CN208393623U - Aircraft - Google Patents
Aircraft Download PDFInfo
- Publication number
- CN208393623U CN208393623U CN201820895727.4U CN201820895727U CN208393623U CN 208393623 U CN208393623 U CN 208393623U CN 201820895727 U CN201820895727 U CN 201820895727U CN 208393623 U CN208393623 U CN 208393623U
- Authority
- CN
- China
- Prior art keywords
- rotation section
- aircraft
- fuselage
- horn
- power
- 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.)
- Active
Links
- 230000007246 mechanism Effects 0.000 claims description 30
- 238000005452 bending Methods 0.000 claims description 15
- 239000000463 material Substances 0.000 description 10
- 230000008859 change Effects 0.000 description 7
- 238000000034 method Methods 0.000 description 5
- 230000008901 benefit Effects 0.000 description 4
- 230000005611 electricity Effects 0.000 description 3
- 230000005684 electric field Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000008450 motivation Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 241000208340 Araliaceae Species 0.000 description 1
- 241000196324 Embryophyta Species 0.000 description 1
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 1
- 235000003140 Panax quinquefolius Nutrition 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
Landscapes
- Toys (AREA)
Abstract
The utility model discloses a kind of aircraft, comprising: fuselage；Multiple horns, multiple horns are arranged along the circumferential direction interval of fuselage, and one end of each horn is connect with fuselage, at least one horn includes the first rotation section, and one end of the first rotation section is rotatably connect with fuselage so that the first rotation section is rotated around center axis thereof；The other end of power device, power device and horn connects, and power device is used to provide flying power for aircraft.Aircraft according to the present utility model by making at least one horn include the first rotation section, and makes one end of the first rotation section and fuselage is rotatably coupled so that the first rotation section is rotated around center axis thereof, the posture of adjustment aircraft that can be more flexible.It can make aircraft during flight in addition combined with power device, guarantee the standard of fuselage of aircraft, advantageously reduce air drag, so that aircraft is flown faster, increase the hang time.
Description
Technical field
The utility model relates to a kind of aircraft.
Background technique
Quadrotor using increasingly extensive, quadrotor has good flexibility, requires landing site
The advantages such as simple, thus quadrotor be widely used in take photo by plane, plant protection, inspection and logistics field.In the related technology,
Speed, height and the change in direction of quadrotor are all the output powers by controlling four motors, for example quadrotor flies forward,
Then increase the output power of two motors next.If quadrotor will turn to, increase or reduce simultaneously cornerwise a pair
The output power of motor.
But the existing control mode of quadrotor is that control to posture is not fine enough, the speed of quadrotor is unable to reach
Quickly.The speed that quadrotor is controlled additionally by the mode of control output power of motor may become four rotations in certain fields
The performance bottleneck of the wing, for example when present quadrotor does movement in a curve in taking photo by plane, the gesture stability of fuselage is just not smart enough
Carefully, the fuselage meeting run-off the straight of quadrotor, also will increase quadrotor cloud in this way when and quadrotor accelerates, slows down and turns to
The control difficulty of platform can also reduce the quality of shooting video if it is taking photo by plane.
Utility model content
The utility model aims to solve at least one of the technical problems existing in the prior art.For this purpose, the utility model mentions
The pose adjustment of a kind of aircraft out, the aircraft is more flexible.
According to the aircraft of the utility model embodiment, comprising: fuselage；Multiple horns, multiple horns are along the machine
The circumferential direction interval of body is arranged, and one end of each horn is connect with the fuselage, and at least one horn includes first
One end of rotation section, first rotation section is rotatably connect with the fuselage so that first rotation section is around central shaft
Line rotation；Power device, the power device are connect with the other end of the horn, and the power device is used to be the flight
Device provides flying power.
According to the aircraft of the utility model embodiment, by making at least one horn include the first rotation section, and make the
One end of one rotation section and fuselage are rotatably coupled so that the first rotation section is rotated around center axis thereof, tune that can be more flexible
The posture of whole aircraft.It can make aircraft during flight in addition combined with power device, guarantee the fuselage water of aircraft
It is flat, air drag is advantageously reduced, so that aircraft is flown faster, increases the hang time.
In some embodiments of the utility model, further includes: the second rotation section, one end of second rotation section and institute
The other end connection of the first rotation section is stated, second rotation section and first rotation section are at an angle to each other, second rotation
Portion can be rotated around center axis thereof, and the other end of second rotation section is connect with the power device.
In some embodiments of the utility model, first rotation section is horizontally extending.
In some embodiments of the utility model, first rotation section and the fuselage are equipped with first rotation
The surface in portion is vertical.
It further include the first driving mechanism in some embodiments of the utility model, first driving mechanism is located at institute
It states in fuselage, first driving mechanism is connect to drive first rotation section around center axis thereof with first rotation section
Rotation.
In some embodiments of the utility model, second rotation section is horizontally extending, and described second turn
Angle between dynamic portion and first rotation section is 90 °.
In some embodiments of the utility model, first is equipped between first rotation section and second rotation section
Bending segment.
It further include the second driving mechanism in some embodiments of the utility model, second driving mechanism is located at institute
It states in the first bending segment, second driving mechanism is connect to drive second rotation section around wherein with second rotation section
The rotation of mandrel line.
It further include motive power section in some embodiments of the utility model, one end of the motive power section and institute
The other end connection of the second rotation section is stated, the other end of the motive power section is connect with the power device.
In some embodiments of the utility model, second is equipped between the motive power section and second rotation section
Bending segment.
In some embodiments of the utility model, the motive power section extends along the vertical direction.
Some embodiments according to the present utility model, the horn are four, the distribution of four horns respectively symmetrically
In the left and right sides of the fuselage.
The additional aspect and advantage of the utility model will be set forth in part in the description, partially will be from following description
In become obvious, or recognized by the practice of the utility model.
Detailed description of the invention
The above-mentioned and/or additional aspect and advantage of the utility model from the description of the embodiment in conjunction with the following figures will
Become obvious and be readily appreciated that, in which:
Fig. 1 is the perspective view according to the aircraft of the utility model embodiment；
Fig. 2 is the posture that wherein aircraft flies forwardly according to the perspective view of the aircraft of the utility model embodiment；
Fig. 3 is according to the perspective view of the aircraft of the utility model embodiment, and wherein aircraft is in the posture flown to the right；
Fig. 4 is according to the perspective view of the aircraft of the utility model embodiment, and wherein aircraft is in the posture turned to.
Appended drawing reference:
Aircraft 100,
Fuselage 1,
Horn 2, the first rotation section 21, the second rotation section 22, motive power section 23, the first bending segment 24, the second bending segment
25,
Power motor 3, propeller 4, power device 5.
Specific embodiment
The embodiments of the present invention are described below in detail, examples of the embodiments are shown in the accompanying drawings, wherein from beginning
Same or similar element or element with the same or similar functions are indicated to same or similar label eventually.Below by ginseng
The embodiment for examining attached drawing description is exemplary, and is only used for explaining the utility model, and should not be understood as to the utility model
Limitation.
In the description of the present invention, it should be understood that term " center ", " longitudinal direction ", " transverse direction ", " length ", " width
Degree ", " thickness ", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside", " suitable
The orientation or positional relationship of the instructions such as hour hands ", " counterclockwise ", " axial direction ", " radial direction ", " circumferential direction " is orientation based on the figure
Or positional relationship, be merely for convenience of describing the present invention and simplifying the description, rather than the device of indication or suggestion meaning or
Element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as the limit to the utility model
System.In addition, defining " first ", the feature of " second " can explicitly or implicitly include one or more of the features.
In the description of the present invention, unless otherwise indicated, the meaning of " plurality " is two or more.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " is pacified
Dress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, be also possible to be electrically connected；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
The concrete meaning of language in the present invention.
Below with reference to Fig. 1-Fig. 4 description according to the aircraft 100 of the utility model embodiment.
As shown in Figure 1, according to the aircraft 100 of the utility model embodiment, including fuselage 1, multiple horns 2 and power dress
Set 5.
Specifically, the roof of fuselage 1 is convex as shown in Figure 1, fuselage 1 is formed generally as the shape of cuboid
Arcwall face.Multiple horns 2 along fuselage 1 circumferential direction interval be arranged, for example, as shown in Figure 1, horn 2 be four, four horns
2 are arranged along the circumferential direction interval of fuselage 1.Certainly, the utility model is without being limited thereto, and fuselage 1 may be formed as other shapes,
Horn 2 can also be three, five, six, seven, eight or more.
As shown in Figure 1, one end of each horn 2 is connect with fuselage 1, and at least one horn 2 includes the first rotation section 21,
One end of first rotation section 21 is rotatably connect with fuselage 1 so that the first rotation section 21 is rotated around center axis thereof, and power fills
It sets 5 to connect with the other end of horn 2, power device 5 is used to provide flying power for aircraft 100.With 21 institute of the first rotation section
Horn 2 connect power device 5 around the first rotation section 21 center axis thereof, power device 5 include 3 He of power motor
Propeller 4, power motor 3 drive propeller 4 to rotate, to provide flying power for aircraft 100, power device 5 is around first
The center axis thereof of rotation section 21, the power direction that power device 5 is supplied to aircraft 100 change, to make to fly
Device 100 has component in the horizontal direction, so as to realize that the direction towards horizontal component of aircraft 100 is flown.
Aircraft 100 without forward, backward, to the left, to the right or turn to etc. operation when, power motor 3 drive spiral
The rotation of paddle 4 is that aircraft 100 provides upward power, and the first rotation section 21 can be rotated, and can make at least one horn 2
Power device 5 rotate therewith, so that 5 aircraft 100 of power device at least one horn 2 is provided the side of power
To the change of generation, to make aircraft 100 that there is component in the horizontal direction, so as to realize the direction of aircraft 100
The direction of horizontal component is flown, such as forward, backward, to the left, to the right or turn to etc..
In addition, the power device 5 at least one horn 2 can be made by adjusting the output power of power motor 3
The component of the power that aircraft 100 provides in vertical direction remains unchanged compared with before adjustment direction, can keep fuselage 1
Level is conducive to survey and draw and take photo by plane.In addition, 1 level of fuselage helps to reduce air drag, increase substantially flight efficiency,
Increase the hang time.
According to the aircraft 100 of the utility model embodiment, by making at least one horn 2 include the first rotation section 21,
And make one end of the first rotation section 21 and fuselage 1 is rotatably coupled so that the first rotation section 21 is rotated around center axis thereof, it can
With the posture of more flexible adjustment aircraft 100.It can make aircraft 100 during flight in addition combined with power device 5,
Guarantee that the fuselage 1 of aircraft 100 is horizontal, advantageously reduce air drag, so that aircraft 100 is flown faster, increase stagnant
The empty time.
Further, as shown in Figure 1, the first rotation section 21 is horizontally extending, from there through making the first rotation section 21
Center axis thereof around the first rotation section 21, convenient for adjusting the power device 5 connecting with the horn 2 where the first rotation section 21
The direction of power is provided for aircraft 100, convenient for the control of aircraft 100.Further, as shown in Figure 1, the first rotation section
21 is vertical equipped with the surface of the first rotation section 21 with fuselage 1.As a result, by making the first rotation section 21 around the first rotation section 21
Center axis thereof is further aircraft convenient for adjusting the power device 5 connecting with the horn 2 where the first rotation section 21
100 provide the direction of power, convenient for the control of aircraft 100.
In addition, the structure of multiple horns 2 can be made identical in order to preferably keep fuselage 1 to balance, it is completely non-rotatable
Horn 2 also can have the first rotation section 21, and the first rotation section 21 on non-rotatable horn 2 cannot turn around center axis thereof
It is dynamic.
For example, in the example depicted in fig. 1, horn 2 is four, and two of them horn 2 is located at the left side of fuselage 1, in addition
Two horns 2 are located at the right side of fuselage 1.Four horns 2 include the first rotation section 21, the first rotation section on each horn 2
21 can rotate around center axis thereof, and hang down positioned at the first rotation section 21 of two horns 2 in left side and the left side wall of fuselage 1
Directly, the first rotation section 21 positioned at two horns 2 on right side is vertical with the right side wall of fuselage 1.Thus it is convenient for the control of aircraft 100
System.
Further, when aircraft 100 needs flight forward, the first rotation section 21 on each horn 2 can be made equal
It is rotated around center axis thereof towards front side, the power direction of the power device 5 on corresponding first rotation section 21 has forward
Horizontal component, so as to so that 100 flight forward of aircraft.In addition, making power by the output power for increasing power motor 3
The component of the power that device 5 provides in the vertical direction remains unchanged, and 1 holding of fuselage can be made horizontal, is conducive to survey and draw and navigate
It claps.In addition, 1 level of fuselage helps to reduce air drag, flight efficiency is increased substantially, increases the hang time.
In some embodiments of the utility model, aircraft 100 further includes the first driving mechanism, and the first driving mechanism can
To be located in fuselage 1, the first driving mechanism is connect to drive the first rotation section 21 to turn around center axis thereof with the first rotation section 21
It is dynamic.Thus convenient for the rotation of the first rotation section 21 of driving.For example, driving mechanism may include driving motor, driving motor can be set
In fuselage 1, it can be toothed around on the internal perisporium of the first rotation section 21, the output shaft of driving motor can be connect with gear,
Gear teeth meshing on 21 internal perisporium of gear and the first rotation section is to drive the first rotation section 21 to rotate.Wherein driving motor can be
Servo motor.Driving motor is connect with the first rotation section 21 may be implemented the rotation of the first rotation section 21 by a relatively large margin, and control
Precision is higher.
In addition, driving mechanism can also be steering engine, steering engine is mainly by shell, circuit board, drive motor, retarder and position
Detecting element is set to be constituted.Its working principle is that issuing signal to steering engine by receiver, driven via the IC on circuit board seedless
Core motor starts turning, and power is reached swing arm through reduction gearing, while sending signal back to by position detector, judged whether
It is positioned through reaching.Drive motor can realize the rotation of the first rotation section 21 with retarder and gear cooperation.
Certain the utility model is without being limited thereto, and the first rotation section 21 can cause deformable material for electrostrictive material or field,
Being powered makes material deformation occurs or make material by electric field or magnetic field deformation occurs, to realize turning for the first rotation section 21
It is dynamic.In addition, the first driving mechanism can also be located in the first rotation section.
In some embodiments of the utility model, as shown in Figure 1, horn 2 further includes the second rotation section 22, the second rotation
The one end in portion 22 is connect, the second rotation section with the other end (first one end of rotation section 21 far from fuselage 1) of the first rotation section 21
22 is at an angle to each other with the first rotation section 21, and the second rotation section 22 can be rotated around center axis thereof, the other end of the second rotation section 22
It is connect with power device 5.Rotatable freedom degree can during aircraft 100 flies there are two tools on horn 2 as a result,
With direction of pull provided by more flexible motivation of adjustment device 5, convenient for aircraft 100 to the left, to the right, forward, backward or
Turn to etc..
Further, as shown in Figure 1, the second rotation section 22 is horizontally extending, and the second rotation section 22 and first turn
Angle between dynamic portion 21 is 90 °.It is possible thereby to further be conveniently adjusted direction of pull provided by power device 5, it is convenient for
Aircraft 100 to the left, to the right, forward, backward or turn to etc..
In addition, the structure of multiple horns 2 can be made identical in order to preferably keep fuselage 1 to balance, it is completely non-rotatable
Horn 2 also can have the second rotation section 22, and the second rotation section 22 on non-rotatable horn 2 cannot turn around center axis thereof
It is dynamic.
For example, in the example depicted in fig. 1, horn 2 is four, and two of them horn 2 is located at the left side of fuselage 1, in addition
Two horns 2 are located at the right side of fuselage 1.Each horn 2 includes the first rotation section 21 and the second rotation section 22, the first rotation section
21 one end is connect with fuselage 1, and the first rotation section 21 is vertical equipped with the surface of the first rotation section 21 with fuselage 1, and first turn
The other end in dynamic portion 21 is connect with one end of the second rotation section 22.First rotation section 21 and the second rotation section 22 are in the horizontal direction
Extend, i.e. the first rotation section 21 and the second rotation section 22 are respectively positioned in horizontal plane and the first rotation section 21 and the second rotation section 22
In in same level.Second rotation section 22 can be rotated around center axis thereof, and power device 5 is located at the another of the second rotation section 22
End, and power device 5 aircraft 100 without forward, backward, to the left, to the right or turn to etc. operation when, power device 5 is
Aircraft 100 provides upward power.
As shown in Fig. 2, the first rotation section 21 on each horn 2 rotates around it axis when 100 flight forward of aircraft
It rotates forward, the second rotation section 22 turns forward, and direction of pull provided by power device 5 is front upper place, while can be increased
The output power of power motor 3 is consistent before vertical stress component and 100 adjustment direction of aircraft provided by power device 5, moves
Horizontal component provided by power device 5 is accelerated forwardly aircraft 100.When 100 flight backward of aircraft, each horn 2
On the first rotation section 21 rotate around it axis and rotate backward, the second rotation section 22 tilts backwards, and draws provided by power device 5
Power direction is back upper place, while can increase the output power of power motor 3, vertical stress component provided by power device 5 and is flown
It is consistent before 100 adjustment direction of row device, horizontal component provided by power device 5 accelerates aircraft 100 backward.
When 100 flight to the right of aircraft, the second rotation section 22 on each horn 2 rotates around it axis and turns right,
Direction of pull provided by power device 5 is upper right side, while can increase the output power of power motor 3,5 institute of power device
It is consistent before the vertical stress component of offer and 100 adjustment direction of aircraft, horizontal component provided by power device 5 to fly
Device 100 accelerates to the right.When 100 flight to the left of aircraft, the second rotation section 22 on each horn 2 rotates around it axis to the left
Rotation, the second rotation section 22 are tilted to the left, and direction of pull provided by power device 5 is upper left side, while can increase power
The output power of motor 3 is consistent before the vertical stress component and 100 adjustment direction of aircraft of power device 5,5 institute of power device
The horizontal component of offer accelerates aircraft 100 to the left.
When aircraft 100 turns to, below by taking aircraft 100 turns to the right as an example, positioned at the of two horns 2 of front side
Two rotation sections 22 turn right around center axis thereof, positioned at rear side two horns 2 the second rotation section 22 around center axis thereof
It turns left, to make the front side of aircraft 100 with horizontal component to the right, the rear side of aircraft 100 is with water to the left
Divide power equally, so as to realize the steering of aircraft 100.
The first bending is equipped in some embodiments of the utility model, between the first rotation section 21 and the second rotation section 22
Section 24.Thus not only convenient for connection between the first rotation section 21 and the second rotation section 22, the first rotation section 21 and the are also convenient for
Two rotation sections 22 are rotated rotating around center axis thereof, consequently facilitating the power direction of adjustment aircraft 100.Certainly, practical at this
In novel, the first rotation section 21 can be fixedly connected with fuselage 1, and the first bending segment 24 and the first rotation section 21 can be rotationally
Connection is with the direction of the provided power of motivation of adjustment device 5.
Further, aircraft 100 further includes the second driving mechanism, and the second driving mechanism is located in the first bending segment 24,
Second driving mechanism is connect to drive the second rotation section 22 to rotate around center axis thereof with the second rotation section 22.Thus convenient for driving
The rotation of second rotation section 22.For example, driving mechanism may include driving motor, driving motor can be located in fuselage 1, second turn
It can be toothed around on the internal perisporium in dynamic portion 22, the output shaft of driving motor can be connect with gear, gear and the second rotation section
Gear teeth meshing on 22 internal perisporiums is to drive the second rotation section 22 to rotate.Wherein driving motor can be servo motor.Driving electricity
Machine is connect with the second rotation section 22 may be implemented the rotation of the second rotation section 22 by a relatively large margin, and it is higher to control precision.
In addition, driving mechanism can also be steering engine, steering engine is mainly by shell, circuit board, drive motor, retarder and position
Detecting element is set to be constituted.Its working principle is that issuing signal to steering engine by receiver, driven via the IC on circuit board seedless
Core motor starts turning, and power is reached swing arm through reduction gearing, while sending signal back to by position detector, judged whether
It is positioned through reaching.Drive motor can realize the rotation of the second rotation section 22 with retarder and gear cooperation.
Certain the utility model is without being limited thereto, and the second rotation section 22 can cause deformable material for electrostrictive material or field,
Being powered makes material deformation occurs or make material by electric field or magnetic field deformation occurs, to realize turning for the second rotation section 22
It is dynamic.In addition, the second driving mechanism can also be located in fuselage or in the second rotation section 22.
In some embodiments of the utility model, as shown in Figure 1, at least one above-mentioned horn 2 further includes motive power
Section 23, one end of motive power section 23 is connect with the other end of the second rotation section 22, the other end and power of motive power section 23
Device 5 connects.It is possible thereby to be spaced apart power device 5 with the second rotation section 22, guarantee that the second rotation section 22 can be smoothly
It is rotated around center axis thereof, power device 5 is avoided to interfere with the second rotation section 22.
Further, as shown in Figure 1, motive power section 23 extends along the vertical direction.Thus motive power section 23 not only may be used
Power device 5 to be spaced apart with the second rotation section 22, power device 5 and the first rotation section 21 and fuselage 1 can also be made to be spaced
It opens, guarantees smoothly rotating around center axis thereof for the first rotation section 21, while can be to avoid the propeller 4 with power device 5
It collides with fuselage 1.
In addition, the structure of multiple horns 2 can be made identical in order to preferably keep fuselage 1 to balance, it is completely non-rotatable
Horn 2 also can have motive power section 23.
In some embodiments of the utility model, as shown in Figure 1, being set between motive power section 23 and the second rotation section 22
There is the second bending segment 25.Thus convenient for the connection between motive power section 23 and the second rotation section 22 and convenient for the second rotation section 22
It is rotated around center axis thereof.
In some embodiments of the utility model, the horn 2 is four, point of four horns 2 respectively symmetrically
Cloth is in the left and right sides of fuselage 1.It is possible thereby to which it is more steady to make aircraft 100 fly.
Below with reference to Fig. 1-Fig. 4 description according to the aircraft 100 of one specific embodiment of the utility model, it is worth understanding
It is that described below is exemplary, it is intended to for explaining the utility model, and should not be understood as the limit to the utility model
System.
As shown in Figure 1, including fuselage 1, horn 2 and power device 5 according to the aircraft 100 of the utility model embodiment.
Specifically, as shown in Figure 1, fuselage 1 is formed generally as the shape of cuboid, the roof of fuselage 1 is the arc of convex
Shape face.Horn 2 is four, and four horns 2 are arranged along the circumferential direction interval of fuselage 1, and two of them horn 2 is located at fuselage 1
Left side and along the longitudinal direction interval setting, other two horn 2 are located at the right side of fuselage 1 and along the longitudinal direction interval setting, position
Two horns 2 in left side and two horns 2 positioned at right side are symmetrical, positioned at two horns 2 of front side and positioned at the two of rear side
A horn 2 is symmetrical.
As shown in Figure 1, each horn 2 includes sequentially connected first rotation section 21, the second rotation section 22 and motive power
Section 23, one end of the first rotation section 21 are rotatably connect with around the center axis thereof of the first rotation section 21 with fuselage 1, and first
Rotation section 21 is horizontally extending, and the surface that fuselage 1 is connect with the first rotation section 21 is vertical with the first rotation section 21, i.e., and first
Rotation section 21 extends in left-right direction.One end of second rotation section 22 is separate by the first bending segment 24 and the first rotation section 21
One end of fuselage 1 connects, and the second rotation section 22 is horizontally extending, and between the second rotation section 22 and the first rotation section 21
Angle is 90 °, i.e. the second rotation section 22 extends along the longitudinal direction, and the second rotation section 22 can be along the central axis of the second rotation section 22
Line rotation.One far from the first rotation section 21 that one end of motive power section 23 passes through the second bending segment 25 and the second rotation section 22
End connection, motive power section 23 upwardly extend along the vertical direction, and power device 5 is located at the upper end of motive power section 23, power dress
Setting 5 includes power motor 3 and propeller 4, and power motor 3 drives propeller 4 to rotate, and provides power for flight.
Aircraft 100 further includes the first driving mechanism and the second driving mechanism, and the first driving mechanism can be located at fuselage 1
Interior, the first driving mechanism is connect to drive the first rotation section 21 to rotate around center axis thereof with the first rotation section 21.Second driving
Mechanism is located in the first bending segment 24, and the second driving mechanism is connect to drive the second rotation section 22 around wherein with the second rotation section 22
The rotation of mandrel line.
Four propellers 4 are added vector controlled by the application respectively, and each propeller 4 can control spiral shell on two dimensions
The direction of paddle 4 is revolved, four propellers 4 can individually control direction, when aircraft 100 needs flight forward, it is only necessary to
The direction of four propellers 4 is turned forward, then adjusting the output power of the power motor 3 connecting with propeller 4 can not
Achieve the purpose that control 100 speed of aircraft with 1 posture of fuselage is changed, only needs to change respectively two pairs of left and right when steering
The direction of propeller 4 can achieve in the case where not changing 1 horizontality of fuselage completely, complete forward-reverse, accelerate
Slow down, the operation such as steering.
In addition, be equipped in fuselage 1 fly control, electricity is adjusted, power device 5 provides flying power, and horn 2 is controlled by winged control, i.e., the
One driving mechanism and the second driving mechanism are controlled by winged control, can be rotated on two dimensions.As shown in Figure 1, first turn
Dynamic portion 21 and the second rotation section 22 can be rotated according to arrow shown in FIG. 1 respectively.It is drawn by adjusting provided by power device 5
The direction of power controls aircraft 100, while flying control and can also pass through the output power that each power motor 3 is made in electricity regulation.
As shown in Fig. 2, the direction of the winged control control horn 2 of aircraft 100 makes it forward when aircraft 100 flies forward
It is tilted into direction.Specifically, the first rotation section 21 of each horn 2, which rotates forward, makes propeller 4 turn forward.Increase simultaneously dynamic
It is consistent before 3 output power of force motor, the vertical stress component of 2 pulling force of horn and the adjustment of 2 direction of horn, the level point of horn 2
Power is accelerated forwardly aircraft 100.The advantage that be that can keep fuselage 1 horizontal always, can take photo by plane field in mapping
There is an outstanding performance, horizontal fuselage 1 helps to reduce air drag, and the direction inclination of marching forward of 4 direction of propeller can make to fly
Efficiency increases substantially, and increases the hang time.
As shown in figure 3, making described in its power device 5 when 100 flight to the right of aircraft again by control horn 2
The direction of pull of offer changes.Specifically, the second rotation section 22 of each horn 2 turn right so that propeller 4 to the right
Inclination, while increasing 3 output power of power motor, one is kept before the vertical stress component of 2 pulling force of horn and the adjustment of 2 direction of horn
It causes, the horizontal component of horn 2 accelerates aircraft 100 to the right.
As shown in figure 4, aircraft 100 controls 2 side of inclination of horn of front and back respectively when aircraft 100 turns to
To so that the direction of pull and subsequent direction of pull of the front of aircraft 100 are not arranged on the same straight line, aircraft 100 is before it
Side and rear side rotate round about respectively.Specifically, the second rotation section 22 on two horns 2 of front side is made to turn right
It is dynamic, so that two propellers 4 positioned at front side be made to be tilted to the right, the second rotation section 22 on two horns 2 of rear side to
Turn left dynamic, so that two propellers 4 positioned at rear side be made to be tilted to the left, and then realizes that aircraft 100 turns to the right.
It is compared according to the aircraft 100 of the utility model embodiment and is turned with traditional quadruple screw propeller 4 by diagonal propeller
Dynamic difference in torque turns to, and this mode adjustment direction is rapider, can be improved 4 aircraft of quadruple screw propeller, 100 flying speed, increases
The scheme for adding 100 flight flexibility and flight stability of aircraft can increase substantially the property of aircraft 100 using this scheme
Energy.
Below with reference to Fig. 1-Fig. 4 description according to the control method of the aircraft 100 of the utility model embodiment, comprising: extremely
Few first rotation section 21 is rotated to control the heading of aircraft 100.The rotation of first rotation section 21, can drive and the
The power device 5 that horn 2 where one rotation section 21 connects rotates, to change the power direction of power device 5, and then realizes
The change of 100 heading of aircraft.
According to the control method of the aircraft 100 of the utility model embodiment, it is easy to implement 100 heading of aircraft
Change, and can guarantee the level of fuselage 1.
In some embodiments of the utility model, when aircraft 100 includes four horns 2, four horns 2 are symmetrically set
In the left and right sides of fuselage 1, each horn 2 includes the first rotation section 21, and the first rotation section 21 is equipped with first turn with fuselage 1
The plane in dynamic portion 21 is vertical, and when the first rotation section 21 is horizontally extending, control method further comprises: working as aircraft
When 100 flight forward, four the first rotation sections 21 rotate so that four power devices 5 turn forward, to provide forward fly
Action edge；When 100 flight backward of aircraft, four the first rotation sections 21 rotate so that four power devices 5 tilt backwards, from
And provide flying power backward.
Further, when each horn 2 further includes the second rotation section 22, one end and the first rotation section of the second rotation section 22
21 other end connection, the second rotation section 22 is vertical with the first rotation section 21, and the second rotation section 22 is horizontally extending, the
Two rotation sections 22 can be rotated around center axis thereof, and when the other end of the second rotation section 21 is connect with power device 5, control method is also
It include: when 100 flight to the left of aircraft, four the second rotation section 22 rotations are so that four power devices 5 are tilted to the left；When winged
When the flight to the right of row device 100, four the second rotation section 22 rotations are so that four power devices 5 are tilted to the right；When aircraft 100 to
When left steering, two the second rotation sections 22 positioned at 1 front side of fuselage are rotated so that two power devices 5 for being located at front side incline to the left
Tiltedly, two the second rotation sections 22 positioned at 1 rear side of fuselage rotate so that two power devices 5 for being located at rear side are tilted to the right；When
When aircraft 100 turns to the right, two the second rotation sections 22 positioned at 1 front side of fuselage are rotated so as to be located at two power of front side
Device 5 is tilted to the right, and two the second rotation sections 22 positioned at 1 rear side of fuselage rotate so as to be located at two power devices 5 of rear side
It is tilted to the left.
In the description of this specification, reference term " one embodiment ", " some embodiments ", " illustrative examples ",
The description of " example ", " specific example " or " some examples " etc. means specific features described in conjunction with this embodiment or example, knot
Structure, material or feature are contained at least one embodiment or example of the utility model.In the present specification, to above-mentioned art
The schematic representation of language may not refer to the same embodiment or example.Moreover, description specific features, structure, material or
Person's feature can be combined in any suitable manner in any one or more of the embodiments or examples.
While there has been shown and described that the embodiments of the present invention, it will be understood by those skilled in the art that:
These embodiments can be carried out with a variety of variations, modification, replacement in the case where not departing from the principles of the present invention and objective
And modification, the scope of the utility model are defined by the claims and their equivalents.
Claims (12)
1. a kind of aircraft characterized by comprising
Fuselage；
Multiple horns, multiple horns are arranged along the circumferential direction interval of the fuselage, one end of each horn and institute
Fuselage connection is stated, at least one horn includes the first rotation section, and one end of first rotation section and the fuselage are rotatable
It connects so that first rotation section is rotated around center axis thereof；
Power device, the power device are connect with the other end of the horn, and the power device is used to be the aircraft
Flying power is provided.
2. aircraft according to claim 1, which is characterized in that further include:
Second rotation section, one end of second rotation section are connect with the other end of first rotation section, second rotation
Portion and first rotation section are at an angle to each other, and second rotation section can be rotated around center axis thereof, second rotation section
The other end is connect with the power device.
3. aircraft according to claim 1, which is characterized in that first rotation section is horizontally extending.
4. aircraft according to claim 3, which is characterized in that first rotation section and the fuselage are equipped with described
The surface of first rotation section is vertical.
5. aircraft according to claim 2, which is characterized in that it further include the first driving mechanism, first driving machine
Structure is located in the fuselage, and first driving mechanism is connect to drive first rotation section around it with first rotation section
Center axis thereof.
6. aircraft according to claim 2, which is characterized in that second rotation section is horizontally extending, and institute
Stating the angle between the second rotation section and first rotation section is 90 °.
7. aircraft according to claim 2, which is characterized in that between first rotation section and second rotation section
Equipped with the first bending segment.
8. aircraft according to claim 7, which is characterized in that it further include the second driving mechanism, second driving machine
Structure is located in first bending segment, and second driving mechanism is connect to drive second rotation with second rotation section
Portion is rotated around center axis thereof.
9. aircraft according to claim 2, which is characterized in that it further include motive power section, the motive power section
One end is connect with the other end of second rotation section, and the other end of the motive power section is connect with the power device.
10. aircraft according to claim 9, which is characterized in that the motive power section and second rotation section it
Between be equipped with the second bending segment.
11. aircraft according to claim 10, which is characterized in that the motive power section extends along the vertical direction.
12. aircraft according to claim 1, which is characterized in that the horn is four, and four horns are right respectively
The left and right sides for being distributed in the fuselage claimed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820895727.4U CN208393623U (en) | 2018-06-08 | 2018-06-08 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820895727.4U CN208393623U (en) | 2018-06-08 | 2018-06-08 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208393623U true CN208393623U (en) | 2019-01-18 |
Family
ID=65135439
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820895727.4U Active CN208393623U (en) | 2018-06-08 | 2018-06-08 | Aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208393623U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110576968A (en) * | 2018-06-08 | 2019-12-17 | 广州极飞科技有限公司 | aircraft and control method of aircraft |
-
2018
- 2018-06-08 CN CN201820895727.4U patent/CN208393623U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110576968A (en) * | 2018-06-08 | 2019-12-17 | 广州极飞科技有限公司 | aircraft and control method of aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2351607B1 (en) | Flying toy | |
| CN108438220B (en) | Multi-degree-of-freedom dragonfly-imitating flapping-wing aircraft and control method thereof | |
| CN106004287B (en) | Amphibious multifunctional vertical landing aircraft | |
| US7798883B2 (en) | Acrobatic rotary-wing toy helicopter | |
| CN108622404A (en) | aircraft and flight system | |
| AU2020101802A4 (en) | Air-jet steering drone | |
| WO2015172559A1 (en) | Control method and control apparatus for multirotor variable-pitch aerial vehicle | |
| CN106143899B (en) | Displacement rotor and the multi-rotor aerocraft including the displacement rotor and its flying method | |
| WO2015172558A1 (en) | Control method and control apparatus for variable-pitch aerial vehicle | |
| CN1318263C (en) | Propellers, propeller stabilizers, and propeller related vehicles | |
| KR102295789B1 (en) | Drone capable of adjusting propulsion direction | |
| CN110254710A (en) | A kind of empty amphibious unmanned plane of mixing wing water of two-stage displacement | |
| CN109878697A (en) | Folding wing and fixed-wing Multi-axis aircraft | |
| WO2016058502A1 (en) | Tail-sitter aircraft | |
| JP2010075568A (en) | Helicopter toy | |
| CN110127037A (en) | A kind of cylindric vertically taking off and landing flyer using foldable single screw and grid fin | |
| CN108528692A (en) | A kind of folded wing double-rotor aerobat and its control method | |
| CN208393623U (en) | Aircraft | |
| CN2915205Y (en) | Aeromodelling | |
| JP6618000B1 (en) | Electronic component and flying object with the electronic component attached | |
| CN110576968A (en) | aircraft and control method of aircraft | |
| CN206243452U (en) | A kind of slow spin oar aircraft | |
| CN206634204U (en) | Machine is maked an inspection tour in a kind of new-type unmanned delivery with gliding function | |
| JPH07148356A (en) | Model rotor craft | |
| CN110626494A (en) | Tandem three-rotor helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 510000 Block C, 115 Gaopu Road, Tianhe District, Guangzhou City, Guangdong Province Patentee after: XAG Co., Ltd. Address before: 510000, Guangdong, Guangzhou, Gaotang Tianhe District Software Park Road, No. 1, 3A01 Patentee before: Guangzhou Xaircraft Technology Co.,Ltd. |