position mirror 816, top is provided with filling oil plug 817, is provided on the lower boxboard and drains the oil stifled 815, Mirror for indicating oil level can be used to observe
Whether the additional amount of lubricating oil is enough.When oil inlet is stifled opens, refueling operation can be carried out to retarder, when stifled open of draining the oil
When, Oil drain operation can be carried out to retarder.
Specifically, as shown, when conical tooth shaft 84 and bevel gear 83 are meshed, the stress of bevel gear can simplify for
Three power of facewidth midpoint, one is horizontal power F1 to the left, and one is power F2 straight down, and one is perpendicular to paper
Outside power Ft.The moment of flexure that F1 is generated is born by cylindrical interference mating part II, and the moment of flexure that F2 is generated is by cylindrical surface transition
Mating part III is born, and the torque that Ft is generated then is born by spline I.Thus dispersed rotor shaft coupling part by
Power keeps the rigidity of support of bevel gear more preferable, is not susceptible to deform.
The transmission of rotor shaft and bevel gear of the invention is by splined connection, cylindrical interference mating part and cylindrical surface
Transition fit part three parts composition, effectively improves its distribution of force, using identical bevel gear and rotor shaft,
It can make torque and moment of flexure by different connection structures to bear, the stress for reducing rotor shaft is concentrated, and improves bevel gear
Rigidity, keeps the face of bevel gear more preferable.It realizes the transfer function of movement and power, and can have different axis and hand over
Angle, such as 90 ° of axle clamp angles are leaned forward or hypsokinesis certain angle, and the axially distinct side of rotor may be implemented in such as 3 ° -10 ° be obliquely installed
To inclination.
It further include being set in the support tube 820 that outside the rotor shaft and bottom end is fixedly connected with the main frame,
It is rotatably connected with the rotor shaft by bearing 821 at the top of the support tube.Retarder has a support tube, can be with
It plays a supporting role to rotor shaft (namely output shaft), to improve the rigidity of rotor shaft.
Meanwhile the support tube upper end and the rotor between centers are provided with sealing strip 822, can have using sealing strip
Effect prevents dust from entering, and the setting of support tube, actually increases the heat dissipation area of main box, is conducive to improve entirety
Heat dissipation effect.
Embodiment two
It further, further include the small box 840 being fixedly connected with the main frame side, the input shaft (cone
Tooth shaft 84) and the rotatable cooperation of small box.The shaft of the conical tooth shaft is relatively described by former and later two bearings 841
Small box positioning, oil sealing 842 is provided between the small box and the shaft of conical tooth shaft.The bearing is taper roller axis
It holds, has the advantages that bearing capacity is high.The oil sealing is double oil seal.It is all used at the input shaft and output shaft of retarder double
Oil sealing is sealed, and has the advantages that good seal performance.Using individual small box structure, it is good to dismantle convenient assembling.
Helicopter deceleration device of the invention can be widely applied to helicopter of the single rotor with tail-rotor and lap siding DCB Specimen
The types such as helicopter.
Embodiment three
To realize, simultaneously vehicle is driven, and freewheel clutch is provided with driving wheel on the synchronizing shaft, the power is defeated
Mechanism and the driving wheel belt are sequentially connected out.Specifically, every engine 91 has pulley assembly, engine
Small pulley rotation is driven by clutch, revolving speed is then passed into driving wheel 93 by belt 92, finally gives power transfer
Synchronizing shaft 6 realizes the mechanical and vehicle of two engine outputs.Specifically, the driving wheel 93 passes through freewheel clutch
It is arranged on line shaft 94, the line shaft inner end correspondence of two driving wheels is fixedly connected with synchronizing shaft 6, such as passes through diaphragm coupling
Connection, the input axis connection of the outer end of two line shafts 94 and corresponding deceleration mechanism.In terms of same direction, two engines are defeated
Shaft direction of rotation is consistent, and the pulley assembly output shaft direction of rotation of two engine institute bands is consistent, and pulley assembly two
End can output power.It moreover, two engines are driven respectively, can be laid out with proportional space, by power intake and be slowed down
Setting is closed at end, reduces the stress of synchronizing shaft, improves whole balance.
Freewheel clutch is installed between driving wheel and transmission shaft, that is, synchronizing shaft, can make the revolving speed of driving wheel with it is synchronous
The revolving speed of axis is inconsistent, meets the requirement that two engines carry out simultaneously vehicle by mechanical structure.When transmission wheel speed is lower than
When synchronizing shaft revolving speed, it can be disengaged between driving wheel and synchronizing shaft (line shaft), driving wheel cannot drive synchronizing shaft to rotate；Work as transmission
When wheel speed is not less than synchronizing shaft revolving speed, driving wheel can drive synchronizing shaft to rotate.Therefore, when two engine speed are consistent
When, synchronizing shaft exports the sum of the power of two engines, synchronizing shaft stress very little, when two engine speed are inconsistent simultaneously
When, synchronizing shaft provides power by the high engine of revolving speed.While significantly improving transmission system general power, system is improved
Safety coefficient.
Example IV
It is different from above-mentioned belt transmission, another kind is achieved in that using simultaneously vehicle deceleration mechanism and output speed reducer structure, institute
Two power take-off mechanisms stated are symmetrically disposed in simultaneously vehicle deceleration mechanism two sides and power output shaft is coaxially disposed but rotation side
To opposite；Described and vehicle deceleration mechanism includes under casing body 4, can be rotatably set among the rod-shaped or tubular under casing body and passes
Dynamic portion 41, and the base cone gear 42 and symmetrically arranged two conical tooth shafts 43 that are fixedly connected with the intermediate transmission portion,
The cone increment of the conical tooth shaft and the base cone gear engaged transmission, the bottom is extended in the shaft end of the conical tooth shaft
Cabinet is simultaneously connect by freewheel clutch 3 with the pto shaft drive of the power take-off mechanism 1.Wherein, and vehicle slows down
The input shaft (namely conical tooth shaft) of mechanism includes but is not limited to be connected with key connection or spline with the mode of external connection.It uses
Bevel-gear sett comes passing movement and power, and tooth system can be the tapered tooth of Gleason system, it is contour to be also possible to Klinglnberg system
The rotation direction of tooth, bevel gear can be left or right rotation according to the difference of input shaft direction of rotation.The helicopter deceleration device
Including main box 1, it can fix with the relative rotation up and down through the rotor shaft 2 of the main box 1 and be set in the rotor shaft
On bevel gear 3, and the conical tooth shaft 4 cooperated with the bevel gear；
Meanwhile yielding coupling 2 is correspondingly arranged between power output shaft and freewheel clutch to reduce power transmission shake
It is dynamic, compensate the installation error of different directions.The use of freewheel clutch can be adapted to the asynchronous of two power take-off mechanisms, or
After one of engine stops working because of failure, it can disengage and connect with transmission system automatically, guarantee transmission system still
It so can work normally, improve the safety coefficient of transmission system.
Two power take-off mechanisms are symmetrical arranged, and reduce integral load, improve operation stability, and subtract using two-stage
Fast structure, deceleration reasonable disposition, assembly maintenance convenience, and have a wide range of application, it can be widely applied to helicopter and industry neck
Domain, the including but not limited to helicopter of lap siding DCB Specimen or single rotor with tail-rotor.
Specifically, the intermediate transmission portion 41 is provided with upper limit ring 44 above base cone gear, by the under casing
The upper limit bearing of the upper cover plate positioning of body is mutually pushed up with the upper limit ring to be held, the bottom end in the intermediate transmission portion and under casing
Lower limit bearing 45 is provided between the lower plate of body.Using the design method of upper and lower clamping position, intermediate conveyor portion positioning stablity
Reliably, guarantee that transmission is gone on smoothly.
Wherein, the under casing body is lower convex type structure to assemble the bearing and oil sealing, is not increasing under casing body
Under the premise of volume, increase the locating effect to intermediate driving section.Under casing body constitutes fuel tank to guarantee transmission heat dissipation, in institute
Multiple heat dissipation fins are provided on the outer wall for the under casing body stated to improve heat dissipation effect.Oil level is provided on the under casing body
Mirror, top are provided with filling oil plug, and the bottom of the under casing body, which is provided with, drains the oil stifled, and Mirror for indicating oil level can be used to observe lubricating oil
Whether additional amount is enough.When oil inlet is stifled opens, refueling operation can be carried out to retarder, when drain the oil stifled open when, can be right
And vehicle retarder carries out Oil drain operation.
The under casing body further includes the support tube 46 being fixedly connected with the upper cover plate, and the intermediate transmission portion is extremely
It is pierced by support tube and bearing is set in its top.It is provided between the support tube upper end and the intermediate transmission portion close
Strip of paper used for sealing can effectively prevent dust to enter using sealing strip, and the setting of support tube, actually increase the radiating surface of under casing body
Product is conducive to improve whole heat dissipation effect.
Preferably, the lower limit ring to bevel gear described in upper limit is provided in the intermediate transmission portion, it is described
Bevel gear centre bore top and the intermediate transmission portion be interference fitted, middle part is matched with the intermediate transmission portion spline
It closes, lower part and the intermediate transmission portion transition fit.
Wherein, the output speed reducer structure includes cabinet 50, through the cabinet and rotatable with the cabinet
The output shaft 5 of cooperation, described and vehicle deceleration mechanism intermediate transmission portion go deep into passing in the cabinet and with the output shaft 5
Dynamic connection, the output shaft both ends are connect with transmission shaft driven respectively, and bevel gear biography can be used in the output speed reducer structure
Motivation structure, cylindrical gear drive, Transmission Mechanism of Planetary Gear System are made of the combination of said mechanism.Wherein, using cone tooth
Wheel transmission when, on the output shaft be fixedly installed output bevel gear wheel 51, in intermediate transmission portion end be provided with it is described
The bevel gear 52 of output bevel gear wheel transmission connection, that is, have the function of communtation deceleration, uses other mechanisms then to slow down in the same direction.
Of the invention and vehicle deceleration mechanism, output speed reducer structure and helicopter deceleration device can be widely applied to single rotor band
The types such as the helicopter and tandem rotors helicopter of tail-rotor.
In conclusion it is characteristic of the invention that two engines and vehicle, power is then respectively delivered to forward and backward rotation
The wing or main rotor and tail-rotor.Two engines can work at the same time, and can also work independently.When two simultaneous firings
When, if a wherein engine breakdown, it can disengage with transmission system and connect, and continue to drive by another engine
Transmission system work.Since the probability that two engines break down simultaneously is much smaller than the probability of an engine breakdown,
Thus substantially increase the reliability of system.
The spatially relative terms such as "upper", "lower", "left", "right" have been used in embodiment for ease of explanation, have been used for
Relationship of the elements or features relative to another elements or features shown in explanatory diagram.It should be understood that in addition to figure
Shown in except orientation, spatial terminology is intended to include the different direction of device in use or operation.For example, if in figure
Device be squeezed, the element for being stated as being located at other elements or feature "lower" will be located into other elements or feature "upper".
Therefore, exemplary term "lower" may include both upper and lower orientation.Device, which can be positioned in other ways, (to be rotated by 90 ° or position
In other orientation), it can be interpreted accordingly used herein of the opposite explanation in space.
Moreover, the relational terms of such as " first " and " second " or the like are used merely to one with another with identical
The component of title distinguishes, without necessarily requiring or implying between these components there are any this actual relationship or
Sequentially.
Illustrative description has been done to the present invention above, it should explanation, the case where not departing from core of the invention
Under, any simple deformation, modification or other skilled in the art can not spend the equivalent replacement of creative work equal
Fall into protection scope of the present invention.
Claims (10)
1. a kind of DCB Specimen unmanned plane dynamical system, which is characterized in that defeated with the power including two power take-off mechanisms
The synchronizing shaft and helicopter deceleration device of mechanism driving connection out；
The helicopter deceleration device include main box, can with the relative rotation up and down run through the main box rotor shaft,
The fixed bevel gear being set in the rotor shaft, and the conical tooth shaft cooperated with the bevel gear, the main box
Including main frame and it is fixed at the lower boxboard of the main frame bottom, is provided in the rotor shaft to the upper limit
The lower flange of bevel gear described in position, the centre bore top of the bevel gear and the rotor shaft are interference fitted, middle part with
The rotor shaft spline fitted, lower part and the rotor shaft transition fit, the power end and synchronizing shaft of the conical tooth shaft
Correspondence is fixedly connected by shaft coupling.
2. DCB Specimen unmanned plane dynamical system as described in claim 1, which is characterized in that by surmounting on the synchronizing shaft
Clutch is provided with driving wheel, and the power take-off mechanism and the driving wheel belt are sequentially connected.
3. DCB Specimen unmanned plane dynamical system as described in claim 1, which is characterized in that including simultaneously vehicle deceleration mechanism and output
Deceleration mechanism, two power take-off mechanisms are symmetrically disposed in and vehicle deceleration mechanism two sides；
Described and vehicle deceleration mechanism includes under casing body, can be rotatably set in the rod-shaped or tubular intermediate transmission under casing body
Portion, the base cone gear being fixedly connected with the intermediate transmission portion and two symmetrically arranged two conical tooth shafts, the cone
The cone increment of tooth shaft and the base cone gear engaged transmission, the shaft end of the conical tooth shaft is extended the under casing body and is led to
Freewheel clutch is crossed to connect with the pto shaft drive of the power take-off mechanism.
4. a kind of DCB Specimen unmanned plane dynamical system according to claim 3, it is characterised in that: the intermediate transmission portion
Upper limit ring is provided with above vertical steel bracket axis, the upper limit bearing positioned by the upper cover plate of the under casing body with it is described upper
Stop collar is mutually pushed up and is held, and is provided with lower limit bearing between the bottom end in the intermediate transmission portion and the lower plate of under casing body.
5. a kind of DCB Specimen unmanned plane dynamical system according to claim 3, it is characterised in that: the under casing body also wraps
The support tube being fixedly connected with the upper cover plate is included, the intermediate transmission portion is pierced by into support tube and in its top setting
Bearing.
6. a kind of DCB Specimen unmanned plane dynamical system according to claim 3, it is characterised in that: the output speed reducer
Structure includes cabinet, described and vehicle deceleration mechanism through the cabinet and in the output shaft of the rotatable cooperation of cabinet
Intermediate transmission portion gos deep into being sequentially connected in the cabinet and with the output shaft.
7. a kind of DCB Specimen unmanned plane dynamical system according to claim 1, it is characterised in that: the lower flange top
Be formed with upper limit mechanism cooperation upper flange, the upper limit mechanism include be fixedly connected with the main frame it is upper
Pressing plate, and top board and convex intermarginal bearing are set.
8. a kind of DCB Specimen unmanned plane dynamical system according to claim 1, it is characterised in that: further include and the master
The small box that frame side is fixedly connected, the input shaft and the rotatable cooperation of the small box, the conical tooth shaft
The shaft small box positioning relatively described by former and later two bearings, is provided with oil between the small box and the shaft of conical tooth shaft
Envelope.
9. a kind of DCB Specimen unmanned plane dynamical system according to claim 1, it is characterised in that: further include be set in it is described
Rotor shaft outside and the support tube that is fixedly connected with the main frame of bottom end, at the top of the support tube and the rotor
Axis is rotatably connected by bearing.
10. a kind of DCB Specimen unmanned plane dynamical system according to claim 1, it is characterised in that: the helicopter slows down
The bevel gear of device and the crossed axis angle of conical tooth shaft are 80 ° -90 °.
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| CN201910135253.2A CN109677599A (en) | 2019-02-22 | 2019-02-22 | DCB Specimen unmanned plane dynamical system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN115352643A (en) * | 2022-08-08 | 2022-11-18 | 北京科技大学 | Multi-parallel-engine coaxial dual-rotor helicopter power assembly based on single-plane gear pair |
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| CN110435883A (en) * | 2019-07-26 | 2019-11-12 | 佛山科学技术学院 | A kind of inverse double-rotation wing helicopter transmission system side by side |
| CN110435883B (en) * | 2019-07-26 | 2023-10-31 | 佛山科学技术学院 | Transmission system of parallel reverse double-rotor helicopter |
| CN115352643A (en) * | 2022-08-08 | 2022-11-18 | 北京科技大学 | Multi-parallel-engine coaxial dual-rotor helicopter power assembly based on single-plane gear pair |
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