CN206394880U - Unmanned vehicle - Google Patents
Unmanned vehicle Download PDFInfo
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- CN206394880U CN206394880U CN201621265726.9U CN201621265726U CN206394880U CN 206394880 U CN206394880 U CN 206394880U CN 201621265726 U CN201621265726 U CN 201621265726U CN 206394880 U CN206394880 U CN 206394880U
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Abstract
The utility model discloses a kind of unmanned vehicle, it is characterized in that, by the fixed wing for sticking up the low aspect ratio that edge airfoil is constituted, an elevator or two elevons near on the inside of trailing edge, one or more rotatable drag irons extended on the aircraft plane of symmetry and to both sides above and below wing, one is pointed on the aircraft plane of symmetry and in the dual rotation propeller driven by motor of wing upstream, the midpoint of the wing root section string of a musical instrument is in the midpoint upstream of the wing tip section string of a musical instrument or concordant, with receiver and battery.The utility model is able to carry out the high skill complex task that various traditional fixed-wings or rotor type can not all be performed.It can at any time be converted to rotor posture collection image and video with VTOL, with fixed-wing posture horizontal flight, not only compact, flexible, stably, and the rotor type of maximal rate, endurance and energy-saving effect all than equivalent size and weight is much higher.
Description
Technical field
The utility model is related 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 is sensed 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 it is used as electronic warfare platform.They can be divided into miniature, small-sized, tactics by size（In）Or strategy（Greatly）,
And it can be typically further categorized into based on the method that its aerodynamic lift is produced：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-, small, 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.
The advantage of mixed type unmanned plane combination fixed-wing and rotary wings unmanned plane, enables them to be successfully executed fixed-wing
Individually can not all being completed 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 aircraft, so
After be transitioned into low latitude and fly slowly, hover etc., purpose reaches that rear unmanned plane can fast and efficiently fly back user again.Substantially,
The unmanned plane is arrived at then as a fixed-wing type when performing task as a rotary wings type, but from original position,
Substantially improve flight range, endurance and maximum speed.The small/micro version of the utility model mixing wing unmanned plane can be with
It is put into knapsack, carry sensors, which pass across a street, drilling building and to be returned, or along path through jagged mountain region ring beyond several kilometers
Border.
Existing mixing unmanned plane uses many different designs and configuration.This configuration is that a tail sitting posture VTOL 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, VD-200 two contraprops and horse
Up to the equal center line away from aircraft, unnecessary complexity is added.If a motor breaks down, aircraft will collapse.
But, the motor and propeller of two long distance separation are favorably improved rolling inertia stability in roll.Its component is in a conventional manner
It is a kind of mixing wing body design within the compartment of centrally located fuselage shape.The utility model uses two positioned at aircraft centerline
Individual coaxial propellers, it is allowed to which aircraft still is able to safe flight after a propeller failure.Another advantage of the design is energy
Offset the slip-stream that propeller is produced, it is to avoid the driftage produced because drag iron is hit in slip-stream, hung down so as to avoid deflection
The additional air resistance that straight stabilizer is compensated and brought.Other each parts of the present utility model are with away from vehicle centre-line point
Cloth, to realize apt rolling inertia and stability.Other are in the unique vital point of the utility model and novel
In：There are two separated slip-streams and two groups of yaw stabilities vertically stablized in VD-200（Rather than one）, it can make
Gone off course with difference feeding force control, and the utility model design employs the drag iron that can be rotated around vertical axis and carried out partially
Boat control.In addition, VD-200 has the aileron and elevating plane of control pitching and rolling respectively.The utility model is then with elevon
The aileron and elevating plane of tradition separation are instead of, so as to control to roll and pitching simultaneously.VD-200 volumes are big in design, cost
Costliness, can only be in military field application.Design of the present utility model can be by personal use（That is explorer, fan, knapsack
Visitor/pioneer）, commercial interest（Shoot, photography etc.）, and less public sector's entity（That is place law enforcement, border security,
Environmental monitoring etc.）, purposes is flexibly extensive.It is that a variety of users can afford, and can be made sufficiently small, energy
Used in jagged mountain area, urban district and the indoor environment that the larger hybrid power aeroplane of volume is unable to safe flight.
The content of the invention
The utility model overcome the deficiencies in the prior art there is provided one it is relatively easy, economic, practical, multi-functional, with
And it is popularized in the UAV in different clients and market.
In order to achieve the above object, the utility model employs following technical scheme：
A kind of unmanned vehicle, it is characterised in that by sticking up the fixed wing for the low aspect ratio that edge airfoil is constituted,
An elevator or two elevons near on the inside of the trailing edge, it is one or more be located on the aircraft plane of symmetry and to
The rotatable drag iron that both sides extend above and below wing, one is pointed on the aircraft plane of symmetry and in wing upstream by motor
The dual rotation propeller of driving, the midpoint of the wing root section string of a musical instrument is in the midpoint upstream of the wing tip section string of a musical instrument or concordant, with connecing
Receive device and battery.
Described aspect ratio is 1-3.5.
Described motor uses the electro-motor with speed control.
Described motor uses internal combustion engine, and equipped with fuel tank and igniter.
Equipped with emitter, 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.
Annex including one or more receivers and battery is located inside wing, 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 becomes 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.
Knuckle with promising installation 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 environment.
Compared with prior art, the utility model has advantages below：
The utility model combines the advantage of fixed-wing and rotary wings unmanned plane, can perform independent fixed-wing and rotation
Task and skill that rotor unmanned plane can not be completed.
It is sufficiently small without automobile or any heavy/expensive equipment is transported, only need a people.It can be in confusion
Urban environment, even capture indoors and transmit video to earth station.
Complicated embodiment of the present utility model has the highly complex function of the size type, including：
1) systems stabilisation based on accelerometer is used in " hovering " and " keeping height " pattern so that this practicality is new
Type " can be stared at " and live object, and obtain stable high-quality video.
2) gps coordinate is used, follow the prescribed course Intelligent flight.
3) it can be maked a return voyage when control signal is disturbed according to the program comprising gps signal.
4) scalability：One user can dispose multiple units, and each fly different routes, and on a small ground
Standing, it is synchronous live from constituent parts to receive.
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 pay(useful) load can be carried to specified location.
9) collision avoidance system is carried.
The utility model have it is safe, strong, inexpensive, relatively easily use, safeguard simple and shock proof spy
Point.
Brief description of the drawings
Fig. 1 is the perspective view of one of the present utility model simple embodiment
Description of reference numerals：1- wings;2- aerofoil profiles;3 elevons;4- drag irons;6- propellers;The 7- wings
The midpoint of the root section string of a musical instrument；The midpoint of the 8- wing tips section string of a musical instrument；9- motors;10- receivers;11- batteries.
Embodiment
Simple embodiment：Simplest embodiment such as Fig. 1 of the present utility model, is constituted by sticking up edge airfoil 2
The fixed wing 1 of low aspect ratio, on the inside of the trailing edge of wing 1 near an elevator or two elevons 3, one or
Multiple to be located on the aircraft plane of symmetry and to the rotatable drag iron 4 of wing both sides extension about 1, one is pointed to aircraft pair
On title face and in the dual rotation propeller 6 driven by motor 9 of the upstream of wing 1, the midpoint 7 of the wing root section string of a musical instrument is cut in wing tip
The upstream of midpoint 8 of the face string of a musical instrument is concordant, with receiver 10 and battery 11.The embodiment does not include any complicated function,
It does not have sensor, data storage and data transmission capabilities, is mainly used in the interesting and unique model of model airplane fan
Aircraft.It may carry tip vane, it is also possible to without.
The utility model can also carry fluid storage tanks, pipeline and nozzle, and pipeline connects storage tank and is discharged into liquid
Nozzle in surrounding environment, nozzle is disposed on below wing 1 along pipeline（It is not shown）, typically storage tank and nozzle it
Between be equipped with hydraulic pump.Described storage tank, hydraulic pump and pipeline is located inside wing, to keep the streamlined and air of wing to move
Force efficiency.Pipeline is located at the trailing edges of wing to improve applications of pesticide effect.The low aspect ratio of wing result in the stronger wing
Point vortex, powerful air-swirl greatly improves the fully dispersed of agricultural chemicals.In order to keep the pitching of fuselage steady during flying
Qualitative, storage tank is designed in the mass centre of aircraft, and the significant change of liquid volume will not cause to fly in such storage tank
The significant change of machine position of mass center, this mass centre and aerodynamics of aircraft for keeping appropriate relative position
Center is extremely important.Because the performance of wing is most sensitive to the barrier and defect of its upper surface, wherein unfavorable barometric gradient
Flow separation may be caused, so nozzle is downwardly directed by the aperture of wing lower surface.In order to the flow obstacle of lower surface and
Issuable turbulent flow is minimized, and nozzle ports are flushed with lower surface.Storage tank is used to inject liquid（Such as agricultural chemicals）, will when using
Liquid in storage tank is gone out through piping from nozzles spray, 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, maximizes rollover inertia, while keeping mass centre on the fuselage plane of symmetry, and is located at away from the leading edge of wing 1 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）Driving is rotatable
Drag iron 4.The slip-stream that dual rotation propeller 6 is produced hardly band whirlpool.This burst very powerful slip-stream is by rising
Aileron 3 and drag iron 4 drop, and, also can be to machine when low-down flying speed and hovering, or when almost there is no wind speed
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 is produced
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 adds 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 the throttle of motor 9 to control its generation
Thrust.Battery 11 is used to power to propeller motor 9 and each servo motor.
The utility model is that the related energy loss of tip vortex is preferably minimized, its wing planform be from wing root to
The unique design of wing tip linear transitions.The design is especially important to low aspect ratio wing.To improve flight stability, wing design
Select swept-back wing mode.The selection of aerofoil profile 2 ensures the change with direction and control input, and its aerodynamic quality is gradually to become
Change（That is " soft " stall）, and ensure that aerodynamic efficiency is maximized while realizing acceptable high coefficient of lift combined.Wing 1
Major part be immersed in propulsion slip-stream, therefore the aerodynamic performance of wing 1（Maximum lift coefficient, stall angle etc.）
It is 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
The robust control algorithm of the complicated aircraft of such aerodynamics, substantial amounts of air stage combustion is necessary.
The utility model is a kind of type for combining rotary wings and fixed wing aircraft advantage, is able to carry out various tradition solid
The high skill complex task that fixed or rotary wings type can not all be performed.For example, it can be with VTOL, including take off from hand
（Hovering ability）Captured with from aerial（During hovering）.This allows it to be used in substantially any place.It is transformed into addition, working as
After horizontal flight posture, it can also fast and effeciently fly, and this well beyond revolves with its similarly sized and weight tradition
The endurance of rotor type.After arriving at, it may switch to low latitude and flies posture slowly, accurately move up and down in the air
It is dynamic, add its compact size so that it is roundabout in urban environment, bypass building and barrier, or even all fit indoors
Close flight.The hovering pattern of its high stability makes it easy to collection fine definition, image and video closely.
Complicated embodiment：
Complicated embodiment includes some or all foregoing complicated functions and associated components.Extra increased sensor
After being added with other assemblies, endurance of the present utility model, endurance and payload capacity would generally be reduced（Keep original chi
It is very little constant）, and cost of the present utility model can increase.
Experimental result
Experimental model of the present utility model has been created, tested and iterative refinement.
Statement：
All above-described embodiments and discussion are merely to illustrate that technological concept of the present utility model and feature, so that ability
The those of ordinary skill in domain it will be appreciated that and implement the utility model, rather than limitation scope of the present utility model purpose.Press
Any change or modification for the equivalent made according to the utility model should belong within the scope of the utility model.
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）, it is one or more to be 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 receiver（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 control
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 emitter, believe for being sent 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 receivers（10）And battery
（11）Annex be located at wing inside.
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 force structure or soft core inside composite, with or without, soft
The material of core includes foam.
11. unmanned vehicle according to claim 1, it is characterised in that wing（1）With dihedral angle or dihedral.
12. unmanned vehicle 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 vehicle according to claim 1, it is characterised in that with taking pictures and/or photographic equipment.
14. unmanned vehicle according to claim 1, it is characterised in that with promising installation video-photographic equipment
Knuckle.
15. unmanned vehicle according to claim 1, it is characterised in that with tip vane.
16. unmanned vehicle according to claim 1, it is characterised in that equipped with collision avoidance system and various detections
Sensor.
17. unmanned vehicle according to claim 1, it is characterised in that with fluid storage tanks and pipeline, pipeline
Connection storage tank and the nozzle being discharged into liquid in surrounding environment.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2016211370670 | 2016-10-19 | ||
| CN201621137067 | 2016-10-19 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206394880U true CN206394880U (en) | 2017-08-11 |
Family
ID=59371800
Family Applications (5)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621265326.8U Active CN206394885U (en) | 2016-10-19 | 2016-11-24 | Unmanned vehicle |
| CN201621265726.9U Active CN206394880U (en) | 2016-10-19 | 2016-11-24 | Unmanned vehicle |
| CN201621265147.4U Active CN206394879U (en) | 2016-10-19 | 2016-11-24 | Unmanned vehicle |
| CN201621265305.6U Active CN206437212U (en) | 2016-10-19 | 2016-11-24 | Unmanned vehicle |
| CN201621265366.2U Active CN206358363U (en) | 2016-10-19 | 2016-11-24 | Unmanned vehicle |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621265326.8U Active CN206394885U (en) | 2016-10-19 | 2016-11-24 | Unmanned vehicle |
Family Applications After (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621265147.4U Active CN206394879U (en) | 2016-10-19 | 2016-11-24 | Unmanned vehicle |
| CN201621265305.6U Active CN206437212U (en) | 2016-10-19 | 2016-11-24 | Unmanned vehicle |
| CN201621265366.2U Active CN206358363U (en) | 2016-10-19 | 2016-11-24 | Unmanned vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (5) | CN206394885U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516097A (en) * | 2016-10-19 | 2017-03-22 | 吴瑞霞 | Unpiloted aircraft |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107450639A (en) * | 2017-08-31 | 2017-12-08 | 广西田阳县创新农业综合开发有限公司 | A kind of agricultural planting intellectualized management system |
| RU2741854C1 (en) * | 2020-09-21 | 2021-01-29 | Общество с ограниченной ответственностью "ДИАМ-АЭРО" | Unmanned aviation system |
-
2016
- 2016-11-24 CN CN201621265326.8U patent/CN206394885U/en active Active
- 2016-11-24 CN CN201621265726.9U patent/CN206394880U/en active Active
- 2016-11-24 CN CN201621265147.4U patent/CN206394879U/en active Active
- 2016-11-24 CN CN201621265305.6U patent/CN206437212U/en active Active
- 2016-11-24 CN CN201621265366.2U patent/CN206358363U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516097A (en) * | 2016-10-19 | 2017-03-22 | 吴瑞霞 | Unpiloted aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN206394879U (en) | 2017-08-11 |
| CN206394885U (en) | 2017-08-11 |
| CN206358363U (en) | 2017-07-28 |
| CN206437212U (en) | 2017-08-25 |
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