Trajectory Optimization of Electric Aircraft Subject to Subsystem Thermal Constraints

Falck, Robert; Chin, Jeffrey; Schnulo, Sydney L.; Burt, Jonathan M.; Gray, Justin S.

doi:10.2514/6.2017-4002

Cited by 62 publications

(38 citation statements)

References 17 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…with the the battery current I Bat and the battery voltage U Bat = 358.9 V, which is assumed to be constant over the state of charge here. Solved for I Bat , Equation (11) reads as (12) This equation can be found in, e.g., [11]. In addition, the Peukert effect [9] is considered, due to which the effective capacity of the battery is decreasing with increasing current taken from the battery.…”

Section: Modelling Aspectsmentioning

confidence: 99%

“…Both of them do not take the Peukert effect into account in their model description. A common numerical solution of the trajectory optimization problem of more complex mathematical models is presented in [12][13][14].…”

Section: Introductionmentioning

confidence: 99%

“…Optimized trajectories regarding technical limitations due to maximal temperature of the propulsion components are shown in [12]. A complex efficiency model of each component is taken to perform trajectory optimization in [13,14].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

The Impact of Peukert-Effect on Optimal Control of a Battery-Electrically Driven Airplane

2020

View full text Add to dashboard Cite

Further investigation on the impact of the so called Peukert effect on optimal control of a battery-electrically driven airplane is presented. To analyse the impact of the Peukert effect, an ideal model without this battery concerning effect and a realistic model containing different Peukert exponents are built up. For the different models, optimal trajectories are generated and altitude dependency of a maximum range horizontal flight criterion is investigated. On the one hand, it can be shown that the Peukert effect causes a special form of optimal trajectories. On the other hand, it turns out that range optimal horizontal flight is more efficient in lower altitudes, if the Peukert effect is taken into account. The particular efficiency properties of battery electrical propulsion can be explained with its consumption characteristic, which appear in form of a power function with real exponent.

show abstract

Section: Modelling Aspectsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

The Impact of Peukert-Effect on Optimal Control of a Battery-Electrically Driven Airplane

2020

View full text Add to dashboard Cite

show abstract

“…1) with goals to reduce the energy required for cruise by 4.8x without sacrificing cruise speed or takeoff distance [9]. Since the X-57, there has been a significant increase in the amount of research regarding DEP for thin-haul commuters in areas such as economics [10], multidisciplinary modeling requirements [11], wing aerodynamic analysis [8,9,12], motor design [13], avionics [14], hybrid propulsion [15], trajectory thermal considerations [16], certification and landing safety [17] and large scale multidisciplinary optimization of design and trajectory [7].…”

Section: Introductionmentioning

confidence: 99%

Takeoff and Performance Trade-Offs of Retrofit Distributed Electric Propulsion for Urban Transport

Moore

Ning

2019

Journal of Aircraft

View full text Add to dashboard Cite

While vertical takeoff and landing aircraft have shown promise for urban air transport, distributed electric propulsion on existing aircraft may offer immediately implementable alternatives. Distributed electric propulsion could potentially decrease takeoff distances enough to enable thousands of potential inter-city runways. This conceptual study explores the effects of a retrofit of open-bladed electric propulsion units. To model and explore the design space we use blade element momentum method, vortex lattice method, linear-beam finite element analysis, classical laminate theory, composite failure, empirically-based blade noise modeling, motor and motor-controller mass models, and gradient-based optimization. With liftoff time of seconds and the safe total field length for this aircraft type undefined, we focused on the minimum conceptual takeoff distance. We found that 16 propellers could reduce the takeoff distance by over 50% compared to the optimal 2 propeller case. This resulted in a conceptual minimum takeoff distance of 20.5 meters to clear a 50 ft (15.24 m) obstacle. We also found that when decreasing the allowable noise by approximately 10 dBa, the 8 propeller case performed the best with a 43% reduction in takeoff distance compared to the optimal 2 propeller case. This resulted in a noise-restricted conceptual minimum takeoff distance of 95 meters.

show abstract

“…One other hand, OpenMDAO has ability to subdivide a problem into groups or components and link their inputs and outputs, made it easier to decompose large and complex problems. OpenMDAO has been used to solve MDO problems in satellite design [8], wind turbine design [9], aircraft design [10] and aircraft trajectory optimization [11].…”

Section: A Open Mdao Frameworkmentioning

confidence: 99%

Aero structural optimization for sailplane wing in preliminary design

2018

J. adv. tec. eng. res.

View full text Add to dashboard Cite

The purpose of this research is to obtain optimized sailplane wing design, which contributes to better performance in terms of range and endurance. This paper presents aerostructural design optimization using Multidisciplinary Design Optimization approach (MDO). This is carried out using Open Aero Struct (OAS), an open-source low-fidelity aerostructural analysis and optimization tool written in Python and developed in NASA's Open MDAO framework. The aerostructural model in OAS coupled a Vortex Lattice Method for aerodynamic with a 1-D FiniteElement Analysis for structure, to model the sailplane wing. An aerostructural optimization problem was formulated to minimize the Sink Speed, as the objective function, with varying twelve design variables, and subjected to two constraints. An initial simple wing design is used as baseline for the optimization. The indings of the aerostructural optimization indicated that the optimized wing exhibited improvements in both disciplines, resulting a better cross-country performance for the sailplane in terms of range and endurance. The optimized wing achieved increase of 37% in endurance and 27% in range.

show abstract

Trajectory Optimization of Electric Aircraft Subject to Subsystem Thermal Constraints

Cited by 62 publications

References 17 publications

The Impact of Peukert-Effect on Optimal Control of a Battery-Electrically Driven Airplane

The Impact of Peukert-Effect on Optimal Control of a Battery-Electrically Driven Airplane

Takeoff and Performance Trade-Offs of Retrofit Distributed Electric Propulsion for Urban Transport

Aero structural optimization for sailplane wing in preliminary design

Contact Info

Product

Resources

About