CN104290904A - Multi-rotor type aircraft - Google Patents
Multi-rotor type aircraft Download PDFInfo
- Publication number
- CN104290904A CN104290904A CN201410534786.5A CN201410534786A CN104290904A CN 104290904 A CN104290904 A CN 104290904A CN 201410534786 A CN201410534786 A CN 201410534786A CN 104290904 A CN104290904 A CN 104290904A
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- China
- Prior art keywords
- main
- motor
- mair motor
- screw
- rotor aerocraft
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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.)
- Pending
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- 230000009471 action Effects 0.000 abstract description 4
- 238000012423 maintenance Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 8
- 230000008569 process Effects 0.000 description 5
- 230000008859 change Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 241000208340 Araliaceae Species 0.000 description 2
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 2
- 235000003140 Panax quinquefolius Nutrition 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 235000008434 ginseng Nutrition 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
- B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/24—Coaxial rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
- Wind Motors (AREA)
Abstract
The invention discloses a multi-rotor type aircraft. The multi-rotor type aircraft comprises a bracket and a main motor which is mounted on the bracket, wherein the main motor comprises a first main motor and a second main motor which are coaxially arranged; the first main motor and the second main motor are respectively connected with first main screw propellers and second main screw propellers; at least three secondary screw propellers surround around each main motor and are mounted on the bracket. According to the multi-rotor type aircraft, large screw propellers are driven by main motors which are used as engines, so that the lifting efficiency is high; the main motors are coaxially arranged; the two pairs of main screw propellers rotate in reverse directions, so that the large torque is offset; the main motors are arranged in the center of an aircraft body, so that the vibration influence is minimized; the gestures and actions of the aircraft body are controlled by the secondary motors, so that the power consumption is reduced; if the aircraft accidently crashes in the takeoff and landing stages, the secondary motors and small screw propellers at the periphery are firstly damaged, so that the main motors and the main screw propellers in the center of the aircraft body are protected, and thus the maintenance cost and difficulty are greatly reduced.
Description
Technical field
The application belongs to aerial photography aircraft field, particularly relates to a kind of multi-rotor aerocraft.
Background technology
Unmanned vehicle has that volume is little, lightweight, expense is low, flexible operation and the high feature of safety, can be widely used in taking photo by plane, monitor, search and rescue, the field such as resource exploration.
In prior art, unmanned vehicle generally comprises multiple rotor, and each rotor is driven by a motor respectively, and its shortcoming is:
1, owing to being provided with multiple motor, fuselage central authorities even circumferential layout in the horizontal direction pressed by motor, makes unmanned vehicle entirety heavier;
2, multiple motor works together, and its high-frequency vibration produced easily has an impact to visibility of taking photo by plane;
3, existing Multi-axis aircraft adopts many motor direct-drive screw propeller separately, and in order to keep balance in aircraft flight, flight control system needs to change motor speed continually.This frequent change rotating speed can cause motor to accelerate power consumption.And each motor has work efficiency, number of motors is more, and complete machine work efficiency can be lower.
4, the multi-motor driving aircraft of existing type is difficult to accomplish large scale, because motor is larger, vibration during work is larger.And the increase of single motor cost causes complete machine cost unprecedented soaring.
In view of this, be necessary to provide a kind of novel unmanned vehicle.
Summary of the invention
The object of the present invention is to provide a kind of multi-rotor aerocraft, to overcome deficiency of the prior art.
For achieving the above object, the invention provides following technical scheme:
The embodiment of the present application discloses a kind of multi-rotor aerocraft, comprise support and be installed on the mair motor on described support, described mair motor comprises the first mair motor and second mair motor of coaxial setting, described first mair motor is connected with the first main screw and the second main screw respectively with the second mair motor, the surrounding of described mair motor is arranged with at least three secondary screw propellers, and described secondary screw propeller is installed on described support.
Preferably, in above-mentioned multi-rotor aerocraft, described each secondary screw propeller is respectively by an independently auxiliary-motor driving.
Preferably, in above-mentioned multi-rotor aerocraft, described first main screw and the second main screw are arranged at the both sides up and down of described support respectively.
Preferably, in above-mentioned multi-rotor aerocraft, described first main screw and the second main screw are all arranged at the top of described support or are all arranged at the below of described support.
Preferably, in above-mentioned multi-rotor aerocraft, the output sleeve of described first mair motor is located at the outside of described second main motor output shaft, and output shaft and described first main screw of described first mair motor are fixed, and output shaft and described second main screw of described second mair motor are fixed.
Preferably, in above-mentioned multi-rotor aerocraft, the pole that described support comprises a bearing and is installed on described bearing, described each secondary screw propeller is installed on the end of pole described in respectively, and described mair motor is installed on described bearing.
Preferably, in above-mentioned multi-rotor aerocraft, the quantity of described secondary screw propeller is even number, and described secondary screw propeller is symmetrically distributed in the surrounding of described bearing.
Preferably, in above-mentioned multi-rotor aerocraft, the quantity of described secondary screw propeller is 4, and these 4 secondary screw propellers equidistantly distribute the surrounding of described bearing.
Preferably, in above-mentioned multi-rotor aerocraft, described first main screw and the second main screw have three blades respectively.
Compared with prior art, the invention has the advantages that:
1, mair motor (driving engine) drives king bolt oar, and lift efficiency is high;
2, mair motor is coaxially arranged, and two width main screws rotate round about, offsets high pulling torque;
3, mair motor is arranged in fuselage central authorities, makes vibration effect minimum;
4, auxiliary-motor controlling machine figure state and action, power consumption reduces;
5, in the take-off and landing stage, the crash if aircraft meets accident, first damageable is auxiliary-motor in periphery and minor spiral oar, can be protected, maintenance cost and difficulty are reduced greatly at the mair motor of fuselage central authorities and main screw.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present application or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, the accompanying drawing that the following describes is only some embodiments recorded in the application, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Figure 1 shows that the schematic perspective view of multi-rotor aerocraft in first embodiment of the invention;
Figure 2 shows that the exploded perspective view of multi-rotor aerocraft in first embodiment of the invention;
Figure 3 shows that the schematic perspective view of multi-rotor aerocraft in second embodiment of the invention.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, be described in detail the technical scheme in the embodiment of the present invention, obviously, described embodiment is only the present invention's part embodiment, instead of whole embodiments.Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under the prerequisite not making creative work, all belongs to the scope of protection of the invention.
Shown in ginseng Fig. 1 and Fig. 2, multi-rotor aerocraft comprises support 10, four secondary screw propellers 40 of the mair motor 20 be installed on described support 10, the main screw 30 driven by described mair motor 20 and distribution mair motor 20 surrounding.
Support 10 comprises a bearing 11, the surrounding of bearing 11 be symmetrically distributed with four poles, 12, four secondary screw propellers 40 respectively by one independently auxiliary-motor 41 be installed on the end of four poles 12.Four secondary screw propellers 40 are respectively by independently auxiliary-motor driving, and therefore the rotating speed of each secondary screw propeller 40 can independently control.Each auxiliary-motor 41 is detachably installed on the end of pole 12 respectively by a mount pad 42.
Four secondary screw propellers 40 are preferably equally distributed in the surrounding of bearing 11, that is adjacent two poles 12 are vertical.In other embodiments, adjacent two poles 12 also can out of plumb.
The output sleeve of the first mair motor 21 and the second mair motor 22, first mair motor 21 that mair motor 20 comprises superposition setting is located at the outside of the output shaft of the second mair motor 22.Mair motor 20 is fixed on the top of bearing 11.
Main screw 30 comprises the second main screw 32 and the first main screw 31 setting up and down, and wherein, the output shaft of the first main screw 31 and the first mair motor 21 is fixed, and the output shaft of the second main screw 32 and the second mair motor 22 is fixed.The blade of the first main screw 31 and the second main screw 32 is preferably provided with 3, it should be noted that, the volume cost invention of each main screw blade does not limit, and such as also can be 2.
In the present embodiment, four secondary screw propellers 40 can also be driven by same motor, being undertaken driving by same motor to keep each secondary screw propeller 40 to have identical rotating speed, and it can be applied to indoor etc. does not have wind can affect its stability and the environment not needing to carry out translation or rotation.
In the present embodiment, the first main screw and the second main screw can also be arranged at the below of bearing simultaneously.
In the present embodiment, symmetrically arranged two poles 12 can also be integrated an oval bar of setting, and this round bar is arranged in the middle part of described bearing 11.
In the present embodiment, the quantity of secondary screw propeller 40 can also be set to more than 3 or 4, when being set to 3, these 3 secondary screw propellers are mainly used in realizing aircraft balance and stability, this aircraft is mainly used in vertical lift and does not need the application of translation, if need to rotate, can be realized by the rotating speed or pitch changing secondary screw propeller 40.The quantity of secondary screw propeller 40 is preferably even number, and it is symmetrically distributed in the surrounding of mair motor 30, can by changing the rotating speed of the secondary screw propeller 40 of symmetric position to realize translation or rotation.
Below the principle of work of multi-rotor aerocraft in the present embodiment is described:
The hand of rotation of two main screws is contrary, and the hand of rotation of the secondary screw propeller of 4 is that the screw propeller hand of rotation on diagonal line is identical, and two adjacent screw propeller hand of rotation are contrary.
Make way for the lift that large scale screw propeller that the mair motor (sustainer, main engine) in the middle of complete machine drives two width to rotate in opposite direction produces complete machine weight 70-90%, adopt 4 auxiliary-motors to drive 4 secondary minor spiral oars to produce the remaining part lift of complete machine weight removing main screw lift and to control attitude and the action of complete machine simultaneously.
The advantage of this scheme is that the main screw size that mair motor (sustainer, main engine) drives is large, and lift efficiency is high.And being different from conventional scheme, conventional scheme increases motor size, because motor is that this structure causes motor larger, vibrates larger under state of flight by the arrangement of fuselage center periphery.The large scale motor of the present embodiment is arranged in fuselage central authorities, makes heavy motor reduce to minimum to the vibration effect that complete machine produces.The high pulling torque effect that two main screws rotated round about produce after also counteracting and adopting single king bolt oar.And 4 auxiliary-motors drive minor spiral oar, the arrangement of 4 auxiliary-motors is identical with conventional scheme, arranges along fuselage center periphery.
Auxiliary-motor then primary responsibility controls attitude and the action of complete machine, and its mode of operation is described as follows:
In lifting process, four secondary screw propellers are in order to control the balance and stability of aircraft;
In rotation process, change the relative rotation speed of diagonal positions two secondary screw propellers;
During parallel motion, wherein two the secondary propeller speed being in diagonal positions increase, and the rotating speed of two other secondary screw propeller reduces.
Shown in ginseng Fig. 3, in a second embodiment, the first main screw and the second main screw can also be arranged at the both sides up and down of support respectively.
It should be noted that, in this article, the such as relational terms of first and second grades and so on is only used for an entity or operation to separate with another entity or operational zone, and not necessarily requires or imply the relation that there is any this reality between these entities or operation or sequentially.And, term " comprises ", " comprising " or its any other variant are intended to contain comprising of nonexcludability, thus make to comprise the process of a series of key element, method, article or equipment and not only comprise those key elements, but also comprise other key elements clearly do not listed, or also comprise by the intrinsic key element of this process, method, article or equipment.When not more restrictions, the key element limited by statement " comprising ... ", and be not precluded within process, method, article or the equipment comprising described key element and also there is other identical element.
The above is only the detailed description of the invention of the application; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the application's principle; can also make some improvements and modifications, these improvements and modifications also should be considered as the protection domain of the application.
Claims (9)
1. a multi-rotor aerocraft, it is characterized in that, comprise support and be installed on the mair motor on described support, described mair motor comprises the first mair motor and second mair motor of coaxial setting, described first mair motor is connected with the first main screw and the second main screw respectively with the second mair motor, the surrounding of described mair motor is arranged with at least three secondary screw propellers, and described secondary screw propeller is installed on described support.
2. multi-rotor aerocraft according to claim 1, is characterized in that: described each secondary screw propeller is respectively by an independently auxiliary-motor driving.
3. multi-rotor aerocraft according to claim 1, is characterized in that: described first main screw and the second main screw are arranged at the both sides up and down of described support respectively.
4. multi-rotor aerocraft according to claim 1, is characterized in that: described first main screw and the second main screw are all arranged at the top of described support or are all arranged at the below of described support.
5. multi-rotor aerocraft according to claim 4, it is characterized in that: the output sleeve of described first mair motor is located at the outside of described second main motor output shaft, output shaft and described first main screw of described first mair motor are fixed, and output shaft and described second main screw of described second mair motor are fixed.
6. multi-rotor aerocraft according to claim 1, it is characterized in that: the pole that described support comprises a bearing and is installed on described bearing, described each secondary screw propeller is installed on the end of pole described in respectively, and described mair motor is installed on described bearing.
7. multi-rotor aerocraft according to claim 6, is characterized in that: the quantity of described secondary screw propeller is even number, and described secondary screw propeller is symmetrically distributed in the surrounding of described bearing.
8. multi-rotor aerocraft according to claim 7, is characterized in that: the quantity of described secondary screw propeller is 4, and these 4 secondary screw propellers equidistantly distribute the surrounding of described bearing.
9. multi-rotor aerocraft according to claim 1, is characterized in that: described first main screw and the second main screw have three blades respectively.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410534786.5A CN104290904A (en) | 2014-10-11 | 2014-10-11 | Multi-rotor type aircraft |
| PCT/CN2014/094293 WO2016054863A1 (en) | 2014-10-11 | 2014-12-19 | Multi-rotor air vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410534786.5A CN104290904A (en) | 2014-10-11 | 2014-10-11 | Multi-rotor type aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104290904A true CN104290904A (en) | 2015-01-21 |
Family
ID=52310909
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410534786.5A Pending CN104290904A (en) | 2014-10-11 | 2014-10-11 | Multi-rotor type aircraft |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN104290904A (en) |
| WO (1) | WO2016054863A1 (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691754A (en) * | 2015-03-12 | 2015-06-10 | 江苏艾锐泰克无人飞行器科技有限公司 | Motor mounting seat and multi-rotor unmanned aerial vehicle |
| CN105253300A (en) * | 2015-11-08 | 2016-01-20 | 北京航空航天大学 | Minitype co-shaft double-rotor wing unmanned aerial vehicle based on oscillation damping rotor wing |
| WO2017106013A1 (en) * | 2015-12-18 | 2017-06-22 | Amazon Technologies, Inc. | Selecting propellers for performance and noise shaping |
| CN107010215A (en) * | 2017-05-31 | 2017-08-04 | 锐合防务技术（北京）有限公司 | Aircraft |
| US9745050B2 (en) | 2015-12-18 | 2017-08-29 | Amazon Technologies, Inc. | Selecting propellers for performance and noise shaping |
| US10232931B2 (en) | 2015-12-18 | 2019-03-19 | Amazon Technologies, Inc. | Selecting propellers for performance and noise shaping |
| CN111319756A (en) * | 2018-12-14 | 2020-06-23 | 常东来 | Public rotating oar |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108357674B (en) * | 2018-04-17 | 2023-11-17 | 山东农业大学 | Multi-rotor unmanned aerial vehicle with tilting propeller, inner large propeller, outer small propeller and multiple rotors |
| CN114619815B (en) * | 2022-01-21 | 2024-06-14 | 南京航空航天大学 | Efficient water-air amphibious unmanned aerial vehicle and control method thereof |
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| GB0905027D0 (en) * | 2009-03-24 | 2009-05-06 | Allen Technology Ltd | Flying apparatus |
| CN203005746U (en) * | 2012-12-20 | 2013-06-19 | 北京航空航天大学 | Composite type multi-rotor aircraft |
| CN103318406A (en) * | 2013-06-27 | 2013-09-25 | 长源动力（北京）科技有限公司 | Composite rotor craft |
| CN103387052B (en) * | 2013-07-23 | 2016-01-06 | 中国科学院长春光学精密机械与物理研究所 | Eight-rotary wing aircraft |
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2014
- 2014-10-11 CN CN201410534786.5A patent/CN104290904A/en active Pending
- 2014-12-19 WO PCT/CN2014/094293 patent/WO2016054863A1/en active Application Filing
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| US20100108801A1 (en) * | 2008-08-22 | 2010-05-06 | Orville Olm | Dual rotor helicopter with tilted rotational axes |
| DE102009033821A1 (en) * | 2009-07-18 | 2011-01-20 | Burkhard Wiggerich | Aircraft i.e. flight drone, has support arm structure coupled with hull such that support arm structure is movable relative to hull for condition and/or position regulation of aircraft, where hull is stabilized in perpendicular position |
| CN202011472U (en) * | 2011-02-28 | 2011-10-19 | 南昌航空大学 | Tilting duct unmanned aerial vehicle |
| CN203439258U (en) * | 2013-06-27 | 2014-02-19 | 长源动力（北京）科技有限公司 | Combined type rotor-wing aircraft |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104691754A (en) * | 2015-03-12 | 2015-06-10 | 江苏艾锐泰克无人飞行器科技有限公司 | Motor mounting seat and multi-rotor unmanned aerial vehicle |
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| WO2017106013A1 (en) * | 2015-12-18 | 2017-06-22 | Amazon Technologies, Inc. | Selecting propellers for performance and noise shaping |
| US9745050B2 (en) | 2015-12-18 | 2017-08-29 | Amazon Technologies, Inc. | Selecting propellers for performance and noise shaping |
| US9902490B2 (en) | 2015-12-18 | 2018-02-27 | Amazon Technologies, Inc. | Intentionally imbalancing propellers for performance and noise-shaping |
| US10214279B2 (en) | 2015-12-18 | 2019-02-26 | Amazon Technologies, Inc. | Operating aerial vehicles with intentionally imbalanced propellers |
| US10232931B2 (en) | 2015-12-18 | 2019-03-19 | Amazon Technologies, Inc. | Selecting propellers for performance and noise shaping |
| CN107010215A (en) * | 2017-05-31 | 2017-08-04 | 锐合防务技术（北京）有限公司 | Aircraft |
| CN107010215B (en) * | 2017-05-31 | 2023-06-23 | 瑞电恩吉能源技术(深圳)有限公司 | Aircraft with a plurality of aircraft body |
| CN111319756A (en) * | 2018-12-14 | 2020-06-23 | 常东来 | Public rotating oar |
| CN111319756B (en) * | 2018-12-14 | 2022-06-10 | 常东来 | Public rotating oar |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2016054863A1 (en) | 2016-04-14 |
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Application publication date: 20150121 |