CN112477608A - Energy feedback device for aviation electric drive system and control method - Google Patents
Energy feedback device for aviation electric drive system and control method Download PDFInfo
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- CN112477608A CN112477608A CN202011512496.2A CN202011512496A CN112477608A CN 112477608 A CN112477608 A CN 112477608A CN 202011512496 A CN202011512496 A CN 202011512496A CN 112477608 A CN112477608 A CN 112477608A
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- 238000000034 method Methods 0.000 title claims description 17
- 238000004146 energy storage Methods 0.000 claims abstract description 55
- 230000002457 bidirectional effect Effects 0.000 claims abstract description 41
- 238000007599 discharging Methods 0.000 claims abstract description 14
- 238000005070 sampling Methods 0.000 claims abstract description 12
- 238000007600 charging Methods 0.000 claims abstract description 11
- 238000012546 transfer Methods 0.000 claims abstract description 6
- 238000006243 chemical reaction Methods 0.000 claims abstract description 4
- 230000008569 process Effects 0.000 claims description 9
- 238000005265 energy consumption Methods 0.000 claims description 4
- 230000000630 rising effect Effects 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims 1
- 238000010248 power generation Methods 0.000 abstract description 3
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 238000010277 constant-current charging Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L7/00—Electrodynamic brake systems for vehicles in general
- B60L7/10—Dynamic electric regenerative braking
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L7/00—Electrodynamic brake systems for vehicles in general
- B60L7/10—Dynamic electric regenerative braking
- B60L7/16—Dynamic electric regenerative braking for vehicles comprising converters between the power source and the motor
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P27/00—Arrangements or methods for the control of AC motors characterised by the kind of supply voltage
- H02P27/04—Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage
- H02P27/06—Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage using dc to ac converters or inverters
- H02P27/08—Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage using dc to ac converters or inverters with pulse width modulation
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P29/00—Arrangements for regulating or controlling electric motors, appropriate for both AC and DC motors
- H02P29/02—Providing protection against overload without automatic interruption of supply
- H02P29/024—Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load
- H02P29/025—Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load the fault being a power interruption
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L2200/00—Type of vehicles
- B60L2200/10—Air crafts
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/64—Electric machine technologies in electromobility
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/72—Electric energy management in electromobility
Abstract
The invention provides an energy feedback device for an aviation electric drive system, which comprises an energy storage unit, a bidirectional DC/DC converter, a signal sampling circuit, a PWM logic control circuit and a drive circuit, wherein the energy storage unit is connected with the bidirectional DC/DC converter; the energy storage unit is used for storing feedback energy of the aviation electric drive system; the bidirectional DC/DC converter realizes energy transfer between the energy storage unit and the aviation electric drive system; the signal sampling circuit collects bus voltage, energy storage unit terminal voltage and energy storage unit charging and discharging current of the aviation electric drive system; the PWM logic control circuit generates a PWM control signal for controlling the bidirectional DC/DC conversion circuit according to the sampling result; the drive circuit converts the control signal into a drive signal for the bidirectional DC/DC converter. The invention stores the feedback electric energy generated when the electric drive system operates in a braking power generation state into the energy storage device; and when the electric drive system operates in an electric state, the motor accelerates or the direct current power supply is suddenly cut off, the energy in the energy storage device is returned to the electric drive system, so that the energy is recycled and reused, and the electric energy utilization rate is improved.
Description
Technical Field
The invention belongs to the field of aviation electrical systems, and relates to an energy feedback device and a control method suitable for an aviation actuating electric drive system.
Background
With the development of multi-electric and full-electric technology, some aviation equipment is gradually transited from hydraulic and pneumatic driving to electric driving, such as various actuators, reverse thrust devices of engines and other actuating equipment. Aviation actuating equipment has short-term, powerful load characteristic, and some special operating modes still require the electric drive system to operate in the four quadrants, can produce the repayment electric energy when the electric drive system operation is in braking power generation state, produce the impact to the electric wire netting. In order to realize four-quadrant operation of an electric drive system and reduce the influence of energy feedback on a power grid, at present, an energy consumption braking mode is mainly adopted to consume feedback energy, namely, electric energy is completely consumed in a high-power resistor through a method of internally or externally adding a braking resistor, the mode can increase the heat productivity of the electric drive system, so that the space and the heat dissipation noise of heat dissipation equipment of the electric drive system are increased, the feedback electric quantity cannot be reused, and the electric energy utilization rate is low.
Disclosure of Invention
In order to improve the efficiency of an airborne electric drive system, maximize the energy utilization efficiency and reduce the influence of the operation process of the electric drive system on the stability of a power grid, the invention provides an energy feedback device for the airborne electric drive system and a control method.
The technical scheme of the invention is as follows:
the energy feedback device for the aviation electric drive system comprises an energy storage unit, a bidirectional DC/DC converter, a signal sampling circuit, a PWM logic control circuit and a drive circuit;
the energy storage unit is used for storing feedback energy of the aviation electric drive system;
the bidirectional DC/DC converter realizes energy transfer between the energy storage unit and the aviation electric drive system;
the signal sampling circuit collects bus voltage, energy storage unit terminal voltage and energy storage unit charging and discharging current of the aviation electric drive system;
the PWM logic control circuit generates a PWM control signal for controlling the bidirectional DC/DC conversion circuit according to the sampling result;
the driving circuit converts the control signals output by the PWM logic control circuit into driving signals of two switching tubes in the bidirectional DC/DC converter and outputs the driving signals to the bidirectional DC/DC converter.
Further, the bidirectional DC/DC converter adopts a non-isolated two-phase DC/DC converter circuit.
Furthermore, the two control signals PWMA and PWMB generated by the PWM logic control circuit are two mutually non-parallel control signals, wherein the two-way DC/DC converter works in a Buck circuit mode through the PWMA signal to charge the energy storage unit at constant current; the PWMB signal causes the bi-directional DC/DC converter to operate in BOOST circuit mode, discharging energy from the energy storage unit to smooth the bus voltage of the avionic electric drive system.
The specific control method comprises the following steps:
the energy feedback device is hung on a direct current bus of the aviation electric drive system;
when the aviation electric drive system is electrified and works, an onboard direct current power supply is loaded to the end of the direct current bus P, N and an energy storage unit of the energy feedback device is pre-charged: when the voltage at the end of the energy storage unit is lower than the preset value UCLWhen the bidirectional DC/DC converter works in a Buck circuit mode, the PWM logic control circuit generates a control signal and outputs a PWMA signal after passing through the driving circuit, and the bidirectional DC/DC converter charges the energy storage unit at a constant current; until the voltage at the energy storage unit is charged to a preset value UCLWhen the pre-charging process is finished, the two switching tubes Q1 and Q2 of the bidirectional DC/DC converter are turned off, and the energy feedback device is in a standby state;
when the load end of the whole system is loaded or suddenly accelerated during the operation of the avionic drive system, the bus voltage U at the end P, N is causedPNWhen fluctuation occurs, if the bus voltage U is detectedPNFalls to a lower threshold value ULThe PWM logic control circuit generates control signals to drive the motorThe post-circuit outputs PWMB signal, the bidirectional DC/DC converter works in a BOOST circuit mode, the energy of the energy storage unit is released to smooth P, N bus terminal voltage, and when the bus voltage U isPNHigher than rated value UdWhen the energy feedback device is in a standby state, discharging is stopped, the Q1 and the Q2 are turned off, and the energy feedback device returns to the standby state;
when the motor at the load end of the aviation electric drive system runs from high speed to emergency stop or runs in a braking state, energy is fed back to the bus to cause P, N end bus voltage UPNSudden rising; if the bus voltage U is detectedPNUp to the upper threshold value UHWhen the bus voltage U is detected, the PWM logic control circuit outputs a PWMA signal to enable the bidirectional DC/DC converter to work in a Buck mode to charge and store energy for the energy storage unit, and when the bus voltage U is detectedPNBelow rated value UdWhen the energy feedback device is in a standby state, discharging is stopped, the Q1 and the Q2 are turned off, and the energy feedback device returns to the standby state; in the process of charging and storing energy for the energy storage unit, if the feedback energy is larger, the voltage at the end of the energy storage unit is higher than the upper limit threshold value UCHWhen the motor driving system is in a standby state, the Q1 and the Q2 are also turned off, the energy feedback device returns to the standby state, and the residual energy fed back by the motor driving system is consumed by the energy consumption resistor of the motor driving system.
Advantageous effects
The energy feedback device for the aviation electric drive system can store the feedback electric energy generated when the electric drive system operates in a braking power generation state into the energy storage equipment, so that the influence of the feedback electric energy on a power grid is reduced, and the quality of a power supply is improved; and when the electric drive system operates in an electric state, the motor accelerates or the direct current power supply is suddenly cut off, the energy in the energy storage device is returned to the electric drive system, so that the energy is recycled and reused, and the electric energy utilization rate is improved. Meanwhile, the heat productivity of the electric drive system is greatly reduced, the space of cooling equipment is saved, the cost is saved, the noise is reduced, and a technical basis and a research basis are provided for the research of the all-electric airplane which is more environment-friendly in the future.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1: energy feedback device structure diagram;
FIG. 2: energy is repayed motor drive system.
Detailed Description
The following detailed description of embodiments of the invention, examples of which are intended to be illustrative, is not to be construed as limiting the invention.
The invention aims to improve the efficiency of an airborne electric drive system, maximize the energy utilization efficiency and simultaneously reduce the influence on the stability of a power grid in the operation process of the electric drive system. As shown in fig. 1, the energy feedback device for an avionic electric drive system mainly comprises an energy storage unit, a bidirectional DC/DC converter, a signal sampling circuit, a PWM logic control circuit and a drive circuit.
The energy storage unit is used for storing feedback energy of the electric drive system; the bidirectional DC/DC converter adopts a non-isolated double-phase DC/DC converter circuit to realize energy transfer between the energy storage unit and the electric drive system; the signal sampling circuit collects bus voltage, energy storage unit terminal voltage and charging and discharging current through a sensor; the PWM logic control circuit generates a PWM control signal for controlling the bidirectional DC/DC conversion circuit according to the sampling result; the driving circuit converts the control signal output by the PWM logic control circuit into driving signals of two switching tubes in the bidirectional DC/DC converter and outputs the driving signals to the bidirectional DC/DC converter.
As shown in fig. 2, the energy feedback device is hung on a dc bus of the motor driving system, and the dc bus voltage U is applied during the operation of the motorPNCan be changed, and the energy feedback device can be charged and discharged in the dynamic process to maintain the bus voltage UPNIs relatively constant and at the same time functions as energy storage. The energy feedback device can also provide rated output voltage U when the on-machine direct-current power supply is suddenly cut offdAnd the power supply machine driving system continues to operate for a period of time, so that energy recovery and reutilization are realized. The energy feedback device can be cut off from the direct current bus at any time without influencing the original system.
The energy feedback device realizes energy transfer between the energy storage unit and the electric drive system through a bidirectional DC/DC converter, the converter can work in Buck and Boost modes, the working mode determines the flow direction of energy transfer, and the working mode is determined by the duty ratios of Q1 and Q2. The physical quantity required by the energy feedback device for controlling is bus voltage, the voltage of the energy storage unit and charging and discharging current of the energy storage unit (constant current charging is convenient), wherein voltage signals are collected through a voltage sensor, and the charging and discharging current is collected through a current sensor. The PWM logic control circuit carries out logic analysis on each collected physical quantity to generate a control signal, and outputs a corresponding PWM signal after passing through the driving circuit to control free switching of different working modes and realize bidirectional flow of energy.
The specific control method comprises the following steps:
when the power supply works, an onboard direct current power supply is loaded to the end of the direct current bus P, N, and an energy storage unit of the energy feedback device is pre-charged firstly: when the voltage at the end of the energy storage unit is lower than the preset value UCLWhen the bidirectional DC/DC converter is used, a PWM logic control circuit generates a control signal and outputs a PWMA signal after passing through a driving circuit, and the bidirectional DC/DC converter works in a Buck circuit mode consisting of Q1, D2, L1 and C2 and charges an energy storage unit at a constant current; PWMA and PWMB are mutually exclusive two-way control signals, and prevent Q1 and Q2 tubes from being directly connected until the end voltage of the energy storage unit is charged to a preset value UCLAnd when the pre-charging process is finished, the Q1 and the Q2 are turned off, and the energy feedback device is in a standby state.
During operation, when the load end of the whole system is loaded or suddenly accelerated, the bus voltage U at the end P, N is causedPNIf the system detects the bus voltage UPNFalls to a lower threshold value ULDuring the operation, the PWM logic control circuit generates a control signal and outputs a PWMB signal after passing through the driving circuit, the bidirectional DC/DC converter works in a BOOST circuit mode consisting of D1, Q2, L1 and C1, the energy of the energy storage unit is released to smooth the voltage of a P, N bus terminal,when the bus voltage UPNHigher than rated value UdWhen the discharging is stopped, the Q1 and the Q2 are turned off, and the energy feedback device returns to the standby state.
When the motor at the load end runs from high speed to emergency stop or runs in a braking state, energy is fed back to the bus to cause P, N-end bus voltage UPNSuddenly rising, if the system detects the bus voltage UPNUp to the upper threshold value UHWhen the bus voltage U is higher than the bus voltage U, the control circuit outputs a PWMA signal to enable the bidirectional DC/DC converter to work in a Buck mode to charge and store energy for the energy storage unit, and when the bus voltage U is higher than the bus voltage U, the control circuit outputs a PWMA signal to enable the bidirectional DC/DC converter to work in a BuPNBelow rated value UdWhen the discharging is stopped, the Q1 and the Q2 are turned off, and the energy feedback device returns to the standby state. In the process, if the feedback energy is larger, the voltage at the end of the energy storage unit is higher than the upper limit threshold value UCHWhen the motor driving system is in a standby state, the Q1 and the Q2 are also turned off, the energy feedback device returns to the standby state, and the residual energy fed back by the motor driving system is consumed by the energy consumption resistor of the motor driving system.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (4)
1. An energy feedback device for an aviation electric drive system is characterized in that: the bidirectional DC/DC converter comprises an energy storage unit, a bidirectional DC/DC converter, a signal sampling circuit, a PWM logic control circuit and a driving circuit;
the energy storage unit is used for storing feedback energy of the aviation electric drive system;
the bidirectional DC/DC converter realizes energy transfer between the energy storage unit and the aviation electric drive system;
the signal sampling circuit collects bus voltage, energy storage unit terminal voltage and energy storage unit charging and discharging current of the aviation electric drive system;
the PWM logic control circuit generates a PWM control signal for controlling the bidirectional DC/DC conversion circuit according to the sampling result;
the driving circuit converts the control signals output by the PWM logic control circuit into driving signals of two switching tubes in the bidirectional DC/DC converter and outputs the driving signals to the bidirectional DC/DC converter.
2. The energy feedback device for the avionic drive system according to claim 1, characterized in that: the bidirectional DC/DC converter adopts a non-isolated two-phase DC/DC converter circuit.
3. The energy feedback device for the avionic drive system according to claim 1, characterized in that: the PWM logic control circuit generates two PWMA and PWMB control signals which are mutually non-parallel, wherein the PWMA signal enables the bidirectional DC/DC converter to work in a Buck circuit mode to charge the energy storage unit at constant current; the PWMB signal causes the bi-directional DC/DC converter to operate in BOOST circuit mode, discharging energy from the energy storage unit to smooth the bus voltage of the avionic electric drive system.
4. The method for realizing energy feedback of the aeronautical electric drive system by using the energy feedback device in claim 1 is characterized in that:
the energy feedback device is hung on a direct current bus of the aviation electric drive system;
when the aviation electric drive system is electrified and works, an onboard direct current power supply is loaded to the end of the direct current bus P, N and an energy storage unit of the energy feedback device is pre-charged: when the voltage at the end of the energy storage unit is lower than the preset value UCLWhen the bidirectional DC/DC converter works in a Buck circuit mode, the PWM logic control circuit generates a control signal and outputs a PWMA signal after passing through the driving circuit, and the bidirectional DC/DC converter charges the energy storage unit at a constant current; until the voltage at the energy storage unit is charged to a preset value UCLWhen the pre-charging process is finished, the two switching tubes Q1 and Q2 of the bidirectional DC/DC converter are turned off, and the energy feedback device is in a standby state;
when the load end of the whole system is loaded or suddenly accelerated during the operation of the avionic drive system, the bus voltage U at the end P, N is causedPNWhen fluctuation occurs, if the detection is successfulMeasuring bus voltage UPNFalls to a lower threshold value ULWhen the bus voltage U is equal to the bus voltage U, the PWM logic control circuit generates a control signal and outputs a PWMB signal after passing through the driving circuit, the bidirectional DC/DC converter works in a BOOST circuit mode, the energy of the energy storage unit is released to smooth the voltage of the P, N bus terminalPNHigher than rated value UdWhen the energy feedback device is in a standby state, discharging is stopped, the Q1 and the Q2 are turned off, and the energy feedback device returns to the standby state;
when the motor at the load end of the aviation electric drive system runs from high speed to emergency stop or runs in a braking state, energy is fed back to the bus to cause P, N end bus voltage UPNSudden rising; if the bus voltage U is detectedPNUp to the upper threshold value UHWhen the bus voltage U is detected, the PWM logic control circuit outputs a PWMA signal to enable the bidirectional DC/DC converter to work in a Buck mode to charge and store energy for the energy storage unit, and when the bus voltage U is detectedPNBelow rated value UdWhen the energy feedback device is in a standby state, discharging is stopped, the Q1 and the Q2 are turned off, and the energy feedback device returns to the standby state; in the process of charging and storing energy for the energy storage unit, if the feedback energy is larger, the voltage at the end of the energy storage unit is higher than the upper limit threshold value UCHWhen the motor driving system is in a standby state, the Q1 and the Q2 are also turned off, the energy feedback device returns to the standby state, and the residual energy fed back by the motor driving system is consumed by the energy consumption resistor of the motor driving system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011512496.2A CN112477608A (en) | 2020-12-19 | 2020-12-19 | Energy feedback device for aviation electric drive system and control method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011512496.2A CN112477608A (en) | 2020-12-19 | 2020-12-19 | Energy feedback device for aviation electric drive system and control method |
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| CN112477608A true CN112477608A (en) | 2021-03-12 |
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| CN202011512496.2A Pending CN112477608A (en) | 2020-12-19 | 2020-12-19 | Energy feedback device for aviation electric drive system and control method |
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| CN106276445A (en) * | 2016-09-23 | 2017-01-04 | 南京理工大学 | A kind of elevator drives control, energy saving integrated system and method |
| CN111384767A (en) * | 2019-11-29 | 2020-07-07 | 国网江苏省电力有限公司 | Energy management strategy of aviation power supply system based on super-capacitor energy storage |
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2020
- 2020-12-19 CN CN202011512496.2A patent/CN112477608A/en active Pending
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|---|---|---|---|---|
| US20050224642A1 (en) * | 2003-12-15 | 2005-10-13 | Sullivan Steven L | Landing gear method and apparatus for braking and maneuvering |
| CN1835329A (en) * | 2006-04-10 | 2006-09-20 | 中国科学院电工研究所 | Hybrid accumulator for elevator and control method thereof |
| KR101191244B1 (en) * | 2012-01-05 | 2012-10-18 | 주식회사 우진산전 | Power storage apparatus of city railway with a both direction dc/dc converter |
| CN202474879U (en) * | 2012-03-26 | 2012-10-03 | 上海理工大学 | DC (direct current) bus ternary Buck-Boost two-way DC-DC voltage-stabilizing energy storage system |
| CN103847959A (en) * | 2014-03-22 | 2014-06-11 | 中国科学院电工研究所 | Aircraft braking energy recovery system based on flywheel energy storage |
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Application publication date: 20210312 |