CN106516097A - Unpiloted aircraft - Google Patents
Unpiloted aircraft Download PDFInfo
- Publication number
- CN106516097A CN106516097A CN201611043631.7A CN201611043631A CN106516097A CN 106516097 A CN106516097 A CN 106516097A CN 201611043631 A CN201611043631 A CN 201611043631A CN 106516097 A CN106516097 A CN 106516097A
- Authority
- CN
- China
- Prior art keywords
- wing
- airfoil
- aircraft
- unmanned vehicle
- vehicle according
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 14
- 238000003860 storage Methods 0.000 claims description 12
- 238000013461 design Methods 0.000 claims description 11
- 229910052742 iron Inorganic materials 0.000 claims description 7
- 230000008859 change Effects 0.000 claims description 6
- 239000007788 liquid Substances 0.000 claims description 6
- 238000011144 upstream manufacturing Methods 0.000 claims description 6
- 230000009977 dual effect Effects 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 4
- 238000002485 combustion reaction Methods 0.000 claims description 3
- 239000002131 composite material Substances 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims description 3
- 239000012530 fluid Substances 0.000 claims description 3
- 210000002615 epidermis Anatomy 0.000 claims description 2
- 239000006260 foam Substances 0.000 claims description 2
- 239000002828 fuel tank Substances 0.000 claims description 2
- 238000009434 installation Methods 0.000 claims 1
- 239000000203 mixture Substances 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 2
- 239000003381 stabilizer Substances 0.000 abstract 2
- 230000008901 benefit Effects 0.000 description 5
- 230000006870 function Effects 0.000 description 4
- 238000005096 rolling process Methods 0.000 description 4
- 238000012544 monitoring process Methods 0.000 description 3
- 230000004888 barrier function Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 230000003028 elevating effect Effects 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 230000033001 locomotion Effects 0.000 description 2
- 239000000575 pesticide Substances 0.000 description 2
- 241001404789 Smilax glabra Species 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 238000013500 data storage Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 210000004247 hand Anatomy 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 235000000396 iron Nutrition 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000000361 pesticidal effect Effects 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 230000011514 reflex Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/12—Adjustable control surfaces or members, e.g. rudders surfaces of different type or function being simultaneously adjusted
-
- 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
- B64D1/00—Dropping, ejecting, releasing or receiving articles, liquids, or the like, in flight
- B64D1/16—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting
- B64D1/18—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting by spraying, e.g. insecticides
-
- 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
- B64D43/00—Arrangements or adaptations of instruments
-
- 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
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- 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
- B64D47/00—Equipment not otherwise provided for
-
- 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
- B64D47/00—Equipment not otherwise provided for
- B64D47/08—Arrangements of cameras
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/10—UAVs characterised by their flight controls autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
- B64U2201/104—UAVs characterised by their flight controls autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS] using satellite radio beacon positioning systems, e.g. GPS
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Life Sciences & Earth Sciences (AREA)
- Pest Control & Pesticides (AREA)
- Toys (AREA)
- Catching Or Destruction (AREA)
Abstract
The invention discloses an unpiloted aircraft. The unpiloted aircraft is characterized by comprising a fixed airfoil, an elevator or two elevons, one or more rotatable perpendicular stabilizers, a pair of coaxial contra-rotating propellers, a receiver and a battery, wherein the fixed airfoil consists of a trailing-edge-warping airfoil profile, and is low in aspect ratio; the elevator or the two elevons are located next to the inner side of the trailing edge of the airfoil; the rotatable perpendicular stabilizers are located on a symmetry plane of the aircraft and extend to the upper side and the lower side of the airfoil; the coaxial contra-rotating propellers are located on the symmetry plane of the aircraft and at the upper part of the airfoil, and are driven by a motor; and the midpoint of a chord line of the section of an airfoil root is in the upper part of or level with the midpoint of a chord line of the section of an airfoil tip. The unpiloted aircraft disclosed by the invention can execute high-skill complex tasks which cannot be executed by various conventional fixed wing aircrafts or rotor aircrafts, can perpendicularly take off and land, can fly horizontally in a posture of the fixed airfoil, and can be changed into a rotor posture for acquiring images and videos at any time; and the unpiloted aircraft disclosed by the invention is small and exquisite, flexible and stable, and the maximum speed, the endurance capability and the energy saving effect of the unpiloted aircraft disclosed by the invention are all higher than those of each of the rotor aircrafts with equal size and equal weight.
Description
Technical field
The present invention relates to unmanned plane and radio/Remote aircraft field.
Background technology
Unmanned plane has many private and business applications as aerial sensor platform（That is, video acquisition）, delivery system, ring
Border senses and communication relay.They can be used for the various uses related to national defence, for example ISR（Information monitoring is scouted）, make
For weapon platform and as electronic warfare platform.They can be divided into miniature, small-sized, tactics by size（In）, or strategy（Greatly）,
And the method produced based on its aerodynamic lift can be typically further categorized into：Fixed-wing, rotary wings, the mixing wing or flapping wing.Root
According to the report of the U.S.-China's economic safety and examination board, existing Chinese unmanned plane lacks micro-, little, mixed, flapping wing
Class, more lacks various in demand private and business application types and functional government departments apply type such as：Search for and rescue,
Border security, law enforcement and environmental monitoring.
Mixed type unmanned plane combines the advantage of fixed-wing and rotary wings unmanned plane, enables them to be successfully executed fixed-wing
Individually can not all completing with rotary wings for task.Most promising mixed type unmanned plane is to take off vertically and land（VTOL）It is fixed
Wing unmanned plane.This unmanned plane can fast and efficiently fly to remote position as a traditional fixed wing airplane, so
After be transitioned into low latitude fly slowly, hovering etc., purpose reaches rear unmanned plane and fast and efficiently can fly back again user.Substantially,
As a rotary wings type during unmanned plane execution task, but arrive at then as a fixed-wing type from original position,
Substantially improve flight range, endurance and maximum speed.The small/micro version of present invention mixing wing unmanned plane can be put into
Knapsack, carry sensors pass across a street and creep into building and return, or pass through several kilometers of mountain environments jagged in addition along path.
Existing mixing unmanned plane uses many different designs and configuration.This configuration is that the VTOL of a tail sitting posture flies
Machine, is rare type.This is the misfortune of domestic market, because this type is better than other types at many aspects.This
The type of design, has important essential different from the VD-200 of China.First, two contraprops of VD-200 and horse
Up to the centrage away from aircraft, unnecessary complexity is increased.If a motor problem, aircraft will collapse.
But, the detached motor of two long distances and propeller are favorably improved rolling inertia stability in roll.Its component is in a conventional manner
Within the compartment of centrally located fuselage shape, it is a kind of mixing wing body design.The present invention is same using two positioned at aircraft centerline
Axle propeller, it is allowed to which aircraft still is able to safe flight after a propeller fails.Another advantage of the design is to offset
The slip-stream that propeller is produced, it is to avoid the driftage produced because drag iron is clashed in slip-stream, it is vertical steady so as to avoid deflection
The additional air resistance determined device compensation and bring.The present invention other each ingredients to be distributed away from vehicle centre-line, with reality
Existing appropriate rolling inertia and stability.Other in place of making the vital point and novelty of uniqueness of the invention are：In VD-200
With two separate slip-streams stable yaw stability vertical with two groups（Rather than one）, it can use difference propulsive force
Control driftage, and the drag iron that the present invention has been designed with to rotate around vertical axis carries out driftage control.In addition, VD-
200 have the aileron and elevating plane for controlling pitching and rolling respectively.It is of the invention then traditional detached pair instead of with elevon
The wing and elevating plane, so as to control to roll and pitching simultaneously.In design, VD-200 volumes are big, involve great expense, can only be in military neck
Apply in domain.The design of the present invention can be by personal use（That is explorer, fan, backpacker/pioneer）, commercial interest（Clap
Take the photograph, photography etc.）, and less public sector's entity（That is place law enforcement, border security, environmental monitoring etc.）, purposes is flexibly wide
It is general.It is that a variety of users can afford, and can be made it is sufficiently small, can be in the larger hybrid power aeroplane of volume
Used in being unable to jagged mountain area, urban district and the indoor environment of safe flight.
The content of the invention
Instant invention overcomes the deficiencies in the prior art, there is provided a relatively easy, economic, practical, multi-functional, Yi Jipu
And in the UAV in different clients and market.
In order to achieve the above object, present invention employs technical scheme below：
A kind of unmanned vehicle, it is characterised in that by the fixed wing for sticking up the low aspect ratio that edge airfoil is constituted, be located at
An elevator or two elevons near on the inside of trailing edge, one or more are located on the aircraft plane of symmetry and to wing
The rotatable drag iron that both sides extend up and down, one is pointed on the aircraft plane of symmetry and is driven by motor in wing upstream
Dual rotation propeller, the midpoint of the wing root section string of a musical instrument in the midpoint upstream of the wing tip section string of a musical instrument or concordant, with receptor
And battery.
Described aspect ratio is 1-3.5.
Described motor is using the electro-motor with speed control.
Described motor adopts internal combustion engine, and equipped with fuel tank and igniter.
Equipped with transmitter, for sending information to user.
Equipped with gyroscope and/or accelerometer.
It is mounted with satellite-based tracking system, including but not limited to GPS.
It is mounted with automated driving system.
It is located inside wing including the adnexa of one or more receptors and battery, rather than is incorporated into central machine cabin
In.
The structure design of described wing is that, using the slim epidermis for having bearing capacity, its material includes composite, band
Have or without internal force structure or soft core, the material of soft core includes foam.
Wing carries dihedral angle or dihedral（dihedral）.
The version that wing is become narrow gradually from wing root to wing tip not only includes linear change, and including other any shapes
Formula.
With taking pictures and/or photographic equipment.
With the promising knuckle for installing video-photographic equipment.
With tip vane.
Equipped with collision avoidance system and various detection sensors.
With fluid storage tanks and pipeline, pipeline connection storage tank and the nozzle being discharged into liquid in surrounding.
Compared with prior art, the present invention has advantages below：
Present invention incorporates the advantage of fixed-wing and rotary wings unmanned plane so as to be able to carry out independent fixed-wing and rotary wings nobody
Task and skill that machine can not be completed.
It is sufficiently small without automobile or any heavy/expensive equipment is transporting, only need a people.It can be in confusion
Urban environment, even capture indoors and video is transmitted to earth station.
The complicated embodiment of the present invention has the function of the high complexity of the size type, including：
1) stabilisation systemss used in " hovering " and " keeping height " pattern based on accelerometer so that the present invention can
" staring at " lives object, and obtains stable high-quality video.
2) gps coordinate is used, follow the prescribed course Intelligent flight.
3) can make a return voyage according to the program comprising gps signal when control signal is disturbed.
4) extensibility：One user can dispose multiple units, the different route of each flight, and on a little ground
Stand and receive from the synchronous live of constituent parts.
5) thermovision is away from detection.
6) field position, course, flying height, speed and acceleration information transmission.
7) customization carries a variety of sensors, including：Chemistry, calorifics and hearing transducer.
8) less payload can be carried to specified location.
9) with collision avoidance system.
The present invention have it is safe, strong, inexpensive, relatively easy it is using, safeguard simple, and shock proof feature.
Description of the drawings
Fig. 1 is the perspective view of a simple embodiment of the present invention
Description of reference numerals：1- wings;2- aerofoil profiles;3 elevons;4- drag irons;6- propellers;7- wing roots cut
The midpoint of the face string of a musical instrument；The midpoint of the 8- wing tips section string of a musical instrument；9- motors;10- receptors;11- batteries.
Specific embodiment
Simple embodiment：Simplest embodiment such as Fig. 1 of the present invention, by sticking up the low exhibition that edge airfoil 2 is constituted
The fixed wing 1 of string ratio, a neighbouring elevator or two elevons 3 on the inside of 1 trailing edge of wing, one or more
On the aircraft plane of symmetry and to the wing rotatable drag iron 4 that both sides extend about 1, one is pointed to the aircraft plane of symmetry
Above and in the dual rotation propeller 6 driven by motor 9 of 1 upstream of wing, the midpoint 7 of the wing root section string of a musical instrument is in wing tip section string
8 upstream of midpoint of line is concordant, with receptor 10 and battery 11.The embodiment does not include any complicated function, and it does not have
There are sensor, data storage and data transmission capabilities, be mainly used in the interesting and model of an airplane of uniqueness of model airplane fan.
It may carry tip vane, it is also possible to without.
The present invention can also carry fluid storage tanks, pipeline and nozzle, and pipeline connects storage tank and liquid is discharged into surrounding
Nozzle in environment, nozzle are disposed on below wing 1 along pipeline（It is not shown）, fill typically between storage tank and nozzle
There is hydraulic pump.Described storage tank, hydraulic pump and pipeline are located inside wing, are imitated with the streamlined and air force for keeping wing
Rate.Pipeline is located at the trailing edges of wing to improve applications of pesticide effect.The low aspect ratio of wing result in higher wingtip vortex
Stream, powerful air-swirl greatly improve the fully dispersed of pesticide.For the pitching stability for keeping fuselage during flying,
Storage tank is designed in the mass centre of aircraft, and the significant change of liquid volume in such storage tank is not result in Aircraft Quality
The significant change of center, this is non-for the aerodynamic center of the mass centre and aircraft that keep appropriate relative position
It is often important.Because the performance of wing is most sensitive to the barrier and defect of its upper surface, wherein unfavorable barometric gradient may be led
Flow separation is caused, so nozzle is downwardly directed by the aperture of wing lower surface.For the flow obstacle lower surface and possible product
Raw turbulent flow is minimized, and nozzle ports are flushed with lower surface.Storage tank is used to inject liquid（Such as pesticide）, by storage tank during use
Interior liquid is gone out from nozzles spray through pipeline, is mainly used in agriculture and forestry production.
Fuselage includes the kernel with composite crust and soft low-density.Each part is distributed in entirely by embedded part
Fuselage, make rollover inertia maximize, while keep mass centre on the fuselage plane of symmetry, and positioned at away from 1 leading edge of wing about
The position of 25% chord length.Wing 1 carries certain dihedral angle or dihedral (dihedral) to improve roll stability.There are two
Embedded servo motor（It is not shown）Drive elevon 3, also one embedded servo motor（It is not shown）Drive rotatable
Drag iron 4.The slip-stream that dual rotation propeller 6 is produced hardly band whirlpool.The very powerful slip-stream of this burst is through rising
Drop aileron 3 and drag iron 4, though in low-down flight speed and hovering, or almost no wind speed when, also can be to machine
Body produces effective controling power, has ensured the functions such as the safety and compound action of flight.The symmetric deflection angle of elevon 3 produces
One non-zero pitching moment, and the differential deflection angle of elevon 3 produces a non-zero rolling moment.The aerofoil profile of wing 1 is thicker,
So that various parts can be embedded in wing 1；The reflex action of aerofoil profile 2 increased the stability of pitching motion（It is common to institute organic
The wing is designed）.Particular case lower wing 1 can also use thin airfoil.Double motor with reciprocating movement components（That is motor 9, with velocity of electrons
Controller）It is used to drive propeller 6.Electronic speed controller therein is used to limit 9 throttle of motor to control its generation
Thrust.Battery 11 is for powering to propeller motor 9 and each servo motor.
The present invention is that the related energy loss of tip vortex is preferably minimized, and its wing planform is from wing root to wing tip
The unique design of linear transitions.The design is to low aspect ratio wing particular importance.To improve flight stability, wing design is selected
Swept-back wing mode.The selection of aerofoil profile 2 guarantees the change with direction and control input, and its aerodynamic quality is gradually changed
（That is " soft " stall）, and guarantee that aerodynamic efficiency is maximized while realizing acceptable high coefficient of lift combined.Wing 1 it is big
Part is immersed in propulsion slip-stream, therefore the aerodynamic performance of wing 1（Maximum lift coefficient, stall angle etc.）Strongly
Depend on the impelling ratio and many other factors of propeller 6（The angle of attack, Reynolds number, dimensionless pitch rate etc.）.In order to obtain so
The robust control algorithm of the complicated aircraft of aerodynamic, substantial amounts of air stage combustion is necessary.
The present invention is a kind of type for combining rotary wings and fixed wing airplane advantage, be able to carry out various tradition it is fixed or
The high skill complex task that rotary wings type cannot all be performed.For example, it can be taken off including from handss with VTOL（Hovering
Ability）With from aerial crawl（During hovering）.This allows it to use in substantially any place.Additionally, work as being transformed into its level
After flight attitude, it fast and effeciently can also fly, and this is well beyond the traditional rotary wings with its similarly sized and weight
The endurance of type.After arriving at, it may switch to low latitude and flies posture slowly, accurately move up and down in the air,
Plus its compact size so that it is roundabout in urban environment, building and barrier are bypassed, or even be suitable for indoors flying
OK.The hovering pattern of its high stability makes it easy to gather fine definition, in-plant image and video.
Complicated embodiment：
Complicated embodiment includes some or all aforesaid complicated functions and associated components.Extra increased sensor and its
After his component is added, the endurance of the present invention, endurance and payload capacity would generally be reduced（Keep original constant dimension）,
And the cost of the present invention can increase.
Experimental result
The experimental model of the present invention has been created, has been tested and iterative refinement.
Statement：
Technological concept and feature that all above-described embodiments and discussion are intended to be merely illustrative of the present, so that this area is common
Technical staff is it will be appreciated that and implement the present invention, rather than the purpose of restriction the scope of the present invention.According to the present invention made etc.
Any change or modification of effect thing should belong within the scope of the present invention.
Claims (17)
1. a kind of unmanned vehicle, it is characterised in that by sticking up edge airfoil（2）The fixed wing of the low aspect ratio of composition
（1）, positioned at wing（1）An elevator or two elevons near on the inside of trailing edge（3）, one or more are located at aircraft pair
On title face and to wing（1）The rotatable drag iron that both sides extend up and down（4）, one be pointed on the aircraft plane of symmetry and
Wing（1）Upstream by motor（9）The dual rotation propeller of driving（6）, the midpoint of the wing root section string of a musical instrument（7）In wing tip section
The midpoint of the string of a musical instrument（8）Upstream is concordant, with receptor（10）And battery（11）.
2. unmanned vehicle according to claim 1, it is characterised in that described aspect ratio is 1-3.5.
3. unmanned vehicle according to claim 1, it is characterised in that described motor（9）Using with speed controlling
The electro-motor of device.
4. unmanned vehicle according to claim 1, it is characterised in that described motor（9）Using internal combustion engine, and it is equipped with
There are fuel tank and igniter.
5. unmanned vehicle according to claim 1, it is characterised in that equipped with transmitter, for sending letter to user
Breath.
6. unmanned vehicle according to claim 1, it is characterised in that equipped with gyroscope and/or accelerometer.
7. unmanned vehicle according to claim 1, it is characterised in that be mounted with satellite-based tracking system, including
But it is not limited to GPS.
8. unmanned vehicle according to claim 1, it is characterised in that be mounted with automated driving system.
9. unmanned vehicle according to claim 1, it is characterised in that including one or more receptors（10）And battery
（11）Adnexa be located inside wing, rather than be incorporated in central machine cabin.
10. unmanned vehicle according to claim 1, it is characterised in that described wing（1）Structure design be
Using the slim epidermis for having bearing capacity, its material includes composite, and inside with or without, force structure or soft core, soft
The material of core includes foam.
11. unmanned vehicles according to claim 1, it is characterised in that wing（1）With dihedral angle or dihedral.
12. unmanned vehicles according to claim 1, it is characterised in that wing（1）Gradually become from wing root to wing tip
Narrow version not only includes linear change, and including other any forms.
13. unmanned vehicles according to claim 1, it is characterised in that with taking pictures and/or photographic equipment.
14. unmanned vehicles according to claim 1, it is characterised in that with promising installation video-photographic equipment
Knuckle.
15. unmanned vehicles according to claim 1, it is characterised in that with tip vane.
16. unmanned vehicles according to claim 1, it is characterised in that equipped with collision avoidance system and various detections
Sensor.
17. unmanned vehicles according to claim 1, it is characterised in that with fluid storage tanks and pipeline, pipeline
Connection storage tank and nozzle liquid being discharged in surrounding.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610912192 | 2016-10-19 | ||
| CN2016109121922 | 2016-10-19 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106516097A true CN106516097A (en) | 2017-03-22 |
Family
ID=58356596
Family Applications (5)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611043635.5A Pending CN106672231A (en) | 2016-10-19 | 2016-11-24 | Unmanned aerial vehicle |
| CN201611044281.6A Pending CN106628177A (en) | 2016-10-19 | 2016-11-24 | Unmanned aerial vehicle |
| CN201611043631.7A Pending CN106516097A (en) | 2016-10-19 | 2016-11-24 | Unpiloted aircraft |
| CN201611043641.0A Pending CN106828916A (en) | 2016-10-19 | 2016-11-24 | Unmanned vehicle |
| CN201611043886.3A Pending CN106516098A (en) | 2016-10-19 | 2016-11-24 | Unpiloted aircraft |
Family Applications Before (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611043635.5A Pending CN106672231A (en) | 2016-10-19 | 2016-11-24 | Unmanned aerial vehicle |
| CN201611044281.6A Pending CN106628177A (en) | 2016-10-19 | 2016-11-24 | Unmanned aerial vehicle |
Family Applications After (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611043641.0A Pending CN106828916A (en) | 2016-10-19 | 2016-11-24 | Unmanned vehicle |
| CN201611043886.3A Pending CN106516098A (en) | 2016-10-19 | 2016-11-24 | Unpiloted aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (5) | CN106672231A (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107364572B (en) * | 2017-08-11 | 2024-01-30 | 昆明学院 | Fixed wing vector unmanned plane |
| CN107757877A (en) * | 2017-09-30 | 2018-03-06 | 肇庆高新区国专科技有限公司 | A kind of unmanned plane and regulative mode of wing adjustable angle |
| CN108298064B (en) * | 2017-11-09 | 2024-04-26 | 青岛兰道尔空气动力工程有限公司 | Unconventional yaw control system |
| US11059378B2 (en) * | 2017-11-16 | 2021-07-13 | The Boeing Company | Charging a rechargeable battery of an unmanned aerial vehicle in flight using a high voltage power line |
| TWI688519B (en) * | 2018-01-08 | 2020-03-21 | 經緯航太科技股份有限公司 | Fixed-wing aeroplane take-off system and method thereof |
| CN113883254B (en) * | 2021-10-26 | 2023-06-23 | 南通睿动新能源科技有限公司 | Double-motor pure electric reduction gearbox anti-suction system |
| CN116755473B (en) * | 2023-08-18 | 2023-11-07 | 四川腾盾科技有限公司 | Unmanned aerial vehicle aerial delivery mission planning method for wing lifting |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2315524A1 (en) * | 2000-07-28 | 2001-05-21 | John F. Austen-Brown | Personal hoverplane having four tiltmotors |
| CN201923320U (en) * | 2011-01-13 | 2011-08-10 | 杨苡 | Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle |
| CN102514712A (en) * | 2011-12-07 | 2012-06-27 | 上海大学 | Vertical take-off and landing aircraft |
| CN203681870U (en) * | 2013-12-23 | 2014-07-02 | 西安理工大学 | Vertical take-off and landing aircraft |
| CN104015925A (en) * | 2014-05-27 | 2014-09-03 | 南京航空航天大学 | Multi-purpose vertical take-off and landing unmanned aerial vehicle |
| CN104269078A (en) * | 2014-09-23 | 2015-01-07 | 苏州天益航空科技有限公司 | Method for collision detection for agricultural plant protection unmanned aerial vehicle |
| CN104290907A (en) * | 2014-10-15 | 2015-01-21 | 西南科技大学 | Novel hybrid vertical/short take-off and landing (V/STOL) unmanned aerial vehicle |
| CN204273018U (en) * | 2014-11-27 | 2015-04-22 | 济南大学 | Based on the coaxial two-wheel autonomic balance orchard spraying machine device people that WiFi controls |
| CN204433033U (en) * | 2015-02-12 | 2015-07-01 | 厦门大学 | A kind of VUAV with high lift device |
| CN204808049U (en) * | 2015-05-22 | 2015-11-25 | 刘道满 | A communication system with drones |
| CN204871604U (en) * | 2015-07-29 | 2015-12-16 | 张飞 | Wing body fuses single duct VTOL aircraft |
| CN105278546A (en) * | 2015-11-06 | 2016-01-27 | 中国航空工业经济技术研究院 | Agricultural plant protection unmanned aerial vehicle planting control system |
| CN205216194U (en) * | 2015-06-05 | 2016-05-11 | 成都航空职业技术学院 | But fixed -wing aircraft of VTOL |
| CN205581645U (en) * | 2016-03-17 | 2016-09-14 | 中山飞旋天行航空科技有限公司 | Plant protection unmanned aerial vehicle control system based on difference GPS |
| CN206394880U (en) * | 2016-10-19 | 2017-08-11 | 青岛兰道尔空气动力工程有限公司 | Unmanned vehicle |
Family Cites Families (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB592264A (en) * | 1940-04-03 | 1947-09-12 | Northrop Aircraft Inc | All-wing airplane |
| US3179352A (en) * | 1959-09-21 | 1965-04-20 | Hiller Aircraft Company Inc | Tilt wing aircraft |
| FR2617119B1 (en) * | 1987-06-26 | 1989-12-01 | Aerospatiale | BLADE OF COMPOSITE MATERIALS, WITH STRUCTURAL CORE AND PROFILED COVERING COVERING, AND MANUFACTURING METHOD THEREOF |
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| CN1321859C (en) * | 2004-03-16 | 2007-06-20 | 清华大学 | Miniature aircraft |
| US20070029403A1 (en) * | 2005-07-25 | 2007-02-08 | The Boeing Company | Dual point active flow control system for controlling air vehicle attitude during transonic flight |
| US20100123047A1 (en) * | 2008-11-14 | 2010-05-20 | Williams Aerospace, Inc. | Blended Wing Body Unmanned Aerial Vehicle |
| CN102133926B (en) * | 2011-03-08 | 2013-05-08 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
| DE102012104783B4 (en) * | 2012-06-01 | 2019-12-24 | Quantum-Systems Gmbh | Aircraft, preferably UAV, drone and / or UAS |
| US8950698B1 (en) * | 2012-10-26 | 2015-02-10 | The Boeing Company | Convertible compounded rotorcraft |
| CN102897323A (en) * | 2012-10-31 | 2013-01-30 | 无锡同春新能源科技有限公司 | Unmanned spraying and fighting aircraft for mosquito killing |
| US20150102175A1 (en) * | 2012-11-15 | 2015-04-16 | Aviron Consulting Developmentand Manufacture For Advanced Aviation | Fixed winged aircraft with foldable auto-rotation rotor |
| CN203567935U (en) * | 2013-11-14 | 2014-04-30 | 现代农装科技股份有限公司 | Ground effect flight pesticide spraying machine |
| CN103640700A (en) * | 2013-12-13 | 2014-03-19 | 江苏大学 | Anti-drifting nozzle device for spraying of fixed wing aircraft |
| CN103754360B (en) * | 2014-02-08 | 2016-08-17 | 厦门大学 | A kind of flying saucer rotorcraft |
| CN204916155U (en) * | 2015-09-16 | 2015-12-30 | 广西万维空间科技有限公司 | Multipurpose unmanned aerial vehicle |
| CN105398563A (en) * | 2015-11-13 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Wing of membrane structure |
| CN105905295A (en) * | 2016-06-14 | 2016-08-31 | 临沂高新区翔鸿电子科技有限公司 | Vertical take-off and landing fixed wing aircraft |
| CN106005366A (en) * | 2016-07-01 | 2016-10-12 | 中国人民解放军海军航空工程学院 | Pneumatic layout of dual flying wings of UAV (Unmanned Aerial Vehicle) |
-
2016
- 2016-11-24 CN CN201611043635.5A patent/CN106672231A/en active Pending
- 2016-11-24 CN CN201611044281.6A patent/CN106628177A/en active Pending
- 2016-11-24 CN CN201611043631.7A patent/CN106516097A/en active Pending
- 2016-11-24 CN CN201611043641.0A patent/CN106828916A/en active Pending
- 2016-11-24 CN CN201611043886.3A patent/CN106516098A/en active Pending
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2315524A1 (en) * | 2000-07-28 | 2001-05-21 | John F. Austen-Brown | Personal hoverplane having four tiltmotors |
| CN201923320U (en) * | 2011-01-13 | 2011-08-10 | 杨苡 | Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle |
| CN102514712A (en) * | 2011-12-07 | 2012-06-27 | 上海大学 | Vertical take-off and landing aircraft |
| CN203681870U (en) * | 2013-12-23 | 2014-07-02 | 西安理工大学 | Vertical take-off and landing aircraft |
| CN104015925A (en) * | 2014-05-27 | 2014-09-03 | 南京航空航天大学 | Multi-purpose vertical take-off and landing unmanned aerial vehicle |
| CN104269078A (en) * | 2014-09-23 | 2015-01-07 | 苏州天益航空科技有限公司 | Method for collision detection for agricultural plant protection unmanned aerial vehicle |
| CN104290907A (en) * | 2014-10-15 | 2015-01-21 | 西南科技大学 | Novel hybrid vertical/short take-off and landing (V/STOL) unmanned aerial vehicle |
| CN204273018U (en) * | 2014-11-27 | 2015-04-22 | 济南大学 | Based on the coaxial two-wheel autonomic balance orchard spraying machine device people that WiFi controls |
| CN204433033U (en) * | 2015-02-12 | 2015-07-01 | 厦门大学 | A kind of VUAV with high lift device |
| CN204808049U (en) * | 2015-05-22 | 2015-11-25 | 刘道满 | A communication system with drones |
| CN205216194U (en) * | 2015-06-05 | 2016-05-11 | 成都航空职业技术学院 | But fixed -wing aircraft of VTOL |
| CN204871604U (en) * | 2015-07-29 | 2015-12-16 | 张飞 | Wing body fuses single duct VTOL aircraft |
| CN105278546A (en) * | 2015-11-06 | 2016-01-27 | 中国航空工业经济技术研究院 | Agricultural plant protection unmanned aerial vehicle planting control system |
| CN205581645U (en) * | 2016-03-17 | 2016-09-14 | 中山飞旋天行航空科技有限公司 | Plant protection unmanned aerial vehicle control system based on difference GPS |
| CN206394880U (en) * | 2016-10-19 | 2017-08-11 | 青岛兰道尔空气动力工程有限公司 | Unmanned vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106672231A (en) | 2017-05-17 |
| CN106628177A (en) | 2017-05-10 |
| CN106516098A (en) | 2017-03-22 |
| CN106828916A (en) | 2017-06-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106516097A (en) | Unpiloted aircraft | |
| JP2021176757A (en) | Vertical Takeoff and Landing (VTOL) Aircraft | |
| CN101549754B (en) | A rotary-fixed-wing composite aircraft and its design method | |
| CN106184737B (en) | Combined type is laid out vertically taking off and landing flyer and VTOL flying method | |
| CN105711832B (en) | One kind is verted the long endurance combined type aircraft of three rotors | |
| CN104364154A (en) | Aircraft, preferably unmanned | |
| CN204473140U (en) | New vertical landing tilting rotor two axle aircraft | |
| KR102135285B1 (en) | Veryical takeoff and landing fixed wing unmanned aerial vehicle | |
| CN104290907A (en) | Novel hybrid vertical/short take-off and landing (V/STOL) unmanned aerial vehicle | |
| CN205076045U (en) | Combined type aircraft of varistructure | |
| CN207772810U (en) | It is a kind of can the aeroamphibious latent four of VTOL dwell three rotor wing unmanned aerial vehicles that vert | |
| CN206394880U (en) | Unmanned vehicle | |
| Moschetta | The aerodynamics of micro air vehicles: technical challenges and scientific issues | |
| CN108501639A (en) | A kind of hovercar | |
| CN113460300B (en) | Carrying equipment suitable for single flight | |
| CN111532428A (en) | Tilting power micro fixed wing unmanned aerial vehicle capable of freely taking off and landing | |
| CN111559499B (en) | Spherical unmanned aerial vehicle and working method | |
| Cetinsoy | Design and control of a gas-electric hybrid quad tilt-rotor UAV with morphing wing | |
| CN207417148U (en) | A Single Lift Duct VTOL Aircraft Based on Tilting Duct | |
| CN110775262B (en) | Tail seat type sea-air cross-domain aircraft device based on four-rotor drive mode | |
| US20240067329A1 (en) | Flying object control method | |
| CN107054638A (en) | A kind of underneath type coaxial double-rotary wing unmanned plane | |
| CN202753709U (en) | Upright vertical take-off and landing aircraft | |
| Hayama et al. | Trial production of variable pitch wing attached multicopter for power saving and long flight | |
| CN207078323U (en) | Microminiature can hover Fixed Wing AirVehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170322 |
|
| RJ01 | Rejection of invention patent application after publication |