Dynamic Model Identification of Marine Electric Propulsion System

2012 ◽  
Vol 503-504 ◽  
pp. 1357-1359
Author(s):  
Qiang Wu ◽  
Hao Xiong ◽  
Guang Wei Meng ◽  
Li Bing Zhou
Keyword(s):  
Dynamic Model ◽  
Electric Propulsion ◽  
System Analysis ◽  
Model Identification ◽  
Propulsion System ◽  
Experimental Result ◽  
Experiment Data ◽  
Electric Propulsion System ◽  
Identification Technique ◽  
Propulsion Unit

This paper applies identification technique to the marine electric propulsion system analysis, adopts the recursive extended least squares (RELS) algorithm to estimate the structure and parameters of the model, employs the variable forgetting factors into the algorithm to improve the tracking characteristic of the parameters, establishes the dynamic model of a simulated electric propulsion unit under the excitation control based on the experiment data, and finally verifies the validity of the method through the consistency between simulation result and experimental result.

scholarly journals System analysis and test-bed for an atmosphere-breathing electric propulsion system using an inductive plasma thruster

2018 ◽  
Vol 147 ◽  
pp. 114-126 ◽  
Author(s):  
F. Romano ◽  
B. Massuti-Ballester ◽  
T. Binder ◽  
G. Herdrich ◽  
S. Fasoulas ◽  
...  
Keyword(s):  
Electric Propulsion ◽  
System Analysis ◽  
Propulsion System ◽  
Test Bed ◽  
Electric Propulsion System ◽  
Plasma Thruster

scholarly journals Method for Characterization of a Multirotor UAV Electric Propulsion System

2020 ◽  
Vol 10 (22) ◽  
pp. 8229
Author(s):  
Petar Piljek ◽  
Denis Kotarski ◽  
Matija Krznar
Keyword(s):  
Electric Propulsion ◽  
High Energy ◽  
Propulsion System ◽  
Signal Acquisition ◽  
Aerial Robots ◽  
Electric Propulsion System ◽  
Measurement Results ◽  
Propulsion Unit ◽  
High Energy Consumption

Due to their abilities, multirotor unmanned aerial vehicles (UAVs) can be used in various missions that require complex and precise movements, so they are a typical representative of aerial robots. Since this type of UAV is characterized by high energy consumption, it is of most importance to precisely choose the system parameters and components in order to achieve the required flight performance that meets the mission requirements. In this paper, a method for characterization of the multirotor UAV propulsion system is proposed, which is a fundamental step in the design process of this type of UAV. For the purpose of method validation, experimental measurements and signal acquisition were performed, and the measurement results for the considered electric propulsion units were shown. An identification procedure is presented, which is used to process the measurement results or manufacturer’s data and display them as propulsion unit static maps. Based on static maps, the characterization process of the electric propulsion system is performed, and the propulsion unit characteristics are shown.

scholarly journals Design of Hybrid-Electric Megayachts: The Impact of Operative Profile and Smart Berthing Infrastructures

2021 ◽  
Vol 9 (2) ◽  
pp. 186
Author(s):  
Francesco Mauro ◽  
Elia Ghigliossi ◽  
Vittorio Bucci ◽  
Alberto Marinó
Keyword(s):  
Electric Propulsion ◽  
Propulsion System ◽  
Storage Devices ◽  
Electric Propulsion System ◽  
Hybrid Electric ◽  
The Impact

Nowadays, sustainable navigation is becoming a trending topic not only for merchant ships but also for pleasure vessels such as motoryachts. Therefore, the adoption of a hybrid-electric propulsion system and the installation of on-board storage devices could increase the greenness of a megayacht. This paper analyses the performance of three commercial propulsive solutions, using a dynamic operative profile and considering the influences of the smart berthing infrastructures. Results compare the yearly fuel consumptions of the analysed configurations for a reference megayacht.

scholarly journals Design and In-orbit Demonstration of REGULUS, an Iodine electric propulsion system

2021 ◽  
Author(s):  
Nicolas Bellomo ◽  
Mirko Magarotto ◽  
Marco Manente ◽  
Fabio Trezzolani ◽  
Riccardo Mantellato ◽  
...  
Keyword(s):  
Electric Propulsion ◽  
Specific Impulse ◽  
Input Power ◽  
Propulsion System ◽  
Electric Propulsion System ◽  
Propulsive Performance ◽  
Plasma Thruster ◽  
Total Impulse ◽  
Acceptance Tests

AbstractREGULUS is an Iodine-based electric propulsion system. It has been designed and manufactured at the Italian company Technology for Propulsion and Innovation SpA (T4i). REGULUS integrates the Magnetically Enhanced Plasma Thruster (MEPT) and its subsystems, namely electronics, fluidic, and thermo-structural in a volume of 1.5 U. The mass envelope is 2.5 kg, including propellant. REGULUS targets CubeSat platforms larger than 6 U and CubeSat carriers. A thrust T = 0.60 mN and a specific impulse Isp = 600 s are achieved with an input power of P = 50 W; the nominal total impulse is Itot = 3000 Ns. REGULUS has been integrated on-board of the UniSat-7 satellite and its In-orbit Demonstration (IoD) is currently ongoing. The principal topics addressed in this work are: (i) design of REGULUS, (ii) comparison of the propulsive performance obtained operating the MEPT with different propellants, namely Xenon and Iodine, (iii) qualification and acceptance tests, (iv) plume analysis, (v) the IoD.

Research on Parameters Matching of Ultralight Electric Aircraft Propulsion System

2013 ◽  
Vol 732-733 ◽  
pp. 1212-1215
Author(s):  
Gui Wen Kang ◽  
Yu Hu ◽  
Ya Dong Li ◽  
Wen Hui Jiang
Keyword(s):  
Electric Propulsion ◽  
High Energy ◽  
Low Noise ◽  
Electric Power System ◽  
Propulsion System ◽  
Heat Radiation ◽  
Design Parameters ◽  
Electric Propulsion System ◽  
Electric Aircraft ◽  
Parameter Matching

The propulsion system of ultralight electric aircraft is one of the general aviation technology development directions. It has the advantages such as light pollution, low noise, high energy utilization ratio, simple structure, easy maintenance, high reliability, less heat radiation, little operation cost and so on. Combined with the certain type of ultralight aircraft design parameters, the layout of aircraft electric propulsion, the principles and steps of the parameter matching of electric propulsion system were presented. The method of parameter matching and performance verification of electric propulsion system was put forward. The feasibility of the system is verified from the point of dynamic property. The study of parameter matching of electric propulsion system could not only provide basis for the integrated optimization for electric power system, but also evaluate the performance of the system simulation as reference.

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