# Power Management Strategy by Enhancing the Mission Profile Configuration of Solar-Powered Aircraft

Authors: Parvathy Rajendran; Kah Wee Lim; Kuan Theng Ong
Journal: International Journal of Aerospace Engineering
 (2016)

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## Abstract

Solar energy offers solar-powered unmanned aerial vehicle (UAV) the possibility of unlimited endurance. Some researchers have developed techniques to achieve perpetual flight by maximizing the power from the sun and by flying in accordance with its azimuth angles. However, flying in a path that follows the sun consumes more energy to sustain level flight. This study optimizes the overall power ratio by adopting the mission profile configuration of optimal solar energy exploitation. Extensive simulation is conducted to optimize and restructure the mission profile phases of UAV and to determine the optimal phase definition of the start, ascent, and descent periods, thereby maximizing the energy from the sun. In addition, a vertical cylindrical flight trajectory instead of maximizing the solar inclination angle has been adopted. This approach improves the net power ratio by 30.84% compared with other techniques. As a result, the battery weight may be massively reduced by 75.23%. In conclusion, the proposed mission profile configuration with the optimal power ratio of the trajectory of the path planning effectively prolongs UAV operation.


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## Body

## 1. Introduction

The current high endurance of UAV has been achieved by harvesting solar energy through photovoltaic cells [1–8]. The sun has been used as an inexhaustible source for the long-endurance flight of UAV. However, solar panels can generate power only at certain times during the day. Hence, rechargeable batteries have been introduced as secondary power storage to store the excess energy that can be discharged during nighttime. Moreover, an appropriate trajectory control in gravitational gliding during nighttime has been considered an efficient method to enhance flight endurance. The energy stored as gravitational potential energy and gained in height is used by the UAV to glide at night without any electrical power supply [3, 9].Some studies focus on UAV kinematics to enhance the performance of UAV. The bank angle of UAV is crucial for determining the incidence angle of the sun on the solar panel for optimal solar harvesting [10]. Other studies specify the heading angle and UAV attitude in flight maneuvers to compensate for the sun’s relative position for maximum solar harvesting [11, 12]. However, a flight path that “follows” the sun consumes additional energy.Another path planning method, also known as energy management strategy (EMS) [13, 14], has been studied to manage an efficient path for UAV using all the above methods. The idea of EMS is to divide the flight trajectory into three phases and utilize the solar energy that can be stored partly as gravitational potential energy during daytime. UAV harvests solar energy during daytime and gains gravitational potential energy that is employed during the gliding stage.The maximum sun inclination angle was determined by changing the UAV’s heading angle, which resulted in higher energy consumption because of the need for establishing a path following the sun [12]. Saghar and Mehran [2] also suggested that the potential energy harvested during the climb phase can be saved for further use. Another study focused on the trajectory along the surface of a vertical circular cylinder with optimized ascending and descending periods to increase the wing’s sun exposure [15]. However, its mission phases are yet to be optimized for better UAV endurance.There are also researches done that suggested that the power net gain can be maximized by referring to local solar spectral density from weather forecasts [16]. Nevertheless, flexible path planning was performed [17], where the path was selected based on the cost function. This plan enables solar-powered unmanned aerial vehicle (UAV) to conduct perpetual flights and even allows for planetary missions by using discretization to solve the approximations of optimal paths [18–20].Moreover, several works have ignored the upper and lower boundary limits of the battery’s state of charge (SOC). These limits must be between 0.25 and 0.90 to prolong the battery’s shelf life and fully utilize the battery pack installed in any UAV [14]. Furthermore, battery weight is approximately 30% of the overall weight of UAV [1, 8]. Thus, reducing battery weight may also significantly reduce the overall weight of UAV.Framed by these contexts, this study adopts the optimal mission phase configuration of solar-powered UAV to optimize energy harvesting with minimal power consumption, to maximize the overall net power ratio, and to reduce the battery weight. Here, an alternative approach is presented by adopting an optimal mission phase’s configuration with vertical cylindrical trajectory to increase the ratio of power gained to power consumed.The sun elevation angle has also been considered to optimize the phases of the UAV flight, which include cruise, ascent, and descent, and to maximize the energy from the sun. This optimization has also minimized the battery capacity required and enables the reduction of the battery weight to maintain perpetual flight. As a result, the overall power consumption is reduced as the overall weight of the UAV is reduced. In addition, the proposed strategy enables the UAV to fly at a low altitude trajectory to avoid the highly volatile wind region at higher altitudes [21].


## 2. Mathematical Model

### 2.1. Aircraft Trajectory

In this section, a recently developed aircraft trajectory model is elaborated [12]. In an inertial (x,y,z) Cartesian coordinate system shown in Figure 1, the 3D vectors of x(t), y(t), and z(t) are expressed as (1)–(3), respectively:(1)xt=rcos⁡φt,(2)yt=rsin⁡φt,(3)zt=zt-1+z˙t.Figure 1
Cartesian coordinate system [3].The aircraft is assumed to fly in still air with a constrained radiusr. The aircraft pitching angle θ and heading angle φ change according to the boundary condition of the optimal flight velocity VPowermin and ceiling altitude z. The vectors velocity V and acceleration a are expressed in terms of a moving coordinate system attached to the aircraft. The tangential, normal, and vertical components of velocity are expressed as Vt, Vn, and Vz using (4)–(6), respectively, whereas the corresponding acceleration equations are expressed as at, an, and az in (7)–(9), respectively [18]:(4)Vtt=rφ˙t,(5)Vnt=0,(6)Vzt=z˙t,(7)att=rφ¨t,(8)ant=rφ˙2t,(9)azt=z¨t.The flight path angleγt between the aircraft tangential and ascending velocity vectors [18] is measured as described in (10)γt=tan-1⁡VztVtt=tan-1⁡z˙trφ˙t.The optimum flight velocity is the velocity at the minimum required powerVPowermin (see (11)) to sustain a level flight [18]. The rate of change of the heading angle φ˙t (see (12)) is determined using this optimum flight velocity and the radius r constraint of the trajectory [18]:(11)VPowermin=4Kmg23CD0ρ∞2S24,(12)φ˙t=VPowerminr.


### 2.2. Aircraft Force and Equation of Motion

According to the Cartesian coordinate system, the equations of motions are derived from three axes, as shown in [18](13)mrφ¨=T-Dcos⁡γ+Lt,mrφ˙2=Ln,mz¨=-mg+T-Dsin⁡γ+Lz,where drag D and thrust T force are measured along the velocity vector. These equations can be rearranged to compute the corresponding lift required by the tangential, normal, and vertical components of velocity and the total lift expressed in (14)–(17), respectively [18]:(14)Lt=mrφ¨-T-Dcos⁡γ,(15)Ln=mrφ˙2,(16)Lz=mz¨+mg-T-Dsin⁡γ,(17)L=Lt2+Ln2+Lz2.


### 2.3. Aircraft Aerodynamics

The thrust vector is assumed to be aligned with the free-stream velocity, which satisfies the small angle of attack.K is the aerodynamic coefficient (see (18)), ρ∞ is the atmospheric density, V is the magnitude of velocity, e is the Oswald efficiency factor, AR is the aspect ratio of the wing, and α is the angle of attack [18]. Hence, the lift coefficient CL, drag coefficient CD, and drag force D can be derived and computed from (19)–(21), respectively:(18)K=1πeAR,(19)CL=2Lρ∞V2S=Cl0+Clα,(20)CD=CD0+KCL2,(21)D=12ρ∞V2SCD.


### 2.4. Energy Modeling

This section explains the energy gained and lost during a flight, where the energy required, gained, and lost during the flight is discussed in terms of charged and discharged battery capacity. The standard electric propulsion model is used to derive the power to sustain a flight, as shown in (22) [12]. Kinetic and potential energy are conserved and excluded from the energy model. Thus, the output energy Eout from the battery storage is shown in (23) [12]:(22)Pout=TVηprop,T≥00,T≤0,(23)Eout=∫t0tfPoutdt.In addition, the UAV is assumed to be fully mounted with solar cells on the wings, and the effective area of solar energy collection is assumed to beS, which is the area of the wing [11, 12]. The location and date are chosen to obtain the solar spectral density Psd and solar elevation angles, se. The flight path angle and angle of attack are integrated as pitch angle θ [12]:(24)θ=γ+α,(25)cos⁡i=cos⁡sesin⁡θsin⁡az-φ+sin⁡secos⁡θ.The solar inclinationi is calculated using (25) [12]. The solar power generated is a piecewise function (see (26)) [12]. This power depends on the conversion efficiency, which, in turn, depends on the temperature and incident solar radiation [22–24]. In addition, the conversion efficiency also depends on the spectral and angular selectivity of the PV cells [25]. Besides, the efficiency of this system may be improved when integrated with maximum power-point tracker and optimizing its speed control [26–28]. The power input Pin is considered zero when the inclination angle i is negative, where ηsol is the solar cell efficiency [24] and Psd is the solar spectral density [12]. Thus, the total energy input Ein is the integral component of the generated solar power, as shown in (27) [12]:(26)Pin=ηsolPsdScos⁡i,cos⁡i≥00,cos⁡i<0,(27)Ein=∫t0tfPindt.The battery power output and capacity are based on a lithium-sulfur rechargeable battery [11], with a battery pack mass and power output that can be expressed as (28)-(29), respectively [11]. The state of charge, SOC, represents the ratio of the current charge capacity to the maximum charge capacity of the battery pack. The upper and lower SOC boundaries are recommended for the health and safety of the battery life, as given by (30) [1, 7]. The SOC change rate SO˙C can be expressed as (31) [11]:(28)mbat=QVocηEb,(29)Pbat=-VocQSO˙C-RQSO˙C2,(30)0.25C≤SOC≤0.90C,(31)SO˙C=-Voc-Voc2-4PbatR2QR3600.The performance of the battery is affected by temperature. However, the working temperature is in the range of low altitude temperature. Battery discharge and charge temperature’s lowest boundary is −20°C. This temperature allows the battery to operate efficiently until the altitude of 5500 m, which is lower than the assumed ceiling altitude.


## 2.1. Aircraft Trajectory

In this section, a recently developed aircraft trajectory model is elaborated [12]. In an inertial (x,y,z) Cartesian coordinate system shown in Figure 1, the 3D vectors of x(t), y(t), and z(t) are expressed as (1)–(3), respectively:(1)xt=rcos⁡φt,(2)yt=rsin⁡φt,(3)zt=zt-1+z˙t.Figure 1
Cartesian coordinate system [3].The aircraft is assumed to fly in still air with a constrained radiusr. The aircraft pitching angle θ and heading angle φ change according to the boundary condition of the optimal flight velocity VPowermin and ceiling altitude z. The vectors velocity V and acceleration a are expressed in terms of a moving coordinate system attached to the aircraft. The tangential, normal, and vertical components of velocity are expressed as Vt, Vn, and Vz using (4)–(6), respectively, whereas the corresponding acceleration equations are expressed as at, an, and az in (7)–(9), respectively [18]:(4)Vtt=rφ˙t,(5)Vnt=0,(6)Vzt=z˙t,(7)att=rφ¨t,(8)ant=rφ˙2t,(9)azt=z¨t.The flight path angleγt between the aircraft tangential and ascending velocity vectors [18] is measured as described in (10)γt=tan-1⁡VztVtt=tan-1⁡z˙trφ˙t.The optimum flight velocity is the velocity at the minimum required powerVPowermin (see (11)) to sustain a level flight [18]. The rate of change of the heading angle φ˙t (see (12)) is determined using this optimum flight velocity and the radius r constraint of the trajectory [18]:(11)VPowermin=4Kmg23CD0ρ∞2S24,(12)φ˙t=VPowerminr.


## 2.2. Aircraft Force and Equation of Motion

According to the Cartesian coordinate system, the equations of motions are derived from three axes, as shown in [18](13)mrφ¨=T-Dcos⁡γ+Lt,mrφ˙2=Ln,mz¨=-mg+T-Dsin⁡γ+Lz,where drag D and thrust T force are measured along the velocity vector. These equations can be rearranged to compute the corresponding lift required by the tangential, normal, and vertical components of velocity and the total lift expressed in (14)–(17), respectively [18]:(14)Lt=mrφ¨-T-Dcos⁡γ,(15)Ln=mrφ˙2,(16)Lz=mz¨+mg-T-Dsin⁡γ,(17)L=Lt2+Ln2+Lz2.


## 2.3. Aircraft Aerodynamics

The thrust vector is assumed to be aligned with the free-stream velocity, which satisfies the small angle of attack.K is the aerodynamic coefficient (see (18)), ρ∞ is the atmospheric density, V is the magnitude of velocity, e is the Oswald efficiency factor, AR is the aspect ratio of the wing, and α is the angle of attack [18]. Hence, the lift coefficient CL, drag coefficient CD, and drag force D can be derived and computed from (19)–(21), respectively:(18)K=1πeAR,(19)CL=2Lρ∞V2S=Cl0+Clα,(20)CD=CD0+KCL2,(21)D=12ρ∞V2SCD.


## 2.4. Energy Modeling

This section explains the energy gained and lost during a flight, where the energy required, gained, and lost during the flight is discussed in terms of charged and discharged battery capacity. The standard electric propulsion model is used to derive the power to sustain a flight, as shown in (22) [12]. Kinetic and potential energy are conserved and excluded from the energy model. Thus, the output energy Eout from the battery storage is shown in (23) [12]:(22)Pout=TVηprop,T≥00,T≤0,(23)Eout=∫t0tfPoutdt.In addition, the UAV is assumed to be fully mounted with solar cells on the wings, and the effective area of solar energy collection is assumed to beS, which is the area of the wing [11, 12]. The location and date are chosen to obtain the solar spectral density Psd and solar elevation angles, se. The flight path angle and angle of attack are integrated as pitch angle θ [12]:(24)θ=γ+α,(25)cos⁡i=cos⁡sesin⁡θsin⁡az-φ+sin⁡secos⁡θ.The solar inclinationi is calculated using (25) [12]. The solar power generated is a piecewise function (see (26)) [12]. This power depends on the conversion efficiency, which, in turn, depends on the temperature and incident solar radiation [22–24]. In addition, the conversion efficiency also depends on the spectral and angular selectivity of the PV cells [25]. Besides, the efficiency of this system may be improved when integrated with maximum power-point tracker and optimizing its speed control [26–28]. The power input Pin is considered zero when the inclination angle i is negative, where ηsol is the solar cell efficiency [24] and Psd is the solar spectral density [12]. Thus, the total energy input Ein is the integral component of the generated solar power, as shown in (27) [12]:(26)Pin=ηsolPsdScos⁡i,cos⁡i≥00,cos⁡i<0,(27)Ein=∫t0tfPindt.The battery power output and capacity are based on a lithium-sulfur rechargeable battery [11], with a battery pack mass and power output that can be expressed as (28)-(29), respectively [11]. The state of charge, SOC, represents the ratio of the current charge capacity to the maximum charge capacity of the battery pack. The upper and lower SOC boundaries are recommended for the health and safety of the battery life, as given by (30) [1, 7]. The SOC change rate SO˙C can be expressed as (31) [11]:(28)mbat=QVocηEb,(29)Pbat=-VocQSO˙C-RQSO˙C2,(30)0.25C≤SOC≤0.90C,(31)SO˙C=-Voc-Voc2-4PbatR2QR3600.The performance of the battery is affected by temperature. However, the working temperature is in the range of low altitude temperature. Battery discharge and charge temperature’s lowest boundary is −20°C. This temperature allows the battery to operate efficiently until the altitude of 5500 m, which is lower than the assumed ceiling altitude.


## 3. Mission Profile Strategy

A solar-powered aircraft mission profile is generally divided into three main phases: cruise, ascent, and descent. During the cruise flight, the UAV employs energy from the battery to sustain a level cruise flight. The ascent flight begins when the UAV starts to gain its gravitational potential energy and stores the excess energy fed into the battery. The descent flight of the UAV occurs when the aircraft starts to glide without using any power source. The power required to control the surface operation may also be disregarded. The UAV continues to cruise when it reaches an initial altitude of 100 m. The mission phases are illustrated in Figure2.Figure 2
Mission phase.


### 3.1. Phase X: Cruise Flight

At cruise, the aircraft begins to discharge the battery with the minimum power required to sustain a level flight. In this simulation, the altitude is set to clearance of 100 m to avoid geographical obstruction. The UAV is also set to fly at the minimum power to maximize the UAV’s endurance in this phase. In addition, the finalSOC of this phase is not lower than the battery SOC boundary of 0.25C, as recommended by previous researchers [1, 7, 8].


### 3.2. Phase Y: Ascent Flight

In the ascent phase, the UAV climbs steadily with the available excess power at a speed that can be calculated using (32). The UAV is constrained by a radius r. Thus, the bank angle, angle of attack, and flight path angle of the UAV vary accordingly. In this phase, the flight is estimated to harvest more energy than the consumed energy. Hence the net energy is positive:(32)z˙=ceilingDaylight time.


### 3.3. Phase Z: Descent Flight

In this phase, the UAV starts to employ the gravitational potential energy collected during the ascent phase for unpowered glide. Thus, it is assumed that the UAV does not consume any power to sustain its level flight during the descent phase. The minimal descent rateVsinkmin is desirable for maximizing the UAV’s endurance. Thus, the UAV must maintain its flight at the maximum CL3/2/CD to obtain a minimal sink rate [18]. The ratio CL3/2/CD and Vsinkmin are defined in (33) and (34), respectively [18]:(33)CL3/2CD=143KCD03/4,(34)Vsinkmin=1CL3/2/CDmax2ρ∞mgS.


### 3.4. Proposed Power Management Strategy

The proposed power management strategy for the mission profile configuration aims to optimize the time management of the mission phase with respect to the elevation angles of the sun to maximize solar energy. Flying according to the sun’s inclination angle does not significantly affect energy efficiency because this consumes more power than the amount of energy generated from the sun.The adaptation of a vertical cylindrical trajectory minimizes the battery mass. Hence an optimal net power is obtained during the flight. Moreover, this study adopts an additional element by defining the optimal time of mission transition in relation to the elevation angle of the sun to improve the overall power ratio gained. This structure of the mission phases, in which the start-end-time of the ascent, cruise, and descent phases of a flight are defined, leads to better energy savings and therefore improves aircraft endurance.The three phases are looped in the time function for 24 hours, starting from 0:15 hours until 00:00 hours at the interval of 15 minutes to obtain the optimal time to start each phase. Although the elevation angle and intensity of the sun differ at each hour, the UAV still flies according to the planned path without following the sun’s angle. Thus, no extra energy is used in the performance of the sun-following maneuver, but changes in solar intensity over time are utilized to improve the final performance.


## 3.1. Phase X: Cruise Flight

At cruise, the aircraft begins to discharge the battery with the minimum power required to sustain a level flight. In this simulation, the altitude is set to clearance of 100 m to avoid geographical obstruction. The UAV is also set to fly at the minimum power to maximize the UAV’s endurance in this phase. In addition, the finalSOC of this phase is not lower than the battery SOC boundary of 0.25C, as recommended by previous researchers [1, 7, 8].


## 3.2. Phase Y: Ascent Flight

In the ascent phase, the UAV climbs steadily with the available excess power at a speed that can be calculated using (32). The UAV is constrained by a radius r. Thus, the bank angle, angle of attack, and flight path angle of the UAV vary accordingly. In this phase, the flight is estimated to harvest more energy than the consumed energy. Hence the net energy is positive:(32)z˙=ceilingDaylight time.


## 3.3. Phase Z: Descent Flight

In this phase, the UAV starts to employ the gravitational potential energy collected during the ascent phase for unpowered glide. Thus, it is assumed that the UAV does not consume any power to sustain its level flight during the descent phase. The minimal descent rateVsinkmin is desirable for maximizing the UAV’s endurance. Thus, the UAV must maintain its flight at the maximum CL3/2/CD to obtain a minimal sink rate [18]. The ratio CL3/2/CD and Vsinkmin are defined in (33) and (34), respectively [18]:(33)CL3/2CD=143KCD03/4,(34)Vsinkmin=1CL3/2/CDmax2ρ∞mgS.


## 3.4. Proposed Power Management Strategy

The proposed power management strategy for the mission profile configuration aims to optimize the time management of the mission phase with respect to the elevation angles of the sun to maximize solar energy. Flying according to the sun’s inclination angle does not significantly affect energy efficiency because this consumes more power than the amount of energy generated from the sun.The adaptation of a vertical cylindrical trajectory minimizes the battery mass. Hence an optimal net power is obtained during the flight. Moreover, this study adopts an additional element by defining the optimal time of mission transition in relation to the elevation angle of the sun to improve the overall power ratio gained. This structure of the mission phases, in which the start-end-time of the ascent, cruise, and descent phases of a flight are defined, leads to better energy savings and therefore improves aircraft endurance.The three phases are looped in the time function for 24 hours, starting from 0:15 hours until 00:00 hours at the interval of 15 minutes to obtain the optimal time to start each phase. Although the elevation angle and intensity of the sun differ at each hour, the UAV still flies according to the planned path without following the sun’s angle. Thus, no extra energy is used in the performance of the sun-following maneuver, but changes in solar intensity over time are utilized to improve the final performance.


## 4. Results and Discussion

The power ratio andSOC obtained at each simulation are analyzed to determine the optimal mission profile configuration. The result shows that the power management strategy improves the net power ratio of a solar-powered UAV (i.e., aircraft specification given in Table 1),  as discussed in the following subsection. Section 4.2 illustrates the simulation scheme to analyze the feasibility of perpetual flight.Table 1
UAV model data.
Parameter Value C D 0 0.011 η p r o p 0.7 η s o l 0.22 b 0.711 m S 0.1566m2 η E b 0.992 Aircraft weight 4.201 N m b a t 0.317 N Q 7.65 Ah V o c 12.6 V R 0.0125ΩThe proposed power management strategy also sustains the perpetual flight capabilities of the solar-powered UAV. However, the results in Sections4.1 and 4.2 do not take into consideration the change in atmosphere condition. Here, the crucial parameters which affect the system include the temperature, especially on the conversion efficiency of solar energy and the density of air, which relates to the flow of air around the aircraft. This assumption made in the simulation results intends to make similar comparison with existing trajectory models as discussed in Sections 4.1 and 4.2.


### 4.1. 24-Hour Mission Simulation

The trend of the power ratio with the start hours of the cruise phase is illustrated in Figure3. The plotted data indicate that a high power ratio is obtained from the 0.25th hour until the 8.5th hour with the highest power ratio at approximately 1.71. This power ratio is achieved again from the 14th to the 24th hour. Hence, this time region of the optimal power ratio is the best for a cruise flight. This finding also emphasizes that the region of the 9th to 13th hour is unfavorable for a cruise flight. Figure 4 presents the power ratio achieved when the UAV begins to ascend. The power ratio fluctuates. However, four peaks of the net power ratio emerge, with an approximate value of 1.71 if the ascent begins at the 8th, 14th, 32nd, and 37th hours of flight.Figure 3
Trend of the power ratio at the initialization of the cruise phase.Figure 4
Trend of the power ratio at the initialization of the ascent phase.The trend of the power ratio at the initialization of the descent phase is shown in Figure5. Similar to that in the ascent phase, the power ratio at the beginning of the descent phase fluctuates over time. In this instance, the highest net power ratio obtained is approximately 1.71 at the four peaks, during the 13th, 19th, 37th, and 43rd hours of the descent phase. The simulation results are also plotted in 3D to analyze the trend line of the power ratio for a few phase combinations. These plots help determine the suitable combination of start times for the phases to obtain the optimum power ratio. For instance, Figure 6 illustrates the combination of start times for the cruise and descent phases and the corresponding power ratios that can be achieved.Figure 5
Trend of the power ratio at the initialization of the descent phase.Figure 6
Trend of the power ratio with respect to the start time of the cruise and descent phases.Figure7 shows the combination of the start times for the cruise and ascent phases to determine the optimum power ratio. The trend line of the power ratio for the combination of the start times of the cruise and descent phases and cruise and ascent phases fluctuates throughout the time of flight. However, for the combination of the start times of the ascent and descent phases shown in Figure 8, the maximum achievable power ratio is quite constant at approximately 1.71. Thus, the start times of the ascent and descent phases do not significantly affect the power ratio compared with the start time of the cruise phase.Figure 7
Trend of the power ratio with respect to the start times of the cruise and ascent phases.Figure 8
Trend of the power ratio with respect to the start times of the ascent and descent phases.Based on these simulation results, the optimum region for UAV to cruise is from the 0.25th hour to the 8.5th hour and from the 14th hour to the 24th hour. The best point for the UAV to ascend is at the interval of the 8th hour to the 14th hour. The optimum region for the descent phase is the region of the 13th hour to the 19th hour. The region of the optimal mission profile phases over time is illustrated in Figure9.Figure 9
Recommended mission profile phase region.The recommended mission profile trajectory obtained based on the extensive simulation is plotted in Figure10. Here, the cruise phase of the UAV begins at the 0.25th hour, when the solar elevation angle is −72.88°. The UAV continues to cruise until the 8th hour, when the solar elevation angle is 8.55°. At this point, the UAV is recommended to begin its ascent flight with a minimum climb rate to gain gravitational potential energy. At the 13.25th hour, when the solar elevation angle is 75.06°, the UAV reaches the optimal time to descend without consuming any power. The descent phase ends when the UAV reaches its initial altitude.Figure 10
Recommended mission trajectory.A comparison of theSOC for the proposed model and a previous model [11] for a simulated 24-hour flight mission using the same UAV model (Table 1) is presented in Figure 11. The minimum SOC is achieved using the proposed model with a value of 0.6308C, which is slightly lower than the original value by 0.32%. This result indicates that the proposed model exhibits better battery utilization than the original model. Moreover, the recommended lower SOC limit for a rechargeable lithium polymer battery is 0.25C [1, 7].Figure 11
Battery SOC for a 24-hour flight.A detailed comparison of the parameters of the proposed and previous models is given in Table2. The proposed model improves the net power ratio by 30.84%. This value can reach 31.04 megawatts for UAV operations over a year. By adopting the proposed power management strategy, UAV operations at a lower altitude may avoid the highly volatile wind region.Table 2
24-hour flight mission performance data.
Parameters Original model Proposed model Improvement (%) Power ratio 1.3070 1.7101 30.84 Ceiling altitude (m) 8  ×  10 3 3.5961  ×   10 3 55.04A comparison of the power ratio performance of the proposed power management strategy and that of various approaches [3, 9, 12] is listed in Table 3. The concept of the proposed strategy significantly improves the power ratio by at least 30.84% relative to the other approaches for perpetual solar-powered UAV missions. Hence, the proposed power management strategy may be a potential alternative for solar-powered UAV operations.Table 3
Comparison of the proposed model with different approaches.
Approaches Power ratio Improvement (%) Flight performance parameters [3] 1.0300 66.03 Aircraft parameters optimization [12] 1.1125 53.71 Energy management system [9] 1.3070 30.84 Proposed power management strategy 1.7101 —


### 4.2. 72-Hour Perpetual Mission Simulation

A case study for a perpetual flight mission was simulated using the proposed power management strategy. This step is crucial for determining whether or not the battery pack contains sufficientSOC continuously for a sustainable powered flight. Thus, a simulation is conducted for a 72-hour mission to validate whether or not the minimal battery SOC stays within the preset boundary, as shown in Figure 12.Figure 12
Battery SOC for 72 hours.The simulation of a 72-hour perpetual mission achieved a power ratio of 1.7100, which is slightly lower than that of a 24-hour flight mission. However, this difference is almost negligible. TheSOC battery level maintained a consistent cycle for more than 48 hours during the first day at a fully charged state. This result further reaffirms the possibility of operating self-sustainable solar-powered UAV missions for months and even years.In addition, the minimal batterySOC level remained effectively within the boundary, with a value of 0.4348C. As mentioned earlier, a fully utilized battery is recommended to be 0.25–0.90C. Thus, in this case study, battery weight was significantly reduced from 1.28 N to 0.317 N as shown in Figure 13. Here, s total of 75.23% of the battery’s weight was reduced. Since UAV battery weight is roughly 30% of the overall take-off weight of UAV, the overall weight of the UAV can be reduced by 22.57%. This finding further affirms the potential of the new model to achieve perpetual flight.Figure 13
Battery weight comparison.


## 4.1. 24-Hour Mission Simulation

The trend of the power ratio with the start hours of the cruise phase is illustrated in Figure3. The plotted data indicate that a high power ratio is obtained from the 0.25th hour until the 8.5th hour with the highest power ratio at approximately 1.71. This power ratio is achieved again from the 14th to the 24th hour. Hence, this time region of the optimal power ratio is the best for a cruise flight. This finding also emphasizes that the region of the 9th to 13th hour is unfavorable for a cruise flight. Figure 4 presents the power ratio achieved when the UAV begins to ascend. The power ratio fluctuates. However, four peaks of the net power ratio emerge, with an approximate value of 1.71 if the ascent begins at the 8th, 14th, 32nd, and 37th hours of flight.Figure 3
Trend of the power ratio at the initialization of the cruise phase.Figure 4
Trend of the power ratio at the initialization of the ascent phase.The trend of the power ratio at the initialization of the descent phase is shown in Figure5. Similar to that in the ascent phase, the power ratio at the beginning of the descent phase fluctuates over time. In this instance, the highest net power ratio obtained is approximately 1.71 at the four peaks, during the 13th, 19th, 37th, and 43rd hours of the descent phase. The simulation results are also plotted in 3D to analyze the trend line of the power ratio for a few phase combinations. These plots help determine the suitable combination of start times for the phases to obtain the optimum power ratio. For instance, Figure 6 illustrates the combination of start times for the cruise and descent phases and the corresponding power ratios that can be achieved.Figure 5
Trend of the power ratio at the initialization of the descent phase.Figure 6
Trend of the power ratio with respect to the start time of the cruise and descent phases.Figure7 shows the combination of the start times for the cruise and ascent phases to determine the optimum power ratio. The trend line of the power ratio for the combination of the start times of the cruise and descent phases and cruise and ascent phases fluctuates throughout the time of flight. However, for the combination of the start times of the ascent and descent phases shown in Figure 8, the maximum achievable power ratio is quite constant at approximately 1.71. Thus, the start times of the ascent and descent phases do not significantly affect the power ratio compared with the start time of the cruise phase.Figure 7
Trend of the power ratio with respect to the start times of the cruise and ascent phases.Figure 8
Trend of the power ratio with respect to the start times of the ascent and descent phases.Based on these simulation results, the optimum region for UAV to cruise is from the 0.25th hour to the 8.5th hour and from the 14th hour to the 24th hour. The best point for the UAV to ascend is at the interval of the 8th hour to the 14th hour. The optimum region for the descent phase is the region of the 13th hour to the 19th hour. The region of the optimal mission profile phases over time is illustrated in Figure9.Figure 9
Recommended mission profile phase region.The recommended mission profile trajectory obtained based on the extensive simulation is plotted in Figure10. Here, the cruise phase of the UAV begins at the 0.25th hour, when the solar elevation angle is −72.88°. The UAV continues to cruise until the 8th hour, when the solar elevation angle is 8.55°. At this point, the UAV is recommended to begin its ascent flight with a minimum climb rate to gain gravitational potential energy. At the 13.25th hour, when the solar elevation angle is 75.06°, the UAV reaches the optimal time to descend without consuming any power. The descent phase ends when the UAV reaches its initial altitude.Figure 10
Recommended mission trajectory.A comparison of theSOC for the proposed model and a previous model [11] for a simulated 24-hour flight mission using the same UAV model (Table 1) is presented in Figure 11. The minimum SOC is achieved using the proposed model with a value of 0.6308C, which is slightly lower than the original value by 0.32%. This result indicates that the proposed model exhibits better battery utilization than the original model. Moreover, the recommended lower SOC limit for a rechargeable lithium polymer battery is 0.25C [1, 7].Figure 11
Battery SOC for a 24-hour flight.A detailed comparison of the parameters of the proposed and previous models is given in Table2. The proposed model improves the net power ratio by 30.84%. This value can reach 31.04 megawatts for UAV operations over a year. By adopting the proposed power management strategy, UAV operations at a lower altitude may avoid the highly volatile wind region.Table 2
24-hour flight mission performance data.
Parameters Original model Proposed model Improvement (%) Power ratio 1.3070 1.7101 30.84 Ceiling altitude (m) 8  ×  10 3 3.5961  ×   10 3 55.04A comparison of the power ratio performance of the proposed power management strategy and that of various approaches [3, 9, 12] is listed in Table 3. The concept of the proposed strategy significantly improves the power ratio by at least 30.84% relative to the other approaches for perpetual solar-powered UAV missions. Hence, the proposed power management strategy may be a potential alternative for solar-powered UAV operations.Table 3
Comparison of the proposed model with different approaches.
Approaches Power ratio Improvement (%) Flight performance parameters [3] 1.0300 66.03 Aircraft parameters optimization [12] 1.1125 53.71 Energy management system [9] 1.3070 30.84 Proposed power management strategy 1.7101 —


## 4.2. 72-Hour Perpetual Mission Simulation

A case study for a perpetual flight mission was simulated using the proposed power management strategy. This step is crucial for determining whether or not the battery pack contains sufficientSOC continuously for a sustainable powered flight. Thus, a simulation is conducted for a 72-hour mission to validate whether or not the minimal battery SOC stays within the preset boundary, as shown in Figure 12.Figure 12
Battery SOC for 72 hours.The simulation of a 72-hour perpetual mission achieved a power ratio of 1.7100, which is slightly lower than that of a 24-hour flight mission. However, this difference is almost negligible. TheSOC battery level maintained a consistent cycle for more than 48 hours during the first day at a fully charged state. This result further reaffirms the possibility of operating self-sustainable solar-powered UAV missions for months and even years.In addition, the minimal batterySOC level remained effectively within the boundary, with a value of 0.4348C. As mentioned earlier, a fully utilized battery is recommended to be 0.25–0.90C. Thus, in this case study, battery weight was significantly reduced from 1.28 N to 0.317 N as shown in Figure 13. Here, s total of 75.23% of the battery’s weight was reduced. Since UAV battery weight is roughly 30% of the overall take-off weight of UAV, the overall weight of the UAV can be reduced by 22.57%. This finding further affirms the potential of the new model to achieve perpetual flight.Figure 13
Battery weight comparison.


## 5. Conclusion

In conclusion, this study proposes adopting vertical cylindrical trajectory with an additional element by defining the optimal time of mission transition in relation to the elevation angle of the sun, which improves the overall gained power ratio. Structuring the mission phases to define the start-end-time of the ascent, cruise, and descent phases of a flight increases the saved energy and improves aircraft endurance. This approach improves the net power ratio by 30.84% compared with other techniques. As a result, the battery weight may be massively reduced by 75.23%. In addition, the proposed strategy also enables a lower-altitude flight, which protects the UAV from highly volatile winds in high-altitude regions. Therefore, the proposed power management strategy confirms that perpetual solar-powered UAV operations are feasible and sustainable.



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*Source: 9345368-2016-06-30.xml*