Summary of the invention
It is a primary object of the present invention to provide a kind of new structural aircraft and unmanned aerial vehicle, skill to be solvedArt problem is that the unmanned aerial vehicle of power prefixed form causes many tasks that can not execute, and solid shafting drives propeller rotational mode to leadThe heat dissipation ventilation for sending a telegraph machine centre is ineffective, and motor transformation efficiency is lower.
The object of the invention to solve the technical problems adopts the following technical solutions to realize.It proposes according to the present inventionA kind of aircraft, comprising: the first noumenon, the second ontology and engine,
The first noumenon includes first end and second end, and the second end passes through the engine and second ontologyConnection；
The main shaft of the engine is hollow shaft.
The object of the invention to solve the technical problems also can be used following technical measures and further realize.
Preferably, aircraft above-mentioned, including working cell, the working cell includes at least a Working mouldBlock, at least one described operational module are set to the first end.
Preferably, aircraft above-mentioned, including electricity energy harvester, the electricity energy harvester and the engineConnection, for the energy of acquisition to be supplied to the engine.
Preferably, aircraft above-mentioned, operational module described in wherein at least one are image capture module.
Preferably, aircraft above-mentioned, wherein the engine is outer rotor motor, in the outer rotor motorThe outer surface of rotor is connected with screw blade.
Preferably, aircraft above-mentioned, wherein the first noumenon is connected with lift portion, which provides for aircraftLift；
The electricity energy harvester is connect with the lift portion.
Preferably, aircraft above-mentioned, wherein the electricity energy harvester is connected with the engine by energy storage device.
Preferably, aircraft above-mentioned, wherein the electricity energy harvester is connected with the engine by energy storage device.
Preferably, aircraft above-mentioned, wherein further include:
Control device, comprising:
Central control unit, comprising:
Processing module, prestores flying quality, and the working cell Xiang Suoshu sends instruction and receives what the working cell was sentInformation, and the confidence sent to the working cell received is calculated and is exported calculated result；
Drive module receives the flight directive that the processing module is sent；
Locating module, for obtaining location information and sending the processing module to；
Second communication module is used for the processing module and peripheral device communication；
Remote control unit, comprising:
First communication module, and the second communication module wireless telecommunications, for the remote control unit and it is described inCentre control unit is communicated, and realizes data transmission；
Operation module is input operation instruction, and is sent and is instructed to the central control unit by first communication module；
Output module, output receive the information that the central control unit is sent by first communication module.
Preferably, aircraft above-mentioned is used for wherein the central control unit further includes transmission module by the workThe information that unit is sent sends the processing module to, and the transmission module includes data transmission module and image transmitting submoduleBlock.
Also the following technical solution is employed for the object of the invention to solve the technical problems to realize.It proposes according to the present inventionA kind of unmanned aerial vehicle, the unmanned aerial vehicle be above-mentioned aircraft, the fuselage of unmanned plane includes the first noumenon and the second ontology.
The object of the invention to solve the technical problems also can be used following technical measures and further realize.
Preferably, wherein catapult-launching gear: unmanned aerial vehicle above-mentioned is set to the first noumenon；
Landing-gear, comprising:
Parachuting equipment is set to the top of the first noumenon；
Landing buffer equipment is set to the bottom of the first noumenon.
Preferably, unmanned aerial vehicle above-mentioned, wherein second ontology is connected with empennage.
Preferably, unmanned aerial vehicle above-mentioned, wherein the lift portion includes fixed-wing and movable wing, wherein the energy is adoptedAcquisition means are arranged on fixed-wing.
Preferably, unmanned aerial vehicle above-mentioned, wherein the electricity energy harvester is gallium arsenide film battery.
By above-mentioned technical proposal, aircraft of the present invention is at least had the advantage that
By the way that motor to be set to the middle part of aircraft, working cell is set to the front end of aircraft, in not shadowOn the basis of ringing aircraft power, working cell setting is had effectively achieved in aircraft front end, is appointed thereby executing correspondingBusiness, is set as hollow shaft by the main shaft of motor, improves the radiating efficiency of motor.
The above description is only an overview of the technical scheme of the present invention, in order to better understand the technical means of the present invention,And can be implemented in accordance with the contents of the specification, the following is a detailed description of the preferred embodiments of the present invention and the accompanying drawings.
Specific embodiment
It is of the invention to reach the technical means and efficacy that predetermined goal of the invention is taken further to illustrate, below in conjunction withAttached drawing and preferred embodiment, to aircraft proposed according to the present invention and unmanned aerial vehicle its specific embodiment, structure, feature andIts effect, detailed description is as follows.In the following description, what different " embodiment " or " embodiment " referred to is not necessarily same realityApply example.In addition, the special characteristic, structure or feature in one or more embodiments can be combined by any suitable form.
As illustrated in fig. 1 and 2, a kind of aircraft that one embodiment of the present of invention proposes comprising: the first noumenon 1, secondOntology 2 and engine 3, the first noumenon 1 include first end and second end, and the second end passes through the engine 3 and instituteState the connection of the second ontology 2；The main shaft of the engine 3 is hollow shaft.
By the way that motor to be set to the middle part of aircraft, working cell is set to the end of the first end of aircraft,On the basis of not influencing aircraft power, the end that aircraft first end is arranged in working cell is had effectively achieved, thusCorresponding task is executed, hollow shaft is set as by the main shaft of motor, improves the radiating efficiency of motor.
It is preferred that the aircraft includes working cell 300, the working cell 300 includes at least a workMake module, at least one described operational module is set to the first end.
Working cell is set to the end of the first end of aircraft, on the basis of not influencing aircraft power, effectivelyGround realizes the end that aircraft first end is arranged in working cell, thereby executing corresponding task.
It is preferred that the aircraft includes electricity energy harvester 4, the electricity energy harvester 4 starts with describedMachine 3 connects, for the energy of acquisition to be supplied to the engine 3.
Electric power is converted by collected energy by electricity energy harvester, the continuation of the journey to motor is realized, increasesThe time of aircraft execution task.
It is preferred that at least one described operational module is image capture module.
Image capture module is set to the end of first end, can effectively acquire aircraft first end with flightThe image information in the opposite direction of device is e.g. arranged image capture module in the front end of former setting motor, motor is arrangedBetween the first noumenon and the second ontology, the image in front can be collected by image capture module, solves front end presenceImage Acquisition dead-time problem.Other operational modules also can be set in the front end of aircraft, weapon is such as set, it can be cooperatedTarget immediately ahead of his weapon strike, turns to without aircraft, and the movement such as overturning greatly facilitates the various work of aircraftIt carries out.
It is preferred that the engine 3 is outer rotor motor, in the appearance of the rotor of the outer rotor motorFace is connected with screw blade 31.
Screw blade is connected in the outer surface of the rotor of outer rotor motor, has effectively achieved the drive to aircraft flightIt is dynamic.
It is preferred that the first noumenon 1 is connected with lift portion 5, which provides lift for aircraft；InstituteElectricity energy harvester 4 is stated to connect with the lift portion 5.
By the way that lift portion is arranged in the first noumenon, aircraft can take off and adjust flying height.Lift portion and firstBody connection, has fixed part, is additionally provided with movable part, by movable part by fixed part at least two parts, and passes through workThe adjusting change of flight height in dynamic portion.
It is preferred that the electricity energy harvester 4 is connect by energy storage device 6 with the engine 3.
Energy storage device is set in aircraft, for storing energy, provides energy needed for power for engine, passes through energyAcquisition device acquires nature energy (e.g., solar energy), and is converted into energy needed for engine (e.g., electric energy) and is stored in energy storage dressIn setting, when engine power deficiency, power is provided for engine by energy storage device.
It is preferred that as shown in figure 3, the aircraft further include:
Control device, comprising:
Central control unit, comprising:
Processing module, prestores flying quality, and the working cell Xiang Suoshu 300 sends instruction and receives the working cell 300The information of transmission, and the confidence sent to the working cell 300 received is calculated and is exported calculated result；
Drive module receives the flight directive that the processing module is sent；
Locating module, for obtaining location information and sending the processing module to；
Second communication module is used for the processing module and peripheral device communication；
Remote control unit, comprising:
First communication module, and the second communication module wireless telecommunications, for the remote control unit and it is described inCentre control unit is communicated, and realizes data transmission；
Operation module is input operation instruction, and is sent and is instructed to the central control unit by first communication module；
Output module, output receive the information that the central control unit is sent by first communication module.
Aircraft is had effectively achieved by above-mentioned control device to fly according to the control information prestored, meanwhile, it canIt, when necessary can be with manual manipulation aircraft, in order to avoid the generation of various fortuitous events can be coped in time remotely to monitor.
Specifically, in advance by the control information of aircraft with there are in processing module, route, time including flight, speedDegree, height and working cell execute the control information etc. to work accordingly.After starting engine, processing module is to drive moduleAccording to the delivering driving instruction prestored, it is made to climb with command speed to specified height, if spiraling within the specified rangeDry circle, so as to ground staff can with the state of flight of observation flight device, meanwhile, processing module turns its speed, height, engineThe information such as number are detected, and such as detect exception, to stall by drive module driving, so that aircraft lands；IfException is not detected, processing module, according to Track fusion aircraft flight is prestored, starts work in designated place by drive moduleMake unit and carries out relevant work, e.g., Image Acquisition etc..In order to which aircraft can pass through positioning accurately according to track flight is prestoredModule carries out positioning in real time to the position of aircraft, and sends location information to processing module, is compared with the track prestoredRight, if there is off-track the case where drives aircraft to correct the deviation of flight path in time.It is preferably fixed in the present embodimentPosition module is GPS positioning module.After completing task specified by working cell according to prestored instruction, by processing module according toPrestored instruction controls aircraft by drive module and makes a return voyage, and lands in designated place.
While processing module controls aircraft flight according to the flight information prestored, it can also be arranged on ground long-rangeControl unit artificially monitor and in time manually control aircraft to the flight of aircraft and work.Specifically, logicalFirst communication module of the second communication module and remote control unit of crossing central control unit in real time believes the flight of aircraftBreath is transferred to the output module of remote control unit, such as monitor, the flight of observation flight device and the working condition of working cell,When necessary, by operation module, such as operation handle issues control instruction, by the first communication module and the second communication module by handDynamic control instruction is transmitted to processing module, and preferential basis is manually controlled instruction and drives aircraft by drive module by processing moduleFlight, or control working cell work.
Above-mentioned control device has effectively achieved aircraft flight and carries out the intelligent control of relevant work, effectively protectsControl aircraft and working cell can be taken timely measure by having demonstrate,proved when fortuitous event occurs, and reduce the generation of accident.
Preferably, aircraft above-mentioned is used for wherein the central control unit further includes transmission module by the workThe information that unit is sent sends the processing module to, and the transmission module includes data transmission module and image transmitting submoduleBlock.
In central control unit, setting transmission module can be effectively in processing module and drive module and working cellBetween carry out the transmission of data, image etc..
Another embodiment of the present invention proposes a kind of unmanned aerial vehicle, and as illustrated in fig. 1 and 2, the unmanned aerial vehicle is above-mentioned fliesRow device, the fuselage of unmanned plane include the first noumenon 1 and the second ontology 2.
Above-mentioned aircraft can be applied in various aerospace equipments, such as dirigible.It is in the present embodiment preferably nothingPeople's aircraft.In the present embodiment, the first noumenon is from the head of unmanned aerial vehicle to motor portion, and wing is fixed on the first noumenonTop, the second ontology be from motor to tail part, empennage is installed in drive end unit.
By the way that motor to be set to the middle part of unmanned aerial vehicle, working cell is set to the front end of unmanned aerial vehicle,On the basis of not influencing unmanned aerial vehicle power, working cell setting is had effectively achieved in unmanned aerial vehicle front end, thereby executingCorresponding task is set as hollow shaft by the main shaft of motor, improves the radiating efficiency of motor, passes through energy acquisition listCollected energy is converted electric power by member, realizes the continuation of the journey to motor, increases the time that unmanned aerial vehicle executes task.
In the present embodiment, preferred energy acquisition device is solar battery chip, for acquiring solar energy, and by the sunElectric energy can be converted into and be stored in energy storage device, that is, in battery, in case providing electric energy when necessary for motor.Solar energy is setWhen battery chip, the damage of solar battery chip in order to prevent is positioned on the fixed part in lift portion of aircraft, that is,The position in addition to aileron rudder face of aircraft wing, while the upper surface for being set to wing can be efficiently received the photograph of sunlightIt penetrates, improves the efficiency of acquisition solar energy.Solar battery chip can be easy to operate using sticking double faced adhesive tape on wing, atThis is low.The upper counterangle of wing is 4 °~9 °.
It is preferred that catapult-launching gear 9: being set to the first noumenon 1；
Landing-gear, comprising:
Parachuting equipment 7 is set to the top of the first noumenon 1；
Landing buffer equipment 8 is set to the bottom of the first noumenon 1.
Unmanned aerial vehicle, which takes off, to be taken many forms, and e.g., sliding rail takes off, take off etc., it uses in the present embodimentThe form of catapult-assisted take-off.Specifically, when taking off, rubber band is hung over ejection hanger in the fixed ejection hanger in the two sides of the first noumenonOn, the propeller starting motor of motor is rotated, unmanned aerial vehicle is discharged.When landing, parachuting equipment is controlled by processing moduleRelease parachute is subtracted with reducing the sinking speed of unmanned aerial vehicle by the landing buffer equipment being arranged in the bottom of unmanned aerial vehicleImpact force suffered by light unmanned aerial vehicle, is effectively protected aircraft, reduces aircraft and break down, or even the possibility crashedProperty.
It is preferred that second ontology 2 is connected with empennage.
Empennage plays balanced action to unmanned aerial vehicle.
It is preferred that the lift portion 5 includes fixed-wing and movable wing, wherein the electricity energy harvester 4 is arrangedOn fixed-wing.
When electricity energy harvester is set in lift portion, in order to not influence the adjusting of aircraft altitude, while energy acquisitionDevice not will receive the active force from movable part, and so as to cause the damage of electricity energy harvester, electricity energy harvester is setIt is placed in fixed-wing.
It is preferred that the electricity energy harvester is gallium arsenide film battery.
Gallium arsenide film battery conversion efficiency reaches 34.5% (AM1.5G), is the current highest flexible thin of efficiency in the worldFilm solar cell.The battery manufacturing cost reduces by 50% or more than traditional high efficiency gallium arsenide cells, can be air equipment, shiftingDynamic electronic equipment, wearable device, internet of things equipment provide the sustainable energy power of best cost performance.
The above described is only a preferred embodiment of the present invention, be not intended to limit the present invention in any form, according toAccording to technical spirit any simple modification, equivalent change and modification to the above embodiments of the invention, this hair is still fallen withinIn the range of bright technical solution.