CN105383679A - Multi-rotor aircraft and closed type frame thereof - Google Patents
Multi-rotor aircraft and closed type frame thereof Download PDFInfo
- Publication number
- CN105383679A CN105383679A CN201510833372.7A CN201510833372A CN105383679A CN 105383679 A CN105383679 A CN 105383679A CN 201510833372 A CN201510833372 A CN 201510833372A CN 105383679 A CN105383679 A CN 105383679A
- Authority
- CN
- China
- Prior art keywords
- rotor
- type frame
- closed type
- horn
- strut bar
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/08—Geodetic or other open-frame structures
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- 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
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
According to a variable-pitch aircraft, the lift force of each rotor is controlled by screw pitch; according to a fixed-pitch aircraft, the lift force of each rotor is controlled by the rotating speed of each rotor; the rotating speed of the variable-pitch aircraft is kept unchanged when the screw pitch is changed, but the screw pitch regulation response speed is far larger than the rotating speed regulation response speed, so the load change frequency of each rotor of a variable-pitch multi-rotor aircraft is high and large in amplitude. A closed type frame of a multi-rotor aircraft comprises arms which sequentially pass the installation position of each rotor and form a closed diagram, and also comprises supporting rods which are positioned between the arms. The closed type frame disclosed by the invention can be used for commendably solving the problem of vibration of the frame of the variable-pitch multi-rotor aircraft.
Description
Technical field
The invention belongs to technical field of aerospace, be specifically related to a kind of multi-rotor aerocraft.
Background technology
Compared with traditional fixed pitch multi-rotor aerocraft, adopt the multi-rotor aerocraft of feather principle to have and follow response rapidly, the advantages such as anti-external disturbance ability is strong, make feather multi-rotor aerocraft have better manoevreability, stronger controllability, and higher stability.Compared with the mode that the mode that feather aircraft pitch controls rotor lift and fixed pitch gyroplane rotate speed control rotor lift, because feather aircraft rotating speed when changing pitch remains unchanged, and pitch adjustment speed of response specific speed adjustment far away fast response time, the load variations frequency therefore on feather multi-rotor aerocraft rotor is high and amplitude is large.For four rotors, fixed pitch multi-rotor aerocraft generally adopts " X " type or " ten " font structure frame, but for feather multi-rotor aerocraft, these two kinds of rack constructions but can not be suitable for, the high frequency that reason is load on rotor significantly change can cause horn high vibration, thus impact comprises the stability of the aircraft of flight control system, therefore, feather multi-rotor aerocraft needs a kind of structure that at utmost can reduce frame vibration.
Summary of the invention
The object of this invention is to provide a kind of closed type frame, can frame vibration be effectively reduced.
Technical scheme of the present invention is: a kind of closed type frame of multi-rotor aerocraft, comprises and forms the horn of closed figures through the installation site of each rotor successively, also comprise the strut bar between horn.
For the multi-rotor aerocraft comprising above-mentioned closed type frame, rotor drive motor is installed on upper and lower two pieces and installs between flat board; At least two looped pipeline sandwicheds are placed in two pieces and install between flat board, and every looped pipeline folder comprises pipe clamp and lower tube clip, and horn or strut bar are held between lower tube clip.
Adopt technical scheme of the present invention, the problem of feather multi-rotor aerocraft frame vibration can be solved well.
Accompanying drawing explanation
Fig. 1 is the aircraft schematic diagram that the present invention adopts rectangle closed type frame;
Fig. 2 is the aircraft mounting structure schematic diagram that the present invention adopts rectangle closed type frame;
Fig. 3 is the aircraft rotor assembly structure schematic diagram that the present invention adopts closed type frame;
Fig. 4 is the aircraft schematic diagram that the present invention adopts rhombus closed type frame;
Fig. 5 is aircraft embodiment 1 schematic diagram that the present invention adopts hexagonal close open frame;
Fig. 6 is aircraft embodiment 2 schematic diagram that the present invention adopts hexagonal close open frame;
Fig. 7 is aircraft embodiment 1 schematic diagram that the present invention adopts circular closure open frame;
Fig. 8 is aircraft embodiment 2 schematic diagram that the present invention adopts circular closure open frame;
Fig. 9 is the aircraft schematic diagram that the present invention adopts cydariform closed type frame.
Detailed description of the invention
Below in conjunction with accompanying drawing 1-9, the specific embodiment of the present invention is described.
As Fig. 1, closed type frame frame is made up of a closed frame and the device support bar be fixed in the middle of closed frame, and comprise four rotor assemblies, each rotor assembly is connected with two horns of closed type frame.
As Fig. 2 closed type frame and use the main structure of its aircraft to comprise a pair straight-bar machines arm 1, a pair vertical horn 2 and a pair device support bar 3 and four rotor assemblies 6.Install two caliber adapters 4 in the middle of straight-bar machines arm 1, caliber adapter 4 is three-port structure, is fixed on by device support bar 3 between two horn 1 horizontal strokes, installs four collar component devices erecting frames 5 in the middle part of device support bar 3.
Fig. 3 is the structural representation of rotor assembly, mainly comprises in rotor assembly structure: primarily of the power output system of motor 66, rotor holder 61 and rotor composition; Primarily of the displacement system of steering wheel 67, rocking arm 60, pallet 68, connecting rod 69 and rotor holder 61 composition; The mounting structure that upper pipe clamp 62,63 and lower tube clip 64,65 are connected and fixed as rotor assembly 6 and frame horn.
In rectangle closed type frame aircraft, each rotor assembly 6 is by upper pipe clamp 63, 63 and lower tube clip 64, 65 with straight-bar machines arm 1, vertical horn 2 is fixed, be different from rotor assembly in " X " type or " ten " font frame and be installed on cantilever beam end respectively, load variations on rotor is carried by the material behavior of cantilever beam, and rotor assembly is independent mutually, closed type frame rotor assembly 6 by straight-bar machines arm 1 and vertical horn 2 two ends spacing, load variations on rotor is carried jointly by material and structure, and rotor assembly 6 connection is a rigid body by closed type structure, therefore closed type frame compares " X " type or " ten " font frame has less amount of deflection, stronger shock resistance.
The main structure body of closed type frame is hollow pipe type material, but shape is not limited to column type pipe, and material can be the conventional aeronautical materials such as carbon fiber, aluminum alloy or glass-felt plastic.The boring structure of hollow tubular is used for the wiring such as motor, steering wheel.
Closed type frame and use its aircraft to adopt displacement principle, its specific embodiment is as follows:
Steering wheel 67 is hinged with rocking arm 60, and rocking arm 60 is hinged with connecting rod 69 lower end, and the upper end of connecting rod 69 is connected with pallet 68, rotor holder 61 by hanger and pallet 68 hinged.When carrying out variable pitch contro l, steering wheel 67 rotating band shakes arm 60 and rotates, the precession of rocking arm 60 rotary actuation connecting rod about 69, and the pallet 68 be connected with connecting rod 69, with connecting rod about 69 precession, makes both sides rotor holder 61 differential, changes the angle of attack of rotor, i.e. pitch.
Gyroplane rotate speed and pitch carry out Collaborative Control, to reach better airworthiness.
In various embodiments, there is a lot of derivative type in the aircraft adopting closed type frame, is not limited to close-shaped and four implementations of overlapping rotors of quadrangle.Fig. 4-Fig. 9 discloses the multiple different embodiment of the aircraft adopting closed type frame, and the shape of its closed type structure can be polygon or circle etc., and rotor group quantity is some, and in typical embodiment, rotor group quantity is 4,6,8 etc.Because Flight Vehicle Structure supports primarily of closing structure, device support bar 3 does not bear Flight Vehicle Structure power except carrying flying control equipment or mission payload, therefore its to design less consideration Flight Vehicle Structure stressed, also there is multiple different distortion in an embodiment in device support bar 3, Fig. 4-Fig. 9 discloses the implementation of different device support bars 3, its typical way of realization has: " ten " font device support bar, " work " font device support bar, " X " type device support bar etc.
The above embodiment is only the preferred embodiment of the present invention; not scope of the present invention is limited; under not departing from the present invention and designing the prerequisite of spirit; the various distortion that those of ordinary skill in the art make technical scheme of the present invention and improvement, all should fall in protection domain that claims of the present invention determine.
Claims (10)
1. a closed type frame for multi-rotor aerocraft, is characterized in that, described frame comprises and forms the horn of closed figures through the installation site of each rotor successively, also comprises the strut bar between horn.
2. closed type frame as claimed in claim 1, is characterized in that, the closed figures that described horn is formed is rectangle, and described strut bar is parallel with the limit of rectangle, and the installation site of rotor is on the summit of rectangle.
3. closed type frame as claimed in claim 2, it is characterized in that, described horn comprises a pair straight-bar machines arm, a pair vertical horn, described strut bar is be parallel to each other a pair, and install two caliber adapters in the middle of straight-bar machines arm, caliber adapter is three-port structure, strut bar is fixed between two straight-bar machines arms, in the middle part of strut bar, four collar component devices erecting frames is installed.
4. closed type frame as claimed in claim 1, is characterized in that, the closed figures that described horn is formed is rhombus, and described strut bar is positioned on the diagonal line of rhombus, and the installation site of rotor is on the summit of rhombus.
5. closed type frame as claimed in claim 1, is characterized in that, the closed figures that described horn is formed is hexagon, and the installation site of rotor is on hexagonal summit, and described strut bar to be positioned on hexagonal diagonal line or arranged in parallel.
6. closed type frame as claimed in claim 1, is characterized in that, the closed figures that described horn is formed is circular, and described strut bar forms trident or I-shape.
7. closed type frame as claimed in claim 1, is characterized in that, the closed figures that described horn is formed is cydariform, comprises two straight line horns and two arc horns, between described strut bar is connected on two straight line horns.
8. the closed type frame as described in any one of claim 1-7, is characterized in that, the main structure body of closed type frame adopts hollow tubular material, comprises carbon fiber, aluminum alloy or glass-felt plastic.
9. comprise a multi-rotor aerocraft for any one of claim 1-8 closed type frame, wherein, rotor drive motor is installed on upper and lower two pieces and installs between flat board; At least two looped pipeline sandwicheds are placed in two pieces and install between flat board, and every looped pipeline folder comprises pipe clamp and lower tube clip, and horn is held between lower tube clip.
10. multi-rotor aerocraft as claimed in claim 9, it is characterized in that, feather steering wheel is installed on below described lower installation board; The wiring of aircraft is in the hollow structure of horn and/or strut bar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510833372.7A CN105383679A (en) | 2015-11-26 | 2015-11-26 | Multi-rotor aircraft and closed type frame thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510833372.7A CN105383679A (en) | 2015-11-26 | 2015-11-26 | Multi-rotor aircraft and closed type frame thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105383679A true CN105383679A (en) | 2016-03-09 |
Family
ID=55416583
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510833372.7A Pending CN105383679A (en) | 2015-11-26 | 2015-11-26 | Multi-rotor aircraft and closed type frame thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105383679A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111542476A (en) * | 2017-12-15 | 2020-08-14 | 因诺泰克轻量化工程与聚合物技术有限公司 | Flight module |
| CN113165728A (en) * | 2019-12-03 | 2021-07-23 | 向杰 | Honeycomb array multi-rotor composite part, rack and aircraft |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104044733A (en) * | 2014-06-16 | 2014-09-17 | 吉林大学 | Six-rotor-wing duct aircraft |
| CN204399473U (en) * | 2014-12-12 | 2015-06-17 | 华南农业大学 | A kind of folding many rotor unmanned aircrafts of fast disassembly type |
| CN204606196U (en) * | 2015-05-13 | 2015-09-02 | 成都市优艾维机器人科技有限公司 | A kind of four axle unmanned plane frames |
| CN104925263A (en) * | 2015-06-29 | 2015-09-23 | 田悦丰 | Aircraft with multiple driving devices |
| CN104960665A (en) * | 2015-06-29 | 2015-10-07 | 田悦丰 | Aircraft having multiple flight modes |
| CN104986335A (en) * | 2015-06-24 | 2015-10-21 | 辽宁锐翔通用航空有限公司 | Long-endurance heavy-load oil-drive direct-driven agricultural plant protection unmanned aerial vehicle |
| CN204750552U (en) * | 2015-05-18 | 2015-11-11 | 北京臻迪智能科技有限公司 | Horn support and unmanned vehicles |
-
2015
- 2015-11-26 CN CN201510833372.7A patent/CN105383679A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104044733A (en) * | 2014-06-16 | 2014-09-17 | 吉林大学 | Six-rotor-wing duct aircraft |
| CN204399473U (en) * | 2014-12-12 | 2015-06-17 | 华南农业大学 | A kind of folding many rotor unmanned aircrafts of fast disassembly type |
| CN204606196U (en) * | 2015-05-13 | 2015-09-02 | 成都市优艾维机器人科技有限公司 | A kind of four axle unmanned plane frames |
| CN204750552U (en) * | 2015-05-18 | 2015-11-11 | 北京臻迪智能科技有限公司 | Horn support and unmanned vehicles |
| CN104986335A (en) * | 2015-06-24 | 2015-10-21 | 辽宁锐翔通用航空有限公司 | Long-endurance heavy-load oil-drive direct-driven agricultural plant protection unmanned aerial vehicle |
| CN104925263A (en) * | 2015-06-29 | 2015-09-23 | 田悦丰 | Aircraft with multiple driving devices |
| CN104960665A (en) * | 2015-06-29 | 2015-10-07 | 田悦丰 | Aircraft having multiple flight modes |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111542476A (en) * | 2017-12-15 | 2020-08-14 | 因诺泰克轻量化工程与聚合物技术有限公司 | Flight module |
| CN113165728A (en) * | 2019-12-03 | 2021-07-23 | 向杰 | Honeycomb array multi-rotor composite part, rack and aircraft |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160309 |