Dynamic Analysis of a Series Hybrid–Electric Powertrain for an Unmanned Aerial Vehicle

2021 ◽  
pp. 1-13
Author(s):  
Darren Dehesa ◽  
Shyam Menon ◽  
Sean Brown ◽  
Christopher Hagen
Keyword(s):  
Dynamic Analysis ◽  
Unmanned Aerial Vehicle ◽  
Aerial Vehicle ◽  
Hybrid Electric ◽  
Hybrid Electric Powertrain

scholarly journals Typical Fault Estimation and Dynamic Analysis of a Leader-Follower Unmanned Aerial Vehicle Formation

2021 ◽  
Vol 2021 ◽  
pp. 1-16
Author(s):  
Jian Shen ◽  
Qingyu Zhu ◽  
Xiaoguang Wang ◽  
Pengyun Chen
Keyword(s):  
Dynamic Analysis ◽  
Unmanned Aerial Vehicle ◽  
Cooperative Control ◽  
Health Management ◽  
Fault Tolerant ◽  
Design Method ◽  
Observer Design ◽  
Fault Estimation ◽  
Proportional Navigation ◽  
Aerial Vehicle

In this paper, the typical fault estimation and dynamic analysis are presented for a leader-follower unmanned aerial vehicle (UAV) formation system with external disturbances. Firstly, a dynamic model with proportional navigation guidance (PNG) control of the UAV formation is built. Then, an intermediate observer design method is adopted to estimate the system states and faults simultaneously. Based on the graph theory, the topology relationship between each node in the UAV formation has been also analyzed. The estimator and the system error have been created. Moreover, the typical faults, including the components failure, airframe damage, communication failure, formation collision, and environmental impact, are also discussed for the UAV system. Based on the fault-tolerant strategy, five familiar fault models are proposed from the perspectives of fault estimation, dynamical disturbances, and formation cooperative control. With an analysis of the results of states and faults estimation, the actuator faults can be estimated precisely with component failure and wind disturbances. Furthermore, the basic dynamic characteristics of the UAV formation are discussed. Besides, a comparison of two cases related to the wind disturbance has been accomplished to verify the performance of the fault estimator and controller. The results illustrate the credibility and applicability of the fault estimation and dynamic control strategies for the UAV system which are proposed in this paper. Finally, an extension about the UAV formation prognostic health management system is expounded from the point of view of the fault-tolerant control, dynamic modeling, and multifault estimation.

scholarly journals Synergy Effects in Electric and Hybrid Electric Aircraft

Aerospace ◽  
2019 ◽  
Vol 6 (3) ◽  
pp. 32 ◽  
Author(s):  
Teresa Donateo ◽  
Claudia Lucia De Pascalis ◽  
Antonio Ficarella
Keyword(s):  
Power System ◽  
Unmanned Aerial Vehicle ◽  
Weight Ratio ◽  
Electric Power System ◽  
Pollutant Emissions ◽  
Synergic Effect ◽  
Vtol Uav ◽  
Aerial Vehicle ◽  
Hybrid Electric ◽  
Different Levels

The interest in electric and hybrid electric power system has been increasing, in recent times, due to the benefits of this technology, such as high power-to-weight ratio, reliability, compactness, quietness, and, above all, elimination of local pollutant emissions. One of the key factors of these technologies is the possibility to exploit the synergy between powertrain, structure, and mission. This investigation addresses this topic by applying multi-objective optimization to two test cases — a fixed-wing, tail-sitter, Vertical Take-off and Landing Unmanned Aerial Vehicle (VTOL-UAV), and a Medium-Altitude Long-Endurance Unmanned Aerial Vehicle (MALE-UAV). Cruise time and payload weight were selected as goals for the first optimization problem, while fuel consumption and electric endurance were selected for the second one. The optimizations were performed with Non-dominated Sorting Genetic Algorithm-II (NSGA-II) and S-Metric Selection Evolutionary Multiobjective Algorithm (SMS-EMOA), by taking several constraints into account. The VTOL-UAV optimization was performed, at different levels (structure only, power system only, structure and power system together). To better underline the synergic effect of electrification, the potential benefit of structural integration and multi-functionalization was also addressed. The optimization of the MALE-UAV was performed at two different levels (power system only, power system, and mission profile together), to explore the synergic effect of hybridization. Results showed that large improvements could be obtained, either in the first test case when, both, the powertrain design and the aircraft structure were considered, and in the optimization of the hybrid electric UAV, where the optimization of the aircraft flight path gave a strong contribution to the overall performances.

Conceptual Design and Simulation of a Small Hybrid-Electric Unmanned Aerial Vehicle

2006 ◽  
Vol 43 (5) ◽  
pp. 1490-1498 ◽  
Author(s):  
Frederick G. Harmon ◽  
Andrew A. Frank ◽  
Jean-Jacques Chattot
Keyword(s):  
Conceptual Design ◽  
Unmanned Aerial Vehicle ◽  
Aerial Vehicle ◽  
Hybrid Electric

Dynamic Analysis of the Meridian Unmanned Aerial Vehicle

2014 ◽  
Author(s):  
Nathan A. Smith ◽  
Luiz Toledo ◽  
Daniel Kennedy ◽  
Alex Sizemore
Keyword(s):  
Dynamic Analysis ◽  
Unmanned Aerial Vehicle ◽  
Aerial Vehicle

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.

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