scholarly journals Conceptual Design, Sizing and Performance Analysis of a Cryo-Electric Propulsion System for a Next-Generation Hydrogen-Powered Aircraft

2021 ◽  
Author(s):  
Christian Hartmann ◽  
Jonas Kristiansen Nøland ◽  
Robert Nilssen ◽  
Runar Mellerud
Keyword(s):  
Performance Analysis ◽  
Electric Propulsion ◽  
Cooling Capacity ◽  
Propulsion System ◽  
Cryogenic Cooling ◽  
Baseline Scenario ◽  
Analysis Framework ◽  
Electric Propulsion System ◽  
And Performance ◽  
Mission Profile

In this paper, we present a comprehensive sizing and performance analysis framework for a disruptive cryo-electric propulsion system intended for a hydrogen-powered regional aircraft. The main innovation lies in the systematic treatment of all the electrical and thermal components to model the overall system performance. One of the main objectives is to study the feasibility of using the liquid hydrogen (LH\textsubscript{2}) fuel to provide cryogenic cooling to the electric propulsion system, and thereby enable ultra-compact designs. Another aim has been to identify the optimal working point of the fuel cell to minimize the overall propulsion system's mass. The full mission profile is evaluated to make the analysis as realistic as possible. Analyses are done for three different 2035 scenarios, where available data from the literature are projected to a baseline, conservative, and optimistic scenario. The analysis shows that the total propulsion system's power density can be as high as 1.63 kW/kg in the optimistic scenario and 0.79 kW/kg in the baseline scenario. In the optimistic scenario, there is also sufficient cryogenic cooling capacity in the hydrogen to secure proper conditions for all components, whereas the DC/DC converter falls outside the defined limit of 110 K in the baseline scenario.

scholarly journals Conceptual Design, Sizing and Performance Analysis of a Cryo-Electric Propulsion System for a Next-Generation Hydrogen-Powered Aircraft

2021 ◽  
Author(s):  
Christian Hartmann ◽  
Jonas Kristiansen Nøland ◽  
Robert Nilssen ◽  
Runar Mellerud
Keyword(s):  
Performance Analysis ◽  
Electric Propulsion ◽  
Cooling Capacity ◽  
Propulsion System ◽  
Cryogenic Cooling ◽  
Baseline Scenario ◽  
Analysis Framework ◽  
Electric Propulsion System ◽  
And Performance ◽  
Mission Profile

In this paper, we present a comprehensive sizing and performance analysis framework for a disruptive cryo-electric propulsion system intended for a hydrogen-powered regional aircraft. The main innovation lies in the systematic treatment of all the electrical and thermal components to model the overall system performance. One of the main objectives is to study the feasibility of using the liquid hydrogen (LH\textsubscript{2}) fuel to provide cryogenic cooling to the electric propulsion system, and thereby enable ultra-compact designs. Another aim has been to identify the optimal working point of the fuel cell to minimize the overall propulsion system's mass. The full mission profile is evaluated to make the analysis as realistic as possible. Analyses are done for three different 2035 scenarios, where available data from the literature are projected to a baseline, conservative, and optimistic scenario. The analysis shows that the total propulsion system's power density can be as high as 1.63 kW/kg in the optimistic scenario and 0.79 kW/kg in the baseline scenario. In the optimistic scenario, there is also sufficient cryogenic cooling capacity in the hydrogen to secure proper conditions for all components, whereas the DC/DC converter falls outside the defined limit of 110 K in the baseline scenario.

scholarly journals Improvement of Electric Propulsion System Model for Performance Analysis of Large-Size Multicopter UAVs

2020 ◽  
Vol 10 (22) ◽  
pp. 8080
Author(s):  
Jinseok Jeong ◽  
Hayoung Shi ◽  
Kichang Lee ◽  
Beomsoo Kang
Keyword(s):  
Performance Analysis ◽  
High Power ◽  
Electric Propulsion ◽  
Propulsion System ◽  
Electric Propulsion System ◽  
Large Size ◽  
Proposed Model ◽  
Armature Reaction ◽  
High Power Operation ◽  
Power Operation

In this study, an improved model of the electric propulsion system is proposed in order to analyze the performance of large-size multicopter unmanned aerial vehicles. The main improvement of the proposed model is to reflect the armature reaction of the motor, which effectively explains the significant performance degradation in high-power operation. The armature reaction is a phenomenon, in which the main field flux is interfered by a magnetic flux and, as the size and output of the motor increase, the effect of armature reaction also rapidly increases. Therefore, the armature reaction must be considered for the optimal design and performance analysis of large-size multicopter platforms. The model proposed in this study includes several mathematical models for propellers, motors, electric speed controllers, and batteries, which are key components of the electric propulsion system, and they can calculate key performance data, such as thrust and torque and power consumption, according to given product specifications and input conditions. However, estimates of the armature reaction constants and heat profiles of motors need to be obtained in advance through experimental methods, since there is not yet enough data available in order to derive an estimation model. In conclusion, a comparison with the static thrust test of some commercial products confirmed that the proposed model could predict performance in the high-power operation of electric propulsion systems for large multicopter platforms, although some errors were noted.

scholarly journals Comparative Analysis and Optimization of Technical and Weight Parameters of Turbo-Electric Propulsion Systems

Aerospace ◽  
2020 ◽  
Vol 7 (8) ◽  
pp. 107 ◽  
Author(s):  
Mykhaylo Filipenko ◽  
Stefan Biser ◽  
Martin Boll ◽  
Matthias Corduan ◽  
Mathias Noe ◽  
...  
Keyword(s):  
Electric Propulsion ◽  
Propulsion System ◽  
Aviation Industry ◽  
Total Efficiency ◽  
Efficiency Gain ◽  
Propulsion Systems ◽  
Electric Propulsion System ◽  
Reduce Emissions ◽  
Passenger Aircraft ◽  
Mission Profile

According to Flightpath 2050, the aviation industry is aiming to substantially reduce emissions over the coming decades. One possible solution to meet these ambitious goals is by moving to hybrid-electric drivetrain architectures which require the electric components to be extremely lightweight and efficient at the same time. It has been claimed in several publications that cryogenic and in particular superconducting components can help to fulfill such requirements that potentially cannot be achieved with non-cryogenic components. The purpose of this work was to make a fair comparison between a cryogenic turbo-electric propulsion system (CEPS) and a non-cryogenic turbo-electric propulsion system (TEPS) on a quantitative level. The results on the CEPS were presented in detail in a previous publication. The focus of this publication is to present the study on the TEPS, which in conclusion allows a direct comparison. For both systems the same top-level aircraft requirements were used that were derived within the project TELOS based on an exemplary mission profile and the physical measures of a 220-passenger aircraft. Our study concludes that a CEPS could be 10% to 40% lighter than a TEPS. Furthermore, a CEPS could have a total efficiency gain of up to 18% compared to a similar TEPS.

scholarly journals Analysis of Key Technologies for New Green Marine Propulsion Systems

2020 ◽  
Vol 194 ◽  
pp. 02008
Author(s):  
Zheng Duan ◽  
Yajie Chen ◽  
Haibo Gao ◽  
Linhao Liao
Keyword(s):  
Energy Storage ◽  
Electric Propulsion ◽  
Low Noise ◽  
Propulsion System ◽  
Hybrid Propulsion ◽  
Electric Propulsion System ◽  
Marine Propulsion ◽  
Key Technologies ◽  
New Energy ◽  
And Performance

The new green Marine propulsion system, as a new generation of marine propulsion, has advantages of strong mobility, low fuel consumption, low noise, safety and comfort. Three green propulsion solutions for different ship types are proposed, including pure electric propulsion system, compound energy storage electric propulsion system and diesel-electric hybrid propulsion system. The structure features and performance advantages are introduced and the key technologies such as new energy storage, DC network and shaft generator/motor are discussed. The related research achievements and typical project cases are also introduced.

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