CN204840939U - Aircraft and power management system thereof - Google Patents
Aircraft and power management system thereof Download PDFInfo
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- CN204840939U CN204840939U CN201520518765.4U CN201520518765U CN204840939U CN 204840939 U CN204840939 U CN 204840939U CN 201520518765 U CN201520518765 U CN 201520518765U CN 204840939 U CN204840939 U CN 204840939U
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Abstract
The utility model provides a power management system of aircraft, including battery case and aircraft control panel, the battery case includes main cell, reserve cell and battery the control unit, the aircraft control panel has wireless transmit and receive unit, serial port communication unit and switching of power unit, wherein: main cell is used for when normally flying, the aircraft supplies power, the backup battery unit is used for before the normal flight of aircraft, supply power when back and the flight of descending is unexpected, the switching of power unit with main cell and reserve cell connect, are used for selecting main cell or reserve cell do the power supply of aircraft control panel. Be used for the self -checking of whole aircraft system before the aircraft starts, start control main battery switch when closing at the aircraft, be used for the real -time electric quantity detection of main battery in the aircraft working process, when the aircraft meets accident the power -off protection with send the emergency rescue signal, guarantee the safety of aircraft, lengthen the live time simultaneously.
Description
Technical field
The utility model relates to aircraft field, particularly relates to a kind of aircraft and power-supply management system thereof.
Background technology
In model plane field, the aircraft of the overwhelming majority is all adopt single battery as power source, does not have emergency response mechanism and reserve battery.If flight control has problem, or remote controller breaks down, if now add main power source to system rashly, the lighter can cause system failure, severe one or cause aircraft out of control, crisis life safety.
Battery electric quantity is related to making a return voyage of aircraft and flight safety, a set of effective electricity check system don't fail to be had, there is a problem in powered battery single at present: aircraft work time, the electricity difference needed under different conditions is very large, as acceleration, hovering, advance etc., main battery voltage fluctuation meeting can be caused so very large.Power with a large power supply of fluctuation will introduce the factors of instability to electric quantity detecting circuit, cause electric power detection inaccurate, thus bring uncertainty to aircraft, if powered with independent current source to eliminate this hidden danger.In addition, be subject to environment and the factor such as artificial impact, factor as inevitable in wind-force, electromagnetic wave, barrier, manipulation error etc., aircraft may be caused to fall or be suspended on the first-class fortuitous event of barrier, if now there is no emergency response mechanism, the long-time large load operation of battery meeting, the lighter can cause the parts damages of aircraft, as drive motors burns out, mainboard burns out, and severe one even can initiation fire.
Utility model content
The utility model object is the power-supply management system providing a kind of aircraft, is intended to the unstable problem reliably of aircraft that the single powered battery of solution is deposited.
The utility model provides a kind of power-supply management system of aircraft, comprise battery case and flying vehicles control plate, described battery case comprises main battery unit, standby battery unit and battery control unit, described flying vehicles control plate has wireless transmit/receive units, serial communication unit and electrical source exchange unit, wherein:
Power when described main battery unit is used for described normal vehicle operation;
Power before described standby battery unit is used for described normal vehicle operation, after landing and when flight is unexpected;
Described battery control unit is connected with described main battery unit and standby battery unit, for receiving instruction, controlling the switch of described main battery unit and standby battery unit;
Described wireless transmit/receive units is for receiving the guidance command of remote controller;
Described serial communication unit is connected with described battery control unit, and the guidance command for receiving according to described wireless transmit/receive units transmits described instruction to described battery control unit;
Described electrical source exchange unit is connected with described main battery unit and standby battery unit, is that described flying vehicles control plate is powered for selecting described main battery unit or standby battery unit.
Further, described battery control unit comprises:
Single-chip microcomputer;
Electric power detection module, is connected with described single-chip microcomputer, for detecting primary, spare battery electric quantity;
Cell switch control module, is connected with described single-chip microcomputer, for controlling the switch of described main battery unit, standby battery unit;
Serial communication module, is connected with described single-chip microcomputer, is connected with described serial communication unit;
Reserve battery charge control module, is connected with described single-chip microcomputer, for giving described battery charging for subsequent use when described reserve battery electricity is not enough;
Keyboard input module, is connected with described single-chip microcomputer, receives user instruction; And
LED indicating module, is connected with described single-chip microcomputer, is used to indicate the state of described battery case.
Further, described main battery unit comprise battery protection chip, electric discharge MOSFET pipe, charging MOSFET pipe, power supply and electric power detection port, described electric discharge MOSFET pipe external priority control port and detect resistance, wherein:
The drain electrode of described electric discharge MOSFET pipe is connected with the described source electrode charging MOSFET pipe as the charging control end of the positive output end of described main battery unit, grid and described battery protection chip, source electrode; The control of discharge end that drain electrode is connected with the positive pole of described main battery, grid connects described battery protection chip of described charging MOSFET pipe and described power supply and electric power detection port; The charging of described external priority control port one end and described battery protection chip with and electric discharge control terminal be connected, single-chip microcomputer described in the other end connects, and for controlling the output of main battery, this pin has the shutoff control having precedence over described battery protection chip; Described detection resistance one end is connected with the negative pole of described main battery, and the other end is as the negative output terminal of described main battery unit.
Further, described standby battery unit comprises:
Described reserve battery;
Charging input end mouth, is connected with described power supply and electric power detection port;
Reserve battery charging module, one end is connected with described charging input end mouth;
Reserve battery charging protecting module, one end is connected with reserve battery charging module, reserve battery described in another termination;
Reserve battery output port, is connected with described reserve battery by described cell switch control module.
The utility model additionally provides a kind of power-supply management system of aircraft, comprise battery case, flying vehicles control plate and remote controller, described battery case comprises main battery unit, standby battery unit and battery control unit, described flying vehicles control plate has wireless transmit/receive units, serial communication unit and electrical source exchange unit, wherein:
Power when described main battery unit is used for described normal vehicle operation;
Power before described standby battery unit is used for described normal vehicle operation, after landing and when flight is unexpected;
Described battery control unit is connected with described main battery unit and standby battery unit, for receiving instruction, controlling the switch of described main battery unit and standby battery unit;
Described wireless transmit/receive units is for receiving the guidance command of described remote controller;
Described serial communication unit is connected with described battery control unit, and the guidance command for receiving according to described wireless transmit/receive units transmits described instruction to described battery control unit;
Described electrical source exchange unit is connected with described main battery unit and standby battery unit, is that described flying vehicles control plate is powered for selecting described main battery unit or standby battery unit.
Further, described battery control unit comprises:
Single-chip microcomputer;
Electric power detection module, is connected with described single-chip microcomputer, for detecting primary, spare battery electric quantity;
Cell switch control module, is connected with described single-chip microcomputer, for controlling the switch of described main battery unit, standby battery unit;
Serial communication module, is connected with described single-chip microcomputer, is connected with described serial communication unit;
Reserve battery charge control module, is connected with described single-chip microcomputer, for giving described battery charging for subsequent use when described reserve battery electricity is not enough;
Keyboard input module, is connected with described single-chip microcomputer, receives user instruction; And
LED indicating module, is connected with described single-chip microcomputer, is used to indicate the state of described battery case.
Further, described main battery unit comprise battery protection chip, electric discharge MOSFET pipe, charging MOSFET pipe, power supply and electric power detection port, described electric discharge MOSFET pipe external priority control port and detect resistance, wherein:
The drain electrode of described electric discharge MOSFET pipe is connected with the described source electrode charging MOSFET pipe as the charging control end of the positive output end of described main battery unit, grid and described battery protection chip, source electrode; The control of discharge end that drain electrode is connected with the positive pole of described main battery, grid connects described battery protection chip of described charging MOSFET pipe and described power supply and electric power detection port; The charging of described external priority control port one end and described battery protection chip with and electric discharge control terminal be connected, single-chip microcomputer described in the other end connects, and for controlling the output of main battery, this pin has the shutoff control having precedence over described battery protection chip; Described detection resistance one end is connected with the negative pole of described main battery, and the other end is as the negative output terminal of described main battery unit.
Further, described standby battery unit comprises:
Described reserve battery;
Charging input end mouth, is connected with described power supply and electric power detection port;
Reserve battery charging module, one end is connected with described charging input end mouth;
Reserve battery charging protecting module, one end is connected with reserve battery charging module, reserve battery described in another termination;
Reserve battery output port, is connected with described reserve battery by described cell switch control module.
The utility model additionally provides a kind of aircraft, comprises the power-supply management system of above-mentioned aircraft.
The power-supply management system of above-mentioned aircraft has double cell scheme, under Systematical control, in order to ensure the safety of aircraft, improve flight efficiency simultaneously, extend cruising time, a kind of double cell scheme is provided, the core technology of the program controls main power switch by remote controller, implementation increases by one piece of reserve battery on the basis of existing single battery powered mode, system is made to have dual power supply, this backup battery is in the case where there for system provides independent stable power supply: for the self-inspection of whole aerocraft system before aircraft starts, host battery switch is controlled when aircraft starts and close, detect for main battery real time electrical quantity in the aircraft course of work, the power-off protection and send emergency management and rescue signal when aircraft meets accident, ensure the safety of aircraft, extend working time simultaneously.
Accompanying drawing explanation
Fig. 1 is the module diagram of the power-supply management system of aircraft in the utility model preferred embodiment;
Fig. 2 is the module diagram of the battery control unit of the power-supply management system of aircraft shown in Fig. 1;
The circuit theory diagrams of the main battery unit that Fig. 3 is the power-supply management system of aircraft shown in Fig. 1;
Fig. 4 is the module diagram of the standby battery unit of the power-supply management system of aircraft shown in Fig. 1;
The module diagram of the electrical source exchange unit that Fig. 5 is the power-supply management system of aircraft shown in Fig. 1.
Detailed description of the invention
In order to make the technical problems to be solved in the utility model, technical scheme and beneficial effect clearly understand, below in conjunction with drawings and Examples, the utility model is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the utility model, and be not used in restriction the utility model.
Refer to Fig. 1, the power-supply management system arranged in aircraft in the utility model preferred embodiment comprises battery case 10 and flying vehicles control plate 20, described battery case 10 comprises main battery unit 11, battery control unit 12 and standby battery unit 13, and described flying vehicles control plate 20 has wireless transmit/receive units 21, serial communication unit 22 and electrical source exchange unit 23.
Described main battery unit 11 is powered for during described normal vehicle operation; Described standby battery unit 13 is for powering before described normal vehicle operation, after landing and when flight is unexpected; Described battery control unit 12 is connected with described main battery unit 11 and standby battery unit 13, for receiving instruction, controlling the switch of described main battery unit 11 and standby battery unit 13; Described wireless transmit/receive units 21 is for receiving the guidance command of remote controller 30; Described serial communication unit 22 is connected with described battery control unit 12, transmits described instruction to described battery control unit 12 for the guidance command received according to described wireless transmit/receive units 21; Described electrical source exchange unit 23 is connected with described main battery unit 11 and standby battery unit 13, powers for described flying vehicles control plate 20 for selecting described main battery unit 11 or standby battery unit 13.
In another embodiment is come, the power-supply management system of aircraft also comprises above-mentioned remote controller 30.Preferably, remote controller 30 comprises operational module 31, radio receiving transmitting module 32 and indicating module 33.Operational module 31 for inputting described guidance command, as key board, remote-control lever, touch-screen etc.; Radio receiving transmitting module 32 can with wireless transmit/receive units 21 wireless telecommunications of described flying vehicles control plate 20 to transmit data, as RF radio-frequency signal generator; Indicating module 33 is used to indicate the state of described aircraft, as indicator lamp, display screen etc.
Refer to Fig. 2, described battery control unit 12 comprises single-chip microcomputer 121, electric power detection module, cell switch control module, serial communication module 126, reserve battery charge control module 127, keyboard input module 128 and LED indicating module 129.
Single-chip microcomputer 121 adopts atmel corp ATmega series as main control chip.Its electric power system is connected on backup battery, and because load is comparatively light, power-supply fluctuation is little, thus ensure that the reliability of single-chip microcomputer 121 system.
Electric power detection module is connected with described single-chip microcomputer 121, for detecting primary, spare battery electric quantity.Particularly, electric power detection module comprises main battery electric power detection module 122 and reserve battery electric power detection module 123.Main battery electric power detection module 122 adopts model to be the device of " MAX17047 ", coordinates external buffer " MAX9910 ", also can adopt the device of " BQ34Z100 ", can compare high certainty of measurement, ensures the accuracy of battery electric quantity data.Reserve battery electric power detection module 123 adopts the A/D translation interface of above-mentioned single-chip microcomputer 121 to realize, by backup battery by receiving on the A/D translation interface of above-mentioned single-chip microcomputer 121 after precision resistance dividing potential drop, cell voltage is calculated by sampling, battery electric quantity can be drawn by converting, because backup battery plays booster action, only need close to when not having electricity, single-chip microcomputer 121 controls charger and charges the battery, so its electric power detection does not require very accurate.
In described battery case 10, main battery adopts three joint 4.2V battery tandem, provides 12.6V maximum output voltage.For prevent battery overcharge and cross put and short circuit time cause battery explosion or bulging, need to add battery protecting circuit to battery.
Cell switch control module is connected with described single-chip microcomputer 121, for controlling the switch of described main battery unit 11, standby battery unit 13.Particularly, cell switch control module comprises the host battery switch control module 124 controlling described main battery unit 11 and the reserve battery switch control module 125 controlling reserve battery.
Serial communication module 126 is connected with described single-chip microcomputer 121, is connected with described serial communication unit 22.Reserve battery charge control module 127 is connected with described single-chip microcomputer 121, for giving described battery charging for subsequent use when described reserve battery electricity is not enough.Keyboard input module 128 is connected with described single-chip microcomputer 121, receives user instruction.LED indicating module 129 is connected with described single-chip microcomputer 121, is used to indicate the state of described battery case 10.
Described single-chip microcomputer 121, when detecting that reserve battery electricity is not enough, can control reserve battery charge control module 127 and charge to reserve battery.Reserve battery charge control module 127 adopts the device of battery charging chip BQ24113A.
Single-chip microcomputer 121 receives user's start-up command by keyboard input module 128, when the long-time switching on and shutting down button pressing battery case 10 after 10 seconds single-chip microcomputer 121 start to start, open reserve battery by reserve battery switch control module 125 simultaneously, give flight control panel, single-chip microcomputer 121 can by main battery electric power detection module 122 and reserve battery electric power detection module 123 simultaneously, detect main battery and reserve battery electricity, and pointed out to user by LED indicating module 129.
Single-chip microcomputer 121, after receiving the serial port command sent of flight control panel, first resolves this order, if " driving main power source " order, then single-chip microcomputer 121 controls host battery switch control module 124 and opens host battery switch; If " pass main power source " order, then single-chip microcomputer 121 controls host battery switch control module 124 and cuts out host battery switch.
Refer to Fig. 3, main battery unit 11 comprises battery protecting circuit.Main battery unit 11 comprise battery protection chip 410, charging MOSFET pipe 411, electric discharge MOSFET pipe 412, power supply and electric power detection port 413, described electric discharge MOSFET pipe 412 external priority control port 414 and detect resistance 415.
The drain electrode of described electric discharge MOSFET pipe 412 is connected with the described source electrode charging MOSFET pipe 411 as the charging control end COP of the positive output end EB+ of described main battery unit 11, grid and described battery protection chip 410, source electrode; The control of discharge end DOP that drain electrode is connected with the positive pole of described main battery, grid connects described battery protection chip 410 of described charging MOSFET pipe 411 and described power supply and electric power detection port 413; The charging of described external priority control port 414 one end and described battery protection chip 410 with and discharge and to be connected with control terminal CTL, described in the other end, single-chip microcomputer 121 connects, for controlling the output of main battery, this pin has the shutoff control having precedence over described battery protection chip 410; Described detection resistance 415 one end is connected with the negative pole of described main battery, and the other end is as the negative output terminal EB-of described main battery unit 11.
Preferably; MOSFET pipe circuit in described protection circuit plays power switch effect simultaneously; above-mentioned single-chip microcomputer 121 system controls the specific control pin of battery protection ic by I/O; realize control MOSFET by battery protection chip 410 to manage; thus realize power switch controlling functions, under allowing this MOSFET pipe be in closed condition under default situations.
Further; the advantage utilizing the MOSFET pipe in battery protection system to do power switch is the MOSFET pipe quantity reducing serial connection, can reduce the internal resistance in electric power system on the one hand, reduces pressure drop and improves power supplying efficiency; can aircraft weight be reduced on the other hand, save cost simultaneously.
Refer to Fig. 4, described standby battery unit 13 comprises reserve battery 134, charging input end mouth 131, reserve battery charging module 132 and reserve battery output port 135.
Power supply and the electric power detection port 413 of charging input end mouth 131 and described main battery unit 11 are connected.One end of reserve battery charging module 132 is connected with described charging input end mouth 131, reserve battery 134 described in another termination.Reserve battery output port 135 is connected with described reserve battery 134 by described cell switch control module (reserve battery switch control module 125).
In the present embodiment, the model of described main battery protect IC 410 is the device of " S8254A ", and three joint main batterys are operated in tandem mode.Main battery protect IC 410 provides over-charge protective, Cross prevention, overcurrent and short-circuit protection for main battery.Each Pin description of S8254A is as shown in table 1 below.
Table 1:
Operation principle is summarized as follows, CV4, CV3, CV2, CV2 pin of main battery protect IC 410 is respectively used to the total voltage of detection three pieces of batteries and the voltage of every block battery, when finding the maximum 4.4V of a certain piece of cell voltage higher than setting, or when total voltage is higher than setting maximum 12.9V, now reach the maximum voltage that battery can bear, in order to prevent further charging damage battery, now the COP pin of main battery protect IC 410 can export a high level, turn off electric discharge MOSFET pipe 412, play the effect of filling protection; With being checked through a certain piece of cell voltage lower than 3.0V, or when total voltage is lower than setting maximum 9.0V, now reach the minimum voltage that battery can bear, in order to prevent further electric discharge, damage battery, now the DOP pin of main battery protect IC 410 can export a high level, turns off charging MOSFET pipe 411, plays the effect of Cross prevention; In addition, main battery protect IC 410 judges the electric current flowed out by the pressure drop detected on power supply and electric power detection port 413, after judging that electric current exceedes predetermined value, turns off charging MOSFET pipe 411, plays the effect of overcurrent and short-circuit protection.
In the present embodiment, electric discharge MOSFET pipe 412 device that to be models be " AOD403 ", because the power consumption of aircraft moment is larger, in order to the safety that ensures to discharge adopts two pattern raising operating currents in parallel.
Charging MOSFET pipe 411 device that to be models be " AOD403 ", be ensure charging safety, charging current is less than 40A, only manages with a MOSFET herein.Power supply and electric power detection port 413 charge for giving reserve battery 134, are connected on the charging input end mouth 131 of standby battery unit 13, simultaneously as the input pin of main battery electric power detection module 122.
The external priority control port 414 of electric discharge MOSFET pipe 412 is received by triode protection circuit on the I/O of single-chip microcomputer 121; for controlling the output of main battery; this pin has the shutoff control having precedence over battery protection chip 410; namely can the pass of priority acccess control electric discharge MOSFET pipe 412 by this external priority control port 414; thus realize the switch control rule of battery output; close during high level and export, during low level, control gives battery protection chip 410.
Described detection resistance 415 adopts a number type for Taiwan Stackpole company to be " CSS2725 " resistance, is mainly used in the pressure drop in test circuit, and then tests out the output current of battery, feeds back to battery protection chip 410.
In the present embodiment, reserve battery charging module 132 adopts general battery special charging IC.Charging IC input is directly connected on main battery.
Described reserve battery charging protecting module 133 adopts general battery protecting circuit, is connected on charhing unit and exports between reserve battery 134, the effect of starting protection reserve battery 134.Described reserve battery 134 adopts two joint lithium ion battery series connection.
Reserve battery switch control unit 125 is connected between stand-by battery box 10 reserve battery output port 135, works under single-chip microcomputer 121 controls.
Refer to Fig. 5, reserve battery output port 135 is received on electrical source exchange unit 23, to be used for before answering normal flight, to power and power to aerocraft system after landing and when flight is unexpected.
Referring to Fig. 5, is reserve battery on flying vehicles control plate 20 134 and the circuit diagram of the electrical source exchange unit 23 of main battery.Mainly comprise the aircraft power input port 24 on reserve battery output port 135, main battery output port 110 (comprising positive output end EB+ and the negative output terminal EB-of main battery unit 11), electrical source exchange unit 23 and flying vehicles control plate 20.
Its operation principle is summarized as follows, with two diodes in parallels in electrical source exchange unit 23, diode anode is connected on reserve battery output port 135, negative electrode is connected in aircraft power input port 24, main battery output port 110 is also connected in aircraft power input port 24 simultaneously, utilize diode forward conducting, the principle of reverse cut-off, when main battery is closed, cathode voltage is zero, anode voltage is backup battery voltage (maximum 8.4V, minimum 6.0V), diode current flow, because host battery switch is closed, electric current both can not flow to main battery, also can not flow out from main battery, now flying vehicles control plate 20 will from power taking reserve battery 134.When the switch opens of main battery; voltage and the main battery voltage of diode cathode are suitable; because the value of main battery under-voltage protection is set to 9V; in normal power supply situation, its output all can be greater than 9V; diode anode voltage lower than cathode voltage, diode cut-off work, electric current both can not flow to reserve battery 134; also can not flow out from reserve battery 134, now flight control system system will from power taking main battery.
The implementation procedure of power control system, is divided into following three kinds of situations:
The first situation: aircraft is subnormal startup flight just, and system can perform as follows:
Flying vehicles control plate 20 obtain standby battery unit 13 power after start-up routine, this program is executive system self-check program first, and whether detection system functions normal, comprise main battery electric power detection, gps signal, digital compass signal, gyroscope signal, electricity regulation and control making sheet signal etc.After self-inspection is passed through, aircraft can use wireless transmit/receive units 21 (as RF signal emission port) that information is sent to remote controller 30.
After remote controller 30 receives the signal of " self-inspection completes wait and takes off " that flying vehicles control plate 20 sends, start self-inspection, also can be set to and aircraft interlock Auto-Sensing Mode, each function in remote controller 30, see that aircraft whether can normal response, by the indicator lamp on panel after completing, or by display screen, information is passed to user, wait for that user assigns takeoff order, ensure that system is reliable when taking off.
Treat that user determines that needs take off, and in operation sequence after remote controller 30, takeoff order is sent to aircraft by RF signal emission port by remote controller 30, after aircraft obtains takeoff order, by single-chip microcomputer 121 system communication on serial ports and battery case 10, after single-chip microcomputer 121 receives orders, open main battery power switch, now main battery starts power supply, and backup battery disconnects, and aircraft starts normal work.
The second situation: aircraft runs into accident in flight course, system can perform as follows:
When systems axiol-ogy is to some motor stalls, or detect that battery electric quantity sharply declines, or detect that flying vehicles control plate 20 temperature significantly rises, when gyroscope and GPS information do not change, illustrate that aircraft has fallen or hung on barrier simultaneously.
Now flying vehicles control plate 20 can be communicated with the battery control unit 12 on battery case 10 by serial communication unit 22, notice battery control unit 12 closes main battery power switch, now main battery is stopped power supply, and backup battery starts power supply automatically, and aircraft starts contingency mode.
Aircraft starts contingency mode, and self warning system opened by aircraft on the one hand, opens acoustooptic alarm system, as prompting.
On the other hand, aircraft can send an SOS continually to remote controller 30, and signal comprises GPS geographical location information, facilitates rescue worker to find.
The third situation: stop flight after aircraft regular descent, system can perform as follows:
When systems axiol-ogy aircraft landing, and each motor all out of service after, start dormancy program, after waiting for certain hour,
Notice battery control unit 12 closes main battery power switch, and now main battery is stopped power supply, and backup battery starts power supply automatically, and aircraft is in park mode.
Aircraft is opened wait and to be taken off awakening mode, waits for that remote controller 30 sends takeoff order simultaneously.
Receive after takeoff order until aircraft and start the step that circulation performs the first situation.
So, when flight control system enters to detect extremely, the backup battery that can start low-voltage small area analysis is immediately powered, and restarts protection mechanism, closes the main power switch of output HIGH voltage big current, avoid loss.
Simultaneously because backup battery charges by main battery, flight control system can last very long be continual sends sound and light alarm signal, gives remote controller 30 GPS locating information simultaneously, conveniently searches.
If first can allow system boot self-inspection, under ensureing all normal situation of aircraft and each function of remote controller 30, more logical remote controller 30 is opened main power switch and just can be eliminated this hidden danger.In addition, in aircraft landing, during groung, system can utilize back battery to enter holding state, and now system closes main power switch automatically, ensures the safety of aircraft, extends working time simultaneously.
The foregoing is only preferred embodiment of the present utility model; not in order to limit the utility model; all do within spirit of the present utility model and principle any amendment, equivalent to replace and improvement etc., all should be included within protection domain of the present utility model.
Claims (10)
1. the power-supply management system of an aircraft, it is characterized in that, comprise battery case and flying vehicles control plate, described battery case comprises main battery unit, standby battery unit and battery control unit, described flying vehicles control plate has wireless transmit/receive units, serial communication unit and electrical source exchange unit, wherein:
Power when described main battery unit is used for described normal vehicle operation;
Power before described standby battery unit is used for described normal vehicle operation, after landing and when flight is unexpected;
Described battery control unit is connected with described main battery unit and standby battery unit, for receiving instruction, controlling the switch of described main battery unit and standby battery unit;
Described wireless transmit/receive units is for receiving the guidance command of remote controller;
Described serial communication unit is connected with described battery control unit, and the guidance command for receiving according to described wireless transmit/receive units transmits described instruction to described battery control unit;
Described electrical source exchange unit is connected with described main battery unit and standby battery unit, is that described flying vehicles control plate is powered for selecting described main battery unit or standby battery unit.
2. the power-supply management system of aircraft as claimed in claim 1, it is characterized in that, described battery control unit comprises:
Single-chip microcomputer;
Electric power detection module, is connected with described single-chip microcomputer, for detecting primary, spare battery electric quantity;
Cell switch control module, is connected with described single-chip microcomputer, for controlling the switch of described main battery unit, standby battery unit;
Serial communication module, is connected with described single-chip microcomputer, is connected with described serial communication unit;
Reserve battery charge control module, is connected with described single-chip microcomputer, for giving described battery charging for subsequent use when described reserve battery electricity is not enough;
Keyboard input module, is connected with described single-chip microcomputer, receives user instruction; And
LED indicating module, is connected with described single-chip microcomputer, is used to indicate the state of described battery case.
3. the power-supply management system of aircraft as claimed in claim 2; it is characterized in that; described main battery unit comprise battery protection chip, electric discharge MOSFET pipe, charging MOSFET pipe, power supply and electric power detection port, described electric discharge MOSFET pipe external priority control port and detect resistance, wherein:
The drain electrode of described electric discharge MOSFET pipe is connected with the described source electrode charging MOSFET pipe as the charging control end of the positive output end of described main battery unit, grid and described battery protection chip, source electrode; The control of discharge end that drain electrode is connected with the positive pole of described main battery, grid connects described battery protection chip of described charging MOSFET pipe and described power supply and electric power detection port; The charging of described external priority control port one end and described battery protection chip with and electric discharge control terminal be connected, single-chip microcomputer described in the other end connects, and for controlling the output of main battery, this pin has the shutoff control having precedence over described battery protection chip; Described detection resistance one end is connected with the negative pole of described main battery, and the other end is as the negative output terminal of described main battery unit.
4. the power-supply management system of aircraft as claimed in claim 3, it is characterized in that, described standby battery unit comprises:
Described reserve battery;
Charging input end mouth, is connected with described power supply and electric power detection port;
Reserve battery charging module, one end is connected with described charging input end mouth;
Reserve battery charging protecting module, one end is connected with reserve battery charging module, reserve battery described in another termination;
Reserve battery output port, is connected with described reserve battery by described cell switch control module.
5. the power-supply management system of an aircraft, it is characterized in that, comprise battery case, flying vehicles control plate and remote controller, described battery case comprises main battery unit, standby battery unit and battery control unit, described flying vehicles control plate has wireless transmit/receive units, serial communication unit and electrical source exchange unit, wherein:
Power when described main battery unit is used for described normal vehicle operation;
Power before described standby battery unit is used for described normal vehicle operation, after landing and when flight is unexpected;
Described battery control unit is connected with described main battery unit and standby battery unit, for receiving instruction, controlling the switch of described main battery unit and standby battery unit;
Described wireless transmit/receive units is for receiving the guidance command of described remote controller;
Described serial communication unit is connected with described battery control unit, and the guidance command for receiving according to described wireless transmit/receive units transmits described instruction to described battery control unit;
Described electrical source exchange unit is connected with described main battery unit and standby battery unit, is that described flying vehicles control plate is powered for selecting described main battery unit or standby battery unit.
6. the power-supply management system of aircraft as claimed in claim 5, it is characterized in that, described battery control unit comprises:
Single-chip microcomputer;
Electric power detection module, is connected with described single-chip microcomputer, for detecting primary, spare battery electric quantity;
Cell switch control module, is connected with described single-chip microcomputer, for controlling the switch of described main battery unit, standby battery unit;
Serial communication module, is connected with described single-chip microcomputer, is connected with described serial communication unit;
Reserve battery charge control module, is connected with described single-chip microcomputer, for giving described battery charging for subsequent use when described reserve battery electricity is not enough;
Keyboard input module, is connected with described single-chip microcomputer, receives user instruction; And
LED indicating module, is connected with described single-chip microcomputer, is used to indicate the state of described battery case.
7. the power-supply management system of aircraft as claimed in claim 6; it is characterized in that; described main battery unit comprise battery protection chip, electric discharge MOSFET pipe, charging MOSFET pipe, power supply and electric power detection port, described electric discharge MOSFET pipe external priority control port and detect resistance, wherein:
The drain electrode of described electric discharge MOSFET pipe is connected with the described source electrode charging MOSFET pipe as the charging control end of the positive output end of described main battery unit, grid and described battery protection chip, source electrode; The control of discharge end that drain electrode is connected with the positive pole of described main battery, grid connects described battery protection chip of described charging MOSFET pipe and described power supply and electric power detection port; The charging of described external priority control port one end and described battery protection chip with and electric discharge control terminal be connected, single-chip microcomputer described in the other end connects, and for controlling the output of main battery, this pin has the shutoff control having precedence over described battery protection chip; Described detection resistance one end is connected with the negative pole of described main battery, and the other end is as the negative output terminal of described main battery unit.
8. the power-supply management system of aircraft as claimed in claim 7, it is characterized in that, described standby battery unit comprises:
Described reserve battery;
Charging input end mouth, is connected with described power supply and electric power detection port;
Reserve battery charging module, one end is connected with described charging input end mouth;
Reserve battery charging protecting module, one end is connected with reserve battery charging module, reserve battery described in another termination; And
Reserve battery output port, is connected with described reserve battery by described cell switch control module.
9. the power-supply management system of aircraft as claimed in claim 5, it is characterized in that, described remote controller comprises:
Operational module, for inputting described guidance command;
Radio receiving transmitting module, can with the wireless transmit/receive units wireless telecommunications of described flying vehicles control plate to transmit data;
Indicating module, is used to indicate the state of described aircraft.
10. an aircraft, is characterized in that, comprises the power-supply management system of the aircraft described in any one of Claims 1-4, or the power-supply management system of aircraft described in any one of claim 5 to 9.
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| CN201520518765.4U CN204840939U (en) | 2015-07-16 | 2015-07-16 | Aircraft and power management system thereof |
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| CN201520518765.4U CN204840939U (en) | 2015-07-16 | 2015-07-16 | Aircraft and power management system thereof |
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| CN204840939U true CN204840939U (en) | 2015-12-09 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106026374A (en) * | 2016-07-29 | 2016-10-12 | 国网浙江省电力公司衢州供电公司 | Unmanned aerial vehicle power supply method and system |
| CN106334322A (en) * | 2015-07-16 | 2017-01-18 | 深圳曼塔智能科技有限公司 | Aircraft and power supply management system |
| CN106716776A (en) * | 2016-02-26 | 2017-05-24 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle, and power supply system, method and device thereof |
| CN107102649A (en) * | 2017-04-13 | 2017-08-29 | 苏州安飞荣工业科技有限公司 | A kind of high security unmanned plane |
| CN107733521A (en) * | 2017-10-31 | 2018-02-23 | 北京邮电大学 | A kind of Unmanned Aerial Vehicle Data transmission method, apparatus and system |
| CN110943510A (en) * | 2019-11-15 | 2020-03-31 | 同方电子科技有限公司 | Power supply controller applied to individual communication system |
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2015
- 2015-07-16 CN CN201520518765.4U patent/CN204840939U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106334322A (en) * | 2015-07-16 | 2017-01-18 | 深圳曼塔智能科技有限公司 | Aircraft and power supply management system |
| CN106716776A (en) * | 2016-02-26 | 2017-05-24 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle, and power supply system, method and device thereof |
| CN106026374A (en) * | 2016-07-29 | 2016-10-12 | 国网浙江省电力公司衢州供电公司 | Unmanned aerial vehicle power supply method and system |
| CN107102649A (en) * | 2017-04-13 | 2017-08-29 | 苏州安飞荣工业科技有限公司 | A kind of high security unmanned plane |
| CN107733521A (en) * | 2017-10-31 | 2018-02-23 | 北京邮电大学 | A kind of Unmanned Aerial Vehicle Data transmission method, apparatus and system |
| CN110943510A (en) * | 2019-11-15 | 2020-03-31 | 同方电子科技有限公司 | Power supply controller applied to individual communication system |
| CN110943510B (en) * | 2019-11-15 | 2023-07-04 | 同方电子科技有限公司 | Power supply controller applied to individual communication system |
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