CN206552264U - A kind of displacement rotor power system module - Google Patents
A kind of displacement rotor power system module Download PDFInfo
- Publication number
- CN206552264U CN206552264U CN201720227272.4U CN201720227272U CN206552264U CN 206552264 U CN206552264 U CN 206552264U CN 201720227272 U CN201720227272 U CN 201720227272U CN 206552264 U CN206552264 U CN 206552264U
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- China
- Prior art keywords
- displacement rotor
- rotor power
- displacement
- engine
- rotor
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- 238000006073 displacement reaction Methods 0.000 title claims abstract description 56
- 239000007858 starting material Substances 0.000 claims abstract description 24
- 230000007246 mechanism Effects 0.000 claims abstract description 21
- 230000008878 coupling Effects 0.000 claims abstract description 9
- 238000010168 coupling process Methods 0.000 claims abstract description 9
- 238000005859 coupling reaction Methods 0.000 claims abstract description 9
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 8
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 2
- 229910052799 carbon Inorganic materials 0.000 claims description 2
- 239000002131 composite material Substances 0.000 claims description 2
- 239000000835 fiber Substances 0.000 claims description 2
- 238000010276 construction Methods 0.000 abstract description 7
- 230000005540 biological transmission Effects 0.000 description 7
- 239000003921 oil Substances 0.000 description 5
- 230000008859 change Effects 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000003213 activating effect Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Abstract
Displacement rotor power system module is a kind of relatively independent rotor power system, including displacement rotor power assembly (1), variable pitch contro l mechanism (2) and displacement rotor (3).Described displacement rotor power assembly (1), including frame (4), it is installed on engine (11), decelerator (14), radiator fan (15) and starter (16) in frame (4), clutch (12) and shaft coupling (13)；The frame (4), including end plate (41), side plate (42), engine support (43), reducer stent (44), support of radiating fan (45) and starter support (46)；The variable pitch contro l mechanism (2), including variable pitch contro l steering wheel (21), distance-variable rocker arm (22), price fixing (23) and Moving plate (24)；The displacement rotor (3), including rotor blade (31) and propeller hub (32).The utility model displacement rotor power system module compact conformation, can drive rotor and realize variable pitch contro l, while housing construction of the rotor power system module independently of unmanned vehicle, it is adaptable to a variety of aircraft layouts.
Description
Technical field
The utility model is related to the displacement rotor power system of aircraft, belongs to aeronautical product technical field.
Background technology
Rotor system is the important component of modern helicopters and multi-rotor aerocraft.Spacing rotor system and displacement rotation
Wing system is the topmost two kinds of rotor systems of current small aircraft, and spacing rotor is to change rotation by changing variable rotor speed
Wing pulling force, and displacement oar is then by changing rotor away from completing.As contemporary aircraft is wanted to rotor power system
Raising is asked, displacement rotor power system increasingly obtains the favor of Flight Vehicle Design personnel, and this key factor is two aspect reasons：
1 is limited in scope with the increase of paddle size, rotor inertia increase, the rotation speed change of spacing oar；2 displacement rotor power systems are led to
Crossing change pitch has higher dynamic response speed.But, compared to spacing rotor system, displacement rotor system adds change
Spacing mechanism, its structure is also relative complex, and which not only improves the difficulty of structure design of its system itself, also complete machine structure is designed
Propose higher requirement.The utility model is related to a kind of displacement rotor system power plant module, and the power plant module is integrated with fuel oil
Engine and its power assembly, starter, radiator fan and rotor pitch-changing mechanism, simplify the structure of the dynamic displacement rotor system of oil
Layout, makes many rotor power parts of displacement independently of overall aircraft frame structure, is not changing drive system mode and inside
In the case of part relative position, a variety of aircraft body structures, including many rotors, tiltrotor aircraft etc. are applicable.
Utility model content
The utility model is related to a kind of displacement rotor power system module, the rotor power system module compact conformation, energy
Enough drive rotor and realize variable pitch contro l, controlled by the mixing to throttle and pitch, reach the lift requirement specified, improve
The lift response speed of dynamical system.
The utility model provides a kind of displacement rotor power system module, including displacement rotor power assembly (1), displacement
Controlling organization (2) and displacement rotor (3).
The displacement rotor power assembly (1), including frame (4), are installed on engine (11) in frame (4), clutch
Device (12), shaft coupling (13), decelerator (14), radiator fan (15) and starter (16).The radiator fan (15), starter
(16), the input of clutch (12), shaft coupling (13) and decelerator (14) is coaxial with engine (11).The power assembly collection
Into the function of starter, radiating, driving and displacement, a variety of displacement rotors (three blade rotors, four blade rotors etc.) are adapted to.Engine
(11) power output is delivered to displacement rotor (3) via clutch (12), shaft coupling (13) and decelerator (14) successively, for flight
Device provides lift；Clutch (12) ensures that engine starts from car, closes car operating.Decelerator (14) can effectively improve power assembly
Output torque, to adapt to the rated operation of displacement rotor (3).Radiator fan (15) can realize cooling engine (11)
Function.Starter (16) provides power for engine start.
The frame (4) includes end plate, two side plates (42) perpendicular to end plate (41) plane, and between biside plate
Multiple equipment support (engine support (43), reducer stent (44), support of radiating fan (45) and starter support (46)),
Described equipment supporter is used to fix the engine (11), decelerator (14), radiator fan (15) and starter (16).Its
In, engine support (43) and starter support (46) plane are both perpendicular to end plate (41) and side plate (42) plane.The machine
Each part is plate stem structure type in frame (4), it is adaptable to carbon fibre composite moulding process, processes low with manufacturing cost,
Each part of structure is easy to dismounting simultaneously, is laid out with the connecting interface of aircraft body structure suitable for a variety of aircraft.
The variable pitch contro l mechanism (2), including variable pitch contro l steering wheel (21), distance-variable rocker arm (22), price fixing (23) and Moving plate
(24).The difference of the pitch-changing mechanism and conventional helicopters pitch-changing mechanism is that it is remained always away from pitch-changing mechanism, eliminates the cycle
It is simple and compact for structure away from pitch-changing mechanism, reliability enhancing.Steering wheel (21) provides driving force, distance-variable rocker arm (22) for pitch-changing mechanism
Driving price fixing (23) and Moving plate (24) are moved along engine output shaft direction, while price fixing (23) is produced along deceleration with Moving plate (24)
Device output shaft is rotated against, realize rotary wing changing away from spinfunction.Variable pitch contro l mechanism (2) all actuation mechanisms and driving
Part is installed in inside modules, and mechanical interface is not present between aircraft body structure.
The displacement rotor (3), including rotor blade (31) and propeller hub (32).The displacement rotor and conventional helicopters rotor
Identical, three leaf oars, four leaf oars and leafy oar are applicable.
Technical characterstic of the present utility model is：
1. the design of the utility model power assembly is compacter, all drive apparatus (radiator fan, starter, connection
Axle device, clutch, decelerator input) it is coaxial with engine shaft, the flexible coupling of use can effectively vibration isolation, and transmission effect
Rate is high.And at present applied or patent of invention ([CN201510352516], [CN201510834969],
[CN201510708147), [CN201410790940]) described in many rotor power systems be rely on belt or bevel gear
Transmission, the transmission efficiency of this mode can lose, and corresponding supporting construction is also complicated, and engine support is located at aircraft machine
The structure design for influencing whether complete machine is changed in internal portion, the design of rotor system, and scalability is not high；
2. the utility model structure design uses drawer-type structure, side plate surrounds semi-closed structure, drive apparatus with end plate
Support can be based on side plate, between biside plate, and this structure type is conducive to the extension and reduction of drive apparatus,
And can be directly by support unit load transmission to end plate, Path of Force Transfer is relatively direct, structural bearing efficiency high.
It is of the present utility model to have the technical effect that：
1. coaxial transmission design is carried out by each part of above-mentioned rotor power assembly and special knot is carried out to driving frame
Structure is designed so that the power section of many rotors of displacement forms independent system module, do not changing system independently of rack construction
In the case of the kind of drive and internal part relative position, it is adaptable to the housing construction of a variety of unmanned planes.
2. on power assembly the removal of equipment and extend it is relatively easy, only need to be added in the drive path of power assembly or
Removing device, and attachment structure is designed on the correspondence position of assembly rack construction, improve displacement rotor power assembly
The flexibility of function.
Brief description of the drawings
Fig. 1 is the utility model displacement rotor power system module schematic diagram；
Fig. 2 is the utility model power assembly schematic diagram；
Fig. 3 is the utility model rack construction schematic diagram；
Fig. 4 is the utility model variable pitch contro l structural representation；
In figure：
Embodiment
Below in conjunction with accompanying drawing, the utility model is described in further detail.
The dynamic displacement rotor power system module of the utility model oil can drive rotor and realize variable pitch contro l, by oil
The mixing of door and pitch is controlled, and reaches the lift requirement specified.It is preferred that, its controller should carry out lift control by changing pitch
System, while being compensated automatically to throttle, to ensure the stability of lift output.
Displacement rotor power system module, including displacement rotor power assembly (1), variable pitch contro l mechanism (2) and displacement rotation
The wing (3), referring to Fig. 1.
Fig. 2 shows the embodiment of displacement rotor power assembly (1) one, including frame (4), is installed on the combustion in frame (4)
Oil turbine (11), centrifugal clutch (12), diaphragm coupling (13), parallel shaft (speed) reducer (14), radiator fan (15) and
Starter (16).Such as Fig. 2, described radiator fan (13), starter (14), centrifugal clutch (15), diaphragm coupling
(16) and parallel shaft (speed) reducer (12) input it is coaxial with fuel engines (11).
Described engine (11) is as the main source of displacement rotor (3) driving force, and four strokes, two stroke engine are equal
It is applicable, it should provide enough running powers to drive rotor.It is preferred that, clutch (12) is centrifugal clutch, structure letter
It is single, and the slow-speed of revolution can be realized from car, high rotating speed closes car function, it is ensured that engine starts from car, closes car operating.It is preferred that, connection
Axle device (13) is diaphragm type coupler, and it can adapt to clutch (12) output shaft and is installed with decelerator (14) input shaft decentraction
Produced eccentric error.Decelerator (14) should effectively improve the output torque of power assembly, to take into account displacement rotor (3) and combustion
The rated operation of oil turbine (11), improves decelerator in fuel utilization ratio, the present embodiment and uses parallel gears decelerator,
It is not limited to parallel gears herein, bevel gear, the retarder variant such as planetary gear is applicable.Radiator fan (15) should be connected directly between
On engine output shaft, radiator fan (15) is directly driven using the power of fuel engines (11), to strengthen local wind rate, from
And the purpose of cooling fuel engines (11) is reached, radiator fan should have wind guide component, directly increase engine cylinder-body fin
Partial local air flow.Starter (16) should be connected directly between on engine output shaft, pass through its motor internal and deceleration
Device driving engine reaches toggle speed and provides enough starting torques, general to require, when electrically activating maximum power operation
Engine can reach more than initial velocity 500rpm, meanwhile, unilateral bearing should be installed between engine shaft by electrically activating, to protect
Power assembly runs well after card starts.
Fig. 3 shows the embodiment of the frame (4) structure one, including end plate, two sides perpendicular to end plate (41) plane
Plate (42), and multiple equipment support (engine support (43), reducer stent (44), radiator fan branch between biside plate
Frame (45) and starter support (46)), described equipment supporter is used to fix the engine (11), decelerator (12), radiating
Fan (13) and starter (14).Wherein, engine support (43) and starter support (46) plane are both perpendicular to end plate
And side plate (42) plane (41).Frame end plate (41) is joined directly together with biside plate (42) in such as Fig. 3, the embodiment carries for each support
For basis, the space between biside plate (42) is from bottom to top successively with bolt connection engine support (43), support of radiating fan
(45), starter support (46) and reducer stent (44).It is preferred that, engine support (43) should be installed between engine to be subtracted
Pad is shaken, is fixed on by engine connecting bolt in engine connecting bracket.Starter support (45) is according to starter form
It is designed, it is preferred that between biside plate (42).It is preferred that, it is defeated that decelerator (46) support mounting point is located at decelerator
Below shaft, directly by rotor load transmission to rack construction, with optimizing load transfer path, to reduce the load of reducer shell
Lotus.
Fig. 4 shows the embodiment of variable pitch contro l mechanism (2) one, including variable pitch contro l steering wheel (21), and distance-variable rocker arm (22) is fixed
Disk (23) and Moving plate (24).The present embodiment pitch-changing mechanism provides drive using single rocking arm type of drive, steering wheel (21) for pitch-changing mechanism
Power, distance-variable rocker arm (22) driving price fixing (23) and Moving plate (24) are moved along engine output shaft direction, price fixing (23) and Moving plate
(24) relatively rotated between, sliding bearing, price fixing (23) and Moving plate should be installed between price fixing (23) and decelerator (14) output shaft
(24) deep groove ball bearing or needle bearing should be installed between.Such as Fig. 4, variable pitch contro l mechanism (2) all actuation mechanisms and drive division
Part is installed in inside modules, and mechanical interface is not present between aircraft body structure.
Core of the present utility model is to carry out coaxial transmission design and pin to each part of power assembly of many rotors of displacement
Special structure design is carried out to assembly frame, displacement rotor power system itself is formd independent system module, is extended
The scope of application of displacement rotor power system on board the aircraft, can in the case where not changing internal system design expanded application
Into many rotor-hub configurations such as six rotors, eight rotors.The utility model is not limited to above-mentioned embodiment, if to this practicality
New various changes and deformation do not depart from the utility model scope, still fall within claim of the present utility model and equivalent technology
Within the scope of.
Claims (10)
1. a kind of displacement rotor power assembly, including frame (4), are installed on engine (11), decelerator in frame (4)
(14), radiator fan (15) and starter (16), clutch (12) and shaft coupling (13), it is characterised in that the radiator fan,
Starter, shaft coupling, clutch and decelerator input it is coaxial with engine shaft.
2. displacement rotor power assembly as claimed in claim 1, it is characterised in that the frame includes end plate and perpendicular to end
Two side plates of plate plane.
3. displacement rotor power assembly as claimed in claim 2, it is characterised in that be provided between described two side plates multiple
Support, the support is used to fix the engine, decelerator, radiator fan and starter.
4. displacement rotor power assembly as claimed in claim 3, it is characterised in that the frame includes engine support
(43), its plane is both perpendicular to the end plate and side plate planar.
5. displacement rotor power assembly as claimed in claim 3, it is characterised in that the frame includes starter support
(46), its plane is both perpendicular to the end plate and side plate planar.
6. displacement rotor power assembly as claimed in claim 1, it is characterised in that the frame is by carbon fibre composite system
Into.
7. a kind of displacement rotor power system module, it is characterised in that total including displacement rotor power as claimed in claim 1
Into (1), variable pitch contro l mechanism (2) and displacement rotor (3).
8. displacement rotor power system module as claimed in claim 7, it is characterised in that variable pitch contro l mechanism (2) bag
Variable pitch contro l steering wheel (21), distance-variable rocker arm (22), price fixing (23) and Moving plate (24) are included, the steering wheel (21) provides driving force, institute
Stating distance-variable rocker arm (22) drives the price fixing (23) and the Moving plate (24) to be moved along engine output shaft direction, while described fixed
Disk (23) and the Moving plate (24) produce rotating against along reducer output shaft, realize rotary wing changing away from spinfunction,
Mechanical interface is not present between the variable pitch contro l mechanism (2) and aircraft body structure.
9. displacement rotor power system module as claimed in claim 7, it is characterised in that the displacement rotor (3) includes rotation
Wing blade (31) and propeller hub (32).
10. displacement rotor power system module as claimed in claim 7, it is characterised in that the displacement rotor (3) includes three
Leaf oar, four leaf oars or more leaf oar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720227272.4U CN206552264U (en) | 2017-03-09 | 2017-03-09 | A kind of displacement rotor power system module |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720227272.4U CN206552264U (en) | 2017-03-09 | 2017-03-09 | A kind of displacement rotor power system module |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206552264U true CN206552264U (en) | 2017-10-13 |
Family
ID=60363768
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720227272.4U Expired - Fee Related CN206552264U (en) | 2017-03-09 | 2017-03-09 | A kind of displacement rotor power system module |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206552264U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106697281A (en) * | 2017-03-09 | 2017-05-24 | 北京天宇新超航空科技有限公司 | Variable-pitch rotor wing power system module |
-
2017
- 2017-03-09 CN CN201720227272.4U patent/CN206552264U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106697281A (en) * | 2017-03-09 | 2017-05-24 | 北京天宇新超航空科技有限公司 | Variable-pitch rotor wing power system module |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171013 |
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| CF01 | Termination of patent right due to non-payment of annual fee |