CN207875998U - A kind of tail-rotor structure and the unmanned plane with it - Google Patents
A kind of tail-rotor structure and the unmanned plane with it Download PDFInfo
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- CN207875998U CN207875998U CN201820221801.4U CN201820221801U CN207875998U CN 207875998 U CN207875998 U CN 207875998U CN 201820221801 U CN201820221801 U CN 201820221801U CN 207875998 U CN207875998 U CN 207875998U
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Abstract
The utility model belongs to air vehicle technique field, disclose a kind of tail-rotor structure and the unmanned plane with it, tail-rotor structure includes tail-rotor main shaft, the tail-rotor hub being connect with tail-rotor main shaft, and it is connected to the tail-rotor of tail-rotor hub both sides, further include tail seesaw axis, tail seesaw axis passes through tail-rotor hub and tail-rotor main shaft to be arranged, bearing is equipped between the both ends and tail-rotor hub of tail seesaw axis, tail-rotor hub is dynamic relative to tail seesaw shaft rotation by bearing.When tail-rotor structure by downwash flow and other air-flows influenced to cause the linear velocity of side is big and when the linear velocity of other side is small; above-mentioned tail-rotor hub can carry out the rotation of certain angle by bearing around tail seesaw axis; make the power suffered by tail-rotor there are one buffering and transfers; protect tail-rotor; the moment of flexure for alleviating the distortion of tail-rotor and being generated to tail-rotor main shaft, reduces vibration.
Description
Technical field
The utility model is related to air vehicle technique field more particularly to a kind of tail-rotor structure and with its unmanned plane.
Background technology
Tail rotor is circular motion, and due to the relationship of radius, linear velocity is maximum at wing tip, and the linear velocity of circle centre position is
Zero.So rotor is generated close to the place of wing tip, lift is maximum, and close to the local lift very little in the center of circle.When tail-rotor works,
The downwash flow of main rotor and other air-flows can have an impact the air-flow of tail-rotor, cause the linear velocity of tail-rotor side big and another
The linear velocity of outer side is small, causes every blade different direction in circumference to will produce different lift and resistance, periodically
Very strong distortion is generated to blade, and this distortion can pass to tail-rotor main shaft and generate a moment of flexure to tail-rotor main shaft, both greatly
The fatigue of material is accelerated greatly, and causes prodigious vibration, and the use of steering engine can be influenced.
Utility model content
The purpose of this utility model is to provide a kind of tail-rotor structure and with its unmanned plane, to solve existing unmanned plane
Tail-rotor shakes to the damage and generation of tail-rotor and tail-rotor main shaft by caused by main rotor downwash flow and other airflow influences
Dynamic problem.
For this purpose, the utility model uses following technical scheme：
A kind of tail-rotor structure, including tail-rotor main shaft, the tail-rotor hub being connect with the tail-rotor main shaft, and it is connected to the tail
The tail-rotor of propeller hub both sides further includes tail seesaw axis, and the tail seesaw axis passes through the tail-rotor hub and tail-rotor main shaft to be arranged,
Bearing is equipped between the both ends of the tail seesaw axis and the tail-rotor hub, the tail-rotor hub is by the bearing relative to described
Tail seesaw shaft rotation is dynamic.
Preferably, intersection and out of plumb between the flapping hinge A of the tail-rotor and axial hinge B.
Preferably, the tail seesaw axis passes through the axle center of the tail-rotor main shaft to be arranged.
Preferably, the both ends that the tail seesaw axis is pierced by the tail-rotor hub are connected with nut, the nut is for limiting
Make the axial movement of the tail seesaw axis.
Preferably, tail-rotor hub both sides are provided with tail-rotor folder, one end of the tail-rotor is fixed in the tail-rotor folder.
Preferably, further including pitch-changing mechanism, described pitch-changing mechanism one end is connected to two tail-rotor folders, and by servo driving
Along the axial movement of tail-rotor main shaft.
Preferably, the pitch-changing mechanism includes the push-pull rod for being rotationally connected with steering engine, it is rotationally connected with the push-pull rod
Distance-variable rocker arm, one end is rotationally connected with the centre position of the distance-variable rocker arm, and the other end is rotationally connected with the switching of reduction box
Rocking arm, the sliding sleeve for being rotationally connected with the distance-variable rocker arm and being set on the tail-rotor main shaft are fixed in the sliding sleeve and are arranged
Type star polygon work on the tail-rotor main shaft is connected to two push-and-pull rocking arms of the type star polygon work, two each turn of push-and-pull rocking arms
One tail-rotor folder of dynamic connection.
Preferably, being provided with limited block on the tail-rotor main shaft, the limited block ring is located on the tail-rotor main shaft, is used
It is limited in the type star polygon work.
It is pressed from both sides preferably, the push-and-pull rocking arm is rotationally connected with the tail-rotor by oscillating bearing.
The utility model also provides a kind of unmanned plane, including above-mentioned tail-rotor structure.
The beneficial effects of the utility model：
The utility model by be arranged tail seesaw axis, and between both ends and tail-rotor hub be equipped with bearing, when tail-rotor structure by
Influence to downwash flow and other air-flows causes the linear velocity of side big and the linear velocity hour of other side, above-mentioned tail-rotor
The rotation that hub can carry out certain angle by bearing around tail seesaw axis changes to change the angle of attack between rotor and air-flow
Become the lift that both sides rotor generates, makes the power suffered by tail-rotor there are one buffering and switching, protect tail-rotor, alleviate the torsion of tail-rotor
Moment of flexure bent and to the generation of tail-rotor main shaft, reduces vibration.And intersect between the flapping hinge A of tail-rotor and axial hinge B and not
Vertically, the amplitude that can effectively reduce the pitch hinge bearing rotation of tail-rotor structure, reduces the abrasion of pitch hinge bearing, improves
Pitch hinge bearing service life.
Description of the drawings
Fig. 1 is the dimensional structure diagram of the utility model tail-rotor structure；
Fig. 2 is the front view of the utility model tail-rotor structure；
Fig. 3 is the vertical view of the utility model tail-rotor structure；
Fig. 4 is the structural schematic diagram that the utility model tail-rotor structure shows tail seesaw axis.
In figure：
1, tail-rotor main shaft；2, tail-rotor hub；3, tail-rotor；4, tail seesaw axis；5, bearing；6, nut；7, tail-rotor presss from both sides；8, rudder
Machine；9, push-pull rod；10, distance-variable rocker arm；11, reduction box；12, switching rocking arm；13, sliding sleeve；14, type star polygon work；15, rocking arm is pushed and pulled；
16, limited block.
Specific implementation mode
Further illustrate the technical solution of the utility model below with reference to the accompanying drawings and specific embodiments.
The utility model provides a kind of tail-rotor structure, and as shown in Figs 1-4, which includes tail-rotor main shaft 1, tail-rotor hub
2, tail-rotor 3, tail seesaw axis 4, reduction box 11, steering engine 8 and pitch-changing mechanism, wherein：
Above-mentioned 1 one end of tail-rotor main shaft is connected to reduction box 11, and the other end is connected with above-mentioned tail-rotor hub 2, above-mentioned tail-rotor hub 2
Both sides, which are provided with, to be fixed in tail-rotor folder 7 relative to the tail-rotor folder 7 that tail-rotor hub 2 rotates, above-mentioned tail-rotor 3.Pass through engine
Structure such as motor drives reduction box 11 to move, and reduction box 11 can drive tail-rotor main shaft 1 to rotate, so that tail-rotor hub 2 drives tail
Paddle folder 7 and tail-rotor 3 rotate, and realize the rotation of tail-rotor structure.
In the present embodiment, above-mentioned tail seesaw axis 4 is threaded through on tail-rotor hub 2 and tail-rotor main shaft 1, specifically, the tail is lifted up
Seesaw axis 4 passes through the axle center of tail-rotor main shaft 1 to be arranged, and both ends are pierced by the setting of tail-rotor hub 2 respectively.Tail seesaw axis 4 passes through tail-rotor
Bearing 5 is provided between the both ends and tail-rotor hub 2 of hub 2, i.e. tail-rotor hub 2 can be rotated relative to tail seesaw axis 4.Tail-rotor structure
In use, when tail-rotor structure by downwash flow and other air-flows influenced to cause the linear velocity of side tail-rotor 3 big and in addition
The linear velocity hour of side tail-rotor 3, tail-rotor 3 can drive tail-rotor hub 2 to be equivalent to the rotation of tail seesaw axis 4 at this time, and then make tail-rotor 3
Suffered power alleviates the distortion of tail-rotor 3, protects tail-rotor 3, and can reduce to tail-rotor master there are one buffering and switching
The moment of flexure that axis 1 generates, protects tail-rotor main shaft 1.
In the present embodiment, the both ends that above-mentioned tail seesaw axis 4 is pierced by tail-rotor hub 2 are connected with nut 6, specifically can be in tail-rotor hub
Counter sink (not shown) is opened up on 2, above-mentioned nut 6 is threadedly connected to tail seesaw axis 4, and is placed in counter sink, passes through
Nut 6 can limit the axial movement of tail seesaw axis 4.
In the present embodiment, as shown in figure 4, the flapping hinge A (shown in Fig. 4 dotted lines) of above-mentioned tail-rotor 3 and axial hinge B (Fig. 4 dotted lines
It is shown) between intersect and out of plumb, setting with this configuration, can effectively reduce tail-rotor structure pitch hinge bearing rotation
Amplitude, reduce the abrasion of pitch hinge bearing, improve pitch hinge bearing service life.I.e. in the prior art, in order to support
The tail-rotor structure that disappears is influenced by downwash flow and other air-flows, and tail-rotor 3 can carry out pitch by the rotation of the bearing 5 of pitch hinge
The amplitude of adjustment, at this time pitch hinge bearing rotation is larger, and with the increase of use time, pitch hinge bearing will produce abrasion.And
The present embodiment passes through intersection and out of plumb between the flapping hinge A of tail-rotor 3 and axial hinge B, can reduce the rotation of pitch hinge bearing
Amplitude.And coordinate the tail seesaw axis 4 of the present embodiment, the abrasion of pitch hinge bearing can be reduced, pitch hinge bearing is improved
Service life.
In the present embodiment, above-mentioned pitch-changing mechanism one end is connected to two tail-rotor folders 7, and by 8 drives edge tail-rotor main shaft 1 of steering engine
Axial movement, for adjusting to 3 pitch of tail-rotor.Specifically, as shown in Figure 1, the pitch-changing mechanism includes being rotationally connected with rudder
The push-pull rod 9 of machine 8, is rotationally connected with the distance-variable rocker arm 10 of push-pull rod 9, and one end is rotationally connected with the centre position of distance-variable rocker arm 10
The other end is rotationally connected with the switching rocking arm 12 of reduction box 11, is rotationally connected with distance-variable rocker arm 10 and is set on tail-rotor main shaft 1
Sliding sleeve 13, the type star polygon work 14 for being fixed in sliding sleeve 13 and being set on tail-rotor main shaft 1, two push-and-pulls for being connected to type star polygon work 14 shake
Arm 15, respectively one tail-rotor of rotation connection presss from both sides 7 to two push-and-pull rocking arms 15, specifically pushes and pulls and is provided between rocking arm 15 and tail-rotor folder 7
Oscillating bearing (not shown), the oscillating bearing are pitch hinge bearing.
By above-mentioned pitch-changing mechanism, when needing the pitch to tail-rotor 3 to be adjusted, push-pull rod 9 is driven to move by steering engine 8
Dynamic, at this time under the synergistic effect of switching rocking arm 12, distance-variable rocker arm 10 drives sliding sleeve 13 and type star polygon work 14 on tail-rotor main shaft 1
Sliding, type star polygon work 14 then drive push-and-pull rocking arm 15 that tail-rotor folder 7 and tail-rotor 3 is driven to rotate, realize the adjusting of 3 pitch of tail-rotor.
In the present embodiment, limited block 16 is provided on tail-rotor main shaft 1, which is located on tail-rotor main shaft 1, uses
It is limited in the axial movement of type star polygon work 14.
The utility model also provides a kind of unmanned plane, including above-mentioned tail-rotor structure, the tail-rotor structure simple structure, tight
It gathers, is light-weight, and the influence of downwash flow and other air-flows to tail-rotor 3 and tail-rotor main shaft 1 can be avoided, effectively subtracting
The light distortion of tail-rotor 3 and the moment of flexure that tail-rotor main shaft 1 is generated.
Obviously, above-described embodiment of the utility model is used for the purpose of clearly illustrating the utility model example, and
It is not the restriction to the embodiment of the utility model.For those of ordinary skill in the art, in above description
On the basis of can also make other variations or changes in different ways.There is no need and unable to give all embodiments
It is exhaustive.All any modification, equivalent and improvement made within the spirit and principle of the present invention etc., should be included in
Within the protection domain of the utility model claims.
Claims (10)
1. a kind of tail-rotor structure, including tail-rotor main shaft (1), the tail-rotor hub (2) being connect with the tail-rotor main shaft (1), and connection
Tail-rotor (3) in tail-rotor hub (2) both sides, which is characterized in that further include tail seesaw axis (4), the tail seesaw axis (4)
Be arranged across the tail-rotor hub (2) and tail-rotor main shaft (1), the both ends of the tail seesaw axis (4) and the tail-rotor hub (2) it
Between be equipped with bearing (5), the tail-rotor hub (2) rotated by the bearing (5) relative to the tail seesaw axis (4).
2. tail-rotor structure according to claim 1, which is characterized in that the flapping hinge A of the tail-rotor (3) and axial hinge B it
Between intersect and out of plumb.
3. tail-rotor structure according to claim 1, which is characterized in that the tail seesaw axis (4) passes through the tail-rotor master
The axle center of axis (1) is arranged.
4. tail-rotor structure according to claim 1, which is characterized in that the tail seesaw axis (4) is pierced by the tail-rotor hub
(2) both ends are connected with nut (6), and the nut (6) is used to limit the axial movement of the tail seesaw axis (4).
5. tail-rotor structure according to claim 1, which is characterized in that tail-rotor hub (2) both sides are provided with tail-rotor folder
(7), one end of the tail-rotor (3) is fixed in the tail-rotor folder (7).
6. tail-rotor structure according to claim 5, which is characterized in that further include pitch-changing mechanism, described pitch-changing mechanism one end
Two tail-rotor folders (7) are connected to, and by the axial movement of steering engine (8) drives edge tail-rotor main shaft (1).
7. tail-rotor structure according to claim 6, which is characterized in that the pitch-changing mechanism includes being rotationally connected with steering engine
(8) push-pull rod (9) is rotationally connected with the distance-variable rocker arm (10) of the push-pull rod (9), and one end is rotationally connected with the displacement and shakes
The centre position of arm (10), the other end are rotationally connected with the switching rocking arm (12) of reduction box (11), are rotationally connected with the displacement
Rocking arm (10) and the sliding sleeve (13) being set on the tail-rotor main shaft (1), are fixed in the sliding sleeve (13) and are set in the tail
Type star polygon work (14) on paddle main shaft (1), is connected to two push-and-pull rocking arms (15) of the type star polygon work (14), and two push-and-pulls are shaken
Respectively one tail-rotor of rotation connection presss from both sides (7) to arm (15).
8. tail-rotor structure according to claim 7, which is characterized in that be provided with limited block on the tail-rotor main shaft (1)
(16), limited block (16) ring is located on the tail-rotor main shaft (1), for being limited to the type star polygon work (14).
9. tail-rotor structure according to claim 7, which is characterized in that the push-and-pull rocking arm (15) is rotated by oscillating bearing
It is connected to the tail-rotor folder (7).
10. a kind of unmanned plane, which is characterized in that including any tail-rotor structures of claim 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820221801.4U CN207875998U (en) | 2018-02-08 | 2018-02-08 | A kind of tail-rotor structure and the unmanned plane with it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820221801.4U CN207875998U (en) | 2018-02-08 | 2018-02-08 | A kind of tail-rotor structure and the unmanned plane with it |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207875998U true CN207875998U (en) | 2018-09-18 |
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ID=63510556
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820221801.4U Active CN207875998U (en) | 2018-02-08 | 2018-02-08 | A kind of tail-rotor structure and the unmanned plane with it |
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| CN (1) | CN207875998U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109466746A (en) * | 2018-11-06 | 2019-03-15 | 珠海隆华直升机科技有限公司 | Helicopter tail rotor displacement drive system and helicopter |
| CN109502010A (en) * | 2018-11-06 | 2019-03-22 | 珠海隆华直升机科技有限公司 | Helicopter tail rotor displacement displacement disc assembly and helicopter |
| CN109606646A (en) * | 2018-11-06 | 2019-04-12 | 珠海隆华直升机科技有限公司 | Helicopter electric rotary directly drives displacement tail-rotor assembly and helicopter |
| CN109677601A (en) * | 2019-02-22 | 2019-04-26 | 一飞智控(天津)科技有限公司 | Seesaw type unmanned plane rotor and unmanned plane |
-
2018
- 2018-02-08 CN CN201820221801.4U patent/CN207875998U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109466746A (en) * | 2018-11-06 | 2019-03-15 | 珠海隆华直升机科技有限公司 | Helicopter tail rotor displacement drive system and helicopter |
| CN109502010A (en) * | 2018-11-06 | 2019-03-22 | 珠海隆华直升机科技有限公司 | Helicopter tail rotor displacement displacement disc assembly and helicopter |
| CN109606646A (en) * | 2018-11-06 | 2019-04-12 | 珠海隆华直升机科技有限公司 | Helicopter electric rotary directly drives displacement tail-rotor assembly and helicopter |
| CN109677601A (en) * | 2019-02-22 | 2019-04-26 | 一飞智控(天津)科技有限公司 | Seesaw type unmanned plane rotor and unmanned plane |
| CN109677601B (en) * | 2019-02-22 | 2024-05-28 | 一飞智控(天津)科技有限公司 | Teeterboard type unmanned aerial vehicle rotor wing and unmanned aerial vehicle |
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Effective date of registration: 20220928 Address after: 300457 No. 105, Building 9, Zone B3 (formerly Zone 2 of Ronghui Business Park), Binhai Zhongguancun Science and Technology Park, Tianjin Economic and Technological Development Zone, Binhai New Area, Tianjin Patentee after: Tianjin Phoenix Intelligent Technology Co.,Ltd. Address before: Floor 1, block B, No.3, Tengfei Road, Junliang City, Dongli District, Tianjin Patentee before: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. |