CN207748003U - Fuselage device applied to unmanned plane - Google Patents
Fuselage device applied to unmanned plane Download PDFInfo
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- CN207748003U CN207748003U CN201721641752.1U CN201721641752U CN207748003U CN 207748003 U CN207748003 U CN 207748003U CN 201721641752 U CN201721641752 U CN 201721641752U CN 207748003 U CN207748003 U CN 207748003U
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Abstract
The utility model discloses a kind of fuselage devices applied to unmanned plane, belong to air vehicle technique field, including second connecting portion, and second connecting portion and first connecting portion are detachably connected;Second ontology, the second ontology are fixedly connected with second connecting portion;And second ontology include first side, second side and third side, and first side and second side are symmetrical along the center vertical pivot of the second ontology, and third side is between first side and second side;And the first postposition wing is provided in first side, the second postposition wing is provided in second side, third is provided with vertical stabilizer on side;Third interconnecting piece, third interconnecting piece and the second ontology are fixedly connected;Wherein, the second ontology is between second connecting portion and third interconnecting piece, and second connecting portion, the second ontology and third interconnecting piece are integrally formed and constitute fuselage.The utility model has reached the fuselage maintenance cost for reducing unmanned plane, promotes the technique effect of the anti-interference ability of unmanned plane.
Description
Technical field
The utility model belongs to air vehicle technique field, more particularly to a kind of fuselage device applied to unmanned plane.
Background technology
Unmanned unmanned plane referred to as " unmanned plane ", is grasped using radio robot and the presetting apparatus provided for oneself
Vertical not manned unmanned plane.Without cockpit on machine, but automatic pilot, presetting apparatus, information collecting device are installed etc.
Equipment.On ground, naval vessels or machine tool remote control station personnel are by equipment such as radars, to its into line trace, positioning, remote control, telemetering and
Digital Transmission.It can take off as common unmanned plane under wireless remotecontrol or be launched with booster rocket, it also can be by machine tool
Aerial launch is taken to fly.
Currently, the fuselage of unmanned plane is mainly formed using integrally formed structure fabrication, the wing of left and right two of unmanned plane
It is fixed on the fuselage of unmanned plane.But unmanned plane breaks down, and the fuselage of unmanned plane is made to damage, need to unmanned plane into
When row is repaired, the entire fuselage of unmanned plane will be replaced, or unmanned plane can only be carried out scrapping processing.Which increase unmanned planes
Maintenance cost, and unmanned plane by two wings in left and right come when providing lift, be in-flight easy to be interfered by air-flow.
In conclusion existing applied in the body techniques of unmanned plane, there is maintenance costs for the fuselage of unmanned plane
Height, the technological deficiency of poor anti jamming capability.
Utility model content
Technical problem to be solved in the utility model is that there is fuselage maintenance cost height, the interference of anti-air-flow for unmanned plane
The technological deficiency of energy force difference.
In order to solve the above technical problems, the utility model provides a kind of fuselage device applied to unmanned plane, described one
It plants and includes applied to the fuselage device of unmanned plane:Second connecting portion, the second connecting portion and first connecting portion are detachably connected;
Second ontology, second ontology are fixedly connected with the second connecting portion;And second ontology includes first side, second
Side and third side, and the first side and the second side are symmetrical along the center vertical pivot of second ontology,
The third side is between the first side and the second side;And the first postposition is provided in the first side
Wing is provided with the second postposition wing in the second side, vertical stabilizer is provided on the third side;Third connects
Portion, the third interconnecting piece are fixedly connected with second ontology;Wherein, second ontology be located at the second connecting portion and
Between the third interconnecting piece, and the second connecting portion, second ontology and the third interconnecting piece are integrally formed and constitute
The fuselage.
Further, the first postposition wing includes fastening end and the first rear open end after first;Wherein, described first
Fastening end and first rear open end are the both ends of the first postposition wing afterwards.
Further, the second postposition wing includes fastening end and the second rear open end after second;Wherein, described second
Fastening end and second rear open end are the both ends of the second postposition wing afterwards.
Further, center vertical pivot pair of the fastening end along second ontology behind fastening end and described second after described first
The both sides for being fixed at second ontology claimed.
Further, a kind of fuselage device applied to unmanned plane further includes:First aileron, first aileron turn
Dynamic setting in first rear open end, and first aileron in first rear open end relative to described first
Rear open end is rotated.
Further, a kind of fuselage device applied to unmanned plane further includes:Second aileron, second aileron turn
Dynamic setting in second rear open end, and second aileron in second rear open end relative to described second
Rear open end is rotated.
Further, a kind of fuselage device applied to unmanned plane further includes:Third aileron, the third aileron turn
Dynamic setting is on the vertical stabilizer, and the third aileron carries out on the vertical stabilizer relative to the vertical stabilizer
Rotation.
Further, the first postposition wing fastening end after described first, along to first rear open end direction
On width be sequentially reduced.
Further, the second postposition wing fastening end after described second, along to second rear open end direction
On width be sequentially reduced.
Further, first aileron, second aileron and the third aileron are rectangle
Advantageous effect:The utility model provides a kind of fuselage device applied to unmanned plane, by by the second ontology and
Two interconnecting pieces are fixedly connected, and are arranged the first postposition wing in the first side of the second ontology, in the second side of the second ontology
Second postposition wing is set, vertical stabilizer is set on the third side of the second ontology, can weaken in-flight air-flow to unmanned plane
It is anti-dry.Since third interconnecting piece and the second ontology are fixedly connected, second connecting portion, the second ontology and third interconnecting piece can be with one
Body formed composition fuselage, the second connecting portion in fuselage can be detachably connected with first connecting portion.Then unmanned plane is made to occur
When some portion of damage, the fuselage of the part can be replaced.To reach the fuselage maintenance cost for reducing unmanned plane, promoted
The technique effect of the anti-interference ability of unmanned plane.
Description of the drawings
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Needed in attached drawing be briefly described, it should be apparent that, the accompanying drawings in the following description is only the utility model
Some embodiments for those of ordinary skill in the art without creative efforts, can also be according to this
A little attached drawings obtain other attached drawings.
Fig. 1 is the overall structure diagram for the unmanned plane that the utility model embodiment provides;
Fig. 2 is the top view illustration of Fig. 1;Fig. 3 is the upward view schematic diagram of Fig. 1;
Fig. 4 is the front view schematic diagram of Fig. 1;Fig. 5 is the rearview schematic diagram of Fig. 1;
Fig. 6 is the side view schematic diagram of Fig. 1;
Fig. 7 is the schematic diagram of the rotor mechanism for the adjustable angle that the utility model embodiment provides;
Fig. 8 is the generator and engine connection relationship diagram that the utility model embodiment provides;
Fig. 9 is the mechanism block diagram for the circuit control system that the utility model embodiment provides.
Specific implementation mode
The utility model discloses a kind of fuselage device applied to unmanned plane, by by the second ontology and second connecting portion
It is fixedly connected, the first postposition wing is set in the first side of the second ontology, is arranged second in the second side of the second ontology
Vertical stabilizer is arranged on the third side of the second ontology in postposition wing, can weaken in-flight air-flow to the anti-dry of unmanned plane.By
It is fixedly connected in third interconnecting piece and the second ontology, second connecting portion, the second ontology and third interconnecting piece can be integrally formed structure
At fuselage, the second connecting portion in fuselage can be detachably connected with first connecting portion.Then occur unmanned plane some portion of
When damage, the fuselage of the part can be replaced.To reach the fuselage maintenance cost for reducing unmanned plane, unmanned plane is promoted
The technique effect of anti-interference ability.
In order to elaborate to the airframe structure applied to unmanned plane that utility model provides, to support utility model institute
Technical problems to be solved first elaborate to unmanned plane in the following, in embodiment provided by the utility model, then exist
During describing unmanned plane, the fuselage knot provided by the utility model applied to unmanned plane is further targetedly drawn
Structure, it is complete, clear, clear to achieve the purpose that.
Following general description is done to the overall condition of unmanned plane first:The utility model is by the way that the fuselage of unmanned plane to be divided into
Including at least three sections, i.e. the first fuselage 10, the second fuselage 20 and third fuselage 30, and pass through detachable connection between three sections
Connection type is attached, and is constituted a dismountable unmanned plane of internal structure with this, so that when the fuselage of unmanned plane goes out
When existing local damage, it corresponding can remove the position for occurring damaging and repair, there is simple, convenient technology to imitate
Fruit.And when the part of fuselage can not be repaired because damaging, can also the position that can not repair of corresponding dismounting, i.e., pair
The position that can not be repaired is substituted, to overcome in the prior art because fuselage is using integrated global design so that
When fuselage local damage occur can not repair, it has to which the technological deficiency for replacing the entire fuselage of unmanned plane reaches and greatly drops
The low technique effect of maintenance cost.
Meanwhile unmanned plane, during executing landing operation, first included by unmanned plane in the utility model is revolved
The rotor mechanism 331 of the wing 1211, the second rotor 1221 and adjustable angle matches operation (being operated) and generates lifting force, draws
It rises or declines with motivation.Such as:When unmanned plane takes off, revolved by controlling the first rotor 1211 and the second rotor 1221
Turn, and adjust the rotation direction (rotor mechanism 331 is made to provide upward pulling force) of the adjustable rotor mechanism of angle 331, by the
Resultant force, carries for unmanned plane caused by the rotation of one rotor 1211, the rotation of the second rotor 1221 and the operating of rotor mechanism 331
For upward lifting force, to realize taking off vertically for unmanned plane.When unmanned plane is drawn high certain altitude, then pass through adjustment angle
The rotation direction (rotor mechanism 331 is made to provide horizontal thrust) for spending adjustable rotor mechanism 331, to generate water on unmanned plane
Flat-pushing power pushes unmanned plane to slide in the air and takes off, and then enters stabilized flight;When declining, by controlling the first rotor
1211, the lifting force of the second rotor 1221, and controlling the adjustable rotor mechanism of angle 331 makes unmanned plane pull fuselage from eminence
Stablize and decline, until stablizing landing, the damage of fuselage and carrying equipment caused by avoiding fuselage hard landing greatly reduces drop
The risk for falling accident, having reached makes unmanned plane be suitble to carry out the technique effect of landing operation in different flying fields.
Below in conjunction with Figure of description, the technical scheme in the embodiment of the utility model is clearly and completely retouched
It states, it is clear that the described embodiments are only a part of the embodiments of the utility model, instead of all the embodiments.
In order to which the unmanned plane that the utility model embodiment provides is described in detail, the utility model is implemented first
Involved technical term does description below explanation in example:
Detachable connection can be bolted or be bonded;Being fixedly connected can be welding or integrated molding;Ground
Face can be the ground that unmanned plane is parked, or the face with this plane parallel;First level face can be flat with level ground
Capable face, and the center vertical pivot 123 of the first noumenon is located in the plane;Minimum flying speed can be that unmanned plane is made to keep flying
Minimum flying speed when going, and not falling.Such as in the present embodiment, the minimum flying speed of unmanned plane can be 20m/s;It rises
The winged stage can be the process that unmanned plane reaches aerial vertical ascent from ground;Take off winged stage that flattens can be that unmanned plane arrives
Up to after aerial, the process of horizontal flight is carried out;The turning stage can be unmanned plane from level flight condition, the mistake turned
Journey, such as left and right turning;Landing phases can be process of the unmanned plane from airborne to ground.
For 10 part of the first fuselage:
Fig. 1-Fig. 6 is referred to, the first fuselage 10 includes:Portion 11, the first noumenon 12 and first connecting portion 13 windward, first
Ontology 12 is located at windward between portion 11 and first connecting portion 13, and portion 11, the first noumenon 12 and first connecting portion 13 1 windward
The first fuselage 10 of body formed composition.In the first fuselage 10, by the way that cone structure will be arranged in portion 11 windward, by portion 11 windward
Diameter of section is sequentially increased on the direction towards the first noumenon 12, and makes the diameter of section of the first noumenon 12 in direction first
It is sequentially reduced, allows in this way in unmanned plane during flying on the direction of interconnecting piece 13, the first fuselage 10 is implemented in the utility model
Global shape design in example advantageously reduces the resistance of air-flow.
In addition, being additionally provided with the first forewing 121 and the second forewing 122 on the first noumenon 12.Wherein, first
Forewing 121 includes:First preceding fastening end 1212 and the first forward open end 1213.Second forewing 122 includes:Before second
Fastening end 1222 and the second forward open end 1223.And first preceding fastening end 1212 and the second preceding fastening end 1222 along the first noumenon 12
Center vertical pivot be symmetrically distributed in the both sides of the first noumenon 12, and three is relatively fixed.
Specifically, can be by can between the first preceding fastening end 1212 of the first forewing 121 and the first noumenon 12
The connection type being detachably connected with is attached.The the second preceding fastening end 1222 and the first noumenon 12 of second forewing 122 it
Between can also be attached by the connection type of detachable connection.It allows for making by way of being detachably connected in this way
It is detachable between first forewing 121, the second forewing 122 and the first noumenon 12, it is convenient for the assembling of the first fuselage 10, makes
Obtain convenience easy to maintenance.
Fig. 4-Fig. 6 is referred to, the first forewing 121 and the angle in first level face can be 2.5 °, at unmanned plane
When minimum flying speed, 2.5 ° of angle can be that unmanned plane obtains enough lift, to overcome the weight of unmanned plane itself, from
And be preferably that unmanned plane generates lift, keep state of flight.Second forewing 122 can also be with first level face angle
2.5 °, when unmanned plane is in minimum flying speed, 2.5 ° of angle also can be that unmanned plane obtains enough lift, to overcome nothing
The man-machine weight of itself keeps state of flight to be preferably that unmanned plane generates lift.
The first rotor 1211 is provided on the first forewing 121, and for driving the first rotor 1211 to be revolved
The first steering engine 471 turned is provided with the second rotor 1221 on the second forewing 122, and for driving the second rotor 1221
The second steering engine 472 rotated.And in the first forward open end 1213 of the first forewing 121, also set up one first
Storage region 12131;One second storage region 12231 is also set up in the second forward open end 1223 of the second forewing 122.
Wherein, the first steering engine 471 includes:First rotor shaft 4712 and the first fixed seat for fixing the first steering engine 471
4713, and the first fixed seat 4713 is fixed in the first storage region 12131;Second steering engine 472 includes:Second rotor shaft 4722
With the second fixed seat 4723 for fixing the second steering engine 472, and the second fixed seat 4723 is fixed on the second storage region 12231
It is interior.First rotor 1211 includes:First rotating vane 12111 and the first clump weight 12112, the first rotating vane 12111 and
One rotor shaft 4712 is fixedly connected, and the first clump weight 12112 is fixedly connected with the first rotor shaft 4712;And the first rotating vane
12111 and first clump weight 12112 it is symmetrical relative to the first rotor shaft 4712, the first rotor shaft 4712 and the first pivoting leaf
The rotational plane of piece 12111 is perpendicular.Second rotor 1221 includes:Second rotating vane 12211 and the second clump weight 12212,
Second rotating vane 12211 is fixedly connected with the second rotor shaft 4722, and the second clump weight 12212 and the second rotor shaft 4722 are fixed
Connection, and the second rotating vane 12211 and the second clump weight 12212 are symmetrical relative to the second rotor shaft 4722, second
Rotor shaft 4722 and the rotational plane of the second rotating vane 12211 are perpendicular.
Specifically, the size and shape of the first storage region 12131 and the second storage region 12231 can be according to required
The form parameter of the steering engine 47 of placement and determine, such as steering engine 47 volume size, to which the first steering engine 471 is positioned over first
It is positioned in the second storage region 12231 in storage region 12131 and by the second steering engine 472.First steering engine 471 passes through its own
The first fixed seat 4713 be fixed in the first storage region 12131, the rotation of the first rotor shaft 4712 and first of the first steering engine 471
First rotating vane 12111 of the wing 1211 is fixedly connected, and the first rotor shaft 4712 and the first clump weight 12112 are fixed and connected
It connects.First rotor shaft 4712 and the rotational plane of the first rotating vane 12111 are perpendicular, i.e., in the first rotating vane 12111
When rotation, the plane of the rotation is mutually perpendicular to the first rotor shaft 4712;First rotating vane 12111 and the first clump weight
12112 is symmetrical relative to the first rotor shaft 4712, i.e. the first rotating vane 12111 and the first clump weight 12112 are with first
Rotor shaft 4712 is symmetric for axis.The making material of first clump weight 12112 can use rigid material so that the first rotation
When wing axis 4712 drives the first rotating vane 12111 and the first clump weight 12112 to rotate together, the first clump weight 12112 will not
It deforms upon, to influence the balance of the first rotor 1211.
On the other hand, the second steering engine 472 is fixed on by the second fixed seat 4723 in the second storage region 12231, the
Second rotor shaft 4722 of two steering engines 472 is fixedly connected with the second rotating vane 12211 of the second rotor 1221, and the second rotation
Wing axis 4722 is fixedly connected with the second clump weight 12212.The rotational plane of second rotor shaft 4722 and the second rotating vane 12211
Perpendicular, i.e., in the rotation of the second rotating vane 12211, the plane of the rotation is mutually perpendicular to the second rotor shaft 4722;The
Two rotating vanes 12211 and the second clump weight 12212 are symmetrical relative to the second rotor shaft 4722, i.e. the second rotating vane
12211 and second clump weight 12212 be symmetric for axis with the second rotor shaft 4722.The making material of second clump weight 12212
Material can use rigid material so that the second rotor shaft 4722 drives the second rotating vane 12211 and the second clump weight 12,212 1
When playing rotation, the second clump weight 12212 will not deform upon, to influence the balance of the first rotor 1211.
In embodiment provided by the utility model, it is especially desirable to it is to be noted that:First rotor 1211 includes the first rotation
Blade 12111 and the first clump weight 12112;Second rotor 1221 includes the second rotating vane 12211 and the second clump weight
12212.Namely the first rotor 1211 uses single blade, and what the second rotor 1221 used is also single blade.Traditional rotation
What the wing used is all twayblade, and traditional rotor is namely made of two blades of similar first rotating vane 12111, this two
A blade is symmetric usually relative to the axis that movable vane piece rotates.Traditional rotor due to the use of be twayblade, if nothing
It is man-machine awing, which, to increase the resistance of air-flow, can produce the flight of unmanned plane along flow rotation
Larger interference is unfavorable for the balance of unmanned plane, while it is larger to cause the amount of power of unmanned plane that can be lost.The utility model is real
It is all to use single blade, while being respectively arranged with each single blade to apply the first rotor 1211 of example offer and the second rotor 1221
First clump weight 12112 and the second clump weight 12212, and then the first rotating vane 12111 and the second rotating vane 12211 are risen
The effect of weight balancing.Due to rotor have single blade, if unmanned plane is awing, the single blade will remain with
The consistent direction of air-flow overcomes traditional twayblade rotor and is produced to the flight of unmanned plane to reduce the resistance of air-flow
Destruction caused by raw larger interference, the balance to unmanned plane and make the power capacity of unmanned plane that larger technology be lost to lack
It falls into.Reach the flight balance for being conducive to unmanned plane, reduces the technique effect of the energy loss of unmanned mechanomotive force.
Refer to Fig. 2, the first forewing 121 is in the first preceding fastening end 1212, along to 1213 direction of the first forward open end
On width be sequentially reduced;And/or second forewing 122 in the second preceding fastening end 1222, along to the second forward open end 1223
Width on direction is sequentially reduced.
Specifically, the shape for the first forewing 121 and the second forewing 122 provides following two embodiment party
Formula illustrates:
The first embodiment, by by the first forewing 121 since the first preceding fastening end 1212, towards to first
Width on 1213 direction of forward open end is sequentially reduced so that the first forewing 121 can be it is trapezoidal, not due to tapered airfoil
By angle of sweep drag reduction, so the angle of sweep of the leading edge of a wing can be smaller, to make unmanned plane that can awing obtain preferable liter
Power.
Second of embodiment, by by the second forewing 122 since the second preceding fastening end 1222, towards to second
Width on 1223 direction of forward open end is sequentially reduced so that the second forewing 122 can be it is trapezoidal, not due to tapered airfoil
By angle of sweep drag reduction, so the angle of sweep of the leading edge of a wing can be smaller, to make unmanned plane that can awing obtain preferable liter
Power.
Above first embodiment and second embodiment can be implemented simultaneously, can also be in first embodiment
Implement with optional one in second embodiment.Such as:Keep the first forewing 121 trapezoidal, and makes second preposition
Wing 122 is also trapezoidal, to make unmanned plane obtain preferable lift.Keep the first forewing 121 trapezoidal, or makes second
Forewing 122 is trapezoidal, in the global design of unmanned plane, make unmanned plane obtain preferable lift.
The utility model provides a kind of embodiment of the fuselage device applied to unmanned plane.The fuselage for being used for unmanned plane can
To refer to the second fuselage 20.For 20 part of the second fuselage:
Fig. 1-6 is referred to, the second fuselage 20 includes second connecting portion 21, the second ontology 22 and third interconnecting piece 23;Its
In, the second ontology 22 is between second connecting portion 21 and third interconnecting piece 23, and second connecting portion 21, the second ontology 22 and
Three interconnecting pieces 23, which are integrally formed, constitutes the second fuselage 20;Second connecting portion 21 and first connecting portion 13 are detachably connected, second
Body 22 is fixedly connected with second connecting portion 21, and third interconnecting piece 23 is fixedly connected with the second ontology 22.
Specifically, since second connecting portion 21 and first connecting portion 13 are detachably connected so that the second fuselage 20 and
It is also to pass through detachable connection between one fuselage 10.Make the first fuselage 10 and the second fuselage by way of being detachably connected
It is detachable between 20, it is convenient for the assembling of the second fuselage 20 so that convenience easy to maintenance significantly reduces maintenance cost.
Further, the second ontology 22 may include:First side 221, second side 222 and third side 223, and
First side 221 and second side 222 are symmetrical along the center vertical pivot 224 of the second ontology, and third side 223 is located at first
Between side 221 and second side 222;And the first postposition wing 2211, second side 222 are provided in first side 221
On be provided with the second postposition wing 2221, be provided with vertical stabilizer 2231 on third side 223.First postposition wing 2211 wraps
It includes:Fastening end 22111 and the first rear open end 22112 after first;Second forewing 122 includes:Fastening end 22211 after second
With the second rear open end 22212.Wherein, after first behind fastening end 22111 and second fastening end 22211 along the center of the second ontology
Vertical pivot 224 is symmetrically fixed at the both sides of the second ontology 22;And fastening end 22111 and the first rear open end after first
22112 be the both ends of the first postposition wing 2211 respectively, and fastening end 22211 and the second rear open end 22212 are respectively after second
The both ends of second postposition wing 2221.
Connect specifically, the first postposition wing 2211 can be fixed by fastening end 22111 after first with first side 221
It connects, the second postposition wing 2221 can be fixedly connected by fastening end 22211 after second with second side 222, vertical stabilizer
2231 can be fixedly connected with third side 223.By the way that the first postposition wing 2211 and the second postposition wing 2221 is arranged, make this
Two wings can provide the lift of bigger when unmanned plane is in flight for unmanned plane.
Second fuselage 20 further includes:First winglet 24 and the second winglet 25.It is small to the first wing tip individually below
The wing 24 and the second winglet 25 are described in detail:
For 24 part of the first winglet.The angle of first winglet 24 and the first postposition wing 2211 is 60 °-
90°;First winglet 24 includes:First wing tip fastening end 241 and the first wing tip open end 242;And the first wing tip fastens
End 241 is fixedly connected with the first rear open end 22112, and the first wing tip open end 242 is away from the first rear open end 22112, with the
One wing tip fastening end 241 constitutes the both ends of the first winglet 24;And the first wing tip open end 242 and vertical stabilizer 2231
In the both sides of the first postposition wing 2211;
For 25 part of the second winglet.The angle of second winglet 25 and the second postposition wing 2221 is 60 °-
90°;Second winglet 25 includes:Second wing tip fastening end 251 and the second wing tip open end 252;And the second wing tip fastens
End 251 is fixedly connected with the second rear open end 22212, and the second wing tip open end 252 is away from the second rear open end 22212, with the
Two wing tip fastening ends 251 constitute the both ends of the second winglet 25;And the second wing tip open end 252 and vertical stabilizer 2231
In the both sides of the second postposition wing 2221.
First wing tip open end 242 of above first winglet 24 and the second wing tip open end of the second winglet 25
252 can symmetrically be distributed along the center vertical pivot 224 of the second ontology.Certainly, the first wing tip open end of the first winglet 24
242 and second second wing tip open end 252 of winglet 25 can be along 224 asymmetric points of the center vertical pivot of the second ontology
Cloth.
Specifically, the first winglet 24 includes:First wing tip fastening end 241 and the first wing tip open end 242;First
First wing tip fastening end 241 of winglet 24 is fixedly connected with the first rear open end 22112 of the first postposition wing 2211, and
And first wing tip open end 242 deviate from the first rear open end 22112, i.e. the first wing tip open end 242 as shown in figure 4, be located at nothing
The lower section of man-machine fuselage.At this point, the first winglet 24 and the first postposition wing 2211 constitute angle, the range of the angle is:
60°-90°;Second rear open end of the second wing tip fastening end 251 and the second postposition wing 2221 of the second winglet 25
22212 are fixedly connected, and the second wing tip open end 252 deviates from the second rear open end 22212, i.e. the second wing tip open end 252
As shown in figure 4, positioned at the lower section of unmanned aerial vehicle body.At this point, the second winglet 25 and the second postposition wing 2221 constitute angle,
The range of the angle is:60°-90°.The spacing of first wing tip fastening end 241 and the first wing tip open end 242, with the second wing tip
The spacing of fastening end 251 and the second wing tip open end 252 is equal to refer to:Assuming that the first wing tip fastening end 241 and first wing
The spacing of sharp open end 242 is W1, and the spacing of the second wing tip fastening end 251 and the second wing tip open end 252 is W2, then W1=
W2.Due to W1=W2, when unmanned plane is parked in level ground, the first wing tip open end 242 and the second wing tip open end 252 can be with
It is all contacted with ground so that the stop of unmanned plane is more steady.
Fig. 4, Fig. 5 are referred to, in order to make specification preferably support the first winglet 24 and first in claims
The numerical value of the numberical range of the angle of postposition wing 2211 and the angle of the second winglet 25 and the second postposition wing 2221
Range is now chosen two endpoint values of angular range, is explained as follows with two embodiments respectively:
The first embodiment, if the angle of the first winglet 24 and the first postposition wing 2211 is 60 °, and the
The angle of two winglets 25 and the second postposition wing 2221 is also 60 °.I.e. when unmanned plane is parked in level ground, by first wing
The angle that first wing tip open end 242 of sharp winglet 24 and the first rear open end 22112 of the first postposition wing 2211 are constituted
It is 60 °;And the second rear open end of the second wing tip open end 252 and the second postposition wing 2221 by the second winglet 25
22212 angles constituted are also 60 °.At this point, the first winglet 24 and the first postposition wing 2211 can effectively hinder first
The air of the upper lower aerofoil of postposition wing 2211 streams, and the second winglet 25 also can be effective with the second postposition wing 2221
The air of the upper lower aerofoil of the second postposition wing 2221 is hindered to stream.To reduce caused by first box the second wing tip trailing vortex
" induced drag ", and then reduce and stream to lift produced by the first postposition of unmanned plane wing 2211 and the second postposition wing 2221
Destruction, improve unmanned plane lift resistance ratio, increase voyage, have the function that increase unmanned plane lift.
Second of embodiment, if the angle of the second winglet 25 and the second postposition wing 2221 is 90 °, and the
The angle of two winglets 25 and the second postposition wing 2221 is also 90 °.I.e. when unmanned plane is parked in level ground, by first wing
The angle that first wing tip open end 242 of sharp winglet 24 and the first rear open end 22112 of the first postposition wing 2211 are constituted
It is 90 °;And the second rear open end of the second wing tip open end 252 and the second postposition wing 2221 by the second winglet 25
22212 angles constituted are also 90 °.At this point, the first winglet 24 and the first postposition wing 2211 can effectively hinder first
The air of the upper lower aerofoil of postposition wing 2211 streams, and the second winglet 25 also can be effective with the second postposition wing 2221
The air of the upper lower aerofoil of the second postposition wing 2221 is hindered to stream.To reduce caused by the first and second wing tip trailing vortexs
" induced drag ", reduce the destruction streamed to lift, improve lift resistance ratio, increase voyage, have the function that increase lift.Together
When, since the first winglet 24 and the second winglet 25 are all mutually perpendicular to first level face, so the first winglet
24 and second the distance between winglet 25 and ground recently so that the first winglet 24 of manufacture and the second winglet 25
Required material is also less, to alleviate the own wt of the first winglet 24 and the second winglet 25, reduces nothing
Man-machine overall weight, has reached increase voyage, reduce unmanned plane kinetic equation loss (such as:Oil consumption, accumulator 45 electric energy)
Technique effect.
Further, the second fuselage 20 further includes:First aileron 26, the second aileron 27 and third aileron 28.First aileron
26, the second aileron 27 and third aileron 28 can be rectangle.The setting of first aileron 26 rotation is in the first rear open end
On 22112, and the first aileron 26 is rotated in the first rear open end 22112 relative to the first rear open end 22112;
And/or second the setting that rotates of aileron 27 in the second rear open end 22212, and the second aileron 27 is in the second rear open end
It is rotated relative to the second rear open end 22212 on 22212;And/or the setting that third aileron 28 rotates is in vertical stabilizer
On 2231, and third aileron 28 is rotated on vertical stabilizer 2231 relative to vertical stabilizer 2231;Wherein, the first postposition
Fastening end 22111 after first of wing 2211 are sequentially reduced along the width on 22112 direction of the first rear open end;And/or
Second fastening end 22211 after second of postposition wing 2221, subtract successively along the width on 22212 direction of the second rear open end
It is small.
Fig. 5 is referred to, specifically, the first rear open end in the first postposition wing 2211 is arranged in the first aileron 26
On 22112, the first aileron 26 can be relative to the plane of the first postposition wing 2211, along the plane of the first postposition wing 2211
Vertically rotate;Second aileron 27 is arranged in the second rear open end 22212 in the second postposition wing 2221, and second is secondary
The wing 27 can vertically turn relative to the plane of the second postposition wing 2221, the plane along the second postposition wing 2221
It is dynamic;Third aileron 28 is arranged on vertical stabilizer 2231, is rotated in the lateral direction along the plane of vertical stabilizer 2231.
Meanwhile first postposition wing 2211 can be trapezoidal, after first fastening end 22111 be the trapezoidal bottom, favorably
In the lift for improving unmanned plane, keeps the in-flight stability of unmanned plane and flying for unmanned plane is controlled by the first aileron 26
Row posture;Second postposition wing 2221 can also be trapezoidal, and fastening end 22211 is also the trapezoidal bottom after second, is conducive to
The lift of unmanned plane is improved, the in-flight stability of unmanned plane is kept and the flight of unmanned plane is controlled by the second aileron 27
Posture.
Referring to Fig. 4, the angle of the first forewing 121 and the first postposition wing 2211 can be 15 °, meanwhile, second
The angle of forewing 122 and the second postposition wing 2221 can also be 15 °.If the first forewing and the first postposition wing
Angle is 15 °, and the angle of the second forewing 122 and the second postposition wing 2221 is also 15 °, is pushed in tail rotor 33123
When unmanned plane during flying, it is beneficial to the balance of unmanned plane surrounding flow, to reach the technology effect for the stability for promoting unmanned plane
Fruit.Fig. 3 is referred to, the abdomen of unmanned plane may include first (when i.e. unmanned plane is parked in level ground, the face of close unmanned plane)
The abdomen of fuselage 10, the second fuselage 20 abdomen and third fuselage 30 abdomen, the abdomen of unmanned plane can be rendered as arc, should
The abdomen of arc advantageously reduces obstruction of the air-flow to unmanned plane, reduces the energy loss of unmanned plane, reaches promotion unmanned plane and flies
The technique effect of row distance.
Fig. 9 is referred to, further, the second driving motor 482 is connect with the first aileron 26, and the second driving motor
482 be fixed at first after between fastening end 22111 and the first rear open end 22112;Third driving motor 483 and the second pair
The wing 27 connects, and third driving motor 483 be fixed at second after fastening end 22211 and the second rear open end 22212 it
Between;4th driving motor 484 is connect with third aileron 28, and the 4th driving motor 484 is fixed on vertical stabilizer 2231.
Specifically, after the second driving motor 482 is connect with the first aileron 26, pass through the work of the second driving motor 482
The pulling force rotated upwardly and downwardly is provided for the first aileron 26;After third driving motor 483 is connect with the second aileron 27, driven by third
The work of motor 483 is that the second aileron 27 provides the pulling force rotated upwardly and downwardly.4th driving motor 484 is connect with third aileron 28
Afterwards, the pulling force of left-right rotation is provided by the work of the 4th driving motor 484 for third aileron 28.
Continuing with referring to Fig. 9, further, current divider 46 further includes:The 4th shunting shunting output of delivery outlet the 465, the 5th
Mouth 466 and the 6th shunting delivery outlet 467.4th shunting delivery outlet 465 is connect with the second driving motor 482;5th shunting output
Mouth 466 is connect with third driving motor 483;6th shunting delivery outlet 467 is connect with the 4th driving motor 484.
Specifically, it can be by conducting wire by current divider that the 4th shunting delivery outlet 465 is connect with the second driving motor 482
46 connect with the second driving motor 482, and the second driving motor 482 is made to power on;5th shunting delivery outlet 466 drives with third
The connection of motor 483 can be connect current divider 46 with third driving motor 483 by conducting wire, and third driving motor 483 is made to connect
Energization source;It can be by conducting wire by current divider 46 and 4 wheel driven that 6th shunting delivery outlet 467 is connect with the 4th driving motor 484
Dynamic motor 484 connects, and the 4th driving motor 484 is made to power on.To be the second driving motor 482, the by current divider 46
Three driving motors 483 and the 4th driving motor 484 provide electric energy.Refer to Fig. 2 and Fig. 3, it should be noted that unmanned plane is set
The weight calculation heart is located at the first lift equalization point and first of the first forewing 121 and the second forewing 122 on unmanned plane
Between the second lift equalization point of postposition wing 2211 and the second postposition wing 2221 on unmanned plane;And the design weight of unmanned plane
The heart is at the 3/4 of the first lift equalization point and the second lift equalization point spacing, and the design gravity of unmanned plane is close to the second lift
Equalization point.
Specifically, the lift equalization point of the first forewing 121 and the second forewing 122 on unmanned plane is first
Lift equalization point (abbreviation A points), the lift equalization point of the first postposition wing 2211 and the second postposition wing 2221 on unmanned plane
It is the second lift equalization point (abbreviation B points);Air line distance length between A points and B points is S, and the design gravity of unmanned plane is referred to as
For C points.In order to explain in detail the design gravity (C points) and the first lift equalization point (A points), the second lift equalization point (B of unmanned plane
Point) position relationship, now enumerate embodiment and be explained as follows:C points are located between A points and B points, and straight between C points and A points
Linear distance is assumed to be L, and L needs to meet:L=(3/4) * S.Meanwhile A points, B points and C points may be alternatively located on same straight line.Due to nothing
Man-machine design center of gravity is at the 3/4 of the first lift equalization point and the second lift equalization point spacing, when unmanned plane weight changes
When, the control performance to unmanned plane will not be influenced.So the design gravity of unmanned plane is in the first lift equalization point and second liter
At the 3/4 of power equalization point spacing, be conducive to the different weight for adapting to unmanned plane, and then reach the technology effect for not influencing control performance
Fruit.
Obviously, in embodiment provided by the utility model, to the design gravity of unmanned plane in the first lift equalization point and
At the 3/4 of second lift equalization point spacing and what position relationship that A points, B points and C points are located along the same line was carried out says
It is bright, it is not to provide constraints to the position, those skilled in the art can be by modifying to the link position
Either equivalent replacement but this modification or equivalent replacement both be within the protection scope of the present invention.Such as:Unmanned plane is set
The heart is counted weight at the 4/5 of the first lift equalization point and the second lift equalization point spacing;C points are located at except the line of B points and C points.
For 30 part of third fuselage:
Fig. 1-Fig. 6 is referred to, third fuselage 30 includes the 4th interconnecting piece 31, third ontology 32 and tail portion 33;Third ontology
32 between the 4th interconnecting piece 31 and tail portion 33, and the 4th interconnecting piece 31, third ontology 32 and tail portion 33 are integrally formed and constitute
Third fuselage 30, the diameter of section of tail portion 33 is towards being sequentially increased on the direction of third ontology 32.Pass through tail portion 33 and third sheet
Body 32 is fixedly connected, and third ontology 32 is fixedly connected with the 4th interconnecting piece 31, and the 4th interconnecting piece 31 and third interconnecting piece 23 are removable
Connection is unloaded, third fuselage 30 and the second fuselage 20 is made to be linked together.
Specifically, since the third interconnecting piece 23 of the 4th interconnecting piece 31 and the second fuselage 20 is detachably connected so that the
It is also to pass through detachable connection between three fuselages 30 and the second fuselage 20.Make third fuselage by way of being detachably connected
30 and second detachable between fuselage 20, it is convenient for the assembling of third fuselage 30 so that convenience easy to maintenance significantly reduces dimension
Accomplish this.
Further, the rotor mechanism 331 of an adjustable angle is provided on tail portion 33;Third fuselage 30 can be divided
For:First caudal face 34, the second caudal face 35, third side caudal face 36 and the 4th caudal face 37 so that by the first caudal face 34,
Second caudal face 35, third side caudal face 36 and the 4th caudal face 37 are surrounded to form third fuselage 30, and the first caudal face 34
The both sides in the second caudal face 35 and/or the 4th caudal face 37 are symmetrically dispersed in third side.
Meanwhile the 4th shunting delivery outlet 465 of setting on current divider 46.First driving motor 481 can also include:First
Drive shaft 4811 and driving fixed seat 4812;Steering engine 47 can also include:Third steering engine 473, the third steering engine 473 include third
Steering engine input port 4733, third rotor shaft 4731 and third fixed seat 4732;By by third steering engine input port 4733 with shunting
4th shunting delivery outlet 465 of device 46 connects, to provide electric energy for third steering engine 473.
It should be noted that for 331 part of rotor mechanism of adjustable angle, the rotor mechanism 331 of the adjustable angle can
To include:Tailspin seat 3311, linkage portion 3312 and tail rotor 33123.Tailspin seat 3311 be fixed at the second caudal face 35 and/
Or the 4th caudal face 37 both sides on, and drive fixed seat 4812 be arranged in tailspin seat 3311 and/or the third ontology 32
On;Linkage portion 3312 includes:First cohesive end 33121 and the second cohesive end 33122, the driving of the first cohesive end 33121 and first
Axis 4811 connects;Second cohesive end 33122 is connect with third fixed seat 4732;Third rotor shaft 4731 and tail rotor 33123
Center is fixedly connected, and third rotor shaft 4731 and the rotational plane of tail rotor 33123 are perpendicular.Pass through the first cohesive end
The driving force of first drive shaft 4811 is transferred to the second cohesive end 33122 by 33121, and third rotor shaft 4731 is made to drive tailspin
The wing 33123 is moved along the first caudal face 34, the second caudal face 35, third side caudal face 36 or 37 direction of the 4th caudal face.
On the other hand, tailspin seat 3311 can also be opened including the first hinged seat, the first hollow portion, the first opening face, second
Mouth face and the first mounting base;First hinged seat can be fixed at the first mounting base in the first hollow portion that (hollow portion can
Be aircraft fuselage in), and the first opening face can be fixedly connected with the tail portion 33 of unmanned plane, and the first opening face and
Second opening face can be two corresponding surfaces of the tailspin seat 3311 respectively;First driving of first driving motor 481
Fixed seat can be fixedly connected with first mounting base.
Base assembly may include the second hinged seat, the second hollow portion, third opening face and the 4th opening face;Third is open
Face can be with the second opening face flexible connection, i.e., third opening face can be hinged with the second opening face, and the second hinged seat
It can be fixedly connected with the 4th opening face, third opening face and the 4th opening face can be two of the second base assembly right respectively
Answer face;Second driving fixed seat can be fixed on the tail portion 33.
Turning part may include that shell, shell may include third hollow portion, first side and second side;The first side
It may include that first end, second end and positioning area, first end can be hinged with the second hinged seat, and second hinged seat
It can be between first end and the 4th opening face;The third fixed seat of third steering engine 473 can be arranged hollow in third
In portion, and third rotor shaft 4731 can also be located at outside the second side, and the third rotor shaft of third steering engine 473
4731 can also be fixedly connected with the center of tail rotor, and third rotor shaft 4731 can also be with the rotational plane phase of tail rotor
It is mutually vertical.
Linkage portion 3312 may include the first cohesive end 33121, the second cohesive end 33122 and third cohesive end.First linking
End 33121 can also be hinged with the second end;Second cohesive end 33122 can also be fixed with second drive shaft to be connected
It connects;Third cohesive end can also be hinged with first hinged seat;And the second cohesive end 33122 can be located at described first
Between cohesive end 33121 and the third cohesive end.
Driving section may include that the first driving wheel and the second driving wheel, the first driving wheel may also include first gear 50 and endoporus, endoporus
The center of first gear 50 can be located at, and endoporus can be fixedly connected with the first drive shaft 4811.Second driving wheel can wrap
Second gear 51 and supporter are included, supporter may include lateral surface and medial surface, and second gear 51 can be with the medial surface
It is fixedly connected, and lateral surface can also be fixedly connected with the second hollow portion, and lateral surface can also be located at the second hollow portion
It is interior, meanwhile, second gear 51 can be meshed with first gear 50;Lateral surface and medial surface can be two of the supporter
Corresponding surface.
Specifically, tailspin seat 3311 to be fixed to the second caudal face 35 and/or the 4th tail outside third fuselage 30
The the second caudal face 35 that tailspin seat 3311 can also be fixed in third fuselage 30 on the both sides of side 37 and/or
On the both sides in four caudal faces 37.By driving the fixation of fixed seat 4812 and tailspin seat 3311, the first driving motor 481 is fixed
On third fuselage 30;Directly the first driving motor 481 can also be fixed in third fuselage 30.
A kind of embodiment as the utility model embodiment.First driving motor 481 can also use straight line steering engine
47, linkage portion 3312 can also use upset connecting rod, the first cohesive end 33121 and the second cohesive end 33122 of linkage portion 3312
Can be the both ends of upset connecting rod respectively.
As shown in fig. 7, upset connecting rod is in " 7 " font, i.e., the first cohesive end 33121 constitutes fixed angle with second end,
The numerical value of the angle can be 90 °.When the first driving motor 481 pushes the first cohesive end 33121 to move right, the will be driven
Two cohesive ends 33122 will move down;When the first driving motor 481 pulls the first cohesive end 33121 to be moved to the left, will drive
Second cohesive end 33122 will move up.By being moved to the left or right so as to cause the second cohesive end for the first cohesive end 33121
33122 move up or down.
Also, tail rotor 33123 can use twayblade rotor, the third rotor of tail rotor 33123 and third steering engine 473
Axis 4731 is fixedly connected, and makes third rotor shaft 4731 that tail rotor 33123 be driven to rotate.When tail rotor 33123 rotates, third rotation
Wing axis 4731 and the plane of the rotation are mutually perpendicular to.One tail rotor can be formed by tail rotor 33123 and third steering engine 473
33123 overturning components, it can be specifically to include which, which overturns component,:Coniform shell.Third steering engine 473 can be with
It is fixed in coniform shell, by the way that the third rotor shaft 4731 of third steering engine 473 is stretched out except coniform shell, from
And tail rotor 33123 is made to be fixedly connected with third rotor shaft 4731 except coniform shell.Since coniform shell can be set
It is set to sealing, and then in the flight of rainwater day, damage of the rainwater to the electric elements inside unmanned plane can be prevented.It can also
In coniform shell, connecting hole can be set on the one side of third fuselage 30, by by the second cohesive end 33122 with should
Connecting hole is fixedly connected, to make the second cohesive end 33122 be connect with third fixed seat 4732, if the second cohesive end 33122
It is mobile, also third steering engine 473 will be driven to move together.
Fig. 7 is referred to, second gear 51 can be set on the one side of third fuselage 30 in coniform shell, this
Two gears 51 can be gear ring, and second gear 51 is made to be rotated centered on first gear 50.It can be in third fuselage 30
One servo motor of interior fixed setting, for driving first gear 50 to rotate, since first gear 50 and second gear 51 rotate
Connection, the rotation of first gear 50 will drive second gear 51 and then to rotate together.Or pass through 481 band of the first driving motor
Dynamic first gear 50 rotates, and due to the connection that first gear 50 and second gear 51 rotate, the rotation of first gear 50 will drive
Second gear 51 and then rotates together.
Furthermore because second gear 51 by first gear 50 with rotating together, it will pass through the rotation of second gear 51
Coniform shell or third steering engine 473 is set to rotate together, to make tail rotor 33123 far from the first vertical pivot 53 or close to first
Vertical pivot 53 moves.
In embodiment provided by the utility model, since tail rotor 33123 moves up or down, tail rotor will be made
33123 move relative to the first vertical pivot 53, i.e. the angular range constituted relative to the movement of the first vertical pivot 53 of tail rotor 33123 can
To be 0 ° -90 °.Since tail rotor 33123 is moved to the left or right, tail rotor 33123 will be made to be moved relative to the first vertical pivot 53
Dynamic, i.e., it can be 0 ° -60 ° that tail rotor 33123 is moved to the left constituted angular range relative to the first vertical pivot 53;Tail rotor
33123 relative to the first vertical pivot 53 constituted angular range that moves right can be 0 ° -60 °.
Embodiment provided by the utility model is described in detail in order to clearer, now respectively to tail rotor 33123
It moves up or down, it is described further below that tail rotor 33123 is moved to the left or right progress:
It is initially noted that:Tail rotor 33123, which moves up, to be:Tail rotor 33123 is along third caudal face
Direction is moved, i.e., is moved along the direction of vertical stabilizer 2231, at this time far from the first horizontal axis 54;Tail rotor 33123 moves down
Can be:Tail rotor 33123 is moved along 37 direction of the 4th caudal face, that is, the direction for deviating from vertical stabilizer 2231 is moved, at this time
Close to the first horizontal axis 54;Tail rotor 33123, which is moved to the left, to be:Tail rotor 33123 is moved along 34 direction of the first caudal face,
It such as Fig. 5, i.e., is moved along 2211 direction of the first postposition wing, at this time far from the first vertical pivot 53;Tail rotor 33123 moves right can
To be:Tail rotor 33123 is moved along 35 direction of the second caudal face, such as Fig. 5, i.e., is moved along 2221 direction of the second postposition wing
It is dynamic, at this time far from the first vertical pivot 53.
Tail rotor 33123 is moved up or down, below by way of two embodiments to tail rotor 33123 upwards or
It moves down and is described in detail respectively:
The first embodiment.If the first cohesive end 33121 moves right, by cause the second cohesive end 33122 to
Lower movement.Since the second cohesive end 33122 is connect with third fixed seat 4732, tail rotor 33123 and the with third steering engine 473
Three rotor shafts, 4731 fixed seat connects.Moving down for second cohesive end 33122 can drive tail rotor 33123 to move downwardly together
Dynamic, to realize unmanned plane in flight, landing, tail rotor 33123 can move gradually downward, reach change tail rotor
33123 directions of motion, and then tail rotor 33123 is controlled to the thrust direction of unmanned plane, so that thrust direction is gradually moved up.
When tail rotor 33123 moves gradually downward, and it is moved to the folder that tail rotor 33123 is moved relative to the first vertical pivot 53
When angle is 90 °.Tail rotor 33123 will upwards (such as Fig. 7) to the thrust direction of unmanned plane, and the rotation of tail rotor 33123 at this time will
Lift is provided for unmanned plane, to make the lift of unmanned plane increase.
Second of embodiment.If the first cohesive end 33121 is moved to the left, by cause the second cohesive end 33122 to
Upper movement.Since the second cohesive end 33122 is connect with third fixed seat 4732, the third of tail rotor 33123 and third steering engine 473
4731 fixed seat of rotor shaft connects.Moving up for second cohesive end 33122 can drive tail rotor 33123 to move upwardly together,
To realize unmanned plane in flight, landing, tail rotor 33123 can be moved up gradually, reach change tail rotor
33123 directions of motion, and then tail rotor 33123 is controlled to the thrust direction of unmanned plane, so that the direction of thrust is moved gradually downward.
When tail rotor 33123 gradually moves up, and it is moved to what tail rotor 33123 was moved relative to the first vertical pivot 53
When angle is 0 °.Tail rotor 33123 will be consistent with 11 direction of portion windward to the thrust direction of unmanned plane, and the thrust direction with
First horizontal axis 54 parallel (such as Fig. 7), the rotation of tail rotor 33123 at this time will provide the thrust of advance for unmanned plane, to make nothing
Man-machine thrust increases.
Tail rotor 33123 is moved to the left or right, below by way of two embodiments to tail rotor 33123 to the left or
It moves right and is described in detail respectively:
Fig. 5 and Fig. 7 are referred to, the first embodiment.If the rotation of first gear 50 drives second gear 51 clockwise
Rotation will drive tail rotor 33123 to move right since second gear 51 is fixedly connected with third steering engine 473.To realize
In flight, landing, tail rotor 33123 can gradually move right unmanned plane, reach 33123 side of moving of change tail rotor
To, and then tail rotor 33123 is controlled to the thrust direction of unmanned plane, so that the direction of thrust is gradually moved right.
Fig. 7 is referred to, is gradually moved right in tail rotor 33123, and it is perpendicular relative to first to be moved to tail rotor 33123
When the angle that axis 53 moves is 60 °.Tail rotor 33123 to the thrust direction of unmanned plane will to the left, at this time tail rotor 33123 turn
It is dynamic to provide thrust to the left for unmanned plane, change the thrust direction of unmanned plane, to change the stressing conditions of unmanned plane entirety.
Refer to Fig. 5, Fig. 7, second of embodiment.If the rotation of first gear 50 drives second gear 51 to turn counterclockwise
It is dynamic, since second gear 51 is fixedly connected with third steering engine 473, tail rotor 33123 will be driven to be moved to the left.To realize
In unmanned plane during flying, landing, tail rotor 33123 can be gradually moved to the left, and reach 33123 direction of motion of change tail rotor,
And then tail rotor 33123 is controlled to the thrust direction of unmanned plane, so that the direction of thrust is gradually moved right.
Fig. 7 is referred to, is gradually moved to the left in tail rotor 33123, and it is perpendicular relative to first to be moved to tail rotor 33123
When the angle that axis 53 moves is 0 °, tail rotor 33123 will be mutually perpendicular to the first horizontal axis 54.Tail rotor 33123 is to unmanned plane
Thrust direction will be towards portion 11 windward, i.e., to the direction of advance of unmanned plane, the rotation of tail rotor 33123 at this time will carry for unmanned plane
For the thrust of advance, the thrust direction of unmanned plane is changed, to make the thrust of unmanned plane increase.
Continuing with referring to Fig. 7, if tail rotor 33123 continues gradually to be moved to the left, and it is moved to 33123 phase of tail rotor
When angle for the movement of the first vertical pivot 53 is 60 °.Tail rotor 33123 will to the right to the thrust direction of unmanned plane, tailspin at this time
Thrust for unmanned plane to the right is changed the thrust direction of unmanned plane by the rotation of the wing 33123, to change unmanned plane it is whole by
Power situation.
In embodiment provided by the utility model, power source 40 may include:Engine 41, generator 42, voltage turn
Parallel operation 43, voltage-stablizer 44, accumulator 45, current divider 46, steering engine 47 and driving motor 48.Power source 40 can be fixed on the first machine
The outside of body 10, the second fuselage 20 or third fuselage 30;In-flight damage of the rainwater to power source 40 in order to prevent, power source
40 can also sealed set be either directly anchored to the inside of the first fuselage 10, the second fuselage 20 or third fuselage 30.Power
The effect in source 40 mainly provides power for flight, the landing of unmanned plane.
In embodiment provided by the utility model, in order to increase unmanned plane the landing stage thrust or increase nobody
Machine shortens the departure time of unmanned plane VTOL in the thrust of mission phase, and improves unmanned plane in flight course
Flight speed.The quantity of power source 40 can be positive integer in unmanned plane, i.e., the quantity of power source 40 can be:1,2,
3,4.
Fig. 2 is referred to, when the quantity of power source 40 is 2, two power sources 40 can symmetrically be distributed in the first machine
The left and right sides of body 10.Since unmanned plane is in landing, flight course, the fuselage of unmanned plane needs to bear multidirectional pressure,
Such as:Gravity, wind direction resistance, stream pressure of unmanned plane itself etc..And the pressure that the fuselage of unmanned plane is born is limited.
If two power sources 40 are all fixed on the left side either right side of the first fuselage 10 of the first fuselage 10, easily increase by first
The pressure that 10 left side of fuselage either the first fuselage, 10 right side is carried, to influence the stationarity of complete machine flight.If moreover,
The pressure that one fuselage, 10 left side either the first fuselage, 10 right side is carried is more than the limit of itself born pressure, will be occurred
The case where first fuselage, 10 left side either the first fuselage, 10 right side is broken.So in implementation provided by the utility model
In example, two power sources 40 are symmetrically distributed in the left and right sides of the first fuselage 10, unmanned plane itself flight can be improved
Stationarity, and can also prevent by the pressure that 10 left side of the first fuselage either the first fuselage, 10 right side is carried to be more than certainly
The limit of the born pressure of body, and there is a situation where 10 left side of the first fuselage either the first fuselage, 10 right sides to be broken.
Certainly, it is obvious to one skilled in the art that two power sources 40 can also symmetrically be distributed in the first machine
The left and right sides of body 10, the second fuselage 20 and third fuselage 30, and first can be symmetrically distributed in for two power sources 40
The left and right sides of fuselage 10 is only a kind of embodiment that the utility model embodiment provides, and is not the office to the utility model
Limit.In actual mechanical process, according to actual demand, the quantity for either reducing power source 40 can be increased or change power source
40 are located at the specific location of the first fuselage 10, the second fuselage 20 or third fuselage 30, these may also apply to the utility model.
Fig. 9 is referred to, further, engine 41 can be two stroke engine 41, and generator 42 connects with engine 41
It connects;Electric pressure converter 43 can be AC/DC converters, and electric pressure converter 43 is connect with generator 42;Voltage-stablizer 44 includes:First
Voltage stabilizing input port 441, the second voltage stabilizing input port 442 and the first voltage stabilizing delivery outlet 443, the first voltage stabilizing input port 441 turn with voltage
Parallel operation 43 connects, and makes electric pressure converter 43 between the first voltage stabilizing input port 441 and generator 42;Accumulator 45 and
Two voltage stabilizing input ports 442 connect;Current divider 46 can also include:First shunting input port 461, first shunts delivery outlet 462, the
Two shunting delivery outlets 463, third shunting delivery outlet 464 and the 7th shunt delivery outlet 468, the first shunting input port 461 and first
Voltage stabilizing delivery outlet 443 connects;Steering engine 47 includes at least:First steering engine 471, the second steering engine 472 and third steering engine 473, the first rudder
Machine 471 includes at least:First steering engine input port 4711 and the first rotor shaft 4712, the shunting of the first steering engine input port 4711 and first
Delivery outlet 462 connects, to provide energy, and the first rotor shaft 4712 and first of the first steering engine 471 for the first steering engine 471
Rotor 1211 connects, and is driven by the rotation of the first rotor shaft 4712, carrys out the rotation of the first rotor 1211;Second steering engine 472 wraps
It includes:Second steering engine input port 4721 and the second rotor shaft 4722;Second steering engine input port 4721 and second shunts delivery outlet 463 and connects
It connects, to provide energy for the second steering engine 472, and the second rotor shaft 4722 of the second steering engine 472 and the second rotor 1221 connect
It connects, by the rotation of the second rotor shaft 4722, to drive the rotation of the second rotor 1221;Third steering engine 473 further includes:Third rudder
Machine input port 4733, third steering engine input port 4733 is connect with the 7th shunting delivery outlet 468, to be provided for third steering engine 473
Energy.Driving motor 48 includes at least:First driving motor 481, the first driving motor 481 connect with third shunting delivery outlet 464
It connects, the rotor mechanism 331 of adjustable angle is connect with the first driving motor 481, and makes the first driving motor 481 positioned at third point
It flows between delivery outlet 464 and the rotor mechanism 331 of adjustable angle.
Specifically, engine 41 is to convert other forms to mechanical energy;Generator 42 is to produce engine 41
Raw mechanical energy is converted into electric energy;Voltage-stablizer 44 is to maintain the electric energy caused by generator 42 and is exported after voltage-stablizer 44 surely
Fixed voltage, and accumulator 45 is also connect with voltage-stablizer 44.The effect being connect with voltage-stablizer 44 for accumulator 45 is:Electric power storage
Pond 45 can be that voltage-stablizer 44 provides electric energy, and voltage-stablizer 44 makes the electric energy generated by accumulator 45 be exported after voltage-stablizer 44 surely
Fixed voltage;And if engine 41 or generator 42 break down, and electric energy can not be provided for unmanned plane, and it at this time can be automatic
It is switched to the power supply of accumulator 45, electric energy is provided for unmanned plane by accumulator 45;If engine 41 or generator 42 can normal works
Make, electric energy can be provided for unmanned plane, then accumulator 45 stops providing electric energy for unmanned plane;Certainly, if electricity occurs in accumulator 45
Power is insufficient, can not provide electric energy for unmanned plane, can be by engine 41 by the normal work of engine 41 or generator 42
Or generator 42 is that accumulator 45 provides electric energy, to supplement the electric energy of accumulator 45.
If it is that voltage-stablizer 44 provides electric energy that engine 41 and generator 42, which is only arranged, when engine 41 or generator 42 occur
Failure, when can not provide electric energy for unmanned plane, unmanned plane in landing or in-flight will be faced with no power resources, and send out
The danger of the raw damage unmanned plane that falls;Or only setting accumulator 45 is that voltage-stablizer 44 provides electric energy, when electricity occurs in accumulator 45
The failures such as energy deficiency, when can not provide electric energy for unmanned plane, unmanned plane in landing or in-flight will be faced with no power
Source, and the danger for the damage unmanned plane that falls.So be that voltage-stablizer 44 provides electric energy by engine 41 and generator 42, with
And accumulator 45 is that voltage-stablizer 44 provides electric energy, and it is voltage-stablizer 44 that this accumulator 45 can mutually switch with generator 42
Electric energy is provided, can overcome unmanned plane awing since generator 42 breaks down or accumulator 45 breaks down, it can not
Electric energy is provided for unmanned plane, makes unmanned plane that will be faced with no power resources, and the technological deficiency for the damage unmanned plane that falls,
Reach the safety for improving unmanned plane, in-flight the technique effect of the stability of power.
Meanwhile the burning voltage that electric pressure converter 43 is exported will enter current divider 46, each shunting of current divider 46 is defeated
Outlet be electric energy is assigned to each steering engine 47 or driving motor 48, such as:First shunting delivery outlet 462 and the first steering engine
471 input ports connect, to provide energy for the first steering engine 471;Second shunting delivery outlet 463 and the second steering engine input port 4721
Connection, to provide energy for the second steering engine 472;Third shunting delivery outlet 464 connect with the first driving motor 481, to for
First driving motor 481 provides energy.
In embodiment provided by the utility model, engine 41 can be two-stroke aviation piston engine 41, i.e., living
Plug from top to bottom, the engine 41 of two strokes from top to bottom, due to two stroke engine 41 have it is simple in structure, weight compared with
Gently, moving component lacks easy to maintain, the big advantage of power per liter density, to be suitble to low latitude, high speed (the utility model of unmanned plane
The unmanned plane F-Zero of the embodiment of offer can be 60m/s) flight.Electric pressure converter 43 can be AC/DC converters,
AC/DC converters are the equipment that alternating current is become to direct current, and there is AC/DC converters the alternating current-direct current of better stability to turn
It changes, stable DC can be provided for unmanned plane, from the stability for improving unmanned mechanomotive force.
Certainly, it is obvious to one skilled in the art that engine 41 can also be started using four stroke aviation pistons
Machine 41.In actual mechanical process, the shunting delivery outlet of current divider 46 can also be arranged according to actual demand, such as:If nothing
Video camera, automatic flight control system, current divider 46 or video camera, automatic flight control system point are provided on man-machine
With electric energy, the mode (including being the mode of steering engine 47, the distribution electric energy of driving motor 48 above) of the distribution electric energy can be passed through
Conducting wire connects or uses wireless power transmission, these may also apply to the utility model.
Fig. 8 is referred to, Fig. 8 is the generator 42 that the utility model embodiment provides and the signal of 41 connection relation of engine
Figure.The generator 42 may include rotor 61 and supply port, and the rotor 61 of the generator 42 can the direct and hair
The output shaft 60 of motivation 41 is fixedly connected, and the electric machine casing 62 of generator 42 can be fixed directly with the end face of 41 shell of engine
Connection.And the electric pressure converter can with the supply port of the generator 42 (supply port be generator 42 electricity
Energy output end) connection;Wherein, the rotor 61 can be between the supply port and the output shaft 60.Engine 41
When rotation, mechanical energy caused by engine 41 can be directly passed to generator 42 by the output shaft 60 of engine 41
Rotor 61 then drives the rotor 61 of generator 42 to rotate together, and is turned by the mechanical energy that generator 42 generates engine 41
Electric energy is turned to, the electric energy of the conversion exports outward from the supply port of generator 42.
The electric energy that the supply port of generator 42 exports outward can be delivered to power unit, which has
Distribute the power to the function of different electrical appliances.What the power distribution unit can export the supply port of generator 42 outward
Electric energy is divided into two parts (abbreviation E1 and E2), and the electric energy of the parts E1 can be delivered to battery (can be accumulator), which can
Required electric energy when carrying out VTOL to be provided for aircraft;The electric energy of the parts E2 can be conveyed to the winged control system of aircraft respectively
The uses such as system, steering engine, motor, load.
Since the mechanical energy that engine 41 generates can be directly passed to the rotor 61 of generator 42 by output shaft 60, and
And the mechanical energy that engine 41 generates can be converted to electric energy by generator 42, then electric energy is conveyed to by conducting wire winged
Electrical appliance in machine.To which the energy that engine 41 generates is converted into conveying by conducting wire by generator 42, to avoid
Loss in produced by conveying engine 41 energy process.It should be noted that:Such as above-mentioned first fuselage 10, second
Fuselage 20 and third fuselage 30, the integral body of the provided unmanned plane of embodiment provided by the utility model be by:First fuselage
10, the second fuselage 20 and third fuselage 30 and form.The fuselage can also include the circuit control system of following unmanned plane, pass through
The circuit control system of unmanned plane carries out the unmanned plane whole control.
Fig. 9 is referred to, further, in embodiment provided by the utility model, unmanned plane circuit control system can
To include at least:Ground remote control device 56, flight control system 55, engine 41, generator 42, electric pressure converter 43, voltage-stablizer
44, accumulator 45, current divider 46, the first steering engine 471, the second steering engine 472, third steering engine 473, the first driving motor 481, second
Driving motor 482, third driving motor 483, the 4th driving motor 484.Wherein, engine 41, generator 42, voltage are turned
Parallel operation 43, voltage-stablizer 44, accumulator 45, current divider 46, the first steering engine 471, the second steering engine 472, third steering engine 473, first drive
Dynamic motor 481, the second driving motor 482, third driving motor 483 and the 4th driving motor 484, as described above in Example.
The ground remote control device 56 on flight control system 55 and ground carries out signal transmission, and then by being controlled from ground remote control device 56 to flight
System 55 processed sends control instruction, and by flight control system 55 control the first steering engine 471 of unmanned plane, the second steering engine 472,
Third steering engine 473, the first driving motor 481, the second driving motor 482, third driving motor 483 and the 4th driving motor 484
Working condition, and then realize the state of unmanned plane landing, flight is controlled.
It is noted that flight control system 55 mainly passes through turn of the first rotor 1211 in the first steering engine 471 of control
In dynamic speed, the second steering engine 472 in the velocity of rotation of second rotor 1221, third steering engine 473 velocity of rotation of third rotor and
It controls the first driving motor 481 and pulls linkage portion 3312, and then control tail rotor 33123 and moved up and down relative to the first vertical pivot 53
The angle change of constituted angle, and the first driving motor 481 of control drive second gear 51 to rotate, and then control tail rotor
33123 move left and right the angle change of constituted angle relative to the first vertical pivot 53.Reach and is controlled by flight control system 55
The motion state to unmanned plane landing, flight is made, and controls the movement speed of unmanned plane landing, flight.
Advantageous effect:
The utility model provides a kind of fuselage device applied to unmanned plane, by consolidating the second ontology and second connecting portion
The first postposition wing is arranged, after being arranged second in the second side of the second ontology in fixed connection in the first side of the second ontology
Wing is set, vertical stabilizer is set on the third side of the second ontology, in-flight air-flow can be weakened, the anti-of unmanned plane is done.Due to
Third interconnecting piece and the second ontology are fixedly connected, and second connecting portion, the second ontology and third interconnecting piece can be integrally formed composition
Fuselage, the second connecting portion in fuselage can be detachably connected with first connecting portion.Then unmanned plane is made some portion of damage occur
When hindering, the fuselage of the part can be replaced.To reach the fuselage maintenance cost for reducing unmanned plane, the anti-of unmanned plane is promoted
The technique effect of interference performance.
It should be noted last that the above specific implementation mode is only to illustrate the technical solution of the utility model rather than limit
System, although the utility model is described in detail with reference to example, it will be understood by those of ordinary skill in the art that, it can be right
The technical solution of the utility model is modified or replaced equivalently, without departing from the spirit and model of technical solutions of the utility model
It encloses, should all cover in the right of the utility model.
Claims (10)
1. a kind of fuselage device applied to unmanned plane, which is characterized in that a kind of fuselage device packet applied to unmanned plane
It includes:
Second connecting portion, the second connecting portion and first connecting portion are detachably connected;
Second ontology, second ontology are fixedly connected with the second connecting portion;And second ontology include first side,
Second side and third side, and the first side and the second side are symmetrically divided along the center vertical pivot of second ontology
Cloth, the third side is between the first side and the second side;And it is provided with first in the first side
Postposition wing is provided with the second postposition wing in the second side, vertical stabilizer is provided on the third side;
Third interconnecting piece, the third interconnecting piece are fixedly connected with second ontology;
Wherein, second ontology is between the second connecting portion and the third interconnecting piece, and the second connecting portion,
Second ontology and the third interconnecting piece, which are integrally formed, constitutes the fuselage.
2. a kind of fuselage device applied to unmanned plane as described in claim 1, it is characterised in that:
The first postposition wing includes fastening end and the first rear open end after first;
Wherein, after described first fastening end and first rear open end be the first postposition wing both ends.
3. a kind of fuselage device applied to unmanned plane as claimed in claim 2, it is characterised in that:
The second postposition wing includes fastening end and the second rear open end after second;
Wherein, after described second fastening end and second rear open end be the second postposition wing both ends.
4. a kind of fuselage device applied to unmanned plane as claimed in claim 3, it is characterised in that:
Fastening end is symmetrically fixedly installed along the center vertical pivot of second ontology behind fastening end and described second after described first
In the both sides of second ontology.
5. a kind of fuselage device applied to unmanned plane as claimed in claim 4, which is characterized in that described a kind of applied to nothing
Man-machine fuselage device further includes:
First aileron, the setting of the first aileron rotation is in first rear open end, and first aileron is described
It is rotated relative to first rear open end in first rear open end.
6. a kind of fuselage device applied to unmanned plane as claimed in claim 5, which is characterized in that described a kind of applied to nothing
Man-machine fuselage device further includes:
Second aileron, the setting of the second aileron rotation is in second rear open end, and second aileron is described
It is rotated relative to second rear open end in second rear open end.
7. a kind of fuselage device applied to unmanned plane as claimed in claim 6, which is characterized in that described a kind of applied to nothing
Man-machine fuselage device further includes:
Third aileron, the setting of the third aileron rotation is on the vertical stabilizer, and the third aileron is described vertical
It is rotated relative to the vertical stabilizer on wing.
8. a kind of fuselage device applied to unmanned plane as claimed in claim 7, it is characterised in that:
First postposition wing fastening end after described first subtracts successively along the width on first rear open end direction
It is small.
9. a kind of fuselage device applied to unmanned plane as claimed in claim 8, it is characterised in that:
Second postposition wing fastening end after described second subtracts successively along the width on second rear open end direction
It is small.
10. a kind of fuselage device applied to unmanned plane as claimed in claim 9, it is characterised in that:First aileron, institute
It states the second aileron and the third aileron is rectangle.
Priority Applications (1)
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CN201721641752.1U CN207748003U (en) | 2017-11-30 | 2017-11-30 | Fuselage device applied to unmanned plane |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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CN201721641752.1U CN207748003U (en) | 2017-11-30 | 2017-11-30 | Fuselage device applied to unmanned plane |
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CN207748003U true CN207748003U (en) | 2018-08-21 |
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ID=63147358
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CN201721641752.1U Expired - Fee Related CN207748003U (en) | 2017-11-30 | 2017-11-30 | Fuselage device applied to unmanned plane |
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2017
- 2017-11-30 CN CN201721641752.1U patent/CN207748003U/en not_active Expired - Fee Related
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