The control of a parallel hybrid-electric propulsion system for a small unmanned aerial vehicle using a CMAC neural network

2005 ◽  
Vol 18 (5-6) ◽  
pp. 772-780 ◽  
Author(s):  
Frederick G. Harmon ◽  
Andrew A. Frank ◽  
Sanjay S. Joshi
Keyword(s):  
Neural Network ◽  
Unmanned Aerial Vehicle ◽  
Electric Propulsion ◽  
Propulsion System ◽  
Electric Propulsion System ◽  
Cmac Neural Network ◽  
Parallel Hybrid ◽  
Aerial Vehicle ◽  
Hybrid Electric

Operating Characteristics of an Electrically Assisted Turbofan Engine

2020 ◽  
Author(s):  
Merijn Rembrandt van Holsteijn ◽  
Arvind Gangoli Rao ◽  
Feijia Yin
Keyword(s):  
Electric Propulsion ◽  
Propulsion System ◽  
Operating Characteristics ◽  
Turbofan Engine ◽  
Electric Propulsion System ◽  
Fuel Burn ◽  
Parallel Hybrid ◽  
Electrical Propulsion ◽  
Hybrid Electric ◽  
Cruise Flight

Abstract With the growing pressure to reduce the environmental footprint of aviation, new and efficient propulsion systems must be investigated. The current research looks at the operating characteristics of a turbofan engine in a parallel hybrid-electric propulsion system. Electric motors are used to supply power in the most demanding take-off and climb phases to achieve the required thrust, which allows the turbofan to be redesigned to maximize the cruise performance (to some extent). It was found that the turbofan’s cruise efficiency can be improved by 1.0% by relaxing the constraints of take-off and climb. It was found that the surge margins of compressors limit the amount of power that could be electrically supplied. On a short-range mission, the hybrid-electric propulsion system showed a potential to reduce around 7% of fuel burn on an A320 class aircraft. Most of these savings are however achieved due to fully electric taxiing. The weight of the electrical propulsion system largely offsets the efficiency improvements of the gas turbine during cruise flight. A system dedicated for fully electric taxiing system could provide similar savings, at less effort and costs. Given the optimistic technology levels used in the current analysis, parallel hybrid-electric propulsion is not likely to be used in the next-generation short to medium range aircraft.

scholarly journals Indirect engine sizing via distributed hybrid-electric unmanned aerial vehicle state-of-charge-based parametrisation criteria

2019 ◽  
Vol 233 (14) ◽  
pp. 5360-5368
Author(s):  
S Wang ◽  
JT Economou ◽  
A Tsourdos
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Electric Propulsion ◽  
Combustion Engine ◽  
Electrical Power ◽  
Propulsion System ◽  
State Of Charge ◽  
Electrical System ◽  
Starting Conditions ◽  
Aerial Vehicle ◽  
Hybrid Electric

This paper presents a design process for the challenging problem of sizing the engine pack for a distributed series hybrid-electric propulsion system of unmanned aerial vehicle. Sizing the propulsion system for hybrid-electric unmanned aerial vehicles is a demanding problem because of the two different categories of propulsion (the engine and the motor), and the electrical system characteristics. Furthermore, what adds to the difficulty is that the internal combustion engine does not directly drive the propellers, but it is connected to an electrical generator and therefore provides electrical power to the electric motors and propellers. Hence there is a clear distinction from the traditional engine solutions which are mechanically coupled to the propeller. This paper addresses this specific distinction and proposes an indirect solution based on properties on the electrical part of the system. In particular, a novel parametric characterisation engine sizing approach is presented using the battery pack state-of-charge during a realistic unmanned aerial vehicle flight scenario. Five candidate engine options were considered with different starting conditions for the electrical system. The results show that by using the state-of-charge properties it is possible to select an appropriate size of engine pack while carrying a suitable electrical propulsion pack. However, the solutions are not unique and are appropriate for given design criteria clearly indicated in the paper.

Performance Assessment of an Integrated Parallel Hybrid-Electric Propulsion System Aircraft

2019 ◽  
Author(s):  
Smruti Sahoo ◽  
Xin Zhao ◽  
Konstantinos G. Kyprianidis ◽  
Anestis Kalfas
Keyword(s):  
Performance Assessment ◽  
Electric Propulsion ◽  
Electrical Power ◽  
Propulsion System ◽  
System Level ◽  
Electric Propulsion System ◽  
The Core ◽  
Parallel Hybrid ◽  
Overall Efficiency ◽  
Hybrid Electric

Abstract Hybrid-electric propulsion system promises avenues for a greener aviation sector. Ground research work was performed in the past for the feasibility assessment, at the system level, for such novel concepts and the results showed were promising. Such designs, however, possess unique challenges from an operational point of view, and for sizing of the sub-system components; necessitating further design space exploration for associating with an optimal operational strategy. In light of the above, the paper aims at presenting an operational analysis and performance assessment study, for a conceptualised parallel hybrid design of an advanced geared turbofan engine, based on 2035 timeframe technology level. It is identified that the hybrid power operation of the engine is constrained with respect to the requirement of maintaining an adequate surge margin for the low pressure side components; however, a core re-optimised engine design with consideration of electrical power add-in for the design condition, relieves such limit. Therefore such a design, makes it suitable for implementation of higher degree of hybridisation. Furthermore, performance assessment is made both at engine and engine-aircraft integrated level for both scenarios of hybrid operation and the benefits are established relative to the baseline engine. The performance at engine level engine specific fuel consumption (SFC), thrust specific power consumption (TSPC), and overall efficiency, shows improvement in both hybridised scenarios. Improvement in SFC is achieved due to supply of the electrical power, whereas, the boost in TSPC, and overall efficiency is attributed to the use of higher efficiency electrical drive system. Furthermore, it is observed that while the hybridised scenario performs better at engine level, the core re-optimised design exhibits a better saving for block fuel/energy consumption, due to the considerable weight savings in the core components.

Experimental evaluation of a hybrid electric propulsion system for small UAVs

2019 ◽  
Vol 92 (5) ◽  
pp. 727-736
Author(s):  
Leonardo Machado ◽  
Jay Matlock ◽  
Afzal Suleman
Keyword(s):  
Fuel Consumption ◽  
Electric Propulsion ◽  
Test Bench ◽  
Combustion Engine ◽  
Propulsion System ◽  
Content Type ◽  
Hybrid Propulsion ◽  
Electric Propulsion System ◽  
Parallel Hybrid ◽  
Hybrid Electric

Purpose This paper aims to experimentally evaluate the performance of a parallel hybrid propulsion system for use in small unmanned aerial vehicles (UAVs). Design/methodology/approach The objective is to combine all the individual components of the hybrid electric propulsion system (HEPS) into a modular test bench to characterize the performance of a parallel hybrid propulsion system, and to evaluate a rule-based controller based on the ideal operating line concept for the control of the power plant. Electric motor (EM) designed to supplement the power of the internal combustion engine (ICE) to reduce the overall fuel consumption, with the supervisory controller optimizing ICE torque. Findings The EM was able to supplement the power of the ICE to reduce fuel consumption, and proved the capability of acting as a generator to recharge the batteries drawing from ICE power. Furthermore, the controller showed that it is possible to reduce the fuel consumption with a HEPS when compared to its gasoline counterpart by running simulated representative UAV missions. The findings also highlighted the challenges to build and integrate the HEPS in small UAVs. Originality/value The modularity of the test bench allows each component to be changed to assess its impact on the performance of the system. This allows for further exploration and improvements of the HEPS in a controlled environment.

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.

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