Aerodynamic and structural analysis of a partial turboelectric commuter aircraft with wingtip propellers at aircraft level

Zumegen, Clemens; Strathoff, Philipp; Stumpf, Eike; Schollenberger, Michael; Lutz, Thorsten; Krämer, Ewald; Kirsch, Bastian; Friedrichs, Jens; Schubert, M.; Dafnis, Athanasios; Schröder, Kai‐Uwe

doi:10.2514/6.2022-3955

Cited by 3 publications

(9 citation statements)

References 7 publications

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“…Whereas mass estimation of most aircraft components, such as fuselage, landing gear, tail plane, is performed using semi-empirical handbook methods, wing mass estimation stands out as a tool based on analytical and semi-empirical methods. This tool takes into account the effect of point masses representing propulsion system components on the resulting wing structure and mass [16]. The secondary wing structure mass and mass penalties were estimated with semi-empirical methods; however, mass penalties due to aeroelastic effects were not included.…”

Section: Overview Of the Conceptual Aircraft Design Tool Micadomentioning

confidence: 99%

“…The results are added to the LIFTING_LINE inputs. A more detailed description of this process can be found in [16]. Remaining drag components of the lifting surfaces and the remaining aircraft components are estimated using semi-empirical handbook methods.…”

Section: Componentmentioning

confidence: 99%

“…They are supplemented by two electric wing tip propellers that are powered directly from two generators mechanically connected to the gas turbines. Subsequently, an aerodynamic optimization of the propeller positions revealed a further outboard location of the conventionally driven propellers, leading to the derivative aircraft design PT2025opt [16]. Since MICADO considers only static loads, the estimation of the wing mass was conducted based on the sizing of the wing box structure considering the three quasi-static load cases, pull-up, gust and landing.…”

Section: Reference and Concept Aircraftmentioning

confidence: 99%

“…As the wing tip propellers reduce the induced drag, their failure will increase the induced drag slightly. As the total reduction in induced drag through the use of a wing tip propulsion is only around 5% for the investigated aircraft [16], this effect is neglected. To reduce the complexity of this study, the propeller-induced side wash interaction on the vertical tail and the possible lift increase on the wing due to the induced velocity, are neglected.…”

Section: Assumptions and Restrictionsmentioning

confidence: 99%

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Influence of Electric Wing Tip Propulsion on the Sizing of the Vertical Stabilizer and Rudder in Preliminary Aircraft Design

et al. 2023

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During preliminary aircraft design, the vertical tail sizing is conventionally conducted by the use of volume coefficients. These represent a statistical approach using existing configurations’ correlating parameters, such as wing span and lever arm, to size the empennage. For a more detailed analysis with regard to control performance, the vertical tail size strongly depends on the critical loss of thrust assessment. This consideration increases in complexity for the design of the aircraft using wing tip propulsion systems. Within this study, a volume coefficient-based vertical tail plane sizing is compared to handbook methods and the possibility to reduce the necessary vertical stabilizer size is assessed with regard to the position of the engine integration and their interconnection. Two configurations, with different engine positions, of a hybrid-electric 19-seater aircraft, derived from the specifications of a Beechcraft 1900D, are compared. For both configurations two wiring options are assessed with regard to their impact on aircraft level for a partial loss of thrust. The preliminary aircraft design tool MICADO is used to size the four aircraft and propulsion system configurations using fin volume coefficients. These results are subsequently amended by handbook methods to resize the vertical stabilizer and update the configurations. The results in terms of, e.g., operating empty mass and mission fuel consumption, are compared to the original configurations without the optimized vertical stabilizer. The findings support the initial idea that the connection of the electric engines on the wing tips to their respective power source has a significant effect on the resulting torque around the yaw axis and the behaviour of the aircraft in case of a power train failure, as well as on the empty mass and trip fuel. For only one out of the four different aircraft designs and wiring configurations investigated it was possible to decrease the fin size, resulting in a 53.7% smaller vertical tail and a reduction in trip fuel of 4.9%, compared to the MICADO design results for the original fin volume coefficient.

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Section: Overview Of the Conceptual Aircraft Design Tool Micadomentioning

confidence: 99%

Section: Componentmentioning

confidence: 99%

Section: Reference and Concept Aircraftmentioning

confidence: 99%

Section: Assumptions and Restrictionsmentioning

confidence: 99%

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Influence of Electric Wing Tip Propulsion on the Sizing of the Vertical Stabilizer and Rudder in Preliminary Aircraft Design

et al. 2023

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The environmental impact of disruptive aircraft and propulsion system architectures are investigated in many studies [37], [17], [23]. Different energy generation and storage paths, in conjunction with the distributed propulsion systems are evaluated.

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confidence: 99%

A simplified automated approach for a preliminary safetyassessment of distributed electric and hybrid propulsionsystems

Albrecht,

Siegel,

Strohmayer

2024

Preprint

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The environmental impact of disruptive aircraft and propulsion system architectures are investigated in many studies. Different energy generation and storage paths, in conjunction with the distributed propulsion systems are evaluated. The complexity of those hybrid powertrains increases significantly. As, the safety impact on aircraft level is not always obvious it has to be analyzed already in a preliminary design stage. Within this work a method shall be introduced that allows a simplified automated safety assessment of any powertrain architecture. All combinations of single and multiple failures are identified and a combined failure rate is derived. As the suitability of a component failure rate is suitable depends on the analysis of its intended function. Therefore, the component failure impact has to be evaluated on aircraft level. A selection of metrics for top-level-aircraft functions, as introduced by Jézégou is used to implement an impact driven analysis for each relevant failure case. The impact on aircraft level is calculated using handbook methods. The metrics used assess the adverse effects on climb performance, lateral controllability and range degradation. For all failure combinations these effects can be validated against requirements imposed on the configuration. The configurations used for the assessment exemplarily were developed within the GNOSIS project. Results show the necessity for a reevaluation of either the architecture or the component failure rate. The method allows an early detection of configuration specific shortcomings of complex hybrid powertrain architectures, for the chosen metrics, already in a preliminary aircraft design stage.

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Aerodynamic interactions between distributed propellers and the wing of an electric commuter aircraft at cruise conditions

Schollenberger,

Kirsch,

Lutz

et al. 2024

CEAS Aeronaut J

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Beneficial interactions that occur between propellers and the wing can be used to increase the overall efficiency of an aircraft in cruise flight. Different concepts with such interacting propellers are distributed propulsion (DP) and wingtip mounted propellers (WTP). For DP, a full distribution over the entire span can be distinguished from a partial distribution, concentrating the propellers at the wing tip area. The paper focuses on the energy efficiency in cruise flight as a result of the interactions and provides a general comparison of the concepts (WTP, full and partial DP) with a Beechcraft 1900D commuter aircraft as a reference. Parametric CFD studies varying the number and the position of the propellers are performed with a half-wing model. The simulations are performed with the second-order finite-volume flow solver TAU, developed by the German Aerospace Center (DLR), employing Reynolds-averaged Navier–Stokes (RANS) equations. The propellers are modeled using an Actuator Disk (ACD). An algorithm is used to reach cruise condition by iteratively adjusting the propeller rotational speed and the wing angle of attack. The CFD results are analyzed and evaluated with respect to the overall efficiency including the aerodynamic efficiency of the wing as well as the propulsive efficiency of the propellers. The parameter study shows that in cruise flight partial DP is more efficient than a full DP. The pure WTP configuration was found as the optimum of the propeller distribution along the wing, resulting in a saving of required power of $$5.6\%$$ 5.6 % , relative to the reference configuration.

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Aerodynamic and structural analysis of a partial turboelectric commuter aircraft with wingtip propellers at aircraft level

Cited by 3 publications

References 7 publications

Influence of Electric Wing Tip Propulsion on the Sizing of the Vertical Stabilizer and Rudder in Preliminary Aircraft Design

Influence of Electric Wing Tip Propulsion on the Sizing of the Vertical Stabilizer and Rudder in Preliminary Aircraft Design

A simplified automated approach for a preliminary safetyassessment of distributed electric and hybrid propulsionsystems

Aerodynamic interactions between distributed propellers and the wing of an electric commuter aircraft at cruise conditions

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