An electric aircraft battery management control system and control method

Abstract

The present invention discloses a battery management control system and a control method for an electric aircraft. The battery management control system includes an onboard battery management module and an underground battery management module; the onboard battery management module includes a working current sensor, a working voltage sensor, a working temperature sensor, an energy recovery monitoring module and a battery power monitoring module; the underground battery management module includes a charging current sensor, a charging voltage sensor, a charging temperature sensor, and a charging power monitoring module; the onboard battery management module and the underground battery management module are both electrically connected to an aircraft battery management controller. The control method includes steps S1-S10. The present invention can obtain battery fault information most accurately, can realize parallel analysis and optimization, and has good global evaluation performance, thereby improving the reliability of the entire evaluation process.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation flight management, and in particular to a battery management control system and a control method for an electric aircraft. Background Art

[0002] Electric aircraft refers to aircraft that are powered by electric motors rather than internal combustion engines. The power sources include fuel cells, solar cells, supercapacitors, wireless energy transmission or other types of batteries. The manned electric aircraft that have been successfully developed mainly include solar aircraft, battery electric aircraft and fuel cell aircraft.

[0003] The battery of an electric aircraft is the key to the flight process. The battery life and capacity are both key factors affecting the distance that an electric aircraft can perform its flight mission. With the development of intelligent aircraft management systems, intelligent management of the batteries of electric aircraft is the key to reducing flight accidents and improving the flight efficiency of electric aircraft. Summary of the invention

[0004] In view of the above-mentioned deficiencies in the prior art, the present invention provides an electric aircraft battery management control system and a control method for comprehensively evaluating the battery life of the electric aircraft from a multi-parameter perspective.

[0005] In order to achieve the above-mentioned object of the invention, the technical solution adopted by the present invention is:

[0006] Provided is an electric aircraft battery management control system, which includes an onboard battery management module and an underground battery management module;

[0007] The onboard battery management module includes a working current sensor, a working voltage sensor, a working temperature sensor, an energy recovery monitoring module and a battery power monitoring module; the working current sensor and the working voltage sensor respectively collect the output current and output voltage of the onboard battery, the working temperature sensor is used to detect the heating temperature of the onboard battery when it is working, the energy recovery monitoring module is used to detect the amount of power recovered by the battery during the flight of the aircraft, and the battery power monitoring module is used to monitor the remaining power of the onboard battery;

[0008] The underground battery management module includes a charging current sensor, a charging voltage sensor, a charging temperature sensor, and a charging power monitoring module; the charging current sensor and the charging voltage sensor respectively monitor the current and voltage of the aircraft's battery during charging, the charging temperature sensor is used to detect the heating temperature of the battery during charging, and the charging power monitoring module is used to monitor the battery charging power;

[0009] Both the onboard battery management module and the underground battery management module are electrically connected to the aircraft battery management controller, which is used to analyze the battery usage status and charging status and evaluate the battery status.

[0010] A control method for the above-mentioned electric aircraft battery management control system is provided, which comprises the following steps:

[0011] S1: During the flight of an aircraft, the working current sensor, working voltage sensor and working temperature sensor of the battery management module on board collect the working current I at a set time interval s. i , voltage U i and the battery heating temperature t i ;

[0012] S2: Establish a life assessment model for the battery under working conditions:

[0013]

[0014] Where i is the number of times the onboard battery management module collects data, I, U and t are the current, voltage and heating temperature of the battery under standard conditions, T is the ambient temperature, a and b are the life assessment coefficients, and X is the average life of the battery. i The input working current I i , voltage U i and the battery heating temperature t i ;δ is the value of f(X i ) value is mapped to the mapping coefficient of the (0,1) interval;

[0015] S3: Each time the onboard battery management module collects data, it substitutes it into the life model to calculate the corresponding life coefficient y. Each time data is collected, a life coefficient y is obtained;

[0016] S4: The energy recovery monitoring module and the battery power monitoring module collect the energy recovery amount D every set time s. i and remaining battery charge i ;

[0017] S5: According to the energy recovery amount D i and remaining battery charge i Calculate the ratio of recycled volume to power consumption, L:

[0018]

[0019] Where d is the full charge of the battery;

[0020] S6: The ratio L of the recovered amount to the consumed amount is used as the battery power recovery coefficient j for evaluation;

[0021] S7: The energy recovery monitoring module and the battery power monitoring module calculate the power recovery coefficient j every time they collect data;

[0022] S8: After the aircraft completes its flight mission, it enters the warehouse for charging. The underground battery management module collects the current e, voltage v, and heating temperature T of the battery during charging. x And the charge F, calculate the capacity attenuation coefficient C of the battery during the charging process:

[0023]

[0024] Among them, a is the influence coefficient of abnormal current on battery capacity attenuation, b is the influence coefficient of heating temperature on battery capacity attenuation, β is the influence index of heating temperature on battery capacity attenuation, n c The number of times the battery has been charged;

[0025] S9: Map the capacity decay coefficient C to the value interval C′→μ·C∈(0,1) of (0,1), and obtain the evaluation coefficient k of the impact of the capacity decay of the battery on the life, where μ is the mapping coefficient of the capacity decay;

[0026] S10: Calculate the quality coefficient z of the battery using the power recovery coefficient j, life coefficient y and evaluation coefficient k: z = j + y + k, and use the quality coefficient z and quality evaluation threshold z 阈值 For comparison:

[0027] If z>z 阈值 , it is determined that the battery of the aircraft is about to fail, and the aircraft battery management controller generates an alarm message and sends it to the staff to remind them to replace the battery of the aircraft;

[0028] If z≤z 阈值 , it is determined that the battery of the aircraft can be used normally.

[0029] The beneficial effects of the present invention are as follows: This solution starts from the life evaluation during the flight of the aircraft and the life evaluation during the charging process, comprehensively evaluates the battery life of the aircraft from two perspectives that most affect the battery life, calculates the battery life coefficient y, the power recovery coefficient j, and the evaluation coefficient k of the impact of capacity decay on the battery life, and considers the comprehensive impact of the three parameters on the battery of the aircraft. It can obtain the most accurate battery fault information, can realize parallel analysis and optimization, and has good global evaluation performance, improving the reliability of the entire evaluation process. The battery power supply of the entire aircraft is realized to achieve the purpose of underground troubleshooting and ground flight comprehensive evaluation. The staff can replace the faulty battery in time underground to avoid the explosion of the aircraft carrying the faulty battery when performing a flight mission. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 This is a functional block diagram of the battery management control system for electric aviation aircraft. DETAILED DESCRIPTION

[0031] The specific implementation modes of the present invention are described below so that those skilled in the art can understand the present invention. However, it should be clear that the present invention is not limited to the scope of the specific implementation modes. For those of ordinary skill in the art, as long as various changes are within the spirit and scope of the present invention as defined and determined by the attached claims, these changes are obvious, and all inventions and creations utilizing the concept of the present invention are protected.

[0032] like Figure 1 As shown, the electric aircraft battery management control system of this solution includes an onboard battery management module and an underground battery management module.

[0033] The onboard battery management module includes a working current sensor, a working voltage sensor, a working temperature sensor, an energy recovery monitoring module and a battery power monitoring module; the working current sensor and the working voltage sensor respectively collect the output current and output voltage of the onboard battery, the working temperature sensor is used to detect the heating temperature of the onboard battery when it is working, the energy recovery monitoring module is used to detect the amount of power recovered by the battery during the flight of the aircraft, and the battery power monitoring module is used to monitor the remaining power of the onboard battery.

[0034] The underground battery management module includes a charging current sensor, a charging voltage sensor, a charging temperature sensor, and a charging power monitoring module; the charging current sensor and the charging voltage sensor respectively monitor the current and voltage of the aircraft's battery during charging, the charging temperature sensor is used to detect the heating temperature of the battery during charging, and the charging power monitoring module is used to monitor the battery charging power.

[0035] Both the onboard battery management module and the underground battery management module are electrically connected to the aircraft battery management controller, which is used to analyze the battery usage status and charging status and evaluate the battery status.

[0036] The control method of the above-mentioned electric aircraft battery management control system comprises the following steps:

[0037] S1: During the flight of an aircraft, the working current sensor, working voltage sensor and working temperature sensor of the battery management module on board collect the working current I at a set time interval s. i , voltage U i and the battery heating temperature t i ;

[0038] S2: Establish a life assessment model for the battery under working conditions:

[0039]

[0040] Where i is the number of times the onboard battery management module collects data, I, U and t are the current, voltage and heating temperature of the battery under standard conditions, T is the ambient temperature, a and b are the life assessment coefficients, and X is the average life of the battery. i The input working current I i , voltage U i and the battery heating temperature t i ;δ is the value of f(X i ) value is mapped to the mapping coefficient of the (0,1) interval;

[0041] S3: Each time the onboard battery management module collects data, it substitutes it into the life model to calculate the corresponding life coefficient y. Each time data is collected, a life coefficient y is obtained;

[0042] S4: The energy recovery monitoring module and the battery power monitoring module collect the energy recovery amount D every set time s. i and remaining battery charge i ;

[0043] S5: According to the amount of energy recovery D i and remaining battery charge i Calculate the ratio of recycled volume to power consumption, L:

[0044]

[0045] Where d is the full charge of the battery;

[0046] S6: The ratio L of the recovered amount to the consumed amount is used as the battery power recovery coefficient j for evaluation;

[0047] S7: The energy recovery monitoring module and the battery power monitoring module calculate the power recovery coefficient j every time they collect data;

[0048] S8: After the aircraft completes its flight mission, it enters the warehouse for charging. The underground battery management module collects the current e, voltage v, and heating temperature T of the battery during charging. x And the charge F, calculate the capacity attenuation coefficient C of the battery during the charging process:

[0049]

[0050] Among them, a is the influence coefficient of abnormal current on battery capacity attenuation, b is the influence coefficient of heating temperature on battery capacity attenuation, β is the influence index of heating temperature on battery capacity attenuation, n c The number of times the battery has been charged;

[0051] S9: Map the capacity decay coefficient C to the value interval C′→μ·C∈(0,1) of (0,1), and obtain the evaluation coefficient k of the impact of the capacity decay of the battery on the life, where μ is the mapping coefficient of the capacity decay;

[0052] S10: Calculate the quality coefficient z of the battery using the power recovery coefficient j, life coefficient y and evaluation coefficient k: z = j + y + k, and use the quality coefficient z and quality evaluation threshold z 阈值 For comparison:

[0053] If z>z 阈值 , it is determined that the battery of the aircraft is about to fail, and the aircraft battery management controller generates an alarm message and sends it to the staff to remind them to replace the battery of the aircraft;

[0054] If z≤z 阈值 , it is determined that the battery of the aircraft can be used normally.

[0055] This solution starts from the life evaluation during the flight of the aircraft and the life evaluation during the charging process, and comprehensively evaluates the battery life of the aircraft from the two perspectives that most affect the battery life. It calculates the battery life coefficient y, the power recovery coefficient j, and the evaluation coefficient k of the impact of capacity decay on the battery life. It considers the comprehensive impact of the three parameters on the battery of the aircraft, and can obtain the most accurate battery fault information. It can not only realize parallel analysis and optimization, but also has good global evaluation performance, improving the reliability of the entire evaluation process. The battery power supply of the entire aircraft is realized to achieve the purpose of underground troubleshooting and ground flight comprehensive evaluation. The staff can replace the faulty battery in time underground to avoid the explosion of the aircraft carrying the faulty battery during the flight mission.

[0056] The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention. It is obvious to those skilled in the art that the present invention is not limited to the details of the above exemplary embodiments, and the present invention can be implemented in other specific forms without departing from the spirit or basic features of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive. The scope of the present invention is defined by the attached claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention. Any figure mark in the claims should not be regarded as limiting the claims involved.

[0057] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A control method for an electric aircraft battery management control system, characterized in that: The following steps are involved: S1: During the flight of an aircraft, the working current sensor, working voltage sensor and working temperature sensor of the battery management module on board collect the working current I at a set time interval s. i , voltage U i and the battery heating temperature t i ; S2: Establish a life assessment model for the battery under working conditions: Among them, i is the number of times the onboard battery management module collects data, I, U and t are the current, voltage and heating temperature of the battery under standard conditions, T is the ambient temperature, a and b are the life assessment coefficients, Xi is the input working current Ii, voltage Ui and battery heating temperature ti; δ is the conversion of f(X i ) value is mapped to the mapping coefficient of the (0,1) interval; S3: Each time the onboard battery management module collects data, it substitutes it into the life model to calculate the corresponding life coefficient y. Each time data is collected, a life coefficient y is obtained; S4: The energy recovery monitoring module and the battery power monitoring module collect the energy recovery amount D every set time s. i and remaining battery charge i ; S5: According to the amount of energy recovery D i and remaining battery charge i Calculate the ratio of recycled volume to power consumption, L: Where d is the full charge of the battery; S6: The ratio L of the recovered amount to the consumed amount is used as the battery power recovery coefficient j for evaluation; S7: The energy recovery monitoring module and the battery power monitoring module calculate the power recovery coefficient j every time they collect data; S8: After the aircraft completes its flight mission, it enters the warehouse for charging. The underground battery management module collects the current e, voltage v, and heating temperature T of the battery during charging. x And the charge F, calculate the capacity attenuation coefficient C of the battery during the charging process: Among them, a is the influence coefficient of abnormal current on battery capacity attenuation, b is the influence coefficient of heating temperature on battery capacity attenuation, β is the influence index of heating temperature on battery capacity attenuation, n c The number of times the battery has been charged; S9: Map the capacity decay coefficient C to the value interval C′→μ·C∈(0,1) of (0,1), and obtain the evaluation coefficient k of the impact of the capacity decay of the battery on the life, where μ is the mapping coefficient of the capacity decay; S10: Calculate the quality coefficient z of the battery using the power recovery coefficient j, life coefficient y and evaluation coefficient k: z = j + y + k, and use the quality coefficient z and quality evaluation threshold z 阈值 For comparison: If z>z 阈值 , it is determined that the battery of the aircraft is about to fail, and the aircraft battery management controller generates an alarm message and sends it to the staff to remind them to replace the battery of the aircraft; If z≤z 阈值 , it is determined that the battery of the aircraft can be used normally.

2. The control method of the battery management control system of the electric aircraft according to claim 1, characterized in that: The battery management and control system for electric aviation aircraft includes an onboard battery management module and an underground battery management module; The onboard battery management module includes a working current sensor, a working voltage sensor, a working temperature sensor, an energy recovery monitoring module and a battery power monitoring module; the working current sensor and the working voltage sensor respectively collect the output current and output voltage of the onboard battery, the working temperature sensor is used to detect the heating temperature of the onboard battery when it is working, the energy recovery monitoring module is used to detect the amount of power recovered by the battery during the flight of the aircraft, and the battery power monitoring module is used to monitor the remaining power of the onboard battery; The underground battery management module includes a charging current sensor, a charging voltage sensor, a charging temperature sensor, and a charging power monitoring module; the charging current sensor and the charging voltage sensor respectively monitor the current and voltage of the aircraft battery during charging, the charging temperature sensor is used to detect the heating temperature of the battery during charging, and the charging power monitoring module is used to monitor the power of the battery charging; The onboard battery management module and the underground battery management module are both electrically connected to an aircraft battery management controller, and the aircraft battery management controller is used to analyze the battery usage status and charging status and evaluate the battery status.

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