CN109484637A - A kind of rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil - Google Patents
A kind of rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil Download PDFInfo
- Publication number
- CN109484637A CN109484637A CN201811580661.0A CN201811580661A CN109484637A CN 109484637 A CN109484637 A CN 109484637A CN 201811580661 A CN201811580661 A CN 201811580661A CN 109484637 A CN109484637 A CN 109484637A
- Authority
- CN
- China
- Prior art keywords
- rotor
- unmanned plane
- distance varying
- varying mechanism
- pulp distance
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/32—Blade pitch-changing mechanisms mechanical
Abstract
This application provides a kind of rotor pulp distance varying mechanisms of improved dynamic unmanned plane of oil, have a hollow spindle, the rotor is fixedly mounted on the upper end of the hollow spindle by a mounting base；The mounting base, which corresponds to each rotor, has horizontally disposed two plate support arms up and down by its rotation center is protruding, and the plain film shape wing root of the rotor is clamped to be mounted between described two plate support arms；There are two spherical joints for setting on the plain film shape wing root；The rotor can be deflected around described two spherical joint lines of centres.The rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil of the application clamps the plain film shape wing root of rotor by the plate support arm of mounting base, eliminate bulky disk-shaped structure, support of the more frivolous plate support arm offer to rotor has been provided instead, rotor can also use tabular wing root, thick and heavy rotary shaft that no setting is required.Construction weight can be mitigated significantly, improve the carrying ability of payload.
Description
Technical field
The present invention relates to air vehicle technique field more particularly to a kind of unmanned plane of more rotors, in particular to a kind of improvement
Oil move unmanned plane rotor pulp distance varying mechanism.
Background technique
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft.Unmanned plane press application field, can be divided into it is military with it is civilian.Military aspect, unmanned plane are divided into reconnaissance plane and target
Machine.Civilian unmanned plane is taking photo by plane, agricultural, plant protection, miniature self-timer, express transportation, disaster relief, observation wild animal, is monitoring biography
It catches an illness, survey and draw, news report, electric inspection process, the disaster relief, the fields such as movies-making are widely used.
Existing multi-rotor unmanned aerial vehicle is usually electronic unmanned plane.The structure of more electronic unmanned planes of rotor is simply easily fabricated,
Motor is light-weight, stability of rotation, and dynamical system is easy to standardize, thus complete machine is relatively easy to manipulate, and flight noise is low,
Develop in short voyage civil field more active.However since the energy density of battery is well below fuel oil, electronic unmanned plane by
To the limitation of battery, voyage is shorter, and load level is lower, can not be applied to military big load scout-attack field.And it is existing
The fuel oil unmanned plane of long voyage generallys use fixed wing structure, and limitation of the landing by airport of taking off can not hover, and cost is high,
Manipulate cumbersome, the flexible property used is inadequate.
106697278 A of CN discloses that a kind of direct-drive type oil is dynamic to determine revolving speed feather multi-rotor unmanned aerial vehicle, including fuselage,
Dynamical system, undercarriage and avionics system, the fuselage are the integrated fuselage of Quan Fucai, and the dynamical system is by starting
Machine system, pitch-variable system, oil supply system and rotor system composition.Six rotors of the unmanned plane of the above-mentioned prior art are angularly
It is arranged intermittently around body, causes the application load carried on body that can only be set to immediately below body, and due to all directions
All by the blocking of rotor, the load of carrying can only carry out downwards operation, weapon delivery or can not be observed obliquely upward,
It is low that there are load levels, and topology layout is unreasonable, it is difficult to play the control of unmanned plane and the defect of security advantages, limit rotor
Unmanned aerial vehicle is in military and monitoring field development and application.
205998123 U of CN discloses a kind of vertical layout fuel power quadrotor flying platform, and composition includes machine
Frame, dynamical system, navigation and control system, electrical system and task platform.Four identical horns are docked at are connected with two-by-two
Rack is formed on the monocogue of undercarriage；The end of each horn is arranged in dynamical system, provides power for flying platform
And the energy；Navigation and control system perception and the posture, height and the position that control flying platform；Electrical system has charging, supplies
Electricity and instruction function；Task platform is for installing different task devices.The unmanned plane of the prior art is provided with four independences
Engine, the mutual interference in air flow of adjacent rotor is difficult to mediate, and the spacing of greater engine can further increase volume
And weight.
The unmanned plane of the above-mentioned prior art configures an oil on each cantilever and moves engine, and exposed engine adds
The noise of rotor causes unmanned plane that cannot almost use in city airspace, using also without what concealment under military environment.
106184740 A of CN disclose it is a kind of for unmanned plane rotary wing changing away from device, wherein also disclose one kind four
The unmanned plane of rotor, the unmanned plane pass through be arranged in fuselage interior two axis output oil move engine to two pairs of front and back rotor into
Row driving, but its special engine technology used is immature, output power is limited, can not be applied to the arms nothing of big load
It is man-machine.In addition, rotary wing changing used by the prior art away from device, the upper sliding block being set in by servo driving on main shaft
It slides up and down, to drive the transmission arm being connected with upper sliding block to be acted, and then rotor rotational is driven by transmission arm,
To change the angle of attack of rotor, to realize rotary wing changing away from purpose.But in the prior art, due to needing to be arranged on main shaft
Sliding block, the height for causing main shaft to stretch out upwards from cantilever is too big, and main shaft needs higher intensity, bigger weight, and main shaft is straight
Diameter is also very big.Around the sliding block of the various hollow structures of main shaft setting, become larger with becoming larger for major axis diameter, in addition, with
Main axis length it is elongated, the stroke for manipulating the connecting rod of displacement can also become larger, and steering engine needs bigger angle to be manipulated, thus
The case where being easy to happen locking, and since the connecting rod of connection steering engine is too far apart from manipulating objects, cause link mechanism very multiple
Miscellaneous, reliability can undoubtedly reduce very much, and construction weight also becomes very big.
For the defect for solving the above-mentioned prior art, present applicant is in the Chinese patent application applied before
In 201711089263.4, a kind of unmanned plane rotor pulp distance varying mechanism is disclosed, there is a hollow spindle, the rotation of unmanned plane
The wing is fixedly mounted on the upper end of the hollow spindle and drives the rotor rotational to generate lift by the hollow spindle；It is described
Hollow spindle is internally provided with a pitch control bar, and the upper end of pitch control bar can be connected with one with rotating to it can be with
The power transmission arm support that the pitch control bar moves up and down, the power transmission arm support drive the bias of the rotor by power transmission arm
Armband is moved the rotor and is rotated around its mounting axis to change the angle of attack of the rotor.The prior art is by by pitch control bar
It is arranged inside hollow spindle, so that do not need to reserve the space of installation pitch-changing mechanism between rotor and cantilever, main shaft is from cantilever
The height stretched out upwards can become smaller as far as possible, significantly reduce construction weight, improve effective load of the unmanned plane of the application
Lotus carries ability.
The prior art effectively overcomes the defect of the prior art, but still has room for improvement.Especially this is existing
There is the mounting base weight of the rotor of technology too big, each rotor is required to be mounted on mounting base by independent shaft, bearing etc.
On, cause the weight of mounting base very big, and due to the increase of the construction weights such as the shaft of rotor, it has to further increase
The intensity of association structure is further degrading the load of unmanned plane, it is accordingly required in particular to further step be taken to mitigate construction weight.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of rotor pulp distance varying mechanisms of improved dynamic unmanned plane of oil, to subtract
Less or avoid the problem that being formerly mentioned.
In order to solve the above technical problems, the invention proposes a kind of rotor pulp distance varying mechanism of improved dynamic unmanned plane of oil,
For moving the rotor rotational of unmanned plane by servo driving oil to change the angle of attack of the rotor, the flight support is in the oil
The end of the cantilever of dynamic unmanned plane；The rotor pulp distance varying mechanism has a hollow spindle, and the rotor passes through an installation
Seat is fixedly mounted on the upper end of the hollow spindle；The hollow spindle is internally provided with one can be along the length of the hollow spindle
The pitch control bar that direction moves up and down is spent, the upper end of the pitch control bar can be connected with one with rotating to it can be with institute
The power transmission arm support of pitch control bar up and down motion is stated, the power transmission arm support drives the eccentric arm of the rotor by power transmission arm
Drive the rotor rotational；The steering engine connect with the lower end of the pitch control bar by connecting rod and manipulates the pitch control
Bar moves up and down；Wherein, the mounting base corresponds to each rotor and is had above and below horizontally disposed by its rotation center is protruding
Two plate support arms, the plain film shape wing root of the rotor is clamped to be mounted between described two plate support arms；The plain film shape
There are two spherical joints for setting on wing root；The rotor can be deflected around described two spherical joint lines of centres.
Preferably, the spherical joint is stuck in the joint hole of the plain film shape wing root.
Preferably, the spherical joint is fixed between described two plate support arms by joint bolt.
Preferably, the mounting hole passed through for the joint bolt, the spherical pass are provided on described two plate support arms
Saving has the joint hole passed through for the joint bolt.
Preferably, the hollow spindle setting is protruding from the inside of a retainer, the bottom tool of the retainer
There is the port that the lower end for the pitch control bar is pierced by.
Preferably, the outside of the cantilever, and the company of the lower section by the way that the retainer is arranged in is arranged in the steering engine
Bar is connect with the lower end of the pitch control bar.
Preferably, the bottom of the retainer is provided with link supports seat.
Preferably, the cantilever is hollow structure, is internally provided with drive rod, the end of drive rod is provided with the first cone
Gear, the first bevel gear are meshed with a second bevel gear, and the second bevel gear is connected to the sky by spline
On heart main shaft, and it is located at the top of the retainer.
The rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil of the application clamps rotor by the plate support arm of mounting base
Plain film shape wing root, eliminate bulky disk-shaped structure, used more frivolous plate support arm instead and support to rotor, rotation are provided
The wing can also use tabular wing root, thick and heavy rotary shaft that no setting is required.Construction weight can be mitigated significantly, improved effectively
The carrying ability of load.
Detailed description of the invention
The following drawings are only intended to schematically illustrate and explain the present invention, not delimit the scope of the invention.Wherein,
The oil that a specific embodiment according to the present invention is shown in Fig. 1 moves the structural schematic diagram of unmanned plane；
The rotor feather machine of the dynamic unmanned plane of improved oil according to the specific embodiment of the application is shown in Fig. 2
The external structure schematic diagram of structure；
The broken section decomposition diagram of Fig. 2 illustrated pitch spacing mechanism is shown in Fig. 3；
The rotor mounting structure schematic diagram of Fig. 2 illustrated pitch spacing mechanism is shown in Fig. 4；
The cross-sectional view of rotor mounting structure shown in Fig. 3 is shown in Fig. 5.
Specific embodiment
For a clearer understanding of the technical characteristics, objects and effects of the present invention, this hair of Detailed description of the invention is now compareed
Bright specific embodiment.Wherein, identical component uses identical label.
As described in background, the application is for disclosed in prior art China patent application 201711089263.4
The deficiency of pulp distance varying mechanism proposes a kind of improved structure, eliminates the Rotor mount of the prior art, and rotor is also no longer logical
It crosses shaft to be mounted in mounting base, greatly reduces construction weight, improve the payload of unmanned plane.
Specifically, the pulp distance varying mechanism of the dynamic unmanned plane of improvement oil of the application is the feather 201711089263.4
The further improvement proposed on the basis of mechanism, text of the statement quote the prior art, and those skilled in the art can be with base
The other structures in relation to the dynamic unmanned plane of oil are understood in the prior art disclosure.As shown in Figure 1, wherein Fig. 1 is shown
The oil of a specific embodiment according to the present invention moves the schematic perspective view of unmanned plane.
It is same as the prior art referring to Fig. 1, the oil of the application move unmanned plane equally include fuselage 1, undercarriage 2, four it is outstanding
Arm 3 and four rotors 5, fuselage 1 connect four cantilevers 3, and the end of each cantilever 3 is supported by the rotor of a same diameter
5.Each rotor 5 is around the pod 4 for being provided with the identical circular ring shape of a shape.
The specific feature of the unmanned plane rotor pulp distance varying mechanism of the application is further described referring to Fig. 2-4,
In, the rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil according to the specific embodiment of the application is shown in Fig. 2
External structure schematic diagram；The broken section decomposition diagram of Fig. 2 illustrated pitch spacing mechanism is shown in Fig. 3；Figure is shown in Fig. 4
The rotor mounting structure schematic diagram of 2 illustrated pitch spacing mechanisms.
Similar with the structure of the 201711089263.4 of background technique pulp distance varying mechanism, cantilever 3 is hollow structure, in
Portion is provided with drive rod (not shown), and the end of drive rod is provided with first bevel gear 91, first bevel gear 91 and one
Second bevel gear 92 is meshed, and second bevel gear 92 connects the hollow spindle 68 for driving rotor 5 to rotate by spline.
Rotor 5 is fixedly mounted on the upper end of hollow spindle 68 and drives the rotation of rotor 5 to generate lift by hollow spindle 68.
Hollow spindle 68 is internally provided with the pitch control bar 65 that can be moved up and down along the length direction of hollow spindle 68, displacement behaviour
Vertical pole 65 manipulates its up and down motion by steering engine 67.The upper end of pitch control bar 65 can be connected with one with rotating to it can be with
Pitch control bar 65 move up and down power transmission arm support 64, power transmission arm support 64 by power transmission arm 641 drive rotor 5 bias
Arm 59 drives rotor 5 to rotate, so as to change the angle of attack of rotor 5.More specifically, steering engine 67 passes through connecting rod and pitch control bar
65 lower end connects and manipulates the up and down motion of pitch control bar 65.Quantity on power transmission arm support 64 corresponding to rotor 5 is connected with
Multiple power transmission arms 641, the eccentric arm 59 of the other end connection rotor 5 of power transmission arm 641.It is each outstanding in diagram specific embodiment
The quantity for the rotor 5 that arm 3 connects is three.
In general, the unmanned plane rotor pulp distance varying mechanism of the application can be used for driving the rotor of unmanned plane by steering engine 67
5 rotations are to change the angle of attack of rotor 5, to achieve the purpose that the pitch for changing the rotor of unmanned plane.The improved oil of the application is dynamic
The working principle of the rotor pulp distance varying mechanism of unmanned plane is identical as the pulp distance varying mechanism of the prior art 201711089263.4, is all
The pitch control bar 65 inside hollow spindle 68 is driven to move up and down by steering engine 67, pitch control bar 65 drives power transmission arm support
64 move up and down, and then the eccentric arm 59 for driving power transmission arm 641 to drive rotor 5 drives rotor 5 to rotate, so as to change rotor
5 angle of attack.
In the pulp distance varying mechanism of the above-mentioned prior art 201711089263.4, rotor 5 is mounted on a peace by installation axle
It fills on seat, mounting base is fixedly mounted on the upper end of hollow spindle 68, when hollow spindle 68 rotates, mounting base is driven to turn
Dynamic, the rotor 5 that mounting base is further driven in installation axle is rotated to generate lift.When carrying out displacement operation, displacement behaviour
Vertical pole 65 manipulates power transmission arm 641 and the eccentric arm 59 of rotor 5 is driven to rotate around installation axle.Therefore, the mounting base of the prior art
On installation axle must have bearing so that rotor 5 can be rotated around installation axle.Simultaneously as the bearing also needs to bear to revolve
The centrifugal force when wing 5 rotates, therefore have sizable requirement to the intensity of installation axle, the type of bearing and intensity.Thus
The volume of the mounting base of the prior art is caused to seem especially huge in its attached drawing, and in the mounting base of the prior art
Installation axle also seems especially sturdy, and the strength demand of the installation axle and mounting base that show the prior art is very big, construction weight
It is very big, very big influence is caused to the payload of unmanned plane.And mounting base is located at the highest point position above cantilever, peace
The weight more large_cantilever structure for filling seat and installation axle is also more unstable.The increase of a series of construction weight, it has into one
Step increases the intensity of association structure, is further degrading the load of unmanned plane.
To solve drawbacks described above, this application provides a kind of rotor pulp distance varying mechanisms of improved dynamic unmanned plane of oil, especially
As shown in Figure 3-4, the rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil of the application, is equally used for driving oil by steering engine 67
The rotor 5 of dynamic unmanned plane is rotated to change the angle of attack of rotor 5.Wherein, the rotor pulp distance varying mechanism of the application equally has one
Hollow spindle 68, rotor 5 are fixedly mounted on the upper end of hollow spindle 68 by a mounting base 651；It is set inside hollow spindle 68
It is equipped with the pitch control bar 65 that can be moved up and down along the length direction of hollow spindle 68, the upper end of pitch control bar 65 can phase
The power transmission arm support 64 that can be moved up and down with displacement control stick 65 is rotationally connected with to it, power transmission arm support 64 passes through biography
The arm of force 641 drives the eccentric arm 59 of rotor 5 that rotor 5 is driven to rotate；Steering engine 67 is connected by the lower end of connecting rod and pitch control bar 65
It connects and manipulates the up and down motion of pitch control bar 65.
The setting of hollow spindle 68 is protruding from the inside of a retainer 69, and the bottom of retainer 69 has grasps for displacement
The port that the lower end of vertical pole 65 is pierced by.The bottom of retainer 69 is provided with link supports seat 691.Cantilever 3 is hollow structure, in
Portion is provided with drive rod (not shown), and the end of drive rod is provided with first bevel gear 91, first bevel gear 91 and one
Second bevel gear 92 is meshed, and second bevel gear 92 is connected on hollow spindle 68 by spline.
In the specific embodiment of the application, the setting of second bevel gear 92 is located at the top of retainer 69, that is,
Rotation during the power transmission of the application, for driving the second bevel gear 92 of hollow spindle 68 and being driven by hollow spindle 68
For spacing between the wing 5 more closely, transmission path is shorter, hollow spindle 68 is not easy bending deformation, reduces to hollow spindle
68 intensity requirement can further decrease construction weight using lighter thinner hollow spindle 68.
In addition, unlike the prior art, this application provides a kind of improved mounting bases 651, and the mounting base 651 is not
It is bulky disc-shaped structure again, also not for installing the shaft of rotor 5, does not also need that specific bearing is installed.As schemed
Show, the mounting base 651 of the application corresponds to each rotor 5 there are horizontally disposed upper and lower two to put down by its rotation center is protruding
Plate support arm 652, the plain film shape wing root 52 of rotor 5 is clamped to be mounted between two plate support arms 652；It is set on plain film shape wing root 52
Spherical joint 53 there are two setting；Rotor 5 can be deflected around two 53 lines of centres 531 of spherical joint.
As it can be seen that spherical joint 53 is stuck in the pass of plain film shape wing root 52 in the cross-sectional view of rotor mounting structure as shown in Figure 5
In knothole 54.Spherical joint 53 is fixed between two plate support arms 652 by joint bolt.It is set on two plate support arms 652
It is equipped with the mounting hole 653 passed through for joint bolt, spherical joint 53 has the joint hole 55 passed through for joint bolt.
In addition, the outside of cantilever 3, and the connecting rod of the lower section by the way that retainer 69 is arranged in is arranged in the steering engine 67 of the application
It is connect with the lower end of pitch control bar 65.The outside of cantilever 3 is arranged in steering engine 67, simplifies the requirement of the position to steering engine 67,
The manipulation of connecting rod can mitigate the stress of connecting rod in the case where operational torque is constant apart from elongated, thus can be using lighter
Thinner connecting rod can also further decrease construction weight.
The rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil of the application clamps rotor by the plate support arm of mounting base
Plain film shape wing root, eliminate bulky disk-shaped structure, used more frivolous plate support arm instead and support to rotor, rotation are provided
The wing can also use tabular wing root, thick and heavy rotary shaft that no setting is required.Because what is mainly generated when rotor wing rotation is
Centrifugal force and lift, plate support arm are horizontally disposed, obtain the concentration of biggish bending moment confrontation lift load enough, because without
More thick and heavy structure is needed, construction weight can be reduced.In addition, the centrifugal force that rotor wing rotation generates mainly passes through joint bolt
It undertakes, joint bolt is clamped between two plate support arms, can provide great shearing force, also do not need equally more to thicken
The structure of weight.And the rotary wing changing of the application away from when, using two spherical joints, individual spherical joint can be any
Direction deflection, two spherical joints mutually limit, so that rotor only can be around the line of centres deflection of two spherical joints.This
The spherical joint of the rotor deflection setting of application itself is not necessarily to undertake the lift and centrifugal force of rotor, it is only necessary to very small behaviour
Vertical torque, thus the spherical joint used does not need king-sized intensity yet, specific bearing compared to the prior art can
To mitigate construction weight significantly, the carrying ability of payload is improved.
It will be appreciated by those skilled in the art that although the present invention is described in the way of multiple embodiments,
It is that not each embodiment only contains an independent technical solution.So narration is used for the purpose of for the sake of understanding in specification,
The skilled in the art should refer to the specification as a whole is understood, and by technical solution involved in each embodiment
Regard as and can be combined with each other into the modes of different embodiments to understand protection scope of the present invention.
The foregoing is merely the schematical specific embodiment of the present invention, the range being not intended to limit the invention.It is any
Those skilled in the art, made equivalent variations, modification and combination under the premise of not departing from design and the principle of the present invention,
It should belong to the scope of protection of the invention.
Claims (8)
1. a kind of rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil, for the rotation by the dynamic unmanned plane of steering engine (67) driving oil
The wing (5) is rotated to change the angle of attack of the rotor (5), and the rotor (5) is supported on the end of the cantilever (3) of the dynamic unmanned plane of the oil
End；The rotor pulp distance varying mechanism has a hollow spindle (68), and the rotor (5) is fixed by a mounting base (651)
It is mounted on the upper end of the hollow spindle (68)；The hollow spindle (68) is internally provided with one can be along the hollow spindle
(68) the pitch control bar (65) that length direction moves up and down, the upper end of the pitch control bar (65) can rotate to it ground
It is connected with the power transmission arm support (64) that can be moved up and down with the pitch control bar (65), the power transmission arm support (64) is logical
Crossing power transmission arm (641) drives the eccentric arm (59) of the rotor (5) to drive rotor (5) rotation；The steering engine (67) passes through
Connecting rod connect with the lower end of the pitch control bar (65) and manipulates the pitch control bar (65) and moves up and down；Its feature exists
In the mounting base (651) corresponds to each rotor (5) has horizontally disposed upper and lower two to put down by its rotation center is protruding
Plate support arm (652), the plain film shape wing root (52) of the rotor (5) is clamped to be mounted between described two plate support arms (652)；
There are two spherical joint (53) for setting on the plain film shape wing root (52)；The rotor (5) can be around described two spherical joints
(53) line of centres (531) deflects.
2. the rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil as described in claim 1, which is characterized in that the spherical pass
Section (53) is stuck in the joint hole (54) of the plain film shape wing root (52).
3. the rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil as claimed in claim 2, which is characterized in that the spherical pass
Section (53) is fixed between described two plate support arms (652) by joint bolt.
4. the rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil as claimed in claim 3, which is characterized in that described two flat
The mounting hole (653) passed through for the joint bolt is provided on plate support arm (652), the spherical joint (53) has described in confession
The joint hole (55) that joint bolt passes through.
5. the rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil as described in one of claim 1-4, which is characterized in that described
Hollow spindle (68) setting is protruding from the inside of a retainer (69), and the bottom of the retainer (69) has described in confession
The port that the lower end of pitch control bar (65) is pierced by.
6. the rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil as claimed in claim 5, which is characterized in that the steering engine
(67) it is arranged in the outside of the cantilever (3), and connecting rod and the displacement by setting in the lower section of the retainer (69)
The lower end of control stick (65) connects.
7. the rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil as claimed in claim 6, which is characterized in that the retainer
(69) bottom is provided with link supports seat (691).
8. the rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil as claimed in claim 5, which is characterized in that the cantilever
(3) it is hollow structure, is internally provided with drive rod, the end of drive rod is provided with first bevel gear (91), first cone
Gear (91) is meshed with a second bevel gear (92), and the second bevel gear (92) is connected to the hollow master by spline
On axis (68), and it is located at the top of the retainer (69).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811580661.0A CN109484637A (en) | 2018-12-24 | 2018-12-24 | A kind of rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811580661.0A CN109484637A (en) | 2018-12-24 | 2018-12-24 | A kind of rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109484637A true CN109484637A (en) | 2019-03-19 |
Family
ID=65711647
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811580661.0A Pending CN109484637A (en) | 2018-12-24 | 2018-12-24 | A kind of rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109484637A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113928541A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Helicopter control system motion control law design method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4243359A (en) * | 1978-01-18 | 1981-01-06 | Messerschmitt-Bolkow-Blohm Gesellschaft Mit Beschrankter Haftung | Rotor structure, especially for hingeless rotary wing aircraft |
| CN202848024U (en) * | 2012-09-25 | 2013-04-03 | 李均 | Propeller hub assembly used for small and medium-sized unmanned helicopters |
| CN105292465A (en) * | 2015-11-04 | 2016-02-03 | 中航维拓（北京）科技有限责任公司 | Rigid rotor system for helicopter |
| CN106741912A (en) * | 2017-01-03 | 2017-05-31 | 山东鹰翼航空科技有限公司 | Multi-rotor unmanned aerial vehicle during a kind of foldable boat long |
| CN206520753U (en) * | 2017-03-07 | 2017-09-26 | 石立松 | Moment of torsion induction type pitch-variable system |
| CN207450249U (en) * | 2017-11-08 | 2018-06-05 | 沈阳旋飞航空技术有限公司 | A kind of unmanned plane rotor pulp distance varying mechanism |
-
2018
- 2018-12-24 CN CN201811580661.0A patent/CN109484637A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4243359A (en) * | 1978-01-18 | 1981-01-06 | Messerschmitt-Bolkow-Blohm Gesellschaft Mit Beschrankter Haftung | Rotor structure, especially for hingeless rotary wing aircraft |
| CN202848024U (en) * | 2012-09-25 | 2013-04-03 | 李均 | Propeller hub assembly used for small and medium-sized unmanned helicopters |
| CN105292465A (en) * | 2015-11-04 | 2016-02-03 | 中航维拓（北京）科技有限责任公司 | Rigid rotor system for helicopter |
| CN106741912A (en) * | 2017-01-03 | 2017-05-31 | 山东鹰翼航空科技有限公司 | Multi-rotor unmanned aerial vehicle during a kind of foldable boat long |
| CN206520753U (en) * | 2017-03-07 | 2017-09-26 | 石立松 | Moment of torsion induction type pitch-variable system |
| CN207450249U (en) * | 2017-11-08 | 2018-06-05 | 沈阳旋飞航空技术有限公司 | A kind of unmanned plane rotor pulp distance varying mechanism |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113928541A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Helicopter control system motion control law design method |
| CN113928541B (en) * | 2021-11-19 | 2023-04-25 | 中国直升机设计研究所 | Helicopter control system motion control law design method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10173771B2 (en) | Tiltrotor aircraft having rotatable wing extensions | |
| US10279892B2 (en) | Tiltrotor aircraft having active wing extensions | |
| EP0696983B1 (en) | Ancillary aerodynamic structures for an unmanned aerial vehicle having ducted, coaxial counter-rotating rotors | |
| CN207403934U (en) | Multi-rotor unmanned aerial vehicle | |
| CN104816821B (en) | Land, water and air three are dwelt multi-rotor aerocraft | |
| CN100391790C (en) | Multi-rotor aerocraft | |
| CN101984331B (en) | Dynamics comprehensive test bed for half-unfolding gas bomb with long tilting rotor wing | |
| CN106347648A (en) | Multi-rotor plant protection unmanned aerial vehicle | |
| CN207450249U (en) | A kind of unmanned plane rotor pulp distance varying mechanism | |
| CN103552686B (en) | A kind of compound type duct aerial reconnaissance machine people | |
| CN107264796A (en) | Propeller component with least two propeller blades | |
| EP3369652B1 (en) | Tiltrotor aircraft having optimized hover capabilities | |
| CN104590555A (en) | Electrodynamic multi-rotor helicopter | |
| US20140314573A1 (en) | Integration of rotary electrical actuator for swashplateless individual blade control | |
| CN106428527A (en) | Dual-axis vector servo turning device with propeller and vertical take-off and landing unmanned aerial vehicle with fixed wings | |
| CN106741918B (en) | Oblique product vector diaxon aircraft control structure | |
| CN108163193A (en) | A kind of active main rotor vertically taking off and landing flyer | |
| JP2019137389A (en) | Flight device | |
| CN108238247A (en) | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer | |
| US8998126B2 (en) | Lift generating device | |
| CN209305827U (en) | A kind of improved unmanned plane pulp distance varying mechanism | |
| CN207956057U (en) | A kind of active main rotor vertically taking off and landing flyer | |
| CN109484637A (en) | A kind of rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil | |
| CN210133283U (en) | Combined type aircraft | |
| Bogdanowicz et al. | Development of a quad-rotor biplane MAV with enhanced roll control authority in fixed wing mode |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190319 |