CN209080172U - Unmanned plane dynamical system - Google Patents
Unmanned plane dynamical system Download PDFInfo
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- CN209080172U CN209080172U CN201820681224.7U CN201820681224U CN209080172U CN 209080172 U CN209080172 U CN 209080172U CN 201820681224 U CN201820681224 U CN 201820681224U CN 209080172 U CN209080172 U CN 209080172U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
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Abstract
The utility model provides a unmanned plane dynamical system, the unmanned plane dynamical system includes an at least fuel supply unit, at least one fuel cell-powered module, an at least lithium battery power supply module, an at least system control module, an at least circuit adjusts unit and an at least unmanned plane power source, wherein the output end of the fuel supply unit is connect with the fuel cell-powered module, the output end of the fuel cell-powered module adjusts unit with the circuit and connect, the output end that the circuit adjusts unit is connect with the lithium battery power supply module and the unmanned plane power source respectively, the both ends of the system control module are connect with the voltage and current sampled point of the voltage and current sampled point of the fuel cell-powered module and the lithium battery power supply module respectively.
Description
Technical field
The utility model belongs to unmanned plane power systems art, and in particular to a kind of dynamical system based on fuel cell.
Background technique
The characteristics of fixed-wing unmanned plane is that the flight time is long, fuselage is long, quality is heavy, volume is big.Taking off for it is that it is entire
When needing energy maximum in flight course.Most of fixed-wing unmanned plane is taken off by runway gliding run-up, this
A take-off process has special requirement to the place taken off, this requires the application that just will limit fixed-wing unmanned plane.It hangs down
The mode of straight landing can allow the unmanned function of fixed-wing can takeoff and landing on very simple level land.VTOL needs it
Dynamical system provide significant energy.It is capable of providing long endurance at present, the best power source of small in volume is exactly
Hydrogen fuel cell.
The dynamical system of fixed-wing unmanned plane in the prior art is lithium battery power supply or hydrogen fuel cell or hydrogen-oxygen
It is fuel cell-powered.And the cruising ability of lithium battery dynamical system is the current major obstacles for restricting Development of UAV, so into
Row open air flight has to carry muti-piece battery back up, therefore will cause the inconvenience using operation.In addition, lithium battery is solid
Determine to be capable of providing very big power when wing unmanned plane takes off vertically, but just wastes a big chunk energy when taking off vertically
And energy is again less than supplement.The cruise duration of the dynamical system of fuel cell is long, and medium-sized fixed-wing unmanned plane takes off
When need the power of 1800~4500W or so, provide power if fuel cell is used alone for it, be capable of providing this
The fuel cell power system weight weight and volume that fixed-wing unmanned plane takes off or lands are big, and the cabin of fixed-wing unmanned plane is difficult
It can hold.In addition, the energy feedback that the propeller of fixed-wing unmanned plane generates can damage fuel cell, only the energy of this part
Amount, which bypasses, could protect fuel cell, but the energy being bypassed just is wasted.
Utility model content
One of the utility model is designed to provide a kind of unmanned plane dynamical system, and the unmanned plane dynamical system can
The cruising ability or voyage of unmanned plane are improved, to be suitble to the demanding application of cruising ability.
One of the utility model is designed to provide a kind of unmanned plane dynamical system, wherein the unmanned plane dynamical system
It is capable of the electric current and voltage of regulating system output, therefore can adapt to very more unmanned plane type and application.
One of the utility model is designed to provide a kind of unmanned plane dynamical system, wherein the unmanned plane dynamical system
It is versatile, be suitble to a plurality of types of unmanned planes such as fixed-wing, the wing that verts, more rotors.
One of the utility model is designed to provide a kind of unmanned plane dynamical system, wherein the unmanned plane dynamical system
Including a fuel cell-powered module and a lithium battery power supply module, the fuel cell-powered module and the lithium battery power supply
Module can provide power simultaneously for the unmanned plane power source in the unmanned plane dynamical system.
One of the utility model is designed to provide a kind of unmanned plane dynamical system, wherein the lithium battery power supply module
The unmanned plane dynamical system huge energy that propeller generates when taking off can be recycled without damaging the fuel cell
Power supply module.
One of the utility model is designed to provide a kind of unmanned plane dynamical system, wherein the unmanned plane dynamical system
Including an at least temperature sensor, for monitoring the temperature of the fuel cell-powered module during the work time.
One of the utility model is designed to provide a kind of unmanned plane dynamical system, wherein the unmanned plane dynamical system
Including an at least pressure sensor, the unmanned plane dynamical system passes through fuel cell-powered described in the pressure sensor monitoring
The admission pressure of module.
One of the utility model is designed to provide a kind of unmanned plane dynamical system, wherein the unmanned plane dynamical system
Including an at least system control module, by the system control module controlling and regulating system output voltage and electric current, to make
The voyage of the unmanned plane dynamical system is improved.
One of the utility model is designed to provide a kind of unmanned plane dynamical system, wherein the unmanned plane dynamical system
Fly control including an at least unmanned plane, the normal flight for guaranteeing the unmanned plane is removed by the winged control of the unmanned plane.
One of the utility model is designed to provide a kind of unmanned plane dynamical system, wherein the unmanned plane dynamical system
Can according to the actual situation regulating system output electric current and voltage, thus enable the unmanned plane dynamical system include nobody
Machine airborne equipment, therefore the use scope of unmanned plane dynamical system described in the utility model can be further increased.
In other words, the utility model mainly provides a unmanned plane dynamical system, and the unmanned plane dynamical system includes at least
One fuel supply unit, at least one fuel cell-powered module, at least a lithium battery power supply module, an at least system control mould
Block, an at least circuit adjust unit and an at least unmanned plane power source, wherein the output end of the fuel supply unit and institute
Fuel cell-powered module connection is stated, the output end of the fuel cell-powered module adjusts unit with the circuit and connect, institute
The output end for stating circuit adjusting unit is connect with the lithium battery power supply module and the unmanned plane power source respectively, the system
The both ends of control module respectively with the voltage and current sampled point of the fuel cell-powered module and the lithium battery power supply module
Voltage and current sampled point connection.
In wherein some embodiments, wherein it includes a DC/DC module and an anti-circnit NOT, institute that the circuit, which adjusts unit,
It states DC/DC module to be connected between the output end of the fuel cell-powered module and the anti-circnit NOT, the anti-circnit NOT
Output end connect with the lithium battery power supply module and the unmanned plane power source.
In wherein some embodiments, wherein the fuel supply unit includes an at least fuel supply module, at least one
Inlet channel and at least an exhaust passage, wherein the input terminal of the inlet channel is connect with the fuel supply module, institute
The output end for stating inlet channel is connect with the fuel cell-powered module, and the inlet channel and the system control module connect
It connects, so that the system control module be enable to control the inlet channel for the fuel supply module to the fuel cell
Power supply module provides fuel, one end connection of the exhaust passage fuel cell-powered module connection, the other end and outside
Connection, so that the excessive gas that the fuel cell-powered module generates be discharged by the exhaust passage.
In wherein some embodiments, wherein the fuel cell-powered module includes an air intlet, air can lead to
The air intlet is crossed into the fuel cell-powered module, to occur with the fuel that the fuel supply module provides anti-
It answers and works normally the fuel cell-powered module.
In wherein some embodiments, wherein the fuel supply unit further comprises a pressure sensor, the pressure
The control terminal of force snesor is connect with the system control module, and the other end is connect with the inlet channel, the system control
Module passes through the pressure in inlet channel described in the pressure sensor monitoring.
In wherein some embodiments, wherein the unmanned plane dynamical system includes a temperature sensor, the temperature is passed
The both ends of sensor are connect with the fuel cell-powered module and the system control module respectively, so that the system controls
Module can monitor the temperature of the fuel cell-powered module by the temperature sensor.
In wherein some embodiments, wherein the unmanned plane dynamical system further comprises that a control system adjusts electricity
Road, the both ends that the control system adjusts circuit are separately connected the fuel cell-powered module and the unmanned plane power source,
And the control system adjusts circuit and connect with the system control module.
In wherein some embodiments, wherein the unmanned plane dynamical system includes at least one first anti-reverse of control system
Block and a control system DC/DC module, wherein the first control system counnter attack module and the control system DC/DC are series at
Between the system control module and the unmanned plane power source.
In wherein some embodiments, wherein the unmanned plane dynamical system includes at least one second anti-reverse of control system
Block, the both ends of the second control system counnter attack module respectively with the system control module and the fuel cell-powered module
Connection, to make the fuel cell-powered module provide power to the system control module and avoid the fuel cell
Power supply module is damaged.
In wherein some embodiments, wherein the unmanned plane dynamical system further comprises an at least fuel cell wind
Fan, the both ends of the fuel cell fan are connect with the fuel cell-powered module and the system control module respectively, institute
The pulse width modulation interface for stating fuel cell fan is connect with the system control module, and the system control module passes through institute
State the revolving speed that pulse width modulation interface controls the fuel cell fan.
In wherein some embodiments, wherein the system control module includes an at least signal acquisition process module, institute
Signal acquisition process module electrical setting is stated in the system control module, wherein the signal acquisition process module is for acquiring
With processing signal.
In wherein some embodiments, wherein the system control module includes an at least power switching module, the electricity
Power conversion module electrical setting is used for the system control module is defeated in the system control module, the power switching module
The electrical power conversion entered is electric power needed for the fuel cell fan.
In wherein some embodiments, wherein the unmanned plane dynamical system further comprise a unmanned plane subsystem and
The attached DC/DC module of one unmanned plane, one end of the attached DC/DC module of unmanned plane be separately connected the circuit adjust unit,
The lithium battery power supply module and the unmanned plane power source, the attached DC/DC module of unmanned plane the other end connection described in
Unmanned plane subsystem, to provide power for the unmanned plane subsystem.
In wherein some embodiments, wherein the unmanned plane subsystem includes at least one unmanned machine head, the nothing
Man-machine holder is connected to the output end of the attached DC/DC module of the unmanned plane.
In wherein some embodiments, wherein the unmanned plane subsystem includes that at least one first unmanned plane flies control, institute
It states unmanned plane and flies the output end that control is connected to the attached DC/DC module of the unmanned plane.
In wherein some embodiments, wherein the flight subsystem includes an at least unmanned aerial vehicle onboard equipment, it is described
Unmanned aerial vehicle onboard equipment is connected to the output end of the attached DC/DC module of the unmanned plane.
In wherein some embodiments, wherein the unmanned plane dynamical system further comprises that one second unmanned plane flies control,
Second unmanned plane fly control input terminal connect with the system control module, second unmanned plane fly control output end and
The unmanned plane power source and the attached DC/DC module connection of the unmanned plane.
In wherein some embodiments, wherein the fuel that the fuel supply module provides includes but is not limited to sodium borohydride
With water, sodium metasilicate and water, lithium hydride and water, magnesium hydride and water, lithium borohydride and water, lithium aluminium hydride and water, aluminum hydride, ammonia borine
Complex compound, hydrocarbon, lithium aluminium hydride, magnesium borohydride, magnesium borohydride-amine complex, compression hydrogen or liquified hydrogen.
In wherein some embodiments, wherein the unmanned plane dynamical system unmanned plane power source is that motor or electricity are adjusted.
In wherein some embodiments, wherein the unmanned plane include but is not limited to fixed-wing unmanned plane, vert the wing nobody
Machine or multi-rotor unmanned aerial vehicle.
In wherein some embodiments, wherein the counnter attack circuit includes an at least metal-oxide-semiconductor and a diode control, institute
Stating inside metal-oxide-semiconductor includes an at least diode, and the pole S of the metal-oxide-semiconductor is set to the input terminal of the anti-circnit NOT, the MOS
The pole D of pipe is set to the output end of the anti-circnit NOT, the pole the S company of the input terminal of the diode control and the metal-oxide-semiconductor
It connects, the output end of the diode control is connect with the pole D of the metal-oxide-semiconductor, the driving end of the diode control and institute
State the pole the G connection of metal-oxide-semiconductor.
In wherein some embodiments, wherein the metal-oxide-semiconductor is the metal-oxide-semiconductor group for including multiple metal-oxide-semiconductor parallel connections.
In wherein some embodiments, wherein the anti-circnit NOT of first control system and the second control system counnter attack
Circuit is identical as the structure of the anti-circnit NOT.
In wherein some embodiments, wherein the DC/DC module be BUCK type circuit, synchronous BUCK type circuit or
It is BUCK-BOOST type circuit.
In wherein some embodiments, wherein the control system DC/DC module and the attached DC/DC mould of the unmanned plane
Block is identical as the DC/DC modular structure.
In wherein some embodiments, wherein the dynamic range that the lithium battery power supply module is capable of providing is 200-
500W。
The utility model further increases a kind of control method of unmanned plane dynamical system, for controlling the unmanned plane
Dynamical system, the control method of the unmanned plane dynamical system the following steps are included:
1001: the maximal work parameter of the setting fuel cell-powered module and the lithium battery power supply module；
1002: the running parameter of the detection fuel cell-powered module and the lithium battery power supply module；
1003: the system control module controls the unlatching quantity of the DC/DC module.
In wherein some embodiments, wherein the step 1001 further includes steps of
10011: the minimum voltage V of the setting fuel cell-powered module generator unitFC-min；
10012: setting the minimum voltage V of the lithium battery power supply moduleLi-min；
10013: setting the ceiling voltage V of the lithium battery power supply moduleLi-max；
10014: setting the charging maximum current I of the lithium battery power supply moduleLi-max。
In wherein some embodiments, wherein the step 1002 further includes steps of
10021: the generator unit voltage V of the detection fuel cell-powered moduleFC；
10022: detecting fuel cell-powered module generator unit electric current IFC；
10023: detecting the voltage V of the lithium battery power supply moduleLi；
10024: detecting the charging current I of the lithium battery power supply moduleLi。
In wherein some embodiments, wherein the step 1003 further includes steps of
10031: the system control module is by the generator unit voltage V of the fuel cell-powered moduleFCWith the combustion
Expect the minimum voltage V of battery power supply module generator unitFC- min is compared and controls the circuit according to comparison result and adjusts
Unit opens or closes；
10032: the system control module is by the voltage V of the lithium battery power supply moduleLiWith the lithium battery power supply mould
The ceiling voltage V of blockLiThe minimum voltage V of-max and the lithium battery power supply moduleLi- min is compared respectively, and according to than
Relatively result controls the circuit and adjusts opening or closing for unit；
10033: the system control module is by the charging current I of the lithium battery power supply moduleLiIt is supplied with the lithium battery
The charging maximum current I of electric moduleLi- max be compared and according to comparison result control the circuit adjust unit unlatching or
It closes.
In wherein some embodiments, wherein the step 10031 further includes steps of
100311: the system control module is by the generator unit voltage V of the fuel cell-powered moduleFCWith the combustion
Expect the minimum voltage V of battery power supply module generator unitFC- min is compared；
100312: if the generator unit voltage V of the fuel cell-powered moduleFC< fuel cell-powered module the hair
The minimum voltage V of electric unitFC- min, then the system control module passes through the output control one or more groups of tune of signal-off
It saves unit (1009121)；If the generator unit voltage V of the fuel cell-powered moduleFC> fuel cell-powered the module
The minimum voltage V of generator unitFC- min, then the system control module output control signal opens one or more groups of adjustings
Unit (1009122).
In wherein some embodiments, wherein the step 10032 further includes steps of
100321: the system control module is by the voltage V of the lithium battery power supply moduleLiWith the lithium battery power supply mould
The ceiling voltage V of blockLi- max is compared；
100322: if system control module is by the voltage V of the lithium battery power supply moduleLi> lithium battery power supply the module
Ceiling voltage VLi- max, then the system control module is adjusted by the one or more groups of circuits of output control signal-off
Unit (1003221)；If system control module is by the voltage V of the lithium battery power supply moduleLi< lithium battery power supply the module
Minimum voltage VLi- min, then the system control module opens one or more groups of circuits by output signal and adjusts unit
(1003222)。
In wherein some embodiments, wherein the step 10033 further includes steps of
100331: the system control module is by the charging current I of the lithium battery power supply moduleLiIt is supplied with the lithium battery
The charging maximum current I of electric moduleLi- max is compared；
100332: if the charging current I of the lithium battery power supply moduleLiCharging with the > lithium battery power supply module is most
High current ILi- max, then the system control module is adjusted single by the one or more groups of circuits of output control signal-off
Member.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of a specific embodiment of unmanned plane dynamical system described in the utility model.
Fig. 2 is the structural schematic diagram of a preferred embodiment of unmanned plane dynamical system described in Fig. 1.
Fig. 3 is the structural schematic diagram of the further preferred embodiment of unmanned plane dynamical system described in Fig. 2.
Fig. 4 is the structural schematic diagram of the further preferred embodiment of unmanned plane dynamical system described in Fig. 3.
Fig. 5 is the structural schematic diagram of the further preferred embodiment of unmanned plane dynamical system described in Fig. 4.
Fig. 6 is the structural schematic diagram of the further preferred embodiment of unmanned plane dynamical system described in Fig. 5.
Fig. 7 is the structural schematic diagram of the further preferred embodiment of unmanned plane dynamical system described in Fig. 6.
Fig. 8 is the structural schematic diagram of the further preferred embodiment of unmanned plane dynamical system described in Fig. 7.
Fig. 9 is the structural schematic diagram of the counnter attack module 42 of unmanned plane dynamical system described in the utility model.Figure 10 is this
The structural schematic diagram of the anti-circnit NOT of unmanned plane dynamical system described in utility model.
Specific embodiment
It is described below for disclosing the utility model so that those skilled in the art can be realized the utility model.It retouches below
Preferred embodiment in stating is only used as illustrating, it may occur to persons skilled in the art that other obvious modifications.It is retouched following
The basic principle of the utility model defined in stating can be applied to other embodiments, deformation scheme, improvement project, etc. Tongfangs
The other technologies scheme of case and the spirit and scope without departing from the utility model.
It will be understood by those skilled in the art that in the exposure of the utility model, term " longitudinal direction ", " transverse direction ", "upper",
The orientation of the instructions such as "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" or position are closed
System is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of describing the present invention and simplifying the description, without
It is that the device of indication or suggestion meaning or element must have a particular orientation, be constructed and operated in a specific orientation, therefore on
Stating term should not be understood as limiting the present invention.
It is understood that term " one " is interpreted as " at least one " or " one or more ", i.e., in one embodiment,
The quantity of one element can be one, and in a further embodiment, the quantity of the element can be it is multiple, term " one " is no
It can be interpreted as the limitation to quantity.
As shown in Figure 1, the utility model mainly provides a kind of unmanned plane dynamical system, the unmanned plane dynamical system includes
One dynamical system 10 provides power for it, and the dynamical system 10 includes at least one fuel cell-powered module 101 and at least one
Lithium battery power supply module 102, the fuel cell-powered module 101 and the lithium battery power supply module 102 are installed in institute respectively
Unmanned plane dynamical system is stated to provide power for the unmanned plane dynamical system.
It as shown in Figures 1 to 8, is the working principle structural block diagram of unmanned plane dynamical system described in the utility model.Its
Described in unmanned plane dynamical system include an at least fuel supply unit 20, at least one fuel cell-powered module 101, at least one
Lithium battery power supply module 102, at least a system control module 30, an at least circuit adjust unit 40 and at least one nobody is motor-driven
Power source 50, wherein the output end of the fuel supply unit 20 is connect with the fuel cell-powered module 101, to be described
Fuel cell-powered module 101 provides fuel, and the output end and the circuit of the fuel cell-powered module 101 adjust unit
40 connections, the circuit adjust the output end of unit 40 respectively with the lithium battery power supply module 102 and the unmanned mechanomotive force
Source 50 connects, and therefore, described by the fuel cell-powered module 101 and/or the lithium battery power supply module 102 is described
Unmanned plane power source 50 is powered, and adjusting unit 40 by the circuit prevents the lithium battery power supply module 102 from being
The fuel cell-powered module 101 is powered, and the both ends of the system control module 30 are supplied with the fuel cell respectively
The voltage and current sampled point of electric module 101 and the connection of the voltage and current sampled point of the lithium battery power supply module 102, thus logical
The fuel cell-powered module 101 or the lithium battery power supply module 102 are crossed as system control module power supply, and institute
The voltage of the fuel cell-powered module 101 and the lithium battery power supply module 102 can be acquired by stating system control module 30
And electric current.
Preferably, the either circuit adjusting unit 40 includes a DC/DC module 401 and a counnter attack module 402, described
DC/DC module 401 is connected between the output end of the fuel cell-powered module 101 and the counnter attack module 402, described anti-
The output end of reverse block 402 is connect with the lithium battery power supply module 102 and the unmanned plane power source 50.Therefore, the lithium
Battery power supply module 102 can not only power as needed for the unmanned plane power source 50, and can be by the spiral shell of unmanned plane
The energy feedback that rotation paddle generates recycles in time, simultaneously because the presence of the counnter attack module 402, what the propeller of unmanned plane generated
Energy will not enter the fuel cell-powered module 101, to avoid the damage of the fuel cell-powered module 101.
It should be noted that the circuit adjusts the quantity of unit 40 by the fuel cell-powered module 101 and institute
The power decision for stating unmanned plane power source 50, when the output power of the fuel cell-powered module 101 is bigger, the circuit tune
The quantity for saving unit 40 is more, correspondingly, if the power of the unmanned plane power source 50 is smaller, the lithium battery power supply module
102 charging current is bigger, then the quantity of the circuit adjusting unit 40 is fewer.
The fuel supply unit 20 further comprises an at least fuel supply module 201, at least an inlet channel 202
And an at least exhaust passage 203, wherein the fuel supply module 201 is connect with the inlet channel 202, the air inlet
The output end in channel 202 is connect with the fuel cell-powered module 101 and the system control module 30, therefore the system
System control module 30 can control the fuel supply module 201 by the inlet channel 202 to described fuel cell-powered
Module 101 provides fuel.
The fuel supply unit 20 further comprises a pressure sensor 204, the control terminal of the pressure sensing 204 with
The system control module 30 connects, and the other end of the pressure sensor 204 is connect with the inlet channel 202, therefore, institute
The pressure of the inlet channel 202 can be acquired by the pressure sensor 204 by stating system control module 30.The exhaust is logical
The control terminal in road 203 is connect with the system control module 30, one end of the exhaust passage 203 with it is described fuel cell-powered
Module 101 connects, other end external connection, and the system control module 30 controls the fuel by the exhaust passage 203
Battery power supply module 101 is externally vented.
The fuel cell-powered module 101 include an at least air intlet 1011, air can by the air into
Mouth 1011 enters the fuel cell-powered module 101, to occur together with the fuel of the fuel supply module 201 conveying
Chemical reaction, so that the fuel cell-powered module 101 be enable to work normally.
The unmanned plane dynamical system includes that an at least temperature sensor 60 and an at least control system adjust circuit 70,
Wherein the temperature sensor 60 is connect with the fuel cell-powered module 101, for detecting the fuel cell-powered mould
The temperature of block 101, the both ends that the control system adjusts circuit 70 are separately connected the fuel cell-powered module 101 and described
Lithium battery power supply module 102, and the control system adjusts circuit 70 and connect with the system control module 30, thus a side
Fuel cell-powered module 101 and the lithium battery power supply module 102 described in face can power to the system control module 30,
On the other hand, adjusting circuit 70 by the control system prevents the system control module 30 to described fuel cell-powered
Module 101 charges, to avoid the damage of the fuel cell-powered module 101.
As shown in fig. 6, specifically, it includes at least one first anti-reverse of control system that the control system, which adjusts circuit 70,
Block 701 and a control system DC/DC module 702, wherein one end of the first control system counnter attack module 701 and the system
Control module 30 of uniting connects, the other end of the first control system counnter attack module 701 and the control system DC/DC module
702 connections, the control system DC/DC module 702 adjust unit 40 and the lithium battery power supply module 102 with the circuit
Connection, so that adjusting unit 40 by the lithium battery power supply module 102 and the circuit is the control system DC/DC module
702 power supplies.
It further comprises one second control system counnter attack module 703 that the control system, which adjusts circuit 70, second control
One end of system counnter attack module 703 processed is connect with the system control module 30 and the first control system counnter attack module 701,
The other end of the second control system counnter attack module 703 is connect with the fuel cell-powered module 101, to make the combustion
Material battery power supply module 101 can prevent the system control module 30 to institute for the system control module 30 power supply
It states fuel cell-powered module 101 to discharge, so that the fuel cell-powered module 101 be protected not to be damaged.
Further, the unmanned plane dynamical system further comprises an at least fuel cell fan 80, the fuel
One end of battery fan 80 is connect with the fuel cell-powered module 101, the other end of the fuel cell fan 80 and institute
The connection of system control module 30 is stated, to be that the fuel cell fan 80 is powered by the system control module 30.The combustion
The pulse width modulation (PWM, similarly hereinafter) of material battery fan 80 is connect with FB1 with the system control module 30, when the system
Control module 30 can pass through tune after collecting the temperature of the fuel cell-powered module 101 by the temperature sensor 60
Whole pwm signal controls the revolving speed of the fuel cell fan 80, so as to adjust the temperature of the fuel cell-powered module 101
Degree.
Further, the system control module 30 includes an at least signal acquisition process module 301 and at least one electricity
Power conversion module 302, the signal acquisition process module 301 and the power switching module 302 distinguish electrical setting in described
System control module 30, wherein the signal acquisition process module 301 is for acquiring and handling signal, the power switching module
302 electrical power conversion for inputting the system control module 30 is electric power needed for the fuel cell fan 80.
In fuel supply module described in the utility model, the fuel includes but is not limited to: sodium borohydride and water, silicon
Sour sodium and water, lithium hydride and water, magnesium hydride and water, lithium borohydride and water, lithium aluminium hydride and water, aluminum hydride, ammonia borane complex,
Hydrocarbon, lithium aluminium hydride, magnesium borohydride, magnesium borohydride-amine complex, compression hydrogen or liquified hydrogen.
Further, unmanned plane dynamical system described in the utility model further comprises a unmanned plane subsystem 90
With the attached DC/DC module 91 of a unmanned plane, one end of the attached DC/DC module 91 of unmanned plane is separately connected the circuit and adjusts
Unit 40, the lithium battery power supply module 102 and the unmanned plane power source 50, the attached DC/DC module 91 of unmanned plane
The other end connect the unmanned plane subsystem 90, to provide electric power support for the unmanned plane subsystem 90.
The unmanned plane subsystem 90 includes at least one unmanned machine head 92, and the unmanned machine head 92 is connected to described
The output end of the attached DC/DC module 91 of unmanned plane, to be powered by the attached DC/DC module 91 of the unmanned plane for it.
The unmanned plane subsystem 90 further comprises that at least one first unmanned plane flies control 93, and first unmanned plane flies
Control 93 is connected to the output end of the attached DC/DC module 91 of the unmanned plane, to pass through the attached DC/DC module 91 of the unmanned plane
It powers for it.
The unmanned plane subsystem 90 further comprises that at least a unmanned aerial vehicle onboard equipment 94, the unmanned aerial vehicle onboard are set
Standby 94 are connected to the output end of the attached DC/DC module 91 of the unmanned plane, to pass through the attached DC/DC module 91 of the unmanned plane
It powers for it.
The unmanned plane dynamical system further comprises that one second unmanned plane flies control 95, and second unmanned plane flies control 95
Input terminal connect with the system control module 30, second unmanned plane fly control 95 output end and the unmanned mechanomotive force
Source 50 and the attached DC/DC module 91 of the unmanned plane connect, and therefore, the system control module 30 can pass through second nothing
Man-machine winged control 95 controls the unmanned plane power source 50 and the attached DC/DC module 91 of the unmanned plane.When the fuel cell
When power supply module 101 or the electric power of the lithium battery power supply module 102 deficiency or bad performance, the system control module 30 is given
Second unmanned plane flies control 95 and sends a control signals, and second unmanned plane flies to control 95 according to the control signal by institute
The output power for stating unmanned plane power source 50 and the attached DC/DC module 91 of the unmanned plane reduces to limit the property of the unmanned plane
Can, the unmanned plane guarantees its normal flight and other functional operations by closing its non-principal performance.
Next, the working principle of unmanned plane dynamical system described in the utility model is further detailed.
It is institute that the control of system control module 30, which controls the fuel supply module 201 by the inlet channel 202,
It states fuel cell-powered module 101 and provides fuel to enable 101 normal power supply of fuel cell-powered module, the electricity
The DC voltage that road adjusts the fixation that the DC/DC module 401 in unit 40 provides the fuel cell-powered module 101 turns
Being changed to variable DC voltage is that the unmanned plane power source 50 is powered, and the lithium battery power supply module 102 also can be
The unmanned plane power source 50 is powered.
The lithium battery power supply module 102 can recycle the energy that the high speed rotation of the propeller of the unmanned plane generates,
And since the circuit adjusts the setting of the counnter attack module 402 in unit 40, the propeller high speed of the unmanned plane is revolved
Raw energy of changing the line of production may not flow into the fuel cell-powered module 101, so as to avoid the fuel cell-powered module 101
It is damaged.
In the course of work of the unmanned plane dynamical system, the system control module 30 by monitoring the combustion at any time
The voltage and current of the voltage and current and the lithium battery power supply module 102 of expecting battery power supply module 101 determines the fuel
The working performance of battery power supply module 101 and the lithium battery power supply module 102, and by send a signal to described second nobody
Machine flies control 95, so that second unmanned plane flies, control 95 controls the unmanned plane power source 50 in time and the unmanned plane is attached
The normal operation of system 90.
Simultaneously as the counnter attack module 402, the first control system counnter attack module 701 and second control system
The setting for counnter attack module 703 of uniting, the fuel cell-powered module 101 can power for the system control module 30, but not
The fuel cell-powered module 101 can be damaged because of the reversed conveying of electric power.
The system control module 30 acquires the fuel cell-powered module 101 by the temperature sensor 60
Operating temperature, if the operating temperature of the fuel cell-powered module 101 is too high or too low, the system control module 30
The fuel cell-powered module is adjusted by adjusting the pwm signal to adjust the revolving speed of the fuel cell fan 80
101 operating temperature.
The system control module 30 detects the fuel cell-powered module 101 by the pressure sensor 204
Operating pressure, if the operating pressure of the fuel cell-powered module 101 is excessively high, the system control module 30 passes through control
The fuel cell-powered module 101 is exhausted in the exhaust passage 203, to reduce the fuel cell-powered module
101 operating pressure.
In unmanned plane dynamical system described in the utility model, the unmanned plane power source 50 include fixed-wing nobody
Motor/electricity tune of machine, vert wing unmanned plane or multi-rotor unmanned aerial vehicle.
Those skilled in the art can also be on the basis of the utility model above-mentioned exposure by the unmanned plane dynamical system
Applied to other kinds of unmanned plane, as long as using technical solution identical or approximate with the utility model, solve and this
The identical or approximate technical problem of utility model, and reached technical effect identical or approximate with the utility model, all belong to
Within the protection scope of the utility model, specific embodiment of the present utility model is not limited thereto.
Correspondingly, the utility model further provides for the control method of a unmanned plane dynamical system, practical for controlling
The novel unmanned plane dynamical system, the control method of the unmanned plane dynamical system the following steps are included:
1001: setting the maximal work ginseng of the fuel cell-powered module 101 and the lithium battery power supply module 102
Number；
1002: the running parameter of the detection fuel cell-powered module 101 and the lithium battery power supply module 102；
1003: the system control module 30 controls the unlatching quantity of the DC/DC module 401.
It should be noted that the step 1001 and the step 1002 have no point of sequencing.In the step
In 1003, the unlatching quantity of the DC/DC module 401 is by the prison in the setting value and the step 1002 in the step 1001
Measured value obtains after being compared.In other words, in the step 1003, the system control module 30 is by by the step
The maximal work parameter of the fuel cell-powered module 101 and the lithium battery power supply module 102 in rapid 1001 with it is described
After the running parameter of fuel cell-powered module 101 and the lithium battery power supply module 102 described in 1002 is compared respectively
Determine the unlatching quantity of the DC/DC module 401.
Preferably, the step 1001 is further included steps of one kind as the utility model
10011: the minimum voltage V of setting fuel cell-powered 101 generator unit of moduleFC-min；
10012: setting the minimum voltage V of the lithium battery power supply module 102Li-min；
10013: setting the ceiling voltage V of the lithium battery power supply module 102Li-max；
10014: setting the charging maximum current I of the lithium battery power supply module 102Li-max。
Correspondingly, the step 1002 further includes steps of
10021: the generator unit voltage V of the detection fuel cell-powered module 101FC；
10022: detecting fuel cell-powered 101 generator unit electric current I of moduleFC；
10023: detecting the voltage V of the lithium battery power supply module 102Li；
10024: detecting the charging current I of the lithium battery power supply module 102Li。
It is emphasized that the step 10011 to the step 10014 has no point of sequencing, the step
10021 to the step 10024 also without sequencing point.
In the step 10011 into the step 10014, fuel cell-powered 101 generator unit of module is most
Low-voltage VFC- min determines that the lithium battery power supply module 102 is most by the concrete composition of the fuel cell-powered module 101
Low-voltage VLiThe ceiling voltage V of-min, the lithium battery power supply module 102LiThe charging of-max and lithium battery power supply module 102
Maximum current ILi- max is also to be determined by the concrete composition of the lithium battery power supply module 102.In other words, different fuel electricity
The minimum voltage V of the generator unit of pond power supply module 101FC- min is different, different lithium battery power supply modules 102 it is minimum
Voltage VLi- min, ceiling voltage VLi- max and charging maximum current ILi- max is also different.
Specifically, the step 1003 further includes steps of
10031: the system control module 30 is by the generator unit voltage V of the fuel cell-powered module 101FCWith
The minimum voltage V of 101 generator unit of fuel cell-powered moduleFC- min is compared and described in being controlled according to comparison result
Circuit adjusts opening or closing for unit 40；
10032: the system control module 30 is by the voltage V of the lithium battery power supply module 102LiIt is supplied with the lithium battery
The ceiling voltage V of electric module 102LiThe minimum voltage V of-max and the lithium battery power supply module 102Li- min is compared respectively
Compared with, and the circuit is controlled according to comparison result and adjusts opening or closing for unit 40；
10033: the system control module 30 is by the charging current I of the lithium battery power supply module 102LiWith the lithium electricity
The charging maximum current I of pond power supply module 102Li- max, which is compared and controls the circuit according to comparison result, adjusts unit 40
Open or close.
It is emphasized that the step 10031 to the step 10033 has no point of sequencing.
One kind as the utility model is preferred, wherein the step 10031 further includes steps of
100311: the system control module 30 is by the generator unit voltage V of the fuel cell-powered module 101FCWith
The minimum voltage V of 101 generator unit of fuel cell-powered moduleFC- min is compared；
100312: if the generator unit voltage V of the fuel cell-powered module 101FC< fuel cell-powered the module
The minimum voltage V of 101 generator unitsFC- min, then the system control module 30 passes through one group or more of signal-off of output control
The group circuit adjusts unit 40 (1009121)；If the generator unit voltage V of the fuel cell-powered module 101FC> described
The minimum voltage V of fuel cell-powered 101 generator unit of moduleFC- min, then the output of system control module 30 controls signal
It opens one or more groups of circuits and adjusts unit 40 (1009122)；
The step 10032 further includes steps of
100321: the system control module 30 is by the voltage V of the lithium battery power supply module 102LiWith the lithium battery
The ceiling voltage V of power supply module 102Li- max is compared；
100322: if system control module 30 is by the voltage V of the lithium battery power supply module 102Li> the lithium battery power supply
The ceiling voltage V of module 102Li- max, then the system control module 30 passes through the output control one or more groups of institutes of signal-off
It states circuit and adjusts unit 40 (1003221)；If system control module 30 is by the voltage V of the lithium battery power supply module 102Li< institute
State the minimum voltage V of lithium battery power supply module 102Li- min, then the system control module 30 opens one group by output signal
Or circuit described in multiple groups adjusts unit 40 (1003222).
Correspondingly, the step 10033 further includes steps of
100331: the system control module 30 is by the charging current I of the lithium battery power supply module 102LiWith the lithium
The charging maximum current I of battery power supply module 102Li- max is compared；
100332: if the charging current I of the lithium battery power supply module 102LiWith > the lithium battery power supply module 102
Charge maximum current ILi- max, then the system control module 30 passes through the output control one or more groups of circuits of signal-off
Adjust unit 40；
In the control method of the unmanned plane dynamical system, can by the system control module 30 to it is described nobody
The output electric current and voltage of motor-driven Force system carry out dynamic adjustment, can also export electricity by detecting the unmanned plane dynamical system
The variation of (voltage) is flowed, so that the fuel cell-powered module 101 when overload be prevented to be damaged.
In addition, by the control method of unmanned plane dynamical system described in the utility model, it can also be to the unmanned plane
The energy of dynamical system is managed by calculating, to make further control to the voyage of the unmanned plane dynamical system
System.
As shown in figure 9, being anti-circnit NOT described in the utility model, the anti-circnit NOT 42 includes one or more
The metal-oxide-semiconductor group 421 of metal-oxide-semiconductor parallel connection and an intelligent diode control 422.The circuit as shown in Fig. 9, metal-oxide-semiconductor group 421
Composed in parallel by a metal-oxide-semiconductor or by multiple metal-oxide-semiconductors, each metal-oxide-semiconductor has been internally integrated diode, anti-circnit NOT 42 it is defeated
Enter end to connect with the pole S of metal-oxide-semiconductor group 421, the output end of anti-circnit NOT 42 is connect with the pole D of metal-oxide-semiconductor group 421；Intelligent diode
The input of controller 422 is connect with the end S of metal-oxide-semiconductor group 421, the output end and metal-oxide-semiconductor group 421 of intelligent diode control 422
The connection of the end D, the driving end of intelligent diode control 422 connect with the pole G of metal-oxide-semiconductor group 421, intelligent diode control
422 be a integrated chip, and when input voltage is higher than output voltage certain value, which can be by sampling unmanned plane motor
Electric current controls the size of 421 driving voltage of metal-oxide-semiconductor group, make 421 both end voltage of metal-oxide-semiconductor group be less than or equal to chip set it is open-minded
Threshold value guarantees that the conduction voltage drop of metal-oxide-semiconductor group 421 is sufficiently small, to reduce loss.When output end voltage is higher than input terminal voltage,
The chip can close metal-oxide-semiconductor group 421 in a very short period of time, prevent output end electric energy from flowing into end.
As shown in Figure 10, in the present invention, the DC/DC module 401 is the structural block diagram of BUCK type circuit.It is described
BUCK circuit is buck chopper, also referred to as decompression transducer, and output voltage is less than input voltage.As shown in Figure 10, it switchs
Pipe is the metal-oxide-semiconductor group 421, and driving voltage is PWM (Pusle width modulation) signal in charging chip, letter
Number period is Ts, then signal frequency is f=1/Ts, turn-on time Ton, turn-off time Toff, then the period is Ts=Ton+
Toff, duty ratio Dy=Ton/Ts (i.e. the turn-on time of semiconductor field effect transistor), output voltage Vo=Vi*Dy, because
This its output voltage Vo is less than input voltage Vi.In addition to this, the DC/DC module 401 or synchronous BUCK type or
BUCK-BOOST type etc., as long as using technical side identical or approximate with the utility model on the basis of the utility model
Case solves the technical problem identical or approximate with the utility model, and has reached identical or approximate as the utility model
Technical effect belongs within the protection scope of the utility model, and specific embodiment of the present utility model is not limited thereto.
The utility model by the way that fuel cell-powered module 101 is used in mixed way with lithium battery power supply module 102, so as to
The dynamic of 200~5000W or so is provided with the moment constantly for the very big energy of the needs such as the VTOL of unmanned plane dynamical system
Power.
In addition, the utility model can adjust dynamical system described in the utility model by the system control module 30
10 output electric current and voltage, to make the applicable surface and the dynamical system 10 of dynamical system 10 described in the utility model
Versatility be improved, enable to adapt to various unmanned plane motor types and application.
Unmanned plane dynamical system described in the utility model is supplied due to having gathered fuel cell-powered module 101 and lithium battery
The advantage of electric module 102, therefore the cruising ability and voyage for the unmanned planes dynamical system such as can greatly improve unmanned plane, therefore
Unmanned plane dynamical system described in the utility model can be applied to the exigent application of cruising ability.
Unmanned plane dynamical system described in the utility model compared with the existing technology in dynamical system for, due to its
It is all greatly improved in terms of cruising ability and voyage, therefore unmanned plane dynamical system described in the utility model can be made
For the dynamical system in a plurality of types of unmanned plane dynamical systems such as fixed-wing, the wing that verts, more rotors.
Those skilled in the art can also be on the basis of the utility model above-mentioned exposure by the unmanned plane dynamical system
Control method be applied to other kinds of unmanned plane, as long as use technical solution identical or approximate with the utility model,
It solves the technical problem identical or approximate with the utility model, and has reached technology identical or approximate with the utility model
Effect belongs within the protection scope of the utility model, and specific embodiment of the present utility model is not limited thereto.
It should be understood by those skilled in the art that foregoing description and the embodiments of the present invention shown in the drawings are only used as
It illustrates and is not intended to limit the utility model.The purpose of this utility model completely and effectively realizes.The function of the utility model
Energy and structural principle show and illustrate in embodiment, under without departing from the principle, the embodiments of the present invention
Can there are any deformation or modification.
Claims (26)
1. a unmanned plane dynamical system characterized by comprising
An at least fuel supply unit；
At least one fuel cell-powered module；
An at least lithium battery power supply module；
An at least system control module；
An at least circuit adjusts unit；And
An at least unmanned plane power source, wherein the output end of the fuel supply unit and the fuel cell-powered module connect
It connects, the output end of the fuel cell-powered module adjusts unit with the circuit and connect, and the circuit adjusts the output of unit
End connect respectively with the lithium battery power supply module and the unmanned plane power source, the both ends of the system control module respectively with
The voltage and current sampled point of the fuel cell-powered module and the connection of the voltage and current sampled point of the lithium battery power supply module.
2. unmanned plane dynamical system according to claim 1, which is characterized in that the fuel supply unit includes at least one
Fuel supply module, at least an inlet channel and at least an exhaust passage, wherein the input terminal of the inlet channel with it is described
Fuel supply module connection, the output end of the inlet channel are connect with the fuel cell-powered module, the inlet channel
It connect with the system control module, supplies the fuel so that the system control module be enable to control the inlet channel
Fuel is provided to the fuel cell-powered module to module, one end of the exhaust passage connects the fuel cell-powered mould
Block connection, the other end and external connection, thus by the exhaust passage by the extra of the fuel cell-powered module generation
Gas discharge.
3. unmanned plane dynamical system according to claim 2, which is characterized in that the fuel cell-powered module includes one
Air intlet, air can enter the fuel cell-powered module by the air intlet, to supply with the fuel
The fuel that module provides reacts and works normally the fuel cell-powered module.
4. unmanned plane dynamical system according to claim 3, which is characterized in that the fuel supply unit further comprises
One pressure sensor, the control terminal of the pressure sensor are connect with the system control module, and the other end and the air inlet are logical
Road connection, the system control module pass through the pressure in inlet channel described in the pressure sensor monitoring.
5. unmanned plane dynamical system according to claim 3, wherein the unmanned plane dynamical system includes a temperature sensing
Device, the both ends of the temperature sensor are connect with the fuel cell-powered module and the system control module respectively, with
The system control module is set to monitor the temperature of the fuel cell-powered module by the temperature sensor.
6. unmanned plane dynamical system according to claim 5, which is characterized in that the unmanned plane dynamical system is further wrapped
Include a control system and adjust circuit, the both ends that the control system adjusts circuit be separately connected the fuel cell-powered module and
The unmanned plane power source, and the control system adjusts circuit and connect with the system control module.
7. unmanned plane dynamical system according to claim 1, which is characterized in that it includes a DC/ that the circuit, which adjusts unit,
DC module and an anti-circnit NOT, the DC/DC module be connected to the fuel cell-powered module output end and the counnter attack
Between circuit, the output end of the anti-circnit NOT is connect with the lithium battery power supply module and the unmanned plane power source.
8. unmanned plane dynamical system according to claim 6, which is characterized in that the control system adjust circuit include to
Few one first control system counnter attack module and a control system DC/DC module, wherein the first control system counnter attack module and
The control system DC/DC is series between the system control module and the unmanned plane power source.
9. unmanned plane dynamical system according to claim 8, which is characterized in that the control system adjust circuit include to
Few one second control system counnter attack module, the both ends of the second control system counnter attack module respectively with the system control module
And the fuel cell-powered module connection, so that it is dynamic to provide the fuel cell-powered module to the system control module
Power and the fuel cell-powered module is avoided to be damaged.
10. unmanned plane dynamical system according to claim 9, which is characterized in that the unmanned plane dynamical system is further
Including an at least fuel cell fan, the both ends of the fuel cell fan respectively with the fuel cell-powered module and described
System control module connection, the pulse width modulation interface of the fuel cell fan are connect with the system control module, institute
State the revolving speed that system control module controls the fuel cell fan by the pulse width modulation interface.
11. unmanned plane dynamical system according to claim 10, which is characterized in that the system control module includes at least
One signal acquisition process module, the signal acquisition process module electrical setting is in the system control module, wherein the letter
Number acquisition processing module is for acquiring and handling signal.
12. unmanned plane dynamical system according to claim 11, which is characterized in that the system control module includes at least
One power switching module, the power switching module electrical setting are used in the system control module, the power switching module
In the electrical power conversion for inputting the system control module be the fuel cell fan needed for electric power.
13. unmanned plane dynamical system according to claim 12, which is characterized in that the unmanned plane dynamical system is further
Including a unmanned plane subsystem and the attached DC/DC module of a unmanned plane, one end of the attached DC/DC module of unmanned plane is distinguished
It connects the circuit and adjusts unit, the lithium battery power supply module and the unmanned plane power source, the attached DC/DC of unmanned plane
The other end of module connects the unmanned plane subsystem, to provide power for the unmanned plane subsystem.
14. unmanned plane dynamical system according to claim 13, which is characterized in that the unmanned plane subsystem includes extremely
A few unmanned machine head, the unmanned machine head are connected to the output end of the attached DC/DC module of the unmanned plane.
15. unmanned plane dynamical system according to claim 14, which is characterized in that the unmanned plane subsystem includes extremely
Few one first unmanned plane flies control, and the unmanned plane flies the output end that control is connected to the attached DC/DC module of the unmanned plane.
16. unmanned plane dynamical system according to claim 14 or 15 further comprises a flight subsystem, wherein institute
Stating flight subsystem includes an at least unmanned aerial vehicle onboard equipment, and it is attached that the unmanned aerial vehicle onboard equipment is connected to the unmanned plane
The output end of DC/DC module.
17. unmanned plane dynamical system according to claim 16, which is characterized in that the unmanned plane dynamical system is further
Flying control including one second unmanned plane, the input terminal that second unmanned plane flies control is connect with the system control module, and described the
The output end that two unmanned planes fly control is connect with the unmanned plane power source and the attached DC/DC module of the unmanned plane.
18. unmanned plane dynamical system according to claim 1, which is characterized in that the unmanned plane power source be motor or
Electricity is adjusted.
19. unmanned plane dynamical system according to claim 18, which is characterized in that the unmanned plane power source be motor or
Electricity is adjusted.
20. unmanned plane dynamical system according to claim 19, which is characterized in that the unmanned plane includes but is not limited to solid
Determine wing unmanned plane, vert wing unmanned plane or multi-rotor unmanned aerial vehicle.
21. unmanned plane dynamical system according to claim 7, which is characterized in that the anti-circnit NOT includes an at least MOS
Pipe and a diode control, the metal-oxide-semiconductor inside includes an at least diode, and the pole S of the metal-oxide-semiconductor is set to the counnter attack
The input terminal of circuit, the pole D of the metal-oxide-semiconductor are set to the output end of the anti-circnit NOT, the input of the diode control
End is connect with the pole S of the metal-oxide-semiconductor, and the output end of the diode control is connect with the pole D of the metal-oxide-semiconductor, two pole
The driving end of tube controller is connect with the pole G of the metal-oxide-semiconductor.
22. unmanned plane dynamical system according to claim 21, which is characterized in that the metal-oxide-semiconductor be include multiple metal-oxide-semiconductors
Metal-oxide-semiconductor group in parallel.
23. unmanned plane dynamical system according to claim 9, which is characterized in that the anti-circnit NOT of the first control system
It is identical as the structure of the anti-circnit NOT with the anti-circnit NOT of the second control system.
24. unmanned plane dynamical system according to claim 7, wherein the DC/DC module is BUCK type circuit, synchronization
BUCK type circuit or BUCK-BOOST type circuit.
25. unmanned plane dynamical system according to claim 13, which is characterized in that the control system DC/DC module and
The attached DC/DC module of unmanned plane is identical as the DC/DC modular structure.
26. unmanned plane dynamical system according to claim 25, wherein the lithium battery power supply module be capable of providing it is dynamic
Power range is 200-500W.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2018201926839 | 2018-02-02 | ||
| CN201820192683 | 2018-02-02 |
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| Publication Number | Publication Date |
|---|---|
| CN209080172U true CN209080172U (en) | 2019-07-09 |
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ID=67112640
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