CN108313263A - Fuselage dynamical system for fixed-wing unmanned plane - Google Patents
Fuselage dynamical system for fixed-wing unmanned plane Download PDFInfo
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- CN108313263A CN108313263A CN201810079373.0A CN201810079373A CN108313263A CN 108313263 A CN108313263 A CN 108313263A CN 201810079373 A CN201810079373 A CN 201810079373A CN 108313263 A CN108313263 A CN 108313263A
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- unmanned plane
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- 238000005183 dynamical system Methods 0.000 title claims abstract description 46
- 230000005611 electricity Effects 0.000 claims abstract description 61
- 238000006073 displacement reaction Methods 0.000 claims abstract description 10
- 230000001105 regulatory effect Effects 0.000 claims abstract description 10
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 46
- 238000000034 method Methods 0.000 abstract description 20
- 230000000694 effects Effects 0.000 abstract description 18
- 230000007246 mechanism Effects 0.000 description 36
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 11
- 238000010586 diagram Methods 0.000 description 10
- 230000006378 damage Effects 0.000 description 9
- 230000033001 locomotion Effects 0.000 description 7
- 230000001276 controlling effect Effects 0.000 description 6
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- 230000008439 repair process Effects 0.000 description 4
- 239000007787 solid Substances 0.000 description 4
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- 241000734468 Listera Species 0.000 description 2
- 230000001174 ascending effect Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
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- 230000035939 shock Effects 0.000 description 2
- 230000033228 biological regulation Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/16—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like specially adapted for mounting power plant
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention discloses a kind of fuselage dynamical systems for fixed-wing unmanned plane, belong to air vehicle technique field, including head and dynamical system, and head includes the first front end, the first noumenon and the first rear end；Dynamical system includes power supply part, displacement component, driving part and regulating member.Power supply part is provided with the first delivery outlet, the second delivery outlet, third delivery outlet and the 4th delivery outlet；Displacement component includes the first steering engine and the second steering engine, and the first steering engine is provided with the first input port；Second steering engine is provided with the second input port；Driving part includes first motor and the second motor, and first motor is provided with third input port, and the second motor is provided with the 4th input port；Regulating member includes that first the second electricity of electricity reconciliation is adjusted, and the first electricity, which is adjusted, is provided with the 5th input port and the 5th delivery outlet.Invention achieves the cruise duration for increasing unmanned plane, meet the needs of each electrical appliance of unmanned plane is to the energy, improve the technique effect of the practicability of unmanned plane.
Description
Technical field
The invention belongs to air vehicle technique fields, more particularly to a kind of fuselage dynamical system for fixed-wing 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.
For fixed-wing unmanned plane, unmanned aerial vehicle body in the prior art using integrally formed structure fabrication and
At head mainly uses cylindrical structure, cylindrical head that can both accommodate the various electric elements needed for unmanned plane, and also might be used
To load more article inside head.But it is in flight course in unmanned plane, the head of unmanned plane and rubbing for air-flow
It is larger to wipe resistance, then reduces cruise duration, understands the power source of severe attrition aircraft, and to the normal flight of unmanned plane
It will produce interference.Meanwhile the dynamical system of unmanned plane is mainly connected by accumulator with the various electric elements of unmanned plane, is passed through
The accumulator being arranged on unmanned plane provides electric energy for the various electrical appliances on unmanned plane.But unmanned plane is in landing and flight
In demand of each electrical appliance to electric energy it is all larger, therefore cannot be satisfied demand of the unmanned plane to different electric energy so that unmanned plane
Cruise duration it is short, poor practicability.
In conclusion in the prior art, the fuselage of unmanned plane can reduce the cruise duration of unmanned plane；Also it cannot be satisfied nothing
Demand of the man-machine each electrical appliance to the energy, the poor practicability of unmanned plane.
Invention content
The technical problem to be solved by the present invention is to the cruise duration that the fuselage of unmanned plane can reduce unmanned plane；Also can not expire
Demand of the sufficient each electrical appliance of unmanned plane to the energy, the poor practicability of unmanned plane.
In order to solve the above technical problems, the present invention provides a kind of fuselage dynamical system for fixed-wing unmanned plane, institute
It states and includes for the fuselage dynamical system of fixed-wing unmanned plane：Head, the head include：First front end, before described first
The tapered structure in end；The first noumenon, the first noumenon are fixedly connected with first front end, and first front end
Diameter of section be sequentially increased on the direction towards the first noumenon；First rear end, first rear end and described
The first noumenon is fixedly connected, and the diameter of section of the first noumenon increases successively on the direction towards first rear end
Greatly；
Wherein, the first noumenon is arranged between first front end and first rear end, and described first
Front end, the first noumenon and first rear end, which are integrally formed, constitutes the head；Dynamical system, the dynamical system
Including：Power supply part, the power supply part are provided with the first delivery outlet, the second delivery outlet, third delivery outlet and the 4th delivery outlet；
Displacement component, the displacement component include the first steering engine and the second steering engine, and first steering engine is provided with the first input port, described
First input port is connected with first delivery outlet；Second steering engine is provided with the second input port, second input port and
The second delivery outlet connection；Driving part, the driving part include first motor and the second motor, and the first motor is set
It is equipped with third input port, second motor is provided with the 4th input port；Regulating member, the regulating member include that the first electricity is adjusted
It is adjusted with the second electricity, first electricity, which is adjusted, is provided with the 5th input port and the 5th delivery outlet, the 5th input port and the third
Delivery outlet connects, and the 5th delivery outlet is connected with the third input port；It is described second electricity adjust be provided with the 6th input port and
6th delivery outlet, the 6th input port are connected with the 4th delivery outlet, the 6th delivery outlet and the 4th input port
Connection.
Further, the fuselage dynamical system for fixed-wing unmanned plane includes：The first motor is provided with
One drive shaft and first base, first drive shaft are fixedly connected with the first propeller, the first base and the first pedestal
It is fixedly connected.
Further, the fuselage dynamical system for fixed-wing unmanned plane includes：Second motor is provided with
Two drive shafts and second base, the second base are fixedly connected with second end, and second drive shaft and the first rotor are fixed
Connection；Wherein, the rotational plane of second drive shaft and first rotor is perpendicular.
Further, the power supply part further includes the 6th delivery outlet；The driving part further includes third motor, described
Third motor is provided with the 7th input port, and the 7th input port is connected with the 6th delivery outlet.
Further, the third motor is provided with third drive shaft and third pedestal, the third drive shaft and second
Propeller is fixedly connected, and the third pedestal and the second pedestal are fixedly connected.
Further, the power supply part further includes the 7th delivery outlet；The driving part further includes the 4th motor, described
4th motor is provided with the 8th input port, and the 8th input port is connected with the 7th delivery outlet.
Further, the fuselage dynamical system for fixed-wing unmanned plane includes：4th motor is provided with
Four drive shafts and the 4th pedestal, the 4th pedestal and the 4th end are fixedly connected, and the 4th drive shaft and the second rotor are fixed
Connection；Wherein, the rotational plane of the 4th drive shaft and second rotor is perpendicular.
Further, the fuselage dynamical system for fixed-wing unmanned plane includes：First steering engine includes first
Shaft and the first fastening seat, the first rotating shaft are connected with first pedestal, and the first fastening seat and the first limiting slot are solid
Fixed connection；Wherein, the first rotating shaft is arranged between first pedestal and first limiting slot.
Further, the fuselage dynamical system for fixed-wing unmanned plane includes：Second steering engine includes second
Shaft and the second fastening seat, second shaft are connected with second pedestal, and the second fastening seat and the second limiting slot are solid
Fixed connection；Wherein, second shaft is arranged between second pedestal and second limiting slot.
Advantageous effect：
The present invention provides a kind of fuselage dynamical system for fixed-wing unmanned plane, and the diameter of section of the first noumenon is designed
To be sequentially increased on the direction towards the first rear end, the diameter of section of the first noumenon is designed as towards after described first
It is sequentially increased on the direction of end, resistance of the air-flow to unmanned plane can be effectively reduced.Meanwhile by by the first of power supply part
First input port of delivery outlet and the first steering engine connects, and the second delivery outlet of power supply part and the second input port of the second steering engine connect
It connects；The 5th input port connection that the third delivery outlet of power supply part and the first electricity are adjusted, the 5th delivery outlet and first that the first electricity is adjusted
The third input port of motor connects；The 6th input port connection that 4th delivery outlet of power supply part and the second electricity are adjusted, the second electricity are adjusted
The 6th delivery outlet and the second motor the 4th input port connection；Then it is the first steering engine, the second steering engine, first motor and second
Motor provides the energy of different size demand, meets the normal work of the first steering engine, the second steering engine, first motor and the second motor
Make, unmanned plane is allow normally to be lifted and be flown.To reach the cruise duration for increasing unmanned plane, it is each to meet unmanned plane
Demand of the electrical appliance to the energy, improves the technique effect of the practicability of unmanned plane.
Description of the drawings
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the present invention
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached drawings.
Fig. 1 is a kind of overall structure diagram of fixed-wing unmanned plane provided in an embodiment of the present invention；
Fig. 2 provides a kind of top view illustration of fixed-wing unmanned plane for the embodiment of the present invention；
Fig. 3 provides a kind of upward view schematic diagram of fixed-wing unmanned plane for the embodiment of the present invention；
Fig. 4 provides a kind of side view schematic diagram of fixed-wing unmanned plane for the embodiment of the present invention；
Fig. 5 provides a kind of front view schematic diagram of fixed-wing unmanned plane for the embodiment of the present invention；
Fig. 6 provides a kind of structure diagram of the dynamical system of fixed-wing unmanned plane for the embodiment of the present invention；
Description of the drawings：
100-heads, the 110-the first front end, 120-the first noumenons, the 130-the first rear end, 140-pitots；
200-fuselages, the 210-the second front end, the 220-the second ontology, the 230-the first wing, the 240-the second wing,
250-the first adjustable rotary wing mechanism, the 251-the first linking arm, the 252-the first propeller, 253-the first verts component,
254-the first rotor, the 255-the first limiting slot, the 260-the second adjustable rotary wing mechanism, the 261-the second linking arm, 262-the
Two propellers, 263-the second verts component, the 264-the second rotor, the 265-the second limiting slot, the 270-the second rear end,
280-the first aileron, the 290-the second aileron；
300-tails, 310-third front ends, 320-third ontologies, 330-third rear ends, the 340-the first aerofoil
Plate, the 350-the second aerofoil plate；
400-dynamical systems, 410-power supply parts, 420-displacement components, the 421-the first steering engine, the 422-the second rudder
Machine, 430-driving parts, 431-first motors, the 432-the second motor, 433-third motors, the 434-the four motor,
440-regulating members, the 441-the first electricity are adjusted, and the 442-the second electricity is adjusted.
Specific implementation mode
The present invention provides a kind of fuselage dynamical system for fixed-wing unmanned plane, and the diameter of section of the first noumenon is designed
To be sequentially increased on the direction towards the first rear end, the diameter of section of the first noumenon is designed as towards after described first
It is sequentially increased on the direction of end, resistance of the air-flow to unmanned plane can be effectively reduced.Meanwhile by by the first of power supply part
First input port of delivery outlet and the first steering engine connects, and the second delivery outlet of power supply part and the second input port of the second steering engine connect
It connects；The 5th input port connection that the third delivery outlet of power supply part and the first electricity are adjusted, the 5th delivery outlet and first that the first electricity is adjusted
The third input port of motor connects；The 6th input port connection that 4th delivery outlet of power supply part and the second electricity are adjusted, the second electricity are adjusted
The 6th delivery outlet and the second motor the 4th input port connection；Then it is the first steering engine, the second steering engine, first motor and second
Motor provides the energy of different size demand, meets the normal work of the first steering engine, the second steering engine, first motor and the second motor
Make, unmanned plane is allow normally to be lifted and be flown.To reach the cruise duration for increasing unmanned plane, it is each to meet unmanned plane
Demand of the electrical appliance to the energy, improves the technique effect of the practicability of unmanned plane.
In order to elaborate to a kind of fuselage dynamical system for fixed-wing unmanned plane provided by the invention, to support
The technical problems to be solved by the invention first do specifically fixed-wing unmanned plane in the following, in embodiment provided by the invention
It is bright, then during describing fixed-wing unmanned plane, further targetedly draw provided by the invention a kind of for solid
The fuselage dynamical system for determining wing unmanned plane is complete, clear, clear to achieve the purpose that.
Before introducing the embodiment of the present invention, the overall condition of fixed-wing unmanned plane provided by the invention is done first as follows
Summarize：The present invention is by being divided into the fuselage 200 of unmanned plane including at least three sections, i.e. head 100, fuselage 200 and tail
300, and be attached by the connection type of detachable connection between three sections, it is dismountable to be constituted an internal structure with this
Fixed-wing unmanned plane, so that when there is local damage in the fuselage 200 of unmanned plane, can corresponding dismounting occur damaging
Position repairs, and has simple, convenient technique effect.And when the part of fuselage 200 can not due to damaging
When reparation, can also the position that can not repair of corresponding dismounting, i.e., the position that can not be repaired is substituted, to overcome
In the prior art because fuselage 200 is using integrated global design so that when 200 local damage of fuselage occur can not repair, no
It must be changed without the technological deficiency of the entire fuselage 200 of unmanned plane, reach the technique effect for significantly reducing maintenance cost.
Also, unmanned plane is during executing landing operation, the setting included by fixed-wing unmanned plane in the present invention
The first adjustable rotary wing mechanism 250 on the first wing 230, and the second adjustable rotor for being arranged on the second wing 240
Mechanism 260 carries out matching operation (being operated) and generates lifting force, and fuselage 200 is pulled to rise or decline.Such as：Work as nothing
It is man-machine when taking off, it pushes first to vert component 253 by the first steering engine 421 controlled in the first adjustable rotary wing mechanism 250, makes
First propeller 252 is located in the plane with unmanned plane level, drives the work of the first propeller 252 by first motor 431, makes
First propeller 252 provides lift for unmanned plane；It controls the second steering engine 422 in the second adjustable rotary wing mechanism 260 and pushes the
Two vert component 263, make the second propeller 262 be located at and the plane of unmanned plane level in, pass through the drive of third motor 433 second
Propeller 262 works, and so that the second propeller 262 is also provided lift for unmanned plane, by the first propeller 252 and the second propeller
Resultant force, upward lifting force is provided for unmanned plane, to realize taking off vertically for unmanned plane caused by 262 rotation.By nothing
It is man-machine when drawing high certain altitude, then push first to vert component 253 by the first steering engine 421, so that the first propeller 252 is located at
With the plane of unmanned plane level in perpendicular plane, pushes second to vert component 263 by the second steering engine 422, make the second spiral shell
It revolves in the plane that paddle 262 is located at and the plane of unmanned plane level is perpendicular, to generate horizontal thrust on unmanned plane, pushes nothing
Man-machine slide in the air is taken off, and then enters stabilized flight.When declining, first is pushed to vert by controlling the first steering engine 421
Component 253, make the first propeller 252 be located at and the plane of unmanned plane level in, verted portion by the second steering engine 422 promotion second
Part 263 makes the second propeller 262 be located in the plane with unmanned plane level, makes 252, the first propeller and the second propeller
262 pull fuselage 200 to stablize decline from eminence, until stablizing landing, avoid fuselage 200 caused by 200 hard landing of fuselage
With the damage of carrying equipment, the risk of landing accident is greatly reduced, having reached makes unmanned plane be suitble in different flying fields
Carry out the technique effect of landing operation.
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation describes, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, the every other embodiment that those of ordinary skill in the art are obtained belong to what the present invention protected
Range；Involved "and/or" keyword wherein in this implementation, indicate and or two kinds of situations, in other words, the present invention is implemented
A and/or B mentioned by example, illustrate two kinds of A and B, A or B situations, describe three kinds of states present in A and B, such as A and/or
B is indicated：It includes B to only include A not；It includes A to only include B not；Including A and B.
Meanwhile in the embodiment of the present invention, when component is referred to as " being fixed on " another component, it can be directly at another
On component or there may also be components placed in the middle.When a component is considered as " connection " another component, it can be direct
It is connected to another component or may be simultaneously present component placed in the middle.When a component is considered as " being set to " another group
Part, it can be set up directly on another component or may be simultaneously present component placed in the middle.Made in the embodiment of the present invention
Term " vertically ", " horizontal ", "left", "right" and similar statement are merely for purposes of illustration, and are not intended to
The limitation present invention.
In order to which fixed-wing unmanned plane provided in an embodiment of the present invention is described in detail, first to the embodiment of the present invention
In involved technical term do description below explanation：
Detachable connection can be：It is bolted or is bonded；
Being fixedly connected to be：Welding is integrally formed；
Ground can be：The ground that unmanned plane is parked, or the face with this plane parallel；
Minimum flying speed can be：Minimum flying speed when making unmanned plane keep flight, and not falling.Such as：
In the present embodiment, the minimum flying speed of unmanned plane can be 20m/s；
Takeoff phase can be：Unmanned plane reaches the process of aerial vertical ascent from ground；
Take off winged stage that flattens can be：After unmanned plane reaches in the air, the process of horizontal flight is carried out；
Landing phases can be：Process of the unmanned plane from airborne to ground.
Fig. 1 is referred to, Fig. 1 is a kind of overall structure diagram of fixed-wing unmanned plane provided in an embodiment of the present invention.This
A kind of fixed-wing unmanned plane that inventive embodiments provide.A kind of fixed-wing unmanned plane includes head 100, fuselage 200, tail 300
With dynamical system 400, following detailed description is now carried out respectively to head 100, fuselage 200, tail 300 and dynamical system 400：
For head 100：
Head 100 may include the first front end 110, the first noumenon 120 and the first rear end 130.First front end 110
It can be rendered as pyramidal structure, pitot 140 can be fixedly connected on the first front end 110；The first noumenon 120 can be with
First front end 110 is fixedly connected, and the diameter of section of the first front end 110 on the direction towards the first noumenon 120 according to
Secondary increase；First rear end 130 can be fixedly connected with the first noumenon 120, and the diameter of section of the first noumenon 120 is in direction
It is sequentially increased on the direction of first rear end 130；Wherein, the first noumenon 120 is arranged in the first front end 110 and the first rear end
Between 130, and the first front end 110, the first noumenon 120 and the first rear end 130 are integrally formed and constitute head 100.
Continuing with the overall structure signal for referring to Fig. 1, Fig. 1 being a kind of fixed-wing unmanned plane provided in an embodiment of the present invention
Figure.First front end 110 can be fixedly connected with the first noumenon 120, and the first rear end 130 can be fixed with the first noumenon 120
Connection, to be made of the head 100 of unmanned plane the first front end 110, the first noumenon 120 and the first rear end 130.Unmanned plane
Head 100 can be rendered as hollow structure, i.e., the sky for the electric elements for placing camera can be accommodated in the inside of head 100
Between.It can be provided with pitot 140 on the first front end 110.Pitot 140 is also Pitot tube, stagnation pressure tube etc., pitot
140 be experience the stagnation pressure (also referred to as total head) and static pressure of air-flow, and by the pressure data measured send to air data computer,
The device of flying instruments.Pitot 140 is primarily used to measure flying speed, while can also have both other multiple functions.
Since the diameter of section of the first front end 110 is sequentially increased on the direction towards the first noumenon 120, the first noumenon
120 diameter of section is sequentially increased on the direction towards the first rear end 130, and the first front end 110 is rendered as taper
Structure.So that 100 overall construction of head of unmanned plane, can be in flight course in unmanned plane, effectively reduce air-flow to nothing
Man-machine obstruction moves loss of energy to reduce unmanned plane itself, can improve the cruise duration of unmanned plane.
For fuselage 200：
Fuselage 200 may include the second front end 210, the second ontology 220 and the second rear end 270.Second front end 210
It is detachably connected with first rear end 130, the second ontology 220 is fixedly connected with the second front end 210, the second rear end
270 are fixedly connected with second ontology 220, and the diameter of section of second ontology 220 is towards second rear end 270
Direction on be sequentially reduced.
Second ontology 220 may include first side and second side, and the first wing 230 is provided in first side, the
The second wing 240 is provided on two side faces, and the first wing 230 and the second wing 240 are perpendicular along the center of the second ontology 220
The axisymmetric both sides for being distributed in the second ontology 220；It is provided with the first adjustable rotary wing mechanism 250 on first wing 230, second
The second adjustable rotary wing mechanism 260 is provided on wing 240.
Second ontology 220 is arranged between the second front end 210 and the second rear end 270, and the second front end 210,
Second ontology 220 and the second rear end 270, which are integrally formed, constitutes the fuselage 200；
First wing 230 may include the first preceding fastening end, the first forward open end and the first positioning area, the first preceding fastening end
It is fixedly connected with first side, and the first positioning area is arranged between the first preceding fastening end and the first forward open end；Wherein,
One forward open end and the first preceding fastening end are the both ends of first wing 230.
Fuselage 200 can also include the first linking arm 251 and the second linking arm 261.First linking arm 251 includes first
End, second end and the first interlude, the first interlude and the first positioning area are detachably connected；First end and second end is described
The both ends of one linking arm 251.First adjustable rotary wing mechanism 250 may include the first propeller 252, first motor 431, first
Vert component 253, the first steering engine 421.First motor 431 is provided with the first drive shaft and first base, the first drive shaft and
One propeller 252 is fixedly connected；First vert component 253 include the first pedestal and the first limiting slot 255, the first pedestal and first
Pedestal is fixedly connected, and the first limiting slot 255 is fixedly connected with first end, and the first limiting slot 255 and the first pedestal are hinged,
First pedestal is arranged between the first limiting slot 255 and first base；First steering engine 421 includes first rotating shaft and the first fastening
Seat, first rotating shaft are connected with the first pedestal, and the first fastening seat and the first limiting slot 255 are fixedly connected, and first rotating shaft is arranged
Between the first pedestal and the first limiting slot 255；Wherein, the rotational plane of the first drive shaft and the first propeller 252 is perpendicular.
Fuselage 200 can also include the first rotor 254 and the second motor 432.Second motor 432 is provided with the second drive shaft
And second base, second base are fixedly connected with second end, the second drive shaft is fixedly connected with the first rotor 254；Described second
The rotational plane of drive shaft and first rotor 254 is perpendicular.
Second wing 240 may include the second preceding fastening end, the second forward open end and the second positioning area, the second preceding fastening end
It is fixedly connected with second side, and the second positioning area is arranged between the second preceding fastening end and the second forward open end；Before second
Open end and the second preceding fastening end are the both ends of second wing 240.
Second linking arm 261 may include third end, the 4th end and the second interlude, the second interlude and the second positioning area
It is detachably connected；Third end and the 4th end are the both ends of second linking arm 261.Second adjustable rotary wing mechanism 260 can be with
It verts component 263 and the second steering engine 422 including the second propeller 262, third motor 433, second.Third motor 433 is provided with
Third drive shaft and third pedestal, third drive shaft are fixedly connected with the second propeller 262；Second component 263 that verts can wrap
The second pedestal and the second limiting slot 265 are included, the second pedestal is fixedly connected with third pedestal, and the second limiting slot 265 and third end are solid
Fixed connection, and the second limiting slot 265 and the second pedestal are hinged, the setting of the second pedestal is in the second limiting slot 265 and described the
Between three pedestals；Second steering engine 422 may include the second shaft and the second fastening seat, and the second shaft is connected with the second pedestal, the
Two fastening seats and the second limiting slot 265 are fixedly connected, and the setting of the second shaft the second pedestal and the second limiting slot 265 it
Between；The rotational plane of third drive shaft and second propeller 262 is perpendicular.
Fuselage 200 can also include the second rotor 264 and the 4th motor 434.4th motor 434 is provided with the 4th drive shaft
With the 4th pedestal, the 4th pedestal and the 4th end are fixedly connected, and the 4th drive shaft is fixedly connected with the second rotor 264；4th driving
The rotational plane of axis and second rotor 264 is perpendicular.
Fuselage 200 can also include first end flank and/or the second end flank.
The angle of first end flank and the first wing 230 can be 60 ° -90 °.First end flank may include first
Wing tip fastening end and the first wing tip open end；And the first wing tip fastening end is fixedly connected with the first forward open end, the first wing tip
Open end constitutes the both ends of first end flank away from the first forward open end and the first wing tip fastening end.
The angle of the second end flank and the second wing 240 can be 60 ° -90 °.The second end flank may include second
Wing tip fastening end and the second wing tip open end；And the second wing tip fastening end is fixedly connected with the second forward open end, the second wing tip
Open end constitutes the both ends of the second end flank away from the second forward open end and the second wing tip fastening end.Wherein, first wing
Sharp open end and second wing tip open end are symmetrically distributed along the center vertical pivot of the fuselage 200.
Fuselage 200 can also include the first aileron 280 and/or the second aileron 290.The setting of first aileron 280 rotation exists
On first wing 230, and the first aileron 280 is rotated on the first wing 230 relative to first side；And/or second
Aileron 290 rotate setting on the second wing 240, and the second aileron 290 on the second wing 240 relative to second side
It is rotated.
Fig. 2 is referred to, Fig. 2 is that the embodiment of the present invention provides a kind of top view illustration of fixed-wing unmanned plane.Fuselage 200
The second front end 210 can be detachably connected with the first rear end 130 of head 100.Fuselage 200 can have hollow knot
Second ontology 220 of structure, i.e. fuselage 200 can be hollow, which can be used for accommodating photography, picture pick-up device, electricity
Device element etc..The diameter of section of second ontology 220 can be sequentially reduced on the direction towards the second rear end 270 so that nothing
Man-machine 200 overall construction of fuselage can be in flight course in unmanned plane, effectively reduce and flow through unmanned aerial vehicle body 200
Air-flow moves loss of energy to reduce unmanned plane itself, improves the cruise duration of unmanned plane to the obstruction of unmanned plane.
First side and second side can be two opposites of 200 second ontology 220 of fuselage, such as can be and ground
Two perpendicular sides of face.First wing 230 is installed on the first side, and the second wing 240 is installed on the second side.The
One wing 230 and the second wing 240 can symmetrically be distributed in the second ontology 220 along the center vertical pivot of the second ontology 220
Both sides.Assuming that the plane residing for the first wing 230 and the second wing 240 is A planes, the top (top, that is, remote of the second ontology 220
Side from the ground, bottom are the side close to ground, and top and bottom make mutually contradictory) residing for plane be B planes,
Can be then that A plane ratio B planes are farther from the ground relative to the distance on ground.The spacing of A planes and B planes can basis
The design of unmanned plane needs to determine, such as distance range can be 10cm -1000cm.It can be between A planes and B planes
It is provided with support member, which connects A planes and B planes, so that A planes and B planes is fixed to each other, such as the first wing
230 and second wing 240 be fixedly mounted on the support columns, the top of the support column and the second ontology 220 is fixedly connected, support column
Between A planes and B planes, and support column is mutually perpendicular to the first wing 230 and the second wing 240 respectively, is then made
The first adjustable rotary wing mechanism 250 on first wing 230 operates in the space far from B planes, also makes on the second wing 240
Second adjustable rotary wing mechanism 260 operates in the space far from B planes, if so as to avoid by the first adjustable rotary wing mechanism
First propeller 252 in 250, the second propeller 262 is all located in B planes in the second adjustable rotary wing mechanism 260, and when the
When one propeller 252 and closer 262 the second ontology of distance 220 of the second propeller, due to the rotation of the first propeller 252, second
The rotation of propeller 262 so that the first propeller 252 and the second propeller 262 collide the second ontology 220, cause to pacify
Full accident, forces unmanned plane to be stopped suddenly, and collides the propeller broken blade generated after generation, jeopardizes flight range
Interior personnel safety.
Fig. 3 is referred to, Fig. 3 is that the embodiment of the present invention provides a kind of upward view schematic diagram of fixed-wing unmanned plane.First
The first linking arm 251, the first interlude of the first linking arm 251 can be installed in first positioning area of wing 230
It can be detachably connected with the first positioning area so that when the first linking arm 251 loses, or be connected to the first linking arm 251
When the first adjustable rotary wing mechanism 250 in middle first end breaks down, the first linking arm 251 can be replaced in time.To
When overcoming the appearance damage of the first adjustable rotary wing mechanism 250 can not repair, it has to replace the entire fuselage 200 of unmanned plane
Technological deficiency reaches the technique effect for significantly reducing maintenance cost.First linking arm 251 can be with 230 phase of the first wing
Mutually vertical, i.e. the first linking arm 251 can be with the center vertical pivot of the second ontology 220 mutually usually, this makes the first linking arm 251
Both ends can be far from the second ontology 220, to be carried for the rotation of the first adjustable rotary wing mechanism 250 and the first rotor 254
For the space of bigger, the safety during unmanned plane during flying or landing is promoted.
The second linking arm 261, the second linking arm 261 can be installed in the second positioning area of the second wing 240
The second interlude can also be detachably connected with the second positioning area so that when the second linking arm 261 loses, or be connected to
It, can be in time to the second linking arm when the second adjustable rotary wing mechanism 260 in second linking arm 261 in second end breaks down
261 replace.When can not be repaired to overcome the appearance damage of the second adjustable rotary wing mechanism 260, it has to replace unmanned plane
The technological deficiency of entire fuselage 200, reaches the technique effect for significantly reducing maintenance cost.Second linking arm 261 can be with
Second wing 240 is mutually perpendicular to, i.e. the second linking arm 261 can be with the center vertical pivot of the second ontology 220 mutually usually, this makes
It the both ends of second linking arm 261 can be far from the second ontology 220, to be revolved for the second adjustable rotary wing mechanism 260 and second
The rotation of the wing 264 provides the space of bigger, promotes the safety during unmanned plane during flying or landing.
Fig. 1 is referred to, Fig. 1 is a kind of overall structure diagram of fixed-wing unmanned plane provided in an embodiment of the present invention.For
First adjustable rotary wing mechanism 250 and the second adjustable rotary wing mechanism 260 be described in detail, following two realities are now provided
The mode of applying is explained in detail：
The first embodiment.First adjustable rotary wing mechanism 250 may include the first propeller 252, first motor
431, first verts component 253, the first steering engine 421.First propeller 252 can be twayblade, i.e. the first propeller 252 can be with
Including two blades；First propeller 252 can also be multiple-blade (more than two blade).Two blades can be with the first electricity
First drive shaft of machine 431 is fixedly connected, and two blades can symmetrically be distributed in the both sides of the first drive shaft, and first drives
Moving axis and the plane of two blades rotation are perpendicular.The first base of first motor 431 can vert the of component 253 with first
One pedestal is fixedly connected, and the first fastening seat of first motor 431 can be fixedly connected with the first limiting slot 255, and first verts portion
First limiting slot 255 of part 253 can be fixedly connected with the first end of the first linking arm 251.Due to the first limiting slot 255 and
One pedestal is hinged, such as：It is fixed with protruding end in one end of the first limiting slot 255, through-hole is provided on the protruding end (referred to as
K1)；It is fixed with another protruding end on a face being away from each other with first motor 431 on the first pedestal, is set on the protruding end
It is equipped with through-hole (abbreviation K2), K1 and K2 match, i.e. the diameter of K1 and K2 can be identical.Bearing can be passed through from K1 and K2,
And the bearing can be connected with the first rotating shaft of the first steering engine 421.Allow first rotating shaft to drive bearing operation, passes through
Operating drive the first pedestal to be moved relative to the first limiting slot 255, the direction of the movement can be relative to ground
For 0 ° -90 ° and/or 0 °-(- 90 °), wherein 90 ° refer to being directed away from ground, are located above unmanned plane, and the ground and
Angle when perpendicular；- 90 ° refer to being directed away from ground, are located at below unmanned plane, and the angle with ground when perpendicular；
0 ° refers to angle with ground when parallel.The first propeller 252 is controlled at 0 ° -90 ° by the first steering engine 421 to realize
And/or 0 °-(- 90 °) in the range of rotated.First electricity can be installed on the first limiting slot 255 and adjust 441, first
Electricity tune 441 can be connected with first motor 431, and 441 rotary speeies that can control first motor 431 are adjusted by the first electricity, from
And it realizes and adjusts 441 to adjust the rotating speed of the first propeller 252 by the first electricity.
It can be fixedly installed the second motor 432 in the second end of the first linking arm 251, the second of the second motor 432
Pedestal can be fixedly connected with second end.Second drive shaft of the second motor 432 can be fixedly connected with the first rotor 254,
And the rotational plane of the second drive shaft and the first rotor 254 is perpendicular.First rotor 254 can be multiple-blade (2 or more leaves
Piece) rotor.Above-mentioned first propeller 252 can be the propeller of big screw pitch, i.e., the pitch of the first rotor 254 is than the first rotor
254 pitch is small.Due to the first rotor 254 pitch be more than the first rotor 254 pitch, so the first rotor 254 0 °-
90 ° and/or 0 °-(- 90 °) in the range of when being rotated, the thrust or lift of bigger can be provided for unmanned plane.
Second of embodiment.Second adjustable rotary wing mechanism 260 may include the second propeller 262, third motor
433, second verts component 263, the second steering engine 422.Second propeller 262 can be twayblade, i.e. the second propeller 262 can be with
Including two blades；Second propeller 262 can also be multiple-blade (more than two blade).Two blades can be with third electricity
The third drive shaft of machine 433 is fixedly connected, and two blades can symmetrically be distributed in the both sides of third drive shaft, and third is driven
Moving axis and the plane of two blades rotation are perpendicular.The third pedestal of third motor 433 can vert the of component 263 with second
Two pedestals are fixedly connected, and the second fastening seat of the second steering engine 422 can be fixedly connected with the second limiting slot 265, and second verts portion
Second limiting slot 265 of part 263 can be fixedly connected with the third end of the second linking arm 261.Due to the second limiting slot 265 and
Two pedestals are hinged, such as：It is fixed with protruding end in one end of the second limiting slot 265, through-hole is provided on the protruding end (referred to as
K3)；It is fixed with another protruding end on a face being away from each other with third motor 433 on the second pedestal, is set on the protruding end
It is equipped with through-hole (abbreviation K4), K3 and K4 match, i.e. the diameter of K3 and K4 can be identical.Bearing can be passed through from K3 and K4,
And the bearing can be connected with the second shaft of the second steering engine 422.Allow the second shaft to drive bearing operation, passes through
Operating drive the second pedestal to be moved relative to the second limiting slot 265, the direction of the movement can be relative to ground
For 0 ° -90 ° and/or 0 °-(- 90 °), wherein 90 ° refer to being directed away from ground, are located above unmanned plane, and the ground and
Angle when perpendicular；- 90 ° refer to being directed away from ground, are located at below unmanned plane, and the angle with ground when perpendicular；
0 ° refers to angle with ground when parallel.The second propeller 262 is controlled at 0 ° -90 ° by the second steering engine 422 to realize
And/or 0 °-(- 90 °) in the range of rotated.Second electricity can be installed on the second limiting slot 265 and adjust 442, second
Electricity tune 442 can be connected with the second motor 432, and 442 rotary speeies that can control the second motor 432 are adjusted by the second electricity, from
And it realizes and adjusts 442 to adjust the rotating speed of the second propeller 262 by the second electricity.
It can be fixedly installed the 4th motor 434 on the 4th end of the second linking arm 261, the 4th of the 4th motor 434 the
Pedestal can be fixedly connected with the 4th end.4th drive shaft of the 4th motor 434 can be fixedly connected with the second rotor 264,
And the rotational plane of the 4th drive shaft and the second rotor 264 is perpendicular.Second rotor 264 can be multiple-blade (2 or more leaves
Piece) rotor.Above-mentioned second propeller 262 can be the propeller of big screw pitch, i.e., the pitch of the second rotor 264 is than the second propeller
262 pitch is small.Since the pitch of the second propeller 262 is more than the pitch of the second rotor 264, so the second propeller 262 exists
0 ° -90 ° and/or 0 °-(- 90 °) in the range of when being rotated, the thrust or lift of bigger can be provided for unmanned plane.
In the first above-mentioned embodiment, the first adjustable rotary wing mechanism 250 may be mounted at the first linking arm 251
In second end, the first rotor 254 may be mounted in the first end of the first linking arm 251；Or the of the first linking arm 251
First adjustable rotary wing mechanism 250 is installed, it is adjustable to be also equipped with first in the second end of the first linking arm 251 on one end
Rotor mechanism 250.In above-mentioned second of embodiment, the second adjustable rotary wing mechanism 260 may be mounted at the second linking arm
On 261 the 4th end, the second rotor 264 may be mounted on the third end of the second linking arm 261；Or in the second linking arm
Second adjustable rotary wing mechanism 260 is installed on 261 third end, is also equipped on the 4th end of the second linking arm 261
Two adjustable rotary wing mechanisms 260.Since the first adjustable rotary wing mechanism 250 being mounted in the second end of the first linking arm 251
Structure and it is above-mentioned by the first adjustable rotary wing mechanism 250 be mounted on the first linking arm 251 first end on structure it is similar
Seemingly；By the second adjustable rotary wing mechanism 260 be mounted on the second linking arm 261 the 4th end on structure and it is above-mentioned can by second
The structure that mode rotor mechanism 260 is mounted on the third end of the second linking arm 261 is similar.It is not repeated herein.
In order to the first adjustable rotary wing mechanism 250 and the second adjustable rotary wing mechanism 260 for unmanned plane provide lift or
Thrust realizes that the landing of unmanned plane is explained in detail, and now provides following embodiment and is described in detail：
The first embodiment, takeoff phase.The first steering engine 421 can be controlled by flight control system, push the first propeller
252 are moved to 90 ° of positions；Then it adjusts 441 control first motors 431 to work by the first electricity, first is driven by first motor 431
Propeller 252 rotates, and adjusts 441 to promote the rotating speed of first motor 431 by the first electricity so that the first propeller 252
Rotating speed increases.Meanwhile by flight control system, the second steering engine 422 is controlled, push the second propeller 262 to be moved to 90 ° of positions；So
It adjusts 442 control third motors 433 to work by the second electricity afterwards, drives the second propeller 262 to rotate by third motor 433, and
442 are adjusted to promote the rotating speed of third motor 433 by the second electricity so that triple propeller rotating speed increases.Due to the first spiral
Paddle 252 and the second propeller 262 are moved to 90 ° of positions, and the lift perpendicular to ground can be then provided for unmanned plane；And the
The rotating speed of one propeller 252 and the second propeller 262 increases, and can then increase the lift of unmanned plane, finally so that unmanned plane
After obtaining enough lift, take off vertically.
Second of embodiment is taken off the winged stage that flattens.It is in and takes off vertically in unmanned plane, and rise to certain altitude
Afterwards.The first steering engine 421 can be controlled by flight control system, the first propeller 252 is pushed to be gradually moved into 0 ° of position；Then pass through
First electricity adjusts 441 control first motors 431 to work, and drives the first propeller 252 to rotate by first motor 431, and pass through the
One electricity adjusts 441 first to reduce the rotating speed of first motor 431, is then lifted out the rotating speed of first motor 431 so that the first propeller
The ascending increase of 252 rotating speed.Meanwhile by flight control system, the second steering engine 422 is controlled, push the second propeller 262 to move
It moves to 0 ° of position；Then it adjusts 442 control third motors 433 to work by the second electricity, the second propeller is driven by third motor 433
262 rotations, and adjust 442 first to reduce the rotating speed of third motor 433 by the second electricity, it is then lifted out turning for third motor 433
Speed so that the ascending increase of triple propeller rotating speed.Since the first propeller 252 and the second propeller 262 are moved to
0 ° of position can then provide the thrust for being parallel to ground for unmanned plane；And the first propeller 252 and the second propeller 262
Rotating speed increase after, can then increase the thrust of unmanned plane, finally so that unmanned plane obtain minimum flying speed, in the air into
Row flight.
The third embodiment, landing phases.During unmanned plane is in flat and flies, the can be controlled by flight control system
One steering engine 421 pushes the first propeller 252 to be gradually moved into 90 ° of positions from 0 °；Then 441 controls first are adjusted by the first electricity
Motor 431 works, and drives the first propeller 252 to rotate by first motor 431, and adjusts 441 to reduce first by the first electricity
The rotating speed of motor 431 so that the rotating speed of the first propeller 252 is gradually reduced.Meanwhile by flight control system, controlling the second steering engine
422, it pushes the second propeller 262 to be moved to and is gradually moved into 90 ° of positions from 0 °；Then 442 control thirds are adjusted by the second electricity
Motor 433 works, and drives the second propeller 262 to rotate by third motor 433, and adjusts 442 to reduce third by the second electricity
The rotating speed of motor 433 so that triple propeller rotating speed is gradually reduced.Since the first propeller 252 and the second propeller 262 move
It moves to 90 ° of positions, the pulling force perpendicular to ground can be then provided for unmanned plane；And the first propeller 252 and the second spiral
After the rotating speed of paddle 262 is gradually reduced, it can be then gradually reduced the thrust of unmanned plane, finally so that unmanned plane is under in the air gradually
Drop to ground to be landed.
First end flank may include the first wing tip fastening end and the first wing tip open end, and the first of first end flank
Wing tip fastening end can be fixedly connected with the first forward open end of the first wing 230, and the first wing tip open end deviates from first
Forward open end, i.e. the first wing tip open end can be located at the lower section of unmanned aerial vehicle body 200.At this point, first end flank and first
Wing 230 constitutes angle (abbreviation F1), and the range of the angle (abbreviation F1) can be 60 ° -90 °；The second of the second end flank
Wing tip fastening end can be fixedly connected with the second forward open end of the second wing 240, and the second wing tip open end deviates from second
Forward open end, i.e. the second wing tip open end are located at the lower section of unmanned aerial vehicle body 200.At this point, the second end flank and the second wing
240 constitute angle (abbreviation F2), and the range of the angle (abbreviation F2) can be 60 ° -90 °.Above-mentioned first wing tip open end and
Two wing tip open ends can be using the center vertical pivot of fuselage 200 as symmetry axis, distribution axisymmetricly.Take the folder of above-mentioned F1 and F2
Angular region can reduce " induced drag " caused by the first wing tip trailing vortex and the second wing tip trailing vortex, be reduced to reach
The destruction to lift is streamed, lift resistance ratio is improved, increases voyage, has the function that the technique effect for increasing lift.Meanwhile first end
Portion's flank and the second end flank are all mutually perpendicular to level ground, so first end flank and the second end flank and ground
Spacing is nearest, keeps the material needed for manufacture first end flank and the second end flank also less, to mitigate first end side
The own wt of the wing and the second end flank, the overall weight for reducing unmanned plane have reached increase voyage, it is motor-driven to reduce nobody
Power loss (such as：Oil consumption) technique effect.When unmanned plane drops to ground, first end flank and the second end flank are also
The effect of undercarriage can be served as.
Fig. 4 is referred to, Fig. 4 is that the embodiment of the present invention provides a kind of side view schematic diagram of fixed-wing unmanned plane.First
The first aileron 280 is also provided on wing 230, the first aileron 280 can be located to be opened before the first of the first wing 230
At mouth end, the first aileron 280 can be hinged with the first wing 230, i.e. the first aileron 280 can be relative on the first wing 230
Lower movement.The second aileron 290 is also provided on the second wing 240, the second aileron 290 can be located at close to the second wing
At 240 the second forward open end, the second aileron 290 can be hinged with the second wing 240, i.e. the second aileron 290 can be relative to
Second wing 240 moves up and down.First pair can be connected with motor respectively with the second aileron 290, pass through the winged control system of unmanned plane
System controls motor, and first is secondary and/or second aileron 290 moves up and down driving, then make in unmanned plane in-flight to
Scheduled direction deflection.
It can be fixedly installed U-shaped rise on the bottom (i.e. close to the side on ground) of the second ontology 220 of unmanned plane
Frame is fallen, which is open towards ground, and undercarriage can integrally be made by foamed material, the angular aperture of U-shaped undercarriage
It can be 90 ° -120 ° to spend range.When unmanned plane lands, the U-shaped undercarriage of foam can be touched in unmanned plane and ground
During touching, the ability of shock is absorbed, reduces the impact force for facing unmanned plane in unmanned plane descent, to reach protection
The safety of unmanned plane and airborne equipment.Also, when the opening angle of U-shaped undercarriage is 90 ° or 120 °, U-shaped undercarriage confrontation
The ability of ground shock power is also strong, to improve the U-shaped undercarriage stability of itself.
For tail 300：
Tail 300 may include third front end 310, third ontology 320 and third rear end 330.
Third front end 310 and the second rear end 270 can be mutually detachably connected；Before third ontology 320 and third
End 310 can be mutually permanently connected；Third rear end 330 and third ontology 320 can be mutually permanently connected.Wherein,
Third ontology 320 can be arranged between third front end 310 and third rear end 330, and can be by third front end
310, third ontology 320 and third rear end 330, which are integrally formed, constitutes tail 300；
Also, empennage can be provided on third ontology 320.Empennage may include the first aerofoil plate 340 and second wing
Panel 350, the first aerofoil plate 340 can be fixedly connected with third ontology 320, and the second aerofoil plate 350 can be with third ontology 320
It is fixedly connected, and the first aerofoil plate 340 can be symmetrically distributed in the both sides of third ontology 320 with the second aerofoil plate 350.Its
In, the first aerofoil plate 340 and the second aerofoil plate 350 may be constructed v-shaped structure, and the angular range of v-shaped structure can be 70 °-
90°。
Fig. 5 is referred to, Fig. 5 is that the embodiment of the present invention provides a kind of front view schematic diagram of fixed-wing unmanned plane.Tail 300
Third front end 310 can be mutually detachably connected with the second rear end 270 of fuselage 200.Third ontology 320 is located at third
Between front end 310 and third rear end 330, third ontology 320 can be rendered as cylindrical structure.It is leaned in third ontology 320
Empennage can be installed at nearly third rear end 330.Third ontology 320 be rendered as cylinder can unmanned plane be in flew
Cheng Zhong effectively reduces resistance of the air-flow to unmanned plane, increases the cruise duration of unmanned plane, improves the flying speed of unmanned plane.
Tail 300 can be rudder-vator.Rudder-vator can form (i.e. 340 He of the first aerofoil plate by two aerofoils in left and right
Second aerofoil plate 350), two aerofoils in left and right can be separately fixed on the third ontology 320 of tail 300, can be on band is big
The horizontal tail of dihedral.Vee tail can have the function of vertical fin and horizontal tail concurrently.Aerofoil can be divided into fixed stabilization and hinged rudder face
Two parts may be alternatively configured full ejector half formula.Two V-shaped tail surfaces have certain projected area, institute in vertical view and side-looking direction
Longitudinal direction (pitching) and course-stability can be played simultaneously.When both sides, rudder face makees same direction deflection, lifting rudder action；Point
When not making different directions deflection (differential), then direction rudder action can be played.But tail 300 can also be tailplane or hang down
Straight tail, if tail 300 is tailplane, tailplane may be mounted on the third ontology 320 of tail 300；If tail
300 be vertical tail, then vertical tail can also be mounted on the third ontology 320 of tail 300.
If tail 300 is rudder-vator, which can be by 350 structure of the first aerofoil plate 340 and the second aerofoil plate
At v-shaped structure, the angular range of v-shaped structure can be 70 ° -90 °, i.e. the folder of the first aerofoil plate 340 and the second aerofoil plate 350
Angle (abbreviation β) range can be 70 ° -90 °, which can be away from the direction of level ground.When Β=70 °, in nothing
It is man-machine to fly the stage in flat, it can effectively stablize the course of unmanned plane；When Β=90 °, make the deflection of different directions in unmanned plane
When, the effect of rudder can be provided for unmanned plane.
It (can mutually hang down with third ontology 320 side on side of the first aerofoil plate 340 towards third rear end 330
Aileron (abbreviation W1) can directly) be installed, W1 ailerons can be hinged with the first aerofoil plate 340, i.e. W1 ailerons can be relative to
First aerofoil plate 340 moves up and down.It (side can be on side of the second aerofoil plate 350 towards third rear end 330
Three ontologies 320 are perpendicular) aileron (abbreviation W2) can also be installed, W2 ailerons can be hinged with the second aerofoil plate 350, i.e. W2
Aileron can be moved up and down relative to the second aerofoil plate 350.It, can be by controlling the upper of W1 and W2 when unmanned plane needs to turn to
Lower movement, to change the navigation direction of unmanned plane.To realize that unmanned plane is flexibly flown towards all directions in the air.
For dynamical system 400：
Dynamical system 400 may include power supply part 410, displacement component 420, driving part 430 and regulating member 440.
Power supply part 410 can be provided with the first delivery outlet, the second delivery outlet, third delivery outlet and the 4th delivery outlet.Position
It may include the first steering engine 421 and the second steering engine 422 to move component 420, and the first steering engine 421 is provided with the first input port, the first rudder
First input port of machine 421 can be connected with the first delivery outlet；Second steering engine 422 is provided with the second input port, the second steering engine 422
The second input port can be connected with the second delivery outlet.
Driving part 430 may include first motor 431 and the second motor 432, and first motor 431 is provided with third input
Mouthful, the second motor 432 is provided with the 4th input port；Regulating member 440 may include 441 and second electricity tune 442 of the first electric tune, the
One electricity adjusts 441 to be provided with the 5th input port and the 5th delivery outlet, the first electricity adjust 441 the 5th input port can and power supply part
410 third delivery outlet connection, the first electricity adjust 441 the 5th delivery outlet that can be connected with the third input port of first motor 431.
Second electricity tune 442 can be provided with the 6th input port and the 6th delivery outlet, and the second electricity adjusts 442 the 6th input port that can and power
4th delivery outlet of component 410 connects, and the second electricity adjusts 442 the 6th delivery outlet can be with the 4th input port of the second motor 432
Connection.
Fig. 6 is referred to, Fig. 6 is that the embodiment of the present invention provides a kind of structural frames of the dynamical system 400 of fixed-wing unmanned plane
Figure.The dynamical system 400 of unmanned plane may include power supply part 410, displacement component 420, driving part 430 and regulating member
440.Power supply part 410 may include engine, generator, voltage-stablizer, accumulator.
Engine can be by the mechanical energy that can be converted into of other forms, such as engine is that two-stroke aviation piston starts
Machine；Generator can convert the mechanical energy that engine generates to electric energy；Voltage-stablizer can keep electric caused by generator
Stable voltage can be exported after voltage-stablizer, voltage-stablizer can be connected with accumulator.Accumulator is connect with voltage-stablizer
Effect can be accumulator can provide electric energy for voltage-stablizer, and voltage-stablizer keeps the electric energy generated by accumulator defeated after voltage-stablizer
Go out stable voltage；And if engine or generator break down, and when can not provide electric energy for unmanned plane, can cut automatically
It is changed to storage battery power supply, electric energy is provided for unmanned plane by accumulator；If engine or power generation function normal work, can be nothing
Man-machine offer electric energy, then accumulator stopping provide electric energy for unmanned plane；Certainly, can not be nothing if electric power deficiency occurs in accumulator
Man-machine offer electric energy can be carried by engine or generator for accumulator by the normal work of engine either generator
For electric energy, to supplement the electric energy of accumulator.
It, can not when engine or generator failure if only setting engine and generator provide electric energy for voltage-stablizer
When providing electric energy for unmanned plane, unmanned plane in landing or in-flight will be faced with no power resources, and damage of falling
The danger of bad unmanned plane；Or only setting accumulator provides electric energy for voltage-stablizer, when the failures such as electric energy deficiency, nothing occurs in accumulator
When method provides electric energy for unmanned plane, unmanned plane in landing or in-flight will be faced with no power resources, and fall
Damage the danger of unmanned plane.So providing electric energy by engine and generator for voltage-stablizer and accumulator provides for voltage-stablizer
Electric energy, and this accumulator can mutually switch with generator and provide electric energy for voltage-stablizer, and unmanned plane can be overcome to fly
In due to generator break down or accumulator break down, electric energy can not be provided for unmanned plane, make unmanned plane that will be faced with
There is no power resources, and the technological deficiency for the damage unmanned plane that falls, reach the safety for improving unmanned plane, in-flight power
Stability technique effect.
Meanwhile the burning voltage that voltage-stablizer is exported will enter current divider, each shunting delivery outlet of current divider can incite somebody to action
Electric energy is assigned to displacement component 420, driving part 430 and regulating member 440, and current divider may be video camera, fly automatically
Control system distributes electric energy, and the mode of the distribution electric energy can connect or use wireless power transmission by conducting wire, these
It may also apply to the present invention.First delivery outlet of power supply part 410 can be connected with the first input port of the first steering engine 421, be supplied
Second delivery outlet of electrical components 410 can be connected with the second input port of the second steering engine 422, then be by power supply part 410
First steering engine 421 and the second steering engine 422 provide electric energy.First electricity adjusts 441 the 5th input port can be with the of power supply part 410
Three delivery outlets connect, and the first electricity adjusts 441 the 5th delivery outlet that can be connected with the third input port of first motor 431；Second electricity
Adjust 442 the 6th input port that can be connected with the 4th delivery outlet of power supply part 410, the second electricity adjusts 442 the 6th delivery outlet can
To be connected with the 4th input port of the second motor 432.So that adjust 441 to control the rotating speed of first motor 431 by the first electricity, the
Two electricity adjust 442 to control the rotating speed of the second motor 432.To pass through the flight control system from ground remote control device into unmanned plane
Control instruction is sent, and controls the first steering engine 421, the second steering engine 422, first motor of unmanned plane by flight control system
431 and second motor 432 working condition, and then reach the technique effect controlled the state of unmanned plane landing, flight.
It is noted that flight control system is mainly by controlling the first steering engine 421, to drive first to vert component
253 movement, with control the first propeller 252 0 ° -90 ° and/or 0 °-(- 90 °) in the range of rotated；Pass through control
Second steering engine 422, come drive second vert component 263 move, with control the second propeller 262 0 ° -90 ° and/or 0 ° -
It is rotated in the range of (- 90 °)；Also, by the rotating speed for controlling first motor 431, to control the first propeller 252
Rotating speed；By controlling the rotating speed of third motor 433, to control the rotating speed of the second propeller 262.So that by flight control system pair
It is carried out in the range of angle of inclination (i.e. the first propeller 252 0 ° -90 ° and/or 0 °-(- 90 °)) of first propeller 252
Rotation and rotating speed, and angle of inclination and rotating speed to the second propeller 262 regulation and control.Reach and is controlled by flight control system
The motion state of unmanned plane landing processed, flight, and control the technique effect of the movement speed of unmanned plane landing, flight.
The present invention provides a kind of fuselage dynamical system for fixed-wing unmanned plane, and the diameter of section of the first noumenon is designed
To be sequentially increased on the direction towards the first rear end, the diameter of section of the first noumenon is designed as towards after described first
It is sequentially increased on the direction of end, resistance of the air-flow to unmanned plane can be effectively reduced.Meanwhile by by the first of power supply part
First input port of delivery outlet and the first steering engine connects, and the second delivery outlet of power supply part and the second input port of the second steering engine connect
It connects；The 5th input port connection that the third delivery outlet of power supply part and the first electricity are adjusted, the 5th delivery outlet and first that the first electricity is adjusted
The third input port of motor connects；The 6th input port connection that 4th delivery outlet of power supply part and the second electricity are adjusted, the second electricity are adjusted
The 6th delivery outlet and the second motor the 4th input port connection；Then it is the first steering engine, the second steering engine, first motor and second
Motor provides the energy of different size demand, meets the normal work of the first steering engine, the second steering engine, first motor and the second motor
Make, unmanned plane is allow normally to be lifted and be flown.To reach the cruise duration for increasing unmanned plane, it is each to meet unmanned plane
Demand of the electrical appliance to the energy, improves the technique effect of the practicability of unmanned plane.
It should be noted last that the above specific implementation mode is merely illustrative of the technical solution of the present invention and unrestricted,
Although being described the invention in detail with reference to example, it will be understood by those of ordinary skill in the art that, it can be to the present invention
Technical solution be modified or replaced equivalently, without departing from the spirit of the technical scheme of the invention and range, should all cover
In the scope of the claims of the present invention.
Claims (9)
1. a kind of fuselage dynamical system for fixed-wing unmanned plane, which is characterized in that the machine for fixed-wing unmanned plane
Body dynamical system includes：
Head, the head include：
First front end, the tapered structure in the first front end；
The first noumenon, the first noumenon are fixedly connected with first front end, and the diameter of section of first front end
It is sequentially increased on the direction towards the first noumenon；
First rear end, first rear end is fixedly connected with the first noumenon, and the diameter of section of the first noumenon
It is sequentially increased on the direction towards first rear end；
Wherein, the first noumenon is arranged between first front end and first rear end, and first front end
Portion, the first noumenon and first rear end, which are integrally formed, constitutes the head；
Dynamical system, the dynamical system include：
Power supply part, the power supply part are provided with the first delivery outlet, the second delivery outlet, third delivery outlet and the 4th delivery outlet；
Displacement component, the displacement component include the first steering engine and the second steering engine, and first steering engine is provided with the first input port,
First input port is connected with first delivery outlet；Second steering engine is provided with the second input port, second input
Mouth is connected with second delivery outlet；
Driving part, the driving part include first motor and the second motor, and the first motor is provided with third input port,
Second motor is provided with the 4th input port；
Regulating member, the regulating member include that first the second electricity of electricity reconciliation is adjusted, and first electricity, which is adjusted, is provided with the 5th input port
With the 5th delivery outlet, the 5th input port is connected with the third delivery outlet, the 5th delivery outlet and third input
Mouth connection；Second electricity, which is adjusted, is provided with the 6th input port and the 6th delivery outlet, the 6th input port and the 4th output
Mouth connection, the 6th delivery outlet are connected with the 4th input port.
2. being used for the fuselage dynamical system of fixed-wing unmanned plane as described in claim 1, which is characterized in that described for fixing
The fuselage dynamical system of wing unmanned plane includes：
The first motor is provided with the first drive shaft and first base, and first drive shaft and the first propeller, which are fixed, to be connected
It connects, the first base is fixedly connected with the first pedestal.
3. being used for the fuselage dynamical system of fixed-wing unmanned plane as claimed in claim 2, which is characterized in that described for fixing
The fuselage dynamical system of wing unmanned plane includes：
Second motor is provided with the second drive shaft and second base, and the second base is fixedly connected with second end, described
Second drive shaft is fixedly connected with the first rotor；
Wherein, the rotational plane of second drive shaft and first rotor is perpendicular.
4. being used for the fuselage dynamical system of fixed-wing unmanned plane as claimed in claim 3, it is characterised in that：
The power supply part further includes the 6th delivery outlet；
The driving part further includes third motor, and the third motor is provided with the 7th input port, the 7th input port and
The 6th delivery outlet connection.
5. being used for the fuselage dynamical system of fixed-wing unmanned plane as claimed in claim 4, it is characterised in that：
The third motor is provided with third drive shaft and third pedestal, and the third drive shaft and the second propeller, which are fixed, to be connected
It connects, the third pedestal and the second pedestal are fixedly connected.
6. being used for the fuselage dynamical system of fixed-wing unmanned plane as claimed in claim 5, it is characterised in that：
The power supply part further includes the 7th delivery outlet；
The driving part further includes the 4th motor, and the 4th motor is provided with the 8th input port, the 8th input port and
The 7th delivery outlet connection.
7. being used for the fuselage dynamical system of fixed-wing unmanned plane as claimed in claim 6, which is characterized in that described for fixing
The fuselage dynamical system of wing unmanned plane includes：
4th motor is provided with the 4th drive shaft and the 4th pedestal, and the 4th pedestal and the 4th end are fixedly connected, described
4th drive shaft is fixedly connected with the second rotor；
Wherein, the rotational plane of the 4th drive shaft and second rotor is perpendicular.
8. being used for the fuselage dynamical system of fixed-wing unmanned plane as claimed in claim 7, which is characterized in that described for fixing
The fuselage dynamical system of wing unmanned plane includes：
First steering engine includes first rotating shaft and the first fastening seat, and the first rotating shaft is connected with first pedestal, described
First fastening seat and the first limiting slot are fixedly connected；
Wherein, the first rotating shaft is arranged between first pedestal and first limiting slot.
9. being used for the fuselage dynamical system of fixed-wing unmanned plane as claimed in claim 8, which is characterized in that described for fixing
The fuselage dynamical system of wing unmanned plane includes：
Second steering engine includes the second shaft and the second fastening seat, and second shaft is connected with second pedestal, described
Second fastening seat and the second limiting slot are fixedly connected；
Wherein, second shaft is arranged between second pedestal and second limiting slot.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810079373.0A CN108313263A (en) | 2018-01-26 | 2018-01-26 | Fuselage dynamical system for fixed-wing unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810079373.0A CN108313263A (en) | 2018-01-26 | 2018-01-26 | Fuselage dynamical system for fixed-wing unmanned plane |
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| CN108313263A true CN108313263A (en) | 2018-07-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810079373.0A Pending CN108313263A (en) | 2018-01-26 | 2018-01-26 | Fuselage dynamical system for fixed-wing unmanned plane |
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Cited By (1)
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| CN113370730A (en) * | 2021-07-20 | 2021-09-10 | 广东汇天航空航天科技有限公司 | Flying car |
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Application publication date: 20180724 |