CN203623961U - Screw pitch varying device, as well as rotor wing suite and multi-rotor-wing aircraft using same - Google Patents
Screw pitch varying device, as well as rotor wing suite and multi-rotor-wing aircraft using same Download PDFInfo
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- CN203623961U CN203623961U CN201320858564.XU CN201320858564U CN203623961U CN 203623961 U CN203623961 U CN 203623961U CN 201320858564 U CN201320858564 U CN 201320858564U CN 203623961 U CN203623961 U CN 203623961U
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- 230000033001 locomotion Effects 0.000 claims abstract description 17
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- 238000009434 installation Methods 0.000 claims description 22
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- 239000011295 pitch Substances 0.000 abstract 7
- 230000000149 penetrating effect Effects 0.000 abstract 2
- 230000009286 beneficial effect Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 4
- 230000004044 response Effects 0.000 description 4
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- 230000007812 deficiency Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
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Abstract
The utility model discloses a screw pitch varying device for varying screw pitches of blades. The screw pitch varying device comprises a fixed seat, a connecting rod, and a driving assembly, wherein the connecting rod is used for penetrating through a rotating main shaft for driving the blades to rotate, and the connecting rod and the fixed seat are movably arranged oppositely; the driving assembly is connected with the fixed seat and consists of a blade mounting base for mounting the blades, the blade mounting base is connected with the connecting rod so that when the connecting rod does reciprocating motion relative to the rotating main shaft, the blade mounting base can be driven by the connecting rod so as to vary the screw pitches of the blades. According to the screw pitch varying device, the connecting rod is arranged after penetrating through the rotating main shaft, thus being beneficial to miniaturization of the screw pitch varying device. In addition, the utility model further provides a rotor wing suite and a multi-rotor-wing aircraft using the screw pitch varying device.
Description
Technical field
The utility model belongs to aircraft field, relates in particular to rotor external member and the multi-rotor aerocraft of a kind of variable pitch device and this device of application.
Background technology
The multi-rotor aerocraft of correlation technique, it comprises fuselage, be connected with described fuselage and some horns symmetrical with respect to described fuselage, lay respectively at the rotor external member on each described horn and be positioned on each described horn for driving the motor of described rotor external member.Rotor external member has rotor and is located at the fixing blade of a pair of pitch on rotor arbitrarily.Wherein, the hand of rotation of adjacent rotor is contrary between two,, the positive hour hands rotation of half motor, second half motor left-hand revolution, controls the lift of the described rotor generation of described multi-rotor aerocraft by coordinating the rotating speed of each motor, thereby controls attitude and the displacement of described multi-rotor aerocraft.
But, the multi-rotor aerocraft of correlation technique, the pitch of its blade is fixed, and can not make described rotor produce negative lift, has following some deficiency:
1, can only, merely by regulating each motor speed to change gyroplane rotate speed, realize the variation of lift, cause that multi-rotor aerocraft response is fast not and wind loading rating is strong not;
2, in decline process, must reduce rotating speed, to reduce rotor lift, lift reduces with regard to meaning, the ability of multi-rotor aerocraft attitude control to be weakened, and multi-rotor aerocraft there will be the situation of waving even out of control;
3, can not realize aerobatics;
4, in the time that any rotor lost efficacy, cannot realize and making a return voyage.
Utility model content
The purpose of this utility model is: a kind of variable pitch device is provided, apply the rotor external member of described variable pitch device and apply described variable pitch device have that response is fast, wind loading rating strong, can aerobatics and can realize the multi-rotor aerocraft making a return voyage.
The utility model is achieved in that a kind of variable pitch device for multi-rotor aerocraft, and wherein, described variable pitch device comprises:
Permanent seat;
Connecting rod, for running through the rotating spindle that drives described blade rotation, described connecting rod movable arrange relative to described permanent seat;
Transmission component, be connected with described permanent seat, described transmission component comprises the blade mount pad for described blade is installed, described blade mount pad is connected with described connecting rod, with when the relatively described rotating spindle crank motion of described connecting rod, drive described blade mount pad to rotate to change the pitch of described blade by described connecting rod.
Preferably, described permanent seat comprises that cover plate and described cover plate are provided with through hole, and described rotating spindle correspondence is provided with the through hole that runs through its axis, and described connecting rod runs through respectively described through hole and described through hole setting.
Preferably, described blade mount pad comprises at least one the first blade mount pad and the second blade mount pad, and described transmission component also comprises:
At least one the first fork, one end of described the first fork is connected with described connecting rod, and the other end is connected with the first blade mount pad, for the crank motion of described connecting rod being converted to rotating around first direction of described the first blade mount pad;
At least one the second fork, one end of described the second fork is connected with described connecting rod, and the other end is connected with the second blade mount pad, for the crank motion of described connecting rod being converted to rotating around second direction of described the second blade mount pad.
Preferably, described transmission component also comprises the guide member, the first lug boss being connected with described the first fork and the second lug boss being connected with described the second fork that are connected with described the second fork with described the first fork respectively for realizing described connecting rod, and described guide member comprises:
Guiding body;
Connecting bore, is located on described guiding body, for connecting described connecting rod;
At least one the first chute, is located on described guiding body, connects for accommodating described the first lug boss relative sliding;
At least one the second chute, is located on described guiding body, connects for accommodating described the second lug boss relative sliding.
Preferably, one end that described the first fork is fixedly connected with described the first blade mount pad is tong-like to clamp described the first blade mount pad, and/or one end that described the second fork is fixedly connected with described the second blade mount pad is tong-like to clamp described the second blade mount pad.
Preferably, one end that described the first fork is fixedly connected with described the first blade mount pad is that corresponding first buckle slot that is provided with of the first clamping part and described the first blade mount pad clamps to realize, and one end that described the second fork is fixedly connected with described the second blade mount pad is that corresponding second buckle slot that is provided with of the second clamping part and described the second blade mount pad is to realize clamping.
Preferably, the first parallel sided that described guiding body closes on described the first blade mount pad is closed on the second side of described the second blade mount pad in described guiding body, described the first side is located at by described the first chute and described the second chute is located at described the second side.
Preferably, described permanent seat is provided with the fixed mount of tubular, and described blade mount pad also comprises the first revolving bar being sheathed in described fixed mount, and is sheathed on outside described the first revolving bar and is housed in the first attaching parts in described fixed mount.
Preferably, described blade mount pad is provided with clamping groove, for clamping, described blade is installed.
The utility model separately provides a kind of rotor external member, it comprises at least two blades and engine installation, and described at least two blades are assembled into rotor, and described engine installation is provided with the rotating spindle for driving described rotor, wherein, described rotor external member also disposes variable pitch device as above.
Preferably, described permanent seat is relative with described engine installation is close to setting, and described permanent seat is provided with sidewall, and described sidewall extends and is connected toward described engine installation direction from the cover plate of described permanent seat.
Preferably, described cover plate and/or described sidewall are provided with some louvres.
Preferably, described rotor external member also comprises straight line steering wheel or the leading screw for driving described connecting rod.
The utility model separately provides a kind of multi-rotor aerocraft, some horns that it comprises fuselage, be connected with described fuselage and lay respectively at the rotor external member on each described horn, and wherein, described rotor external member disposes variable pitch device as above.
Preferably, described multi-rotor aerocraft also comprises the second attaching parts being sheathed on described connecting rod.
The rotor external member of variable pitch device provided by the utility model and the described variable pitch device of application, its connecting rod, through described rotating spindle setting, is conducive to the miniaturization of variable pitch device and rotor external member.In addition, the multi-rotor aerocraft of the above-mentioned variable pitch device of application that the utility model provides, change by adjusting the mode of pitch of blade the lift that rotor produces, make its fast response time, wind loading rating strong, be difficult for waving, can realize aerobatics and in the time of any rotor inefficacy, can realize the function of making a return voyage.
Accompanying drawing explanation
Fig. 1 is the three-dimensional exploded view of the variable pitch device that provides of the utility model embodiment, wherein, has also shown the engine installation for driving blade;
Fig. 2 is the block diagram of the variable pitch device that provides of the utility model embodiment, wherein, has also shown the engine installation for driving blade;
Fig. 3 is the cutaway view of the variable pitch device that provides of the utility model embodiment, wherein, has also shown the engine installation for driving blade;
Fig. 4 is the birds-eye view of the variable pitch device that provides of the utility model embodiment, wherein, has also shown the engine installation for driving blade;
The schematic top plan view of the multi-rotor aerocraft of the variable pitch device shown in Fig. 5 application drawing 1;
The block diagram of the rotor external member of the variable pitch device shown in Fig. 6 application drawing 1.
The specific embodiment
In order to make goal of the invention of the present utility model, technical scheme and advantage clearer, below in conjunction with drawings and Examples, the utility model is further elaborated.Should be appreciated that specific embodiment described herein is only in order to explain the utility model, and be not used in restriction the utility model.
A kind of multi-rotor aerocraft that the utility model embodiment provides, it coordinates with remote controller and is used for taking photo by plane, ground mapping, Investigating and rescue, monitoring and polling transmission line etc. in the air.When work, described multi-rotor aerocraft carries The Cloud Terrace and pick up camera and receives the remote signal of remote controller, thereby realizes above-mentioned functions.In addition, described multi-rotor aerocraft also can be realized the function of making a return voyage after aerials and rotor inefficacy.
As shown in Figures 1 to 6, multi-rotor aerocraft 100 of the present utility model comprises fuselage 1, is connected with described fuselage 1 and with respect to the symmetrical some horns 2 of described fuselage 1 with lay respectively at the rotor external member 3 on each described horn 2.Any described rotor external member 3 comprise there is the rotor 32 of at least two blades 31, for change described blade 31 pitch variable pitch device 10 and drive the steering wheel 11 of described variable pitch device 10.Described multi-rotor aerocraft 100 also comprises the engine installation 41 that drives described blade 31 to rotate.It should be noted that, the present embodiment also can be according to actual needs and by the manufacture that forms a complete production network of horn 2 and rotor external member 3, horn 2 is attached in rotor external member 3, in this no limit.
Described variable pitch device 10 comprises the be close to permanent seat 12 that arrange, the connecting rod 13 and the transmission component 50 that with described permanent seat 12 be connected that run through described permanent seat 12 and relatively described permanent seat 12 movable settings relative to described engine installation 41.
Described permanent seat 12 comprises cover plate 14, extends and the some sidewalls 15, the through hole 16 that is positioned at described cover plate 14 middle parts that are connected with engine installation 41, be located at the fixed mount 61 a pair of separated by a distance on described cover plate 14 and be arranged on the some louvres 17 on described cover plate 14 and/or sidewall 15 to described engine installation 41 directions from described cover plate 14.When assembling, described connecting rod 13 is positioned at the interval of described a pair of described fixed mount 61.Any described fixed mount 61 is hollow tubular, and it comprises the fixed orifice 611 running through on it.
Blade mount pad 60 on the fixed orifice 611 that described transmission component 50 comprises the guide member 51 that is fixed on described connecting rod 13 and the first crank 521 and the second crank 522 that are rotatedly connected with the two ends of described guide member 51 respectively and is housed in respectively described fixed mount 61.
Described blade mount pad 60 comprises the first blade mount pad 601 and the second blade mount pad 602 of fixing respectively each blade 30.Described guide member 51 is elongated, and it comprises guiding body 53, is located on described guiding body 53 for connecting the connecting bore 54 of described connecting rod 13 and being located at respectively the first chute 551 and the second chute 552 on described guiding body 53.Described guiding body 53 is vertical with the axis of described connecting rod 13, the propulsive effort of described connecting rod 13 is passed to fast to described first, second crank 521,522, it comprises the first side 531 of closing on described the first blade mount pad 601 and the second side 532 of closing on described the second blade mount pad 602.Described the first side 531 is located at by described the first chute 551 and described the second chute 552 is located at described the second side 532; Described the first side 531 is parallel with the second side 532.Preferably, the bearing of trend of described first, second chute 551,552 is respectively perpendicular to the axis of described connecting rod 13.Described the first crank 521 comprises that the first fork 571 is connected with described the first fork 571 and is housed in the first lug boss 561 in described the first chute 551.Described the second crank 522 comprise the second fork 572 and with described the second fork 572 on and be housed in the second lug boss 562 in described the second chute 552.Described first, second fork 571,572 can be tabular or shaft-like etc., and itself and described guiding body 53 be arranged in parallel, and the compact conformation of described like this transmission component 50, to reduce the volume of described rotor craft 100.The utility model utilizes the bearing fit of described first, second chute 551,552 and described first, second lug boss 561,562, realizes transmission agency and is conducive to described multi-rotor aerocraft 100 miniaturizations.In fact, the sliding matching structure of described first, second chute 551,552 and described first, second lug boss 561,562 also can be replaced by bulb connection structure well known in the art.
First, second blade mount pad 601,602 of described blade mount pad 60 is housed in respectively in described fixed mount 61.Described the first blade mount pad 601 comprises the first revolving bar 630 of column and the first blade holding piece 641 extending parallel to each other from one end of described the first revolving bar 630.Described blade mount pad 60 is also provided with the clamping groove 66 of the corresponding described blade 30 of clamping installation.The structure of described the second blade mount pad 602 is identical with the structure of the first blade mount pad 601, therefore repeat no more.One end that described the first fork 571 is fixedly connected with described the first blade mount pad 601 is tong-like to clamp described the first blade mount pad 601, and/or one end that described the second fork 572 is fixedly connected with described the second blade mount pad 602 is tong-like to clamp described the second blade mount pad 602.In present embodiment, described the first fork 571 is also provided with the first clamping part 581; Described the second fork 572 is also provided with the second clamping part 582.Described the first blade mount pad 601 also comprises and lays respectively on described the first revolving bar 630 and can be buckled in respectively the first buckle slot 651 in the first clamping part 581 of described the first fork 571; Described the second blade mount pad 602 comprises the second buckle slot 652 in the second clamping part 582 that is buckled in described the second fork 572.Preferably, described the first blade mount pad 601 also comprises that to be set in described the first revolving bar 630 outer and be housed in the first attaching parts 631 in described fixed orifice 611.Described the first attaching parts 631 can be assisted the stable and rotation glibly in described fixed mount 61 of the first revolving bar 630.In present embodiment, described the first attaching parts 631 is antifriction-bearing box.Certainly, described the first attaching parts also can be replaced with the parts that realize above-mentioned connection and stable rotation well known to those skilled in the art.
In present embodiment, described connecting rod 13 is connected with described steering wheel 11, can be along its axis with respect to the upper and lower crank motion of described permanent seat 12.The described connecting rod 13 of described variable pitch device 10 is connected with described steering wheel 11, described transmission component 50 coordinates with described connecting rod 13, in order to the upper and lower crank motion power of described connecting rod 13 is converted to the motion of described blade mount pad 60 around the axle rotation of its first revolving bar 630, thereby control described blade 31 fast, precisely change, change the pitch of described blade 31.The preferred straight line steering wheel of described steering wheel 11, in order to improve adjustment precision and the speed of response of pitch of described blade 31; Certainly, also can adopt in other embodiments leading screw to carry out drive link 13, in this no limit.
Described engine installation 41 comprises the rotating spindle 43, the rotor 45 being rotatedly connected with described rotating spindle 43 and the stator 44 being connected with described rotating spindle 43 that drive described blade 31 to rotate.The described sidewall 15 of described permanent seat 12 is connected with described rotor 45.In the time that described rotor 45 rotates, it drives described permanent seat 12 unitary rotation, thereby drives described blade mount pad 60 to rotate, and finally realizes the rotation of described blade 31.Described rotating spindle 43 is hollow, and it is provided with the through hole 431 that runs through its axis.The outer wall opposing parallel of the inwall of described rotating spindle 43 and described connecting rod 13 arranges.When assembling, one end of described connecting rod 13 is connected with described transmission component 50 through the described through hole 431 of described rotating spindle 43 and the described through hole 16 of described permanent seat 12 respectively, can realize like this miniaturization of described multi-rotor aerocraft 100.Certainly, described connecting rod 13 can only also can be realized the miniaturization of described multi-rotor aerocraft 100 through described rotating spindle 43.Described transmission component 50 during with respect to described rotating spindle 43 crank motion, drives described blade mount pad 60 to rotate to change the pitch of described blade 31 at described connecting rod 13.Wherein, the present embodiment engine installation 41 can adopt the mode of motor, specifically can adopt small-sized brushless motor, in this no limit.
Preferably, described multi-rotor aerocraft 100 also comprises and is positioned at the described through hole 431 of described rotating spindle 43 and is set in the second attaching parts 46 on described connecting rod 13.Described the second attaching parts 46 plays a part lubricated in the time of described connecting rod 13 upper and lower crank motion.Described engine installation 41 relies on the described some louvres 17 on described permanent seat 12 to dispel the heat.Described the second attaching parts 46 is linear bearing, also can replace with the parts of the familiar lubricate in this areas such as axle sleeve.
Except said structure; the variable pitch device 10 of the present embodiment can also be provided with upper cover (not shown); described upper cover is used for accommodating protection guide 51; further; described upper cover is fixed frame 61 and cover plate 14 and forms the space of relative closure; so that the structures such as guide 51, connecting rod 13 are enveloped, can protect in this way tiny structure by impact wreckage, can also improve the aesthetic property of variable pitch device 10 entirety.
In other selectable embodiments, for reducing the total weight of described multi-rotor aerocraft, the described engine installation 41 that the described rotor 32 of described driving rotates, except adopting the mode of motor, also can utilize the mechanical drives such as belt transmission to replace., described belt transmission drives described permanent seat to rotate.In present embodiment, described rotating spindle 43 is directly connected with described permanent seat 12 respectively with described rotor 45, utilizes described rotor 45 and 43 combineds action of described rotating spindle, drives described permanent seat 12 unitary rotation.In fact, described permanent seat also can be connected with rotor and/or described permanent seat indirectly by miscellaneous part; Or only rely on described rotating spindle to be directly connected respectively with described permanent seat, drive described permanent seat unitary rotation; Rely on again or only described rotor to be directly connected respectively with described permanent seat, permanent seat unitary rotation.In the time only utilizing described rotor to drive described permanent seat, described rotating spindle is followed described permanent seat and is rotated together; Or described rotating spindle does not rotate, only have described permanent seat to rotate separately.In sum, the utility model alleged " being connected " comprises the directly connected and two kinds of connection modes that are indirectly connected.In addition, described rotating spindle can be not be realized and being rotated by described rotor, and it can utilize under the drive of the mechanicals device such as belt transmission and realize and rotating.
The variable pitch process of described blade 31 is: described steering wheel 11 rotates, drive coupled described connecting rod 13 upward movements, described guide member 51 promotes described the first crank 521 simultaneously and rotates around second direction around first direction rotation and described the second crank 522 under the drive of described connecting rod 13, thereby around corresponding direction rotation, (the first blade mount pad 601 rotates around first direction respectively to drive described blade mount pad 60, the second blade mount pad rotates around second direction), and then make the angle between two blades 31 and its rotational plane increase (being that pitch increases) simultaneously, increase resultant couple, otherwise if desired reduce moment, make described connecting rod 13 move downward, now the first blade mount pad 601 rotates around first direction around second direction rotation, the second blade mount pad, make the angle between two blades 31 and horizontal surface reduce (being that pitch reduces) simultaneously, or be negative angle and increase and form negative lift (making to produce the reverse power of accelerating decline after rotor wing rotation), the present embodiment is realized described multi-rotor aerocraft variable pitch process by said process.Wherein, in the time only having two blades, described first, second direction is reciprocal.
It should be noted that, the utility model also can be adjusted the type of drive between described connecting rod 13 and blade 31 according to actual conditions, and described connecting rod 13 upward movements are set to reduce pitch, described connecting rod 13 moves downward and is set to increase pitch, its corresponding structure and fit system that changes transmission component 50, in the art personnel scope that easily combination is understood, do not repeat and limit.
In other selectable embodiment, described transmission component can directly only adopt the mode of blade mount pad, between described connecting rod and described blade mount pad, can adopt the gear structure being engaged with each other, described connecting rod direct motion can drive the rotation of blade mount pad.
In addition, the described guide member of described transmission component, described first, second chute and described first, second lug boss can omit, and directly utilize described first, second fork to be connected with corresponding described blade mount pad with described connecting rod respectively.Be specially: described transmission component comprises the first blade mount pad and the second blade mount pad, at least one the first fork and at least one the second fork that are connected with described connecting rod at least two blades described in installing.One end of described the first fork is connected with described connecting rod, and the other end is connected with the first blade mount pad, for the crank motion of described connecting rod being converted to rotating around first direction of described the first blade mount pad; One end of described the second fork is connected with described connecting rod, and the other end is connected with the second blade mount pad, for the crank motion of described connecting rod being converted to rotating around second direction of described the second blade mount pad; Wherein, described first direction and described second direction are reciprocal.
In addition, in the selectable embodiment of another kind, described first, second fork adopts flexible material, and described connecting rod can rotate by twisting, pulls blade mount pad and forces its rotation.
It should be noted that the function that can also adopt the variable pitch device of the helicopter tail rotor of prior art to realize variable pitch in other embodiment of the present utility model, therefore not to repeat here.
Described multi-rotor aerocraft of the present utility model, it is provided with described variable pitch device, brings following advantage:
(1) the described multi-rotor aerocraft in the utility model, it is provided with described variable pitch device.The described connecting rod of described variable pitch device, through the axis setting of described rotating spindle, is conducive to the miniaturization of described multi-rotor aerocraft.
(2) the described multi-rotor aerocraft in the utility model has described variable pitch device, in rotation speed change, the pitch of described blade can change thereupon, effectively raise the peak efficiency of described engine installation under each rotating speed, having improved workload, is efficient multi-rotor aerocraft.Meanwhile, described gyroplane rotate speed can wide variation, to the control ability of described multi-rotor aerocraft attitude is stronger and wind resistance is better, is a kind of stable multi-rotor aerocraft.
(3) lifting of workload can reduce the diameter of described rotor.According to aerodynamics, described rotor diameter is larger, and maneuvering performance is poor, wind loading rating is low, easily wave with out of control; Therefore, the operating characteristic of multi-rotor aerocraft of the present utility model improves greatly.
(4), in the time that any described rotor lost efficacy, can, by the variation of the pitch of the described blade of other effective described rotors of control, realize the function of making a return voyage of described multi-rotor aerocraft.
(5) the described variable pitch device of the described multi-rotor aerocraft in the utility model, can realize the aerobatics of multi-rotor aerocraft.
It should be noted that front end in the present embodiment, the position terms such as upper and lower are take the conventional operation attitude of multi-rotor aerocraft as reference, and are not considered to be restrictive.What the utility model embodiment accompanying drawing provided is a kind of cross-shape layout quadrotor, and described fuselage and horn have adopted omissive representation, and the utility model can also be applied on the even number rotor craft that is greater than four.Certainly, the utility model also can be used on the aircraft of five above odd number rotors.
These are only preferred embodiment of the present utility model, not in order to limit the utility model, all any modifications of doing within spirit of the present utility model and principle, be equal to and replace or improvement etc., within all should being included in protection domain of the present utility model.
Claims (15)
1. for changing a variable pitch device for blade pitch, it is characterized in that, described variable pitch device comprises:
Permanent seat;
Connecting rod, for running through the rotating spindle that drives described blade rotation, described connecting rod movable arrange relative to described permanent seat;
Transmission component, be connected with described permanent seat, described transmission component comprises the blade mount pad for described blade is installed, described blade mount pad is connected with described connecting rod, with when the relatively described rotating spindle crank motion of described connecting rod, drive described blade mount pad to rotate to change the pitch of described blade by described connecting rod.
2. variable pitch device according to claim 1, it is characterized in that, described permanent seat comprises that cover plate and described cover plate are provided with through hole, and described rotating spindle correspondence is provided with the through hole that runs through its axis, and described connecting rod runs through respectively described through hole and described through hole setting.
3. variable pitch device according to claim 1 and 2, is characterized in that, described blade mount pad comprises at least one the first blade mount pad and the second blade mount pad, and described transmission component also comprises:
At least one the first fork, one end of described the first fork is connected with described connecting rod, and the other end is connected with the first blade mount pad, for the crank motion of described connecting rod being converted to rotating around first direction of described the first blade mount pad;
At least one the second fork, one end of described the second fork is connected with described connecting rod, and the other end is connected with the second blade mount pad, for the crank motion of described connecting rod being converted to rotating around second direction of described the second blade mount pad.
4. variable pitch device according to claim 3, it is characterized in that, described transmission component also comprises the guide member, the first lug boss being connected with described the first fork and the second lug boss being connected with described the second fork that are connected with described the second fork with described the first fork respectively for realizing described connecting rod, and described guide member comprises:
Guiding body;
Connecting bore, is located on described guiding body, for connecting described connecting rod;
At least one the first chute, is located on described guiding body, connects for accommodating described the first lug boss relative sliding;
At least one the second chute, is located on described guiding body, connects for accommodating described the second lug boss relative sliding.
5. variable pitch device according to claim 4, it is characterized in that, one end that described the first fork is fixedly connected with described the first blade mount pad is tong-like to clamp described the first blade mount pad, and/or one end that described the second fork is fixedly connected with described the second blade mount pad is tong-like to clamp described the second blade mount pad.
6. variable pitch device according to claim 5, it is characterized in that, one end that described the first fork is fixedly connected with described the first blade mount pad is that corresponding first buckle slot that is provided with of the first clamping part and described the first blade mount pad clamps to realize, and one end that described the second fork is fixedly connected with described the second blade mount pad is that corresponding second buckle slot that is provided with of the second clamping part and described the second blade mount pad is to realize clamping.
7. variable pitch device according to claim 4, it is characterized in that, the first parallel sided that described guiding body closes on described the first blade mount pad is closed on the second side of described the second blade mount pad in described guiding body, described the first side is located at by described the first chute and described the second chute is located at described the second side.
8. variable pitch device according to claim 1, it is characterized in that, described permanent seat is provided with the fixed mount of tubular, described blade mount pad also comprises the first revolving bar being sheathed in described fixed mount, and is sheathed on outside described the first revolving bar and is housed in the first attaching parts in described fixed mount.
9. variable pitch device according to claim 1 and 2, is characterized in that, described blade mount pad is provided with clamping groove, for clamping, described blade is installed.
10. the rotor external member for multi-rotor aerocraft, described rotor external member comprises at least two blades and engine installation, described at least two blades are assembled into rotor, described engine installation is provided with the rotating spindle for driving described rotor, it is characterized in that, described rotor external member also disposes according to the variable pitch device described in claim 1～9 any one.
11. rotor external members according to claim 10, is characterized in that, described permanent seat is relative with described engine installation is close to setting, and described permanent seat is provided with sidewall, and described sidewall extends and is connected toward described engine installation direction from the cover plate of described permanent seat.
12. rotor external members according to claim 11, is characterized in that, described cover plate and/or described sidewall are provided with some louvres.
13. according to the rotor external member described in claim 10～12 any one, it is characterized in that, described rotor external member also comprises straight line steering wheel or the leading screw for driving described connecting rod.
14. 1 kinds of multi-rotor aerocrafts, some horns that it comprises fuselage, be connected with described fuselage and lay respectively at the rotor external member on each described horn, it is characterized in that, described rotor external member disposes according to the variable pitch device described in claim 1～9 any one.
15. multi-rotor aerocrafts according to claim 14, is characterized in that, described multi-rotor aerocraft also comprises the second attaching parts being sheathed on described connecting rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320858564.XU CN203623961U (en) | 2013-12-24 | 2013-12-24 | Screw pitch varying device, as well as rotor wing suite and multi-rotor-wing aircraft using same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320858564.XU CN203623961U (en) | 2013-12-24 | 2013-12-24 | Screw pitch varying device, as well as rotor wing suite and multi-rotor-wing aircraft using same |
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| Publication Number | Publication Date |
|---|---|
| CN203623961U true CN203623961U (en) | 2014-06-04 |
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|---|---|---|---|
| CN201320858564.XU Expired - Fee Related CN203623961U (en) | 2013-12-24 | 2013-12-24 | Screw pitch varying device, as well as rotor wing suite and multi-rotor-wing aircraft using same |
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| CN (1) | CN203623961U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103661926A (en) * | 2013-12-24 | 2014-03-26 | 深圳市大疆创新科技有限公司 | Variable-screw-pitch device and rotor wing assembly and multiple rotor wing aircraft adopting same |
| CN105539832A (en) * | 2015-12-24 | 2016-05-04 | 上海埃威航空电子有限公司 | Variable-pitch power device for multi-rotor-wing unmanned aerial vehicle |
| CN106892103A (en) * | 2017-01-23 | 2017-06-27 | 南京航空航天大学 | The helicopter rotor system and method for the electronic displacement of energy and automatic installing/dismounting blade |
| CN111065577A (en) * | 2017-08-23 | 2020-04-24 | 维曼机器人股份有限公司 | Driving mechanism |
-
2013
- 2013-12-24 CN CN201320858564.XU patent/CN203623961U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103661926A (en) * | 2013-12-24 | 2014-03-26 | 深圳市大疆创新科技有限公司 | Variable-screw-pitch device and rotor wing assembly and multiple rotor wing aircraft adopting same |
| CN103661926B (en) * | 2013-12-24 | 2016-09-28 | 深圳市大疆创新科技有限公司 | Variable-screw-pitch-device and rotor external member and the multi-rotor aerocraft of applying this device |
| CN105539832A (en) * | 2015-12-24 | 2016-05-04 | 上海埃威航空电子有限公司 | Variable-pitch power device for multi-rotor-wing unmanned aerial vehicle |
| CN106892103A (en) * | 2017-01-23 | 2017-06-27 | 南京航空航天大学 | The helicopter rotor system and method for the electronic displacement of energy and automatic installing/dismounting blade |
| CN111065577A (en) * | 2017-08-23 | 2020-04-24 | 维曼机器人股份有限公司 | Driving mechanism |
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