CN207267532U - A kind of aircraft active differential mechanism speed adjusting gear - Google Patents
A kind of aircraft active differential mechanism speed adjusting gear Download PDFInfo
- Publication number
- CN207267532U CN207267532U CN201720501189.1U CN201720501189U CN207267532U CN 207267532 U CN207267532 U CN 207267532U CN 201720501189 U CN201720501189 U CN 201720501189U CN 207267532 U CN207267532 U CN 207267532U
- Authority
- CN
- China
- Prior art keywords
- gear
- differential mechanism
- semiaxis
- active
- assisted
- 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
- Retarders (AREA)
Abstract
Vehicle technology field is the utility model is related to, is specially the chamber that a kind of aircraft active differential mechanism speed adjusting gear includes three side by side including frame shell, the frame shell；Differential mechanism is equipped with intermediate cavity；The output terminal of the differential mechanism with from half axis connection；It is connected from semiaxis with propeller drive；In both sides, symmetry is equipped with active arrangements for speed regulation.Aircraft active differential mechanism speed adjusting gear provided by the utility model improves the overall function of aircraft, adds the attitude regulation means of aircraft, improves power utilization efficiency.
Description
Technical field
Vehicle technology field is the utility model is related to, is specially a kind of aircraft active differential mechanism speed adjusting gear.
Background technology
The electronic multi-rotor aerocraft of tradition, the motor of every branch shaft end is all independent driving, can be adjusted and divided by each electricity
The rotating speed of motor Tiao Zheng not corresponded to, using each motor speed difference with the rotor pulling force difference that produces adjust the appearance of aircraft
State.The electronic more rotors of tradition are each independent speed governing of branch spindle motor, simple in structure between each other without the contact of mechanical aspects, are adjusted
It is single to save the means of posture, it is usually out of question for self-contained power driving, but if using other high-powers but react
The single power of slow power source (for example engine etc.) composition disperses the multi-rotor aerocraft for exporting this new structure,
It can not just meet the needs for adjusting posture.The driving motor of the electronic multi-rotor aerocraft of tradition must simultaneously meet active force driving
With the needs of pose adjustment, power utilization efficiency is low, can not always work in optimum state.
There is no good solution to this innovative multi-rotor aerocraft pose adjustment under the prior art, not only very
The feature of aircraft is defined in big degree, and very big use obstacle is caused to user, limits whole more rotors
The fast development of aircraft industry.
Utility model content
The purpose of this utility model is to provide a kind of aircraft active differential mechanism speed adjusting gear, to solve above-mentioned background skill
The problem of being proposed in art.Aircraft active differential mechanism speed adjusting gear provided by the utility model improves the overall work(of aircraft
Energy property, adds the attitude regulation means of aircraft, improves power utilization efficiency.
To achieve the above object, the utility model provides following technical solution：
A kind of aircraft active differential mechanism speed adjusting gear, including frame shell, the frame shell include three side by side
Chamber；Differential mechanism is equipped with intermediate cavity；The output terminal of the differential mechanism with from half axis connection；From semiaxis and propeller drive
Device connects；In both sides, symmetry is equipped with active arrangements for speed regulation；The active arrangements for speed regulation include adjustment actuating mechanism and control
Mechanism processed；The adjustment actuating mechanism includes power-assisted adjusting mechanism and damper regulation mechanism；The power-assisted adjusting mechanism includes master
Dynamic power-assisted gear, the driven power-assisted gear for driving the assist motor of active power-assisted gear and being engaged with active power-assisted gear, institute
State driven power-assisted gear with from half axis connection；The damper regulation mechanism includes damping adjustment disk and adjusts dish gap with damping
The damping brake block of cooperation；The damping brake block with from half axis connection；The control mechanism is connected with assist motor electric signal
And control the operation of assist motor；The control mechanism is connected with damping adjustment disk electric signal and adjusts damping adjustment disk and damping
The gap of brake block；The differential mechanism includes a pinion frame, and it is symmetrical to be provided with least two inside the pinion frame
Planet conical tooth, with the slave semiaxis conical tooth from half axis connection respectively the left and right sides by gear engage connection two planets
Conical tooth；Connection driven gear on the outside of the pinion frame, the driving gear that driven gear engagement is fixedly connected with transmission shaft.
Wherein, the frame shell is that integrated formed structure or three separate chambers cooperations form.
Compared with prior art, the beneficial effects of the utility model are：The utility model is rational in infrastructure, functional, main
The control mechanism output mixing cross-over control signal of dynamic arrangements for speed regulation, mixing cross-over control both sides adjustment actuating mechanism, in side
The work of power-assisted power adjusting mechanism when, the damper regulation mechanism of other side cooperates, so that active controlled differential mechanism both sides
From the torque size inverse change suffered by semiaxis, the revolution speed of propeller on the both sides fulcrum of equispeed output is set to occur reversely to become
Change, i.e., other side is slowed down while side accelerates, and then realizes the purpose for changing both sides revolution speed of propeller difference；It can reach actively
The effect of speed governing, both sides propeller are connected by mechanical structure, and interaction, economical and practical, durability is strong, and the utility model leads to
Cross rational structure to add up to, by changing the speed discrepancy of each propeller in real time respectively, can dynamically be adjusted in flight course
The posture of aircraft, adds the attitude regulation means of aircraft, greatly enhances the overall function of aircraft, be
Develop various new multi-rotor aerocrafts to provide more choices space, disperse to export particularly suitable for various single powers,
And more rotors in high-power low-response speed power source are equipped with, meet the needs of its pose adjustment.Provided for user very big
Facility.
Brief description of the drawings
Fig. 1 is the overall structure diagram of the utility model；
Fig. 2 is the active arrangements for speed regulation structure diagram of the utility model；
Attached drawing identifies：
1. frame shell, 2. differential mechanisms, 3. first active arrangements for speed regulation, 3 ' the second actives of arrangements for speed regulation, 4. deflecting tapers
Tooth group, 5. adjustment actuating mechanisms, 6. control mechanisms, 7. propeller drives, 8. power-assisted adjusting mechanisms, 9. damping adjusting machines
Structure, 10. propellers, 11. driving gears, 12. driven gears, 13. active power-assisted gears, 14. driven power-assisted gears, 15. planets
Conical tooth, 17. axle shaft gears, 18. driving conical tooths, 19. rotating shaft conical teeth, 21. assist motors, 22. damping adjustment disks, 23 resistances
Buddhist nun's brake block, 24. shaft couplings, 31. pinion frames, 41. transmission shafts, 45. are from semiaxis, 47. rotary-wing transmission axis, 48. propellers
Shaft, 55.T types fixed seat, 56. shaft seats, 61. bearings.
Embodiment
The following is a combination of the drawings in the embodiments of the present utility model, the technical solution of the utility model is carried out clear, complete
Site preparation describes.
Please refer to Fig.1 and Fig. 2, the utility model provide a kind of aircraft active differential mechanism speed adjusting gear, including outside frame
Shell 1, the frame shell 1 include the chamber three side by side；Differential mechanism 2 is equipped with intermediate cavity；The output of the differential mechanism 2
End is connected with from semiaxis 45；It is connected from semiaxis 45 with propeller drive 7；
In both sides, symmetry is equipped with active arrangements for speed regulation 3,3 '；
The active arrangements for speed regulation 3,3 ' include adjustment actuating mechanism 5 and control mechanism 6；The adjustment actuating mechanism 5 wraps
Include power-assisted adjusting mechanism 8 and damper regulation mechanism 9；
The power-assisted adjusting mechanism 8 include active power-assisted gear 13, driving active power-assisted gear 13 assist motor 21 with
And the driven power-assisted gear 14 engaged with active power-assisted gear 13, the driven power-assisted gear 14 are connected with from semiaxis 45；
The damper regulation mechanism 9 includes damping adjustment disk 22 and the damping with damping 22 clearance fit of adjustment disk is braked
Piece 23；The damping brake block 23 is connected with from semiaxis 45；
The control mechanism 6 is connected with 21 electric signal of assist motor and controls the operation of assist motor 21；The control machine
Structure 6 is connected with damping 22 electric signal of adjustment disk and adjusts damping adjustment disk 22 with damping the gap of brake block 23.
Preferably, the differential mechanism 2 includes a pinion frame 31, and at least two are provided with inside the pinion frame 31
A symmetrical planet conical tooth 15, is engaged in the left and right sides by gear respectively with the slave semiaxis conical tooth 17 being connected from semiaxis 45
Connect two planet conical tooths 15；The outside of the pinion frame 31 connection driven gear 12, the engagement of driven gear 12 and transmission
The driving gear 11 that axis 41 is fixedly connected.
Preferably, the frame shell 1 is that integrated formed structure or three separate chambers cooperations form.
Preferably, the propeller drive 7 is by deflecting conical tooth group 4, rotary-wing transmission axis 47, propeller shaft 48, T
Type fixed seat 55, shaft seat 56 and bearing 61 etc. form.
Preferably, the deflecting conical tooth group 4 include the driving conical tooth 18 that be connected with rotary-wing transmission axis 47 and top and
The rotating shaft conical tooth 19 that propeller shaft 48 connects, driving conical tooth 18 engage connection rotating shaft conical tooth 19 by gear.
Preferably, the driving gear 11, driven gear 12, active power-assisted gear 13, driven power-assisted ratchet 14, OK
Star conical tooth 15, main semiaxis conical tooth 16, axle shaft gear 17, driving conical tooth 18, the specification of rotating shaft conical tooth 19 are no less than one
Kind.
Preferably, the frame shell 1 is equipped with bearing 61 with transmission shaft 41, from 45 junction of semiaxis.
Preferably, the planet conical tooth 15 is equipped with bearing 61 with 31 junction of pinion frame.
Preferably, the T-shaped fixed seat 55 is equipped with bearing 61 with 47 junction of rotary-wing transmission axis.
Preferably, the shaft seat 56 is equipped with bearing 61 with 48 junction of propeller shaft.
Preferably, the transmission shaft 41, many from semiaxis 45, rotary-wing transmission axis 47 and the diameter specifications of propeller shaft 48
In one kind.
Preferably, the planet conical tooth 15 is no less than two.
The operation principle of the utility model is：The symmetrically arranged first active arrangements for speed regulation 3 and second in the left and right sides are actively
Arrangements for speed regulation 3 ' cooperate, their output mixing cross-over control signal of control mechanism 6, mixing cross-over control both sides, which are adjusted, holds
Row mechanism 5, when the power-assisted power adjusting mechanism 8 of side works, the damper regulation mechanism 9 of other side cooperates, so that main
Dynamic control damping inverse change of 2 both sides of differential mechanism from semiaxis 45, the planet conical tooth 15 of differential mechanism 2 rotate, and both sides are from semiaxis
45 rotating speed inverse change therewith, by shaft coupling 24, occurs 10 rotating speed of propeller on the both sides fulcrum of equispeed output anti-
To change, i.e., other side is slowed down while side accelerates, and makes each propeller 10 of aircraft can be realized in flight course
The operation of relative rotation speed difference；Economical and practical, durability is strong.
It by being used cooperatively for multigroup bearing 61, can not only be improved integrally-built stability and practicality,
And substantial amounts of operating noise can be avoided the occurrence of, practicality is very strong.
The power of engine drives driven gear through transmission shaft by driving gear, so that planetary wheel carrier is driven, then by going
Star wheel frame drives left and right two semiaxis, drives left and right rotor respectively.The design requirement of differential mechanism meets：Left half axle rotating speed+the right side
Half rotating speed=2 × planetary wheel carrier rotating speed.When aircraft keeps horizontal attitude, left and right rotor turns with planetary wheel carrier three's
Speed is equal to be in equilibrium state, and when aircraft needs to tilt to side, intersected by the mixing of both sides active arrangements for speed regulation
Control, causes side rotor rotating speed to reduce, the increase of other side rotor rotating speed.
The utility model is connected by rational structure design, both sides propeller by mechanical structure, interaction, can
Speed discrepancy between easy and convenient each propeller of change, by changing the speed discrepancy of each propeller, very great Cheng in real time respectively
The overall function of aircraft is improved on degree, adds the attitude regulation means of aircraft.
The utility model is rational in infrastructure, highly practical, passes through active power drive mechanism and device for adjusting posture relative separation
And the technological means realized respectively, provide more choices space, be particularly suitable for develop various new multi-rotor aerocrafts
Disperse to export in various single powers, and be equipped with more rotors in high-power low-response speed power source, meet its pose adjustment
Need.Provide great convenience for user, there is very strong practicality.
The foregoing is merely the patent model of specific embodiment of the present utility model, not thereby limitation the utility model
Enclose, every equivalent structure transformation made based on the specification and figures of the utility model, is directly or indirectly used in it
His relevant technical field, is equally included in the patent within the scope of the utility model.
Claims (2)
- A kind of 1. aircraft active differential mechanism speed adjusting gear, it is characterised in that：Including frame shell（1）, the frame shell（1） Including the chamber three side by side；Differential mechanism is equipped with intermediate cavity（2）；The differential mechanism（2）Output terminal with from semiaxis （45）Connection；From semiaxis（45）With propeller drive（7）Connection；In both sides, symmetry is equipped with active arrangements for speed regulation（3,3 '）；The active arrangements for speed regulation（3,3 '）Including adjustment actuating mechanism（5）And control mechanism（6）；The adjustment actuating mechanism （5）Including power-assisted adjusting mechanism（8）And damper regulation mechanism（9）；The power-assisted adjusting mechanism（8）Including active power-assisted gear（13）, driving active power-assisted gear（13）Assist motor （21）And with active power-assisted gear（13）The driven power-assisted gear of engagement（14）, the driven power-assisted gear（14）With from semiaxis （45）Connection；The damper regulation mechanism（9）Including damping adjustment disk（22）And with damping adjustment disk（22）The damping of clearance fit is stopped Car piece（23）；The damping brake block（23）With from semiaxis（45）Connection；The control mechanism（6）With assist motor（21）Electric signal connects and controls assist motor（21）Operation；The control Mechanism（6）With damping adjustment disk（22）Electric signal connects and adjusts damping adjustment disk（22）With damping brake block（23）Gap；The differential mechanism（2）Including a pinion frame（31）, the pinion frame（31）Inside is provided with least two pairs The planet conical tooth of title（15）, and from semiaxis（45）The slave semiaxis conical tooth of connection（17）Nibbled respectively in the left and right sides by gear Close two planet conical tooths of connection（15）；The pinion frame（31）Outside connects driven gear（12）, driven gear（12） Engagement and transmission shaft（41）The driving gear being fixedly connected（11）.
- A kind of 2. aircraft active differential mechanism speed adjusting gear according to claim 1, it is characterised in that：The frame shell （1）It is that integrated formed structure or three separate chambers cooperations form.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720501189.1U CN207267532U (en) | 2017-05-08 | 2017-05-08 | A kind of aircraft active differential mechanism speed adjusting gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720501189.1U CN207267532U (en) | 2017-05-08 | 2017-05-08 | A kind of aircraft active differential mechanism speed adjusting gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207267532U true CN207267532U (en) | 2018-04-24 |
Family
ID=61959648
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720501189.1U Expired - Fee Related CN207267532U (en) | 2017-05-08 | 2017-05-08 | A kind of aircraft active differential mechanism speed adjusting gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207267532U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106956770A (en) * | 2017-05-08 | 2017-07-18 | 莆田市双普信息科技有限公司 | A kind of aircraft active differential mechanism speed adjusting gear |
| WO2019210640A1 (en) * | 2018-05-02 | 2019-11-07 | 深圳市道通智能航空技术有限公司 | Motor control method and apparatus |
-
2017
- 2017-05-08 CN CN201720501189.1U patent/CN207267532U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106956770A (en) * | 2017-05-08 | 2017-07-18 | 莆田市双普信息科技有限公司 | A kind of aircraft active differential mechanism speed adjusting gear |
| WO2019210640A1 (en) * | 2018-05-02 | 2019-11-07 | 深圳市道通智能航空技术有限公司 | Motor control method and apparatus |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107244234B (en) | Dual-motor dual-planet electricity-discharging driving device and working method thereof | |
| CN206926509U (en) | A kind of more gear electric drive transmission devices | |
| CN106143120B (en) | The wheel motor drive device of electric vehicle and electric vehicle method of work | |
| CN206485572U (en) | A kind of double differectial active speed regulating structure of multi-rotor aerocraft | |
| CN207961431U (en) | A kind of parallel dual input planetary transmission for mixed power electric car | |
| CN207267532U (en) | A kind of aircraft active differential mechanism speed adjusting gear | |
| CN106956770A (en) | A kind of aircraft active differential mechanism speed adjusting gear | |
| CN109882557A (en) | A kind of compound planet gear hub reduction gear | |
| CN112895883A (en) | Dual-drive-source and double-row planetary gear train multi-mode coupling driving system and automobile | |
| CN109760501A (en) | Double planet wheel rows of mixing power coupling mechanism | |
| CN206884717U (en) | Single planetary row hybrid power system and the vehicle using the hybrid power system | |
| CN113696676A (en) | Torque-oriented distribution electric drive axle using planet row and double gear | |
| CN104309466B (en) | Birotor motor type hybrid power drive of tracked vehicle | |
| CN103978882B (en) | The power transmission of motor vehicle driven by mixed power | |
| CN107627832A (en) | Reverse-flow type power coupling transmission system | |
| CN106494216A (en) | Driving force system before plug-in hybrid vehicle | |
| CN108327496B (en) | Dual-motor pure electric driving system and electric automobile using same | |
| CN106741930A (en) | A kind of double differectial active speed regulating structure of multi-rotor aerocraft | |
| CN105644344B (en) | Hybrid vehicle infinitely variable transmission | |
| CN101549643B (en) | Electrically driven speed change system of vehicle | |
| CN104165214B (en) | A kind of double dynamical synthesizer | |
| CN110281760A (en) | Hybrid electric drive system and application | |
| CN106828066B (en) | Dual-motor nutation speed change device and working method thereof | |
| CN110966360A (en) | Transmission device, control method thereof and automobile | |
| CN201590715U (en) | Deceleration variable-speed drive device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| 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: 20180424 Termination date: 20210508 |