Simultaneous Combined Optimal Design and Control Formulation for Aircraft Hybrid-Electric Propulsion Systems

Nakka, Sai Krishna Sumanth; Alexander-Ramos, Michael J.

doi:10.2514/1.c035678

Cited by 19 publications

(6 citation statements)

References 23 publications

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“…P max maxP t@VTOL ; P t@Transition ; P t@Cruise (13) The maximum power for the aircraft P total;max is used for the hybridization of the propulsion system. The maximum powers of the thrusters P t1;max and P t2;max are used for sizing the components.…”

Section: Step 1: Calculation Of Maximum Powermentioning

confidence: 99%

“…In the field of transport aircraft, research on hybrid-electric aircraft (HEA), which employ a hybrid-electric propulsion system (HEPS), has been actively conducted in recent years [2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18]. A HEPS is a propulsion system that combines electric and mechanical powertrains.…”

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confidence: 99%

“…However, previous studies [6][7][8][9][10][11][12][13][14][15][16][17][18][19][20][21][22] concerning the HEA design have not examined the HEPS-powered VTOL UAM vehicle's inherent characteristics (diversity for configuration, flight mechanism, and HEPS architectures) because most of them only focused on combining HEPS with the conventional aircraft sizing method. Pornet et al [6] reconstructed the thrust table using a hybridization factor and supplemented the fuel-flow table with an energy table to consider the parallel-HEPS.…”

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confidence: 99%

“…Sgueglia et al [7,8] developed a version of the Fixed Aircraft Sizing Tool [12] tailored to the HEA sizing and integrated sizing tool with OpenMDAO to conduct the multidisciplinary design optimization. Nakka and Alexander-Ramos [13] suggested a design methodology applied to the simultaneous formulation within the multidisciplinary dynamic system design optimization codesign method. Because these studies were limited to series-HEPS only, it was difficult to consider the diversity of HEPS architectures.…”

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confidence: 99%

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Generic Design Methodology for Vertical Takeoff and Landing Aircraft with Hybrid-Electric Propulsion

Lee

Lim

Yee

2022

Journal of Aircraft

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This paper proposes a conceptual methodology for designing vertical takeoff and landing aircraft with a hybridelectric propulsion system as an alternative to facilitate intercity missions for urban air mobility. Four new modules are developed to consider the diversity of configurations, flight mechanisms, and hybrid-electric propulsion system architectures. The flight-analysis module is proposed to account for various lift-and thrust-generating devices. The hybrid-electric propulsion system sizing module is modified for the vertical takeoff and landing aircraft by additionally considering transition flight. Based on a new proposed battery charge/discharge criterion, the mission-analysis module is constructed to predict the battery capacity and fuel consumption required for a given mission. The weight-estimation module is also developed considering the weight of the mechanical and electric powertrains. The proposed methodology is demonstrated by designing an urban air mobility vehicle and comparing the results with those of other sizing tools. A systematic comparative study and design optimization are carried out to highlight the improvement in the performance of the hybrid-electric-powered vertical takeoff and landing aircraft compared to its battery-driven counterpart. The extended mission range of the designed aircraft presents the possibility of intercity urban air mobility vehicles.

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Section: Step 1: Calculation Of Maximum Powermentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

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Generic Design Methodology for Vertical Takeoff and Landing Aircraft with Hybrid-Electric Propulsion

Lee

Lim

Yee

2022

Journal of Aircraft

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“…Carlo [19] proposed an energy-optimal power management strategy to reduce energy expenditure by properly setting throttles of internal combustion engine and electric motor for a light single-propeller hybrid electric motor glider. Nakka et al [20] proposed a combined optimal design and control method using a simultaneous formulatoin of multidisciplinary dynamic system design optimizaion to enable the integration of EMS with hybrid electric propulsoin configuration component sizing. Xie et al [21] proposed a fuzzy logic based equivalent consumption optimization for hybrid electric unmanned aerial vehicles.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear Model Predictive Control-Based Optimal Energy Management for Hybrid Electric Aircraft Considering Aerodynamics-Propulsion Coupling Effects

Zhang

Roumeliotis

Zolotas

2022

IEEE Trans. Transp. Electrific.

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Hybrid electric propulsion systems have been identified as the feasible solutions for regional jets and narrowbody aircraft to reduce block fuel burn, emissions, and operating cost. Different from land-based vehicles, weight is a major consideration for air transport due to weight-related lift-induced drag penalty. Thus, energy onboard balance, variation in aircraft mass during flight and the aerodynamics-propulsion coupling effects should be considered in hybrid electric aircraft energy management strategy (EMS) while satisfying aircraft maximum take-off weight constraints. In this paper, a Nonlinear Model Predictive Control based optimal energy management scheme (MPC-EMS) has been proposed to minimize the block fuel burn during flight. Firstly, the Artificial Neural Network (ANN) model is adopted with back-propagation algorithm to predict turbofan engine performance with high accuracy and computational efficiency, meanwhile gas turbine-electrical powertrain coupling effects are investigated and analysed for typical operating conditions. Then, by combining a point-mass aircraft dynamic model, nonlinear model predictive control with Cross-Entropy Method (CEM) is proposed to obtain optimal energy management based on a fully coupled aerodynamicspropulsion hybrid electric aircraft model. Besides, this state-constrained optimal control problem is re-formulated as a state-unconstrained problem with penalty function to reduce the computational load. Finally, the proposed MPC EMS algorithm is applied to Boeing 737-800 aircraft with mechanically parallel hybrid electric propulsion configuration to minimize the block fuel burn and compared with the optimization results using global Genetic Algorithm (GA) based EMS. The simulation results indicate that the proposed MPC-EMS can significantly reduce the computational time by more than 97% while obtaining similar objectives of block fuel burn and emissions reduction.

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Simultaneous optimal system and controller design for multibody systems with joint friction using direct sensitivities

Verulkar,

Sandu,

Sandu

et al. 2024

Multibody Syst Dyn

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Real-world multibody systems are often subject to phenomena like friction, joint clearances, and external events. These phenomena can significantly impact the optimal design of the system and its controller. This work addresses the gradient-based optimization methodology for multibody dynamic systems with joint friction using a direct sensitivity approach. The Brown–McPhee model has been used to characterize the joint friction in the system. This model is suitable for the study due to its accuracy for dynamic simulation and its compatibility with sensitivity analysis. This novel methodology supports codesign of the multibody system and its controller, which is especially relevant for applications like robotics and servo-mechanical systems, where the actuation and design are highly dependent on each other. Numerical results are obtained using a software package written in Julia with state-of-the-art libraries for automatic differentiation and differential equations. Three case studies are provided to demonstrate the attractive properties of simultaneous optimal design and control approach for certain applications.

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Simultaneous Combined Optimal Design and Control Formulation for Aircraft Hybrid-Electric Propulsion Systems

Cited by 19 publications

References 23 publications

Generic Design Methodology for Vertical Takeoff and Landing Aircraft with Hybrid-Electric Propulsion

Generic Design Methodology for Vertical Takeoff and Landing Aircraft with Hybrid-Electric Propulsion

Nonlinear Model Predictive Control-Based Optimal Energy Management for Hybrid Electric Aircraft Considering Aerodynamics-Propulsion Coupling Effects

Simultaneous optimal system and controller design for multibody systems with joint friction using direct sensitivities

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