An aircraft hybrid electric power supply system and power supply control method

Abstract

The application discloses an airplane hybrid power supply system and a power supply control method, which can combine a fuel cell system, a photovoltaic cell system and a power battery system to form a comprehensive airborne energy source, has the advantages of high output power, fast response speed and long endurance time, and can real-timely regulate and control the output states of the fuel cell system, the photovoltaic cell system and the power battery system according to the total machine load power, timely charges and discharges the power battery system when the airborne energy source is not used, and can timely meet the instantaneous airborne energy consumption increase demand.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft hybrid power supply, and particularly relates to an aircraft hybrid power supply system and a power supply control method. BACKGROUND

[0002] With the proposal of the green aviation concept and the development of electrification, in recent years, more and more power forms driven by batteries, hydrogen fuel cells and solar energy are emerging in the field of aircraft. The development of pure electric aircraft is relatively mature, and the advantages are large instantaneous output power, and the disadvantages are low mass power density of the battery and short cruising time of the aircraft, generally only tens of minutes; the cruising time of the solar aircraft is long under specific weather conditions, but the weather conditions are relatively high; the cruising time of the fuel cell is relatively long, and the disadvantage is slow response and limited power increase speed in a short time.

[0003] When two or more than two energy forms of batteries, hydrogen fuel cells and solar energy are combined to realize energy supply, how to take advantage of the control scheme to make up for the shortcomings and realize the rapid, stable and long-time output of energy on the aircraft is a relatively urgent challenge.

[0004] Therefore, in view of the problem that the power battery, fuel cell and solar photovoltaic cell are not comprehensively applied in the airborne energy supply in the prior art, the application discloses an aircraft hybrid power supply system and a power supply control method. SUMMARY

[0005] The application discloses an aircraft hybrid power supply system and a power supply control method, which combines a power battery, a solar photovoltaic cell and a fuel cell as hybrid electric energy to provide airborne energy, and has the advantages of large instantaneous output power, fast output power response and long cruising time, so as to meet the comprehensive energy output demand of the aircraft.

[0006] The application is realized through the following technical scheme:

[0007] An aircraft hybrid power supply system comprises a power supply bus, a fuel cell system, a power battery system and a photovoltaic cell system, the fuel cell system and the photovoltaic cell system are unidirectionally connected in parallel to the power supply bus, so that the fuel cell system and the photovoltaic cell system can only supply power to the power supply bus in one direction; the power battery system is bidirectionally connected in parallel to the power supply bus, so that the power battery system can supply power to the power supply bus or take power from the power supply bus, and the output end of the power battery system is provided with a low-voltage branch, the low-voltage branch is connected with an airborne low-voltage power consumption system; the output end of the power supply bus is provided with an electric governor assembly, and the output end of the electric governor assembly is connected with a propeller system.

[0008] In order to better realize the present invention, further, the fuel cell system includes a fuel cell module and a DC converter, and the fuel cell module is connected to the power supply bus through the DC converter; the photovoltaic cell system includes a solar photovoltaic panel module and a photovoltaic inverter, and the solar photovoltaic panel module is connected to the power supply bus through the photovoltaic inverter.

[0009] In order to better realize the present invention, further, the propeller system includes a motor and a propeller module, the motor is connected to the output end of the electronic adjustment component, and the output end of the motor is connected to the propeller module; the airborne low-voltage power consumption system includes a step-down module and an airborne low-voltage power consumption module, and the low-voltage branch is connected to the airborne low-voltage power consumption module through the step-down module.

[0010] A method for controlling hybrid power supply of an aircraft is implemented based on a hybrid power supply system of the aircraft, comprising the following steps:

[0011] Step 1: Determine the state of the propeller system. If the propeller system is in the parked state, proceed to step 2; if the propeller system is in the running state, proceed to step 3. Set a first power threshold K1, a second power threshold K2, and a third power threshold K3, and K1>K2>K3.

[0012] Step 2: Detect the real-time power soc of the power battery system. If soc ≥ K1, keep the fuel cell system and the photovoltaic battery system in standby mode. If soc < K1, compare the input power PS0 of the photovoltaic battery system with the maximum allowable charging power PB0 of the power battery system. Based on the comparison result, control the photovoltaic battery system to charge the power battery system alone or control the photovoltaic battery system and the fuel cell system to charge the power battery system together.

[0013] Step 3: Detect the real-time power soc of the power battery system. If soc < K3, proceed to step 4; if K3 ≤ soc ≤ K2, proceed to step 5; if K2 < soc < K1, proceed to step 6; if soc ≥ K1, proceed to step 7;

[0014] Step 4: Detect the total load power PM and the maximum output power PFC1 of the fuel cell system; if PM≤PS0, control the photovoltaic battery system alone, or control the photovoltaic battery system and the fuel cell system to jointly perform the first mode of power supply; if PS0<PM<PS0+PFC1, control the photovoltaic battery system and the fuel cell system to jointly perform the second mode of power supply; if PM≥PS0+PFC1, control the photovoltaic battery system and the fuel cell system to jointly perform the third mode of power supply;

[0015] Step 5, detecting the total machine load power PM and the maximum output power PFC1 of the fuel cell system; if PM≤PS0, controlling the photovoltaic cell system to supply power in the fourth mode alone; if PS0

[0016] Step 6, detecting the total machine load power PM and the maximum output power PFC1 of the fuel cell system; if PM≤PS0, controlling the photovoltaic cell system to supply power in the seventh mode alone; if PS0

[0017] Step 7, keeping the photovoltaic cell system and the fuel cell system in standby state.

[0018] In order to better realize the present application, further, the step 2 specifically comprises:

[0019] Step 2.1, detecting the real-time power soc of the power battery system;

[0020] Step 2.2, if soc≥K1, keeping the fuel cell system and the photovoltaic cell system in standby state and supplying power to the low-voltage branch by the power battery system; if soc

[0021] Step 2.3, if PS0> PB0, adjusting the output power PS1 of the photovoltaic cell system to PS1=PB0, charging the power battery system by the photovoltaic cell system; if PS0≤PB0, starting the fuel cell system and detecting the minimum output power PFC0 of the fuel cell system and then turning to step 2.4;

[0022] Step 2.4, if PS0+PFC0> PB0, controlling the real-time output power PFC of the fuel cell system to be PFC0 and ensuring that PFC0+PS1=PB0; if PS0+PFC0≤PB0, controlling PS1=PS0 and PFC+PS0=PB0.

[0023] In order to better realize the present application, further, the step 4 specifically comprises:

[0024] Step 4.1, detecting the total machine load power PM, detecting the maximum output power PFC1 of the fuel cell system, detecting the maximum allowable charging power PB0 of the power battery system; if PM≤PS0, then turning to step 4.2; if PS0

[0025] Step 4.2, if PS0> PB0+PM, then controlling the output power PS1=PM+PB0 of the photovoltaic cell system, and supplying power to the power battery system by the photovoltaic cell system alone; if PS0≤PB0+PM, then starting the fuel cell system, detecting the minimum output power PFC0 of the fuel cell system, if PFC0+PS0> PB0+PM, then controlling the real-time output power PFC=PFC0 of the fuel cell system and PS1+PFC0=PB0+PM, and supplying power to the power battery system by the photovoltaic cell system and the fuel cell system jointly; if PFC0+PS0≤PB0+PM, then controlling the output power PS1=PS0 of the photovoltaic cell system and PFC+PS0=PB0+PM, and supplying power to the power battery system by the photovoltaic cell system and the fuel cell system jointly;

[0026] Step 4.3, starting the fuel cell system, if PFC0+PS0> PB0+PM, then controlling the real-time output power PFC=PFC0 of the fuel cell system and PS1+PFC0=PB0+PM, and supplying power to the power battery system by the photovoltaic cell system and the fuel cell system jointly; if PFC0+PS0≤PB0+PM, then controlling the output power PS1=PS0 of the photovoltaic cell system and PFC+PS0=PB0+PM, and supplying power to the power battery system by the photovoltaic cell system and the fuel cell system jointly;

[0027] Step 4.4, starting the fuel cell system, controlling the real-time output power PFC=PFC1 of the fuel cell system and the output power PS1=PS0 of the photovoltaic cell system for joint power supply, and reducing the rotating speed of the propeller system so that PM+PB0≤PFC+PS0.

[0028] In order to better realize the present application, further, the step 5 specifically comprises:

[0029] Step 5.1, if PM≤PS0, then turning to step 5.2; if PS0

[0030] Step 5.2, controlling the output power PS1=PM of the photovoltaic cell system, and supplying power to the power battery system by the photovoltaic cell system and the power battery system jointly;

[0031] Step 5.3, starting the fuel cell system, if PM < PS0+PFC0, controlling the real-time output power PFC of the fuel cell system as PFC0 and PS1+PFC0=PM, jointly supplying power through the photovoltaic cell system, the fuel cell system and the power battery system; if PM ≥ PS0+PFC0, controlling the output power PS1 of the photovoltaic cell system as PS0 and PFC+PS0=PM, jointly supplying power through the photovoltaic cell system, the fuel cell system and the power battery system;

[0032] Step 5.4, starting the fuel cell system, controlling the output power PS1 of the photovoltaic cell system as PS0 and controlling the real-time output power PFC of the fuel cell system as PFC1, jointly supplying power through the photovoltaic cell system, the fuel cell system and the power battery system.

[0033] In order to better realize the present application, further, the step 6 specifically comprises:

[0034] Step 6.1, detecting the total machine load power PM, detecting the maximum output power PFC1 of the fuel cell system and detecting the input power PS0 of the photovoltaic cell system; if PM ≤ PS0, turning to step 6.2; if PS0 < PM < PS0+PFC1, turning to step 6.3; if PM ≥ PS0+PFC1, turning to step 6.4;

[0035] Step 6.2, controlling the output power PS1 of the photovoltaic cell system as 0.8PM, jointly supplying power through the photovoltaic cell system and the power battery system;

[0036] Step 6.3, detecting the minimum output power PFC0 of the fuel cell system, if PM < PS0+PFC0, controlling the output power PS1 of the photovoltaic cell system as PS0, jointly supplying power through the photovoltaic cell system and the power battery system; if PM ≥ PS0+PFC0, starting the fuel cell system, controlling the output power PS1 of the photovoltaic cell system as PS0 and controlling the real-time output power PFC of the fuel cell system as PFC0, jointly supplying power through the photovoltaic cell system, the fuel cell system and the power battery system;

[0037] Step 6.4, starting the fuel cell system, controlling the output power PS1 of the photovoltaic cell system as PS0 and controlling the real-time output power PFC of the fuel cell system as PFC0, jointly supplying power through the photovoltaic cell system, the fuel cell system and the power battery system.

[0038] In order to better realize the present application, further, the first electric quantity threshold K1=98%; the second electric quantity threshold K2=80%; and the third electric quantity threshold K3=40%.

[0039] Compared with the prior art, the present application has the following advantages and beneficial effects:

[0040] The application can combine a fuel cell system, a photovoltaic cell system and a power battery system to form a comprehensive airborne energy source, has the advantages of high output power, fast response speed and long endurance time, and can real-time regulate the output state of the fuel cell system, the photovoltaic cell system and the power battery system according to the total machine load power, timely charge and discharge the power battery system when the airborne energy source is not used, and timely meet the instantaneous airborne energy consumption increase demand. BRIEF DESCRIPTION OF DRAWINGS

[0041] Figure 1 It is a schematic diagram of an aircraft hybrid power supply system;

[0042] Figure 2 It is a schematic diagram of power supply control process steps in the parking state of the propeller system;

[0043] Figure 3 It is a schematic diagram of power supply control process steps in the starting state of the propeller system.

[0044] Wherein: 1-fuel cell module; 2-direct current converter; 3-solar photovoltaic panel module; 4-photovoltaic inverter; 5-power battery system; 6-electric governor assembly; 7-motor; 8-propeller module; 9-voltage reduction module; 10-airborne low-voltage power consumption module. DETAILED DESCRIPTION

[0045] Example 1:

[0046] The aircraft hybrid power supply system of the embodiment, as shown in Figure 1 The schematic diagram of the aircraft hybrid power supply system, includes a power supply bus, and further includes a fuel cell system, a power battery system 5 and a photovoltaic cell system, the fuel cell system and the photovoltaic cell system are unidirectionally connected in parallel to the power supply bus, so that the fuel cell system and the photovoltaic cell system can only unidirectionally supply power to the power supply bus; the power battery system 5 is bidirectionally connected in parallel to the power supply bus, so that the power battery system 5 can supply power to the power supply bus or take power from the power supply bus, the output end of the power battery system 5 is provided with a low-voltage branch, the low-voltage branch is connected with an airborne low-voltage power consumption system; the output end of the power supply bus is provided with an electric governor assembly 6, and the output end of the electric governor assembly 6 is connected with a propeller system.

[0047] The fuel cell system and the photovoltaic cell system are unidirectionally connected with the power supply bus, that is, only the fuel cell system and the photovoltaic cell system are allowed to supply power to the power supply bus, and the fuel cell system and the photovoltaic cell system are not allowed to take power from the power supply bus. By setting the fuel cell system and the photovoltaic cell system, the power battery system 5 is jointly supplied, or when the power of the power battery system 5 is insufficient, the fuel cell system and the photovoltaic cell system are used to charge the power battery system 5.

[0048] The fuel cell system includes a fuel cell module 1, a direct current converter 2, the fuel cell module 1 is connected with the power supply bus through the direct current converter 2; the photovoltaic cell system includes a solar photovoltaic panel module 3, a photovoltaic inverter 4, the solar photovoltaic panel module 3 is connected with the power supply bus through the photovoltaic inverter 4.

[0049] The fuel cell module 1 adopts a hydrogen fuel cell module, which is used for converting chemical energy of hydrogen and oxygen reaction into electric energy. The direct current converter 2 is used for converting the voltage of the direct current generated by the fuel cell module 1 into the working voltage range required by the electronic speed control assembly 6. The solar photovoltaic module 3 includes a solar photovoltaic panel, which is used for converting solar energy into electric energy. Through the setting of the photovoltaic inverter 4, the highest efficiency utilization of solar power generation can be realized, and the voltage generated by the solar photovoltaic module 3 can be converted into the working voltage range required by the electronic speed control assembly 6. The power battery system 5 itself has a certain capacity, and is bidirectionally connected with the power supply bus. Through the power battery system 5, power can be supplied to the power supply bus, and at the same time, the power battery system 5 can also take power from the power supply bus. The electronic speed control assembly 6 is used for monitoring and controlling the rotating speed of the motor in the propeller system.

[0050] The propeller system includes a motor 7 and a propeller module 8, the motor 7 is connected with the output end of the electronic speed control assembly 6, and the output end of the motor 7 is connected with the propeller module 8. The airborne low-voltage power consumption system includes a voltage reduction module 9 and an airborne low-voltage power consumption module 10, the low-voltage branch is connected with the airborne low-voltage power consumption module 10 through the voltage reduction module 9. The electronic speed control assembly 6 is used for monitoring and controlling the rotating speed of the motor 7, and the motor 7 drives the propeller module 8 to rotate. At the same time, the output end of the power battery system 5 supplies low-voltage power to the airborne low-voltage power consumption module 10 through the low-voltage branch, and the voltage output by the power battery system 5 can be converted to the working voltage range required by the airborne low-voltage power consumption module 10 through the voltage reduction module 9.

[0051] Embodiment 2:

[0052] The aircraft hybrid power supply control method of the embodiment is realized based on the aircraft hybrid power supply system in embodiment 1, and includes the following steps:

[0053] Step 1, judge the propeller system state, if the propeller system is in the parking state, turn to step 2, if the propeller system is in the running state, turn to step 3; set the first electric quantity threshold K1, the second electric quantity threshold K2 and the third electric quantity threshold K3, and K1>K2>K3;

[0054] Step 2, detecting the real-time power soc of the power battery system 5, if soc≥K1, keeping the fuel cell system and the photovoltaic cell system in standby state; if soc<K1, comparing the input power PS0 of the photovoltaic cell system with the maximum allowable charging power PB0 of the power battery system 5, and controlling the photovoltaic cell system to charge the power battery system 5 alone or controlling the photovoltaic cell system and the fuel cell system to charge the power battery system 5 together according to the comparison result;

[0055] Step 3, detecting the real-time power soc of the power battery system 5, if soc<K3, turning to step 4; if K3≤soc≤K2, turning to step 5; if K2<soc<K1, turning to step 6; if soc≥K1, turning to step 7;

[0056] Step 4, detecting the total machine load power PM and the maximum output power PFC1 of the fuel cell system; if PM≤PS0, controlling the photovoltaic cell system to supply power in the first mode alone or in combination with the fuel cell system; if PS0<PM<PS0+PFC1, controlling the photovoltaic cell system and the fuel cell system to supply power in the second mode; if PM≥PS0+PFC1, controlling the photovoltaic cell system and the fuel cell system to supply power in the third mode;

[0057] Step 5, detecting the total machine load power PM and the maximum output power PFC1 of the fuel cell system; if PM≤PS0, controlling the photovoltaic cell system to supply power in the fourth mode alone; if PS0<PM<PS0+PFC1, controlling the photovoltaic cell system and the fuel cell system to supply power in the fifth mode; if PM≥PS0+PFC1, controlling the photovoltaic cell system and the fuel cell system to supply power in the sixth mode;

[0058] Step 6, detecting the total machine load power PM and the maximum output power PFC1 of the fuel cell system; if PM≤PS0, controlling the photovoltaic cell system to supply power in the seventh mode alone; if PS0<PM<PS0+PFC1, controlling the photovoltaic cell system to supply power in the eighth mode alone or in combination with the fuel cell system; if PM≥PS0+PFC1, controlling the photovoltaic cell system and the fuel cell system to supply power in the ninth mode;

[0059] Step 7, keeping the photovoltaic cell system and the fuel cell system in standby state.

[0060] For the convenience of description, the following symbols are defined as follows:

[0061] SOC represents the real-time power of the power battery system 5; PB0 represents the maximum allowable charging power of the power battery system 5; Pm0 represents the load power of the motor in the propeller system; PS0 represents the input power of the photovoltaic cell system; PS1 represents the output power of the photovoltaic cell system; PFC0 represents the minimum output power of the fuel cell system; PFC1 represents the maximum output power of the fuel cell system; PFC represents the real-time output power of the fuel cell system; Pm1 represents the load power of the airborne low-voltage power consumption system; and PM represents the total machine load power.

[0062] PB0, PFC0, and PFC1 are constant values;

[0063] 0≤PS1≤PS0, the output power PS1 of the photovoltaic cell system can be controlled in real time, but the output power PS1 of the photovoltaic cell system is not greater than the input power PS0 of the photovoltaic cell system.

[0064] 0

[0065] PM=Pm0+Pm1, that is, the total machine load power is the sum of the load power of the airborne low-voltage power consumption system and the load power of the motor in the propeller system.

[0066] PFC0≤PB0, which means that when the control system is selected, the minimum output power PFC0 of the fuel cell system should not be greater than the maximum allowable charging power PB0 of the power battery system 5.

[0067] When the propeller system is in the parking state, the total machine load power mainly comes from the load power of the airborne low-voltage power consumption system, and at this time, the total machine load power is small. When the propeller system starts, the total machine load power comes from the sum of the load power of the airborne low-voltage power consumption system and the load power of the motor in the propeller system, and at this time, the total machine load power is large.

[0068] Further, when the aircraft is powered on and the propeller system is in the parking state, first enter the ground inspection stage. The aircraft needs to be prepared for flight in the ground inspection mode. Therefore, it is necessary to ensure that the power battery system 5 is in a full power or high power state before takeoff, and at this time, step 2 is executed, as shown in Figure 2 The step 2 specifically includes:

[0069] Step 2.1, detecting the real-time power SOC of the power battery system 5;

[0070] Step 2.2, if soc≥K1, here K1=98%, the SOC of the power battery system 5 is considered to meet the requirements of the aircraft for takeoff, the fuel cell system and the photovoltaic cell system are kept in standby state to prevent the power battery system 5 from being in overcharged state, and the power battery system 5 is powered at the same time. If soc

[0071] The input power PS0 of the photovoltaic cell system is compared with the maximum allowable charging power PB0 of the power battery system 5, and then step 2.3 is entered.

[0072] Step 2.3, if PS0> PB0, the output power PS1 of the photovoltaic cell system is adjusted to PS1=PB0, and the power battery system 5 is charged by the photovoltaic cell system; at this time, the photovoltaic cell system is in the state of charging the power battery system 5, and no energy carried by the aircraft is consumed.

[0073] If PS0≤PB0, it is determined whether to start the fuel cell system according to the emergency degree of the flight task and the state of the aircraft.

[0074] If the fuel cell system is started, the minimum output power PFC0 of the fuel cell system is detected, and then step 2.4 is entered.

[0075] Step 2.4, if PS0+PFC0> PB0, the real-time output power PFC of the fuel cell system is controlled to be PFC0, and PFC0+PS1=PB0 is ensured, that is, the fuel cell system is kept at the minimum output power, and the output power of the photovoltaic cell system is adjusted to be equal to the difference between the maximum allowable charging power of the power battery system 5 and the minimum output power of the fuel cell system. If PS0+PFC0≤PB0, PS1=PS0 is controlled, and PFC+PS0=PB0 is ensured, that is, the output power of the photovoltaic cell system is kept equal to its input power, and the output power of the fuel cell system is equal to the difference between the maximum allowable charging power of the power battery system 5 and the input power of the photovoltaic cell system.

[0076] Further, if soc Figure 3 As shown in the figure, the step 4 specifically includes:

[0077] Step 4.1, detecting the total machine load power PM, detecting the maximum output power PFC1 of the fuel cell system, and detecting the maximum allowable charging power PB0 of the power battery system 5; if PM≤PS0, then turning to step 4.2; if PS0

[0078] Step 4.2, if PS0> PB0+PM, then controlling the output power PS1=PM+PB0 of the photovoltaic cell system to supply power to the power battery system 5 alone by controlling the photovoltaic cell system; if PS0≤PB0+PM, then starting the fuel cell system, detecting the minimum output power PFC0 of the fuel cell system, if PFC0+PS0> PB0+PM, then controlling the real-time output power PFC=PFC0 of the fuel cell system and PS1+PFC0=PB0+PM to supply power to the power battery system 5 by the photovoltaic cell system and the fuel cell system in combination; if PFC0+PS0≤PB0+PM, then controlling the output power PS1=PS0 of the photovoltaic cell system and PFC+PS0=PB0+PM to supply power to the power battery system 5 by the photovoltaic cell system and the fuel cell system in combination;

[0079] Step 4.3, starting the fuel cell system, if PFC0+PS0> PB0+PM, then controlling the real-time output power PFC=PFC0 of the fuel cell system and PS1+PFC0=PB0+PM to supply power to the power battery system 5 by the photovoltaic cell system and the fuel cell system in combination; if PFC0+PS0≤PB0+PM, then controlling the output power PS1=PS0 of the photovoltaic cell system and PFC+PS0=PB0+PM to supply power to the power battery system 5 by the photovoltaic cell system and the fuel cell system in combination;

[0080] Step 4.4, starting the fuel cell system, controlling the real-time output power PFC=PFC1 of the fuel cell system and the output power PS1=PS0 of the photovoltaic cell system to supply power in combination, and reducing the rotation speed of the propeller system so that PM+PB0≤PFC+PS0.

[0081] Further, if K3≤soc≤K2, where K2=80% and K3=40%, it indicates that the power of the power battery system 5 is moderate, the discharge margin is appropriate, the power balance of the power battery system 5 should be ensured, the machine energy consumption is small, and the photovoltaic cell system power can meet the demand of the machine energy consumption. At this time, step 5 is executed, as shown in the following table, which specifically includes: Figure 3

[0082] ​Step 5.1, if PM≤PS0, then go to step 5.2; if PS0

[0083] Step 5.2, control the output power of the photovoltaic cell system PS1=PM, and supply power by the photovoltaic cell system and the power battery system 5 jointly;

[0084] Step 5.3, start the fuel cell system, if PM

[0085] Step 5.4, start the fuel cell system, control the output power of the photovoltaic cell system PS1=PS0, and control the real-time output power of the fuel cell system PFC=PFC1, and supply power by the photovoltaic cell system, the fuel cell system and the power battery system 5 jointly.

[0086] Further, if K2 Figure 3 As shown in the step 6, the step 6 specifically includes:

[0087] Step 6.1, detect the total machine load power PM, detect the maximum output power of the fuel cell system PFC1, and detect the input power of the photovoltaic cell system PS0; if PM≤PS0, then go to step 6.2; if PS0

[0088] Step 6.2, control the output power of the photovoltaic cell system PS1=0.8PM, and supply power by the photovoltaic cell system and the power battery system 5 jointly;

[0089] Step 6.3: Detect the minimum output power PFC0 of the fuel cell system. If PM < PS0 + PFC0, control the output power PS1 of the photovoltaic battery system to PS0, and jointly supply power through the photovoltaic battery system and the power battery system 5. If PM ≥ PS0 + PFC0, start the fuel cell system, control the output power PS1 of the photovoltaic battery system to PS0, and control the real-time output power PFC of the fuel cell system to PFC0, and jointly supply power through the photovoltaic battery system, the fuel cell system, and the power battery system 5.

[0090] Step 6.4: Start the fuel cell system, control the output power PS1 of the photovoltaic battery system to PS0 and the real-time output power PFC of the fuel cell system to PFC0, and jointly supply power through the photovoltaic battery system, the fuel cell system, and the power battery system 5.

[0091] Furthermore, if soc≥K1, K1=98% is assumed here, indicating that the power battery system 5 is fully charged. To prevent the power battery system 5 from being overcharged, the photovoltaic battery system and the fuel cell system are kept in a standby state.

[0092] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification or equivalent change made to the above embodiment based on the technical essence of the present invention shall fall within the scope of protection of the present invention.

Claims

1. A method for controlling hybrid power supply of an aircraft, which is implemented based on a hybrid power supply system of the aircraft, wherein the hybrid power supply system of the aircraft includes a power supply bus, a fuel cell system, a power battery system (5), and a photovoltaic battery system, wherein the fuel cell system and the photovoltaic battery system are connected in parallel to the power supply bus in one direction, so that the fuel cell system and the photovoltaic battery system can only supply power to the power supply bus in one direction; the power battery system (5) is connected in parallel to the power supply bus in two directions, so that the power battery system (5) can supply power to the power supply bus or take power from the power supply bus, and the output end of the power battery system (5) is provided with a low-voltage branch, and the low-voltage branch is connected to the airborne low-voltage power consumption system; the output end of the power supply bus is provided with an electric adjustment component (6), and the output end of the electric adjustment component (6) is connected to the screw The propeller system is connected; the fuel cell system includes a fuel cell module (1) and a DC converter (2), and the fuel cell module (1) is connected to the power supply bus through the DC converter (2); the photovoltaic cell system includes a solar photovoltaic panel module (3) and a photovoltaic inverter (4), and the solar photovoltaic panel module (3) is connected to the power supply bus through the photovoltaic inverter (4); the propeller system includes a motor (7) and a propeller module (8), the motor (7) is connected to the output end of the electric adjustment component (6), and the output end of the motor (7) is connected to the propeller module (8); the airborne low-voltage power consumption system includes a step-down module (9) and an airborne low-voltage power consumption module (10), and the low-voltage branch is connected to the airborne low-voltage power consumption module (10) through the step-down module (9); It is characterized in that The following steps are involved: Step 1: Determine the state of the propeller system. If the propeller system is in the parking state, proceed to step 2; if the propeller system is in the running state, proceed to step 3. Set a first power threshold K1, a second power threshold K2, and a third power threshold K3, and K1>K2>K3; Step 2: Detect the real-time power soc of the power battery system (5); if soc≥K1, keep the fuel cell system and the photovoltaic battery system in a standby state; if soc<K1, compare the input power PS0 of the photovoltaic battery system with the maximum allowable charging power PB0 of the power battery system (5); and control the photovoltaic battery system to charge the power battery system (5) alone or control the photovoltaic battery system and the fuel cell system to charge the power battery system (5) together according to the comparison result; Step 3: Detect the real-time power soc of the power battery system (5). If soc < K3, proceed to step 4; if K3 ≤ soc ≤ K2, proceed to step 5; if K2 < soc < K1, proceed to step 6; if soc ≥ K1, proceed to step 7; Step 4: Detect the total load power PM and the maximum output power PFC1 of the fuel cell system; if PM≤PS0, control the photovoltaic battery system alone, or control the photovoltaic battery system and the fuel cell system to jointly perform the first mode of power supply; if PS0<PM<PS0+PFC1, control the photovoltaic battery system and the fuel cell system to jointly perform the second mode of power supply; if PM≥PS0+PFC1, control the photovoltaic battery system and the fuel cell system to jointly perform the third mode of power supply; Step 5: Detect the total load power PM and the maximum output power PFC1 of the fuel cell system; if PM ≤ PS0, control the photovoltaic battery system alone to perform the fourth mode of power supply; if PS0 < PM < PS0 + PFC1, control the photovoltaic battery system and the fuel cell system to jointly perform the fifth mode of power supply; if PM ≥ PS0 + PFC1, control the photovoltaic battery system and the fuel cell system to jointly perform the sixth mode of power supply; Step 6: Detect the total load power PM and the maximum output power PFC1 of the fuel cell system; if PM ≤ PS0, control the photovoltaic battery system alone to perform the seventh mode of power supply; if PS0 < PM < PS0 + PFC1, control the photovoltaic battery system alone, or control the photovoltaic battery system and the fuel cell system jointly to perform the eighth mode of power supply; if PM ≥ PS0 + PFC1, control the photovoltaic battery system and the fuel cell system jointly to perform the ninth mode of power supply; Step 7: Keep the photovoltaic battery system and the fuel cell system in standby mode.

2. The aircraft hybrid power supply control method according to claim 1, characterized in that: The step 2 specifically includes: Step 2.1, detecting the real-time power soc of the power battery system (5); Step 2.2: If soc ≥ K1, the fuel cell system and the photovoltaic battery system are kept in a standby state, and the low-voltage branch is powered by the power battery system (5); if soc < K1, the input power PS0 of the photovoltaic battery system is compared with the maximum allowable charging power PB0 of the power battery system (5); Step 2.3, if PS0>PB0, then adjust the output power PS1 of the photovoltaic battery system to PS1=PB0 photovoltaic battery system, and charge the power battery system (5) through the photovoltaic battery system; if PS0≤PB0, then start the fuel cell system, and detect the minimum output power PFC0 of the fuel cell system and then go to step 2.4; Step 2.4: If PS0+PFC0>PB0, then control the real-time output power of the fuel cell system to PFC=PFC0, and ensure that PFC0+PS1=PB0; if PS0+PFC0≤PB0, then control PS1=PS0, and PFC+PS0=PB0.

3. The aircraft hybrid power supply control method according to claim 1, characterized in that: The step 4 specifically includes: Step 4.1: Detect the total load power PM, the maximum output power PFC1 of the fuel cell system, and the maximum allowable charging power PB0 of the power battery system (5); if PM≤PS0, proceed to step 4.2; if PS0<PM<PS0+PFC1, proceed to step 4.3; if PM≥PS0+PFC1, proceed to step 4.4; Step 4.2: If PS0>PB0+PM, then control the output power of the photovoltaic battery system to PS1=PM+PB0, and control the photovoltaic battery system to supply power to the power battery system (5) alone; if PS0≤PB0+PM, start the fuel cell system, detect the minimum output power PFC0 of the fuel cell system, and if PFC0+PS0>PB0+PM, then control the real-time output power of the fuel cell system to PFC=PFC0 and PS1+PFC0=PB0+PM, and supply power to the power battery system (5) jointly through the photovoltaic battery system and the fuel cell system; if PFC0+PS0≤PB0+PM, then control the output power of the photovoltaic battery system to PS1=PS0 and PFC+PS0=PB0+PM, and supply power to the power battery system (5) jointly through the photovoltaic battery system and the fuel cell system; Step 4.3, start the fuel cell system. If PFC0+PS0>PB0+PM, then control the real-time output power of the fuel cell system to PFC=PFC0 and PS1+PFC0=PB0+PM, and power the power battery system (5) through the photovoltaic battery system and the fuel cell system; if PFC0+PS0≤PB0+PM, then control the output power of the photovoltaic battery system to PS1=PS0 and PFC+PS0=PB0+PM, and power the power battery system (5) through the photovoltaic battery system and the fuel cell system; Step 4.4: Start the fuel cell system, control the real-time output power PFC of the fuel cell system to PFC1 and the output power PS1 of the photovoltaic cell system to PS0 for joint power supply, and reduce the speed of the propeller system so that PM+PB0≤PFC+PS0.

4. The aircraft hybrid power supply control method according to claim 1, characterized in that: The step 5 specifically includes: Step 5.1: If PM ≤ PS0, proceed to step 5.2; if PS0 < PM < PS0 + PFC1, proceed to step 5.3; if PM ≥ PS0 + PFC1, proceed to step 5.4; Step 5.2, control the output power PS1=PM of the photovoltaic battery system, and supply power through the photovoltaic battery system and the power battery system (5); Step 5.3: Start the fuel cell system. If PM < PS0 + PFC0, then control the real-time output power of the fuel cell system to PFC = PFC0 and PS1 + PFC0 = PM, and jointly supply power through the photovoltaic battery system, the fuel cell system, and the power battery system (5); if PM ≥ PS0 + PFC0, then control the output power of the photovoltaic battery system to PS1 = PS0 and PFC + PS0 = PM, and jointly supply power through the photovoltaic battery system, the fuel cell system, and the power battery system (5); Step 5.4: Start the fuel cell system, control the output power PS1 of the photovoltaic battery system to PS0 and control the real-time output power PFC of the fuel cell system to PFC1, and jointly supply power through the photovoltaic battery system, the fuel cell system, and the power battery system (5).

5. The aircraft hybrid power supply control method according to claim 1, characterized in that: The step 6 specifically includes: Step 6.1: Detect the total load power PM, the maximum output power PFC1 of the fuel cell system, and the input power PS0 of the photovoltaic cell system; if PM ≤ PS0, proceed to step 6.2; if PS0 < PM < PS0 + PFC1, proceed to step 6.3; if PM ≥ PS0 + PFC1, proceed to step 6.4; Step 6.2, control the output power PS1 of the photovoltaic battery system to 0.8PM, and supply power through the photovoltaic battery system and the power battery system (5); Step 6.3: Detect the minimum output power PFC0 of the fuel cell system. If PM < PS0 + PFC0, control the output power PS1 of the photovoltaic battery system to PS0, and jointly supply power through the photovoltaic battery system and the power battery system (5); If PM ≥ PS0 + PFC0, start the fuel cell system, control the output power PS1 of the photovoltaic battery system to PS0, and control the real-time output power PFC of the fuel cell system to PFC0, and jointly supply power through the photovoltaic battery system, the fuel cell system, and the power battery system (5); Step 6.4: Start the fuel cell system, control the output power PS1 of the photovoltaic battery system to PS0 and control the real-time output power PFC of the fuel cell system to PFC0, and jointly supply power through the photovoltaic battery system, the fuel cell system, and the power battery system (5).

6. The aircraft hybrid power supply control method according to any one of claims 1 to 5, characterized in that: The first power threshold K1 = 98%; the second power threshold K2 = 80%; and the third power threshold K3 = 40%.

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