Suitability of the Reforming-Controlled Compression Ignition Concept for UAV Applications

: Reforming-controlled compression ignition (RefCCI) is a novel approach combining two methods to improve the internal combustion engine’s e ﬃ ciency and mitigate emissions: low-temperature combustion (LTC) and thermochemical recuperation (TCR). Frequently, the combustion controllability challenge is resolved by simultaneous injection into the cylinder of two fuel types, each on the other edge of the reactivity scale. By changing the low-to-high-reactivity fuel ratio, ignition timing and combustion phasing control can be achieved. The RefCCI principles, beneﬁts, and possible challenges are described in previous publications. However, the suitability of the RefCCI approach for aerial, mainly unmanned aerial vehicle (UAV) platforms has not been studied yet. The main goal of this paper is to examine whether the RefCCI approach can be beneﬁcial for UAV, especially HALE (high-altitude long-endurance) applications. The thermodynamic ﬁrst-law and the second-law analysis is numerically performed to investigate the RefCCI approach suitability for UAV applications and to assess possible e ﬃ ciency gains. A comparison with the conventional diesel engine and the previously developed technology of spark ignition (SI) engine with high-pressure TCR is performed in view of UAV peculiarities. The results indicate that the RefCCI system can be beneﬁcial for UAV applications. The RefCCI higher e ﬃ ciency compared to existing commercial engines compensates the lower heating value of the primary fuel, so the fuel consumption remains almost the same. By optimizing the compression pressure ratio, the RefCCI system e ﬃ ciency can be improved.


Introduction
According to leading experts, the internal combustion engine (ICE) will keep being a prime propulsion tool for the next decades [1][2][3]. The ICE is also a major propulsion tool for unmanned aerial vehicle (UAV) applications including drones; while the main challenge and main global trend of the UAV industry are achieving high flight altitudes together with long endurance-HALE (high-altitude long-endurance). Higher flight altitude allows the covering of larger surfaces by one aircraft, more stealth, whereas long endurance makes longer times above an object possible . To be even more valuable for all platforms, the ICE has to significantly improve its energy efficiency to enable longer endurance. In recent decades, much work has been done to meeting this target. Low-temperature combustion (LTC) engines can increase engine efficiency and reduce pollutant emissions simultaneously [4,5]. This is possible since the combustion is simultaneous all over the cylinder resulting in eliminating the compression ratio (CR) restriction owing to the knocking phenomenon characterized in SI engines. In addition, the low-temperature combustion results in lower heat loss to the cylinder walls and NO x formation. However, the LTC engine has some challenges to be addressed before this approach can be commercial. The major challenges are ignition and combustion-phasing control, high CO To overcome the challenges of catalyst coking, to avoid the need for multiple reformers, and enable the use of a single primary fuel, the reforming-controlled compression ignition (RefCCI) approach was suggested and analyzed by the authors in [7] and [9]. The RefCCI method couples the benefits of the HP-TCR and the advanced combustion concept, the reactivity-controlled compression ignition (RCCI) developed by researchers from the University of Wisconsin [6]. According to the RefCCI method, a part of the primary fuel is reformed using the steam reforming of DME (SRD) in a catalytic reactor [7] to create a hydrogen-rich reformate. Both the nonreformed high-reactivity primary fuel (DME) and the low-reactivity gaseous reformate (mainly H 2 ) are injected directly into the cylinder in a controllably varied ratio. The simulation results [7] showed that, as a result of the heat recovery effect, only efficiency improvement of up to 5.4% is achieved compared to the basic engine without TCR. The predicted efficiency of the RefCCI engine was approximately 50% for a very basic engine configuration.
The second-law analysis is an accepted tool of recognizing ways to improve efficiency [19]. Mapping the exergy destruction causes allows redesign of the tested system to minimize exergy destruction [20] and consequently to improve system efficiency [21]. This approach is very common in many different engineering areas [22] such as gas turbines [23,24], power plants with CO 2 capture [25], and organic Rankine cycle-based waste energy recovery [26]. The second-law analysis concept is also extensively applied in the ICE field. It begins with fundamental research [27][28][29] and continues to the analysis of engineering applications [30][31][32][33].
The second-law analysis of the RefCCI engine [9] showed that approximately 33% of the fuel exergy consumed by the system is destroyed owing to the irreversible process in the combustion chamber. An additional 5% is destroyed in the reforming system. Chemical reaction and in-cylinder gas to walls heat interaction are the major contributors to exergy destruction in the engine, accounting for approximately 45% and 38%, respectively. After the optimization of parameters affecting the exergy destruction, the obtained results revealed indicated efficiency improvement above 7%, and even higher if the compression ratio is increased.
The main goal of the reported study is to examine the suitability of the RefCCI concept to UAV applications with an emphasis on HALE (high-altitude long-endurance) platforms. Ambient conditions at high altitude require some adjustments to the RefCCI system. First, the known problem of limited power owing to reduced air density should be considered. Second, since the autoignition principle is applied in the RefCCI method, the pressure after compression has a very important role in enabling the charge compression ignition. Too low pressure may result in misfiring since the autoignition delay becomes longer with pressure reduction [5]. Turbocharging enables both challenges to be resolved. An intercooler usually is applied as well to reduce the compressed air temperature and increase further its density.
Considering the mentioned above, the issue that should be examined whether there is sufficient available exhaust gas energy for simultaneous powering the turbocharger turbine and sustaining the efficient reforming process. The enthalpy required by the latter increases so much as the required hydrogen flow rate is higher. This happens as the average pressure and temperature in the cylinder rise, for example with load increase. Boosting the air in the compressor on one hand increases the intake pressure and consequently, the average pressure and, on the other hand, decreases the average temperature during combustion owing to the air dilution effect. Therefore, the combined effect of over-boosting should be examined. If the engine demand for hydrogen is higher with boosting, the lack of available energy to operate both systems may be a realistic scenario. However, in this case, the produced turbine power is reduced resulting in lower boosting until the system arrives at a certain point enabling operation of both systems. Nevertheless, as mentioned above, if the intake pressure is too low combustion may not occur. This consequence can restrict the altitude range. Thus, this work investigates the ability of the boosted RefCCI system to operate at the HALE UAV conditions. The focus is on altitudes from 20,000 to 40,000 ft (approximately 6.1 to 12.2 km).

RefCCI Concept Description
The RefCCI concept uses a combination of RCCI [6] and HP-TCR [13] advantages with DME as a primary fuel and an onboard single-stage reformer filled with a bifunctional catalyst. In the RefCCI system, the engine exhaust gases are exploited to sustain endothermic reactions of fuel reforming in a single catalytic reformer. Three main reactions occur simultaneously in this reformer throughout the steam reforming of the DME (SRD) process. Each of them is supported by one of the catalyst functions (acid or metal): DME-hydrolysis (Equation (1), the opposite reaction to methanol dehydration), methanol steam reforming (SRM; Equation (2)), and reverse water gas shift (r-WGS; Equation (3)). These reactions and their enthalpy values are listed below: The sum of the first two reactions gives: The produced hydrogen-rich reformate is injected into the engine cylinder directly. DME is injected into the engine cylinder separately from the reformate. Combustion characteristics of DME and hydrogen differ substantially (the first is a high-reactive fuel and the second is a low-reactive fuel). The low-reactivity fuel has a shorter ignition delay than the high-reactivity fuel. Therefore, the increase of ratio between the injected low-reactivity primary fuel (DME) and the hydrogen-rich reformate results in advanced igniting timing and vice versa. Thus, varying this ratio can solve the controllability issue of compression autoignition (CAI) engines.

Model Description
The model used in this work is based on the previously developed two models described in [7,9]. The model is 1-D, homogenous combustion calculated using a reduced mechanism based on the work of Kaiser et al. [34]. The vaporizer, reformer, and intercooler are considered as adiabatic. The saturated water and DME thermodynamic properties are based on data from [18,35], respectively. The superheated water and DME vapors thermodynamic properties (considered as an ideal gas) were taken from NASA's database [36]. The dependency of the ambient conditions on the flight altitude is shown in Figure 1. The model numerically analyzes the RefCCI system ( Figure 2) from both the first and the second law perspectives. As seen, the primary fuel (DME) and water are compressed and enter into the intercooler from the cool side. Then they enter into the vaporizer (pt. 1) to complete the evaporation process. The gas mixture flows into the reformer (pt. 2) and a low-reactivity hydrogen-rich reformate is obtained. The reformate is cooled down in the intercooler. In parallel, DME is injected directly into the engine cylinder. The reformer and vaporizer receive heat from the exhaust. The rest of the exhaust enthalpy is utilized to operate the turbine supplying power to the turbocharger compressor. To simplify the model calculation, it is assumed that the DME and water stream in different pipes and mixing before entering the reformer (pt.2). Based on the first-law calculation, the model finds all states in the systems. Since DME has a lower saturation temperature than water, it evaporates first, probably almost entirely in the intercooler. The maximal temperature that the model allows in pt. 2 is 600 K even if the vaporizer can warm it to greater temperature. However, pt. 2 temperature may be lower than 600 K when no energy is available to warm up the flow to this temperature or T 6 is lower than 600 K. The chemical reaction rate is calculated according to the model proposed by Oar-Artera et al. [38]. The bifunctional catalyst in this chemical model is CuFe 2 O 4 /γ-Al 2 O 3 . This chemical model, in particular its mathematical description part, is explained in more detail in [7].
A full explanation about assumptions made, mathematical descriptions, and other useful details about the model can be found in [7,9]. The modeled engine specification is listed below in Table 2. The previously developed model was modified for UAV propulsion conditions. The turbine and compressor sub-models are universally applicable and are not based on a specific commercial device, but the efficiency of 0.72 was selected for both and the turbine pressure ratio was obtained from Bernoulli's principle where a wastegate is utilized to control this pressure ratio. The turbine power is then calculated using Equation (5).
Here, p in,T is the turbine inlet or engine exhaust pressure (pt. 7- Figure 2), p out,T is the turbine exit pressure assumed to be the ambient pressure, c p is the average specific heat of gas streaming through the turbine, T in,T is the gas temperature at the turbine inlet, . m exhaust is the exhaust mass flow rate, η T is the turbine efficiency, and γ is the exhaust gas heat capacity ratio.
The power produced by the turbine is supplied to the compressor and, as a result, a compression pressure ratio is calculated using Equation (6).
Here, p in,C is the compressor inlet pressure assumed to be the ambient pressure (pt. 7- Figure 2), p out,C is the compressor exit pressure, c p is the average specific heat of air streaming through the compressor, T in,C is the air temperature at the compressor inlet, . m intake is the intake air mass flow rate, η C is the compression efficiency, and γ is the intake air heat capacity ratio. Note that in this work a simple turbocharging system is thermodynamically modeled. In reality, a two-stage turbocharging could be required, as discussed in [39], to enable efficient system operation in real high-altitude flight conditions.
To reduce the reforming average temperature, the reformer wastegate opening degree ( Figure 2) is controlled by a PID controller. The selected set-point is 600 K at the reformate exit (pt. 6, Figure 2), which is the temperature resulting in high fuel conversion according to chemical equilibrium considerations.
Too high exhaust-side reformer temperature may result in extensive exergy destruction owing to a large temperature difference.
The surrounding reference state chosen for this analysis is the sea-level typical state meaning 25°C and 1013 mbar. The environment is composed of N 2 , O 2 , H 2 O (g) , CO 2 , and other components in the molar fractions 75.67%, 20.35%, 3.12%, 0.03%, and 0.83%, respectively [35].
Notably, the general engine model uses existing and well-verified sub-models of the commercial GT-Suite SW. The latter is an extensively validated commercial SW widely used worldwide in engine research and development. Therefore, it was not essential to validate the engine model. As regards the reformer model, its validation for the methanol steam reforming reaction (SRM) was performed and described in detail in the previous publication of the Technion research group [14].

Second-Law Analysis
In each RefCCI component (Figure 2), the exergy destruction is calculated according to its thermodynamic classification and operating conditions. The reformer, vaporizer, turbine, compressor, and both intercoolers are assumed to be adiabatic and in steady-state control volumes. Among these parts, chemical reactions take place only in the reformer. In the model, the exergy destruction is calculated either by Equation (7) or by exergy balance-Equation (8).
Here, T 0 is the reference temperature, . Q j is the heat interaction rate of the system with the walls, and T j is the wall j temperature.
where, b f low is the specific flow exergy including both thermomechanical and chemical exergy, b TM and b ch , respectively. To calculate exergy destruction in the reformer, intercooler, and evaporator the exergy balance was applied. Since these systems are assumed to be adiabatic in steady-state operation mode, only the exergy flows are considered. For the combustion chamber, the integration of Equation (7) over an entire cycle results in the total exergy destruction in the combustion chamber per engine cycle. Thus, the engine exergy destruction rate in steady-state ( . B d,engine ) is obtained by multiplying this term by the engine speed (RPM) and dividing by 120. The exergy destruction in the combustion chamber is a result of the three main irreversible processes: chemical reaction, heat interaction, and injection. When engine valves are closed, Equation (7) degenerates so only the entropy change in time and heat interaction take place. It is reasonable to relate the chemical reaction exergy destruction ( . B d,chem ) to the change in entropy between EOI and EVO and exergy destruction due to heat interaction ( . B d,heat interaction ) to the sum of heat interactions between the combustion chamber and its walls during the same interval. The exergy destruction produced during injection is the total engine exergy destruction subtracted by the two mentioned above parameters.
For the turbine and compressor, the exergy destruction is obtained from the exergy balance derivative of Equation (8) as described in Equation (9).
Here, . m, b in , b out , and .
W are the mass flow rate, inlet specific exergy, outlet specific exergy, and mechanical power of the turbine/compressor, respectively.
The engine second-law efficiency is defined as follows: W . m DME,DI b ch DME + . m re f ormate b re f ormate , Here, . m DME,DI is the DME consumption of the DME directly injected into the cylinder, . m re f ormate is the reformate consumption, and b re f ormate is the reformate exergy containing the chemical and thermomechanical exergy. Evidently, the chemical constituent is dominant.
The RefCCI system second-law efficiency is defined as: Here, . m DME is the entire DME consumption and b ch DME is the DME chemical exergy (Table 1). Similarly, the system efficiency is defined as: Where, LHV DME is the DME lower heating value (Table 1).

The Effect of Boosting on RefCCI Engine Behavior
Since the RefCCI system works according to the autoignition principle, the conditions in the vicinity of TDC must be sufficient to enable the autoignition of the fuel-air mixture. In particular, the initial pressure at the beginning of the compression stroke has a crucial role since it determines the maximal pressure before TDC. If this pressure is too low, autoignition will not occur. At high altitude, the surrounding pressure is very low (Figure 1), and therefore boosting is required. Besides, to gain the advantages of low-temperature combustion (LTC), such as RefCCI, it would be beneficial to have the air-fuel mixture as lean as possible. This means that extra air should enter the cylinder which requires extra boosting. However, extra boosting might cause negative phenomena such as elevated backpressure in the exhaust. Hence, the compression pressure ratio has a range in which the engine can work and this range varies depending on engine operating mode and flight altitude. Note that, in this work, the boosting system is not studied, and the compressor and turbine efficiency are fixed at 0.72. However, the effect of changing the compression pressure ratio on the RefCCI system performance is examined. Figure 3 shows this trade-off. When the compression pressure ratio increases, the air-fuel equivalence ratio (λ) expectedly increases as well. The extra air entering into the cylinder decreases the maximal temperature and consequently heat losses to walls. As a result, the indicated gross efficiency consistently increases when the pressure becomes higher. However, the higher pressureratio is, the higher the pumping losses. This results in a trend change and an optimum appearance when the indicated net efficiency is considered. Eventually, for the case illustrated in Figure 3 (30,000 ft), the optimal pressure ratio is 3.25. The system efficiency is higher than the engine efficiency by approximately 1.75-2 percentage points (absolute) owing to waste heat recovery. Another interesting trend that is unique to a boosted RefCCI compared with a naturally aspirated RefCCI [7,9] is that the required H 2 /DME ratio does not extendedly modify. This is probably because of the opposite trends that boosting causes. As much as more air enters into the cylinder, the average in-cylinder pressure during the compression stroke is higher resulting in lower required fuel reactivity (higher H 2 /DME ratio). However, since the air is also a diluter, higher dilution results in the lower average temperature, which demands higher fuel reactivity. The simulation results show that at a flight altitude of 40,000 ft, the minimal compression pressure ratio that achieves the required in-cylinder pressure before ignition (to allow autoignition) is 3.25 compared to 1.5 at 20,000 ft. In fact, the intake pressure enabling autoignition is around 0.7 bar, reflecting approximately a minimum of 35 bar maximal pressure before combustion. Figure 3. Engine performance, the air-fuel equivalence ratio, and H 2 /DME ratio vs. compression pressure ratio. Engine regime: is 12.75 kW for a single-cylinder, 5000 RPM, and 30,000 ft altitude.

Exergy and Energy Analysis
To understand better the reasons for process irreversibility in the RefCCI system, it is useful to map the exergy and energy flow inside the system. After that, by utilizing tools that can reduce the process irreversibility, the system efficiency can be enhanced. Figure 4 shows an example of an exergy and energy flow map for a single case of engine operation at 40,000 ft. altitude, while the compression pressure ratio is 3.25 and the engine power is 12.75 kW for a single cylinder (defined as 50% of the maximal power) and engine speed 5000 RPM.
The main exergy destruction source is the engine itself. The exergy destruction in the reformer and vaporizer is significant as well. Therefore, to improve the system efficiency this destruction should be reduced as much as possible. In this case (Figure 4), the relatively low compression ratio does not allow the supply of extra air, so the air-fuel equivalence ratio (λ) is very close to 1. This causes some bad consequences affecting energy utilization in the system. On the one hand, low λ causes high in-cylinder temperature increasing heat losses. Only part of this heat can be utilized to produce work, while the exergy transferred by heat interaction ( j T 0 /T j − 1 Q j ) is the maximum work value that can be produced (according to Carnot). Evidently, additional tools are necessary to harvest this work. Consequently, the high in-cylinder temperature results in high exhaust gas temperature and therefore higher temperature difference between the exhaust side and the fuel/reformate side both in the reformer and the vaporizer. On the second hand, increasing λ requires higher compression pressure ratio which inevitably leads to higher exhaust backpressure. The latter may result in lower cycle work.
When analyzing the sources of exergy destruction in the cylinder, chemical and heat exergy destruction are the major contributors. Two main factors affect the chemical exergy destruction during combustion. First, the fuel properties: as much as the fuel contains more hydrogen, the chemical exergy destruction is lower since, for a constant amount of air, the number of product molecules becomes lower compared to the number of the reactants (air/fuel) molecules [40]. Second, the amount of air participating in combustion: the higher mass is, the higher the entropy change rate. Figure 5 illustrates this trend. Note that, in this graph and from now on, the relative difference (Ψ i ) in the parameter i value appearing on the vertical axis is defined as the following:  Where Ψ i is the predicted parameter i value and ψ re f is its value for the reference case. The reference case is the lowest investigated value (unless it is defined differently), meaning the relative difference for the reference case is by definition zero.
The H 2 /DME ratio value shown in Figure 5 is the value required to maintain the engine combustion process in such a way that CA50 would be the same and equal 10 degrees ATDC. Generally, the chemical destruction increases with the increase of the compression pressure ratio. However, its slope varies depending on the H 2 /DME ratio. In the range of 2.25-3.25, when the H 2 /DME ratio decreases, the chemical exergy destruction curve slope is sharper than between 3.5-4.5 when the H 2 /DME ratio increases.
Increasing compression pressure ratio has some more effects on the boosted RefCCI system. It reduces exhaust temperature and consequently decreases reformer exergy destruction. It causes more recovery of waste energy by the boosting system and, as a result, less energy/exergy flows through the system exhaust. However, the increase of the compression pressure ratio is not unlimited. It may result in the need for more complex compression procedures such as two-stage compression with its accompanying problems [39]. In Figure 6 the results of the simulation for 40,000 ft, 5000 RPM, and 50% power are presented. The results match the mentioned above qualitative considerations. As explained, the system exhaust exergy flow (pt. 8 in Figure 2) significantly decreases (up to 90%) when the pressure ratio increases. In parallel, the system intake exergy flow, which is negative because the surrounding pressure and temperature are lower than in the reference state, becomes lower meaning more air-flow enters the system. The exergy transferred by heat decreases since the average temperature in the cylinder is lower. Consequently, the second-law efficiency increases with the pressure ratio increase meaning DME exergy consumption is lower. The reformer and vaporizer exergy destruction both decrease since the exhaust temperature is lower resulting in lower heat transfer temperature difference.
In the previous study [9], the authors investigated the influence of various parameters on exergy destruction in the RefCCI system. Some of them could affect the RefCCI system performance somewhat differently at UAV-relevant conditions. In addition to the previously studied parameters, there are some additional ones, which are unique for UAVs. For instance, since the UAV engine typically operates at higher speeds than a typical automotive engine, for the same load, the required H 2 /DME ratio and, as a result, hydrogen consumption would be lower. Therefore, either the reformer can be smaller or the temperature difference inside the reformer can be lower, resulting in reduced irreversibility. Another parameter, the range of which changes in UAV applications, is the boosted air temperature after intercooling (hereinafter, intercooling temperature). At high altitudes, the ability to cool the compressed air is enhanced. On the one hand, extra cooling of the air enables charging more air into the cylinder resulting in lower heat losses. On the other hand, it increases the chemical exergy destruction. In addition, the heat rejected from the intercooler is lost. Figure 7 shows the influence of the reduction in the intercooling temperature on exergy destruction and second-law efficiency of the boosted RefCCI system. The reference case is a temperature of 25°C, while all other parameters remain constant. As can be seen from Figure 7, the exergy destruction in the engine itself grows slightly with the decrease of the intercooling temperature. This is a result of the increase in chemical exergy destruction, which is higher than the reduction of exergy destroyed owing to heat transfer to the cylinder walls. However, the reduction in exergy flowing out of the system leads to improvement of the second-law efficiency by almost 4% at the intercooling temperature of −25 • C compared to the 25 • C case (as a reminder, the ambient air temperature at the flight altitude of 40,000 ft is below −50 • C). When optimizing the boosted RefCCI system according to the findings of this and the previous work [9], it is possible to enhance the system performance significantly. Table 3 shows a comparison between the two cases, the reference case, which is presented in Figure 4, and the optimized case. The parameters changed are also shown in the Table. The results show that although the engine exergy destruction slightly increases, the significant reduction in the reforming exergy destruction and the exergy lost with the exhaust flow result in an increase of almost 4% in the second-law efficiency of the boosted RefCCI system. We believe that extensive optimization including more parameters than those investigated in this work can lead to even higher improvement. Table 3. Exergy flow and destruction in the boosted-RefCCI system for the nonoptimized and optimized cases. The optimization was done according to the findings in this and previous work.

Comparison between the RefCCI Concept and HP-TCR and a Commercial SI Engine
In this section, the investigated boosted RefCCI approach is compared with the HP-TCR SI engine and a commercial Rotax 914 engine. The Rotax 914 is a gasoline SI four-cylinder engine. The prediction of its performance was carried out based on the model described in [41]. The HP-TCR method is explained in detail and its model is described in [13]. All models were adjusted to enable a comparison with the investigated boosted RefCCI engine. Both HP-TCR and RefCCI models simulate the engine modified from the Lester Petter AD1 commercial engine. Both concepts enable the use of a high compression ratio. The RefCCI since it is based on compression autoignition, and HP-TCR since the combusted fuel in this concept is hydrogen, which has strong resistance to the ringing phenomenon. This ability was proven in [42]. To enable a comparison between the engines of different displacement, the indicated mean effective pressure (IMEP) value was kept the same. The compared propulsion technologies are summarized in Table 4. The models above are based on models presented in 1 [41]; 2 [13]; 3 [7,9].
In the UAV field, reducing the aircraft mass has an important significance. Thus, the main parameter that should be examined is ISFC. Fuel consumption depends on both engine efficiency and fuel heating value. The HP-TCR and RefCCI concepts are beneficial from the efficiency point of view than the commercial SI Rotax 914 engine, since both enable the use of higher CR and combust hydrogen, the fuel with much higher burning velocity (to remind: the latter enables getting closer to the ideal Otto cycle). However, the conventional Rotax 914 engine uses gasoline as the primary fuel, and gasoline has a considerably higher lower heating value (LHV) than methanol and DME (44 MJ/kg compared to 19.92 and 28.9, respectively-see Table 1). Thus, even if the efficiency of HP-TCR and RefCCI are higher than the SI Rotax 914, still their ISFCs may be larger. Nevertheless, the HP-TCR and RefCCI have other advantages that in the future might be crucial such as using non-fossil alternative fuel and cleaner combustion.
For the purpose of comparison, equal conditions in intake were set-1.08 bar and 298 K. Three regimes were tested, all at 5000 RPM, where the indicated power was set to three values: 50%, 39%, and 29.5% of the maximal power defined as 25.5 kW per cylinder for the HP-TCR and RefCCI. The Rotax 914 displacement volume is 82.5% of the HP-TCR and RefCCI engine. Thus, the maximal power was reduced according to this value to keep the IMEP value unchanged. Figure 8 shows the results for the tested cases. The efficiency of the RefCCI system is relatively higher than that of the HP-TCR by approximately 10% on average and that of the Rotax 914 by approximately 50% on average. In on-land applications, this is a huge advantage. Yet, in the aerial application, the fuel mass carried by the platform should be minimal and thus the fuel consumption is the main consideration. The results show that the ISFC of the RefCCI system and the Rotax 914 engine are very close (approximately 1.2% only higher in the RefCCI vs. the Rotax 914). This means that the efficiency enhancement compensates for the lower heating value of DME compared to gasoline. The HP-TCR system has fairly high efficiency but also high ISFC meaning that it is less applicable for UAV applications. It should be noted that both HP-TCR and RefCCI require water for the reforming process [7]. This water was not considered as part of the fuel mass consumption since the water can be easily condensed and reused from the exhaust flow. In the RefCCI, to produce two molecules of hydrogen, a single molecule of steam is required (CH 3 OCH 3 + 3H 2 O 6H 2 + 2CO 2 ) and incomplete combustion from a molecule of hydrogen a single molecule of steam is formed ( . In total, the ratio between the combustion-formed water molecules to the required for reforming molecules is two. In the HP-TCR, this ratio is 3. To condense this steam, even if the air-fuel equivalence ratio is high and as a result, the partial pressure of the exhaust steam is very low, the surrounding temperature is low enough to enable condensation in any case. Keep in mind that the steam partial pressure decreases with the increase of flight altitude, but the surrounding temperature decreases as well.
Besides DME, other fuels may be considered as a primary fuel for the RefCCI engine. For aerial applications, the primary fuel should have as high LHV as possible and together with the high system efficiency, the fuel mass consumption might be even lower than that achieved in the RefCCI engine with DME as the primary fuel. However, to the best of the authors' knowledge, no relevant works dealing with this issue have been published yet, and further research is required. Some challenges still delay the practical penetration of the RefCCI method into UAV applications. The major challenge is ringing, which is not unique for UAV only. However, it may be more significant in UAV applications. Ringing owing to rapid heat release rate may be more severe in UAVs because of reduced air mass entering the engine. Intensive research is ongoing nowadays to find solutions to this problem. Among possible solutions, suiting appropriate injection strategy enabling to restrain the heat release rate should be mentioned. Evidently, a practical implementation of the RefCCI engine in the UAV platform would be easier if an alternative non-fossil primary fuel with an LHV similar to that of diesel is applied.

Summary and Conclusions
In this work, the suitability of the reforming-controlled compression ignition for UAV application was examined. First, the influence of boosting on the RefCCI engine behavior was discussed, then an exergy analysis to map the sources of exergy destruction in the RefCCI system was executed, and possibilities of performance improvement were analyzed. A comparison of the RefCCI approach with the high-pressure thermochemical recuperation SI engine and the commercial SI Rotax 914 engine were carried out.
The main findings are listed below: 1.
Increasing compression pressure ratio consistently increases the gross indicated efficiency of the RefCCI system, but this has also an opposite effect reflected in the pumping work increase. The net indicated efficiency has a maximum value where the first effect is the most dominant.

2.
The necessary fuel reactivity (H 2 /DME ratio) varies only slightly with the increase of the compression pressure ratio and actually shows some volatility because of its opposite effects on autoignition timing. Increasing the compression pressure ratio, on the one hand, increases average pressure before combustion, but, on the other hand, decreases average temperature owing to the excess air dilution effect. 3.
The RefCCI method seems to be a good alternative candidate for UAV application since, despite the relatively low heating value of DME, the high system efficiency leads to fuel consumption very close to that of the conventional gasoline engine.

4.
The results of the RefCCI system performance optimization show that a significant reduction in the reforming exergy destruction and the exergy lost with the exhaust flow can be achieved. This results in an improvement of almost 4% in the second-law efficiency of the boosted RefCCI system. We believe that extensive optimization including more parameters than those investigated in this work can lead to even higher improvement.
Besides DME, other fuels may be considered as a primary fuel for the RefCCI engine. For aerial applications, the primary fuel should have as high LHV as possible, and, together with the high RefCCI system efficiency, lower fuel mass consumption compared to other engine technologies may be achieved with cleaner combustion.
Experimental research of the RefCCI engine is necessary to better understand complicated processes taking place in the system in their mutual relationship. Developing injection strategies to restrain ringing in the engine cylinder is vital.

Conflicts of Interest:
The authors declare no conflict of interest.