CN108045565A - A kind of single shaft aircraft - Google Patents
A kind of single shaft aircraft Download PDFInfo
- Publication number
- CN108045565A CN108045565A CN201810033985.6A CN201810033985A CN108045565A CN 108045565 A CN108045565 A CN 108045565A CN 201810033985 A CN201810033985 A CN 201810033985A CN 108045565 A CN108045565 A CN 108045565A
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- CN
- China
- Prior art keywords
- steering engine
- pair
- aircraft
- blade
- mission module
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/006—Safety devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/06—Helicopters with single rotor
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The present invention relates to vehicle technology fields, and in particular to a kind of single shaft aircraft；Purpose is to provide a kind of uniaxial aircraft more stablized with safety.A kind of single shaft aircraft, including mission module, motor, propeller, a pair of of blade, the lower blade of a pair, the upper steering engine of a pair, it is a pair of under steering engine, fender bracket；The mission module is divided into two sections, and top is hemisphere face, and lower part is the rounding conical surface, and the rounding conical surface is upper coarse and lower fine, their tangent transition connections；The present invention is compared with the advantages of prior art：The mission module of the present invention is designed as streamlined, is conducive to reduce pneumatic consume and fuselage rocks, improve the stability and security of aircraft；It is easily controllable using upper and lower blade, while eliminate empennage propeller and coaxial counter rotating propeller, make compact-sized, be conducive to lightweight.
Description
Technical field：
The present invention relates to vehicle technology fields, and in particular to a kind of single shaft aircraft.
Background technology：
Aircraft is roughly divided into fixed-wing and two major class of rotor by type of drive.Fixed Wing AirVehicle is by fixed wing
The pressure differential that the air velocity difference of downside is formed generates lift, its main feature is that flying speed is fast, is suitble to navigate by water over long distances at a high speed.
And rotor craft generates lift by the propeller rotated, compared with Fixed Wing AirVehicle, have low cruise, spot hover,
Vertical landing, can narrow space perform task the advantages that.But the common fault of rotor craft is flying radius and flying speed
Well below Fixed Wing AirVehicle.Therefore, it is necessary to a kind of more efficient rotor crafts.
The content of the invention：
The present invention provides a kind of uniaxial single-blade aircraft, makes up uniaxial aircraft at present and is difficult to control, flying speed is low, flies
The defects of row radius is small.The present invention uses following technical proposals：
A kind of single shaft aircraft, including mission module 10, motor 3, propeller 2, a pair of of blade 5, the lower blade 8 of a pair, one
To upper steering engine 6, the lower steering engine 9 of a pair, fender bracket 1；The mission module is divided into two sections, and top is hemisphere face, and lower part is the rounding conical surface,
The rounding conical surface is upper coarse and lower fine, their tangent transition connections；Mission module top center sets motor, the output terminal connection of motor
Propeller；The fender bracket is quadrangle, and lower short center is fixedly connected with the center of mission module bottom surface；Institute
State the upper steering engine of outer conical surface top fixed setting of mission module, the lower steering engine of lower part fixed setting；Described each blade one end with
Upper steering engine output terminal connection, the other end are flexibly connected with fender bracket side；Described each lower blade one end and lower steering engine output terminal
Connection, the other end are flexibly connected with fender bracket side.
Preferably, the fender bracket is inverted trapezoidal, wide at the top and narrow at the bottom；It is the pair of as further preferred scheme
The vertical installation position of upper steering engine is located at the position of centre of gravity of entire aircraft；As still more preferably scheme, further include：It is located at
Flying vehicles control device, electron speed regulator and battery in mission module.
The present invention is compared with the advantages of prior art：
(1) due to adjusting flight attitude using upper and lower blade, easily controllable, flying speed carries significantly with flying radius
It is high.
(2) compared with traditional uniaxial aircraft, present invention eliminates empennage propeller mechanisms and coaxial reverse double-helix paddle
Mechanism, it is simple in structure, the dimension and weight of aircraft is reduced, is conducive to minimize, be miniaturized.
(3) mission module of the invention is designed as streamlined, and inverted cone surface combines under specially upper spherical surface, on the one hand, streamlined
Configuration design is conducive to reduce the air drag during aircraft flight, is conducive to reduce the pneumatic loss of itself, is conducive to
Reduce rocking for flow perturbation generation, be conducive to improve the stability of aircraft entirety.On the other hand, the curved surface of mission module shape
Design occurs without larger pyramid corner angle, can reduce destructiveness when aircraft occurs unexpected.The third aspect, lower bottom part are
Plane is conducive to steadily rise sheer from ground during aircraft initial take-off, and reduction artificially helps the unexpected injury occurred.
(4) this invention takes single fender bracket, space of the aircraft during transport, storage can be efficiently reduced and accounted for
With.
(5) blade and lower blade are that both ends are fixed in the present invention, are installed compared to cantilevered blade, on the one hand
The rigidity of blade, lower blade is improved, it can be achieved that the light-weight design of the two；On the other hand by blade, lower blade by
Power has been distributed to the side of fender bracket, has been transferred to mission module bottom surface again by side, is equivalent to and increases blade, inferior lobe
Piece improves the efficiency for adjusting flight attitude compared with the arm of force of propeller center position.
(6) in embodiment, the structure of inverted trapezoidal fender bracket in the case where propeller length is identical, on the one hand reduces
The length of fender bracket outer perimeter, so as to alleviating the weight of fender bracket；On the other hand, inverted trapezoidal can make fender bracket in itself
Position of centre of gravity moves up, and reduces the distance between propeller and whole center of gravity, and then improves the stability and security of aircraft.
(7) in embodiment, the vertical installation position of steering engine and the entire same height of aircraft center of gravity vertical direction in a pair
Degree, and then when making aircraft horizontal flight, the power of the horizontal direction that blade is subject to are conducive to heighten aircraft steady by center of gravity
It is qualitative, convenient for control.
Description of the drawings：
Fig. 1 shows a kind of assembling schematic diagram of uniaxial aircraft in the embodiment of the present invention；In figure, 1 represents fender bracket, and 2
Propeller is represented, 3 represent motor, and 4 represent blade fixed frame, and 5 represent blade, and 6 represent upper steering engine, and 7, which represent lower blade, consolidates
Determine frame, 8 represent lower blade, and 9 represent lower steering engine, and 10 represent mission module.
Fig. 2 is the exploded perspective view of Fig. 1.
Fig. 3 is blade, the schematic diagram of lower blade in Fig. 1.
Fig. 4 is the A-A directional profile figures of Fig. 3.
Fig. 5 is the mission module schematic diagram in Fig. 1.
Specific embodiment：
Embodiment：
Compares figure 1-5, illustrates the specific technical solution of the present invention.
A kind of single shaft aircraft, including mission module 10, motor 3, propeller 2, a pair of of blade 5, the lower blade 8 of a pair, one
To upper steering engine 6, the lower steering engine 9 of a pair, fender bracket 1, a pair of of blade fixed frame 4 on fender bracket side, positioned at fender bracket
Blade fixed frame 7 and flying vehicles control device, electron speed regulator and battery in mission module under a pair on side；
The mission module is divided into two sections, and top is hemisphere face, and lower part is the rounding conical surface, and spherical surface and conical surface junction are tangent, the rounding conical surface
It is upper coarse and lower fine；The fender bracket is inverted trapezoidal, wide at the top and narrow at the bottom；Mission module top center sets motor, the output terminal of motor
Connect propeller；The fender bracket is quadrangle, and company is fixed in lower short center and the center of mission module bottom surface
It connects；The upper steering engine of outer conical surface top fixed setting of the mission module, the lower steering engine of lower part fixed setting；The pair of upper steering engine
Vertical installation position is located at the position of centre of gravity of entire aircraft；Described each blade one end is connected with upper steering engine output terminal, separately
One end is flexibly connected with fender bracket side；Described each lower blade one end is connected with lower steering engine output terminal, the other end and fender bracket
Side is flexibly connected.
Propeller is twayblade, by the regulation and control to its rotating speed, changes the size of vertical lift, realizes the lifting of aircraft
Function.Blade cross section is streamlined, can reduce windage loss, and the deflection angle of blade is regulated and controled by upper steering engine, is made
Blade is subject to a normal force in propeller flow field, and then gives the power of one horizontal direction of aircraft, realizes the water of aircraft
Square to position move.Lower leaf cross-section is streamlined, can reduce windage loss, regulates and controls the inclined of lower blade by lower steering engine
The direction of corner and size, make aircraft generate a corresponding size and direction around shaft torque, overcome aircraft from
Rotation, and can realize aircraft rotation control.
Flying vehicles control device mainly is flown to control by intelligence, electron speed regulator, three axis inertia measurement sensors, and gyroscope adds
The compositions such as speedometer, fluxmeter, GPS, communication module and control circuit, main function are to automatically keep the normal of aircraft to fly
Row posture；The major function of electron speed regulator is that suitable voltage is conveyed to motor according to the signal of receiver, controls motor
Rotating speed, so as to the flight attitude of change of flight device, position etc.；Battery is powered for whole system.
Claims (4)
1. a kind of single shaft aircraft, which is characterized in that including mission module (10), motor (3), propeller (2), a pair of of blade
(5), a pair of lower blade (8), the upper steering engine (6) of a pair, a pair of steering engine (9) down, fender bracket (1)；The mission module is divided into two sections, on
Portion is hemisphere face, and lower part is the rounding conical surface, and the rounding conical surface is upper coarse and lower fine, their tangent transition connections；Mission module top center position
Install motor, the output terminal connection propeller of motor；The fender bracket is quadrangle, lower short center and mission module
The center of bottom surface is fixedly connected；The upper steering engine of outer conical surface top fixed setting of the mission module, lower part fixed setting
Lower steering engine；Described each blade one end is connected with upper steering engine output terminal, and the other end is flexibly connected with fender bracket side；It is described every
A lower blade one end is connected with lower steering engine output terminal, and the other end is flexibly connected with fender bracket side.
2. a kind of uniaxial aircraft according to claim 1, which is characterized in that the fender bracket is inverted trapezoidal, wide at the top and narrow at the bottom.
A kind of 3. uniaxial aircraft according to claim 2, which is characterized in that the vertical installation position of the pair of upper steering engine
Positioned at the position of centre of gravity of entire aircraft.
4. a kind of single shaft aircraft according to claim 1-3 any one, which is characterized in that further include：Positioned at mission module
Interior flying vehicles control device, electron speed regulator and battery.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810033985.6A CN108045565A (en) | 2018-01-15 | 2018-01-15 | A kind of single shaft aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810033985.6A CN108045565A (en) | 2018-01-15 | 2018-01-15 | A kind of single shaft aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108045565A true CN108045565A (en) | 2018-05-18 |
Family
ID=62126553
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810033985.6A Pending CN108045565A (en) | 2018-01-15 | 2018-01-15 | A kind of single shaft aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108045565A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5289994A (en) * | 1989-10-10 | 1994-03-01 | Juan Del Campo Aguilera | Equipment carrying remote controlled aircraft |
| US20060011777A1 (en) * | 2004-04-14 | 2006-01-19 | Arlton Paul E | Rotary wing vehicle |
| JP2010052713A (en) * | 2009-03-05 | 2010-03-11 | Technical Research & Development Institute Ministry Of Defence | Globular aircraft and tail sitter machine |
| CN204563606U (en) * | 2015-04-08 | 2015-08-19 | 杜文龙 | Single shaft aircraft |
| CN106005392A (en) * | 2016-06-29 | 2016-10-12 | 汇星海科技（天津）有限公司 | Spherical aerial vehicle |
| CN205916329U (en) * | 2016-05-25 | 2017-02-01 | 王硕堃 | Coaxial double -oar unmanned vehicles |
| CN106828908A (en) * | 2017-01-24 | 2017-06-13 | 北京电子工程总体研究所 | A kind of electronic single shaft shrouded propeller aircraft |
| CN106965923A (en) * | 2017-04-01 | 2017-07-21 | 苏州科伊嘉航空科技有限公司 | Driven helicopter |
| CN207748013U (en) * | 2018-01-15 | 2018-08-21 | 天津大学 | A kind of single shaft aircraft |
-
2018
- 2018-01-15 CN CN201810033985.6A patent/CN108045565A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5289994A (en) * | 1989-10-10 | 1994-03-01 | Juan Del Campo Aguilera | Equipment carrying remote controlled aircraft |
| US20060011777A1 (en) * | 2004-04-14 | 2006-01-19 | Arlton Paul E | Rotary wing vehicle |
| JP2010052713A (en) * | 2009-03-05 | 2010-03-11 | Technical Research & Development Institute Ministry Of Defence | Globular aircraft and tail sitter machine |
| CN204563606U (en) * | 2015-04-08 | 2015-08-19 | 杜文龙 | Single shaft aircraft |
| CN205916329U (en) * | 2016-05-25 | 2017-02-01 | 王硕堃 | Coaxial double -oar unmanned vehicles |
| CN106005392A (en) * | 2016-06-29 | 2016-10-12 | 汇星海科技（天津）有限公司 | Spherical aerial vehicle |
| CN106828908A (en) * | 2017-01-24 | 2017-06-13 | 北京电子工程总体研究所 | A kind of electronic single shaft shrouded propeller aircraft |
| CN106965923A (en) * | 2017-04-01 | 2017-07-21 | 苏州科伊嘉航空科技有限公司 | Driven helicopter |
| CN207748013U (en) * | 2018-01-15 | 2018-08-21 | 天津大学 | A kind of single shaft aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 蒋海超等: "某型舵机输出轴径向摆动分析与设计改进", 《教练机》 * |
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| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180518 |
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| WD01 | Invention patent application deemed withdrawn after publication |