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.

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 Iron loss analysis and calculation of high energy density permanent magnet machine

2021 ◽  
Vol 72 (4) ◽  
pp. 262-267
Author(s):  
Yangyang Zhao ◽  
Xu Zhang ◽  
Peihao Zhu ◽  
Qingchun Zheng
Keyword(s):  
Energy Density ◽  
Permanent Magnet ◽  
Electric Propulsion ◽  
High Energy ◽  
Propulsion System ◽  
High Energy Density ◽  
Iron Loss ◽  
Outer Diameter ◽  
Permanent Magnet Machine ◽  
Electric Propulsion System

Abstract It is a research hotspot of electric propulsion system that a high energy density permanent magnet machine is used as its main power. In general, the power system of electric propulsion consists of batteries, inverters and high energy density permanent magnet machines and loads. Based on harmonic effect of PWM sine alternating current generated by inverter, iron loss model of high energy density permanent magnet machine is established under inverter power harmonic, and iron loss calculation flow chart of high energy density permanent magnet machine for electric propulsion system is shown. The influences of different stator outer diameter and rotor inner diameter on iron loss are analyzed by using the finite element method. Through the above analysis, a 30 kW high energy density permanent magnet machine was designed. Then the noload test and iron loss separation test were carried out, verifying that the machine has very low core loss.

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.

scholarly journals Primary parameters design method for distributed electric propulsion unmanned aerial vehicle

2021 ◽  
Vol 39 (1) ◽  
pp. 27-36
Author(s):  
Yiyuan Ma ◽  
Wei Zhang ◽  
Xingyu Zhang ◽  
Xiaobin Zhang ◽  
Yuelong Ma ◽  
...  
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Electric Propulsion ◽  
Design Method ◽  
Flight Test ◽  
Propulsion System ◽  
Specific Power ◽  
Design Parameters ◽  
Electric Propulsion System ◽  
Aerial Vehicle ◽  
Short Takeoff And Landing

Distributed electric propulsion technology brings new ideas to the design of unmanned aerial vehicle(UAV), such as improving aerodynamic efficiency and propulsive efficiency, and new concept of vertical/short takeoff and landing configurations. However, compared with conventional UAV, the propulsion system of distributed electric propulsion UAV is more complex, which brings difficulties and challenges to the design of distributed electric propulsion UAV. Based on its special aerodynamic/propulsive coupling characteristics, this paper studies the design method and process of primary parameters of distributed electric propulsion UAV. A short takeoff and landing UAV with distributed electric propulsion system is taken as an example for the conceptual design and primary parameter design, and the influence of design parameters on the takeoff mass and endurance is analyzed. Finally, the validity of the established design method is verified by the flight test of the prototype. Results indicate that the distributed electric propulsion system accounts for more than 20% of the takeoff mass; the electric ducted fan efficiency, mass specific power of the motor, mass specific power of the electronic speed controller and the resistivity of power wires are the most significant design parameters that affect the performance of the UAV; with the improvement of technologies, the takeoff mass is expected to be reduced by more than 20%, and the endurance is expected to be increased by more than three times.

Low-orbit spacecraft for highly detailed observation with a long lifetime in working orbits with an altitude below four hundred kilometers

2021 ◽  
Author(s):  
V.V. Volotsuev
Keyword(s):  
Electric Propulsion ◽  
High Spatial Resolution ◽  
Aerodynamic Drag ◽  
Propulsion System ◽  
Upper Atmosphere ◽  
Design Parameters ◽  
Electric Propulsion System ◽  
Dimensional Parameters ◽  
Long Lifetime ◽  
Main Mirror

The paper analyzes mass-dimensional design parameters of the optical-electronic equipment for Earth’s remote sensing from heights in the range of 300...400 km. Within the research, we carried out the synthesis of a mirror-lens telescopic complex with an additional rotary mirror tilted to the optical axis of the main mirror and selected the design parameters from the conditions for ultra-high spatial resolution satellite images. Furthermore, we analyzed the mass-dimensional parameters of the spacecraft as a whole, the parameters allowing for the smaller effect of the Earth’s upper atmosphere on the evolution of the parameters of the working orbit. To maintain the radius of the low working orbit of the spacecraft for seven years, an electric propulsion system is proposed. To compensate for the aerodynamic drag force in the investigated range of heights and in any conditions of the upper atmosphere, a thrust force of no more than 18 milliNewtons is sufficient. The reserves of the mass of the working body for the operation of the electric propulsion system depend on the design-ballistic parameters of the spacecraft and the required lifetime in a given working orbit.

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