CN209321229U - A kind of foldable propeller, power device and unmanned plane - Google Patents
A kind of foldable propeller, power device and unmanned plane Download PDFInfo
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- CN209321229U CN209321229U CN201821226833.XU CN201821226833U CN209321229U CN 209321229 U CN209321229 U CN 209321229U CN 201821226833 U CN201821226833 U CN 201821226833U CN 209321229 U CN209321229 U CN 209321229U
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Abstract
The utility model discloses a kind of foldable propeller, power device and unmanned plane, the foldable propeller includes paddle seat and the blade that is installed on paddle seat, further includes pin shaft and elastic component, and one end of the blade is articulated and connected by pin shaft and paddle seat；The both ends of the elastic component are respectively acting on paddle seat and blade.The foldable propeller is used for the power device, and the power device is used for the unmanned plane, and the structure design of the propeller can voluntarily recycle blade after revolution speed of propeller reduction, not only be conducive to the safety of propeller when unmanned plane landing in this way；The recycling of blade is inputted independent of external energy simultaneously；While this propeller arrangement is simple, light weight, high reliablity.
Description
Technical field
The utility model relates to aviation flight apparatus field, more particularly to a kind of foldable propeller, power device and
Unmanned plane.
Background technique
In the prior art, the application field of unmanned plane is extremely extensive, is such as widely used in monitoring, investigation and survey field.
Unmanned plane can substantially be divided into fixed-wing unmanned plane, unmanned helicopter, multi-rotor unmanned aerial vehicle and composite wing unmanned plane at present.Gu
Determine wing unmanned plane and composite wing unmanned plane by wing generate aerodynamic lift, on voyage, speed, ceiling better than rotor class nobody
Machine is more suitable for completing the tasks such as monitoring, investigation, mapping.
The power arrangement of fixed-wing unmanned plane and composite wing unmanned plane can divide are as follows: preceding drawing, waist are pushed away and pushed away with tail.Preceding granny rag office
Limit very much the arrangement of task device: the passive Force system of preceding end spaces occupies and propeller rotational scope limitation photographic equipment view
Angle, tail feeding office can generate the excess weight of carrier.Waist motive force is it is possible to prevente effectively from the above problem, therefore in the prior art, waist
Motive force distribution form is the preferred power arrangement form for completing the tasks unmanned planes such as monitoring, investigation, mapping.
And it is directed to the Design of Propeller of unmanned plane, especially flat winged propeller (horizontal power propeller), in the prior art,
To make thrust or the direction of pull of propeller generation are variable, reduce the resistance that propeller generates unmanned plane etc., the prior art
In there is folding propeller.90 ° of progress on the basis of propeller Plane of rotation is realized as folded propeller in the prior art
Rotary folding is with the portable for rotor wing unmanned aerial vehicle；Screw blade is fixed on paddle folder, rotation realization up and down folding is pressed from both sides by paddle
Overturning etc..
The structure design for advanced optimizing the propeller for unmanned plane, is those skilled in the art's skill urgently to be resolved
Art problem.
Utility model content
It is those skilled in the art for the structure design for advanced optimizing the propeller for unmanned plane set forth above
Technical problem urgently to be resolved the problem of, the utility model provides a kind of foldable propeller, power device and unmanned plane,
The foldable propeller is used for the power device, and the power device is used for the unmanned plane, the structure of the propeller
Design can voluntarily recycle blade after revolution speed of propeller reduction, not only be conducive to the safety of propeller when unmanned plane landing in this way；
The recycling of blade is inputted independent of external energy simultaneously；While this propeller arrangement is simple, light weight, high reliablity.
The technological means of this programme is as follows, a kind of foldable propeller, including paddle seat and the blade being installed on paddle seat, also
Including pin shaft and elastic component, one end of the blade is articulated and connected by pin shaft and paddle seat；
And paddle seat, in rotation, the direction of motion of the installation point of paddle seat upper pin is conllinear with the axial direction of pin shaft；
The both ends of the elastic component are respectively acting on paddle seat and blade, and the elastic component passes through elastic-restoring force to blade
Apply torque, the torque using pin shaft is shaft rotation for forcing blade, and rotation direction is so that the free end of blade is to spiral shell
Revolve the axis rotation of paddle.
Specifically, in the present solution, the installation point of the paddle seat upper pin be for installing the installation point of pin shaft on paddle seat,
As those skilled in the art, in propeller rotation, if defining the above installation point is the A point on paddle seat, cross A point do perpendicular to
The cross section of propeller axis, using propeller axis position on cross section as the center of circle, distance is between the center of circle and A point
Radius does circle, and gained circle is consistent with the direction of motion of A point this moment in the tangential direction of A point.
Meanwhile after the axis direction by limiting the pin shaft, while the elastic component is set in this programme, this
Sample, in propeller rotary course, with the raising of revolution speed of propeller, blade can overcome the elastic force of elastic component under centrifugal force and
It is rotated around pin shaft, if remaining 0 ° of folder when propeller is static between blade and propeller shaft under the action of the elastic member
Angle, with the raising of revolution speed of propeller, the above angle can be by 0 ° of continuous state for being extended to 90 ° and be maintained at 90 °, above procedure
In, propeller can provide thrust or pulling force for unmanned plane.
And after cutting off to the input of the power of propeller, revolution speed of propeller constantly declines, and blade is in windage and elastic component
Under elastic-restoring force using pin shaft as shaft rotate, rotate above so that blade the free end direction of motion towards propeller axis
Line, in this way, the form recycling for making blade to fold.
In this way, this programme is when applying on unmanned plane, voluntarily putting away the oars for blade on propeller can be realized by elastic component,
The above resilient property put away the oars dependent on elastic component itself simultaneously, does not need other energy inputs, while as art technology
It is simple, light-weight either to all have structure using the spring of spring steel preparation or air spring etc. in the prior art by personnel
The characteristics of, therefore the above blade can be recycled scheme and be not only simple in structure, while light-weight, and more simple structure is conducive to reduce spiral shell
The failure rate of paddle is revolved, therefore a kind of present solution provides structures simple, light weight, high reliablity propeller scheme；Meanwhile especially
It is the especially horizontal power propeller in unmanned plane landing, since the excessive blade that may cause of the diameter of blade contacts to earth, in this way
It is unfavorable for the propeller even safety of unmanned plane, periphery personnel, article when unmanned plane landing.Therefore it is directed to spiral in the prior art
The size design of paddle needs to consider the installation site of the efficiency and propeller of propeller on unmanned plane.Using this programme, in nothing
It can be by the deceleration of reduction propeller, so that blade reduces the space ruler that blade is influenced during putting away the oars before man-machine landing
It is very little, reach conducive in unmanned plane descent safety, in design by increasing the length of blade improve propeller
The purpose of efficiency.So that this propeller scheme is especially suitable for fixed-wing unmanned plane, composite wing unmanned plane etc. using as press horizontal mobile
Wrench of a force system paddle.
As a kind of above-described further technical solution of foldable propeller: the paddle seat is annular in shape, described
The piece number of blade is multi-disc, and blade annular is distributed on paddle seat；
Each blade passes through a pin shaft and paddle seat is articulated and connected, and an elastic component is provided between each blade and paddle seat.It adopts
With this programme, the stabilized flight that propeller generates eccentric force during the work time and influences unmanned plane can avoid.Meanwhile with top
Case makes each blade that can put away the oars by corresponding elastic component realization when revolution speed of propeller reduces.
Specific setting form as propeller: the paddle seat includes the pedestal in annulus and is arranged in multiple on pedestal
For realizing the mounting portion of blade installation, the quantity of the mounting portion and the quantity of blade are equal, and each mounting portion is used to install
A piece of blade；
Multiple mounting portion annulars are distributed on pedestal；
The mounting portion includes two panels trunnion, and each trunnion is fixedly connected with pedestal, the two panels branch that each mounting portion includes
Ear is in face relationship, and the pin hole for wearing pin shaft is provided on each trunnion, and two pin holes that each mounting portion includes are in face
Relationship；
There is the clamping gap for accommodating blade tips between the two panels trunnion that each mounting portion includes；
After each blade is embedded in the clamping gap by one end for connecting with paddle seat, by corresponding pin shaft insertion pin
Hole, and corresponding pin shaft realizes the articulated connection blade and paddle seat across blade.In the present solution, passing through two on each mounting portion
Pin hole on ear realizes the support to pin shaft both ends, in this way, can optimize the stress of pin shaft in use；Above scheme simultaneously
Each component assembling of the propeller arrangement design composition propeller of offer is convenient.
Specific setting form and assembling form as elastic component: the elastic component is overall U-shaped torque spring,
The torque spring includes the bottom edge as middle part and two sides as side section, is all had on each side positioned at place
Helical ring between the both ends of side, and helical ring is coaxial on two sides；
The free end of the torque spring side is fixed on paddle seat, and the pin shaft on each mounting portion is by torsion on each mounting portion
Passed through in two helical rings of spring, on each mounting portion two helical rings of torque spring be respectively positioned on the clamping gap of each mounting portion with
It is interior；
Holding tank is additionally provided on the inside of each mounting portion upper journal, the holding tank is for accommodating torque spring insertion clamping
The paragraph in gap；
The bottom edge and corresponding blade phase separation.Using this programme, it is equivalent to one end of elastic component and the effect of paddle seat about
Beam passes through the connection of the fiting constraint elastic component and paddle seat of helical ring and pin shaft in the clamping gap, in this way, reachable
To the purpose for being conducive to elastic component assembly reliability in this programme；As those skilled in the art, the inside of the trunnion is
The positive opposite side of two trunnions included by any mounting portion, while by being arranged holding tank in the inside of trunnion, while elastic component
The paragraph for being installed as torque spring insertion clamping gap is embedded in the holding tank, in this way, can avoid the thickness shadow of torque spring
Effective gripping width in clamping gap is rung in favor of the thickness of torque spring is rotated, can weakened in blade installation and the course of work
Spend to clamping gap width influence and reach be conducive to weaken torque spring to blade installation and the course of work in rotate institute
Caused by influence；Meanwhile using torque spring as the elastic component, have be easy to draw materials, the cost of material is low, high reliablity,
The characteristics of being easily installed and safeguarding.
As those skilled in the art, since this programme realizes that purpose is rotated dependent on blade by shaft of pin shaft, simultaneously
Resets of putting away the oars that blade is realized by elastic component is pretended as those skilled in the art, mounting portion provided above and blade and
The fit form of the fit form of mounting portion, elastic component and mounting portion is actually only preferred embodiment, while above-described bullet
The both ends of property part, which are respectively acting on paddle seat and blade, can be divided into direct contact action or indirectly-acting, such as be set as pin shaft and paddle
Leaf is fixedly connected, and one end of elastic component is directly connected on paddle seat, and it is also the two of elastic component on pin shaft that the other end, which is directly connected in,
End is respectively acting on paddle seat and blade, i.e., actually blade be articulated and connected by pin shaft and paddle seat be not limited to it is mentioned above
The preferred embodiment of confession；And elastic component is normal spiral spring, above-mentioned mesh can be achieved in torque spring provided above, scroll spring
's.
Meanwhile this programme also discloses a kind of power device, including driving portion and the spiral being connected with driving portion output end
Paddle, the propeller are foldable propeller provided by any one as above.To sum up, present solution provides a kind of propellers to turn
The power device that blade can be recycled voluntarily after speed reduces, this power device are not only conducive to the safety of propeller when unmanned plane landing
Property；The recycling of blade is inputted independent of external energy simultaneously；Simultaneously because propeller arrangement has simple, light weight, reliable
Property high feature, also have the characteristics that the characteristics of simple, light weight, high reliablity using the power device of the propeller.
As the further technical solution of above-described power device, the driving portion includes stator and rotor, described
Stator and rotor are annular in shape；
Rotor is set in the outside of stator；
Paddle seat is fixed on rotor.
In the prior art, relative to drawing before unmanned plane and tail motive force layout, waist motive force is laid out it is possible to prevente effectively from such as
The problems such as propeller rotational scope limitation photographic equipment visual angle, tail feeding office can generate the excess weight of carrier.But conventional waist
Motive force is to avoid propeller rotational from interfering with each other mostly height with tail pipe to set, therefore propeller size is restricted, and can only be used
The lesser propeller of paddle diameter, reduces the efficiency of propeller；And set because of power height and increase additional weight, lead to unmanned mechanomotive force
Efficiency reduces；As shown in the utility model patent application No. is 201410771974.X, in the prior art, part waist motive force dress
It sets and propeller is placed on tail pipe, although this set-up mode solves the problems, such as that propeller size is restricted, but the tool of motor
Although motor power is passed in such a way that gear transmits torque in body form and selection toothed belt transmission, other implementations
Propeller is delivered to so that propeller is rotated around tail pipe, but is understood off-energy during gear drive, toothed belt transmission, reduced
Efficiency, at the same the connecting component between motor and motor and propeller to entire unmanned plane vertically and horizontally
Position of centre of gravity is affected.
Specifically, in the present solution, the stator and rotor are the important component of motor: the stator and rotor structure
As the power device being driven by electricity.It is annular in shape to be set as the stator, when this programme applies on unmanned plane, stator is arranged
And be fixed on the tail pipe of unmanned plane, rotor be set in the axis on stator and around stator rotation, propeller be connected with rotor and
Rotor is servo-actuated, passes through in this way, being equivalent in centre bore of the tail pipe by both stator and rotor, blade is along tail pipe on propeller
Circumferential direction distribution, propeller provide thrust during rotation, for unmanned plane.
The power device of waist motive force layout is provided for unmanned plane present solution provides a kind of, before facilitating airborne task device
It sets to obtain optimal field angle and installation site；This programme applies to unmanned plane and produces with waist pushing-type power device to unmanned plane
The small feature of raw supernumerary structure weight；In powerplant configuration design, when using propeller size not by placement constraint, this
Sample facilitates increase propeller efficiency；Powerplant configuration design in, it can be achieved that the installation form on tail pipe will not be because of nobody
Mechanomotive force height sets generation thrust line and center of gravity line is staggered, to generate nose-down pitching moment, avoids the need for increasing the wing angle of attack or liter
Rudder pull rod is dropped to offset the torque, generates more air drag；This programme is easy to implement stationary part, rotor portion center is fallen
On the axis of tail pipe or the above center is smaller at a distance from tail pipe axis, is easy to implement and reduces power device to unmanned plane perpendicular
The influence of the upward center of histogram, so that the structure design of power device has the spy for facilitating unmanned plane overall construction design
Point.
To sum up, this programme can effectively solve existing unmanned plane form installation power device and task device bring space benefit
With defect, transmission efficiency is low the problems such as, ensure that on unmanned plane as detect camera system preposition installation site, increase power
The efficiency of system ensure that the reasonability of mounting arrangement, therefore, can obtain using the unmanned plane of this kind of waist pushing-type power device
Longer cruise time and cruising range.
As the specific implementation form of the power device, setting are as follows: the stator, rotor, paddle seat are annular in shape, and
Stator, rotor, paddle seat three axis collinear；
The blade be it is a plurality of, a plurality of blade annular is distributed on paddle seat；
It further include second bearing, the second bearing connects for realizing bearing between paddle seat and tail pipe；
It further include first bearing, the first bearing is for realizing bearing connection between rotor and stator or rotor and tail pipe
Between bearing connection.Using this programme, facilitates and realize that stator, rotor, paddle seat three coaxially assemble with tail pipe, facilitate realization paddle
Leaf is uniformly distributed relative to the axis annular of tail pipe, in this way, can make as far as possible this power device at work produced by thrust conjunction
Power falls on the axis of this power device and direction along the axis of tail pipe, so that the center of gravity of this power device falls in the axis of tail pipe
On line, so that the center of gravity for the blade entirety being made of a plurality of blade is fallen on the axis of tail pipe.The first bearing of arrangement above and
The reliability that second bearing is conducive to rotor, paddle seat is connect with tail pipe, conducive to the concentricity of rotor, paddle seat, stator, tail pipe.
Preferably, it is set as the first bearing and second bearing is deep groove ball bearing, to utilize deep groove ball bearing body
Product is small, light-weight, can bear axial force and radial force, advantage at low cost, high reliablity；Preferably, for convenience by stator sleeve
It is connected on tail pipe, while facilitating and realizing being co-axially mounted for stator and tail pipe, be arranged are as follows: further include the mounting base in hoop-like, institute
Stator is stated to be fixedly connected with mounting base, the centre bore in mounting base is communicated with the centre bore on stator, in mounting base centre bore with
The axis of both centre bores is parallel on stator；Preferably, further include for realizing second bearing inner ring and tail pipe tight fit and/or
The support ring of second bearing outer ring and paddle seat tight fit, the support ring is annular in shape, and support ring is for being mounted on second bearing
In in gap between the inner ring and tail pipe or gap that is mounted between second bearing outer ring and paddle seat.In the present solution, the branch
Pushing out ring also can be for one it is multiple, when such as using one, may be provided between second bearing inner ring and tail pipe, may be provided at the
Between two bearing outer rings and paddle seat, the close-fitting between inner ring and tail pipe between tight fit or second bearing outer ring and paddle seat is realized
It closes, specific tight fit mode can be used to be embedded in the gap between second bearing inner ring and tail pipe or second bearing using support ring
In gap between outer ring and paddle seat, swelling is carried out using the wall thickness of support ring, is also embedded in the gap using support ring
It carries out part to fill up, the colloid for then injecting for example solidifiable realizes the tight fit as agent is filled up.In the quantity of support ring
When being two, different support rings can be embedded in gap by the different ends in same gap and be provided commonly for second bearing and tail pipe or second
The tight fit of bearing and paddle seat, different support rings can also be respectively used to realize second bearing and tail pipe, second bearing and paddle seat
Tight fit；When the quantity of support ring is more than two, the tight of second bearing and tail pipe, second bearing and paddle seat can be respectively used to
Cooperation；Preferably, for the benefit of concentricity of rotor, also can be between first bearing and rotor, first bearing and tail pipe or stator
Between the support ring is set.
Meanwhile this programme also discloses a kind of unmanned plane, including fuselage, the tail pipe to be extended back by afterbody, also wraps
The stator sleeve of power device described in any one provided by including, the power device is set on tail pipe, and stator and tail
Pipe is fixedly connected.To sum up, this unmanned plane uses the above power device, and the structure design of propeller can after revolution speed of propeller reduction
Blade is voluntarily recycled, is not only conducive to the safety of propeller when unmanned plane landing in this way；The recycling of blade is independent of outer simultaneously
Portion's energy input；While this propeller arrangement is simple, light weight, high reliablity；This programme can effectively solve existing unmanned plane shape
The problems such as formula installs power device and task device bring space utilization defect, transmission efficiency is low, ensure that on unmanned plane such as
The preposition installation site for detecting camera system, increases the efficiency of dynamical system, ensure that the reasonability of mounting arrangement, therefore,
Longer cruise time and cruising range can be obtained using the unmanned plane of this kind of waist pushing-type power device.
To make high-speed flight ability and long boat ability and multi-rotor unmanned aerial vehicle of this unmanned plane with fixed-wing unmanned plane
VTOL ability, widened the application range of industrial unmanned plane, be as the further technical solution of the unmanned plane,
The unmanned plane is composite wing unmanned plane.As those skilled in the art, realize that this programme can install use on the wing of fuselage
In the Vertical Dynamic propeller for realizing VTOL.
It further include being installed on front fuselage to make this unmanned plane can operate with monitoring, investigation or survey field field
Airborne equipment, the airborne equipment are one or more of monitoring, investigation, mapping equipment.The monitoring, investigation, mapping are set
Standby as monitoring device, such as video camera, mapping radar.
Preferably, the controllability put away the oars of blade when for the benefit of unmanned plane lands, setting are as follows: blade under the action of the centrifugal force around
The rotation direction that pin shaft is rotated and opened is opposite with rotation direction of the blade under air drag around pin shaft rotation.Such as use power
Device waist pushing-type layout, when blade is in and puts away the oars state, the empennage of the free end of blade towards unmanned plane.
The utility model has the following beneficial effects:
The propeller that this programme provides when applying on unmanned plane, by elastic component can realize blade on propeller from
Row is put away the oars, while the resilient property put away the oars above dependent on elastic component itself, does not need other energy inputs, while as ability
Field technique personnel, in the prior art either using spring or air spring etc. of spring steel preparation, all have structure simply,
Light-weight feature, therefore the above blade can be recycled scheme and be not only simple in structure, while light-weight, and more simple structure is conducive to
The failure rate of propeller is reduced, therefore a kind of present solution provides structures simple, light weight, high reliablity propeller scheme；Together
When, especially when unmanned plane lands, especially horizontal power propeller may cause blade touching since the diameter of blade is excessive
Ground is unfavorable for the propeller even safety of unmanned plane, periphery personnel, article when unmanned plane landing in this way.Therefore in the prior art
Need to consider the installation site of the efficiency and propeller of propeller on unmanned plane for the size design of propeller.Using we
Case, can be by the deceleration of reduction propeller, so that blade reduces blade during putting away the oars and influenced before unmanned plane landing
Bulk, reach conducive in unmanned plane descent safety, improved by increasing the length of blade in design
The purpose of efficiency of propeller.So that this propeller scheme is especially suitable for fixed-wing unmanned plane, composite wing unmanned plane etc. to make
For horizontal power propeller.
The power device of waist motive force layout is provided for unmanned plane present solution provides a kind of, while providing one kind and including
The unmanned plane of the power device facilitates airborne task device preposition using the above power device to obtain optimal field angle
And installation site；The above power device, which applies to unmanned plane, has the characteristics that the supernumerary structure weight generated to unmanned plane is small；It is dynamic
In the design of power apparatus structure, when using, propeller size is not by placement constraint, in this way, facilitating increase propeller efficiency；Power
In apparatus structure design, it can be achieved that the installation form on tail pipe will not be set because of unmanned mechanomotive force height and generate thrust line and center of gravity
Line is staggered, to generate nose-down pitching moment, avoids the need for increasing the wing angle of attack or elevator pull rod to offset the torque, generate compared with
More air drag；This programme is easy to implement stationary part, rotor portion center is all fallen on the axis of tail pipe or the above center with
The distance of tail pipe axis is smaller, is easy to implement the influence for reducing power device to unmanned plane center in the vertical direction, makes
The structure design for obtaining power device has the characteristics that facilitate unmanned plane overall construction design.
To sum up, this programme can effectively solve existing unmanned plane form installation power device and task device bring space benefit
With defect, transmission efficiency is low the problems such as, ensure that on unmanned plane as detect camera system preposition installation site, increase power
The efficiency of system ensure that the reasonability of mounting arrangement, therefore, can obtain using the unmanned plane of this kind of waist pushing-type power device
Longer cruise time and cruising range.
Detailed description of the invention
Fig. 1 is a kind of foldable propeller one specific state diagram for using embodiment described in the utility model, the shape
State figure reflection blade put away the oars state and propeller structure, propeller and unmanned aerial vehicle tail pipe assembly method；
Fig. 2 is a kind of foldable propeller one specific state diagram for using embodiment described in the utility model, the shape
State figure reflects structure, the assembly method of propeller and unmanned aerial vehicle tail pipe of blade open configuration and propeller；
Fig. 3 is in one specific embodiment of a kind of foldable propeller described in the utility model, and the structure of elastic component is shown
It is intended to；
Fig. 4 is a kind of partial structural diagram of one specific embodiment of power device described in the utility model, this shows
It is intended to the structure of reflection paddle seat and the connection relationship of paddle seat and rotor；
Fig. 5 is a kind of partial structural diagram of one specific embodiment of power device described in the utility model, this shows
It is intended to the assembly method of the reflection structure of paddle seat, the connection relationship of paddle seat and rotor, elastic component and pin shaft on paddle seat；
Fig. 6 is a kind of partial structural diagram of one specific embodiment of unmanned plane described in the utility model；
Fig. 7 is a kind of partial structural diagram of one specific embodiment of unmanned plane described in the utility model, the signal
The structure of figure reflection power device and the matching relationship of power device and tail pipe, which is explosive view.
Appended drawing reference in figure is respectively as follows: 1, mounting base, 2, stator, 3, first bearing, 4, rotor, 5, second bearing, 6,
Support ring, 7, paddle seat, 8, blade, 9, tail pipe, 10, power device, 11, fuselage, 12, airborne equipment, 13, elastic component, 14, pin
Axis, 15, side, 16, bottom edge, 17, helical ring, 18, holding tank.
Specific embodiment
Below with reference to embodiment, the utility model is described in further detail, but the structure of the utility model is not only
It is limited to following embodiment.
Embodiment 1:
As shown in Figures 1 to 7, a kind of foldable propeller is also wrapped including paddle seat 7 and the blade being installed on paddle seat 78
Pin shaft 14 and elastic component 13 are included, one end of the blade 8 is articulated and connected by pin shaft 14 and paddle seat 7；
And paddle seat 7, in rotation, the direction of motion of the installation point of 7 upper pin 14 of paddle seat and the axial direction of pin shaft 14 are total
Line；
The both ends of the elastic component 13 are respectively acting on paddle seat 7 and blade 8, and the elastic component 13 passes through elastic-restoring force
Apply torque to blade 8, for forcing blade 8 with pin shaft 14 for shaft rotation, rotation direction is so that blade 8 for the torque
Free end is rotated to the axis of propeller.
Specifically, in the present solution, the installation point of 7 upper pin 14 of the paddle seat is on paddle seat 7 for installing pin shaft 14
Installation point, in propeller rotation, if defining the above installation point is the A point on paddle seat 7, crosses A point as those skilled in the art
Do the cross section perpendicular to propeller axis, using propeller axis position on cross section as the center of circle, the center of circle and A point it
Between distance be that radius does circle, gained circle is consistent with the direction of motion of A point this moment in the tangential direction of A point.
Meanwhile after the axis direction by limiting the pin shaft 14, while the elastic component 13 is set in this programme,
In this way, with the raising of revolution speed of propeller, blade 8 can overcome elastic component 13 under centrifugal force in propeller rotary course
Elastic force and around pin shaft 14 rotate, if being protected between blade 8 and propeller shaft under the action of elastic component 13 when propeller is static
The angle for 0 ° is held, with the raising of revolution speed of propeller, the above angle can be by 0 ° of continuous shape for being extended to 90 ° and be maintained at 90 °
State, in above procedure, propeller can provide thrust or pulling force for unmanned plane.
And after cutting off to the power input of propeller, revolution speed of propeller constantly declines, and blade 8 is in windage and elastic component 13
Elastic-restoring force under with pin shaft 14 be shaft rotation, rotate above so that the free end direction of motion of blade 8 is towards propeller
Axis, in this way, recycling blade 8 in the form of folding.
In this way, when applying on unmanned plane, the voluntarily receipts of blade 8 on propeller can be realized by elastic component 13 for this programme
Paddle, while the resilient property put away the oars above dependent on elastic component 13 itself, do not need other energy inputs, while as this field
Technical staff either all has structure simply, again using the spring of spring steel preparation or air spring etc. in the prior art
Light feature is measured, therefore scheme can be recycled in the above blade 8 is not only simple in structure, while light-weight, and more simple structure is conducive to
The failure rate of propeller is reduced, therefore a kind of present solution provides structures simple, light weight, high reliablity propeller scheme；Together
When, especially when unmanned plane lands, especially horizontal power propeller may cause blade 8 since the diameter of blade 8 is excessive
It contacts to earth, is unfavorable for the propeller even safety of unmanned plane, periphery personnel, article when unmanned plane landing in this way.Therefore the prior art
In for the size design of propeller need to consider the installation site of the efficiency and propeller of propeller on unmanned plane.Using this
Scheme, can be by the deceleration of reduction propeller, so that blade 8 reduces 8 institute of blade during putting away the oars before unmanned plane landing
The bulk of influence, reach conducive in unmanned plane descent safety, design when by increase blade 8 length come
The purpose of improving the efficiency of propeller.So that this propeller scheme is especially suitable for fixed-wing unmanned plane, composite wing unmanned plane etc.
Using as horizontal power propeller.
Embodiment 2:
As shown in Figures 1 to 7, the present embodiment is further qualified on the basis of embodiment 1: as above-described one
Kind of the further technical solution of foldable propeller: the paddle seat 7 is annular in shape, and the piece number of the blade 8 is multi-disc, and blade
8 annulars are distributed on paddle seat 7；
Each blade 8 is articulated and connected by a pin shaft 14 with paddle seat 7, and an elasticity is provided between each blade 8 and paddle seat 7
Part 13.Using this programme, the stabilized flight that propeller generates eccentric force during the work time and influences unmanned plane can avoid.Together
When, above scheme makes each blade 8 that can put away the oars by the corresponding realization of elastic component 13 when revolution speed of propeller reduces.
Specific setting form as propeller: the paddle seat 7 includes the pedestal in annulus and is arranged in more on pedestal
A mounting portion installed for realizing blade 8, the quantity of the mounting portion is equal with the quantity of blade 8, and each mounting portion is used to
A piece of blade 8 is installed；
Multiple mounting portion annulars are distributed on pedestal；
The mounting portion includes two panels trunnion, and each trunnion is fixedly connected with pedestal, the two panels branch that each mounting portion includes
Ear is in face relationship, the pin hole for wearing pin shaft 14 is provided on each trunnion, two pin holes that each mounting portion includes are in just
To relationship；
There is the clamping gap for accommodating 8 end of blade between the two panels trunnion that each mounting portion includes；
After each blade 8 is embedded in the clamping gap by one end for connecting with paddle seat 7, corresponding pin shaft 14 is inserted into
Pin hole, and corresponding pin shaft 14 realizes the articulated connection blade 8 and paddle seat 7 across blade 8.In the present solution, passing through each installation
Pin hole in portion on two trunnions realizes the support to 14 both ends of pin shaft, in this way, can optimize the stress of pin shaft 14 in use；
Each component assembling for the propeller arrangement design composition propeller that above scheme provides simultaneously is convenient.
Specific setting form and assembling form as elastic component 13: the elastic component 13 is overall U-shaped torsion
Spring, the torque spring include the bottom edge 16 as middle part and two sides 15 as side section, on each side 15
With the helical ring 17 between 15 both ends of place side, and on two sides 15, helical ring 17 is coaxial；
The free end of the torque spring side 15 is fixed on paddle seat 7, and the pin shaft 14 on each mounting portion is by each mounting portion
It is passed through in two helical rings 17 of upper torque spring, two helical rings 17 of torque spring are respectively positioned on the folder of each mounting portion on each mounting portion
It holds within gap；
Holding tank 18 is additionally provided on the inside of each mounting portion upper journal, the holding tank 18 is for accommodating torque spring insertion
Clamp the paragraph in gap；
The bottom edge 16 and corresponding 8 phase separation of blade.Using this programme, it is equivalent to and acts on elastic component 13 and paddle seat 7
One end constrains in the clamping gap, while passing through the fiting constraint elastic component 13 and paddle seat 7 of helical ring 17 and pin shaft 14
Connection, in this way, can reach conducive to the purpose of the assembly reliability in this programme of elastic component 13；As those skilled in the art, institute
The inside for stating trunnion is the positive opposite side of two trunnions included by any mounting portion, while being accommodated by being arranged in the inside of trunnion
Slot 18, while the paragraph for being installed as torque spring insertion clamping gap of elastic component 13 is embedded in the holding tank 18, in this way, can
The thickness effect of torque spring is avoided to clamp effective gripping width in gap in favor of revolving in the installation of blade 8 and the course of work
Turn, the influence to clamping gap width of the thickness of torque spring can be weakened and reaches and be conducive to weaken torque spring blade 8 is installed
With caused influence is rotated in the course of work；Meanwhile having as the elastic component 13 using torque spring and being easy to take
Material, the cost of material is low, high reliablity, the characteristics of being easily installed and safeguarding.
As those skilled in the art, since this programme realizes that purpose is rotated dependent on blade 8 with pin shaft 14 for shaft, together
When by elastic component 13 realize blade 8 reset of putting away the oars, pretend as those skilled in the art, mounting portion and paddle provided above
The fit form of the fit form of leaf 8 and mounting portion, elastic component 13 and mounting portion actually only preferred embodiment, while the above institute
The both ends for the elastic component 13 stated, which are respectively acting on paddle seat 7 and blade 8, can be divided into direct contact action or indirectly-acting, such as be arranged
It is fixedly connected for pin shaft 14 with blade 8, one end of elastic component 13 is directly connected on paddle seat 7, and the other end is directly connected in pin shaft
Both ends on 14 also for elastic component 13 are respectively acting on paddle seat 7 and blade 8, i.e., actually blade 8 passes through pin shaft 14 and paddle seat 7
Articulated connection is not limited to preferred embodiment presented above；And elastic component 13 is normal spiral spring, torsion provided above
Above-mentioned purpose can be achieved in power spring, scroll spring.
Embodiment 3:
As shown in Figures 1 to 7, it present embodiments provides a kind of power device 10, including driving portion and is exported with driving portion
The connected propeller in end, the propeller are any one foldable propeller provided by any one embodiment as above.It is comprehensive
On, the power device 10 that blade 8 can be recycled voluntarily after reducing present solution provides a kind of revolution speed of propeller, this power device 10 is not
Only it is conducive to the safety of propeller when unmanned plane landing；The recycling of blade 8 is inputted independent of external energy simultaneously；Simultaneously because
Propeller arrangement has the characteristics that simple, light weight, high reliablity, also has letter using the power device 10 of the propeller
The characteristics of the characteristics of list, light weight, high reliablity.
Embodiment 4:
As shown in Figures 1 to 7, the present embodiment is further qualified on the basis of embodiment 3, and the driving portion includes fixed
Son 2 and rotor 4, the stator 2 and rotor 4 are annular in shape；
Rotor 4 is set in the outside of stator 2；
Paddle seat 7 is fixed on rotor 4.
In the prior art, relative to drawing before unmanned plane and tail motive force layout, waist motive force is laid out it is possible to prevente effectively from such as
The problems such as propeller rotational scope limitation photographic equipment visual angle, tail feeding office can generate the excess weight of carrier.But conventional waist
Motive force is to avoid propeller rotational from interfering with each other mostly height with tail pipe 9 to set, therefore propeller size is restricted, and can only be used
The lesser propeller of paddle diameter, reduces the efficiency of propeller；And set because of power height and increase additional weight, lead to unmanned mechanomotive force
Efficiency reduces；As shown in the utility model patent application No. is 201410771974.X, in the prior art, part waist motive force dress
It sets and propeller is placed on tail pipe 9, although this set-up mode solves the problems, such as that propeller size is restricted, but the tool of motor
Although motor power is passed in such a way that gear transmits torque in body form and selection toothed belt transmission, other implementations
Propeller is delivered to so that propeller is rotated around tail pipe 9, but understands off-energy, drop during gear drive, toothed belt transmission
Poor efficiency, at the same the connecting component between motor and motor and propeller to entire unmanned plane vertically and horizontally
Position of centre of gravity be affected.
Specifically, in the present solution, the stator 2 and rotor 4 are the important component of motor: the stator 2 and turning
Son 4 is configured to the power device 10 being driven by electricity.It is annular in shape to be set as the stator 2, when this programme applies on unmanned plane,
Stator 2 is arranged and is fixed on the tail pipe 9 of unmanned plane, and rotor 4 is arranged on the stator 2 and rotates around the axis of stator 2, propeller
It is connected with rotor 4 servo-actuated with rotor 4, is passed through in this way, being equivalent in centre bore of the tail pipe 9 by both stator 2 and rotor 4, spiral
Blade 8 is distributed along the circumferential direction of tail pipe 9 on paddle, and propeller provides thrust during rotation, for unmanned plane.
The power device 10 of waist motive force layout is provided for unmanned plane present solution provides a kind of, facilitates airborne task device
It is preposition to obtaining optimal field angle and installation site；This programme applies to unmanned plane with waist pushing-type power device 10 to nobody
The small feature of the supernumerary structure weight that machine generates；In the design of 10 structure of power device, when using, propeller size is not laid out
Limitation, in this way, facilitating increase propeller efficiency；10 structure of power device design in, it can be achieved that the installation form on tail pipe 9
Generation thrust line will not be set because of unmanned mechanomotive force height and center of gravity line is staggered, to generate nose-down pitching moment, avoid the need for increasing wing
The angle of attack or elevator pull rod offset the torque, generate more air drag；This programme is easy to implement 2 part of stator, rotor 4
Portion centers are all fallen on the axis of tail pipe 9 or the above center is smaller at a distance from 9 axis of tail pipe, are easy to implement and are reduced power dress
The influence of 10 pairs of unmanned planes center in the vertical direction is set, so that the structure design of power device 10, which has, facilitates unmanned plane
The characteristics of overall construction design.
To sum up, this programme can effectively solve existing unmanned plane form installation power device 10 and task device bring space
Using defect, transmission efficiency is low the problems such as, ensure that on unmanned plane as detect camera system preposition installation site, increase dynamic
The efficiency of Force system ensure that the reasonability of mounting arrangement, therefore, can be with using the unmanned plane of this kind of waist pushing-type power device 10
Obtain longer cruise time and cruising range.
As the specific implementation form of the power device 10, setting are as follows: the stator 2, rotor 4, paddle seat 7 are in annulus
Shape, and stator 2, rotor 4,7 three of paddle seat axis collinear；
The blade 8 be it is a plurality of, a plurality of 8 annular of blade is distributed on paddle seat 7；
It further include second bearing 5, the second bearing 5 connects for realizing bearing between paddle seat 7 and tail pipe 9；
It further include first bearing 3, the first bearing 3 is for realizing bearing connection or rotor 4 between rotor 4 and stator 2
Bearing is connect between tail pipe 9.Using this programme, facilitate realize stator 2, rotor 4,7 three of paddle seat with the coaxial dress of tail pipe 9
Match, facilitates and realize that blade 8 is uniformly distributed relative to the axis annular of tail pipe 9, in this way, this power device 10 can be made as far as possible to work
When produced thrust resultant force fall on the axis of this power device 10 and direction along the axis of tail pipe 9, so that this power fills
It sets 10 center of gravity to fall on the axis of tail pipe 9, so that the center of gravity for the blade entirety being made of a plurality of blade 8 falls in the axis of tail pipe 9
On line.The reliability that the first bearing 3 and second bearing 5 of arrangement above are conducive to rotor 4, paddle seat 7 is connect with tail pipe 9 is conducive to turn
The concentricity of son 4, paddle seat 7, stator 2, tail pipe 9 four.
Preferably, it is set as the first bearing 3 and second bearing 5 is deep groove ball bearing, to utilize deep groove ball bearing
It is small in size, light-weight, axial force and radial force, advantage at low cost, high reliablity can be born；Preferably, for convenience by stator 2
It is socketed on tail pipe 9, while facilitating and realizing being co-axially mounted for stator 2 and tail pipe 9, be arranged are as follows: further include the installation for being in hoop-like
Seat 1, the stator 2 is fixedly connected with mounting base 1, and the centre bore in mounting base 1 is communicated with the centre bore on stator 2, mounting base 1
Upper centre bore is parallel with the axis of both centre bores on stator 2；It preferably, further include for realizing 5 inner ring of second bearing and tail
9 tight fit of pipe and/or the support ring 6 of 5 outer ring of second bearing and 7 tight fit of paddle seat, the support ring 6 is annular in shape, support ring 6
In gap for being mounted between 5 inner ring of second bearing and tail pipe 9 or it is mounted between 5 outer ring of second bearing and paddle seat 7
In gap.In the present solution, the support ring 6 can for one also be it is multiple, such as use one when, may be provided at second bearing 5
Between inner ring and tail pipe 9, may be provided between 5 outer ring of second bearing and paddle seat 7, realize between inner ring and tail pipe 9 tight fit or
Tight fit between 5 outer ring of second bearing and paddle seat 7, specific tight fit mode, which can be used, is embedded in second bearing 5 using support ring 6
In gap in gap between inner ring and tail pipe 9 or between 5 outer ring of second bearing and paddle seat 7, using support ring 6 wall thickness into
Row swelling is also embedded in the gap using support ring 6 and partially fill up, then injects the colloid conduct of for example solidifiable
It fills up agent and realizes the tight fit.When the quantity of support ring 6 is two, different support rings 6 can be by the different ends in same gap
The tight fit of second bearing 5 and tail pipe 9 or second bearing 5 and paddle seat 7 is provided commonly in insertion gap, different support rings 6 also may be used
It is respectively used to realize the tight fit of second bearing 5 and tail pipe 9, second bearing 5 and paddle seat 7；Support ring 6 quantity be two with
When upper, the tight fit of second bearing 5 and tail pipe 9, second bearing 5 and paddle seat 7 can be respectively used to；Preferably, for the benefit of rotor 4
Also the support ring 6 can be arranged between first bearing 3 and rotor 4, between first bearing 3 and tail pipe 9 or stator 2 in concentricity.
Embodiment 5:
As shown in Figures 1 to 7, the present embodiment also discloses a kind of unmanned plane, including fuselage 11, by 11 tail portion of fuselage backward
The tail pipe 9 of extension, further include on power device 10 described in any one provided by any one embodiment, the power
The stator 2 of device 10 is sheathed on tail pipe 9, and stator 2 is fixedly connected with tail pipe 9.To sum up, this unmanned plane is filled using the above power
10 are set, the structure design of propeller can voluntarily recycle blade 8 after revolution speed of propeller reduction, be not only conducive to unmanned plane in this way and land
When propeller safety；The recycling of blade 8 is inputted independent of external energy simultaneously；While this propeller arrangement is simple, matter
Measure light, high reliablity；This programme can effectively solve existing unmanned plane form installation power device 10 and task device bring is empty
Between using defect, transmission efficiency is low the problems such as, ensure that on unmanned plane as detect camera system preposition installation site, increase
The efficiency of dynamical system ensure that the reasonability of mounting arrangement, therefore, can using the unmanned plane of this kind of waist pushing-type power device 10
To obtain longer cruise time and cruising range.
To make high-speed flight ability and long boat ability and multi-rotor unmanned aerial vehicle of this unmanned plane with fixed-wing unmanned plane
VTOL ability, widened the application range of industrial unmanned plane, be as the further technical solution of the unmanned plane,
The unmanned plane is composite wing unmanned plane.As those skilled in the art, realize that this programme can be installed on the wing of fuselage 11
For realizing the Vertical Dynamic propeller of VTOL.
It further include being installed on 11 front end of fuselage to make this unmanned plane can operate with monitoring, investigation or survey field field
Airborne equipment 12, the airborne equipment 12 is monitoring, investigation, one or more of mapping equipment.It is described monitoring, investigation,
Mapping equipment is monitoring device, such as video camera, mapping radar.
Preferably, the controllability that blade 8 is put away the oars when for the benefit of unmanned plane lands, setting are as follows: blade 8 is under the action of the centrifugal force
The rotation direction for rotating and opening around pin shaft 14 is opposite with rotation direction of the blade 8 under air drag around the rotation of pin shaft 14.Such as
It is laid out using 10 waist pushing-type of power device, when blade 8 is in and puts away the oars state, the empennage of the free end of blade 8 towards unmanned plane.
The above content is the further descriptions made in conjunction with specific preferred embodiment to the utility model, cannot recognize
Determine specific embodiment of the present utility model to be only limited to these instructions.For the common skill of the utility model technical field
For art personnel, the other embodiments obtained in the case where not departing from the technical solution of the utility model be should be included in corresponding real
With in novel protection scope.
Claims (10)
1. a kind of foldable propeller, including paddle seat (7) and the blade (8) being installed on paddle seat (7), which is characterized in that also wrap
Pin shaft (14) and elastic component (13) are included, one end of the blade (8) is articulated and connected by pin shaft (14) and paddle seat (7)；
And paddle seat (7) is in rotation, the axial direction of the direction of motion of the installation point of paddle seat (7) upper pin (14) and pin shaft (14)
Collinearly；
The both ends of the elastic component (13) are respectively acting on paddle seat (7) and blade (8), and the elastic component (13) is returned by elasticity
Multiple power applies torque to blade (8), and for forcing blade (8) with pin shaft (14) for shaft rotation, rotation direction is for the torque
So that the free end of blade (8) is rotated to the axis of propeller.
2. a kind of foldable propeller according to claim 1, which is characterized in that the paddle seat (7) is annular in shape, described
The piece number of blade (8) is multi-disc, and blade (8) annular is distributed on paddle seat (7)；
Each blade (8) is articulated and connected by a pin shaft (14) and paddle seat (7), is provided between each blade (8) and paddle seat (7)
One elastic component (13).
3. a kind of foldable propeller according to claim 2, which is characterized in that the paddle seat (7) includes in annulus
Pedestal and the multiple mounting portions for realizing blade (8) installation being arranged on pedestal, quantity and blade (8) of the mounting portion
Quantity it is equal, each mounting portion is used to install a piece of blade (8)；
Multiple mounting portion annulars are distributed on pedestal；
The mounting portion includes two panels trunnion, and each trunnion is fixedly connected with pedestal, and the two panels trunnion that each mounting portion includes is in
Face relationship, the pin hole for wearing pin shaft (14) is provided on each trunnion, and two pin holes that each mounting portion includes are in face
Relationship；
There is the clamping gap for accommodating blade (8) end between the two panels trunnion that each mounting portion includes；
After each blade (8) is embedded in the clamping gap by one end for connecting with paddle seat (7), corresponding pin shaft (14) are inserted
Enter pin hole, and corresponding pin shaft (14) realize the articulated connection blade (8) and paddle seat (7) across blade (8).
4. a kind of foldable propeller according to claim 3, which is characterized in that it is in U that the elastic component (13), which is whole,
The torque spring of shape, the torque spring include the bottom edge (16) as middle part and two sides (15) as side section,
The helical ring (17) between place side (15) both ends, and helical ring on two sides (15) are all had on each side (15)
(17) coaxial；
The free end of the torque spring side (15) is fixed on paddle seat (7), and the pin shaft (14) on each mounting portion is by each installation
It is passed through in two helical rings (17) of torque spring in portion, two helical rings (17) of torque spring are respectively positioned on each installation on each mounting portion
Within the clamping gap in portion；
It is additionally provided on the inside of each mounting portion upper journal holding tank (18), the holding tank (18) is for accommodating torque spring insertion
Clamp the paragraph in gap；
The bottom edge (16) and corresponding blade (8) phase separation.
5. a kind of power device, including driving portion and the propeller being connected with driving portion output end, which is characterized in that the spiral
Paddle is foldable propeller provided by any one of Claims 1-4.
6. power device according to claim 5, which is characterized in that the driving portion includes stator (2) and rotor (4),
The stator (2) and rotor (4) are annular in shape；
Rotor (4) is set in the outside of stator (2)；
Paddle seat (7) is fixed on rotor (4).
7. power device according to claim 6, which is characterized in that the stator (2), rotor (4), paddle seat (7) are in
Annular shape, and stator (2), rotor (4), paddle seat (7) three axis collinear；
The blade (8) be it is a plurality of, a plurality of blade (8) annular is distributed on paddle seat (7)；
It further include second bearing (5), the second bearing (5) connect for realizing bearing between paddle seat (7) and tail pipe (9)；
It further include first bearing (3), the first bearing (3) connect or turns for realizing bearing between rotor (4) and stator (2)
Bearing is connect between sub (4) and tail pipe (9).
8. a kind of unmanned plane, including fuselage (11), the tail pipe (9) to be extended back by fuselage (11) tail portion, which is characterized in that also wrap
The power device (10) as described in any one of claim 5 to 7 is included, the stator (2) of the power device (10) is sheathed on
On tail pipe (9), and stator (2) is fixedly connected with tail pipe (9).
9. a kind of unmanned plane according to claim 8, which is characterized in that the unmanned plane is composite wing unmanned plane.
10. a kind of unmanned plane according to claim 8, which is characterized in that further include the machine for being installed on fuselage (11) front end
It carries equipment (12), the airborne equipment (12) is one or more of monitoring, investigation, mapping equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821226833.XU CN209321229U (en) | 2018-07-31 | 2018-07-31 | A kind of foldable propeller, power device and unmanned plane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821226833.XU CN209321229U (en) | 2018-07-31 | 2018-07-31 | A kind of foldable propeller, power device and unmanned plane |
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| CN209321229U true CN209321229U (en) | 2019-08-30 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108688792A (en) * | 2018-07-31 | 2018-10-23 | 成都纵横大鹏无人机科技有限公司 | A kind of foldable propeller, power plant and unmanned plane |
| CN110871881A (en) * | 2019-12-02 | 2020-03-10 | 西安毫米波光子科技有限公司 | Screw folding mechanism that ejection formula unmanned aerial vehicle used |
-
2018
- 2018-07-31 CN CN201821226833.XU patent/CN209321229U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108688792A (en) * | 2018-07-31 | 2018-10-23 | 成都纵横大鹏无人机科技有限公司 | A kind of foldable propeller, power plant and unmanned plane |
| CN110871881A (en) * | 2019-12-02 | 2020-03-10 | 西安毫米波光子科技有限公司 | Screw folding mechanism that ejection formula unmanned aerial vehicle used |
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