CN205916327U - Aircraft - Google Patents
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- CN205916327U CN205916327U CN201620447947.1U CN201620447947U CN205916327U CN 205916327 U CN205916327 U CN 205916327U CN 201620447947 U CN201620447947 U CN 201620447947U CN 205916327 U CN205916327 U CN 205916327U
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- aircraft
- horn
- propeller
- aircraft body
- plane
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- 230000001939 inductive effect Effects 0.000 claims description 12
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 5
- 230000003068 static effect Effects 0.000 claims description 4
- 230000000994 depressogenic effect Effects 0.000 claims description 3
- 230000009194 climbing Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 abstract description 4
- 238000009434 installation Methods 0.000 description 5
- 238000004364 calculation method Methods 0.000 description 2
- 238000005183 dynamical system Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 230000001154 acute effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000037396 body weight Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
- B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/296—Rotors with variable spatial positions relative to the UAV body
- B64U30/297—Tilting rotors
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Aerials (AREA)
- Toys (AREA)
Abstract
The utility model discloses an aircraft, including the aircraft main part, set up in horn subassembly in the aircraft main part and set up in power device on the horn subassembly, power device include the driving piece, and the screw that the driving piece is connected, the surface of revolution of screw is followed the advancing direction of aircraft nose deflect and with the slope of aircraft main part is arranged. When aircraft moved ahead, the aircraft main part was parallel with the horizontal plane, and through being the design of aircraft main part upper surface the cambered surface, the lower surface design is the plane, thereby lost one's temper in the poor power of climbing that produces of upper and lower surperficial generate pressure when flowing through the aircraft main part, did from this the aircraft main part plays the effect of lifting, and to reduce right from this the reliance of screw reduces the load of screw to aircraft can possess longer time of endurance to greatly reduced motor power under the configuration of same battery and driving system in order to reach.
Description
Technical field
This utility model is related to vehicle technology field, especially relates to a kind of aircraft.
Background technology
In recent years, low cost that the multi-rotor aerocraft constantly rising had because of it, easy to operate, there is high degree of flexibility
With can with super low altitude flight the features such as increasingly widely used by all trades and professions, existing most of aircraft are mainly applied
In fields such as scientific research, geographical detection, agricultural pouring and video captures.At present, due to the efficiency of battery and dynamical system etc.
Problem, leads to the aircraft flight time shorter, maintains essentially in the level of 10-30 minute, its main cause is because many rotors
The propeller of aircraft almost assume responsibility for the thru-flight amount of thinking highly of, thus leading to the larger power of aircraft needs, but because
The aircraft body size of aircraft is unsuitable excessive, so limiting battery capacity.Therefore, above-mentioned technical problem is that many rotors fly
Row device one technical bottleneck, is difficult to break through in a short time.
Content of the invention
Based on this, this utility model is to overcome the defect of prior art, provides a kind of reduction propeller load, prolongation to fly
Row device flight time and the simple aircraft of structure.
The purpose of this utility model is achieved in that
A kind of aircraft, including aircraft body, the horn assembly that is arranged in described aircraft body, be arranged at described
Power set on horn assembly, described power set include actuator and the propeller being connected with described actuator, described winged
Row device main body one end is head, and the other end is tail, and described propeller is obliquely installed with respect to described aircraft body.
Below technical scheme is further described:
Further, during described aircraft water placing flat, the surfaces of revolution of described propeller and the inclination angle of horizontal plane are δ,
And δ is more than 0 degree and is less than 90 degree.
Further, during described aircraft water placing flat, the surfaces of revolution of described propeller with the inclination angle δ of horizontal plane is
28.5 degree.
Further, the length of the top surface to described tail for the described head is more than described head to the length of described tail bottom surface
Degree.
Further, the curvature of the top surface of described aircraft body is more than the curvature of bottom surface.
Further, described horn assembly includes the first horn, the second horn, the 3rd horn and the 4th horn, and described
One horn and described second horn are arranged in the left and right sides of the heading of described aircraft body, and described first horn
It is extended along described aircraft direct of travel respectively with described second horn, described 3rd horn and described 4th horn are arranged
On the top surface in the tail direction of described aircraft body, described 3rd horn and described 4th horn prolong in the vertically upward direction
Stretch setting.
Further, described first horn, described second horn, described 3rd horn and described 4th horn all along away from
The symmetrical direction of principal axis of described aircraft stretches out setting.
Further, described aircraft body includes the left drag reduction portion being arranged on the left of described aircraft body and is arranged on
Right drag reduction portion on the right side of described aircraft body, described left drag reduction portion and described right drag reduction portion are equipped with cambered surface.
Further, projection one air dam upwards in the middle part of the top surface of described aircraft body, described air dam is from described machine
Head extends to states tail.
Further, the top surface of described aircraft body is also arranged with air inducing portion, and described air inducing portion is located at described air dam
And described drag reduction portion between, described air inducing portion smooths downwards to extend to smooth upwards to described drag reduction portion from described air dam again and extends
Formed.
Further, it is arranged with recess between described head front end and described first horn, the second horn.
Further, described tail end symmetrical is provided with depressed part.
This utility model also provides a kind of aircraft, and including an aircraft body, described aircraft front end is a head, after
Hold as a tail；
In described aircraft body, described power set are used for driving a propeller one power set；
Described aircraft has two states and is respectively first state and the second state, in first state, described spiral
The surfaces of revolution of oar and horizontal plane have an inclination angle；In the second state, the surfaces of revolution of described propeller and plane-parallel.
Further, in first state, plane and plane-parallel that described aircraft body bottom surface is located.
Further, in the second state, plane and horizontal plane that described aircraft bottom surface is located have an inclination angle.
This utility model also provides a kind of aircraft, and including an aircraft body, described aircraft front end is a head, after
Hold as a tail；
In described aircraft body, described power set are used for driving a propeller one power set；
When the horizontal flight forward of described aircraft or static on the ground when, it is flat that described aircraft body bottom surface is located
Face and described plane-parallel；
When described aircraft vertical flies upwards or hovers in the air, the plane that described aircraft body bottom surface is located
With described horizontal plane, there is an inclination angle.
Further, when the horizontal flight forward of described aircraft or static on the ground when, the rotation of described propeller
Face and horizontal plane have an inclination angle.
Further, when described aircraft vertical flies upwards or hovers in the air, the surfaces of revolution of described propeller
With plane-parallel.
The beneficial effects of the utility model are:
Above-mentioned aircraft passes through the structure of inclined to the surfaces of revolution of described propeller and described aircraft body arrangement, when
During aircraft forward flight, aircraft body and plane-parallel, by the length of the top surface to described tail by described head
Be set greater than described head to the length of described tail bottom surface so that air-flow when aircraft body in upper and lower table
Face produces pressure differential thus producing power of climbing, and thus plays, to described aircraft body, the effect of lifting, thus to reduce aircraft
Dependence to described propeller, thus reducing the load of described propeller, thus substantially reduce motor power consumption to reach same
Battery and arrangements of power system under aircraft can possess longer cruising time.
Brief description
Fig. 1 is the forward traveling schematic diagram of the aircraft described in this utility model embodiment；
Fig. 2 is the structural representation of the aircraft described in this utility model embodiment；
Fig. 3 is the top view of the aircraft described in this utility model embodiment；
Fig. 4 is the side view of the aircraft described in this utility model embodiment；
Fig. 5 is the front view of the aircraft described in this utility model embodiment；
Fig. 6 is the rearview of the aircraft described in this utility model embodiment.
Description of reference numerals:
100th, aircraft body, 120, left drag reduction portion, 130, right drag reduction portion, 140, air dam, 150, air inducing portion, 160, machine
Head, 170, tail, 200, horn assembly, 220, mounting seat, the 230, first horn, the 240, second horn, the 250, the 3rd horn,
260th, the 4th horn, 300, power set, 320, actuator, 322, driving member, 340, propeller, 400, undercarriage.
Specific embodiment
Below embodiment of the present utility model is described in detail:
As shown in Figures 1 to 4, a kind of aircraft, including aircraft body 100, is arranged in described aircraft body 100
Horn assembly 200 and be fixed on power set 300 on described horn assembly 200, described power set 300 include driving
Part 320 and the propeller 340 being connected with described actuator 320, one end of described aircraft body 100 is head 160, another
Hold as tail 170；
Described propeller 340 is in tilted layout with respect to described aircraft body 100, and wherein, described propeller 340 is along described
The direct of travel of head is in tilted layout.
In the described aircraft of this preferred embodiment, the described horn assembly 200 of setting in described aircraft body 100
Including four horns, each horn is mounted on described actuator 320, and is fixed on the spiral on described actuator 320
Oar 340, and by the traveling of the surfaces of revolution of four described propellers 340 and described aircraft body 100 in complete machine structure arrangement
Direction is obliquely arranged, specifically described aircraft body 100 includes head 160, the inclination side of four described propellers 340
The direction yaw tilt of the described head 160 of aircraft body 100 described in Xiang Weichao.
Based on this, the top surface area of described aircraft body 100 makes more than the base area of described aircraft body 100
Described aircraft body 100 substantially becomes arch form structure, and further, described head 160 arrives the length of the top surface of described tail 170
Arrive the length of described tail 170 bottom surface more than described head 160, and the curvature of the top surface of described aircraft body 100 is more than bottom
The curvature in face is so that during aircraft forward flight, air-flow produces pressure differential on upper and lower surface when aircraft body 100
Thus producing power of climbing, thus the effect of lifting being played to described aircraft body 100, thus to reduce to described propeller 340
Dependence, reduce described propeller 340 load, thus substantially reducing motor power consumption to reach in same battery and dynamical system
Under unified central planning put the purpose that lower aircraft can possess longer cruising time.Preferably, the surfaces of revolution of four described propellers 340 is equal
It is parallel to each other.
Projection one air dam 140 upwards in the middle part of the top surface of described aircraft body 100, described air dam 140 is from described machine
160 extend to described tail 170.When aircraft forward flight, aircraft body and plane-parallel, air-flow warp can be made
Cross and produce pressure differential between described air dam 170 and bottom surface during described aircraft body 100, thus producing power of climbing, thus
The load of described propeller 340 can be reduced, allow more power for the normal flight of aircraft, so that flying instrument is standby
Longer cruising time.
In the present embodiment, described horn assembly 200 is provided with mounting seat 220, and described actuator 320 is arranged at described peace
In dress seat 220, described actuator 320 includes driving member 322, and described propeller 340 is connected with described driving member 322.Wherein, institute
State mounting seat 220 corresponding with the quantity of horn, that is, each horn is equipped with a described mounting seat 220, described mounting seat 220 has
Body is installed on the end of horn, and described mounting seat 220 is to be integrally formed with horn so that it to possess enough overall structures strong
Degree.Additionally, described mounting seat 220 is the frame-type structure being provided with installation cavity, this frame-type structure is preferably cylinder, described actuator
320 is motor, this motor is installed on above-mentioned installation intracavity, assembles described propeller 340 afterwards, thus can make the dress of whole machine
Distribution structure is compacter, firm, installs connected mode simple.
In addition, described mounting seat 220 being laid in the end of described horn assembly 200, can effectively reduce motor and producing
Moment, so that the weight of described horn assembly 200 end is down to minimum, effectively mitigate main screw lift, thus when extending flight
Between.Certainly, described mounting seat 220 is needed can also to be arranged at the other positions on described horn assembly 200 according to practical application.
In another embodiment, the both sides up and down of described mounting seat 220 are equipped with installation cavity, install all fixing electricity of intracavity for upper and lower two
Machine, and a propeller is respectively mounted on each motor, it is consequently formed the twin-propeller structure of single mounting seat, so can make to fly
Row device obtains bigger flying power, obtains the longer flight time.
As shown in figure 4, during described aircraft water placing flat, the surfaces of revolution of described propeller 340 and the inclination angle of horizontal plane
For δ, and δ is more than 0 degree less than 90 degree.In actually used, the different size according to aircraft and weights, do not changing battery
Under the power situation of capacity and actuator 320, by reliable Theoretical Calculation and simulation analysis, can be in above-mentioned inclination angle δ model
Enclose the value of actual tilt angles δ of the interior surfaces of revolution selecting suitably described propeller 340 and horizontal plane, so that described propeller
340 auxiliary liftings being provided enough, thus reducing the load burden of described propeller 340, and then can significantly alleviate electricity
Tankage is not enough and the short slab of actuator 320 power limited.Certainly, in other embodiments, the inclination angle of described propeller 340
δ can also be other numerical value, preferably acute angle, also all in protection domain of the present utility model.
Further, the surfaces of revolution of preferably described propeller 340 and the inclination angle δ of horizontal plane are 28.5 in the present embodiment
Degree.Can be drawn by conversion according to the data that Theoretical Calculation and simulation analysis obtain, certain in battery capacity and power of motor
In the case of, when the inclination angle arrangement δ by the surfaces of revolution of described propeller 340 and horizontal plane is 28.5 degree, described propeller 340
The auxiliary lifting highest providing, and then the degree that the Reduction of Students' Study Load to described propeller 340 and minimizing rely on is the most obvious, so that flying
Row device has longer cruising time under identical load condition.
As shown in Fig. 2 described horn assembly 200 includes the first horn 230, the second horn 240, the 3rd horn 250 and
Four horns 260, the height of described 3rd horn 250 and the 4th horn 260 end is higher than described first horn 230 and the second horn
The height of 240 ends, described first horn 230 and described second horn 240 are arranged in the head with described aircraft body 100
The left and right sides in direction, and described first horn 230 and described second horn 240 prolong along described aircraft direct of travel respectively
Stretch setting, the distance that described first horn 230 arrives described air dam 140 is equal to described second horn 240 and arrives described air dam 140
Distance.Described 3rd horn 250 and described 4th horn 260 are arranged at the top in the tail direction of described aircraft body 100
On face, described 3rd horn and described 4th horn are extended respectively in the vertically upward direction, and described 3rd horn 250 arrives institute
The distance stating air dam 140 is equal to the distance that described 4th horn 260 arrives described air dam 140.By above-mentioned arrangement not
Moreover it is possible to make housing construction compacter on the premise of only meeting load-carrying requirement, take less space, lift aircraft simultaneously
Flying quality.
Refer to Fig. 5, Fig. 6, in another embodiment, described first horn 230, the second horn 240, the 3rd horn
250 and the 4th the cross sectional dimensions of horn 260 and described aircraft body 100 junction be more than and be connected with described mounting seat 220
The cross sectional dimensions at place, further, described first horn 230, described second horn 240, described 3rd horn 250 and described
The sectional dimension of the 4th horn 260 is equal to the direction of described mounting seat 200 with the junction of described aircraft body 100 by horn
In the trend being gradually reduced, so not only can guarantee that horn is big with the connection area of the junction of described aircraft body 100,
Thus possessing higher bonding strength, the overall weight of horn can also being reduced simultaneously, thus mitigating main screw lift, reducing spiral
The load of oar, extends the flight time.Described first horn 230 rear end is provided with a fixed part and is connected with described aircraft body 100,
Extend forward a cantilever from described fixed part, the thickness of described fixed part is more than the thickness of described cantilever.
Additionally, described first horn 230 and described second horn 240 are preferably outer surface for even in another embodiment
The cylinder of continuous curved surface, can also use up windage when reducing flight to greatest extent on the premise of ensureing higher bonding strength；Institute
State the 3rd horn 250 identical with both described 4th horns 260 structure, described 3rd horn has a windward side and is located at left and right
The one side of both sides, the width of described side is more than the width of described windward side, and the area of described side is more than described windward side
Area so that described 3rd horn be in triangle tabular.Form obtuse angle between described windward side and horizontal plane, thus can reduce
3rd horn 250 described in during flight and described 4th horn 260 and the contact area of wind, thus reducing windage further, improve
The endurance of aircraft.It is further preferred that being also associated between described 3rd horn 250 and described 4th horn 260 reinforcing
Bar, this reinforcing bar can integrally formed or assembling get on, so can improve described 3rd horn further
250 and the structural strength of described 4th horn 260, it is to avoid fracture because stress is excessive, the service life of impact aircraft.
Refer to Fig. 3, Fig. 6, described first horn 230, described second horn 240, described 3rd horn 250 and described
The direction of the axis of symmetry away from described aircraft for the equal edge of four horn 260 stretches out setting.Particularly, by described first horn
230 and described second horn 240 stretch out extension along the left and right side of head.Described 3rd horn 250 and described 4th horn
260 stretch vertically upward and are in tilted layout to the direction away from described aircraft body 100, simultaneously along tail left and right side to
Outer extension is expanded, thus not only can make propeller on adjacent described first horn 230 and described second horn 240,
Propeller on described 3rd horn 250 and described 4th horn 260 has enough and safe rotation space, it is to avoid horn away from
Close to excessively, collide interference, affects service life；The arrangement that four described propellers 340 simultaneously can also be made more balances,
The weight sharing described aircraft body 100 more equalizes, so that the skyborne flight of aircraft is more steady, flight attitude
More stable.
Further, described aircraft body 100 includes being arranged on the left drag reduction portion in described aircraft body 100 left side
120 and be arranged on right drag reduction portion 130 on the right side of described aircraft body, described left drag reduction portion 120 and described right drag reduction portion 130 are equal
It is provided with cambered surface.In the present embodiment, described left drag reduction portion 120 and described right drag reduction portion 130 are respectively described aircraft body 100
Left side wall and right side wall, this cambered surface is the surface configuration of left side wall and right side wall, and this cambered surface is along described aircraft body 100
Top surface to bottom surface direction be extended, that is, left side wall and right side wall are approximately cylinder, thus can reduce aloft fly
The crosswind resistance of the left and right both direction of row device, reducing lateral wind during aircraft moves ahead makes the navigation route of aircraft produce partially
From impact, reduce propeller load, thus extending the flight time.
As shown in figure 3, in a preferred embodiment, projection one upwards in the middle part of the top surface of described aircraft body 100
Air dam 140, described air dam 140 extends to described tail 170 from described head 160, further, along described head
160 first smooth upwards to described tail 170 from described head 160 and extend from the direction of described tail 170, described air dam 140
Smooth from described head 160 to described tail 170 again and extend downwardly.Described air dam 140 and the axis of symmetry weight of described aircraft
Close, and it is that the strip that the direction along described head 160 to described tail 170 is disposed to extend is raised, described air dam 140
Top surface has the cambered surface of one fixed width, thus plays good guide functions in aircraft flight.Additionally, described aircraft master
Inside body 100, there is cavity, for installing control board, battery etc., this cavity can be by the lid closing of coupling.This is led
The part protuberance certain altitude that wind portion 140 is located at described head 160, and the air dam 140 described in direction towards described tail 170
Height be in the trend gradually successively decreased, further, the thickness of described head is more than the thickness of described tail.This structure not only may be used
Aircraft body is made to possess as far as possible big installation on the basis of meeting excellent flying quality with described aircraft body 100 empty
Chamber, accommodates various devices or part in order to install, including battery component and chip assembly, described aircraft body top surface is provided with
Cover on one, described upper lid has open mode and closure state with respect to described aircraft body.Described air dam 140 can simultaneously
So that aircraft has more preferable aerodynamic performance, more preferably, cruising time is longer for flying quality.Additionally, described aircraft
The bottom of main body 100 is provided with undercarriage.Described aircraft body 100 undercarriage described in the installation settings of bottom it can be ensured that
Safer, steady during aircraft landing ground.
Additionally, the top surface of described aircraft body 100 is also arranged with air inducing portion 150, described air inducing portion 150 is located at described leading
Between wind portion 140 and described left drag reduction portion 120, described right drag reduction portion 130, described air inducing portion 150 be from described air dam 140 to
Lower smooth extension smooths upwards to extend to described left drag reduction portion 120 and/or described right drag reduction portion 130 again and is formed.In the present embodiment
In preferably two described air inducing portions 150 are set in the both sides of described air dam 140, the transition of this air inducing portion 150 connects described wind-guiding
Portion 140 and left and right side wall, not only can reduce the thickness of aircraft body, to reduce weight it is ensured that excellent duration performance,
Windage windward can be reduced, air lifting effect more preferably can reduce the load of described propeller 340, carry further simultaneously
High cruising time.In addition, being arranged with recessed between described first horn 230, described second horn 240 and described head 160
Portion, and the surface of this recess is set to cambered surface, thus can reduce aircraft body weight, reduces windage during flight.Described
Tail 170 end symmetrical is provided with depressed part, thus can reduce aircraft body 100 weight further.
In the present embodiment, described aircraft has two states and is respectively first state and the second state, and first state is
It is the state when the horizontal flight forward of described aircraft or when being still on bottom surface, in first state, described propeller 340
The surfaces of revolution and horizontal plane there is described inclination angle δ, the plane that described aircraft body 100 bottom surface is located is put down with described horizontal plane
OK；The surfaces of revolution of described propeller 340 and the inclination angle δ of horizontal plane are more than 0 degree less than 90 degree it is preferable that described propeller 340
The inclination angle δ of the surfaces of revolution and horizontal plane be 28.5 degree.The surfaces of revolution of described propeller 340 and horizontal plane, thus produce
One component overcoming described aircraft self gravitation, reduces the load of described propeller 340, improves hours underway, Yi Jiyi
The component of individual horizontal direction, the component direction of horizontal direction is the direct of travel of described aircraft.Second state is when described
State when aircraft vertical flies upwards or hovers in the air, in the second state, the surfaces of revolution of described propeller 340 with
Plane-parallel, the plane that described aircraft bottom surface is located and horizontal plane have described inclination angle δ.
Each technical characteristic of embodiment described above can arbitrarily be combined, for making description succinct, not to above-mentioned reality
The all possible combination of each technical characteristic applied in example is all described, as long as however, the combination of these technical characteristics is not deposited
In contradiction, all it is considered to be the scope of this specification record.
Embodiment described above only have expressed several embodiments of the present utility model, and its description is more concrete and detailed,
But therefore can not be interpreted as the restriction to utility model patent scope.It should be pointed out that the common skill for this area
For art personnel, without departing from the concept of the premise utility, some deformation can also be made and improve, these broadly fall into
Protection domain of the present utility model.Therefore, the protection domain of this utility model patent should be defined by claims.
Claims (18)
1. a kind of aircraft it is characterised in that include aircraft body, the horn assembly being arranged in described aircraft body,
It is arranged at the power set on described horn assembly, described power set include actuator and the spiral shell being connected with described actuator
Rotation oar, described aircraft body one end is head, and the other end is tail, and described propeller tilts with respect to described aircraft body
Setting.
2. aircraft according to claim 1 is it is characterised in that during described aircraft water placing flat, described propeller
The surfaces of revolution is δ with the inclination angle of horizontal plane, and δ is more than 0 degree and is less than 90 degree.
3. aircraft according to claim 1 and 2 is it is characterised in that during described aircraft water placing flat, described propeller
The inclination angle δ of the surfaces of revolution and horizontal plane be 28.5 degree.
4. aircraft according to claim 1 is it is characterised in that the length of the top surface to described tail for the described head is more than
Described head is to the length of described tail bottom surface.
5. aircraft according to claim 1 is it is characterised in that the curvature of the top surface of described aircraft body is more than bottom surface
Curvature.
6. aircraft according to claim 1 it is characterised in that described horn assembly include the first horn, the second horn,
3rd horn and the 4th horn, described first horn and described second horn are arranged in the heading of described aircraft body
The left and right sides, and described first horn and described second horn are extended along described aircraft direct of travel respectively, described
3rd horn and described 4th horn are arranged on the top surface in tail direction of described aircraft body, described 3rd horn and institute
State the 4th horn to be extended in the vertically upward direction.
7. aircraft according to claim 6 it is characterised in that described first horn, described second horn, the described 3rd
Horn and described 4th horn all stretch out setting along the symmetrical direction of principal axis away from described aircraft.
8. aircraft according to claim 1 is it is characterised in that described aircraft body includes being arranged on described aircraft
Left drag reduction portion on the left of main body and be arranged on right drag reduction portion and air dam on the right side of described aircraft body, described left drag reduction portion and
Described right drag reduction portion is equipped with cambered surface.
9. aircraft according to claim 1 is it is characterised in that projection one upwards in the middle part of the top surface of described aircraft body
Air dam, described air dam extends to described tail from described head.
10. aircraft according to claim 8 is it is characterised in that the top surface of described aircraft body is also arranged with air inducing
Portion, described air inducing portion is located between described air dam and described left drag reduction portion, described right drag reduction portion, and described air inducing portion is from described
Air dam smooths downwards to extend to smooth upwards to extend to described drag reduction portion again and is formed.
11. aircraft according to claim 6 it is characterised in that described head front end and described first horn, described the
It is arranged with recess between two horns.
12. aircraft according to claim 1 are it is characterised in that described tail end symmetrical is provided with depressed part.
It is characterised in that including an aircraft body, described aircraft front end is a head to a kind of 13. aircraft, and rear end is one
Tail；
In described aircraft body, described power set are used for driving a propeller one power set；
Described aircraft has two states and is respectively first state and the second state, in first state, described propeller
The surfaces of revolution and horizontal plane have an inclination angle；In the second state, the surfaces of revolution of described propeller and plane-parallel.
14. aircraft according to claim 13 it is characterised in that in first state, described aircraft body bottom surface
The plane being located and plane-parallel.
15. aircraft according to claim 13 are it is characterised in that in the second state, described aircraft bottom surface is located
Plane and horizontal plane there is an inclination angle.
It is characterised in that including an aircraft body, described aircraft front end is a head to a kind of 16. aircraft, and rear end is one
Tail；
In described aircraft body, described power set are used for driving a propeller one power set；
When the horizontal flight forward of described aircraft or static on the ground when, the plane that described aircraft body bottom surface is located with
Described plane-parallel；
When described aircraft vertical flies upwards or hovers in the air, plane and institute that described aircraft body bottom surface is located
State horizontal plane and there is an inclination angle.
17. aircraft according to claim 16 are it is characterised in that when the horizontal flight forward of described aircraft or static
When on the ground, the surfaces of revolution of described propeller and horizontal plane have an inclination angle.
18. aircraft according to claim 16 are it is characterised in that when described aircraft vertical flies upwards or hovers
When in the air, the surfaces of revolution of described propeller and plane-parallel.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620447947.1U CN205916327U (en) | 2016-05-17 | 2016-05-17 | Aircraft |
| PCT/CN2017/083456 WO2017198082A1 (en) | 2016-05-17 | 2017-05-08 | Aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620447947.1U CN205916327U (en) | 2016-05-17 | 2016-05-17 | Aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882953A (en) * | 2016-05-17 | 2016-08-24 | 亿航智能设备（广州）有限公司 | Aircraft |
| WO2017198082A1 (en) * | 2016-05-17 | 2017-11-23 | 亿航智能设备（广州）有限公司 | Aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US7874513B1 (en) * | 2005-10-18 | 2011-01-25 | Smith Frick A | Apparatus and method for vertical take-off and landing aircraft |
| CN204688409U (en) * | 2015-04-27 | 2015-10-07 | 广州快飞计算机科技有限公司 | The unmanned vehicle that a kind of many rotors and fixed-wing combine |
| CN204623835U (en) * | 2015-04-30 | 2015-09-09 | 何春旺 | Multi-axis aircraft |
| CN204642150U (en) * | 2015-04-30 | 2015-09-16 | 江苏数字鹰科技发展有限公司 | Become axial multi-rotor aerocraft |
| CN105882953B (en) * | 2016-05-17 | 2018-10-02 | 亿航智能设备（广州）有限公司 | Aircraft |
| CN205916327U (en) * | 2016-05-17 | 2017-02-01 | 亿航智能设备（广州）有限公司 | Aircraft |
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2016
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882953A (en) * | 2016-05-17 | 2016-08-24 | 亿航智能设备（广州）有限公司 | Aircraft |
| WO2017198082A1 (en) * | 2016-05-17 | 2017-11-23 | 亿航智能设备（广州）有限公司 | Aerial vehicle |
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| WO2017198082A1 (en) | 2017-11-23 |
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