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 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.

A Novel Control Model for Electric Propulsion Systems in All-Electric Ships

2012 ◽  
Vol 433-440 ◽  
pp. 2541-2545
Author(s):  
Chun Lien Su ◽  
Ruei Hung Weng
Keyword(s):  
Electric Propulsion ◽  
Pulse Width Modulation ◽  
Power Conversion ◽  
Harmonic Distortion ◽  
Control Model ◽  
Propulsion System ◽  
Nonlinear Loads ◽  
Propulsion Systems ◽  
Electric Propulsion System ◽  
Proposed Model

In recent sea and undersea vehicles, implementation of all-electric ships (e-ships) technologies that employ various types of semiconductor switching devices based power conversion modules has brought revolution. These power converters that are nonlinear loads can produce non-sinusoidal distorted currents and these currents are then delivered and broadcasted through the power network and thus bus voltages are distorted. This effect can be more obvious while large loads fed and controlled through power conversion modules, such as electric propulsion system, operate for different purposes of missions. In order to improve the harmonic distortion due to operation of electric propulsion systems, a novel control model for electric propulsion motors is proposed in this paper. The electric motor drivers are controlled through three inverter triggering signals including pulse width modulation (PWM), Quasi-Six Step, and Six-Step for different ship navigation scenarios. Simulation results of application of the proposed model to a practical ship with electric propulsion system are presented. Test results have demonstrated that with the proposed model the harmonic distortions produced by electric propulsion systems under different speed situations can be effectively mitigated and consequently the system supply quality is maintained.

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.

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