Aircraft energy rapid storage method based on storage battery and supercapacitor

Abstract

The invention belongs to the technical field of energy generation in the field of aircraft energy and heat, and particularly relates to an aircraft energy rapid storage method based on a storage battery and a supercapacitor, the energy demand of a more electric aircraft is divided into a rapid response demand and a slow response demand, and when it is judged that the energy demand is the rapid response demand, the supercapacitor is used for discharging to provide electric energy; and when the slow response demand is judged, the storage battery is used for providing electric energy. Rapid storage and efficient utilization of energy are realized; by utilizing the combination of the super capacitor and the storage battery, the power density and the energy density of energy storage are improved, the charging time is shortened, and the energy consumption is reduced; the super capacitor is charged through the surplus power generated by the airborne generator, so that the charging efficiency is improved; and the output voltage is stabilized in a voltage range required by the more-electric aircraft through the power electronic converter, so that the quality and the stability of the electric energy are ensured.

Description

Technical Field

[0001] This application belongs to the technical field of energy generation in the field of aircraft energy, and particularly relates to a method for rapid energy storage of an aircraft based on a battery and a supercapacitor. Background Art

[0002] With the development of technology, more-electric aircraft have gradually become a research hotspot in the aviation field. More-electric aircraft adopt advanced power electronics technology and store energy through batteries and supercapacitors to improve flight efficiency and energy-saving effects. However, traditional energy storage methods have problems such as slow charging speed and low energy density, making it difficult to meet the requirements of more-electric aircraft. Therefore, it is necessary to develop a rapid energy storage method based on batteries and supercapacitors to achieve rapid storage of aircraft energy. Summary of the Invention

[0003] The purpose of this application is to provide a method for rapid energy storage of an aircraft based on a battery and a supercapacitor to solve the problems of slow charging speed and low energy density in energy storage through batteries and supercapacitors in the prior art.

[0004] The technical solution of this application is: A method for rapid energy storage of an aircraft based on a battery and a supercapacitor, including:

[0005] Dividing the energy requirements of the more-electric aircraft into fast-response requirements and slow-response requirements;

[0006] Connecting both the battery and the supercapacitor to the power supply system of the more-electric aircraft; before use, both the battery and the supercapacitor store a certain amount of electrical energy; setting up a charging control unit, the charging control unit collects current working condition data and identifies fast-response requirements and slow-response requirements. When it is determined that it is a fast-response requirement, obtain the working voltage of the current supercapacitor and determine whether the current working voltage is the normal working voltage. If so, connect the supercapacitor to the power supply system of the more-electric aircraft and use the supercapacitor to discharge and provide electrical energy;

[0007] When it is determined that it is a slow-response requirement, obtain the floating charge voltage and discharge cut-off voltage of the current battery, and determine whether the floating charge voltage and the discharge cut-off voltage are in a normal working state. If so, control the battery to be connected to the power supply system; use the battery to provide electrical energy;

[0008] The charging control unit continuously obtains the working parameters of the on-board generator and calculates the current working power and surplus power of the on-board generator. When the supercapacitor is charging, control the on-board generator to work at the rated power and use the surplus power generated by the on-board generator to charge the supercapacitor;

[0009] When the storage battery is charged, its output voltage is stabilized within the voltage range set for the multi - electric aircraft through a power electronic converter, and then the storage battery is charged.

[0010] Preferably, the charging control unit includes a working parameter processing module, a connection control module, and a charge - discharge control module. The working parameter processing module is used to obtain the demand type of the aircraft, and then obtain the working parameters of the storage battery or the supercapacitor according to the corresponding demand type to judge the working state; the connection control module is used to perform connection or disconnection control according to the current working state of the storage battery or the supercapacitor; the charge - discharge control module is used to perform charge - discharge control according to the current working state and power level of the storage battery or the supercapacitor.

[0011] Preferably, temperature sensors are arranged on the outer sides of both the storage battery and the supercapacitor. The temperature sensors collect the temperature signals of the storage battery and the supercapacitor in real - time and send them to the working parameter processing module. In the working parameter processing module, the temperature signals are compared with the standard temperature value to judge whether the storage battery and the supercapacitor are over - temperature;

[0012] Meanwhile, a liquid - cooling module is arranged on the outer side of the storage battery, and electrode plates are arranged on the outer side of the supercapacitor. When the storage battery or the supercapacitor is over - temperature, the storage battery dissipates heat through the liquid - cooling module, and the supercapacitor first reduces power or stops power supply, and then dissipates heat through the electrode plates.

[0013] Preferably, discharge circuits and boost circuits are arranged on both the storage battery and the supercapacitor; when the working parameter processing module judges that the voltage on the storage battery or the supercapacitor is higher than the normal working voltage, it controls the discharge circuit to work for discharging; when it judges that the voltage on the storage battery or the supercapacitor is lower than the normal working voltage, it controls the boost circuit to work for boosting until the normal working voltage is reached.

[0014] Preferably, the discharge circuit adopts a PWM chopper discharge circuit; the boost circuit adopts a matrix converter.

[0015] Preferably, power nodes sorted from low to high are arranged in the charge - discharge control module. When the surplus power generated by the airborne generator is between two adjacent power nodes, the supercapacitor is charged according to the power corresponding to the power node at the first level.

[0016] The aircraft energy rapid storage method based on a storage battery and a supercapacitor of the present application divides the energy requirements of a multi-electric aircraft into fast-response requirements and slow-response requirements, achieving rapid energy storage and efficient utilization; by using the combination of a supercapacitor and a storage battery, the power density and energy density of energy storage are improved, and the charging time and energy consumption are reduced; the surplus power generated by the on-board generator is used to charge the supercapacitor, improving the charging efficiency; the output voltage is stabilized within the voltage range required by the multi-electric aircraft through a power electronic converter, ensuring the quality and stability of the electric energy. Brief Description of the Drawings

[0017] To more clearly illustrate the technical solutions provided by the present application, the drawings will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application.

[0018] Figure 1 It is a flowchart of the overall design of the present application. Detailed Embodiments

[0019] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, rather than all of them. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0020] An aircraft energy rapid storage method based on a storage battery and a supercapacitor, as Figure 1 shown, includes the following steps:

[0021] Step S100, dividing the energy requirements of a multi-electric aircraft into fast-response requirements and slow-response requirements. Among them, the fast-response requirements include transient working conditions such as takeoff, climb, and rapid descent, and the slow-response requirements include steady-state working conditions such as cruise, level flight, and descent.

[0022] Step S200, connecting both the storage battery and the supercapacitor to the power supply system of the multi-electric aircraft; before use, both the storage battery and the supercapacitor store a certain amount of electric energy. A charging control unit is set up. The charging control unit collects the current working condition data and identifies the fast-response requirements and slow-response requirements. When it is determined that it is a fast-response requirement, the working voltage of the current supercapacitor is obtained, and it is judged whether the current working voltage is the normal working voltage. If so, the supercapacitor is connected to the power supply system of the multi-electric aircraft, and the supercapacitor is used to discharge and provide electric energy. The supercapacitor has the characteristics of high power density and fast charge and discharge, and can meet the energy requirements of the transient working conditions of the multi-electric aircraft. An overly high working voltage of the supercapacitor may cause gas evolution or liquid leakage.

[0023] Preferably, the charging control unit includes a working parameter processing module, a connection control module, and a charge and discharge control module. The working parameter processing module is used to obtain the demand type of the aircraft, and then obtain the working parameters of the battery or supercapacitor corresponding to the demand type to judge the working state; the connection control module is used to control connection or disconnection according to the current working state of the battery or supercapacitor; the charge and discharge control module is used to control charge and discharge according to the current working state and power level of the battery or supercapacitor.

[0024] Preferably, temperature sensors are provided on the outer sides of both the battery and the supercapacitor. The temperature sensors collect the temperature signals of the battery and the supercapacitor in real time and send them to the working parameter processing module. In the working parameter processing module, the temperature signals are compared with the standard temperature values to judge whether the battery and the supercapacitor are overheated.

[0025] Meanwhile, a liquid cooling module is provided on the outer side of the battery, and an electrode plate is provided on the outer side of the supercapacitor. When the battery or the supercapacitor is overheated, the battery dissipates heat through the liquid cooling module, and the supercapacitor first reduces power or stops power supply, and then dissipates heat through the electrode plate.

[0026] Preferably, discharge circuits and boost circuits are provided on both the battery and the supercapacitor; when the working parameter processing module determines that the voltage on the battery or the supercapacitor is higher than the normal working voltage, it controls the discharge circuit to work for discharging; when it determines that the voltage on the battery or the supercapacitor is lower than the normal working voltage, it controls the boost circuit to work for boosting until the normal working voltage is reached. Among them, the discharge circuit preferably adopts a PWM chopper discharge circuit; the boost circuit preferably adopts a matrix converter.

[0027] Step S300, when it is determined that it is a slow response demand, obtain the floating charge voltage and discharge cut-off voltage of the current battery, and judge whether the floating charge voltage and discharge cut-off voltage are in the normal working state. If so, control the battery to be connected to the power supply system; use the battery to provide electrical energy. The battery has the characteristics of high energy density and long-term power supply, and can meet the energy requirements of the multi-electric aircraft under steady-state conditions. Abnormal floating charge voltage and discharge cut-off voltage of the battery are likely to cause thermal runaway or deep discharge.

[0028] Step S400, the charging control unit obtains the working parameters of the airborne generator in real time, and calculates the working power and surplus power of the current airborne generator. When the supercapacitor is charged, control the airborne generator to work at the rated power, and use the surplus power generated by the airborne generator to charge the supercapacitor. At this time, the battery is in a dormant state and does not participate in the charging process to extend its service life.

[0029] When the supercapacitor discharges, its output voltage is stabilized within the voltage range required by the more-electric aircraft through a power electronic converter. Meanwhile, the supercapacitor is charged to keep it in a fully charged state and ready for the next discharge.

[0030] Preferably, power nodes sorted from low to high are provided in the charge and discharge control module. When the surplus power generated by the airborne generator is between two adjacent power nodes, the supercapacitor is charged according to the power corresponding to the power node of the first level to ensure the stability of the supercapacitor.

[0031] Step S500, when the battery is charged, its output voltage is stabilized within the voltage range set for the more-electric aircraft through a power electronic converter, and then the battery is charged to keep it in a fully charged state and ready for the next discharge.

[0032] In summary, by dividing the energy requirements of the more-electric aircraft into fast-response requirements and slow-response requirements, the present application realizes the rapid storage and efficient utilization of energy; by using the combination of a supercapacitor and a battery, the power density and energy density of energy storage are improved, and the charging time and energy consumption are reduced; by charging the supercapacitor with the surplus power generated by the airborne generator, the charging efficiency is improved; by stabilizing the output voltage within the voltage range required by the more-electric aircraft through a power electronic converter, the quality and stability of the electric energy are ensured.

[0033] Finally, it should be noted that: in the drawings of the disclosed embodiments of the present invention, only the structures related to the disclosed embodiments are involved. For other structures, reference may be made to the general design. Without conflict, the same embodiment and different embodiments of the present invention can be combined with each other;

[0034] Finally: The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for rapid storage of aircraft energy based on batteries and supercapacitors, characterized in that: include: The energy demand of more electric aircraft is divided into fast response demand and slow response demand; The storage battery and the supercapacitor are connected to the power supply system of the more-electric aircraft; before use, the storage battery and the supercapacitor both store a certain amount of electrical energy; A charging control unit is provided, which collects current working condition data and identifies fast response requirements and slow response requirements. When a fast response requirement is determined, the current working voltage of the supercapacitor is obtained, and it is determined whether the current working voltage is a normal working voltage. If so, the supercapacitor is connected to the power supply system of the multi-electric aircraft, and the supercapacitor is discharged to provide electrical energy; When it is determined that the demand is slow response, the floating charge voltage and discharge cut-off voltage of the current battery are obtained, and it is determined whether the floating charge voltage and the discharge cut-off voltage are in a normal working state. If so, the battery is controlled to be connected to the power supply system; the battery is used to provide power; The charging control unit obtains the working parameters of the onboard generator in real time, and calculates the current working power and surplus power of the onboard generator. When the supercapacitor is charging, the onboard generator is controlled to operate at the rated power, and the surplus power generated by the onboard generator is used to charge the supercapacitor; when the battery is charging, its output voltage is stabilized within the voltage range set by the multi-electric aircraft through the power electronic converter, and then the battery is charged.

2. The method for rapid aircraft energy storage based on batteries and supercapacitors as claimed in claim 1, characterized in that: The charging control unit includes a working parameter processing module, a connection control module and a charge and discharge control module. The working parameter processing module is used to obtain the demand type of the aircraft, and then obtain the working parameters of the battery or supercapacitor corresponding to the demand type to judge the working state; the connection control module is used to perform connection or disconnection control according to the current working state of the battery or supercapacitor; the charge and discharge control module is used to perform charge and discharge control according to the current working state and power status of the battery or supercapacitor.

3. The method for rapid aircraft energy storage based on batteries and supercapacitors as claimed in claim 2, characterized in that: The battery and the supercapacitor are both provided with temperature sensors on the outside, the temperature sensors collect temperature signals of the battery and the supercapacitor in real time and send them to the working parameter processing module, the temperature signals are compared with the standard temperature value in the working parameter processing module, and it is determined whether the battery and the supercapacitor are over-temperature; At the same time, a liquid cooling module is arranged on the outside of the battery, and an electrode sheet is arranged on the outside of the supercapacitor. When the battery or the supercapacitor is overheated, the battery dissipates heat through the liquid cooling module, and the supercapacitor first reduces power or stops supplying power, and then dissipates heat through the electrode sheet.

4. The method for rapid aircraft energy storage based on batteries and supercapacitors as claimed in claim 2, characterized in that: The battery and the supercapacitor are both provided with a discharge circuit and a boost circuit; when the working parameter processing module determines that the voltage on the battery or the supercapacitor is higher than the normal working voltage, the discharge circuit is controlled to discharge; when it is determined that the voltage on the battery or the supercapacitor is lower than the normal working voltage, the boost circuit is controlled to boost the voltage until the normal working voltage is reached.

5. The method for rapid aircraft energy storage based on batteries and supercapacitors as claimed in claim 2, characterized in that: The discharge circuit adopts a PWM chopping discharge circuit; the boost circuit adopts a matrix converter.

6. The method for rapid aircraft energy storage based on batteries and supercapacitors as claimed in claim 2, characterized in that: The charge and discharge control module is provided with power nodes arranged in ascending order. When the surplus power generated by the onboard generator is between two adjacent power nodes, the supercapacitor is charged according to the power corresponding to the power node of the first level.

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