CN205811542U - A kind of unmanned plane electric power system - Google Patents
A kind of unmanned plane electric power system Download PDFInfo
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- CN205811542U CN205811542U CN201620504614.8U CN201620504614U CN205811542U CN 205811542 U CN205811542 U CN 205811542U CN 201620504614 U CN201620504614 U CN 201620504614U CN 205811542 U CN205811542 U CN 205811542U
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Abstract
The utility model discloses a kind of unmanned plane electric power system, described electric power system includes main power source, secondary power supply, accessory power supply；Main power source, secondary power supply, accessory power supply are sequentially connected with；Described main power source includes: electronic control unit ECU, electromotor, electromotor, controller, throttle, rectification unit, encoder, filter unit；Described secondary power supply includes: intelligent charge unit, constant voltage unit；Filter unit in described main power source is connected with intelligent charge unit and constant voltage unit respectively；Described accessory power supply includes accumulator；Described accumulator is connected with intelligent charge unit.Unmanned plane electric power system of the present utility model can be powered for all kinds of unmanned planes, be applicable to multi-rotor aerocraft, driven helicopter, can tiltrotor etc., power can be adjusted according to actual needs, convenient, flexible, science and technology is strong, meets the power demands of all kinds of heavy load long endurance unmanned aircraft.
Description
Technical field
This utility model relates to aircraft intelligent power supply technical field, particularly relates to a kind of unmanned plane electric power system.
Background technology
Along with controlling the development of technology, hardware technology etc., the product technology such as fixed-wing unmanned plane, depopulated helicopter and four rotor wing unmanned aerial vehicles is the most ripe, and many products have put goods on the market, but its function singleness, during boat short, carrying load ability is poor, it is impossible to meet needs when heavy load, long boat.
Since being born, unmanned plane is mainly used in military aspect, as the weapon of intelligentize and informatization, unmanned plane scouting, monitor, communicate, at a distance the aspect such as attack played an important role.In recent years, unmanned plane also gets more and more in the application of civilian aspect, and various countries gradually open at the civilian aspect of unmanned plane, multiple fields such as unmanned plane has been widely used for public safety, emergency rescue, agricultural, environmental protection, traffic, communication, meteorology, video display are taken photo by plane.Certainly, along with renewal and the development of technology, civilian unmanned plane will welcome unprecedented opportunity to develop, and application prospect is the most wide.
And the most extensive with fixed-wing unmanned plane, depopulated helicopter and four rotor wing unmanned aerial vehicles in the unmanned plane of reality application now, but weak point is also apparent from.Although common fixed-wing unmanned plane speed is fast, but takes off and need runway, based on runway or net collision recovery during landing, the most usually it is limited by site influence, it is impossible to response quick to accident, adapts to ability.Although common rotor wing unmanned aerial vehicle or depopulated helicopter can be with VTOL, but it is owing to being affected by design itself, it is impossible to high-speed flight, voyage is shorter, and loads the lowest, the performance of the pure the most restricted battery of electronic gyroplane, it is impossible to flying for long time.These all deficiencies, greatly limit the range of application of unmanned plane.Therefore, currently marketed unmanned plane is still based on " can see ", observe just for target, and going deep into along with unmanned plane application, people have only been not content with " can see ", also require " can touch ", " can operate ", such as flying platform lift-launch mechanical arm, circuit are patrolled and examined middle damaged location and simply repair, or carry out circuit de-icing work, even carry out rescue rescues life etc..Therefore, aerial work platform when current social is badly in need of a kind of heavy load, long boat solves the tradition insurmountable problem of unmanned plane, namely needs a kind of electric power system that can continue a journey sustainedly and stably for unmanned plane.
Utility model content
For solving the problems referred to above, the utility model proposes a kind of unmanned plane electric power system, described electric power system includes main power source, secondary power supply, accessory power supply；Main power source, secondary power supply, accessory power supply are sequentially connected with；Described main power source includes: electronic control unit ECU, electromotor, electromotor, controller, throttle, rectification unit, encoder, filter unit；Described ECU is connected with electromotor, electromotor is connected with electromotor and throttle respectively, and controller is connected with throttle and is controlled throttle, and electromotor exports to rectification unit, described rectification unit is connected with electromotor and filter unit respectively, the intelligent charge unit of filter unit output to secondary power supply；Described ECU controls the time of ignition of electromotor for detecting the running status of electromotor；Described throttle uses steering wheel Tiebar structure, and controller adjusts the size of throttle by controlling the rotating speed and turning to of steering wheel, thus controls the power rotating speed output of electromotor；Described encoder is connected with generator coaxle, the speed feedback signal encoded device input of electromotor to controller, and the throttle that controller adjusts electromotor according to rotating speed set in advance to control the rotating speed of electromotor；Described secondary power supply includes: intelligent charge unit, constant voltage unit；Filter unit in described main power source is connected with intelligent charge unit and constant voltage unit respectively；Described accessory power supply includes accumulator；Described accumulator is connected with intelligent charge unit.
Wherein, described electromotor uses piston type gasoline engine, and described electromotor uses DC permanent-magnetic brushless generator.
Wherein, described rectification unit uses the uncontrollable type rectifier structure being made up of diode, or uses switching tube synchronous rectification structure.
Wherein, when using switching tube synchronous rectification structure, the three-phase output of electromotor, as the input of rectification unit, controls the conducting state of each switching tube by the state of hardware circuit detection triphasic potential.
Wherein, described filter unit uses multiple filter form, or uses various filters complex form.
Unmanned plane electric power system of the present utility model can be powered for all kinds of unmanned planes, be applicable to multi-rotor aerocraft, driven helicopter, can tiltrotor etc., power can be adjusted according to actual needs, convenient, flexible, science and technology is strong, meets the power demands of all kinds of heavy load long endurance unmanned aircraft.
This utility model has the advantages that
(1) generation technology that this utility model relates to, uncontrollable commutation technique, manostatic technique comparative maturity, it is organically merged with filtering technique and multistage intelligent charge technique, it is carried out the integrated of novelty, theory is feasible and is capable of so that unmanned vehicle can carry out flight during heavy load length boat；
(2) intelligent charge technique of the present utility model can not only make battery full charge, it is to avoid the overcharge of accumulator, has fully taken into account the relation of accumulator electric-quantity and temperature when design simultaneously, so that accumulator full charge extend its service life.This charging technique is possible not only to be charged aircraft accumulator, applies also for all kinds of accumulator in daily life, enables accumulator to play its maximum utility.
(3) this utility model is as a kind of novel intelligent power supply system, there is wide market application foreground, it is possible not only to provide design guidelines for domestic and international unmanned vehicle, apply to various unmanned vehicle, can be also used for various small-power, large-power occasions, there is wide dual-use value.
Accompanying drawing explanation
Fig. 1 is unmanned plane electric power system schematic diagram of the present utility model；
Fig. 2 is the schematic diagram of the unmanned plane electric power system of a kind of embodiment of the present utility model；
Fig. 3 is a kind of rectification unit schematic diagram of the present utility model.
Detailed description of the invention
In order to make the purpose of this utility model and advantage clearer, below in conjunction with embodiment, this utility model is further elaborated.Should be appreciated that specific embodiment described herein, only in order to explain this utility model, is not used to limit this utility model.
The utility model proposes a kind of unmanned plane electric power system, it is desirable to reaching unmanned plane and can carry out VTOL, it is possible to carry 10kg net load, it is that each electrical equipment is powered that system can export stable direct current supply voltage.
As it is shown in figure 1, the utility model proposes a kind of unmanned plane electric power system, including main power source, secondary power supply, accessory power supply.Described main power source, secondary power supply, accessory power supply are sequentially connected with.
As in figure 2 it is shown, a kind of unmanned plane electric power system of the present utility model, including main power source, secondary power supply, accessory power supply.
Described main power source includes electronic control unit ECU, electromotor, electromotor, controller, throttle, rectification unit, filter unit, encoder.Described ECU is connected with electromotor, electromotor is connected with electromotor and throttle respectively, and controller is connected with throttle and is controlled throttle, and electromotor exports to rectification unit, described rectification unit is connected with electromotor and filter unit respectively, the intelligent charge unit of filter unit output to secondary power supply.Encoder is connected with generator coaxle, the speed feedback signal encoded device input of electromotor to controller, and the throttle that controller adjusts electromotor according to rotating speed set in advance to control the rotating speed of electromotor.Described main power source, by the direct driven generator of electromotor, is the power source of whole electrical equipments on machine.
Described ECU controls the time of ignition of electromotor for detecting the running status of electromotor.
Described throttle uses steering wheel Tiebar structure, and controller adjusts the size of throttle by controlling the rotating speed and turning to of steering wheel, thus controls the power rotating speed output of electromotor.
Described electromotor uses piston type gasoline engine, and it is the machine that chemical energy is converted into mechanical energy, is a kind of using gasoline as fuel, by the interior electromotor that can change into kinetic energy.Owing to gasoline viscosity is little, evaporation is fast, with gasoline injection system, gasoline can be sprayed into cylinder, after the temperature and pressure that overcompression reaches certain, by spark ignitor, make gas expansion for doing work.The feature of petrol engine machine is rotating speed height, simple in construction, light weight, cheap, smooth running, easy maintenance.Owing to electronic response speed is far longer than the response speed that oil is dynamic, therefore utilize the kinetic energy of electromotor to provide driving source for electromotor, electromotor the electric energy sent is that whole system is powered.
Described electromotor uses DC permanent-magnetic brushless generator, and as the one of magneto, it possesses all advantages of magneto.(1) volume is little, lightweight: rotor portion uses the permanent magnet of highfield to replace solenoid, the much smaller of permanent magnet, and therefore the volume and weight of electromotor is less than conventional electric excitation generator；(2) efficiency is high, and energy-saving effect is notable: owing to permanent magnetism physical ability produces invariable magnetic field, eliminates excitation power consumption；(3) voltage waveform quality is good, it is applicable to various loading condition: owing to using electromechanical integration technology, electromotor all can make voltage-form distortion rate be maintained in less scope in the case of various different loads (including perception and capacitive load)；(4) motor overload ability is strong, is suitable for working in the presence of a harsh environment: the loss of motor is little, and temperature rise is low, and overload capacity is strong, is more suitable for working under various adverse circumstances；(5) brushless, simple in construction, reliability is high, service life is long: this electromotor brushless and slip ring, both coil on rotor simultaneously, also without electronic devices and components, permanent-magnet on rotor and iron core is fixing becomes a rigidity entirety, structure is very simple, is all much better than the electric excitation generator of routine in its reliability and service life；(6) electromagnetic interference is little, and Electro Magnetic Compatibility is good: the electromagnetic noise of motor is minimum, and the interference to communication apparatus and electronic machine is the most small, and its impact almost negligible is disregarded.
Described rectification unit can use the uncontrollable type rectifier structure being made up of diode, is characterized in can judging zero point voluntarily, it is achieved automatic reverse, it is not necessary to complicated control system；May be used without switching tube synchronous rectification structure, its topological structure, as it is shown on figure 3, the three-phase output of electromotor is as the input of rectification unit, controls the conducting state of each switching tube by the state of hardware circuit detection triphasic potential.Switching tube can use Metal-Oxide Semiconductor field effect transistor M OSFET, insulated gate bipolar transistor IGBT and other controllable type transistors, and this method for rectifying carrying load ability is strong, and voltage drop, power attenuation are relatively low, it is possible to meet all kinds of occasion.
Described filter unit uses multiple filter form, or various filters complex form.The first order of multiple filter filters the triple-frequency harmonics of first-harmonic, and the second level filters the d. c. voltage signal the seventh harmonic exported by rectification unit；Various filters is the compound, so that output voltage is a constant d. c. voltage signal of τ mode filter and pi type filter；
Described secondary power supply includes intelligent charge unit, constant voltage unit.Filter unit in described main power source is connected with intelligent charge unit and constant voltage unit respectively.Secondary power supply is by the electric energy that main power source transformation of electrical energy is another kind of specification, to meet the power demands of each several part.Owing to the voltage of main power source does not mates with the voltage value of electrical equipment and accumulator charging voltage value, so needing the magnitude of voltage that main power voltage is transformed to be mated with electrical equipment and battery charging voltage through constant voltage unit and intelligent charge unit.
Described intelligent charge unit uses Four step charge method, when the voltage of battery is less than predetermined threshold voltage, a little trickle current charging can be used, make voltage rise to the voltage corresponding with battery zero capacity, it is to avoid to cause short circuit due to big charging current；When cell voltage has exceeded the threshold voltage of trickle charge, and at this moment charger circuit proceeds to large current charge duty, and in this charged state, the main electricity of battery is resumed；Then charge up device and proceed to overcharge condition, make battery full charge within a short period of time to guarantee to deposit；After experienced by the stage of overcharging, battery enters Float duty, now the charging voltage of battery is a steady state value, and at this moment charger is for maintaining the constant required charging current of cell voltage, and this charging current can be utilized to compensate the battery electric quantity minimizing caused by the leakage current of battery.
Described constant voltage unit uses ancient card converter technique and soft resonant transformation technological incorporation, and ancient card converter technique both can carry out boosting inverter can also carry out decompression transformation, simultaneously through the combination with integrated magnetic, can be greatly reduced the ripple of output voltage；And by the fusion of ancient card converter technique with soft resonant transformation technology, then can be substantially reduced the switching loss of power power-supply, reduce sound pollution and electromagnetic interference；Output voltage can be maintained desired value through accurate parameter tuning, there is stronger carrying load ability.Described constant voltage unit exports to electrical equipment.In the present embodiment, carrying out example only with two constant voltage unit, and in reality, constant voltage unit can have multiple, can need configuration according to real work, this utility model is not limited thereto.
Described accessory power supply includes accumulator.Described accumulator is connected with intelligent charge unit.Described accessory power supply is as the backup battery of main power source, and predominantly unmanned plane boat front/rear is prepared, started sustainer etc..
Unmanned plane of the present utility model uses electronic rotor provide lift, onward impulse for complete machine and realize the stability contorting of unmanned plane, makes the characteristics match of electromotor and electromotor play respective strong point.The electronic rotor of the design uses tilting rotor, make unmanned plane can VTOL, do not limited by landform, landing of can taking off on level land or the vehicles, and had the collocation of tilting rotor and fixed-wing, can realize flying during the heavy load length boat of unmanned plane.
The kinetic energy utilizing electromotor provides driving source for electromotor, and be connected drawing generator with generator coaxle and send three-phase alternating current, alternating current is adjusted as unidirectional current by the rectified unit of three-phase alternating current, the most serious filtered unit of DC voltage of this harmonic wave becomes the voltage signal that an interference is less, this voltage is on the one hand via stand-by power supply (accumulator) charging that intelligent charge unit is system, and another aspect is that electrical equipment is powered via constant voltage unit；
The design of unmanned plane electric power system of the present utility model is firstly the need of considering supply voltage and output power, it is therefore desirable to calculates the power of whole system, carries out electromotor, electromotor and the type selecting of unmanned plane rotor motor according to output power and supply voltage.Owing to the output voltage of electromotor and the rotating speed of electromotor are directly related, and electromotor is coaxially connected with electromotor, therefore the rotating speed of electromotor directly influences the output voltage of electromotor, and electromotor uses piston-mode motor, the output of its rotating speed is controlled by adjusting throttle, the response speed that oil moves is far smaller than electronic response speed, so needing to carry out the coupling of oil electrical characteristics.The alternating current sent due to electromotor, the supply voltage adjusted with rotor electric machine controller-electricity is DC voltage, so the alternating current that electromotor exports have to be converted to unidirectional current by rectification unit, but the DC voltage harmonic ratio converted is more serious, and the general supply voltage do not adjusted with electricity matches, so needing filtered unit to filter its harmonic wave, then the DC voltage matched through the output of constant voltage unit and electricity tune supply voltage.
It should be noted that, described output power and supply voltage are directly related with rotor motor and propeller, the maximum lift that the net load that unmanned plane is carried by can be provided by with the nt wt net weight of unmanned plane (i.e. complete machine weight outside Ex-all load) and rotor motor is directly related, the lift that rotor motor is provided is then directly related with its power consumption, so the power of system is dependent on making rotor driven by motor set the power that net load amount is consumed, in view of efficiency, need to consider certain allowance when selecting electromotor, it is also required to stop allowance when selecting electromotor.
The work process of this utility model detailed description of the invention: first net load is fixed on unmanned plane, electromotor is carried out ignition trigger electromotor, controlled the rotating speed of electromotor according to the throttle of setting speed adjustment electromotor by the speed feedback signal of encoder, when electromotor reaches rated speed, start rotor motor and be gradually increased the rotating speed of rotor motor, make its rotating speed, lift is gradually increased, when rotor motor total life is more than the gross weight of fuselage net weight and net load, unmanned plane starts vertical ascent, when unmanned plane reach a certain height, tilting rotor starts to vert, the power output horizontal component of rotor motor provides forward thrust, vertical stress component and fixed-wing provide lift jointly, now owing to mainly being provided lift by fixed-wing, therefore can suitably reduce rotor motor speed, system consumption power reduces.When there are abnormal conditions, system cannot detect output voltage, bussed supply is switched to storage battery power supply, to prevent falling of unmanned plane.
Although describing this utility model by embodiment, skilled addressee will appreciate that, this utility model has many deformation and change without deviating from spirit of the present utility model, it is desirable to appended claim includes that these deformation and change are without deviating from spirit of the present utility model.
Claims (5)
1. a unmanned plane electric power system, it is characterised in that described electric power system includes main power source, secondary power supply, accessory power supply；Main power source, secondary power supply, accessory power supply are sequentially connected with；
Described main power source includes: electronic control unit ECU, electromotor, electromotor, controller, throttle, rectification unit, encoder, filter unit；Described ECU is connected with electromotor, electromotor is connected with electromotor and throttle respectively, and controller is connected with throttle and is controlled throttle, and electromotor exports to rectification unit, described rectification unit is connected with electromotor and filter unit respectively, the intelligent charge unit of filter unit output to secondary power supply；Described ECU controls the time of ignition of electromotor for detecting the running status of electromotor；Described throttle uses steering wheel Tiebar structure, and controller adjusts the size of throttle by controlling the rotating speed and turning to of steering wheel, thus controls the power rotating speed output of electromotor；Described encoder is connected with generator coaxle, the speed feedback signal encoded device input of electromotor to controller, and the throttle that controller adjusts electromotor according to rotating speed set in advance to control the rotating speed of electromotor；
Described secondary power supply includes: intelligent charge unit, constant voltage unit；Filter unit in described main power source is connected with intelligent charge unit and constant voltage unit respectively；
Described accessory power supply includes accumulator；Described accumulator is connected with intelligent charge unit.
Electric power system the most according to claim 1, it is characterised in that: described electromotor uses piston type gasoline engine, and described electromotor uses DC permanent-magnetic brushless generator.
Electric power system the most according to claim 1, it is characterised in that: described rectification unit uses the uncontrollable type rectifier structure being made up of diode, or uses switching tube synchronous rectification structure.
Electric power system the most according to claim 3, it is characterised in that: when using switching tube synchronous rectification structure, the three-phase output of electromotor, as the input of rectification unit, controls the conducting state of each switching tube by the state of hardware circuit detection triphasic potential.
Electric power system the most according to claim 1, it is characterised in that: described filter unit uses multiple filter form, or uses various filters complex form.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201620504614.8U CN205811542U (en) | 2016-05-30 | 2016-05-30 | A kind of unmanned plane electric power system |
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| CN201620504614.8U CN205811542U (en) | 2016-05-30 | 2016-05-30 | A kind of unmanned plane electric power system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105914731A (en) * | 2016-05-30 | 2016-08-31 | 西安交通大学 | Unmanned aerial vehicle power supply system |
| CN108494167A (en) * | 2018-03-23 | 2018-09-04 | 中科灵动航空科技成都有限公司 | The electric mixed power supply system of oil, method of supplying power to for vertical take-off and landing drone |
| CN109502032A (en) * | 2018-11-28 | 2019-03-22 | 中电科（德阳广汉）特种飞机系统工程有限公司 | A kind of power supply system and autogyro |
-
2016
- 2016-05-30 CN CN201620504614.8U patent/CN205811542U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105914731A (en) * | 2016-05-30 | 2016-08-31 | 西安交通大学 | Unmanned aerial vehicle power supply system |
| CN108494167A (en) * | 2018-03-23 | 2018-09-04 | 中科灵动航空科技成都有限公司 | The electric mixed power supply system of oil, method of supplying power to for vertical take-off and landing drone |
| CN109502032A (en) * | 2018-11-28 | 2019-03-22 | 中电科（德阳广汉）特种飞机系统工程有限公司 | A kind of power supply system and autogyro |
| CN109502032B (en) * | 2018-11-28 | 2022-05-24 | 中电科特种飞机系统工程有限公司 | Power supply system and autorotation gyroplane |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161214 Termination date: 20190530 |