CN108674645A - A kind of aircraft device - Google Patents
A kind of aircraft device Download PDFInfo
- Publication number
- CN108674645A CN108674645A CN201810597523.7A CN201810597523A CN108674645A CN 108674645 A CN108674645 A CN 108674645A CN 201810597523 A CN201810597523 A CN 201810597523A CN 108674645 A CN108674645 A CN 108674645A
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- Prior art keywords
- energy
- driving part
- aircraft
- needed
- rotor
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- 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.)
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- 239000003990 capacitor Substances 0.000 claims description 4
- 238000004804 winding Methods 0.000 claims description 4
- 239000000446 fuel Substances 0.000 claims description 3
- 239000000126 substance Substances 0.000 claims description 3
- 238000010276 construction Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 11
- 238000012544 monitoring process Methods 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 6
- 238000013461 design Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000011835 investigation Methods 0.000 description 2
- 241000251468 Actinopterygii Species 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 229910018095 Ni-MH Inorganic materials 0.000 description 1
- 229910018477 Ni—MH Inorganic materials 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- OJIJEKBXJYRIBZ-UHFFFAOYSA-N cadmium nickel Chemical compound [Ni].[Cd] OJIJEKBXJYRIBZ-UHFFFAOYSA-N 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
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- 238000011161 development Methods 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 229940079593 drug Drugs 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 229910021389 graphene Inorganic materials 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
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- 239000007787 solid Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Braking Arrangements (AREA)
Abstract
The present invention provides a kind of aircraft device, including：Aircraft body；At least one rotor being connect with the aircraft body is configured to drive the movement of the aircraft body by rotating；The drive module being set on each rotor is configured to provide for the driving force needed for the corresponding rotor wing rotation；And the control module being connect with the drive module, the drive module provides the driving force needed for the corresponding rotor wing rotation to construction in order to control；The drive module includes multiple driving parts, and each driving part separately provides the driving force needed for the corresponding rotor wing rotation.By the way that the redundancy structure of multiple driving parts is arranged in aircraft rotor, does not influence the normal use of aircraft in single driving part failure, improve the reliability and safety of aircraft.
Description
Technical field
The present invention relates to aircraft fields, and in particular to a kind of aircraft device structure with multiple driving parts.
Background technology
In recent years, with the continuous development of vehicle technology, the aircraft such as unmanned plane Aerial photography, aeroplane photography,
The mapping of quality looks, forest fire protection, seismic survey, nuclear radiation detection, border patrol, emergency disaster relief, Crop Estimation, agricultural land information
Monitoring, pipeline, ultra-high-tension power transmission line inspection, the conservation of wildlife, scientific experiment, maritime affairs scouting, movement pattern of fish monitoring, environmental monitoring,
Air sampling, increase rain, resource exploration, the prohibition of drug, anti-terrorism, police investigation patrol, security monitoring, fire-fighting take photo by plane investigation, communication relay,
Urban planning, digitalized city are built and the extensive use of the multiple fields such as unmanned, is all due to flying instrument
Have that advantage of lower cost, no one was injured risk, survival ability is strong, mobility is good, the advantages such as easy to use so that aircraft
At civilian aspect using wide, aircraft applications distant view is preferable.
But related application at this stage also in not yet formed scale primary stage, vehicle technology also not completely at
It is ripe, there is also certain failure rate, when aircraft breaks down in flight course, it may fall, gently then damage aircraft
It causes any property loss, it is heavy then may fall and cause casualties because of aircraft, therefore, how to improve the reliability of aircraft
The problem of with safety being present urgent need to resolve.
Invention content
The technical problem to be solved by the present invention is to for the not high problem of above-mentioned vehicle reliability and safety, it is proposed that
A kind of aircraft device improves the security reliability of aircraft using the Redundancy Design of multiple driving parts.
In order to solve the above-mentioned technical problem, one embodiment of the invention provides a kind of aircraft device, including：Aircraft sheet
Body；At least one rotor being connect with the aircraft body is configured to drive the movement of the aircraft body by rotating；
The drive module being set on each rotor is configured to provide for the driving force needed for the corresponding rotor wing rotation；It is described
Drive module includes multiple driving parts, and each driving part separately provides described needed for the corresponding rotor wing rotation
Driving force.
In one embodiment, the multiple driving part includes with the combination of Types Below any one or more of：One
Multiwinding machine；One multiple stators motor；Multiple motors.
In a further embodiment, the multiple driving part includes with the group of Types Below any one or more of
It closes：One double-winding motor；One Double-stator motor；Two motors.
In one embodiment, the multiple driving part is arranged in parallel, and one in the multiple driving part individually carries
For the driving force needed for the corresponding rotor wing rotation；Or at least two common offers in the multiple driving part
The driving force needed for the corresponding rotor wing rotation.
In one embodiment, described device further comprises：Energy module is configured to provide for the multiple driving part institute
The energy needed.
In one embodiment, the energy module includes at least one energy unit, and each energy unit independently carries
For the energy needed at least one of the multiple driving part.
In a further embodiment, the energy module includes two energy units.
In one embodiment, described two energy units are arranged in parallel, and one in described two energy units
It is a that at least one required energy in the multiple driving part is provided separately；Or described two energy units are total
With at least one required energy in the multiple driving part of offer.
In one embodiment, the energy cell block includes any one of following energy source type：Chemical cell；Photocell；
Fuel cell；Super capacitor.
In one embodiment, described device includes multiple rotors, and the multiple rotor is uniformly arranged on described
In the circumferential direction of aircraft body.
Beneficial effects of the present invention are：It is multiple by being arranged in aircraft rotor using the aircraft device of the present invention
The redundancy structure of driving part does not influence the normal use of aircraft in single driving part failure, improves aircraft
Reliability and safety.
Description of the drawings
Fig. 1 show the structural schematic diagram of the aircraft device of one embodiment of the invention offer.
Fig. 2 show the aircraft device structural schematic diagram of another embodiment of the present invention offer.
Fig. 3 show the aircraft device structural schematic diagram of another embodiment of the present invention offer.
Fig. 4 show the aircraft device structural schematic diagram of another embodiment of the present invention offer.
Fig. 5 show the aircraft device structural schematic diagram of another embodiment of the present invention offer.
Specific implementation mode
The invention discloses a kind of aircraft device, those skilled in the art can use for reference present disclosure, be suitably modified work
Skill parameter is realized.It is important to note that all similar substitutions and modifications are aobvious and easy for a person skilled in the art
See, they are considered as being included in the present invention, and related personnel can obviously not depart from the content of present invention, spirit and scope
On the basis of content described herein is modified or is suitably changed and combined, to realize and apply the technology of the present invention.
In the present invention, unless otherwise stated, Science and Technology noun used herein has art technology
The normally understood meaning of personnel institute.
In order to make those skilled in the art more fully understand technical scheme of the present invention, with reference to specific embodiment pair
The present invention is described in further detail.
Fig. 1 show the structural schematic diagram of the aircraft device of one embodiment of the invention offer.As shown in Figure 1, this implementation
The aircraft device that is there is provided of example includes：Aircraft body 1, rotor 2, rotor 2 are connect with aircraft body 1, the quantity of rotor 2
It is at least one, is configured to drive the movement of aircraft body 1 by rotation.It should be appreciated that the packet that the present embodiment attached drawing provides
The aircraft device structural schematic diagram for including six rotors is only exemplary, and the embodiment of the present invention does not limit the quantity of rotor
It is fixed.
Fig. 2 show the aircraft device structural schematic diagram of another embodiment of the present invention offer.As shown in Fig. 2, each rotation
One drive module 3 is set on the wing 2, is configured to provide for corresponding rotor 2 and rotates required driving force, drive module 3 includes more
A driving part 4, each driving part 4 separately provide corresponding rotor 2 and rotate required driving force.
By on each rotor be arranged include multiple driving parts drive module, each driving part can be independent
Driving force needed for corresponding rotor wing rotation is provided, can also jointly be provided needed for corresponding rotor wing rotation by multiple driving parts
Driving force.When one or more of multiple driving parts (at least one is normal) break down, remaining normal drive
Dynamic component can provide the driving force needed for corresponding rotor wing rotation, be arranged by the driving part of redundancy, improve each rotation
The reliability of the wing, while also improving the safety of aircraft.
In one embodiment, drive module 3 can also include control module 5, and control module 5 is connect with driving part 4, structure
It makes driving part 4 in order to control corresponding rotor 2 is provided and rotate required driving force；Control module 5 may include a controller,
The controller is connect with each driving part 4.Control module 5 can also include multiple controllers, be communicated between multiple controllers
Connection；The quantity of multiple controllers can be corresponding with the quantity of driving part 4, and a driving part 4 is controlled by each controller；
The quantity of multiple controllers can also be not corresponding with the quantity of driving part 4, simultaneously by the segment controller in multiple controllers
Control multiple driving parts 4.A controller, the controller and all rotors on aircraft can also be only arranged in control module 5
Corresponding drive module 3 is electrically connected, and the corresponding drive module of all rotors is controlled by the controller.
It should be appreciated that the embodiment of the present invention can choose the quantity of different controllers according to different application scenarios,
As long as selected controller can control drive module to provide the driving force needed for aircraft rotor, the present invention for
The quantity of controller does not limit.
In one embodiment, multiple driving parts may include with the combination of Types Below any one or more of：More than one
Winding electric machine；One multiple stators motor；Multiple motors.Preferably, multiple driving parts may include with any one of Types Below
Or a variety of combination：One double-winding motor；One Double-stator motor；Two motors.
Multiple driving parts may include any one of multiple motors, multiple stators motor, multiwinding machine or a variety of
Combination, by multiple motors either the redundancy structure of multiple stators motor or multiwinding machine be arranged, driving mould can be improved
The reliability of block and safety.
It should be appreciated that the embodiment of the present invention can choose different driving parts according to different application scenarios, as long as
Selected driving part can realize redundancy structure design to improve the reliability of drive module, and the present invention is for driving
The type of component does not limit.
In one embodiment, multiple driving parts are arranged in parallel, and one in multiple driving parts is provided separately corresponding
Rotor 2 rotates required driving force；Or at least two in multiple driving parts are provided jointly needed for corresponding rotor 2 rotates
Driving force.
, can be when the driving force needed for rotor 2 to be little according to the demand of rotor 2, a driving part is provided separately pair
The rotor 2 answered rotates required driving force, can also be when the driving force needed for rotor 2 is larger, in multiple driving parts extremely
Few two provide corresponding rotor 2 and rotate required driving force jointly.
It should be appreciated that the embodiment of the present invention can choose the current driving for providing driving force according to different application scenarios
Component, as long as the selected current driving part for providing driving force disclosure satisfy that the demand of rotor wing rotation, the present invention couple
It is not limited in the quantity and object of the driving part for currently providing driving force.
In one embodiment, device can further comprise：Energy module is configured to provide for the energy needed for driving part.
Energy module can individually set for that with storage energy and can export the energy of its storage so that drive module uses in energy module
Energy monitoring module is set, energy monitoring module can also be set in control module 5, the energy residual for monitoring energy module
Amount, and prompted less than preset value alarm in energy thus, further increase safety.
In one embodiment, energy module may include that at least one energy unit, each energy unit separately provide multiple
Energy needed for one or more in driving part.Energy module may include one or more energy units, Mei Geneng
Amount unit can separately provide the energy needed for one or more in multiple driving parts.
Fig. 3 show the aircraft device structural schematic diagram of another embodiment of the present invention offer.Such as
Shown in Fig. 3, energy module 6 may include an energy unit 7, all rotors 2 of energy unit 7 and aircraft device
Corresponding drive module 3 is electrically connected, and is configured to provide for the energy needed for all drive modules 3.
Fig. 4 show the aircraft device structural schematic diagram of another embodiment of the present invention offer.As shown in figure 4, energy mould
Block 6 may include multiple energy units 7, and the quantity of energy unit 7 is corresponding with the quantity of drive module 3, and each energy unit 7 is independent
Energy needed for one drive module 3 is provided.
Fig. 5 show the aircraft device structural schematic diagram of another embodiment of the present invention offer.As shown in figure 5, energy mould
Block 6 may include multiple energy units 7, at least partly electrical connection in corresponding with 2 wings of all rotations drive module of energy unit 73,
Be configured to each energy unit 7 provide in 2 corresponding drive module 3 of all rotors at least partly needed for energy.Energy unit 7
Quantity can be corresponding with the quantity of drive module 3, can also be not corresponding with the quantity of driving part.Pass through the superfluous of energy module
Remaining design can improve the course continuation mileage of aircraft device.
It should be appreciated that Fig. 3 at least illustratively gives several enforceable sides of the present invention to embodiment shown in fig. 5
Case, the embodiment of the present invention includes but be not limited to above-mentioned several schemes.
In a further embodiment, energy module 6 may include two energy units 7.It should be appreciated that the embodiment of the present invention
The quantity of energy unit can be chosen according to different application scenarios, as long as the quantity of selected energy unit disclosure satisfy that
The demand of drive module, the present invention do not limit the quantity of energy unit.
In one embodiment, two energy units 7 are arranged in parallel, and driving is provided separately in one in two energy units 7
Energy needed for component 4；Or two energy units 7 provide the energy needed for driving part 4 jointly.
, can be when the energy needed for driving part 4 to be little according to the demand of driving part 4, an energy unit 7 is independent
Energy needed for driving part 4 is provided, can also be when the energy needed for driving part 4 to be larger, two energy units 7 carry jointly
For the energy needed for driving part 4.
In one embodiment, energy unit 7 may include any one of following energy source type：Chemical cell；Photocell；Combustion
Expect battery；Super capacitor.Energy unit 7 can be super capacitor, lithium battery, fuel cell, solar cell, nickel-cadmium cell,
Ni-MH battery, lead-acid battery, flying wheel battery, biobattery, graphene battery, solid state battery etc..On energy module 6 may include
State the combination of one or more of multiple battery.
It should be appreciated that the embodiment of the present invention can choose the energy of different energy units according to different application scenarios
Type and quantity, as long as the energy source type of selected energy unit and quantity disclosure satisfy that the demand of driving part, this
Invention does not limit the energy source type and quantity of energy unit.
In one embodiment, device may include that multiple rotors 2, multiple rotors 2 are uniformly arranged on the week of aircraft body 1
Upwards.According to actual demand, aircraft device may include multiple rotors 2, it is generally the case that and the quantity of rotor 2 is even number,
It is symmetrically disposed in the circumferential direction of aircraft body 1；However the quantity of rotor 2 may be odd number, as long as being uniformly arranged on winged
It is also ensured that the normal flight of aircraft in the circumferential direction of row device ontology 1.
It should be appreciated that the embodiment of the present invention can choose different rotor quantity according to different application scenarios, as long as
The quantity of selected rotor can realize that the normal flight of aircraft, the present invention do not limit the quantity of rotor.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
It is considered as protection scope of the present invention.
Claims (10)
1. a kind of aircraft device, which is characterized in that including：
Aircraft body；
At least one rotor being connect with the aircraft body is configured to drive the shifting of the aircraft body by rotating
It is dynamic；And
The drive module being set on each rotor is configured to provide for the driving force needed for the corresponding rotor wing rotation；
The drive module includes multiple driving parts, and each driving part separately provides the corresponding rotor wing rotation institute
The driving force needed.
2. the apparatus according to claim 1, which is characterized in that the multiple driving part includes with any in Types Below
Kind or a variety of combinations：One multiwinding machine；One multiple stators motor；Multiple motors.
3. the apparatus of claim 2, which is characterized in that the multiple driving part includes with any in Types Below
Kind or a variety of combinations：One double-winding motor；One Double-stator motor；Two motors.
4. the apparatus of claim 2, which is characterized in that the multiple driving part is arranged in parallel, the multiple drive
One in dynamic component is provided separately the driving force needed for the corresponding rotor wing rotation；Or
At least two in the multiple driving part provide the driving force needed for the corresponding rotor wing rotation jointly.
5. the apparatus according to claim 1, which is characterized in that described device further comprises：
Energy module is configured to provide for the energy needed for the multiple driving part.
6. device according to claim 5, which is characterized in that the energy module includes at least one energy unit, often
A energy unit separately provides the energy needed at least one of the multiple driving part.
7. device according to claim 6, which is characterized in that the energy module includes two energy units.
8. device according to claim 7, which is characterized in that described two energy units are arranged in parallel, and described two
One in a energy unit energy being provided separately needed at least one of the multiple driving part；Or
Described two energy units provide the energy needed at least one of the multiple driving part jointly.
9. device according to claim 6, which is characterized in that the unit module includes any in following energy source type
Kind：Chemical cell；Photocell；Fuel cell；Super capacitor.
10. the apparatus according to claim 1, which is characterized in that described device includes multiple rotors, the multiple institute
Rotor is stated to be uniformly arranged in the circumferential direction of the aircraft body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810597523.7A CN108674645A (en) | 2018-06-11 | 2018-06-11 | A kind of aircraft device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810597523.7A CN108674645A (en) | 2018-06-11 | 2018-06-11 | A kind of aircraft device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108674645A true CN108674645A (en) | 2018-10-19 |
Family
ID=63810623
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810597523.7A Pending CN108674645A (en) | 2018-06-11 | 2018-06-11 | A kind of aircraft device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108674645A (en) |
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