CN207725606U - A kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanism - Google Patents
A kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanism Download PDFInfo
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- CN207725606U CN207725606U CN201720989409.XU CN201720989409U CN207725606U CN 207725606 U CN207725606 U CN 207725606U CN 201720989409 U CN201720989409 U CN 201720989409U CN 207725606 U CN207725606 U CN 207725606U
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- paddle folder
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Abstract
The utility model proposes a kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanisms, including pedestal, control arm A, control arm B, and shaft control set, paddle, which presss from both sides, pushes arm, joins in paddle folder, paddle folder, axis sliding block, and paddle folder controls set, and control set bearing rotates steering engine rocking arm, shaft parts；Pedestal is fixed on fuselage, control arm A and base hinge, control arm B are again with control arm A hinges, control arm B also controls set hinge, pedestal, control arm A with shaft simultaneously, and control arm B and rotation steering engine rocking arm constitute multi link rocking arm control mechanism.The variation that rotor wing unmanned aerial vehicle pitch can be fast implemented, than originally rotating speed come more accurate by way of controlling tail-rotor reaction torque, control efficiency is also substantially improved.
Description
Technical field：
The utility model belongs to air vehicle technique field, specifically provides a kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanism.
Background technology：
Rotor vertical take-off and landing drone is generally divided into single rotor or multi-rotor unmanned aerial vehicle, is all to drive list by transmission mechanism
Paddle or the rotation of more paddles push unmanned plane to fly to generate pulling force.It can be turned by adjusting rotor in flight course
Dynamic speed controls pulling force, can also by distance changing mechanism come change pitch to achieve the effect that change pulling force, with
This flies to control.Pitch is controlled by pitch-changing mechanism, there can be the state of flight for quickly and effectively changing unmanned plane.
For this purpose, suitable blade distance changing mechanism is particularly important in rotor wing unmanned aerial vehicle control aspect.
Utility model content：
The purpose of this utility model：Based on rotor wing unmanned aerial vehicle tail-rotor control problem, a kind of novel tail-rotor displacement knot is provided
Structure can fast implement the variation of rotor wing unmanned aerial vehicle pitch, than originally rotating speed come more smart by way of controlling tail-rotor reaction torque
Really, control efficiency is also substantially improved.
The technical solution of the utility model：A kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanism includes pedestal, control arm A, control
Arm B, shaft control set, paddle folder push arm, join in paddle folder, paddle folder, axis sliding block, and paddle folder control set, control set bearing rotates steering engine
Rocking arm, shaft parts.Pedestal is fixed on fuselage, control arm A and base hinge, control arm B again with control arm A hinges, same
When control arm B set hinge, pedestal, control arm A are also controlled with shaft, control arm B and rotation steering engine rocking arm constitute multi link
Rocking arm control mechanism；It concentric install and can relatively rotate but position in the smooth end that shaft control set covers bearing and axis sliding block by control
Set opposing stationary, axis slide block set is in shaft and can carry out axially opposing sliding in shaft, and the end of thread and the paddle of axis sliding block press from both sides
Control set connects and keeps relative position constant, and paddle folder control set both sides cantilever arm and paddle folder push arm one end hinge, shaft control
System set, axis sliding block, paddle folder control set, control set bearing and paddle folder push arm to constitute co-rotation mechanism.In multi link rocking arm
Under control mechanism and the synergy of co-rotation mechanism, by multi link rocker arm body, blade pitch in rotation process is controlled
Variation, simultaneously as the presence of co-rotation mechanism, it is ensured that multi link rocker arm body is opposite in blade rotation process
In fuselage remains stationary, when rotating steering engine rocking arm, the variation of pitch, i.e. displacement may be implemented in integrated model.
The technique effect of the utility model：A kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanism is in three kinds of rotor unmanned helicopters
On carried out Installation And Test, test works well, and meets flight demand for control well.
Description of the drawings：
Fig. 1 is mounting structure diagram of the utility model on rotor wing unmanned aerial vehicle
Fig. 2 is structure sectional view of the utility model along shaft vertical direction
Fig. 3 is that the distance changing mechanism of the utility model carries out forward and reverse displacement schematic diagram
Number explanation：1- pedestals, 2- control arms A, 3- control arm B, 4- shaft control set, 5- paddles folder push arm, 6- paddles folder
Middle, 7- paddles folder, 8- axis sliding blocks, 9- paddles folder, which controls, to be covered, and 10- control set bearings, 11- rotates steering engine rocking arm, 12- shafts, 13- tails
Fixed plate, 14- paddles press from both sides bearing
Specific implementation mode：
Referring to attached drawing 1-3
1, a kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanism, including pedestal (1), (2) one end control arm A and pedestal (1) hinge,
(3) one end control arm B and the other end hinge of control arm A (2) while the other end of control arm B (3) and shaft control set simultaneously
(4) hinge, shaft control set (4) cover the concentric installation in smooth end of bearing (10) and axis sliding block (8) by control and opposite can turn
Dynamic but position is opposing stationary, and axis sliding block (8) is sleeved on shaft (12) and can carry out axially opposing sliding but rotation in shaft in itself
It is consistent, the end of thread and the paddle of axis sliding block (8) press from both sides control set (9) and connect and keep relative position constant, paddle folder control set
(9) both sides cantilever arm and paddle folder push arm (5) one end hinge, paddle folder push the other end of arm (5) and paddle press from both sides (7) hinge, two
Paddle folder (7) is connected to connection (6) in the both ends for joining (6) in paddle folder, paddle folder (7) paddle folder and presss from both sides both bearing (14) holdings by paddle
It can relatively rotate, pedestal (1) is fixed in tail fixed plate (13) and keeps opposing stationary, by rotating steering engine rocking arm with fuselage
(11) make total linkage to realize that paddle folder and the angle of horizontal plane change (displacement of rotor).
In aircraft flight, paddle folder in connection (6), paddle folder (7) be all with shaft (12) keep together same speed into
Row rotation, to drive the rotation of rotor (rotor is fixed on paddle folder) to lead at this time if rotation steering engine rocking arm (11)
It crosses and shaft control set (4) may be implemented by pedestal (1), control arm A (2) and control arm B (3) mechanism that mutually hinge connection forms
Opposite sliding in shaft axial direction, the opposite sliding of axis control set (4) in the axial direction can drive paddle folder control set (9) to exist
Opposite sliding in axial direction moves down to which the paddle folder of driving and paddle folder control set (9) both sides cantilever arm hinge pushes on arm (5)
Dynamic, it will be paddle folder (7) variation corresponding with the generation of the angle of horizontal plane that paddle folder, which pushes arm (5) to move up and down, to realize paddle
Away from variation (displacement), meet flight demand for control.
Claims (4)
1. a kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanism, including pedestal, control arm A, control arm B, shaft control set, paddle folder push
Arm, paddle join in pressing from both sides, paddle folder, axis sliding block, and paddle folder control set controls set bearing, rotates steering engine rocking arm, shaft parts；Its feature
It is：Pedestal is fixed on fuselage, control arm A and base hinge, control arm B again with control arm A hinges, simultaneously control arm B
Set hinge is controlled with shaft, pedestal, control arm A, control arm B and rotation steering engine rocking arm constitute multi link rocking arm control machine
Structure；The smooth end that shaft control set covers bearing and axis sliding block by control is installed, and axis slide block set is in shaft, the screw thread of axis sliding block
End pushes arm one end hinge, shaft control set, axis to slide with paddle folder control set connection, paddle folder control set both sides cantilever arm with paddle folder
Block, paddle folder control set, control set bearing and paddle folder push arm to constitute co-rotation mechanism.
2. a kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanism according to claim 1, it is characterised in that：The shaft control set
Keep relative position constant with axis sliding block.
3. a kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanism according to claim 1, it is characterised in that：The axis slide block set with
Shaft carries out axially opposing sliding.
4. a kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanism according to claim 1, it is characterised in that：The shaft control set
It concentric installs at the smooth end that bearing and axis sliding block are covered by control.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720989409.XU CN207725606U (en) | 2017-08-09 | 2017-08-09 | A kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720989409.XU CN207725606U (en) | 2017-08-09 | 2017-08-09 | A kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207725606U true CN207725606U (en) | 2018-08-14 |
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ID=63090283
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720989409.XU Active CN207725606U (en) | 2017-08-09 | 2017-08-09 | A kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanism |
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| CN (1) | CN207725606U (en) |
Cited By (7)
| 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 |
| CN109552599A (en) * | 2018-11-06 | 2019-04-02 | 珠海隆华直升机科技有限公司 | Helicopter tail rotor displacement blade assembly and helicopter |
| CN109774919A (en) * | 2018-11-06 | 2019-05-21 | 珠海隆华直升机科技有限公司 | High-torque pull rod transmission system and helicopter |
| CN110723277A (en) * | 2019-11-28 | 2020-01-24 | 湖南捷飞科技有限公司 | Unmanned digital telex control mechanism based on mosquito manned helicopter |
| CN111547252A (en) * | 2020-04-21 | 2020-08-18 | 中国航发湖南动力机械研究所 | Tail rotor pitch control shaft device and preparation method thereof |
| JP7424995B2 (en) | 2019-06-17 | 2024-01-30 | レオナルド・エッセ・ピ・ア | Anti-torque rotor for helicopter |
-
2017
- 2017-08-09 CN CN201720989409.XU patent/CN207725606U/en active Active
Cited By (8)
| 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 |
| CN109552599A (en) * | 2018-11-06 | 2019-04-02 | 珠海隆华直升机科技有限公司 | Helicopter tail rotor displacement blade assembly and helicopter |
| CN109774919A (en) * | 2018-11-06 | 2019-05-21 | 珠海隆华直升机科技有限公司 | High-torque pull rod transmission system and helicopter |
| JP7424995B2 (en) | 2019-06-17 | 2024-01-30 | レオナルド・エッセ・ピ・ア | Anti-torque rotor for helicopter |
| CN110723277A (en) * | 2019-11-28 | 2020-01-24 | 湖南捷飞科技有限公司 | Unmanned digital telex control mechanism based on mosquito manned helicopter |
| CN110723277B (en) * | 2019-11-28 | 2021-05-07 | 湖南捷飞科技有限公司 | Unmanned digital telex control mechanism based on mosquito manned helicopter |
| CN111547252A (en) * | 2020-04-21 | 2020-08-18 | 中国航发湖南动力机械研究所 | Tail rotor pitch control shaft device and preparation method thereof |
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