CN205738063U - The dynamic multi-rotor aerocraft displacement system of a kind of oil - Google Patents
The dynamic multi-rotor aerocraft displacement system of a kind of oil Download PDFInfo
- Publication number
- CN205738063U CN205738063U CN201620463159.1U CN201620463159U CN205738063U CN 205738063 U CN205738063 U CN 205738063U CN 201620463159 U CN201620463159 U CN 201620463159U CN 205738063 U CN205738063 U CN 205738063U
- Authority
- CN
- China
- Prior art keywords
- pitch change
- rotor
- change axes
- pitch
- main shaft
- 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.)
- Expired - Fee Related
Links
Landscapes
- Hydraulic Motors (AREA)
Abstract
The dynamic multi-rotor aerocraft displacement system of oil relates to the dynamic multi-rotor aerocraft displacement system of a kind of oil.Mainly move the problems such as the displacement system motion parts of multi-rotor aerocraft are many and design for solving existing oil.It includes that main shaft, rotor head are fixed on main shaft, and rotor head and rotor folder are by joining in pressure bearing and location bearing；Pitch change axes is had in main shaft, pitch change axes is stretched out from the top of rotor head, the top of pitch change axes is fixed with displacement shift fork, two ends with displacement shift fork respectively, the upper end of two pitch-change-links are connected by bearing pin, the lower end of two pitch-change-links is connected with two rotor folders respectively, and the lower end of pitch change axes is fixed with pitch bearing inner ring.It is provided with copper sheathing between pitch change axes and the hole wall of rotor head, between rotor head hole wall and the pitch change axes above upper copper sheathing, is provided with sealing ring.There is lower copper sheathing between bottom pitch change axes and main shaft, between main shaft and the pitch change axes below lower copper sheathing, be provided with lower seal.Advantage is that moving component is few.
Description
Technical field:
This utility model relates to the dynamic multi-rotor aerocraft displacement system of a kind of oil.
Background technology:
nullExisting oil moves the displacement system of multi-rotor aerocraft and includes displacement dish，Displacement dish is sleeved on from the main shaft that change speed gear box stretches out and is slidably matched with main shaft，Rotor head is fixed on the top of main shaft，Rotor head and the rotor being positioned at its both sides press from both sides by pressure bearing and middle coupling connection，Two rotors are connected with rotor folder by rotor connecting bolt respectively，Also has the rotor angle adjusting mechanism being used for regulating two rotor angles that two structures are identical，Servo-controller that each rotor angle adjusting mechanism includes being fixed on reduction box top and fixing seat，Described Servo-controller and fixing seat are respectively provided at the both sides of main shaft，The rocking arm of Servo-controller and the lower end of connecting rod connect，The upper end of connecting rod and one end of displacement dish shift fork connect，The lower end of swing connecting bar is connected by little axle and fixing seat，The upper end of swing connecting bar is connected by the other end of little axle and displacement dish shift fork，The middle part of displacement dish shift fork is arranged on displacement dish by little axle，Transverse axis is arranged at displacement dish top，The lower end of pitch pull bar is sleeved on transverse axis，The upper end of pitch pull bar is sleeved on the rear end of rotor folder pull bar，The front end of the rotor folder pull bar of two rotor angle adjusting mechanisms is separately fixed on two rotor folders.It is disadvantageous in that moving component is many, and structure is complicated, and weight is big, and cost is high, and fault rate is high.
Summary of the invention:
It is few that technical problem to be solved in the utility model is to provide a kind of moving component, and simple in construction, weight is little, and the oil of low cost moves multi-rotor aerocraft displacement system.
Above-mentioned purpose is achieved in that it includes that main shaft, rotor head are fixed on main shaft, and rotor head and the rotor folder being positioned at its both sides by pressure bearing and position connection in bearing；It is characterized in that: described main shaft is hollow-core construction, pitch change axes it is provided with in main shaft, the hole passed through for pitch change axes it is provided with in rotor head, described pitch change axes is stretched out from the top of rotor head, the top of pitch change axes is fixed with displacement shift fork, two ends with displacement shift fork respectively, the upper end of two pitch-change-links are connected by bearing pin, and the lower end of two pitch-change-links is connected with two rotors folders respectively, and the lower end of described pitch change axes is fixed with pitch bearing inner ring.
During installation, the outer ring of pitch bearing is connected with the rocking arm of Servo-controller.Servo-controller works, and drives pitch change axes to move up and down.
Being provided with copper sheathing between described pitch change axes and the hole wall of rotor head, described pitch change axes is slidably matched with upper copper sheathing, is provided with sealing ring between rotor head hole wall and the pitch change axes above described upper copper sheathing.
Being provided with lower copper sheathing between bottom described pitch change axes and main shaft, described pitch change axes is slidably matched with lower copper sheathing, is provided with lower seal between main shaft and the pitch change axes below described lower copper sheathing.
The utility model has the advantages that: Servo-controller works, drive pitch change axes to move up and down, drive while pitch change axes motion and drive two rotor folders to rotate by two pitch-change-links, it is achieved displacement.This displacement system structure is simple, and moving component is few, and weight is little, low cost, failure rate is low.
Accompanying drawing illustrates:
Fig. 1 is perspective view of the present utility model；
Fig. 2 is that master of the present utility model regards cross-sectional view；
Fig. 3 is plan structure schematic diagram of the present utility model.
Detailed description of the invention:
With reference to Fig. 13, it includes that main shaft 1, rotor head 2 are fixed on main shaft, and rotor head passes through connection in pressure bearing 4 and location bearing 5 with the rotor folder 3 being positioned at its both sides；It is characterized in that: described main shaft is hollow-core construction, pitch change axes 6 it is provided with in main shaft, the hole passed through for pitch change axes it is provided with in rotor head, described pitch change axes is stretched out from the top of rotor head, the top of pitch change axes is fixed with displacement shift fork 7, two ends with displacement shift fork respectively, the upper end of two pitch-change-links 8 are connected by bearing pin, and the lower end of two pitch-change-links is connected with two rotors folders respectively, and the inner ring of the lower end of described pitch change axes and pitch bearing 9 is fixed.
Being provided with copper sheathing 10 between described pitch change axes and the hole wall of rotor head, described pitch change axes is slidably matched with upper copper sheathing, is provided with sealing ring 11 between rotor head hole wall and the pitch change axes above described upper copper sheathing.
Being provided with lower copper sheathing 12 between bottom described pitch change axes and main shaft, described pitch change axes is slidably matched with lower copper sheathing, is provided with lower seal 13 between main shaft and the pitch change axes below described lower copper sheathing.
Claims (3)
1. oil moves a multi-rotor aerocraft displacement system, and including main shaft (1), rotor head (2) is fixed on main shaft, and rotor head and rotor folder (3) being positioned at its both sides join by pressure bearing (4) and location bearing (5) are middle；It is characterized in that: described main shaft is hollow-core construction, pitch change axes (6) it is provided with in main shaft, the hole passed through for pitch change axes it is provided with in rotor head, described pitch change axes is stretched out from the top of rotor head, the top of pitch change axes is fixed with displacement shift fork (7), two ends with displacement shift fork respectively, the upper end of two pitch-change-links (8) are connected by bearing pin, and the lower end of two pitch-change-links is connected with two rotors folders respectively, and the lower end of described pitch change axes is fixed with pitch bearing (9) inner ring.
2. according to the dynamic multi-rotor aerocraft displacement system of a kind of oil described in claim 1, it is characterized in that: between described pitch change axes and the hole wall of rotor head, be provided with copper sheathing (10), described pitch change axes is slidably matched with upper copper sheathing, is provided with sealing ring (11) between rotor head hole wall and the pitch change axes above described upper copper sheathing.
3. according to the dynamic multi-rotor aerocraft displacement system of a kind of oil described in claim 1 or 2, it is characterized in that: between bottom described pitch change axes and main shaft, be provided with lower copper sheathing (12), described pitch change axes is slidably matched with lower copper sheathing, is provided with lower seal (13) between main shaft and the pitch change axes below described lower copper sheathing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620463159.1U CN205738063U (en) | 2016-05-20 | 2016-05-20 | The dynamic multi-rotor aerocraft displacement system of a kind of oil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620463159.1U CN205738063U (en) | 2016-05-20 | 2016-05-20 | The dynamic multi-rotor aerocraft displacement system of a kind of oil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205738063U true CN205738063U (en) | 2016-11-30 |
Family
ID=57364386
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620463159.1U Expired - Fee Related CN205738063U (en) | 2016-05-20 | 2016-05-20 | The dynamic multi-rotor aerocraft displacement system of a kind of oil |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205738063U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105857578A (en) * | 2016-05-20 | 2016-08-17 | 辽宁辽飞航空科技有限公司 | Pitch-variable system for oil-driven multi-rotor wing aircraft |
| CN106741860A (en) * | 2016-12-30 | 2017-05-31 | 中航维拓（天津）科技有限公司 | A kind of oil based on composite moves many rotor flexible rotor systems |
-
2016
- 2016-05-20 CN CN201620463159.1U patent/CN205738063U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105857578A (en) * | 2016-05-20 | 2016-08-17 | 辽宁辽飞航空科技有限公司 | Pitch-variable system for oil-driven multi-rotor wing aircraft |
| CN106741860A (en) * | 2016-12-30 | 2017-05-31 | 中航维拓（天津）科技有限公司 | A kind of oil based on composite moves many rotor flexible rotor systems |
| CN106741860B (en) * | 2016-12-30 | 2023-09-29 | 重庆驼航科技有限公司 | Oil-driven multi-rotor flexible rotor system based on composite material |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103318404B (en) | A kind of guided missile aileron control mechanism | |
| CN205738063U (en) | The dynamic multi-rotor aerocraft displacement system of a kind of oil | |
| CN102211667A (en) | Flapping wing driving mechanism of two-level parallel gear reduction | |
| CN105857578A (en) | Pitch-variable system for oil-driven multi-rotor wing aircraft | |
| CN201330900Y (en) | Universal ball-and-socket joint | |
| CN207015582U (en) | Depopulated helicopter displacement limit adjusting mechanism | |
| CN207109902U (en) | A kind of machinery rotation hydraulic shear | |
| CN207346093U (en) | A kind of inclining rotary mechanism and motor reclining device | |
| CN202987497U (en) | Mechanical rotating actuator | |
| CN205315632U (en) | Rotary motion changes linear movement device | |
| CN202319808U (en) | Balance suspension for heavy duty truck | |
| CN203602209U (en) | Rigidity-variable structure assembly suitable for lifting | |
| CN203401369U (en) | Swing frame and swing angle mechanism of beveling machine | |
| CN206087266U (en) | Control large -scale unmanned helicopter tilting plate's device | |
| CN201195531Y (en) | Brake structure | |
| CN205587783U (en) | Screw tap device | |
| CN205930888U (en) | Put a section arm front axle in motor sweeper | |
| CN201165677Y (en) | Valve control device of slipping loader | |
| CN202780366U (en) | Rear wheel adjusting mechanism for pipe diameter pneumatic internal aligning device | |
| CN204197275U (en) | For preventing the mechanism of helicopter tail rotor locking | |
| CN209650362U (en) | A kind of chassis transmission shaft | |
| CN206856794U (en) | A kind of transfer for dual axle | |
| CN204055201U (en) | Four-wheeled tractor elasticity propons | |
| CN203187261U (en) | Flexible connection structure for transmission gear and suspension cage of elevator | |
| CN203614521U (en) | Fast electric locking device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161130 Termination date: 20180520 |