CN102355044A - Dual-redundancy aircraft power supply and power supply mode thereof - Google Patents

Dual-redundancy aircraft power supply and power supply mode thereof Download PDF

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Publication number
CN102355044A
CN102355044A CN2011102582272A CN201110258227A CN102355044A CN 102355044 A CN102355044 A CN 102355044A CN 2011102582272 A CN2011102582272 A CN 2011102582272A CN 201110258227 A CN201110258227 A CN 201110258227A CN 102355044 A CN102355044 A CN 102355044A
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circuit
power supply
direct
current switch
battery
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Pending
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CN2011102582272A
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Chinese (zh)
Inventor
张一鸣
陈贺娜
王海娟
仝江涛
高俊侠
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Beijing University of Technology
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Beijing University of Technology
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Priority to CN2011102582272A priority Critical patent/CN102355044A/en
Publication of CN102355044A publication Critical patent/CN102355044A/en
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Abstract

The invention discloses a dual-redundancy aircraft power supply and a power supply mode thereof, which belong to the field of aerospace power supplies. The power supply comprises two battery packs, four switching circuits, two direct current switching power supplies, two detection circuits and a control circuit, wherein the direct current switching power supplies reduce battery voltage to voltage required by a load to supply power to the load; the detection circuits detect voltage signals of each battery pack and each direct current switching power supply, and feeds the detected voltage signals back to the control circuit; the control circuit controls the switching circuits according to comparison between the detected voltage and set reference voltage; the batteries and the direct current switching power supplies all supply the power to the load by adopting redundancy systems; each battery pack and each direct current switching power supply are connected with a switching circuit and then connected in parallel to ensure that the electrical equipment of an unmanned aerial vehicle can be supplied with the power as long as the two battery packs and the two direct current switching power supplies are damaged at the same time. The dual-redundancy aircraft power supply supplies the power to each piece of electrical equipment by adopting a centralized power supply mode and the dual redundancy systems, so system safety and reliability are comprehensively improved.

Description

A kind of pair of remaining airplane power source and supply power mode thereof
Technical field
The present invention relates to a kind of pair of remaining airplane power source and supply power mode thereof, belong to the Aero-Space field of power supplies.
Background technology
Aviation power system is one of critical system of whole air equipment, and it is undertaking the vital task that the payload power supply is provided for other subsystems.The good and bad whole operating state of air equipment that directly influences of power-supply system power supply quality; And along with the develop rapidly of modern science and aeronautical technology; Various electronic equipments are increasing, and power consumption constantly increases, and the structure and the control of aviation power system become increasingly complex.Therefore designing an aviation power system with high reliability is necessary.
At present; Airplane power source adopts the decentralized power-supply method usually; Be that each power consumption equipment is worn a battery respectively and supplied power; This method has just caused to guaranteeing normal operation; Need to carry more jumbo battery and come to be electric, this invisible air equipment load of giving has caused burden, and the decentralized power-supply method does not have power-supply management system yet; Can't monitor, manage each load electricity consumption situation, whole power supply is in be operated in a kind of fringe.The deficiency that causes to this mode; Developed two remaining airplane power source and supply power mode thereof specially, it adopts the centrally connected power supply method that each power consumption equipment is supplied power, and is furnished with power-supply management system; Can come according to the electric weight of battery each load electricity consumption is controlled, guarantee safe flight.
Airplane power source often adopts the decentralized power-supply method; And cell voltage also adopts the single circuit conversion to the change-over circuit of load voltage; There is not fallback circuit; This will cause if change-over circuit goes wrong; Entire equipment also can't operate as normal, or even damages, therefore; For guaranteeing the two remaining airplane power source of safe operation development, improved the reliability of airplane power source to a great extent.
Summary of the invention
The present invention is primarily aimed at the problem of airplane power source decentralized power-supply mode and single power supply existence, overcomes its weak point, from improving the angle of airplane power source reliability and power density, develops a kind of pair of remaining airplane power source and supply power mode thereof.
For realizing above-mentioned purpose, a kind of pair of remaining airplane power source provided by the invention is characterized in that: comprise that 2 battery pack are battery pack A, battery pack B, 4 switching circuits are switching circuit S 1, S 2, S 3, S 4, 2 direct Switching Power Supplies are first direct-current switch power supply, second direct-current switch power supply, 2 testing circuits are first testing circuit, second testing circuit, 1 control circuit;
Wherein, the positive pole of battery A, B links to each other with two inputs of first testing circuit respectively, and the output of first testing circuit is linking to each other with control circuit, the positive pole of battery A, B more respectively with switching circuit S 1, S 2Input join switching circuit S 1, S 2Control end link to each other switching circuit S respectively with control circuit 1, S 2Output link to each other switching circuit S 1, S 2Output link to each other with the input of first direct-current switch power supply, second direct-current switch power supply respectively again; The output of first direct-current switch power supply, second direct-current switch power supply links to each other with the input of second testing circuit; The output of second testing circuit with the linking to each other of control circuit; The output of first direct-current switch power supply, second direct-current switch power supply links to each other, the output of first direct-current switch power supply, second direct-current switch power supply more respectively with switching circuit S 3, S 4Input link to each other switching circuit S 3, S 4Control end link to each other switching circuit S respectively with control circuit 3, S 4Output link to each other switching circuit S 3, S 4Output be connected with load respectively again.
Two remaining airplane power source adopt centralized power supply system to give each power consumption equipment power supply; Direct-current switch power supply reduces cell voltage to load required voltage powering load; Testing circuit feeds back to control circuit through detecting the voltage signal of each battery and direct-current switch power supply, and control circuit is controlled switching circuit according to detected voltage and reference voltage comparative result; Battery and direct-current switch power supply all adopt the redundant system powering load; Each battery and direct-current switch power supply all connect a switching circuit respectively, and then respectively parallel connection, have guaranteed so long as not two batteries and two direct-current switch power supplies simultaneously badly, just can supply power to power consumption equipment.Centralized power supply system is adopted in this invention, and two redundant system supplies power for each power consumption equipment, raising in all directions the fail safe of system, reliability.
Further, wherein all connect an inverter between the control end of each switching circuit and the control circuit respectively.Can guarantee like this that if control circuit goes wrong under all normal situation of battery and DC/DC circuit, power consumption equipment can also normally move.
Described pair of remaining airplane power source always has 4 kinds of supply power mode powering loads; First kind is a battery pack, two direct-current switch power supply circuit powering loads, if battery or direct-current switch power supply break down, through control circuit control switch circuit, comes powering load; Second kind is a battery and a direct-current switch power supply powering load, if battery or direct-current switch power supply break down, through control circuit control switch circuit, switches to another road battery and direct-current switch power supply and comes powering load; The third two batteries, direct-current switch power supply be powering loads all simultaneously, if battery or direct-current switch power supply break down, through control circuit control switch circuit, come powering load; The 4th kind is two batteries, two direct-current switch power supplies powering load all simultaneously, if battery or direct-current switch power supply circuit break down, through control circuit control switch circuit, comes powering load.
Two remaining airplane power source adopt centralized power supply system to give each power consumption equipment power supply; Direct-current switch power supply reduces cell voltage to load required voltage powering load; Testing circuit feeds back to control circuit through detecting the voltage signal of each battery and direct-current switch power supply, and control circuit is relatively controlled switching circuit according to the reference voltage of detected voltage and setting; Battery and direct-current switch power supply all adopt the redundant system powering load; Each battery and direct-current switch power supply all connect a switching circuit respectively, and then respectively parallel connection, have guaranteed so long as not two batteries and two direct-current switch power supplies simultaneously badly, just can supply power to power consumption equipment.Centralized power supply system is adopted in this invention, and two redundant system supplies power for each power consumption equipment, raising in all directions the fail safe of system, reliability.
Description of drawings
Fig. 1 is an overall structure block diagram of the present invention.
Fig. 2 is switching circuit S 1
Fig. 3 is switching circuit S 2
Fig. 4 is switching circuit S 3
Fig. 5 is switching circuit S 4
Fig. 6 is a battery, two direct-current switch power supplies (being called for short DC/DC) circuit powering load.
Fig. 7 is a battery, a DC/DC circuit powering load.
Fig. 8 is two batteries, DC/DC circuit powering load simultaneously.
Fig. 9 is two batteries, two DC/DC circuit powering load simultaneously.
Concrete label is following among the figure:
1. battery pack
2. switching circuit S 1, S 2
3.DC/DC circuit
4. switching circuit S 3, S 4
5. load
6. first testing circuit
7. control circuit
8. second testing circuit
9. inverter 1
12. inverter 2
15. inverter 3
18. inverter 4
10.Mos pipe switching circuit 1
13.Mos pipe switching circuit 2
16.Mos pipe switching circuit 3
19.Mos pipe switching circuit 4
11. diode D 1
14. diode D 3
17. diode D 5
20. diode D 7
K 1, K 2, K 3, K 4. the control end of switching circuit
Bat1, Bat2. switching circuit S 1, S 2Input
DC 1, DC 2. switching circuit S 3, S 4Input
The DC/DC circuit. direct-current switch power supply
Q 2, Q 4, Q 6, Q 8.P raceway groove mos manages
Q 2_ d, Q 4_ d, Q 6_ d, Q 8The drain electrode of _ d.P raceway groove mos pipe
Q 2_ s, Q 4_ s, Q 6_ s, Q 8The source electrode of _ s.P raceway groove mos pipe
Q 1, Q 3, Q 5, Q 7.NPN type triode
D 2, D 4, D 6, D 8. diode
U 1, U 2, U 3, U 4. inverter
R 1, R 2, R 3, R 4, R 5, R 6, R 7, R 8, R 9, R 10, R 11, R 12, R 13, R 14, R 15, R 16, R 17, R 18, R 19, R 20, R 21, R 22, R 23, R 24. resistance
A 1, A 2. the input of testing circuit 1
A 3, A 4. the input of testing circuit 2
Embodiment
Narrate the specific embodiment of the present invention with reference to the accompanying drawings.A kind of pair of remaining airplane power source of the present invention and supply power mode preferred implementation thereof comprise battery pack 1, switching circuit S 1, S 22, DC/DC3, switching circuit S 3, S 44, testing circuit 6,8, control circuit 7, load 5; The positive pole of battery A, B respectively with the A of first testing circuit 1, A 2Link to each other, the output of testing circuit with the Io of control circuit 5Link to each other, the positive pole of battery A, B more respectively with switching circuit S 1, S 2Input Bat1, Bat2 join switching circuit S 1, S 2Control end K 1, K 2Respectively with the Io of control circuit 1, Io 2Link to each other switching circuit S 1, S 2Output Q 2_ d, Q 4_ d links to each other and links to each other the output of a DC/DC, the 2nd DC/DC and the A of second testing circuit again with the input of a DC/DC, the 2nd DC/DC 3, A 4Link to each other, the output of second testing circuit with the Io of control circuit 6Link to each other, the output of a DC/DC, the 2nd DC/DC more respectively with switching circuit S 3, S 4Input DC 1, DC 2Link to each other switching circuit S 3, S 4Control end K 3, K 4Respectively with the Io of control circuit 3, Io 4Link to each other switching circuit S 3, S 4Output Q 6_ d, Q 8_ d links to each other, and is connected with load, shown in figure one connects again;
In the better embodiment of the present invention; Described battery comprises two battery A, B; Two batteries all connect a switching circuit respectively; And connect an inverter respectively at the control end of switching circuit; Can guarantee like this if control circuit goes wrong; Under all normal situation of battery and DC/DC circuit, power consumption equipment can also normally move.The wherein positive pole of battery A, B and switching circuit S 1, S 2Input Bat1, Bat2 link to each other, Bat1, Bat2 again with diode D 1, D 3Anode link to each other diode D 1, D 3Negative electrode and mos pipe Q 2_ s, Q 4_ s links to each other, and mos manages Q 2_ d, Q 4_ d links to each other and is connected switching circuit S again with the DC/DC circuit 1, S 2Control end K 1, K 2Respectively with the Io of control circuit 1, Io 2Link to each other K 1, K 2Connect a pull down resistor and an inverter again, the input of the output termination mos pipe switching circuit 1,2 of inverter is shown in Fig. 2,3 connects;
In the better embodiment of the present invention; Described DC/DC circuit comprises two DC/DC reduction voltage circuits; Their output links to each other and then powering load with two switching circuits; And connect an inverter respectively at the control end of switching circuit; Can guarantee like this if control circuit goes wrong; Under all normal situation of battery and DC/DC circuit, entire equipment can also operate as normal.The wherein output of a DC/DC, the 2nd DC/DC and switching circuit S 3, S 4Input DC 1, DC 2Join DC 1, DC 2Again with diode D 5, D 7Anode link to each other diode D 5, D 7Negative electrode and mos pipe Q 6_ s, Q 8_ s links to each other, and mos manages Q 6_ d, Q 8_ d links to each other and is connected switching circuit S again with the DC/DC circuit 3, S 4Control end K 3, K 4Respectively with the Io of control circuit 3, Io 4Link to each other K 3, K 4Connect a pull down resistor and an inverter again, the output of inverter connects the input of mos pipe switching circuit 3,4, shown in Fig. 4,5 connects;
Instance one:
A battery two DC / DC power supply to the load circuit, the control circuit can control the DSP, DSP in the IO port to the control signal Io 1 and Io 2 a high level, a low level so that only one battery, DS? P to the control signal Io 3 and Io 4 low, ensure that the two DC / DC circuits are working, if and when the battery is faulty or out of power, the Io 1 and Io 2 of high and low reverse, so that another battery; if the battery is normal, one DC / DC circuit fails, just under the detection circuit detects the voltage signal and the comparison controller compares the reference voltage signal, wherein if the DC / DC circuit output voltage is 12V, then the comparator reference voltage is set to 12v, after comparing the comparator if the difference in 0-2v are considered within the normal circuit, beyond this Range is considered circuit fails, the final result of the comparison back to the DSP, DSP based on the comparison of the fault branch which outputs a high level control signal to switch off, so that the way of normal DC / DC work is available.
Instance two:
A DC/DC circuit of battery powering load, another piece battery and DC/DC circuit are as subsequent use, and wherein control circuit can adopt DS P control, and the Io mouth among the DSP is given control signal Io 1And Io 2A high level, a low level, only allow wherein one battery operated, DSP gives control signal Io 3And Io 4A high level, a low level only allows one of them DC/DC circuit working, and another backups, if when battery breaks down or do not have electricity, Io 1And Io 2High-low level reverse, make another battery operated; If battery is normal, when the DC/DC circuit breaks down, give control signal Io so 3And Io 4High-low level reverse.
Instance three:
Two batteries (If the battery voltage is 72V) a DC / DC power supply to the load circuit, DSP in the mouth to the control signal Io Io 1 and Io 2 are low, two batteries simultaneously, DSP to the control signal Io 3 and Io 4 A low a high level to ensure a DC / DC circuit, wherein if and when a battery fails, put the first detection circuit detects the voltage signal and a comparator for comparing the reference voltage signal, wherein if Battery voltage is 72V then the comparator reference voltage is set to 72V, after comparing the comparator if the difference between 0 and 10V are considered within the normal circuit, and finally to compare the results back to DSP, DSP based on the comparison of the fault circuit That way battery control signal outputs a high level disconnect it, just let another battery; if the DC / DC circuit fails, then according to the detection circuit detects the voltage comparator reference voltage signal comparison, which if DC / DC circuit output voltage is 12V, then the comparator reference voltage is set to 12v, if after a comparator comparing the difference in the 0-2v are considered within the normal circuit, not in this range is considered the circuit fails, the final the comparison result to the DSP, DSP based on the comparison of the fault branch which outputs a high level control signal to switch off, a low level to another circuit can be allowed to work.
Instance four:
Two batteries two DC / DC power supply to the load circuit, DSP in the mouth to the control signal Io Io 1 and Io 2 will output low, to ensure two battery, DSP to the control signal Io 3 and Io 4 are low , ensure that the two DC / DC circuits operate, if and when the battery fails then according to the voltage detection circuit detects the signal and the comparator reference voltage, wherein if the battery voltage is 72V reference voltage of the comparator is set to 72V After comparing the comparator if the difference between 0 and 10V are considered within the normal circuit, the circuit beyond this range is considered a failure, and finally to compare the results back to DSP, DSP based on the comparison of which branch of the fault circuit battery outputs a high level control signal to disconnect it so that only one battery; if when the DC / DC circuit fails, just under the detection circuit detects the voltage signal and a comparator for comparing the reference voltage signal, wherein if DC / DC circuit output voltage is 12V, then the comparator reference voltage is set to 12v, if after a comparator comparing the difference in the 0-2v are considered within the normal circuit, beyond this range is considered the circuit fails, the final the comparison result to the DSP, DSP based on the comparison of the fault branch which outputs a high level control signal to switch off, so that the way of normal DC / DC work can.

Claims (3)

1. two remaining airplane power source, it is characterized in that: comprise that 2 battery pack are battery pack A, battery pack B, 4 switching circuits are switching circuit S 1, S 2, S 3, S 4, 2 direct Switching Power Supplies are first direct-current switch power supply, second direct-current switch power supply, 2 testing circuits are first testing circuit, second testing circuit, 1 control circuit;
Wherein, the positive pole of battery A, B links to each other with two inputs of first testing circuit respectively, and the output of first testing circuit is linking to each other with control circuit, the positive pole of battery A, B more respectively with switching circuit S 1, S 2Input join switching circuit S 1, S 2Control end link to each other switching circuit S respectively with control circuit 1, S 2Output link to each other switching circuit S 1, S 2Output link to each other with the input of first direct-current switch power supply, second direct-current switch power supply respectively again; The output of first direct-current switch power supply, second direct-current switch power supply links to each other with the input of second testing circuit; The output of second testing circuit with the linking to each other of control circuit; The output of first direct-current switch power supply, second direct-current switch power supply links to each other, the output of first direct-current switch power supply, second direct-current switch power supply more respectively with switching circuit S 3, S 4Input link to each other switching circuit S 3, S 4Control end link to each other switching circuit S respectively with control circuit 3, S 4Output link to each other switching circuit S 3, S 4Output be connected with load respectively again.
2. according to the said a kind of pair of remaining airplane power source of claim 1, it is characterized in that: described 4 switching circuits wherein all connect an inverter respectively between the control end of each switching circuit and the control circuit.
3. application rights requires the supply power mode of 1 described pair of remaining airplane power source, it is characterized in that: always have 4 kinds of supply power mode powering loads; First kind is a battery pack, two direct-current switch power supply circuit powering loads, if battery or direct-current switch power supply break down, through control circuit control switch circuit, comes powering load; Second kind is a battery and a direct-current switch power supply powering load, if battery or direct-current switch power supply break down, through control circuit control switch circuit, switches to another road battery and direct-current switch power supply and comes powering load; The third two batteries, direct-current switch power supply be powering loads all simultaneously, if battery or direct-current switch power supply break down, through control circuit control switch circuit, come powering load; The 4th kind is two batteries, two direct-current switch power supplies powering load all simultaneously, if battery or direct-current switch power supply circuit break down, through control circuit control switch circuit, comes powering load.
CN2011102582272A 2011-09-02 2011-09-02 Dual-redundancy aircraft power supply and power supply mode thereof Pending CN102355044A (en)

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CN103023334A (en) * 2012-11-26 2013-04-03 北京工业大学 Multi-redundance aircraft electric power source and starting method thereof
CN103227503A (en) * 2013-05-07 2013-07-31 国家电网公司 Power supply system of transformer substation
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CN103475084A (en) * 2013-08-23 2013-12-25 苏州工业园区安电电子有限公司 Safe power distribution system
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CN103023334A (en) * 2012-11-26 2013-04-03 北京工业大学 Multi-redundance aircraft electric power source and starting method thereof
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Application publication date: 20120215