CN107211575B - Aircraft low-voltage dc power supply system - Google Patents
Aircraft low-voltage dc power supply systemInfo
- Publication number
- CN107211575B CN107211575B CN200510000626.3A CN200510000626A CN107211575B CN 107211575 B CN107211575 B CN 107211575B CN 200510000626 A CN200510000626 A CN 200510000626A CN 107211575 B CN107211575 B CN 107211575B
- Authority
- CN
- China
- Prior art keywords
- voltage
- power supply
- supply system
- regulation range
- range converter
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 230000001360 synchronised effect Effects 0.000 claims description 36
- 238000004804 winding Methods 0.000 claims description 10
- 239000003990 capacitor Substances 0.000 claims description 7
- 238000001514 detection method Methods 0.000 claims description 3
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 9
- 238000010586 diagram Methods 0.000 description 4
- 230000003068 static effect Effects 0.000 description 3
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 2
- OJIJEKBXJYRIBZ-UHFFFAOYSA-N cadmium nickel Chemical compound [Ni].[Cd] OJIJEKBXJYRIBZ-UHFFFAOYSA-N 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Abstract
The invention discloses a kind of aircraft low-voltage dc power supply system, it includes a magneto alternator [1] and three-phase bridge rectifier circuit [2], Width funtion adjustable range converter [3] and controller [4], Width funtion adjustable range converter [3] is made up of inductance L, electric capacity C, diode D and power switch pipe VT, controller [4] is Voltage Feedback type controller, is made up of detection circuit, reference voltage, comparison circuit, triangular-wave generator, PWM modulator and drive circuit；Controller [4] is by controlling power switch pipe VT conducting and deadline in Width funtion adjustable range converter [3], power switch pipe VT dutycycle is adjusted, so that the output voltage of the aircraft low-voltage dc power supply system does not change with the rotation speed change of magneto alternator [1].It is big that the aircraft low-voltage dc power supply system of the present invention is suitable for the range of speeds, the electric energy that power-supply system output multi-channel can be made separate, improve flight control system power or emergency service reliability.
Description
Technical Field
The invention relates to a low-voltage direct-current power supply system of an airplane, which can be used as a special power supply system of a flight control system and can also be used as an emergency power supply system of the airplane.
Background
Modern aircraft, especially advanced fighters after the third generation, adopt the fly-by-wire operating system, have greatly raised the requirement for reliability of power supply. In order to ensure flight safety, the conventional special power supply system for the flight control system adopts a redundancy power supply system, so that the power supply system and the power distribution system of the airplane are very complex, and the number of power supply subsystems is large, such as French phantom-2000 and American F-16 fighters.
The unreal image-2000 fighter plane flight control system is powered by a special power supply consisting of an onboard secondary power supply 150A transformer rectifier, a static converter, a storage battery, a static converter, two hydraulically driven 350VA permanent magnet generators and a transformer rectifier thereof. Under the normal state, the flight control system is powered by a 150A transformer rectifier and a static converter; when two generators serving as main power supplies have faults, the 350VA permanent magnet generator driven by two hydraulic pressures and the transformer rectifier thereof supply power; when the engine is stopped in the air, a 40Ah cadmium-nickel storage battery and a 350VA converter are used for supplying power.
The F-16 fighter flight control system is powered by the permanent magnet generator and the rectifier thereof of the backup generator, the emergency direct current bus bar, the storage battery bus bar, the permanent magnet generator of the emergency generator and the rectifier thereof, wherein the permanent magnet generator and the rectifier thereof of the backup generator are used as main power supply channels. When the engine is stopped in the air, the main power supply channel consisting of the permanent magnet generator of the backup generator and the rectifier thereof can not supply power any more, and only a 5kVA emergency generator driven by an emergency power device and a 15Ah cadmium-nickel storage battery can supply power, but the emergency generator can only be maintained for 10 minutes due to the limitation of hydrazine fuel.
As can be seen from the power supply system special for the phantom-2000 and F-16 fighter flight control system, in order to ensure the power supply reliability, a plurality of independent power supply channels can be arranged. The disadvantage is that the dedicated power supply and distribution system is quite complex, and although the mission reliability is guaranteed, the basic reliability of the system is greatly reduced.
Disclosure of Invention
The invention aims to overcome the defects, simplify the power supply system of the airplane, improve the basic reliability of the power supply system and ensure the reliability of the power supply of the flight control system.
The airplane low-voltage direct-current power supply system for achieving the purpose comprises a permanent magnet synchronous generator 1, a three-phase bridge rectifier circuit 2, a wide voltage regulation range converter 3 and a controller 4; the permanent magnet synchronous generator 1 consists of a permanent magnet synchronous generator rotor 11 and a permanent magnet synchronous generator stator 12 and is used for converting mechanical energy extracted from an aircraft engine into three-phase alternating current electric energy; the three-phase bridge rectifier circuit 2 is used for converting three-phase alternating current output by the permanent magnet synchronous generator 1 and changing along with the rotating speed of an aircraft engine into direct current; the wide voltage regulation range converter 3 consists of an inductor L, a capacitor C, a diode D and a power switch tube VT, the input end of the wide voltage regulation range converter 3 is connected with the output end of the three-phase bridge rectifier circuit 2, and the output end of the wide voltage regulation range converter 3 is the output end of the airplane low-voltage direct-current power supply system; the controller 4 is a voltage feedback type controller and consists of a detection circuit, a reference voltage, a comparison circuit, a triangular wave generator, a PWM modulator and a driving circuit, the input end of the controller 4 is connected with the output end of the wide voltage regulation range converter 3, and the output end of the controller 4 is connected with the base electrode of a power switching tube VT in the wide voltage regulation range converter 3; the controller 4 regulates the duty ratio of the power switching tube VT by controlling the on-off time of the power switching tube VT in the wide voltage regulation range converter 3, so that the output voltage of the airplane low-voltage direct-current power supply system does not change along with the change of the rotating speed of the permanent magnet synchronous generator 1.
The wide voltage regulation range converter 3 adopts a Boost-buck, Cuk, Sepic or Zeta chopper circuit.
The permanent magnet synchronous generator 1 is characterized in that a permanent magnet synchronous generator stator 12 adopts a multi-winding structure, and the number of the three-phase bridge rectifier circuit 2, the wide voltage regulation range converter 3 and the controller 4 is equal to the number of windings on the permanent magnet synchronous generator stator 12 and corresponds to the number of windings on the permanent magnet synchronous generator stator.
Compared with the prior art, the airplane low-voltage direct-current power supply system adopting the structure has the advantages that the adaptable engine rotating speed range is large, even if the airplane engine stops in the air and is in the windmill rotating speed, the power supply system can still output multiple paths of electric energy which are mutually independent and meet the power utilization requirement, and the reliability of power supply or emergency power supply of a flight control system is greatly improved.
Drawings
Fig. 1 is a schematic structural diagram of a low-voltage direct-current power supply system of an airplane.
Fig. 2 is a schematic circuit diagram of a permanent magnet synchronous generator in the low-voltage direct-current power supply system of the airplane.
Fig. 3(a), (b), (c) and (d) are schematic circuit diagrams of a three-phase bridge rectifier circuit and a wide voltage regulation range converter in the low-voltage direct-current power supply system of the airplane.
Fig. 4 is a functional block diagram of a controller.
Detailed Description
The aircraft low-voltage direct-current power supply system of the invention is further described in detail with reference to the accompanying drawings.
The symbol names and meanings in the drawings are as follows:
n, S-N, S poles of permanent magnet synchronous generator rotor;
Wa、Wb、Wc-a three-phase winding on the stator of the permanent magnet synchronous generator;
ua、ub、uc-the three-phase windings of the permanent magnet synchronous generator output phase voltages;
D1、D2、...、D7-a rectifier diode;
VT-power switching tube;
l, C-Filter inductance, capacitance;
ud-an output voltage of a three-phase bridge rectifier circuit;
uL-filtering the voltage across the inductor;
uo-the output dc voltage of the aircraft low voltage dc power supply system of the invention;
PWM-pulse width modulation.
As shown in fig. 1, the low-voltage dc power supply system of the present invention comprises a permanent magnet synchronous generator 1, a three-phase bridge rectifier circuit 2, a wide voltage regulation range converter 3 and a controller 4; wherein, the permanent magnet synchronous generator 1 consists of a permanent magnet synchronous generator rotor 11And a permanent magnet synchronous generator stator 12 for converting mechanical energy extracted from the aircraft engine into three-phase ac electrical energy; the three-phase bridge rectifier circuit 2 is used for converting three-phase alternating current output by the permanent magnet synchronous generator 1 and changing with the rotating speed of the aircraft engine into direct current, and the three-phase input end U of the three-phase bridge rectifier circuit 2a、Ub、UcThree-phase output end U connected with permanent magnet synchronous generator stator 12a、Ub、Uc(ii) a The wide voltage regulation range converter 3 is composed of an inductor L, a capacitor C, a diode D and a power switch tube VT, as shown in fig. 3(a), (b), (C) and (D), the input end of the wide voltage regulation range converter 3 is connected with the output end U of the three-phase bridge rectifier circuit 2dThe output end of the wide voltage regulation range converter 3 is the output end U of the low-voltage direct-current power supply system of the airplaneo(ii) a The controller 4 is a voltage feedback type controller and consists of a detection circuit, a reference voltage, a comparison circuit, a triangular wave generator, a PWM modulator and a driving circuit, the input end of the controller 4 is connected with the output end UO of the wide voltage regulation range converter 3, and the output end of the controller 4 is connected with the base electrode of a power switching tube VT in the wide voltage regulation range converter 3; the controller 4 regulates the duty ratio of the power switching tube VT by controlling the on-off time of the power switching tube VT in the wide voltage regulation range converter 3, so that the output voltage Uo of the airplane low-voltage direct-current power supply system does not change along with the change of the rotating speed of the permanent magnet synchronous generator 1.
The wide voltage control range converter 3 may employ a Boost-buck, Cuk, Sepic, or Zeta chopper circuit, as shown in fig. 3(a), (b), (c), and (d), respectively.
In order to further improve the overall reliability of the system and simplify the structure, the stator 12 of the permanent magnet synchronous generator 1 can adopt a multi-winding structure, the windings are independent, and the number of the three-phase bridge rectifier circuit 2, the wide voltage regulation range converter 3 and the controller 4 is equal to the number of the windings on the stator 12 of the permanent magnet synchronous generator and corresponds to one another, as shown in fig. 1 and fig. 2; therefore, the output voltage of the airplane low-voltage direct-current power supply system can be ensuredUoThe permanent magnet synchronous generator 1 does not change along with the change of the rotating speed of the permanent magnet synchronous generator, can obtain 28.5V direct current even if an aircraft engine is in a windmill state (low-speed rotation), and simultaneously obtains multi-path low-voltage direct current output (28.5V) by a simpler structure, thereby further improving the reliability of an aircraft low-voltage direct current power supply system.
Output voltage U of wide voltage regulation range converter 30With three-phase rectified voltage U at its inputdThe relation of (A) is as follows:
wherein,is the duty cycle. The controller 4 adjusts the on-off time of the power switch tube VT in the wide voltage regulation range converter 3, namely the duty ratio D, then the output voltage U0Can be compared with rectified voltage UdHigh, also can be higher than UdLow; when the rotating speed of the engine is higher, the rotating speed of a permanent magnet synchronous generator rotor 11 of the driven permanent magnet synchronous generator 1 is also higher, and D is more than 0 and less than 0.5, the wide voltage regulation range converter 3 is regulated to be voltage reduction conversion; when the engine speed is low, even in a windmill state, the speed of the rotor 11 of the permanent magnet synchronous generator 1 is low, and when D is more than 0.5 and less than 1, the wide voltage regulation range converter 3 is regulated to be boost conversion.
The airplane low-voltage direct-current power supply system for achieving the purpose has the advantages of simple system structure, high reliability, wide rotating speed range and the like. The method is not only suitable for the normal working rotating speed range of the generator (corresponding to the range from slow running to maximum rotating speed of the aircraft engine), but also suitable for the emergency working state of the aircraft engine when the aircraft engine is in the extremely low rotating speed of the generator under the rotating speed of the windmill, and greatly improves the power supply reliability of the flight control system.
Claims (6)
1. A low-voltage direct-current power supply system of an airplane comprises a permanent magnet synchronous generator [1] and a three-phase bridge rectifier circuit [2], wherein the permanent magnet synchronous generator [1] comprises a permanent magnet synchronous generator rotor [11] and a permanent magnet synchronous generator stator [12] and is used for converting mechanical energy extracted from an engine of the airplane into three-phase alternating-current electric energy; the airplane low-voltage direct-current power supply system is characterized by further comprising a wide voltage regulation range converter [3] and a controller [4], wherein the wide voltage regulation range converter [3] consists of an inductor L, a capacitor C, a diode D and a power switch tube VT, the input end of the wide voltage regulation range converter [3] is connected with the output end of the three-phase bridge rectifier circuit [2], and the output end of the wide voltage regulation range converter [3] is the output end of the airplane low-voltage direct-current power supply system; the controller [4] is a voltage feedback type controller and consists of a detection circuit, a reference voltage, a comparison circuit, a triangular wave generator, a PWM modulator and a driving circuit, wherein the input end of the controller [4] is connected with the output end of the wide voltage regulation range converter [3], and the output end of the controller [4] is connected with the base electrode of a power switching tube VT in the wide voltage regulation range converter [3 ]; the controller [4] regulates the duty ratio of the power switching tube VT by controlling the on-off time of the power switching tube VT in the wide voltage regulation range converter [3] so as to ensure that the output voltage of the airplane low-voltage direct current power supply system does not change along with the change of the rotating speed of the permanent magnet synchronous generator [1 ].
2. The aircraft low-voltage direct-current power supply system according to claim 1, wherein the wide-voltage regulation range converter [3] adopts a Boost-buck chopper circuit composed of an inductor L, a capacitor C, a diode D and a power switch tube VT.
3. The aircraft low-voltage direct-current power supply system according to claim 1, wherein the wide-voltage regulation range converter [3] adopts a Cuk chopper circuit composed of an inductor L, a capacitor C, a diode D and a power switch tube VT.
4. The aircraft low-voltage direct-current power supply system according to claim 1, wherein the wide-voltage regulation range converter [3] adopts a Sepic chopper circuit composed of an inductor L, a capacitor C, a diode D and a power switch tube VT.
5. The aircraft low-voltage direct-current power supply system according to claim 1, wherein the wide-voltage regulation range converter [3] adopts a Zeta chopper circuit composed of an inductor L, a capacitor C, a diode D and a power switch tube VT.
6. The aircraft low-voltage direct-current power supply system according to claim 1, 2, 3, 4 or 5, wherein a permanent magnet synchronous generator stator [12] in the permanent magnet synchronous generator [1] adopts a multi-winding structure, and the number of the three-phase bridge rectifier circuit [2], the wide voltage regulation range converter [3] and the controller [4] is equal to and corresponds to the number of windings on the permanent magnet synchronous generator stator [12 ].
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107211575B true CN107211575B (en) | 2006-04-26 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108134440A (en) * | 2017-12-28 | 2018-06-08 | 广州市风力新能源科技有限公司 | A kind of high power wind-mill generating equipment |
| CN108288853A (en) * | 2018-04-04 | 2018-07-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aircraft DC power supply system and method for supplying power to |
| CN110391758A (en) * | 2019-07-23 | 2019-10-29 | 无锡芯朋微电子股份有限公司 | Multiple Output Power System |
| CN111181454A (en) * | 2019-12-05 | 2020-05-19 | 陕西航空电气有限责任公司 | Wide output range's frequency conversion alternator controller power supply circuit |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108134440A (en) * | 2017-12-28 | 2018-06-08 | 广州市风力新能源科技有限公司 | A kind of high power wind-mill generating equipment |
| CN108288853A (en) * | 2018-04-04 | 2018-07-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aircraft DC power supply system and method for supplying power to |
| CN108288853B (en) * | 2018-04-04 | 2024-05-28 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aircraft DC power supply system and power supply method |
| CN110391758A (en) * | 2019-07-23 | 2019-10-29 | 无锡芯朋微电子股份有限公司 | Multiple Output Power System |
| CN111181454A (en) * | 2019-12-05 | 2020-05-19 | 陕西航空电气有限责任公司 | Wide output range's frequency conversion alternator controller power supply circuit |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR03 | Grant of secret patent right | ||
| DC01 | Secret patent status has been lifted | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20060426 Termination date: 20180118 |