CN105109697A

CN105109697A - Remote piloted vehicle powered by external power supply

Info

Publication number: CN105109697A
Application number: CN201510595305.6A
Authority: CN
Inventors: 施国樑
Original assignee: Shanghai Changyu Information Science & Technology Co Ltd
Current assignee: Shanghai Changyu Information Science & Technology Co Ltd
Priority date: 2015-09-18
Filing date: 2015-09-18
Publication date: 2015-12-02

Abstract

The invention relates to a remote piloted vehicle powered by an external power supply. The remote piloted vehicle powered by the external power supply comprises a vehicle body, the external power supply and a remote controller, wherein the external power supply continuously supplies power to the vehicle body through power transmission lines, which are used for connecting the external power supply and the vehicle body. When being only needed at a fixed point or within a small range, the remote piloted vehicle powered by the external power supply, provided by the invention, is advantaged in that the weight of a battery is smaller and the remote piloted vehicle exerts long-time air-staying flight capacity. As the acting range of the vehicle can be defined through the adoption of the power transmission lines, the remote piloted vehicle powered by the external power supply, provided by the invention, is conducive to reducing a negative effect of the vehicle as a novel weapon.

Description

External power source remotely-piloted vehicle

Technical field

The present invention relates to external power source remotely-piloted vehicle.

Background technology

Existing electric remote control aircraft comprises fixed-wing and rotary wind type, and wherein rotary wind type can be divided into again single rotor and many rotors, and they rely on battery-operated, can free flight within the scope of certain space.But its hang time is subject to capacity of cell restriction.

Summary of the invention

The object of the invention is the remotely-piloted vehicle that the hang time will be provided longer.

The present invention realizes its object and can do like this: manufacture an external power source remotely-piloted vehicle system, and described aircraft comprises fixed-wing and the large class of rotary wind type two; Aircraft comprises fuselage, electric propeller or electronic rotor, state of flight computer control system, radio signal reception process launch facility, aircraft load and remote controller, state of flight computer control system comprises satellite positioning-terminal, accelerometer, magnetometer, pressure sensor and gyroscope, adopts one group more than two to form the power transmission line in loop with the electricity consumption load of external power supply and described aircraft; External power supply supplies aircraft continually;

Manufacture a power supply unsteady flow module, realizing is the electric energy form that described aircraft needs by the high voltage-small current electric energy morphological transformation of power line transmission, the circuit that power supply unsteady flow module comprises voltage transformer, inverter and powers to DC machine, or;

Between power transmission line with described aircraft, be connected in series an automatic connector, automatic connector comprises a connector jack and a line connector plug; Line connector plug is connected with power transmission line; And automatically lock device containing a power transmission line; Connector jack and power transmission line automatically lock device and are arranged on fuselage; Power transmission line automatically locks the execution unit of device as state of flight computer control system; Power transmission line automatically locks device and comprises an electronic pressure tongue; Electronic pressure tongue comprises electromagnetism pressure tongue; Electronic pressure tongue is normally closed pushes down power transmission line; When electronic pressure tongue state from normally closed become open time, line connector plug departs from fuselage and drops under self and power transmission line Action of Gravity Field, or:

Aircraft contains an automatic wire winding device, is positioned at power transmission line below for folding and unfolding, or;

On board the aircraft and the PLC communication module that is all connected with powerline signal containing one of external power supply place, power line carrier is utilized to realize wire signal transmission; The control of aircraft flight state is comprised and adopts prior art and following technology:

The motor of electronic rotor is DC machine, and described motor adopts and is connected in series, and to described each motor parallel multifunction module, changes by the state changing multifunction module the state controlling described each motor, or;

The motor of electronic rotor is AC induction motor and directly utilizes outside three-phase alternating voltage work, the three-phase windings of described each motor adopts and is connected in series formation three branch roads, to at least one winding of described each motor or a part for a winding multifunction module in parallel, and the uniform as far as possible multifunction module of each phase power supply; The state controlling described each motor is changed by the state changing multifunction module, or;

The motor of electronic rotor is AC induction motor and utilizes voltage transformer to work after outside three-phase alternating voltage step-down, the three-phase windings of described each motor adopts and is connected in series formation three branch roads, to at least one winding of described each motor or a part for a winding or multifunction module in parallel with a part for the voltage transformer of described winding parallel, change by the state changing multifunction module the state controlling described each motor;

More than one the general linkage interface of functional component can also be adopted, or containing more than one functional component,

The described aircraft of more than two framves can also be adopted, two the above aircraft of frame be concatenated into a circuit loop by electric load by same group of power transmission line; Power transmission line contains one group of automatic branching line connector near middle part, automatic branching line connector contains an interface circuit be connected with state of flight computer control system wireless signal; The state of automatic branching line connector changes according to the state of state of flight computer control system and changes, or;

Several rotor crafts pass through one group or a branch of power transmission line and external power supply and are electrically connected; Several rotor crafts described are connected with same load is embedded, and described load comprises rigidity and nonrigid; At least two or more aircraft in several rotor crafts described and same remote controller are directly or indirect signal is connected and its state changes according to the change of described remote controller state;

Can also track be set, and order loads the trolley travelling of external power supply on track; Further, can also arrange and parallel track or the integrated electric mains made.

The present invention realizes the technical scheme of its object: manufacture an external power source remotely-piloted vehicle system, comprise aircraft and external power supply, and aircraft comprises fixed-wing and the large class of rotary wind type two; Aircraft comprises fuselage, electric propeller or electronic rotor, state of flight computer control system, radio signal reception process launch facility, aircraft load and remote controller, state of flight computer control system comprises satellite positioning-terminal, accelerometer, magnetometer, pressure sensor and gyroscope, adopts one group more than two to form the power transmission line in loop with the electricity consumption load of external power supply and described aircraft.

Described power transmission line can be connected from any orientation with aircraft.Described power transmission line adopt a ground connection or all described power transmission lines all earth-free.

One end that distributor in power transmission line and fuselage is electrically connected is called near-end, and one end that power transmission line and external power supply are electrically connected is called far-end; External power supply continues the described aircraft electric energy of supply by power transmission line.

Aircraft load comprises the facility for wireless telecommunications launch and accept, such as wifi.Related content can with reference to existing technology.

A power supply unsteady flow module can also be adopted, realizing the high voltage-small current electric energy morphological transformation of power line transmission is the electric energy form that described aircraft needs, the traditional direct current booster circuit that power supply unsteady flow module comprises voltage transformer, inverter and powers to DC machine, or;

Between power transmission line with described aircraft, be connected in series an automatic connector, automatic connector comprises a connector jack and a line connector plug; Line connector plug is connected with power transmission line; And adopt a power transmission line to automatically lock device; Connector jack and power transmission line automatically lock device and are arranged on fuselage; Power transmission line automatically locks the execution unit of device as state of flight computer control system.Power transmission line automatically locks device and comprises an electronic pressure tongue.Electronic pressure tongue comprises electromagnetism pressure tongue, and electronic pressure tongue is normally closed pushes down power transmission line; When electronic pressure tongue state from normally closed become open time, line connector plug departs from fuselage and drops under self and power transmission line Action of Gravity Field.Relevant technologies can also with reference to existing relay and Solenoid Valve Technology.

Aircraft can also be made to contain an automatic wire winding device, be positioned at power transmission line below for folding and unfolding, or;

On board the aircraft and external power supply place a PLC communication module be connected with powerline signal is all set, utilize power line carrier realize wire signal transmission.

Line connector plug and/or fuselage can also be made to connect a parachute, and set: in 0.2 second after send the instruction departing from fuselage to line connector plug, parachute starts to open.Like this, provide the means of an aircraft security, speed when line connector plug and power transmission line can also be made to fall down is unlikely to too fast, guarantees that power transmission line is packed up.

Described aircraft can also be made to be the rotary aircraft of a more than axle, to comprise more than one electronic rotor;

And make each motor of the electronic rotor of all drivings be more than one group of motors according to Space Axisymmetric two components that distribute, make the stator winding of the motor of each group of motors be connected in series and form one or more branch road, the all branch roads formed each group of motors are taked to connect or the mode of parallel connection, are connected with power supply;

To the part multifunction module in parallel of at least one winding of every platform motor or a winding and every bar branch road at least containing a multifunction module;

Multifunction module comprises flight control circuit, controlled rectification or chopper circuit, rechargeable battery, uses electric load and fictitious load; Controlled rectification or chopper circuit regulate its electric energy to export by the service time changing rectifying device; With electric load comprise filter circuit of pressure-stabilizing, state of flight computer control system, flight control circuit, for detecting the detection means of each multifunction module electric current and voltage, radio reception transmission circuit and other all possible electricity consumption devices; Fictitious load comprises variable resistance, the silicon control also comprising permanent resistor device and be connected in series with it, and fictitious load is for consuming electric energy to affect the state of its rotor motor in parallel and all rotor motors; Flight control circuit also not from controlled rectification or chopper circuit power taking, can this means that aircraft power supply capacity increases to some extent from rechargeable battery power taking when normally working completely; Flight control circuit is connected as the part of state of flight computer control system with state of flight computer control system host signal and accepts it and controls; The state controlling described each motor is changed by the state changing multifunction module, comprise: as required, when the state control overflow of aircraft flies to certain direction, can under gyrostatic guide, make some electric currents of the many consumptions of multifunction module with the rotor motor parallel being positioned at described direction, the silicon controlled service time specifically comprising the fictitious load branch road of the relevant multifunction module of order is longer; Or make variable-resistance resistance diminish, therefore this rotor reduces lift also reduce to cause the run-off the straight of aircraft axial line thus the lift of aircraft produces horizontal component to described direction promotes aircraft and move to described direction because the by-pass current of motor increases self horsepower input; The silicon control be connected in series with fictitious load, as an execution unit of the control circuit that flies, guarantees that flight control circuit controls the power of each multifunction module; For the problem that may cause aircraft lift deficiency because described multifunction module increases use energy, can solve by other means, the voltage that comprising increases external power supply solves;

Each aircraft also can adopt special lateral thrust rotor to provide the thrust of horizontal direction;

The branch road that the power load that electric attribute is suitable can also form with all described motors is connected or parallel connection;

The motor of electronic rotor can also be made to be DC machine, and described motor adopts and is connected in series, and to described each motor parallel multifunction module, changes by the state changing multifunction module the state controlling described each motor, or;

Make the motor of electronic rotor be AC induction motor and directly utilize outside three-phase alternating voltage work, the three-phase windings of described each motor adopts and is connected in series formation three branch roads, to at least one winding of described each motor or a part for a winding multifunction module in parallel, and the uniform as far as possible multifunction module of each phase power supply; The state controlling described each motor is changed by the state changing multifunction module, or;

Make the motor of electronic rotor be AC induction motor and utilize voltage transformer to work after outside three-phase alternating voltage step-down, the three-phase windings of described each motor adopts and is connected in series formation three branch roads, to at least one winding of described each motor or a part for a winding or multifunction module in parallel with a part for the voltage transformer of described winding parallel, change by the state changing multifunction module the state controlling described each motor.

External power supply can also be made to be installed on a vehicle.Directly be transported on client balcony from express delivery car for use in by courier packages.Or make external power supply be installed on a naval vessel.Or make external power supply be installed on a Submarine.Or make external power supply be installed on another aircraft.Or make external power supply be installed on aerial ladder.Or make external power supply be installed on other machines or robot; Or external power supply is worn and is cared on the body of people and animal.Trained animal such as dog can load external power supplys follow described aircraft movements on sandy beach.This conveniently takes photo by plane, or;

Track is set, comprises aerial conveyor; Aerial conveyor comprises some stubs and one group of two one steel rail be connected with ground by stub; Aerial conveyor also comprises employing one group two electric insulating the rail that is electrically connected with two electrodes of power supply respectively each other; Rail doubles as electric mains, with power supply with together with electric load, form loop; Track also comprises the form of employing two closed conducts, and described pipeline is for carrying fluid, and fluid comprises water, liquid pesticidal and fertilizer, or;

Adopt independent Transmission main line, independent Transmission main line arranges with parallel track and forms a loop with power supply, load together with the earth; Typical independent Transmission main line comprises the electric mains be positioned at above electrified railway;

The place that track is arranged includes but not limited to our side of ground, forest zone and boundary line,

Travel the logistics car loading external power supply in orbit; Logistics car comprises chassis and the logistics car computer control system of band electric drive wheel group, and logistics car loads external power supply, and external power supply is powered to aircraft by power transmission line;

The vehicle travelled in orbit also comprises freight trolley and powered dolly;

Freight trolley comprises chassis and the freight trolley computer control system of band electric drive wheel group, and its purposes comprises loads Agriculture, forestry And Animal Husbandry product and feed fertilizer and pesticide;

Powered dolly comprises the chassis of band electric drive wheel group, powered device and powered dolly computer control system, and is powered to aircraft by power transmission line;

Powered device be used for described rail or independently electric mains be electrically connected; Typical powered device is the pantograph of electrified railway locomotive;

The slide block that electronic wheels comprise roller, electric roller and coordinate with track, slide block coordinates with track and is able to take upwards not de-orbit with side pulling force; Slide block is a kind of universal component be connected with track; Stub is a kind of common components of aerial conveyor, and simple pier stud comprises the steel pipe of band concrete pipe base; The particular content of slide block and stub can with reference to prior art;

Logistics car and freight trolley also can comprise powered device;

Described aircraft configures a video monitor, comprises the video monitoring near border line for scene.

Or on described aircraft, configure an early warning radar, for completing the work of early warning plane and early warning band can being formed.Having with use cost of the unmanned early warning plane of external power supply is low, can configure a frame or multi rack in each naval vessel; Or a wireless network communication local area network antenna facility, provides Communications service to backcountry on described aircraft.

Described aircraft can also be made to be the above rotary aircraft of an axle, and this rotary aircraft comprises one is roughly in same level position film-form object with rotor; The area of this film-form object is more than 0.4 sq m and weight is light as far as possible; This film-form object in electronic rotor place perforate, or;

Film-form object is transparent or tympan surface has high-absorbility characteristic and comprises blacking, or film-form object comprises film photovoltaic cell;

Film photovoltaic cell can utilize sunshine to provide electric power.Film-form object be transparent can allow sunlight through and the photovoltaic cell arrived on fuselage.Film-form object has high-absorbility characteristic to the barrier effect of air and surface thereof can change heat energy into for the formation of the described aircraft of fire balloon effect help lifting to save electric power by sunshine.The thermal current that film-form object can also utilize below to rise lifts the described aircraft of holder to reduce power consumption; Just as eagle stretches open wings the motionless situation that just can hover in the air.Film-form object can also for the protection of umbrella effect, and at this moment, the airintake wind-tunnel on it or air inlet then both can have been kept off the rain the hail side of blocking pendant thing protection rotor, can guarantee that again rotor normally works.

More than one the general linkage interface of functional component can also be adopted, or adopt more than one functional component,

Described functional component also comprises a telemechanical flame atomizing device.For national defence and for struggle with mountain fire and to burn insulation strip in advance used.

Described functional component also comprises projectile weapon and electromagnetism projectile weapon.Tackle pirate for ocean liner to defend oneself, frighten or eliminate terrorist.

Described functional component also comprises bomb, kinetic energy bomb or glomb and loud horn, forms the pirate ship and antitank on battlefield threatened for warning to vessel.

Described functional component also comprises many physical quantity transducers.Comprise collect self suffer stricken position and strength information and send, the firepower for battlefield is investigated.

Described functional component also comprises a tracking powder and dispenses device.Invisible but the available dedicated equipment of this tracking powder is observed, and on the hair that can remain in people for a long time and clothes, for dividing into tagging in the situation letting alone target person, on road, cullet are set to destroy people and other bad persons of tire to help to seize.About the content of following the tracks of powder can with reference to prior art.

Described functional component also comprises airport bird scaring device, comprises sound scarer.

Described functional component also comprises explosive and removes or igniter; Comprise and sweep the floor thunder device and sweep submarine mine device.

Described functional component also comprises laser cutting device, needs object to be processed for cutting.

Described functional component also comprises and hangs on flexible cable below rotor craft or cloth, for sweeping away snow to building or photovoltaic battery panel.

Described functional component also comprises single load interface, and described single load interface comprises a buttocks sling apparatus and a handgrip.Buttocks sling apparatus can mention related personnel.Handgrip can make related personnel catch described aircraft to do hop.Be applicable to on-the-spot transport soldier and fire fighter.

These functional components can combinationally use, such as spray medicine and sowing simultaneously.Adopt more than one the general linkage interface of functional component can a tractor serves several purposes by connecting different functional component, manufacturing products for both peacetime and wartime us, dual-use.

Can also make between automatic wire winding device and basis and contain a revolute pair mechanism, described automatic wire winding device can be swayed, can prevent from like this because the power transmission line that the reasons such as described aircraft circuit produce is harmful to being wound around or rotation.

Or the interior storehouse making the line storehouse of non-bare wire automatic deploying and retracting line apparatus contain conductive material manufacturing, described interior storehouse keep close to non-bare wire with high potential.The operating mode of non-bare wire in cabin can be kept so good.

The described aircraft of more than two framves can also be adopted, two the above aircraft of frame be concatenated into a circuit loop by electric load by same group of power transmission line; Power transmission line contains one group of automatic branching line connector near middle part, automatic branching line connector contains an interface circuit be connected with state of flight computer control system wireless signal; The state of automatic branching line connector changes according to the state of state of flight computer control system and changes; Like this, weight or the wind-force of wherein unmanned plane burden part power transmission line described in a frame can be utilized, can wind loading rating be improved.

Like this, can also realize the turning round of mountain region place, at water surface flying time power transmission line can be avoided to be subject to the water surface tie down.

Or, several rotor crafts can also be made to be electrically connected by one group or a branch of power transmission line and external power supply; Several rotor crafts described are connected with same load is embedded, and described load comprises rigidity and nonrigid; At least two or more aircraft in several rotor crafts described and same remote controller are directly or indirect signal is connected and its state changes according to the change of described remote controller state.

Speed governing mentioned herein comprises for controlling the state of aircraft.

Rotor craft comprises a post and multiaxis rotor craft, and a post comprises single-blade and double-vane.

Insulating barrier can also be provided with in the surface at bifurcated terminals place on two naked steel wire power transmission lines are close, or;

Containing a monitor be connected with state of flight computer control system host signal on described aircraft, or;

Containing an acceleration pick-up be connected with state of flight computer control system host signal on described aircraft.

Can also form a spraying machine group, comprise two frame rotor crafts spray medicine aircraft, assisting in flying device and logistics car, logistics car is mounted with automatic wire winding device, the automatic retraction device of water delivery pipe, external power supply and pesticide container; Connect containing spray medicine port, the delivery pipe that adopts two ends to be communicated with pesticide container with spray medicine port respectively on external power supply and the power load on aircraft unit, spray medicine aircraft with power transmission line, or;

Form a sowing unit, comprise two sowing of frame rotor crafts aircraft, assisting in flying device and logistics cars, logistics car is mounted with automatic wire winding device, external power supply, the automatic retraction device of seed transport tube and seed cabin; Connect on external power supply and the power load on aircraft unit, sowing aircraft containing sowing module, the seed transport tube that adopts two ends to be communicated with seed cabin with sowing module respectively with power transmission line.

A Fiber connection aircraft and the external world can also be adopted to realize optical-fibre communications.

Also a computer control system is configured on ground.

Beneficial effect of the present invention: when only needing attachment point or one to use relevant flight device among a small circle, the remotely-piloted vehicle of external power source of the present invention can be saved the weight of many batteries by means of external power supply facility and have the ability of long-time stagnant sky flight.Civilian vessel can be made to have deal with many pirate ship to be attacked protection capability---self-dependent pre-alerting ability finds the suspicious boat beyond 10 kms, once suspicious boat leans on to obtain too near for example 60 meters, set out described unmanned plane immediately and carry gasoline or combustion gas.Shock wave that oil gas fires hits and pirates can be made dare not go infringement or open fire easily again.Because electric power supply is free, unmanned plane described in a frame can rely on power transmission three pieces of electromagnetism shooting firebombs in 1 minute.Before entering harbour, as long as report the situation of all unmanned planes to maritime sector and the fuel in firebomb is taken out, namely think to be in and no longer hold any automatic weapon state.

Still keep regular flight condition and be unlikely to direct aircraft bombing when utilizing pressure sensor to can be implemented in satellite positioning signal poor quality.Power line transmission signal is utilized more to be conducive to maintaining secrecy.

The present invention is also used in and arranges puppet role, background and performer in the air, and aloft carries out performing the bullfight comprising aerial machine ox, obtains than by synthesizing better visual effect with software to picture.The present invention can also be used for arranging screen movie or video frequency program at the water surface.Amateur photographers also can utilize aircraft of the present invention to carry out taking the acquisition in midair shooting effect close with adopting large-scale photography facility.The present invention can also by long apart from pulling the mode of electric wireline for providing driving electric power for the field machine on terraced fields aloft.

Aircraft of the present invention comprises various unmanned flight's device, adopts power transmission line can limit the sphere of action of aircraft, thus contributes to reducing its negative effect as modern weapon.

Accompanying drawing explanation

Fig. 1 is the structural representation that an external power source fixed-wing remotely-piloted vehicle is connected with external power supply.

Fig. 2 is the structural representation that the aerial marshalling of an external power source rotor remotely-piloted vehicle is connected with external power supply.

Fig. 3 and Fig. 4 is that the two plug in automatic connector of three ends is inserted into single state change structure schematic diagram inserted from two respectively, and it can be regarded as the amplification of the two plug in automatic connector of three ends in Fig. 2 embodiment.

Fig. 5 is one and utilizes aircraft to be below the structural representation that power transmission line load shared by aircraft above.

Fig. 6 is that a power transmission line surface arranges tusk and engages the structural representation realizing being in transmission connection with synchronous pulley.

Fig. 7 is that a power transmission line reels more than 270 degree azimuthal structural representations on driving rolls.

Fig. 8 is the circuit block diagram of 4 asynchronous motors serial connections of 4 axle rotor crafts.

Fig. 9 is the upper TV structure schematic diagram of an external power source 4 axle rotor remotely-piloted vehicle.

Figure 10 is the functional block diagram of a multifunction module.

Figure 11 is an autocoupling type three phase transformer circuit diagram.

Figure 12 is one 4 electronic rotor DC machine series connection and motor connect the block diagram of multifunction module.

Figure 13 is the top view of four rotor external power source remotely-piloted vehicle systems of a band isolation layer.

Figure 14 is the front elevation of four rotor external power source remotely-piloted vehicle systems of a band isolation layer.

Figure 15 is a schematic diagram utilizing power transmission line to carry out wire signal transmission.

Figure 16 is the fundamental diagram of an agricultural chemical spraying flight unit.

Figure 17 is the fundamental diagram of an agricultural sowing flight unit.

Figure 18 is the structural representation of several rotor crafts embedded connection load.

Figure 19 is the field activity schematic diagram of shared external power supply remotely-piloted vehicle hyper-speed clean-up device.

Figure 20 mono-operates in the fundamental diagram that the powered dolly doubled as on the aerial conveyor of electric mains is powered to aircraft; Figure 21 is the enlarged drawing of powered dolly in Figure 20 broken circle.

1. aircraft in figure; 2. fuselage; 3. electric propeller; 4. remote controller; 5. external power supply; 6. power transmission line; 7. automatic wire winding device; 8. wheels; 9. chassis; 10. Plane Rotation vice mechanism; 11. line storehouses; 12. line doors; The two plug in automatic connector of 13. 3 ends; 14. driverless operation ships; 15. waters surface; 16. sockets; 17. plugs; 18. Auto-plug locks; 19. electronic rotors; 21. springs; 22. support block; 23. electronic pressure tongues; 24. electric reels; 25. pedestals; 26. bifurcated terminals; 27. monitors; 28. acceleration pick-ups; 29. automatic wire winding devices; 31. tusks; 32. synchronous pulleys; 33. limiting pressure rollers; 34. close storehouse; 35. aluminium sheet inner cores; 36. heat absorption coil pipes; 37. blower fans; 38. reason line wheels; 41. rollers; 42,43,44,45. electronic rotors; 42.1,43.1,44.1,45.1 motors; 46. parachutes; 47. variable resistances; 48-51. multifunction module; 52. DC machine; 53. controlled rectification or chopper circuit; 54. rechargeable batteries; 55. use electric load; 56. fictitious loads; 57. voltage transformers; 58. windings; 59. early warning radars; 60. isolation layers; 61. flange; 62. lightweight retaining frames; 63. axial flow air channels; 64. high-pressure areas; 65. areas of low pressure; 66. aerocameras; 67. PLC communication modules; 68. spray medicine aircraft; 69. assisting in flying devices; 70. rise and fall platform; 71. pesticide containers; 72. logistics cars; 73. spray medicine port; 74. delivery pipes; 75. sowing aircraft; 76. seed cabins; 77. sowing modules; 78. seed transport tube; 79. loads; 80. flexible cable cloths; 81. photovoltaic battery panels; 82. mountain forests; 83. stubs; 84. rail; 85. power supplys; 86. electronic wheels; 87. powered devices; 88. terraced fields; 89. agricultural machinery.

Detailed description of the invention

Fig. 1 provides embodiment 1.

In embodiment 1, manufacture an external power source fixed-wing remotely-piloted vehicle 1, comprise fuselage 2, electric propeller 3, state of flight computer control system, radio signal reception process launch facility, aircraft load and remote controller 4, adopt one group two to form the power transmission line 6 in loop with external power supply 5 and aircraft electricity consumption load.

Power transmission line 6 one end near-end and aircraft 1 are electrically connected, and the other end far-end of power transmission line 6 and an automatic wire winding device 7 are in transmission connection, and are electrically connected by automatic wire winding device 7 and external power supply 5; External power supply 5 continues supply aircraft 1 electric energy by power transmission line 6.

Automatic wire winding device 7 comprises the band chassis 9 of wheels 8, Plane Rotation vice mechanism 10 and electronic reel.Automatic wire winding device 7 along with the distance flown away from of aircraft 1, automatic deploying and retracting power transmission line 6.Chassis 9 with wheels 8 makes automatic wire winding device 7 to move freely.Plane Rotation vice mechanism 10 is swayed for the automatic wire winding device 7 above chassis 9.Automatic wire winding device 7 also can not comprise chassis 9 and the plane revolute pair mechanism 10 of band wheels 8.

Can also be provided with a line storehouse 11 in fuselage 2 inside, line storehouse 11 is with a line door 12, and inside arranges the power transmission line of some windings; When line door 12 is opened, the power transmission line of inside, line storehouse is pulled out in order.The situation just opened for line door 12 in Fig. 1.Line storehouse 11 can be the cage of the hollow adopting some parallel shafts to form.

Line storehouse 11 is mainly used in the lower situation of the flight path last stages of aircraft 1, comprises enemy position and executes the task, and at this moment require that pasting ground flying as far as possible keeps hidden, unwrapping wire is just very suitable in order to use line storehouse 11.

Fig. 2 provides embodiment 2.

In embodiment 2, form a marshalling in the air with two frame rotor remotely-piloted vehicles 1.Aircraft 1 comprises fuselage 2, electronic rotor 19, state of flight computer control system, radio signal reception process launch facility, aircraft load and remote controller 4.Two frame aircraft 1 share one group of power transmission line 6 by a multichannel automatic socket device 13 and to be connected with the automatic wire winding device 7 on driverless operation ship 14 and from external power supply 5 power taking.

Adopt the frame in two frame aircraft 1 for sharing the weight of part power transmission line, be called assisting in flying device, its taking on of task comprises pull-up power transmission line 6 to avoid other frame flying distance aircraft far away---and main carry-on power transmission line 6 easily touches the unfavorable operating mode of the water surface 15.

Carry out naval searching, originally drive ship with the people that has of a scale of construction 100 tonnes, detector height 10 meters.Now change 10 tonnes, the driverless operation ship of configuring external Power supply remotely-piloted vehicle system into, flying height and the detector height of described aircraft bring up to 50 meters, and search efficiency improves 1000 times.Make described carry-on image signal transmission realize human assistance search to backstage, and employing carry out detection search in driverless operation ship 10 left and right sides configuring external Power supply remotely-piloted vehicle form.Search efficiency can reach unprecedented height.Searching ship cost is reduced to original 1/10th.

Compared with relying on the aircraft of the self-contained power supply of aircraft completely, the continuous hang time of embodiment 2 external power source remotely-piloted vehicle system extends to tens of sky from several tens minutes.

Driverless operation ship 14 in embodiment 2 can also change unmanned submarines into.Such disguise is better.

Main aircraft in embodiment 2 can be newly defined as wired cruise missile.End flight land mine, end flight submarine mine or fish, and configure relevant hot weapons, for battlefield.

External power source remotely-piloted vehicle system self configures a small amount of power electric battery for making a return voyage under the emergency state.Because the battery carried is few, even if calculate the weight into power transmission line, the lift-off weight of external power source remotely-piloted vehicle system is still lower.The aircraft of same load, its power of motor is less.

Fig. 3 and Fig. 4 provides embodiment 3.

In embodiment 3, the two plug in automatic connector of three ends comprises two sockets, 16, two plugs 17 and two Auto-plug locks 18.Plug 17 is concentric double structure and is electrically connected with power transmission line 6.Concentric double structure particular content can comprise handset earphone plug with reference to prior art.Spring 21 bearing fit is enclosed within power transmission line 6.Auto-plug lock 18 comprises to block 22 and electronic pressure tongue 23, and adopts signal to be connected with state of flight computer control system or be electrically connected.Auto-plug lock 18 for normally closed i.e. electronic pressure tongue 23 protruding and plug 17 to be pressed on block 22 thus locking plug 17; At this moment spring 21 is in compressive state.Socket 17 is also electrically connected with power transmission line 6.

Once Auto-plug lock 18 obtains electric opening according to the instruction of state of flight computer control system main frame, then electronic pressure tongue 23 is retracted, and plug 17 ejects under spring 21 promotes, and realizes automatically extracting of plug 17, and power transmission line 6 and aircraft depart from.

The two plug in automatic connector 13 of three ends of embodiment 3 removes one group of socket and plug, and the socket 16 of remainder is connected with the fuselage of aircraft after rotating up and down by picture, just forms the single plug in automatic connector in two ends.It can be used for the electrical connection of aircraft and external power supply, and in case of emergency automatically can get rid of power transmission line.Getting rid of the unmanned plane after power transmission line can rely on the electric energy of storage battery to make a return voyage.

Spring in the various automatic connector of the present invention also can.At this moment gravity can be relied on to realize automatically pulling the plug out of the socket.About the technology of these plugs can with reference to prior art.Usually require that the contact engaging and separating force of these plugs is close to zero.At the electric connector using ZIF on carrier rocket.Fig. 5 provides embodiment 4.

In embodiment 4, two frame external power source rotor remotely-piloted vehicles 1 are connected in series are connected with the automatic wire winding device 7 on ground and from external power supply 5 power taking by sharing one group of power transmission line 6.Automatic wire winding device 7 comprises an electric reel 24 and two pedestals 25 be connected with electric reel 24.And superincumbent aircraft 1 is inner, is also provided with an automatic wire winding device 29, comprises an electric reel 24.But with the automatic wire winding device 7 being arranged at ground unlike, automatic wire winding device 29 folding and unfolding is arranged in the automatic wire winding device 7 of the related content ginseng embodiment 1 of power transmission line 6(automatic wire winding device 29 below).This tandem and power transmission line arrangement bear the weight of power transmission line greatly due to aircraft below, and the aircraft be conducive to above flies get Geng Gao, freer.

Single rack aircraft adopts automatic wire winding device 29, is applicable to nap of the earth flight and without the need to dilatory power transmission line, can avoids or greatly alleviate wearing and tearing and the yoke of power transmission line, and can pack up power transmission line realization recycling.

In embodiment 4, below an aircraft adopt three naked steel wires as power transmission line, and adopt bifurcated terminals 26 to draw three power transmission lines 6, every root power transmission line adopts an automatic wire winding device to receive separately separately.Naked steel wire without insulating barrier, be conducive to heat radiation, weigh light, there is no the problem of wearout.

Insulating barrier can also be set to the surface at three naked steel wire power transmission lines close bifurcated terminals 26 place above, because once three power transmission lines generation winding upper surface portion branches first collide.

A monitor 27 be connected with state of flight computer control system host signal can also be set on described aircraft, when recognizing that three power transmission lines are in the hole, monitor 27 is reported, to cut off the electricity supply in time avoid accident to state of flight computer control system.

An acceleration pick-up 28 be connected with state of flight computer control system host signal can also be set on described aircraft, when recognize the state of described aircraft go wrong comprise horizontally rotate more than 100 degree, three power transmission lines are likely wound around time, to the report of state of flight computer control system, to cut off the electricity supply in time avoid accident.

Automatic wire winding device can also comprise retractable cable control circuit and retractable cable execution unit.Retractable cable execution unit contains the interface circuit be connected with retractable cable control circuit signal, and the state of automatic wire winding device changes according to the change of described control circuit state; Described control circuit and state of flight computer control system are networked.

In embodiment 4, make the inside face of electric reel 24 conduct heat with the heat absorption coil pipe of a compressor fridge equipment and be connected, the temperature of the two-layer power transmission line being close to electric reel 24 inside face is significantly reduced, to keep good operating mode.When most of power transmission line remains in electric reel surface, the power transmission line of aircraft load is few, its load light, the electric current of power transmission line is also less.

Two-layer diameter that the electric reel of, external diameter 0.67 meter long 1 meter at reels is the power transmission line of 2 millimeters, then the length of power transmission line reaches 2 kms.

In embodiment 4, the automatic wire winding device comprising an electric reel and two pedestals can also be reduced to a power main storehouse, namely only for depositing power transmission line.And also can conduct heat with the heat absorption coil pipe of a compressor fridge equipment and be connected in described line storehouse, for cooling.

Fig. 6 provides embodiment 5.

In embodiment 5, power transmission line 6 adopts one flat type two-wire or trigram formula; Power transmission line 6 one side surface is evenly equipped with tusk 31, forms a Timing Belt, and is connected by meshing transmission with a synchronous pulley 32 and realizes folding and unfolding.Synchronizing belt gear 32 also coordinates with a limiting pressure roller 33 and prevents power transmission line 6 from coming off.And provide power transmission line to the suitable tension of automatic wire winding device.

Below synchronous pulley 32, have a closed storehouse 34 adopting high thermal resistance material to manufacture, the hole of power transmission line 6 above closed storehouse 34 is pierced into closed storehouse 34 and is wound in the aluminium sheet inner core 35 of electric reel 24.Aluminium sheet inner core 35 conducts heat with the heat absorption coil pipe 36 of a compressor fridge equipment and is connected, and the line temperature be close on aluminium sheet inner core 35 is significantly reduced.In closed storehouse 34, fan-coil device is also set and keeps good operating mode for carrying out forced air cooling to inside, closed storehouse.Fan-coil device comprises blower fan 37 and is placed in another heat absorption coil pipe 36 of Cempression engine refrigerating apparatus in blower fan 37 front.

It is large that the Timing Belt power line transmission mode of embodiment 6 has tractive force, and power transmission line folding and unfolding length controllable precise such as can to survey at the advantage.

For the naked steel wire that friction coefficient is less, then can increase the tractive force of roller by increasing its azimuth be wrapped on roller.

Fig. 7 provides embodiment 6.

In embodiment 6, make naked steel wire power transmission line 6 first form through reason line wheels 38 suitable tension follow-up object being comprised to automatic wire winding device, keep not coming off.Then power transmission line 6 is wound around azimuth more than 290 degree on roller 41, to increase the tractive force of the less power transmission line of roller 41 pairs of friction coefficient---cable shape thing column be wound around the number of turns more, the tractive force of column to cable shape thing is larger.

Fig. 8 to 10 provides embodiment 7.

In embodiment 7, external power source 4 axle rotor craft 1 comprises fuselage 2, by the electronic rotor 42,43,44,45 of 4 ACasynchronous motor drives and parachute 46.Adopt automatic connector.The threephase stator coil of described motor is connected in series formation three branch roads respectively between two, and the head end of three branch roads is connected with the controlled three-phase alternating-current supply in variable resistance 47 and outside by naked steel wire power transmission line 6, automatic wire winding device 7.Article three, branch road end connecing, because the voltage and current of the corresponding phase winding of all described motors is equal, the state of motor is also equal, but the hand of rotation two requiring them is just two anti-.

4 described motors are divided into two groups, and order is often organized the axial line of described motor in space with aircraft and is arranged symmetrically with, the contrary rotating reactive force with cancel out each other rotor and rotor of hand of rotation.From Fig. 9 plane right-angle coordinate: electronic rotor 42,43,44,45 is in the 1st, 2,3,4 respectively, four quadrants.

By motor 42.1,43.1,44.1,45.1 tapping to 4 electronic rotors 42,43,44,45, be connected in parallel 4 multifunction modules 48,49,50,51 altogether in tap place and relevant winding overhang.To the tapping of described motor be in order to obtain lower voltage come and light current load matching.

Multifunction module 48,49,50,51 comprises flight control circuit, controlled rectification or chopper circuit 53, rechargeable battery 54, uses electric load 55 and fictitious load 56.Controlled rectification or chopper circuit 53 regulate its electric energy to export by the service time changing rectifying device.Filter circuit of pressure-stabilizing, state of flight computer control system, flight control circuit, radio reception transmission circuit and other all possible electricity consumption devices is comprised by electric load 55; Fictitious load 56 comprises resistance device and is connected in series a silicon control.Rechargeable battery 54 also has voltage regulation filtering effect; All carry out detecting to its dump energy after each aerial mission terminates and discharge and recharge to 62% to 65% of setting range such as Full Charge Capacity.The function of flight control circuit comprises the control to described motor.Flight control circuit when normally working can completely from rechargeable battery 54 power taking not from controlled rectification or chopper circuit power taking.Flight control circuit is connected as the part of state of flight computer control system with state of flight computer control system host signal and accepts it and controls.As required, when the state control overflow of aircraft flies to certain direction, some electric currents of the many consumptions of multifunction module with the rotor motor parallel in certain direction can be made, the silicon controlled service time specifically comprising the fictitious load branch road of the relevant multifunction module of order is longer, and therefore this rotor reduces lift also reduce to cause the run-off the straight of aircraft axial line thus the lift of aircraft produces a horizontal component to described direction promotes aircraft and move to described direction because the by-pass current of motor increases self horsepower input.The silicon control be connected in series with fictitious load, as an execution unit of the control circuit that flies, guarantees that flight control circuit controls the power of each multifunction module.

When flowing through the electric current of multifunction module 48,49,50,51 from zero to time maximum, the power of asynchronous dynamo 42.1,43.1,44.1,45.1 is minimum from being up to.

The status controlling packet of aircraft is drawn together:

By regulating the voltage of the controlled three-phase alternating-current supply in outside and/or frequency, and regulate each variable resistance 52, can realize described motor power control and/or rotating speed control thus realize to the status controlling packet of aircraft 1 draw together risings, in the air static, decline and stopping.

Utilize multifunction module 48,49,50,51 to regulate the principle of state of flight to sketch to be: when aircraft 1 is in floating state, changed the state of described a certain or several motors by synchronization regulation multifunction module 48,49,50,51 or several power, thus realize the control to flight state.For example:

Order be in the 1st, the motor winding of two electronic rotors 42,45 of 4 quadrants the electric power of the multifunction module 48,51 connect is greater than the electric power with two other multifunction module 49,50, the power reducing electronic rotor 45,42 associated motor is increased the power of electronic rotor 43,44 associated motor by this simultaneously, and causing the spatial altitude of electronic rotor 45,42 slightly lower than the spatial altitude of electronic rotor 43,44, this state makes aircraft 1 start to the direct north flight in other words of the Y-axis direction of arrow.Now, by the electric power of simultaneous equation 4 multifunction modules 48,49,50,51, will recover the power of electronic rotor 45,42, and cause electronic rotor 42,43,44,45 to be in sustained height, aircraft recovers to be in aerial quiescence.

As a same reason, reduce the power of quadrant two electronic rotor associated motor in two, the right side in 4 quadrants, aircraft can be caused to the positive flight of direction in the east.Further, because the mechanism of this change of flight device flight can superpose, thus aircraft can be realized can fly to any direction.Some measure voltage & current facilities can also be configured when needing control with convenient.The technology controlling flight state also can with reference to utilizing existing technology.

Can not certainly from the winding centre tap of described motor but directly from the relevant multifunction module of two ends power taking supply of described motor winding, and the mode of change of flight device 1 state of flight recited above is still set up.

Even if three multifunction modules are all in full power and charge condition, because can increase the input of external power supply, aircraft still can normal flight.

When external power supply 5 can not supply regular power time, extract power transmission line 6 by automatic connector and open each parachute 46, aircraft 1 declines with enough slow speed under the effect of parachute 46; Each power transmission line 6 also declines with slower speed so that the normal take-up of automatic wire winding device 7 under the effect of parachute 46.

The beneficial effect of embodiment 7 comprises: utilize and load on carry-on about 1520 volts of controlled three-phase alternating-current supplies and drive 4 operating voltages to be the AC induction motor of the electronic rotor of 380 volts, because power line voltage is high, the corresponding reduction of electric current of power transmission line, the waste of heat being quadratic relationship with electric current significantly reduces, the thinner lighter power transmission line of convenient employing; Comprise adopting adjustable transformer to regulate to realize flight power control easily by carrying out adjustment to the power supply voltage of the controlled three-phase alternating-current supply in outside.

Although use source of AC danger to increase, more reasonable to four unsteady flow modules of the feeding electric motors of 4 electronic rotors than using.Although the insulating requirements of high tension supply to motor increases, electric current is decreased to 1/4th, thinks worth.

When adopting other motors, also can adopt that this motor to electronic rotor divides into groups, the associated winding of each motor serial connection is with the design using high voltage.

Figure 11 provides embodiment 8.

In embodiment 8, there is the autocoupling type three phase transformer 57 of four taps, there are 9 taps and two terminals.The tap of 8, the right side and right side terminal form four groups of equal outputs; Often group exports and comprises a middle tap for light current multifunction module and provide the voltage of tens of volt.

With every platform motor 0.75 kilowatt meter, during three stator winding each employing 1000 volts of voltage, electric current is also with regard to 0.3 ampere.Therefore, also the design in embodiment 7 can be adopted---voltage transformer 57 is connected in series with 4 asynchronous motors, and provides the power supply of multifunction module from the stator winding tap of motor.

For the load that the early warning radar of 5 kw of power is such, relative to the voltage of 0.3 ampere tens of kilovolts, a voltage transformer is needed to provide big current.Again owing to adopting Switching Power Supply design, more need to use voltage transformer.Winding 58 provides a road independently power supply for aircraft load.

Use alternating current directly to adopt reliability high and the AC induction motor of lighter in weight, and the state of aircraft can be controlled by change voltage and/or frequency.

Embodiment 8 achieves small area analysis to adapt to the requirement to power transmission line weight, significantly reduces again the volume and weight of voltage transformer because adopting upper frequency.When adopting voltage transformer to be connected in series with asynchronous dynamo, both ensureing the operating mode of motor, having cut down again the bulking value of voltage transformer further.

Each winding of embodiment 8 autotransformer 57 also can change independent winding into and comprise coupling transformer autotransformer being changed into primary and secondary isolation.

Early warning radar can take unmanned submarines as platform, and extreme weather drops to Submarine and sinks to below the water surface.Owing to may be advanced into beyond seashore 200 nautical miles, early warning range is larger.

Figure 12 provides embodiment 9.

In embodiment 9, the DC machine 52 that the direct current (DC) supply provided by external power supply is connected in series mutually.DC machine 52 comprises motor such as the brushless motor of various applicable series connection.Each DC machine 52 all and connect a multifunction module 48,49,50,51(joins the related content of embodiment 7 above).By the flight control circuit of state of flight computer control system and multifunction module, realize the control to aircraft.

Meeting DC machine mutually under serial connection condition, the state of aircraft controls other method that prior art can also be adopted to provide.

Figure 13 and 14 provides embodiment 10 jointly.

In embodiment 10, four rotor external power source remotely-piloted vehicle systems 1 of band isolation layer comprise fuselage 2, electronic rotor 42, state of flight computer control system, radio signal reception process launch facility, early warning radar 59, bifurcated terminals 26, remote controller, external power supply 7, power transmission line 6 and isolation layer 60 as aircraft load.

Isolation layer 60 comprises aluminium sheet and plastic sheeting making with light laminated, is arranged at plane place, electronic rotor 42 place; The seamless link flange 61 up and down in the periphery of isolation layer 60; The upper edge hole of flange 61 is connected with a lightweight retaining frame 62; Isolation layer 60 is in electronic rotor 42 place's perforate and seamless adapter shaft stream air channel 63.The technology in axial flow air channel can the prior art such as axis of reference flow fan.

Lightweight retaining frame can adopt carbon fiber material, light, shock-resistant.Port below axial flow air channel can be larger than port above.

Adopt the benefit of isolation layer 60 be by isolation layer 60 can the plane of each electronic rotor 42 place below and above a maintenance high-pressure area 64 and an area of low pressure 65 respectively.When the pressure of high-pressure area 64 exceeds about 0.003 standard atmosphere in area of low pressure 65, every sq m just can produce about 30kg(10000*0.003*1) lift.And the electric power consumed is only about 1.5kw, significantly reduce than not adopting during isolation layer.Flange 61 and axial flow air channel 63 contribute to strengthening the difference of pressure between high-pressure area 64 and area of low pressure 65.The efficiency of electronic rotor can be improved in axial flow air channel 63.The altitude range of flange 61 can get 50 to 600 millimeters; The altitude range in axial flow air channel 63 can get 10 to 65 millimeters.

When embodiment 10 is used as the radar picket in 7 km high-altitudes, adopt 22kv900 hz AC electricity and adopt transformer pressure-reducing, power line current 0.3 ampere, power is about 10kw(1.732*22000*0.3*0.88 ≈ 10.059).

Adopt the copper facing corrosion-resistant steel multiply bare wire of 3 sectional area 0.15mm2, consider that the resistance of temperature rise is total up to 15400 Ω (3*0.11/0.15*7000), line loss is total up to 1.386kw, round 1.4kw; Copper coated effect makes weight constant resistance reduce to some extent, is applicable to 900 hz AC electricity and reply hydrogen embrittlement.Article 3, copper facing corrosion-resistant steel multi cord gross weight 24kg.

The load of the quadrotor 1 with isolation layer amounts to 50kg and comprises: power transmission line 24kg(0.15*0.01*100*7.6*7*3=23.94), self 16kg of early warning radar 10kg, unmanned plane comprises the electronic rotor of 4 axle 4kg, fuselage comprise parachute 4kg, communication control and other 1kg, voltage transformer 7kg altogether.

In aircraft 1 every kilowatt of rotor motor load 20kg, electrical efficiency 0.95, embodiment 7 is power consumption 9.6kw altogether, comprising: 4 electronic rotor power consumption 2.7kw(50/20/0.95 ≈ 2.64), power transmission line and transformer loss 1.9kw, other part electricity consumptions of unmanned plane 0.4kw, early warning radar 5kw.

The permissible stress of steel wire: 24/(0.15*3) ≈ 53.3.Pass through.

When motor adopts 20 pole, rotating speed is a little less than 5400 revs/min.Aircraft in embodiment 10 is when taking off, and power transmission line 6 load is light, at this moment adopts low voltage and lower frequency; Along with aircraft rising power transmission line load increases, voltage and frequency are also improved later.The full power state of maximum voltage and frequency is finally reached when opening all loads.

Early warning radar in embodiment 10 can also change wireless network communication local area network antenna facility into, comprises wifi sending and receiving apparatus, on a large scale, provide related service.

Figure 15 provides embodiment 11.

In embodiment 11, external power source remotely-piloted vehicle system 1 comprises aerocamera 66, is connected with automatic wire winding device 7 by power transmission line 6 with external power supply 5; Remote controller 4 is adopted to realize the communication contact with aircraft 1.In embodiment 11, also on aircraft 1 and external power supply 5 place a PLC communication module 67 be connected with power transmission line 6 signal is all set, utilize power transmission line 6 realize wire signal transmission, carry out communication.About the content of electric line carrier communication can with reference to existing electric wireline Internet technology.

Figure 16 provides embodiment 12.

Embodiment 12, spraying machine group comprises two frame rotor crafts spray medicine aircraft 68, assisting in flying device 69 and logistics car 72, and logistics car 72 is mounted with automatic wire winding device 7, the automatic retraction device of water delivery pipe 74, external power supply 5, landing platform 70 and pesticide container 71.Connect on external power supply 5 and the power load on aircraft unit, spray medicine aircraft containing spray medicine port 73, the delivery pipe 74 that adopts two ends to be communicated with pesticide container 71 with spray medicine port 73 respectively with power transmission line 6.Pesticide container 71 is configured with liquid and promotes facility, comprises boost pump.Logistics car 72 is from motion tracking assisting in flying device 69.Spray medicine port 73 is a pipe horizontal, its side has round, and related content such as spray medicine port 73 grade can with reference to prior art.

The brief introduction of work principle of embodiment 13 is: system boot self-inspection comprises assisting in flying device 69 and spray medicine aircraft 68 and successively stops from landing platform 70 hovering that rises; Then logistics car 72 is followed spraying machine group and is reached the spot, and pesticide container 71 starts liquid and promotes facility and implement the operation of spray medicine.And adopt resupply vehicle in good time to pesticide container dosing.In operation process, the automatic retraction device automatic deploying and retracting power transmission line 6 of automatic wire winding device 7 and water delivery pipe 74 and water delivery pipe 74.Operation completes, and makes liquid promote facility and oppositely sucks back liquid to pesticide container 71.Then two frame aircraft drop on landing platform 70, recall storehouse.

Due to can long-time continuous operation, the present invention be higher 3 times than the existing spray medicine aircraft work efficiency that can only work several minutes, need not configure the employee changing battery.Again because the operation of spray medicine is not interrupted, neither drain spray is also seldom sprayed.Efficiency height also means can be killed locust and not allow it run away within a few hours.The wind of cyclogyro contributes to the back side that medicament arrives plant leaf, and this is original advantage.

The weight of water delivery pipe 74 and power transmission line 6 shared by assisting in flying device 69, realizes spray medicine aircraft 68 above its fuselage, connect the degree of freedom that power transmission line 6 adds spray medicine; The support of assisting in flying device 69 can also increase the Distance geometry area of spray medicine aircraft 68 operation.

Figure 17 provides embodiment 13.

Embodiment 13, sowing unit comprises two sowing of frame rotor crafts aircraft 75, assisting in flying device 69 and logistics cars 72, and logistics car 72 is mounted with automatic wire winding device 7, external power supply 5, the automatic retraction device of seed transport tube 78, landing platform 70 and seed cabin 76.Connect on external power supply 5 and the power load on aircraft unit, sowing aircraft 75 containing sowing module 77, the seed transport tube 78 that adopts two ends to be communicated with seed cabin 76 with sowing module 77 respectively with power transmission line 6.Seed cabin 76 is configured with the automatic retraction device that seed promotes facility and seed transport tube 78, comprises pneumatic convey facility, specifically can with reference to related art.Logistics car 72 is from motion tracking assisting in flying device 69.Sowing module 77 is according to the design of different seeds, and related content can with reference to prior art.

The brief introduction of work principle of embodiment 13 is: system boot self-inspection comprises assisting in flying device 69 and sowing aircraft 75 and successively to go up to the air hovering; Then logistics car 72 follow sowing unit reach the spot, seed cabin 76 start seed promote facility implement seeding operation.And adopt resupply vehicle to carry out supply to seed cabin 76 in good time.In operation process, the automatic retraction device automatic deploying and retracting power transmission line 6 of automatic wire winding device 7 and seed transport tube 78 and seed transport tube 78.Operation completes, and makes seed promote facility and oppositely sucks back seed to seed cabin 76.Then storehouse is recalled.

Due to can long-time continuous operation, it is high that the present invention sows flight unit work efficiency.

The weight of seed transport tube 78 and power transmission line 6 shared by assisting in flying device 69, and the support of assisting in flying device 69 can also increase the operation Distance geometry area of sowing aircraft 75.

In embodiment 12, in the automatic retraction device of water delivery pipe 74 and embodiment 13, the automatic retraction device related content of seed transport tube 78 please join automatic wire winding device 7 in embodiment 1 and prior art.

The function of the operation Distance geometry area of embodiment 12 increase sowing aircraft 75 can also by long apart from pulling the mode of electric wireline for providing driving electric power for the field machine on terraced fields aloft.

Figure 18 provides embodiment 14.

Embodiment 14, several rotor crafts 1 are electrically connected with external power supply 5 by one group or a branch of power transmission line 6; Several rotor crafts 1 described are connected with same nonrigid load 79 is embedded.Two or more aircraft in several rotor crafts 1 and same remote controller 4 are directly or indirect signal is connected and its state changes according to the change of remote controller 4 state.

Load in embodiment 14 also can be the load of rigidity.And the element of traditional culture, the element of magic can be added.Embodiment 14 is aloft played and is described various story, can meet the demand of the aesthetic of people and amusement.

Figure 19 provides embodiment 15.

Embodiment 15, manufactures remotely-piloted vehicle hyper-speed clean-up device, comprises rotor craft 1 and flexible cable cloth 80; Rotor craft 1 comprises fuselage 2, several electronic rotor 45, state of flight computer control system and remote controllers; Flexible cable cloth 80 hangs on below aircraft 1; Flexible cable comprises nylon rope; Cloth comprises canvas.Adopt a power transmission line 6 to connect external power supply 5 and aircraft 1, and provide electric energy to aircraft 1 continually.Embodiment 15 adopts two frame aircraft 1 to share an external power supply 5.External power supply 5 is loaded on a logistics car 72; The passage of logistics car 72 between the photovoltaic battery panel 81 not yet swept away snow crosses automatically.

When sweeping away snow, the powerful bottom blowing air current of the electronic rotor of rotor craft 1 45 add flexible cable cloth 80 take out hit shake double action under, as Figure 19 dashed middle line describe photovoltaic battery panel 81 on accumulated snow be slipped to ground.

Figure 20 and Figure 21 provides embodiment 16.

Embodiment 16, arranges aerial conveyor in mountain forest 82, and aerial conveyor is comprised mutual electric insulating between some stubs 83 and one group of two one steel rail 84, two one steel rail 84 be connected with ground by stub 83 and is electrically connected with two electrodes of power supply 85 respectively; Rail 84 doubles as electric mains, with power supply 85 with together with electric load, form loop.Rail 84 adopts roundabout form, and the length variations caused expanding with heat and contract with cold is insensitive.

Aerial conveyor travels powered dolly; Powered dolly comprises the chassis 9 of band electric drive wheel group 86, powered device 87 and powered dolly computer control system, and powered dolly computer control system comprises communication module; Powered dolly is powered to aircraft 1 by power transmission line 5; Powered device 87 is the pantograph of a band pantograph arm;

Powered device 87 rolls or sliding block joint realize being electrically connected for coordinating with rail 84; The slide block that electronic wheels 86 comprise roller, electric roller and coordinate with rail 84, the slide block coordinated with rail 84 is able to take upwards not depart from rail 84 with lateral force;

Also the logistics car and freight trolley that load external power supply can be travelled above aerial conveyor in embodiment 10; Logistics car and freight trolley also can be able to adopt powered device and rail to be electrically connected for powering to aircraft from charged pool.

In embodiment 16, power transmission line 5 is from the powered dolly on aerial conveyor, by greatly extending the distance of horizontal direction after the pulling of that assisting in flying device above, and simultaneously for the agricultural machinery 89 of terraced fields 88 li provides electric energy, provides electric energy for the agricultural main aircraft above terraced fields 88; These all contribute to solving from now on, and who comes and how to cultivate the problem of terraced fields.

Aerial conveyor travelling the logistics car loading battery can with the pine forests spray medicine in Yushan Hill; Aerial conveyor travels freight trolley, utilizes unmanned plane mao bamboon harvesting robotic to be cut down by the mao bamboon in mountain and handling to freight trolley transported a segment distance arrival highway again with truck outward transport, can realize replacing manually with machine part.

Claims

1. external power source remotely-piloted vehicle system, is characterized in that comprising aircraft and external power supply; Aircraft comprises fuselage, electric propeller or electronic rotor, state of flight computer control system, radio signal reception process launch facility, aircraft load and remote controller, state of flight computer control system comprises satellite positioning-terminal and communication module, adopts one group more than two to form the power transmission line in loop with the electricity consumption load of external power supply and described aircraft; External power supply supplies aircraft continually.

2. according to external power source remotely-piloted vehicle system according to claim 1, it is characterized in that containing a power supply unsteady flow module, realizing the high voltage-small current electric energy morphological transformation of power line transmission is the electric energy form that described aircraft needs, the circuit that power supply unsteady flow module comprises voltage transformer, inverter and powers to DC machine, or;

Aircraft contains an automatic wire winding device, is positioned at power transmission line below for folding and unfolding.

3. according to external power source remotely-piloted vehicle system according to claim 2, it is characterized in that line connector plug and/or fuselage connect a parachute, and set: 0.2 second after send the instruction departing from fuselage to line connector plug, parachute starts to open, or, described aircraft is the rotary aircraft of a more than axle, comprises more than one electronic rotor;

Multifunction module comprises flight control circuit, controlled rectification or chopper circuit, rechargeable battery, uses electric load and fictitious load; Controlled rectification or chopper circuit regulate its electric energy to export by the service time changing rectifying device; With electric load comprise filter circuit of pressure-stabilizing, state of flight computer control system, flight control circuit, for detecting the detection means of each multifunction module electric current and voltage, radio reception transmission circuit and other all possible electricity consumption devices; Fictitious load comprises variable resistance, the silicon control also comprising permanent resistor device and be connected in series with it, and fictitious load is for consuming electric energy to affect the state of its rotor motor in parallel and all rotor motors; Flight control circuit is connected as the part of state of flight computer control system with state of flight computer control system host signal and accepts it and controls; The state controlling described each motor is changed by the state changing multifunction module, comprise: as required, when the state control overflow of aircraft flies to certain direction, can under gyrostatic guide, make some electric currents of the many consumptions of multifunction module with the rotor motor parallel being positioned at described direction, the silicon controlled service time specifically comprising the fictitious load branch road of the relevant multifunction module of order is longer; Or make variable-resistance resistance diminish, therefore this rotor reduces lift also reduce to cause the run-off the straight of aircraft axial line thus the lift of aircraft produces horizontal component to described direction promotes aircraft and move to described direction because the by-pass current of motor increases self horsepower input; The silicon control be connected in series with fictitious load, as an execution unit of the control circuit that flies, guarantees that flight control circuit controls the power of each multifunction module;

The motor of electronic rotor comprises DC machine, and described motor adopts and is connected in series, and to described each motor parallel multifunction module, changes by the state changing multifunction module the state controlling described each motor, or;

The motor of electronic rotor is AC induction motor and utilizes voltage transformer to work after outside three-phase alternating voltage step-down, the three-phase windings of described each motor adopts and is connected in series formation three branch roads, to at least one winding of described each motor or a part for a winding or multifunction module in parallel with a part for the voltage transformer of described winding parallel, change by the state changing multifunction module the state controlling described each motor.

4., according to external power source remotely-piloted vehicle system according to claim 1, it is characterized in that external power supply is installed on a vehicle; Or external power supply is installed on a naval vessel; Or external power supply is installed on a Submarine; Or external power supply is installed on another aircraft; Or external power supply is installed on aerial ladder; Or external power supply is installed on other machines or robot; Or external power supply is worn and is cared on the body of people and animal, or;

Track is set, comprises aerial conveyor; Aerial conveyor comprises some stubs and one group of two one steel rail be connected with ground by stub; Aerial conveyor also comprises employing two electric insulating the rail that is electrically connected with two electrodes of power supply respectively each other; Rail doubles as electric mains, with power supply with together with electric load, form loop; Track also comprises the form of employing two closed conducts, and described pipeline is for carrying fluid, and fluid comprises water, liquid pesticidal and fertilizer, or;

Freight trolley comprises chassis and the freight trolley computer control system of band electric drive wheel group;

The slide block that electronic wheels comprise roller, electric roller and coordinate with track, slide block coordinates with track and is able to take upwards not de-orbit with side pulling force;

Logistics car and freight trolley also can comprise powered device;

Described aircraft contains a video monitor; Or containing an early warning radar; Or containing a wireless network communication local area network antenna facility.

5., according to external power source remotely-piloted vehicle system according to claim 1, it is characterized in that described aircraft is the above rotary aircraft of an axle, it comprises one is roughly in same level position film-form object with rotor; This film-form object is in electronic rotor place perforate.

6., according to external power source remotely-piloted vehicle system according to claim 1, it is characterized in that containing more than one the general linkage interface of functional component, or containing more than one functional component,

Described functional component also comprises telemechanical flammenwerfer, projectile weapon, electromagnetism projectile weapon, bomb, loud horn, tracking powder dispenses device, explosive is removed or igniter; Described functional component also comprises and hangs on flexible cable below rotor craft or cloth.

7., according to external power source remotely-piloted vehicle system according to claim 1, it is characterized in that between automatic wire winding device and basis containing a revolute pair mechanism; Or the interior storehouse that conductive material manufactures is contained in the line storehouse of non-bare wire automatic deploying and retracting line apparatus, described interior storehouse keep close to non-bare wire with high potential.

8., according to external power source remotely-piloted vehicle system according to claim 1, it is characterized in that containing described aircraft more than two framves, two the above aircraft of frame be concatenated into a circuit loop by electric load by same group of power transmission line; Power transmission line contains one group of automatic branching line connector near middle part, automatic branching line connector contains an interface circuit be connected with state of flight computer control system wireless signal; The state of automatic branching line connector changes according to the state of state of flight computer control system and changes, or;

Several rotor crafts pass through one group or a branch of power transmission line and external power supply and are electrically connected; Several rotor crafts described are connected with same load is embedded, and described load comprises rigidity and nonrigid; At least two or more aircraft in several rotor crafts described and same remote controller are directly or indirect signal is connected and its state changes according to the change of described remote controller state.

9., according to external power source remotely-piloted vehicle system according to claim 1, it is characterized in that the surface at bifurcated terminals place on two naked steel wire power transmission lines are close is provided with insulating barrier, or;

10. according to external power source remotely-piloted vehicle system according to claim 1, it is characterized in that composition spraying machine group, comprise two frame rotor crafts spray medicine aircraft, assisting in flying device and logistics car, logistics car is mounted with automatic wire winding device, the automatic retraction device of water delivery pipe, external power supply and pesticide container; Connect containing spray medicine port, the delivery pipe that adopts two ends to be communicated with pesticide container with spray medicine port respectively on external power supply and the power load on aircraft unit, spray medicine aircraft with power transmission line, or;