# Fuzzy State Machine Energy Management Strategy for Hybrid Electric UAVs with PV/Fuel Cell/Battery Power System

Authors: Xiaohui Zhang; Li Liu; Yueling Dai
Journal: International Journal of Aerospace Engineering
 (2018)

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## Abstract

Energy management strategies are the key technology for hybrid electric UAVs. This paper proposes a fuzzy state machine (FSM) energy management strategy with an online potential to control the power flow for the hybrid electric UAV which includes the photovoltaic, fuel cell, and battery power sources. The FSM strategy couples the fuzzy logical strategy with a state machine strategy where the fuzzy logical strategy controls the power split between a fuel cell and a battery and the state machine deals with the power flow of photovoltaics and battery. To evaluate the FSM strategy, a simulation platform integrating the hybrid power system model and UAV model is developed with a Matlab/Simulink tool. An existed online thermostat control strategy for the same type of UAV is employed to compare with the proposed strategy based on the developed platform. The energy management process and the state of each power source are analyzed under a given mission scenario. The comparison of the two strategies about the power and energy contribution rates of each power source, the battery state of charge, and the hydrogen consumption is presented. The results indicate that the FSM strategy can satisfy the demand power effectively during the mission and performs better than the thermostat control strategy on power distribution and fuel consumption.


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## Body

## 1. Introduction

The hybrid electric UAVs in this paper are defined as the full electric UAVs powered by three or more kinds of power sources. In recent years, photovoltaic (PV) panels, fuel cells, and batteries are usually used as the electric propulsion energy. Heavily influenced by the climate, photovoltaic panels generally need to coordinate with batteries to power the UAVs which are called solar-powered UAVs. The relatively low energy density of batteries results in the extreme design of the solar-powered UAVs for a lighter structure weight. Fuel cells with higher energy density compared to batteries are potential for longer endurance. Due to soft electric characteristics and relatively slow response, the fuel cells are usually hybrid with batteries in the fuel cell-powered UAVs. Based on the principle of complementary advantages, the hybrid electric power system consisting with the photovoltaic, fuel cell, and battery power sources for UAVs has been proposed. Different dynamic characteristics of the three kinds of power sources make the hybrid power system more complicated. Thereby, a reasonable and efficient energy management is very important and necessary.Energy management strategies (EMS) determine the power allocation among different power sources and promote the energy efficiency and service life of the hybrid power system. In general, the energy management strategies can be classified into two categories [1]: optimization-based strategies and rule-based strategies. Optimization-based strategies include, dynamic programming (DP) [2–7], Pontryagin’s minimum principle (PMP) [8–10], genetic algorithm (GA) [11], and particle swarm optimization (PSO) [12]. Such optimal strategies usually can get the local or global optimal fuel economy. However, they cannot be used for online management because of the high computational cost. For real-time optimization, some instantaneous optimization strategies are proposed by introducing a cost function that depends only on the present state of the system parameters. Then the concept of energy consumption minimization strategy (ECMS) [13–16] and model predictive control (MPC) [17] is introduced for online optimal energy management of the hybrid electric vehicles. But for hybrid electric UAVs, they are still on research.Most online strategies for hybrid electric vehicles and UAVs are based on the rule-based strategies, mainly containing the fuzzy logical control (FCL) [18–24] and the state machine (SM) [25–29]. These strategies are easily implemented online to manage the power flow in the hybrid power system, because they can handle complex “black box” problems with low computational cost. Only a few of researchers tried to use the modified dynamic programming called the iterative dynamic programming (IDP) [30, 31] on the hybrid electric UAVs with an internal combustion engine and a motor as the hybrid propulsion system.For the full electric UAVs with different types of power sources, most researchers only considered two types of power sources, such as a fuel cell and a battery (FC + B) [32–37] or photovoltaics and a battery (PV + B) [38–44]. Very few of researchers concentrated on the hybrid PV/fuel cell/battery (PV + FC + B) [25, 29, 45, 46] power system as they are more complicated. So the rule-based strategies were mostly used as they are more suitable and easier to be implemented online. Li et al. [25, 47] and Lee et al. [28, 46] built a hybrid photovoltaic/fuel cell/battery power system for UAVs to estimate the behaviors of each power source using state machine strategy. However, their studies only developed the hybrid power system model with a given demand power profile and paid little attention to UAV models. The influence of the flight dynamic on the hybrid power system and energy management was not directly presented and analyzed. Zhang et al. [29] used the simple linear kinematic and dynamic UAV model to investigate the rule-based power tracking strategy for the PV + FC + B hybrid electric UAVs. But the UAV model was constrained in a vertical plane. Neither turns nor banks were considered. The EMS used in the three studies were all rule-based strategies with simple rules and limited applicability. To investigate more advanced online energy management strategies for PV + FC + B, a platform that can simulate the real flight of full electric UAVs is needed and necessary.In this study, a fuzzy state machine strategy combing the fuzzy logical control with the state machine strategy is proposed for PV + FC + B hybrid electric UAVs. To evaluate the FSM strategy, a closed loop simulation platform integrating the hybrid power system model and UAV model is developed to simulate the real flight conditions. The developed platform is also verified by comparing with the gasoline Aerosonde UAV model under a classical mission scenario. Based on such platform, the FSM strategy is compared with an existing online thermostat control strategy which has been implemented online for the same type of UAV. The comparison of the two strategies about the battery state of charge, the hydrogen consumption, and the power and energy contribution rates of each power source are discussed and analyzed.The rest of the paper is organized as follows: the fuzzy state machine strategy for hybrid electric UAVs is described in Section2, including the hybrid electric UAV framework and the details of the fuzzy state machine strategy. Section 3 provides the development and integration of the simulation platform containing the hybrid power system and the UAV model. Section 4 presents the simulation results and associated discussion including the comparison of the strategies. Finally, the conclusions are made in Section 5.


## 2. Fuzzy State Machine Strategy for Hybrid Electric UAVs

### 2.1. Sizing of Hybrid Electric UAV

The hybrid electric UAV is constructed by modifying the Aerosonde UAV [37] with the hybrid power system developed above to replace the GA propulsion system with an internal combustion (IC) engine. The Aerosonde UAV was developed by Aerosonde Pty Ltd. in Australia. To be comparable, the gross weight and aerodynamic configuration of the hybrid electric UAV remain the same with that of the IC engine Aerosonde UAV. The configuration sizes and weight breakdowns of the Aerosonde UAV and hybrid electric UAV are presented in Table 1.Table 1
Comparison of the Aerosonde UAV and hybrid electric UAV.
Aerosonde UAV
Hybrid electric UAV
Configuration size
Length (m)
1.74
Length (m)
1.74
Wingspan (m)
2.87
Wingspan (m)
2.87
Wing area (m2)
0.55
Wing area (m2)
0.55
Weight distribution (kg)
Airframe
3.6
Airframe
3.6
Avionics/payload
2.1
Avionics/payload
2.1
Fuel and fuel tank
5.6
H2 and tank
0.9
Power plant
2.2
BLDC motor
0.4
Electric speed controller
0.04
Propeller
0.06
Fuel cell
3
Li battery
0.9
PV panel
1
DCDC converter
1.2
MPPT
0.1
Flight controller
0.2
Gross weight
13.5
Gross weight
13.5As shown in Table1, the wing area is only 0.55 m2 which limits the photovoltaic panel available on board. That also means the photovoltaic panel will not be the main power source. To match the weight, the sizing of the fuel cell and that of the battery are both limited. The cruise power of the Aerosonde UAV determines the fuel cell size. The peak power demand and the climb phase give a reference for the sizing of the battery.


### 2.2. Hybrid Electric UAV Framework

The framework of the hybrid electric UAV contains four parts: energy system, energy management system, powertrain system, and airframe system as illustrated in Figure1. The energy system, energy management system, and powertrain system constitute the hybrid power system for the UAV. The energy system, including a hydrogen tank, a fuel cell (FC), a battery, photovoltaic panels (PV), and solar irradiance, provides electric energy for the powertrain system through the energy management system. The energy control unit (ECU) as the core processor of energy management system generates the current command for the DCDC converter and the maximum power point tracker (MPPT) based on the system state and power demand information from the current and voltage sensors, such as Batt CV and Bus CV. The DCDC and MPPT are the actuators to control the output power of FC and PV, respectively, and their output voltages are matched with the battery. The solar irradiance on the PV panel surface is influenced by the UAV flight state, such as bank, pitch, heading angles, and the latitude. The powertrain system includes a motor and a propeller to convert the electrical energy to mechanical energy and provides thrust and torque to the airframe system. The motor is controlled by the autopilot to generate the online demand power for the energy management system. The autopilot gets the flight state information from the UAV model and provides deflection angles for the control surfaces of the UAV. This framework can simulate the online situation at every flight moment with the causal relationship between demand power and energy management.Figure 1
Topology of the hybrid electric UAV framework.


### 2.3. Purposes of Energy Management Strategy

The energy management strategy (EMS), employed in the ECU module, must have the online potential to control the power flow among the PV panel, fuel cell, and battery based on the online situation provided by the hybrid electric UAV platform. The EMS also should take advantage of each power source based on their characteristics and state information. The criteria followed by the EMS are summarized as follows:(i)
The PV panel has the top priority to discharge. Through the MPPT, the PV panel always works at the maximum power point to provide energy as much as possible for flying or charging the battery.
(ii)
The battery, cooperating with the PV panel and fuel cell, makes up for surplus demand power. It is also responsible for sharp fluctuations of the power demand and peak power demand. The battery can be charged by the PV panel and fuel cell with a limited charge rate.
(iii)
The fuel cell generally has the lowest output priority to save the fuel for longer endurance.
(iv)
The DC bus demand power is always satisfied by the three kinds of power sources:(1)PD=Ppv+Pbatt+Pfc,where PD is the DC power demand and Ppv, Pbatt, and Pfc are the power extracted from the PV panel, battery, and fuel cell, respectively.


### 2.4. Implementation of Fuzzy State Machine

The fuzzy logical control algorithm coupled with the state machine strategy is proposed as the fuzzy state machine (FSM) strategy to enhance the online potential and adaptability of the energy management strategy. The implementation process of the FSM strategy is presented in Figure2. The state of charge (SOC) is from the battery model. The PpvMax from the PV panel model is the maximum available power of the PV panel on the wing. PD as the demand power of the DC bus can be calculated using
(2)PD=Ibus⋅Ubus=Ibus⋅Ubatt,where Ibus is the current through the BLDC motor and Ubus is the voltage of DC bus. Both of them are measured by the Bus CV sensor. Ubus is equal to the battery voltage Ubatt as the battery is directly connected on the DC bus in parallel.Figure 2
Fuzzy state machine energy management strategy.The FSM strategy used to determine the output of the PV panel and fuel cell has five states:State 1:
the maximum available power of the PV panel (PpvMax) is higher than the demand power (PD). That means the surplus demand power (Pd) is negative. The battery with a high state of charge does not need to be charged. The PV panel alone is selected to satisfy the power demand.
State 2:
the PV has the ability to satisfy the demand power. The redundant power from the PV panel for charging the battery is lower than the maximum charge power (Pchrg). Then the PV panel outputs its maximum power to meet the demand power and charge the battery.
State 3:
the maximum power from the PV panel is higher than the summation of demand power (PD) and maximum charge power (Pchrg). Then the output power of the PV panel equates to the power summation.
State 4:
the PV panel cannot satisfy the power demand alone. To save the fuel, the PV panel gives its maximum power. Then the fuzzy logical control algorithm is used to decide the desired output of fuel cellPF. Considering the constraints of the battery’s maximum charge rate, the fuel cell power is modified to be the summation of surplus demand power (Pd) and maximum charge power (Pchrg).
State 5:
the PV panel operates with maximum available power. And the desired fuel cell powerPF is under the constraint of (3); then the fuel cell will output the desired power.
(3)PF+PpvMax−PD<Pchrg.From state 1 to state 3, the EMS only uses the state machine strategy to deal with the output power of the PV panel and battery. The last two states couple with the fuzzy logical control strategy to control the output power of the fuel cell and battery. The PV power and fuel cell power are directly decided using the FSM strategy, but the battery power is derived automatically based on the power balance principle.


### 2.5. Fuzzy Logic Control

The fuzzy logical control has two input variables and one output variable, where the surplus demand powerPd and the state of charge SOC are the input variables and the desired fuel cell power is the output variable. The battery SOC is categorized into three different statuses called low (L), middle (M), and high (H). Similarly, the Pd is assigned into five regions: very high (VH), high (H), middle (M), low (L), and very low (VL). The fuzzy output PF is also defined in five statuses just like Pd, such as VH, H, M, L, and VL. The rule base which has 15 rules for the fuzzy logical control algorithm is given in Table 2. The membership functions of the Pd, SOC, and PF are given in Figures 3(a)–3(c), respectively. The fuel cell power rule base surface is presented in Figure 3(d). Mamdani’s fuzzy inference approach is used along with the centroid method for defuzzification.Table 2
Rule base of fuzzy logical control.
PF
Pd
VH
H
M
L
VL
SOC
L
VH
VH
H
M
L
M
VH
H
M
L
L
H
H
M
L
VL
VLFigure 3
Membership functions and rule base surface.
(a)
Surplus demand power membership functions
(b)
Battery SOC membership functions
(c)
Fuel cell power membership functions
(d)
Fuel cell-desired power rule base surfaceThe ECU module with the FSM strategy is modeled for the hybrid power system as shown in Figure4. The PD is calculated using the Ibus and Ubus which are measured at every time step. The EMS generates the reference current for the fuel cell and PV panel using the output power commands dividing the DC bus voltage. The battery will compensate the demand power automatically based on (1).Figure 4
Topology of ECU simulation module.


## 2.1. Sizing of Hybrid Electric UAV

The hybrid electric UAV is constructed by modifying the Aerosonde UAV [37] with the hybrid power system developed above to replace the GA propulsion system with an internal combustion (IC) engine. The Aerosonde UAV was developed by Aerosonde Pty Ltd. in Australia. To be comparable, the gross weight and aerodynamic configuration of the hybrid electric UAV remain the same with that of the IC engine Aerosonde UAV. The configuration sizes and weight breakdowns of the Aerosonde UAV and hybrid electric UAV are presented in Table 1.Table 1
Comparison of the Aerosonde UAV and hybrid electric UAV.
Aerosonde UAV
Hybrid electric UAV
Configuration size
Length (m)
1.74
Length (m)
1.74
Wingspan (m)
2.87
Wingspan (m)
2.87
Wing area (m2)
0.55
Wing area (m2)
0.55
Weight distribution (kg)
Airframe
3.6
Airframe
3.6
Avionics/payload
2.1
Avionics/payload
2.1
Fuel and fuel tank
5.6
H2 and tank
0.9
Power plant
2.2
BLDC motor
0.4
Electric speed controller
0.04
Propeller
0.06
Fuel cell
3
Li battery
0.9
PV panel
1
DCDC converter
1.2
MPPT
0.1
Flight controller
0.2
Gross weight
13.5
Gross weight
13.5As shown in Table1, the wing area is only 0.55 m2 which limits the photovoltaic panel available on board. That also means the photovoltaic panel will not be the main power source. To match the weight, the sizing of the fuel cell and that of the battery are both limited. The cruise power of the Aerosonde UAV determines the fuel cell size. The peak power demand and the climb phase give a reference for the sizing of the battery.


## 2.2. Hybrid Electric UAV Framework

The framework of the hybrid electric UAV contains four parts: energy system, energy management system, powertrain system, and airframe system as illustrated in Figure1. The energy system, energy management system, and powertrain system constitute the hybrid power system for the UAV. The energy system, including a hydrogen tank, a fuel cell (FC), a battery, photovoltaic panels (PV), and solar irradiance, provides electric energy for the powertrain system through the energy management system. The energy control unit (ECU) as the core processor of energy management system generates the current command for the DCDC converter and the maximum power point tracker (MPPT) based on the system state and power demand information from the current and voltage sensors, such as Batt CV and Bus CV. The DCDC and MPPT are the actuators to control the output power of FC and PV, respectively, and their output voltages are matched with the battery. The solar irradiance on the PV panel surface is influenced by the UAV flight state, such as bank, pitch, heading angles, and the latitude. The powertrain system includes a motor and a propeller to convert the electrical energy to mechanical energy and provides thrust and torque to the airframe system. The motor is controlled by the autopilot to generate the online demand power for the energy management system. The autopilot gets the flight state information from the UAV model and provides deflection angles for the control surfaces of the UAV. This framework can simulate the online situation at every flight moment with the causal relationship between demand power and energy management.Figure 1
Topology of the hybrid electric UAV framework.


## 2.3. Purposes of Energy Management Strategy

The energy management strategy (EMS), employed in the ECU module, must have the online potential to control the power flow among the PV panel, fuel cell, and battery based on the online situation provided by the hybrid electric UAV platform. The EMS also should take advantage of each power source based on their characteristics and state information. The criteria followed by the EMS are summarized as follows:(i)
The PV panel has the top priority to discharge. Through the MPPT, the PV panel always works at the maximum power point to provide energy as much as possible for flying or charging the battery.
(ii)
The battery, cooperating with the PV panel and fuel cell, makes up for surplus demand power. It is also responsible for sharp fluctuations of the power demand and peak power demand. The battery can be charged by the PV panel and fuel cell with a limited charge rate.
(iii)
The fuel cell generally has the lowest output priority to save the fuel for longer endurance.
(iv)
The DC bus demand power is always satisfied by the three kinds of power sources:(1)PD=Ppv+Pbatt+Pfc,where PD is the DC power demand and Ppv, Pbatt, and Pfc are the power extracted from the PV panel, battery, and fuel cell, respectively.


## 2.4. Implementation of Fuzzy State Machine

The fuzzy logical control algorithm coupled with the state machine strategy is proposed as the fuzzy state machine (FSM) strategy to enhance the online potential and adaptability of the energy management strategy. The implementation process of the FSM strategy is presented in Figure2. The state of charge (SOC) is from the battery model. The PpvMax from the PV panel model is the maximum available power of the PV panel on the wing. PD as the demand power of the DC bus can be calculated using
(2)PD=Ibus⋅Ubus=Ibus⋅Ubatt,where Ibus is the current through the BLDC motor and Ubus is the voltage of DC bus. Both of them are measured by the Bus CV sensor. Ubus is equal to the battery voltage Ubatt as the battery is directly connected on the DC bus in parallel.Figure 2
Fuzzy state machine energy management strategy.The FSM strategy used to determine the output of the PV panel and fuel cell has five states:State 1:
the maximum available power of the PV panel (PpvMax) is higher than the demand power (PD). That means the surplus demand power (Pd) is negative. The battery with a high state of charge does not need to be charged. The PV panel alone is selected to satisfy the power demand.
State 2:
the PV has the ability to satisfy the demand power. The redundant power from the PV panel for charging the battery is lower than the maximum charge power (Pchrg). Then the PV panel outputs its maximum power to meet the demand power and charge the battery.
State 3:
the maximum power from the PV panel is higher than the summation of demand power (PD) and maximum charge power (Pchrg). Then the output power of the PV panel equates to the power summation.
State 4:
the PV panel cannot satisfy the power demand alone. To save the fuel, the PV panel gives its maximum power. Then the fuzzy logical control algorithm is used to decide the desired output of fuel cellPF. Considering the constraints of the battery’s maximum charge rate, the fuel cell power is modified to be the summation of surplus demand power (Pd) and maximum charge power (Pchrg).
State 5:
the PV panel operates with maximum available power. And the desired fuel cell powerPF is under the constraint of (3); then the fuel cell will output the desired power.
(3)PF+PpvMax−PD<Pchrg.From state 1 to state 3, the EMS only uses the state machine strategy to deal with the output power of the PV panel and battery. The last two states couple with the fuzzy logical control strategy to control the output power of the fuel cell and battery. The PV power and fuel cell power are directly decided using the FSM strategy, but the battery power is derived automatically based on the power balance principle.


## 2.5. Fuzzy Logic Control

The fuzzy logical control has two input variables and one output variable, where the surplus demand powerPd and the state of charge SOC are the input variables and the desired fuel cell power is the output variable. The battery SOC is categorized into three different statuses called low (L), middle (M), and high (H). Similarly, the Pd is assigned into five regions: very high (VH), high (H), middle (M), low (L), and very low (VL). The fuzzy output PF is also defined in five statuses just like Pd, such as VH, H, M, L, and VL. The rule base which has 15 rules for the fuzzy logical control algorithm is given in Table 2. The membership functions of the Pd, SOC, and PF are given in Figures 3(a)–3(c), respectively. The fuel cell power rule base surface is presented in Figure 3(d). Mamdani’s fuzzy inference approach is used along with the centroid method for defuzzification.Table 2
Rule base of fuzzy logical control.
PF
Pd
VH
H
M
L
VL
SOC
L
VH
VH
H
M
L
M
VH
H
M
L
L
H
H
M
L
VL
VLFigure 3
Membership functions and rule base surface.
(a)
Surplus demand power membership functions
(b)
Battery SOC membership functions
(c)
Fuel cell power membership functions
(d)
Fuel cell-desired power rule base surfaceThe ECU module with the FSM strategy is modeled for the hybrid power system as shown in Figure4. The PD is calculated using the Ibus and Ubus which are measured at every time step. The EMS generates the reference current for the fuel cell and PV panel using the output power commands dividing the DC bus voltage. The battery will compensate the demand power automatically based on (1).Figure 4
Topology of ECU simulation module.


## 3. Development of Simulation Platform

### 3.1. Modeling of the Hybrid Power System

#### 3.1.1. Battery Model

In this study, a lithium-ion battery is used to store energy and quickly respond to demand power in the hybrid power system. With higher specific power, lithium-ion batteries remedy the limitation of fuel cells. The rechargeable characteristic enhances the utilization efficiency of the PV panel by storing the surplus solar energy when the power demand is low. The battery also provides a relatively stable operation voltage on DC bus for the BLDC motor. The dynamic model of the lithium-ion battery from the SimPowerSystems library in Matlab/Simulink is used and presented in(4)Discharge:Vbatt=E0−R0⋅ib−KQbQ−ibtibt+i∗+Aexp−B⋅ibt,Charge:Vbatt=E0−R0⋅ib−KQbibt−0.1Qb⋅i∗−KQbQb−ibt+Aexp−B⋅ibt,where Vbatt is the battery voltage, E0 is the constant voltage, K is the polarization constant, Qb is the maximum battery capacity, ibt=∫ibdt is the extracted capacity (Ah), A is the exponential voltage, B is the exponential capacity, R0 is the internal resistance, ib is the battery current, and i∗ is the filtered current. The state of charge (SOC) presents the battery state limited within [0, 1], where 1 indicates full charge and 0 means empty. The SOC is expressed in
(5)SOC=1−∫0tibdtQb.


#### 3.1.2. Solar Irradiance and PV Panel Model

As the UAV is flying, the solar irradiance on the PV panel varies with the maneuver. The PV panel surface is assumed to be flat. The incidence angle depends on the azimuth and zenith angles of the sun. The Euler angles and latitude decide the angle between sun rays and the PV panel. According to [48], the azimuth and zenith angles are described in
(6)sinαe=sinnlatsinδ+cosnlatcosδcosωt,sinαs=cosδsinωtcosαe,δ=0.4093sin2π284+n365,ωt=0.2618×12−tlocal,where αe and αs are the azimuth and zenith angles of the sun, respectively; nlat is the latitude of the UAV; δ is the declination angle of the sun; ωtis the hour of the sun; tlocal is the current hour of the day; and n is the date in the year.The expression of the incidence anglei is calculated by [49]
(7)cosi=SA→⋅Z→,where SA→ is the unit vector to the sun in the earth-fixed frame and Z→ is the aircraft-fixed vertical axis. The unit vector to the sun in the aircraft-fixed frame can be expressed in
(8)SA→=R1ϕR2θR3ψ⋅SE→,where the vector SE→ is the unit vector to the sun in the earth-fixed frame defined in
(9)SE→=cosαecosαscosαesinαssinαeTand R1, R2, and R3 are rotation matrices about the bank angle ϕ, pitch angle θ, and heading angle ψ, respectively. If the efficiency of the photovoltaic panel is assumed as a constant, the power of the PV panel is given in
(10)Ppv=ηmpptηpvQirrScosi,where ηpv is the efficiency of the photovoltaic panel, Qirr is the solar irradiance, S is the area of the PV panel on the wing surface, i is the incidence angle of sun rays, and ηmppt is the efficiency of the MPPT. So the PpvMax is equal to Ppv for the simplification of the MPPT model.


#### 3.1.3. Fuel Cell Model

The proton exchange membrane fuel cell (PEMFC) with high energy density and low operating temperature is suitable to power the electric UAV for long endurance. The dynamic fuel cell model used here is also from the SimPowerSystems library, but the model parameters are from our experiment. The fuel cell output voltageVfc is decided by the number of cells (ncell) in series and every single cell voltage (Vcell) as shown in
(11)Vfc=ncellVcell.The air and hydrogen flow rates are calculated by(12)UO2=60000RTNifczFPairVlpmairO2%,UH2=60000RTNifczFPH2VlpmH2H2%,where UO2 and UH2 are the rates of utilizations of oxygen and hydrogen, respectively, R is the universal gas constant 8.3145 J/(mol·K), F is the Faraday constant 96,485 As/mol, O2% is the percentage of oxygen in oxidant, T is the temperature, Pair is the absolute supply pressure of air, Vlpmair is the air flow rate, VlpmH2 is the H2 flow rate, H2% is the percentage of hydrogen in fuel, PH2 is the absolute supply pressure of fuel, and z is the number of moving electrons. The H2 gas is stored in a carbon fiber tank with a maximum pressure of 20 MPa. The state of pressure (SOP) is defined as the remnant H2 pressure in a tank can be calculated in
(13)SOP=P0−1Vol∫0tVlpmtdt,where P0 is the initial pressure of H2 in the tank, Vol is the tank volume, and Vlpmt is the H2 flow rate. When SOP is less than low pressure Plow, the fuel cell will stop working.


#### 3.1.4. Powertrain Model

The powertrain contains a BLDC motor and a fixed pitch propeller. The motor model is presented in(14)Im=Um−Ω/kvrm,Mm=Im−I030πkv,where Im and Um are the terminal voltage and current of the electric motor, respectively, rm is the terminal resistance, kv is the rotation speed constant, Ω is the rotation speed, Mm is the torque produced by the motor, and I0 is the idle current without load.The fixed pitch propeller is modeled as presented in(15)Fp=4π2ρR4Ω2CT,Mp=4π3ρR5Ω2CP,where Fp and Mp are the thrust and torque of the propeller, respectively, ρ is the air density, R is the radius of the propeller, Ω is also the rotation speed, and CT and CP are the thrust and power coefficients, respectively. When the motor drives the propeller, the dynamic model of the powertrain is given in (16), where J is the rotational inertia of the motor shaft and propeller.
(16)Mm−Mp=JΩ̇.The DCDC converter is modeled in(17)UoutIout=ηdcUinIin,where the Uout and Iout are the output voltage and current, Uin and Iin are the input voltage and current, and ηdc is the efficiency of the DCDC converter.


#### 3.1.5. Integration of the Hybrid Power System

By integrating these models presented above, the topology of the hybrid power system model is shown in Figure5. The fuel cell current is controlled by the DCDC converter. The simple DCDC converter and BLDC motor simulation models are shown in Figure 6.Figure 5
Topology of the hybrid power system.Figure 6
Topology of the DCDC converter and electric motor.
(a)
DCDC converter
(b)
Electric motor


### 3.2. Closed-Loop Simulation Platform of Hybrid Electric UAV

The closed-loop simulation platform of a hybrid electric UAV is developed with the AeroSim Blockset library in Matlab/Simulink as shown in Figure7. The general aviation (GA) engine propulsion system is replaced by the developed hybrid power system as shown in Figure 5. Except for the UAV model, the platform also contains the aircraft control module and flight planner module. Using the great circle navigation method, the flight planner module calculates the necessary bearing/yaw adjustment, target altitude, and target airspeed based on the waypoint information including the latitude, longitude, altitude, and airspeed. Then the UAV will trace the waypoints correctly. The aircraft control module uses the current and target position, altitude, and airspeed information to generate the throttle signal, rudder deflection angle, aileron deflection angle, and elevator deflection angle. The classical PID control algorithm is used in this module. The throttle range is between 0 and 1. The details of the autopilot model are given in [50].Figure 7
Closed loop simulation platform of the hybrid electric Aerosonde UAV.


### 3.3. Simulation Parameters

The mission scenario includes basic UAV operations such as climb, cruise, descent, and loiter. The waypoint information is listed in Table3 [50]. It is assumed that the takeoff time is 12:00 at noon on the summer solstice and the maximum irradiance of the day is 1200 W/m2.Table 3
Waypoint information of mission scenario.
Waypoint
Latitude
Longitude
Altitude (m)
Airspeed (m/s)
WP1 (origin)
26°34′51′′S
151°50′28′′E
800
20
WP2
26°33′58′′S
151°51′10′′E
900
20
WP3
26°34′08′′S
151°51′25′′E
900
20
WP4
26°34′18′′S
151°53′13′′E
750
30
WP5
26°34′08′′S
151°53′18′′E
750
20
WP6
26°33′59′′S
151°53′13′′E
750
20
WP7
26°34′08′′S
151°53′25′′E
900
20
WP8
26°34′14′′S
151°53′17′′E
900
20
WP9 (end)
26°34′51′′S
151°50′28′′E
800
30The initial parameters of the hybrid power system are listed in Table4 which includes the parameters of the battery, fuel cell, H2 tank, photovoltaic panel, motor, propeller, and DCDC converter. The propeller is still the same as the original Aerosonde UAV. The CT and CP of the propeller are given in [50]. The simulation used the ode14x solver with the fixed-step, and the step size is 0.1 s.Table 4
Initial parameters of the hybrid power system.
Power source
Parameters
Values
Unit
Battery
Nominal voltage
22.2
V
Rated capacity
6
Ah
Fully charged voltage
25.2
V
Cut-off voltage
21
V
Internal resistance
0.04
Ω
Capacity at nominal voltage
5.0
Ah
Exponential zone
[23.5, 1]
[V, Ah]
Initial state of charge
90
%
Maximum charge power
200
W
Fuel cell
Voltage at 0A and 1A
[37, 33.7]
V
Nominal operating point
[24, 25]
[A, V]
Maximum operating point
[23, 28]
[A, V]
Number of cells
41
—
Nominal stack efficiency
43
%
Operating temperature
50
°C
Nominal air flow rate
40
lpm
Nominal supply pressure [fuel, air]
[0.55, 1]
bar
Nominal composition [H2, O2, H2O (air)]
[99.95, 21, 1]
%
Volume of H2 tank
0.5
L
Purge water period
15
ms
Maximum H2 flow rate when purging water
40
lpm
Initial pressure in tank
200
bar
Out of fuel pressure in tank
2
bar
Photovoltaics
Solar irradiance
1200
W/m2
PV panel area
0.5
m2
PV efficiency
0.3
—
MPPT efficiency
0.98
—
Motor
Motor idle current
10
A at 10 V
Rotation speed constant
420
rpm/V
Motor internal resistance
33
mΩ
Motor shaft rotational inertia
0.0001
kg·m2
Propeller
Propeller diameter
0.254
m
Propeller rotational inertia
0.002
kg·m2
DCDC
Conversion efficiency
0.9
—
Output voltage
25
V


## 3.1. Modeling of the Hybrid Power System

### 3.1.1. Battery Model

In this study, a lithium-ion battery is used to store energy and quickly respond to demand power in the hybrid power system. With higher specific power, lithium-ion batteries remedy the limitation of fuel cells. The rechargeable characteristic enhances the utilization efficiency of the PV panel by storing the surplus solar energy when the power demand is low. The battery also provides a relatively stable operation voltage on DC bus for the BLDC motor. The dynamic model of the lithium-ion battery from the SimPowerSystems library in Matlab/Simulink is used and presented in(4)Discharge:Vbatt=E0−R0⋅ib−KQbQ−ibtibt+i∗+Aexp−B⋅ibt,Charge:Vbatt=E0−R0⋅ib−KQbibt−0.1Qb⋅i∗−KQbQb−ibt+Aexp−B⋅ibt,where Vbatt is the battery voltage, E0 is the constant voltage, K is the polarization constant, Qb is the maximum battery capacity, ibt=∫ibdt is the extracted capacity (Ah), A is the exponential voltage, B is the exponential capacity, R0 is the internal resistance, ib is the battery current, and i∗ is the filtered current. The state of charge (SOC) presents the battery state limited within [0, 1], where 1 indicates full charge and 0 means empty. The SOC is expressed in
(5)SOC=1−∫0tibdtQb.


### 3.1.2. Solar Irradiance and PV Panel Model

As the UAV is flying, the solar irradiance on the PV panel varies with the maneuver. The PV panel surface is assumed to be flat. The incidence angle depends on the azimuth and zenith angles of the sun. The Euler angles and latitude decide the angle between sun rays and the PV panel. According to [48], the azimuth and zenith angles are described in
(6)sinαe=sinnlatsinδ+cosnlatcosδcosωt,sinαs=cosδsinωtcosαe,δ=0.4093sin2π284+n365,ωt=0.2618×12−tlocal,where αe and αs are the azimuth and zenith angles of the sun, respectively; nlat is the latitude of the UAV; δ is the declination angle of the sun; ωtis the hour of the sun; tlocal is the current hour of the day; and n is the date in the year.The expression of the incidence anglei is calculated by [49]
(7)cosi=SA→⋅Z→,where SA→ is the unit vector to the sun in the earth-fixed frame and Z→ is the aircraft-fixed vertical axis. The unit vector to the sun in the aircraft-fixed frame can be expressed in
(8)SA→=R1ϕR2θR3ψ⋅SE→,where the vector SE→ is the unit vector to the sun in the earth-fixed frame defined in
(9)SE→=cosαecosαscosαesinαssinαeTand R1, R2, and R3 are rotation matrices about the bank angle ϕ, pitch angle θ, and heading angle ψ, respectively. If the efficiency of the photovoltaic panel is assumed as a constant, the power of the PV panel is given in
(10)Ppv=ηmpptηpvQirrScosi,where ηpv is the efficiency of the photovoltaic panel, Qirr is the solar irradiance, S is the area of the PV panel on the wing surface, i is the incidence angle of sun rays, and ηmppt is the efficiency of the MPPT. So the PpvMax is equal to Ppv for the simplification of the MPPT model.


### 3.1.3. Fuel Cell Model

The proton exchange membrane fuel cell (PEMFC) with high energy density and low operating temperature is suitable to power the electric UAV for long endurance. The dynamic fuel cell model used here is also from the SimPowerSystems library, but the model parameters are from our experiment. The fuel cell output voltageVfc is decided by the number of cells (ncell) in series and every single cell voltage (Vcell) as shown in
(11)Vfc=ncellVcell.The air and hydrogen flow rates are calculated by(12)UO2=60000RTNifczFPairVlpmairO2%,UH2=60000RTNifczFPH2VlpmH2H2%,where UO2 and UH2 are the rates of utilizations of oxygen and hydrogen, respectively, R is the universal gas constant 8.3145 J/(mol·K), F is the Faraday constant 96,485 As/mol, O2% is the percentage of oxygen in oxidant, T is the temperature, Pair is the absolute supply pressure of air, Vlpmair is the air flow rate, VlpmH2 is the H2 flow rate, H2% is the percentage of hydrogen in fuel, PH2 is the absolute supply pressure of fuel, and z is the number of moving electrons. The H2 gas is stored in a carbon fiber tank with a maximum pressure of 20 MPa. The state of pressure (SOP) is defined as the remnant H2 pressure in a tank can be calculated in
(13)SOP=P0−1Vol∫0tVlpmtdt,where P0 is the initial pressure of H2 in the tank, Vol is the tank volume, and Vlpmt is the H2 flow rate. When SOP is less than low pressure Plow, the fuel cell will stop working.


### 3.1.4. Powertrain Model

The powertrain contains a BLDC motor and a fixed pitch propeller. The motor model is presented in(14)Im=Um−Ω/kvrm,Mm=Im−I030πkv,where Im and Um are the terminal voltage and current of the electric motor, respectively, rm is the terminal resistance, kv is the rotation speed constant, Ω is the rotation speed, Mm is the torque produced by the motor, and I0 is the idle current without load.The fixed pitch propeller is modeled as presented in(15)Fp=4π2ρR4Ω2CT,Mp=4π3ρR5Ω2CP,where Fp and Mp are the thrust and torque of the propeller, respectively, ρ is the air density, R is the radius of the propeller, Ω is also the rotation speed, and CT and CP are the thrust and power coefficients, respectively. When the motor drives the propeller, the dynamic model of the powertrain is given in (16), where J is the rotational inertia of the motor shaft and propeller.
(16)Mm−Mp=JΩ̇.The DCDC converter is modeled in(17)UoutIout=ηdcUinIin,where the Uout and Iout are the output voltage and current, Uin and Iin are the input voltage and current, and ηdc is the efficiency of the DCDC converter.


### 3.1.5. Integration of the Hybrid Power System

By integrating these models presented above, the topology of the hybrid power system model is shown in Figure5. The fuel cell current is controlled by the DCDC converter. The simple DCDC converter and BLDC motor simulation models are shown in Figure 6.Figure 5
Topology of the hybrid power system.Figure 6
Topology of the DCDC converter and electric motor.
(a)
DCDC converter
(b)
Electric motor


## 3.1.1. Battery Model

In this study, a lithium-ion battery is used to store energy and quickly respond to demand power in the hybrid power system. With higher specific power, lithium-ion batteries remedy the limitation of fuel cells. The rechargeable characteristic enhances the utilization efficiency of the PV panel by storing the surplus solar energy when the power demand is low. The battery also provides a relatively stable operation voltage on DC bus for the BLDC motor. The dynamic model of the lithium-ion battery from the SimPowerSystems library in Matlab/Simulink is used and presented in(4)Discharge:Vbatt=E0−R0⋅ib−KQbQ−ibtibt+i∗+Aexp−B⋅ibt,Charge:Vbatt=E0−R0⋅ib−KQbibt−0.1Qb⋅i∗−KQbQb−ibt+Aexp−B⋅ibt,where Vbatt is the battery voltage, E0 is the constant voltage, K is the polarization constant, Qb is the maximum battery capacity, ibt=∫ibdt is the extracted capacity (Ah), A is the exponential voltage, B is the exponential capacity, R0 is the internal resistance, ib is the battery current, and i∗ is the filtered current. The state of charge (SOC) presents the battery state limited within [0, 1], where 1 indicates full charge and 0 means empty. The SOC is expressed in
(5)SOC=1−∫0tibdtQb.


## 3.1.2. Solar Irradiance and PV Panel Model

As the UAV is flying, the solar irradiance on the PV panel varies with the maneuver. The PV panel surface is assumed to be flat. The incidence angle depends on the azimuth and zenith angles of the sun. The Euler angles and latitude decide the angle between sun rays and the PV panel. According to [48], the azimuth and zenith angles are described in
(6)sinαe=sinnlatsinδ+cosnlatcosδcosωt,sinαs=cosδsinωtcosαe,δ=0.4093sin2π284+n365,ωt=0.2618×12−tlocal,where αe and αs are the azimuth and zenith angles of the sun, respectively; nlat is the latitude of the UAV; δ is the declination angle of the sun; ωtis the hour of the sun; tlocal is the current hour of the day; and n is the date in the year.The expression of the incidence anglei is calculated by [49]
(7)cosi=SA→⋅Z→,where SA→ is the unit vector to the sun in the earth-fixed frame and Z→ is the aircraft-fixed vertical axis. The unit vector to the sun in the aircraft-fixed frame can be expressed in
(8)SA→=R1ϕR2θR3ψ⋅SE→,where the vector SE→ is the unit vector to the sun in the earth-fixed frame defined in
(9)SE→=cosαecosαscosαesinαssinαeTand R1, R2, and R3 are rotation matrices about the bank angle ϕ, pitch angle θ, and heading angle ψ, respectively. If the efficiency of the photovoltaic panel is assumed as a constant, the power of the PV panel is given in
(10)Ppv=ηmpptηpvQirrScosi,where ηpv is the efficiency of the photovoltaic panel, Qirr is the solar irradiance, S is the area of the PV panel on the wing surface, i is the incidence angle of sun rays, and ηmppt is the efficiency of the MPPT. So the PpvMax is equal to Ppv for the simplification of the MPPT model.


## 3.1.3. Fuel Cell Model

The proton exchange membrane fuel cell (PEMFC) with high energy density and low operating temperature is suitable to power the electric UAV for long endurance. The dynamic fuel cell model used here is also from the SimPowerSystems library, but the model parameters are from our experiment. The fuel cell output voltageVfc is decided by the number of cells (ncell) in series and every single cell voltage (Vcell) as shown in
(11)Vfc=ncellVcell.The air and hydrogen flow rates are calculated by(12)UO2=60000RTNifczFPairVlpmairO2%,UH2=60000RTNifczFPH2VlpmH2H2%,where UO2 and UH2 are the rates of utilizations of oxygen and hydrogen, respectively, R is the universal gas constant 8.3145 J/(mol·K), F is the Faraday constant 96,485 As/mol, O2% is the percentage of oxygen in oxidant, T is the temperature, Pair is the absolute supply pressure of air, Vlpmair is the air flow rate, VlpmH2 is the H2 flow rate, H2% is the percentage of hydrogen in fuel, PH2 is the absolute supply pressure of fuel, and z is the number of moving electrons. The H2 gas is stored in a carbon fiber tank with a maximum pressure of 20 MPa. The state of pressure (SOP) is defined as the remnant H2 pressure in a tank can be calculated in
(13)SOP=P0−1Vol∫0tVlpmtdt,where P0 is the initial pressure of H2 in the tank, Vol is the tank volume, and Vlpmt is the H2 flow rate. When SOP is less than low pressure Plow, the fuel cell will stop working.


## 3.1.4. Powertrain Model

The powertrain contains a BLDC motor and a fixed pitch propeller. The motor model is presented in(14)Im=Um−Ω/kvrm,Mm=Im−I030πkv,where Im and Um are the terminal voltage and current of the electric motor, respectively, rm is the terminal resistance, kv is the rotation speed constant, Ω is the rotation speed, Mm is the torque produced by the motor, and I0 is the idle current without load.The fixed pitch propeller is modeled as presented in(15)Fp=4π2ρR4Ω2CT,Mp=4π3ρR5Ω2CP,where Fp and Mp are the thrust and torque of the propeller, respectively, ρ is the air density, R is the radius of the propeller, Ω is also the rotation speed, and CT and CP are the thrust and power coefficients, respectively. When the motor drives the propeller, the dynamic model of the powertrain is given in (16), where J is the rotational inertia of the motor shaft and propeller.
(16)Mm−Mp=JΩ̇.The DCDC converter is modeled in(17)UoutIout=ηdcUinIin,where the Uout and Iout are the output voltage and current, Uin and Iin are the input voltage and current, and ηdc is the efficiency of the DCDC converter.


## 3.1.5. Integration of the Hybrid Power System

By integrating these models presented above, the topology of the hybrid power system model is shown in Figure5. The fuel cell current is controlled by the DCDC converter. The simple DCDC converter and BLDC motor simulation models are shown in Figure 6.Figure 5
Topology of the hybrid power system.Figure 6
Topology of the DCDC converter and electric motor.
(a)
DCDC converter
(b)
Electric motor


## 3.2. Closed-Loop Simulation Platform of Hybrid Electric UAV

The closed-loop simulation platform of a hybrid electric UAV is developed with the AeroSim Blockset library in Matlab/Simulink as shown in Figure7. The general aviation (GA) engine propulsion system is replaced by the developed hybrid power system as shown in Figure 5. Except for the UAV model, the platform also contains the aircraft control module and flight planner module. Using the great circle navigation method, the flight planner module calculates the necessary bearing/yaw adjustment, target altitude, and target airspeed based on the waypoint information including the latitude, longitude, altitude, and airspeed. Then the UAV will trace the waypoints correctly. The aircraft control module uses the current and target position, altitude, and airspeed information to generate the throttle signal, rudder deflection angle, aileron deflection angle, and elevator deflection angle. The classical PID control algorithm is used in this module. The throttle range is between 0 and 1. The details of the autopilot model are given in [50].Figure 7
Closed loop simulation platform of the hybrid electric Aerosonde UAV.


## 3.3. Simulation Parameters

The mission scenario includes basic UAV operations such as climb, cruise, descent, and loiter. The waypoint information is listed in Table3 [50]. It is assumed that the takeoff time is 12:00 at noon on the summer solstice and the maximum irradiance of the day is 1200 W/m2.Table 3
Waypoint information of mission scenario.
Waypoint
Latitude
Longitude
Altitude (m)
Airspeed (m/s)
WP1 (origin)
26°34′51′′S
151°50′28′′E
800
20
WP2
26°33′58′′S
151°51′10′′E
900
20
WP3
26°34′08′′S
151°51′25′′E
900
20
WP4
26°34′18′′S
151°53′13′′E
750
30
WP5
26°34′08′′S
151°53′18′′E
750
20
WP6
26°33′59′′S
151°53′13′′E
750
20
WP7
26°34′08′′S
151°53′25′′E
900
20
WP8
26°34′14′′S
151°53′17′′E
900
20
WP9 (end)
26°34′51′′S
151°50′28′′E
800
30The initial parameters of the hybrid power system are listed in Table4 which includes the parameters of the battery, fuel cell, H2 tank, photovoltaic panel, motor, propeller, and DCDC converter. The propeller is still the same as the original Aerosonde UAV. The CT and CP of the propeller are given in [50]. The simulation used the ode14x solver with the fixed-step, and the step size is 0.1 s.Table 4
Initial parameters of the hybrid power system.
Power source
Parameters
Values
Unit
Battery
Nominal voltage
22.2
V
Rated capacity
6
Ah
Fully charged voltage
25.2
V
Cut-off voltage
21
V
Internal resistance
0.04
Ω
Capacity at nominal voltage
5.0
Ah
Exponential zone
[23.5, 1]
[V, Ah]
Initial state of charge
90
%
Maximum charge power
200
W
Fuel cell
Voltage at 0A and 1A
[37, 33.7]
V
Nominal operating point
[24, 25]
[A, V]
Maximum operating point
[23, 28]
[A, V]
Number of cells
41
—
Nominal stack efficiency
43
%
Operating temperature
50
°C
Nominal air flow rate
40
lpm
Nominal supply pressure [fuel, air]
[0.55, 1]
bar
Nominal composition [H2, O2, H2O (air)]
[99.95, 21, 1]
%
Volume of H2 tank
0.5
L
Purge water period
15
ms
Maximum H2 flow rate when purging water
40
lpm
Initial pressure in tank
200
bar
Out of fuel pressure in tank
2
bar
Photovoltaics
Solar irradiance
1200
W/m2
PV panel area
0.5
m2
PV efficiency
0.3
—
MPPT efficiency
0.98
—
Motor
Motor idle current
10
A at 10 V
Rotation speed constant
420
rpm/V
Motor internal resistance
33
mΩ
Motor shaft rotational inertia
0.0001
kg·m2
Propeller
Propeller diameter
0.254
m
Propeller rotational inertia
0.002
kg·m2
DCDC
Conversion efficiency
0.9
—
Output voltage
25
V


## 4. Results and Discussion

### 4.1. Hybrid Electric UAV Model Validation

The hybrid electric UAV model is verified by comparison with the original gasoline Aerosonde UAV in Matlab/Simulink under the same mission scenario. The comparison results are presented in Figures8 and 9. The top and side views of flight paths agree with each other for the two UAVs. The bank and heading angles of the UAVs are the same with each other. That is also the reason for the coincidence of top view paths. Figure 9(c) shows the pitch angles of the two UAVs are a little different during the transition from descent to level flight. That results in the difference of the transitional path as seen in Figure 8(b). The comparison of the two UAVs proves that the hybrid electric UAV model almost has the same performance with the original Aerosonde.Figure 8
Comparison of the flight path.
(a)
Top view of flight path
(b)
Side view of flight pathFigure 9
Comparison of the attitude angles.
(a)
Bank angle
(b)
Heading angle
(c)
Pitch angle


### 4.2. Energy Management Analysis

For the electric UAV, the flight height varying with time is presented in Figure10. During the mission, the energy management system with the proposed FMS strategy calculates the demand power and distributes the power among the three power sources as shown in Figure 11. Based on the mission scenario, the energy management process can be separated into seven stages from S1 to S7:
Stage 1
(S1): from waypoint 1 to waypoint 2 about 0–98 s, the UAV climbs from 800 m to 900 m then turns to level flight. During the climb, the demand power is about 1100 W much higher than the maximum power of the PV panel which has the highest priority to provide power. The surplus demand power is split between the battery and the fuel cell by the fuzzy logical control strategy. Since the initial SOC is high, the battery gives more power than the fuel cell. When reaching target altitude 900 m, the UAV turns to level flight, the demand power down to 620 W; the output power of the PV panel shows slight variations due to the decrease of the pitch angle. The output powers of the battery and fuel cell both fall down.
Stage 2
(S2): from waypoint 2 to waypoint 3 about 98–126 s, the UAV turns left and the bank angle significant changes at about 100 s. The power demand also arises a sudden change which is followed by the battery and fuel cell successfully. The bank angle results in a serious power loss of the PV panel.
Stage 3
(S3): from waypoint 3 to waypoint 4 about 126–265 s, the UAV changes from descent to level flight. In descent, it glides without any power in need. The power of the PV panel is higher than the demand power which means the PV panel can save the surplus energy by charging the battery. When approaching the target altitude 750 m, the UAV turns to level flight. The pitch angle oscillates heavily. The demand power also waves strongly. The outputs of the battery and fuel cell following the demand power present serious fluctuations, but the power of the PV panel presents light change. Then the UAV gives a long time stable level flight until reaching waypoint 4. Each power source provides a constant output during the level flight.
Stage 4
(S4): from waypoint 4 to waypoint 6 about 265–290 s, the UAV turns right three times in a short time which causes the variations of the demand power. The PV panel power fluctuates with the bank angle and heading angle. The surplus demand power is followed by the battery and fuel cell.
Stage 5
(S5): from waypoint 6 to waypoint 7 about 290–448 s, the UAV changes from climb to level flight. At the beginning of the climb, the demand power presents a sharp increase which is tracked by the battery as the demand power is much higher than the maximum power of the fuel cell and PV panel. During this climb, the demand power is up to 1100 W again; the fuel cell operates near the maximum power point, until the UAV is arriving at the target altitude 900 m. Then the UAV turns to level flight and the demand power decreases to 620 W, the output power of battery and fuel cell both decrease, and the PV panel still provides the maximum power to decrease the onboard fuel consumption.
Stage 6
(S6): from waypoint 7 to waypoint 8 about 448–460 s, the UAV turns right and the demand power changes slightly. The PV panel power varies with the Euler angles. The battery makes up the loss of PV panel, but the fuel cell output makes no change.
Stage 7
(S7): from waypoint 8 to waypoint 9 about 460–540 s, the UAV glides from 900 m to 800 m, then turns to level flight until reaching the end waypoint. During gliding, the battery is charged again by the PV panel. The fluctuation of the pitch angle during the turning maneuver causes the heavy change of power demand which is followed by the battery and fuel cell. The PV panel power remains relatively stable. After the turning, the UAV has a short level flight to reach waypoint 9 with a stable demand power. The output power of each power source is also stable.Figure 10
Height and velocity of the hybrid electric UAV.Figure 11
Demand power and power distribution.As an assumption, 60% of the SOC belongs to low level considering the battery health and the service life in practical application. Furthermore, to prevent the wind disturbance or other emergencies during the mission, the SOC should not be used too low. The battery SOC, hydrogen SOP, and the consumption flow rate of hydrogen during the mission are shown in Figure12(a). The SOC varies from 90% to 65% keeping in the ideal operating range. As the SOC decreases, the output power of the fuel cell is higher in the second climb than that in the first climb. The hydrogen in the tank is consumed from 200 bar down to 70 bar. Except for purging water at every 15 s, the hydrogen flow rate varies with the fuel cell power. About 35 g hydrogen is consumed in the mission. The irradiance on the PV panel surface and the output of PV panel are influenced by the flight attitude angles, especially the bank angle in this mission as shown in Figure 12(b).Figure 12
State of each power source.
(a)
State of the battery and fuel cell
(b)
Irradiance and power varying with bank angle


### 4.3. Comparison with Thermostat Control Strategy

To be compared with the proposed FSM strategy for the same mission, a constrained thermostat control (CTC) strategy proposed by Lee et al. [28] for the hybrid electric UAV using the same power sources is illustrated in Figure 13. The CTC maintains a certain SOC during the flight process in order to cope with the influence of the weather on the PV panel. The CTC also takes the PV panel as the highest priority output. The surplus power of the PV panel is used to charge the battery. When the SOC is higher than SOCL, the battery is used to make up the insufficient power of the PV panel and fuel cell during high power demand.Figure 13
Diagram of the constrained thermostat control strategy.The power contribution rate (PCR) and energy contribution rate (ECR), used to analyze the contribution of each power source, are defined as the output power and energy of each power source divided by the total consumed power and energy, respectively.The PCR and ECR of each power source for the FSM and CTC strategies are seen in Figure14. Figure 14(a) shows that the PCRs of the PV panel in both strategies are almost the same. When the demand power is zero, the PCRs of the battery, PV panel, and fuel cell for both strategies are the same, and they are −100%, 100%, and 0%, respectively. But the PCRs of the battery and the fuel cell for the two strategies are different. The PCR of the battery for FSM is higher than that for CTC during most time of the mission. Contrarily, the PCR of the fuel cell for FSM is lower than that for CTC.Figure 14
Power and energy contribution rates of each power source.
(a)
Power contribution rate
(b)
Energy contribution rateFor the battery and the fuel cell in the two strategies, different PCRs result in different ECRs as shown in Figure14(b). In the FSM test, the ECRs of the PV panel, battery, and fuel cell are 18%, 31%, and 51%, respectively. But in the CTC test, they are 17%, 15%, and 67%, respectively. The energies from the PV panel in the two strategy tests are almost the same. But the energy from the battery for FSM is more than twice as much as that for CTC. The energy from the fuel cell for CTC is obviously more than that for FSM.The state variations of the battery and the hydrogen in the two strategy tests are shown in Table5. With the same initial SOC and SOP, the battery is used more efficiently in the FSM test. Compared with the consumed hydrogen under the CTC strategy, less hydrogen is consumed for the FSM strategy. The amount of saved hydrogen fuel is 26.7% under the FSM strategy.Table 5
Comparison of the state of the battery and fuel cell between FSM and CTC.
SOC (%)
SOP (bar)
Consumed H2(L)
Initial
Final
Consumed
Initial
Final
Consumed
FSM
90
65
25
200
70
130
66
CTC
90
77
13
200
19
181
90


## 4.1. Hybrid Electric UAV Model Validation

The hybrid electric UAV model is verified by comparison with the original gasoline Aerosonde UAV in Matlab/Simulink under the same mission scenario. The comparison results are presented in Figures8 and 9. The top and side views of flight paths agree with each other for the two UAVs. The bank and heading angles of the UAVs are the same with each other. That is also the reason for the coincidence of top view paths. Figure 9(c) shows the pitch angles of the two UAVs are a little different during the transition from descent to level flight. That results in the difference of the transitional path as seen in Figure 8(b). The comparison of the two UAVs proves that the hybrid electric UAV model almost has the same performance with the original Aerosonde.Figure 8
Comparison of the flight path.
(a)
Top view of flight path
(b)
Side view of flight pathFigure 9
Comparison of the attitude angles.
(a)
Bank angle
(b)
Heading angle
(c)
Pitch angle


## 4.2. Energy Management Analysis

For the electric UAV, the flight height varying with time is presented in Figure10. During the mission, the energy management system with the proposed FMS strategy calculates the demand power and distributes the power among the three power sources as shown in Figure 11. Based on the mission scenario, the energy management process can be separated into seven stages from S1 to S7:
Stage 1
(S1): from waypoint 1 to waypoint 2 about 0–98 s, the UAV climbs from 800 m to 900 m then turns to level flight. During the climb, the demand power is about 1100 W much higher than the maximum power of the PV panel which has the highest priority to provide power. The surplus demand power is split between the battery and the fuel cell by the fuzzy logical control strategy. Since the initial SOC is high, the battery gives more power than the fuel cell. When reaching target altitude 900 m, the UAV turns to level flight, the demand power down to 620 W; the output power of the PV panel shows slight variations due to the decrease of the pitch angle. The output powers of the battery and fuel cell both fall down.
Stage 2
(S2): from waypoint 2 to waypoint 3 about 98–126 s, the UAV turns left and the bank angle significant changes at about 100 s. The power demand also arises a sudden change which is followed by the battery and fuel cell successfully. The bank angle results in a serious power loss of the PV panel.
Stage 3
(S3): from waypoint 3 to waypoint 4 about 126–265 s, the UAV changes from descent to level flight. In descent, it glides without any power in need. The power of the PV panel is higher than the demand power which means the PV panel can save the surplus energy by charging the battery. When approaching the target altitude 750 m, the UAV turns to level flight. The pitch angle oscillates heavily. The demand power also waves strongly. The outputs of the battery and fuel cell following the demand power present serious fluctuations, but the power of the PV panel presents light change. Then the UAV gives a long time stable level flight until reaching waypoint 4. Each power source provides a constant output during the level flight.
Stage 4
(S4): from waypoint 4 to waypoint 6 about 265–290 s, the UAV turns right three times in a short time which causes the variations of the demand power. The PV panel power fluctuates with the bank angle and heading angle. The surplus demand power is followed by the battery and fuel cell.
Stage 5
(S5): from waypoint 6 to waypoint 7 about 290–448 s, the UAV changes from climb to level flight. At the beginning of the climb, the demand power presents a sharp increase which is tracked by the battery as the demand power is much higher than the maximum power of the fuel cell and PV panel. During this climb, the demand power is up to 1100 W again; the fuel cell operates near the maximum power point, until the UAV is arriving at the target altitude 900 m. Then the UAV turns to level flight and the demand power decreases to 620 W, the output power of battery and fuel cell both decrease, and the PV panel still provides the maximum power to decrease the onboard fuel consumption.
Stage 6
(S6): from waypoint 7 to waypoint 8 about 448–460 s, the UAV turns right and the demand power changes slightly. The PV panel power varies with the Euler angles. The battery makes up the loss of PV panel, but the fuel cell output makes no change.
Stage 7
(S7): from waypoint 8 to waypoint 9 about 460–540 s, the UAV glides from 900 m to 800 m, then turns to level flight until reaching the end waypoint. During gliding, the battery is charged again by the PV panel. The fluctuation of the pitch angle during the turning maneuver causes the heavy change of power demand which is followed by the battery and fuel cell. The PV panel power remains relatively stable. After the turning, the UAV has a short level flight to reach waypoint 9 with a stable demand power. The output power of each power source is also stable.Figure 10
Height and velocity of the hybrid electric UAV.Figure 11
Demand power and power distribution.As an assumption, 60% of the SOC belongs to low level considering the battery health and the service life in practical application. Furthermore, to prevent the wind disturbance or other emergencies during the mission, the SOC should not be used too low. The battery SOC, hydrogen SOP, and the consumption flow rate of hydrogen during the mission are shown in Figure12(a). The SOC varies from 90% to 65% keeping in the ideal operating range. As the SOC decreases, the output power of the fuel cell is higher in the second climb than that in the first climb. The hydrogen in the tank is consumed from 200 bar down to 70 bar. Except for purging water at every 15 s, the hydrogen flow rate varies with the fuel cell power. About 35 g hydrogen is consumed in the mission. The irradiance on the PV panel surface and the output of PV panel are influenced by the flight attitude angles, especially the bank angle in this mission as shown in Figure 12(b).Figure 12
State of each power source.
(a)
State of the battery and fuel cell
(b)
Irradiance and power varying with bank angle


## 4.3. Comparison with Thermostat Control Strategy

To be compared with the proposed FSM strategy for the same mission, a constrained thermostat control (CTC) strategy proposed by Lee et al. [28] for the hybrid electric UAV using the same power sources is illustrated in Figure 13. The CTC maintains a certain SOC during the flight process in order to cope with the influence of the weather on the PV panel. The CTC also takes the PV panel as the highest priority output. The surplus power of the PV panel is used to charge the battery. When the SOC is higher than SOCL, the battery is used to make up the insufficient power of the PV panel and fuel cell during high power demand.Figure 13
Diagram of the constrained thermostat control strategy.The power contribution rate (PCR) and energy contribution rate (ECR), used to analyze the contribution of each power source, are defined as the output power and energy of each power source divided by the total consumed power and energy, respectively.The PCR and ECR of each power source for the FSM and CTC strategies are seen in Figure14. Figure 14(a) shows that the PCRs of the PV panel in both strategies are almost the same. When the demand power is zero, the PCRs of the battery, PV panel, and fuel cell for both strategies are the same, and they are −100%, 100%, and 0%, respectively. But the PCRs of the battery and the fuel cell for the two strategies are different. The PCR of the battery for FSM is higher than that for CTC during most time of the mission. Contrarily, the PCR of the fuel cell for FSM is lower than that for CTC.Figure 14
Power and energy contribution rates of each power source.
(a)
Power contribution rate
(b)
Energy contribution rateFor the battery and the fuel cell in the two strategies, different PCRs result in different ECRs as shown in Figure14(b). In the FSM test, the ECRs of the PV panel, battery, and fuel cell are 18%, 31%, and 51%, respectively. But in the CTC test, they are 17%, 15%, and 67%, respectively. The energies from the PV panel in the two strategy tests are almost the same. But the energy from the battery for FSM is more than twice as much as that for CTC. The energy from the fuel cell for CTC is obviously more than that for FSM.The state variations of the battery and the hydrogen in the two strategy tests are shown in Table5. With the same initial SOC and SOP, the battery is used more efficiently in the FSM test. Compared with the consumed hydrogen under the CTC strategy, less hydrogen is consumed for the FSM strategy. The amount of saved hydrogen fuel is 26.7% under the FSM strategy.Table 5
Comparison of the state of the battery and fuel cell between FSM and CTC.
SOC (%)
SOP (bar)
Consumed H2(L)
Initial
Final
Consumed
Initial
Final
Consumed
FSM
90
65
25
200
70
130
66
CTC
90
77
13
200
19
181
90


## 5. Conclusions

In this paper, a fuzzy state machine strategy with an online potential is proposed for PV + FC + B hybrid electric UAVs. A simulation platform integrating the hybrid power system model and UAV model is developed with a Matlab/Simulink tool. Based on such platform, the proposed FSM strategy is verified and compared with an existed online thermostat control strategy. The results of the study are summarized as follows:(1)
By comparison with the Aerosonde UAV, it indicates that the developed platform is reasonable and acceptable for energy management researches. The platform with a fixed-step size can generate the demand power at every time step for energy management strategies to simulate the online situation.
(2)
Under the FSM strategy, the PV panel generally provides its maximum available power which is only influenced by the flight attitude, especially the bank angle for this mission. The battery is charged by the PV panel during descent stages, and it can compensate for the surplus demand power or peak power demand. The fuel cell can automatically regulate its output power based on the demand power and battery SOC.
(3)
In both strategies, the ECRs show that the fuel cell as the main power source provides the most energy for the propulsion system and the PV panel as the additional power source outputs the least energy. The battery as the assist power source responses to high demand power and can be charged at low power demand.
(4)
The contribution of the PV panel for the FSM strategy is almost the same with that for the CTC strategy. The FSM strategy prefers to consume more battery energy than CTC does. Compared with the CTC strategy, less fuel cell energy is consumed in the FSM strategy which leads to 26.7% of the hydrogen fuel saved.



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*Source: 2852941-2018-07-02.xml*