CN207748013U - A kind of single shaft aircraft - Google Patents
A kind of single shaft aircraft Download PDFInfo
- Publication number
- CN207748013U CN207748013U CN201820057646.7U CN201820057646U CN207748013U CN 207748013 U CN207748013 U CN 207748013U CN 201820057646 U CN201820057646 U CN 201820057646U CN 207748013 U CN207748013 U CN 207748013U
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- China
- Prior art keywords
- steering engine
- aircraft
- pair
- blade
- mission module
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Abstract
The utility model is related 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 utility model compared with the existing technology the advantages of be：The mission module of the utility model is designed as streamlined, is conducive to reduce pneumatic consume and fuselage shakes, improve stability and the safety of aircraft；It is easily controllable using upper and lower blade, while eliminating empennage propeller and coaxial counter rotating propeller, make compact-sized, is conducive to lightweight.
Description
Technical field：
The utility model is related to vehicle technology fields, and in particular to a kind of single shaft aircraft.
Background technology：
Aircraft is roughly divided into fixed-wing and rotor two major classes by type of drive.Fixed Wing AirVehicle is on fixed wing
The pressure difference that the air velocity difference of downside is formed generates lift, its main feature is that flying speed is fast, high speed is suitble to navigate by water over long distances.
And rotor craft generates lift by the propeller rotated, relative to Fixed Wing AirVehicle, have low cruise, spot hover,
Vertical landing, can be the advantages that narrow space executes task.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.
Invention content：
The utility model provides a kind of uniaxial single-blade aircraft, makes up uniaxial aircraft at present and is difficult to control, flying speed
It is low, the small defect of flying radius.The utility model 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；Motor, the output end connection of motor is arranged in mission module top center
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 end connection, the other end are flexibly connected with fender bracket side；Described each lower blade one end and lower steering engine output end
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 utility model compared with the existing technology the advantages of be：
(1) due to adjusting flight attitude using upper and lower blade, easily controllable, flying speed carries significantly with flying radius
It is high.
(2) relative to traditional uniaxial aircraft, the utility model eliminates empennage propeller mechanism and twin screw machine
Structure, it is simple in structure, the dimension and weight of aircraft is reduced, miniaturization, micromation are conducive to.
(3) mission module of the utility model is designed as streamlined, and inverted cone surface combines under specially upper spherical surface, on the one hand, stream
Line style configuration design is conducive to reduce the air drag during aircraft flight, is conducive to the pneumatic loss for reducing itself, has
Conducive to the shaking that flow perturbation generates is reduced, be conducive to the stability for improving aircraft entirety.On the other hand, mission module shape
Curved design, not larger pyramid corner angle occur, and can reduce destructiveness when aircraft occurs unexpected.The third aspect, bottom
Portion is plane, is conducive to steadily rise sheer from ground when aircraft initial take-off, reduces the unexpected injury for artificially helping to occur.
(4) the utility model takes single fender bracket, can efficiently reduce sky of aircraft during transport, storage
Between occupy.
(5) blade and lower blade are that both ends are fixed in the utility model, are installed compared to cantilevered blade, one
Aspect improve blade, lower blade rigidity, it can be achieved that the two light-weight design；On the other hand by blade, lower blade
Force dispersion arrived the side of fender bracket, be transmitted to mission module bottom surface again by side, be equivalent to increase blade,
The arm of force of the lower blade relative to propeller center position improves the efficiency of adjustment flight attitude.
(6) in embodiment, the structure of inverted trapezoidal fender bracket, it is identical in propeller length, on the one hand reduce
The length of fender bracket outer perimeter, to alleviating the weight of fender bracket；On the other hand, inverted trapezoidal itself can make fender bracket
Center moves up, and reduces the distance between propeller and whole center of gravity, and then improves stability and the safety 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
When spending, and then making aircraft horizontal flight, it is steady to be conducive to height-regulating aircraft by center of gravity for the power for the horizontal direction that blade is subject to
It is qualitative, convenient for control.
Description of the drawings：
Fig. 1 shows a kind of assembling schematic diagram of uniaxial aircraft in the utility model embodiment；In figure, 1 represents protection
Frame, 2 represent propeller, and 3 represent motor, and 4 represent blade fixed frame, and 5 represent blade, and 6 represent upper steering engine, and 7 represent inferior lobe
Piece fixed 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 the schematic diagram of blade, 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 implementation mode：
Embodiment：
Compares figure 1-5 illustrates the specific technical solution of the utility model.
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 the blade fixed frame 4 being located on fender bracket side, positioned at fender bracket
Blade fixed frame 7 under a pair on side, and flying vehicles control device, electron speed regulator and battery in mission module；
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；Motor, the output end of motor is arranged in mission module top center
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 connect with upper steering engine output end, separately
One end is flexibly connected with fender bracket side；Described each lower blade one end is connect with lower steering engine output end, 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 in propeller flow field by a normal force, and then to one horizontal direction of aircraft power, realize 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, to change of flight device flight attitude, 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
Motor is installed, the output end of motor connects propeller；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 connect with upper steering engine output end, and the other end is flexibly connected with fender bracket side；It is described every
A lower blade one end is connect with lower steering engine output end, 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.
3. a kind of 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. according to a kind of single shaft aircraft described in 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 |
|---|---|---|---|
| CN201820057646.7U CN207748013U (en) | 2018-01-15 | 2018-01-15 | A kind of single shaft aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820057646.7U CN207748013U (en) | 2018-01-15 | 2018-01-15 | A kind of single shaft aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207748013U true CN207748013U (en) | 2018-08-21 |
Family
ID=63153066
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820057646.7U Expired - Fee Related CN207748013U (en) | 2018-01-15 | 2018-01-15 | A kind of single shaft aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207748013U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108045565A (en) * | 2018-01-15 | 2018-05-18 | 天津大学 | A kind of single shaft aircraft |
-
2018
- 2018-01-15 CN CN201820057646.7U patent/CN207748013U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108045565A (en) * | 2018-01-15 | 2018-05-18 | 天津大学 | A kind of single shaft aircraft |
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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: 20180821 Termination date: 20190115 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |