Sizing Method and Sensitivity Analysis for Distributed Electric Propulsion Aircraft

Ma, Yiyuan; Zhang, Wei; Zhang, Yizhe; Zhang, Xingyu; Zhong, Yujiang

doi:10.2514/1.c035581

Cited by 47 publications

(14 citation statements)

References 23 publications

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“…However, the flexibility of electrical motors allows the propulsive power to be divided over multiple adjacent OTW propellers without compromising the specific weight or efficiency of the motors, thus reducing the diameter of each propulsor while maintaining an equivalent disk loading. This layout, known as over-the-wing distributed propulsion [17], can partially mitigate the penalties associated with large OTW propellers [18] and, additionally, enables short takeoff and landing operations when installed on a flap [19]. As a consequence, several studies focusing on the aerodynamic characteristics of an array of small propellers or fans placed over the wing have been performed in recent years [20][21][22].…”

Section: Experimental Investigation Of Over-the-wingmentioning

confidence: 99%

Experimental Investigation of Over-the-Wing Propeller–Boundary-Layer Interaction

et al. 2021

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This experimental study focuses on the aerodynamic interaction between an over-the-wing (OTW) propeller and a wing boundary layer. An OTW propeller is positioned above the hinge line of a wing with a trailing-edge flap. Measurements are carried out with and without axial pressure gradients by deflecting the flap and by extending the flat upper surface of the wing in the streamwise direction, respectively. Surface-pressure taps, microphones, and particle image velocimetry are combined to quantify both the time-averaged and unsteady interaction effects. Results show that the propeller generates an adverse pressure gradient on the wing surface that scales linearly with thrust and decreases with increasing blade-tip clearance. The pressure gradient is partially caused by slipstream contraction, which decelerates the flow near the wall. Additionally, the surface-pressure fluctuations generated beneath the propeller blades and slipstream are stronger than the time-averaged pressure increase due to flow deceleration. Consequently, the propeller triggers flow separation over the hinge line when the flap is deflected. A parametric study of different propeller locations indicates that increasing the tip clearance is not an effective way to mitigate flow separation. However, displacing the propeller half a radius upstream of the hinge line creates a Coandă effect, which allows the flow to remain attached.

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Section: Experimental Investigation Of Over-the-wingmentioning

confidence: 99%

Experimental Investigation of Over-the-Wing Propeller–Boundary-Layer Interaction

et al. 2021

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“…10 The German Aerospace Center (DLR) has developed and flown a 4-seat TF aircraft HY4, which is powered by a hydrogen fuel cell system. 11 Ma et al 12 developed and flight-tested a TF aircraft with distributed electric propulsion. Moreover, there are many studies on TF transport aircraft.…”

Section: Introductionmentioning

confidence: 99%

Initial weight estimation of twin-fuselage configuration in aircraft conceptual design

Yan

Elham

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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The Ultra-High Aspect Ratio Wing (UHARW) concept can improve the aircraft’s aerodynamic efficiency and reduce fuel consumption. The Twin-Fuselage (TF) configuration is one of the promising concepts for the UHARW design to reduce the wing bending moments and shear forces. This paper presents the development of a semi-empirical method for the weight estimation of TF aircraft in the initial sizing stage. A physics-based wing weight estimation method is improved for higher fidelity aerodynamic analysis and modified for composite material structures of TF aircraft. This method is used in the design of experiments and the results are applied for regression analysis to establish a semi-empirical method. Eventually, the established semi-empirical weight estimation method is integrated into a TF aircraft conceptual design and performance analysis framework. A mid-range TF aircraft and a long-range TF aircraft are designed and sized to illustrate its application and efficiency in rapidly estimating the TF aircraft weight breakdown.

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“…Moreover, twin-fuselage (TF) aircraft use the fuselage volume better than the single wide-body configuration for integrating passengers on large aircraft, thereby reducing fuselage weight by up to 40% [9]. The TF concept has already been realized in large aircraft and unmanned aerial vehicles (UAVs), such as a TF UAV [10], a general aircraft HY4 [11], WhiteKnightTwo [12], etc. However, this concept still has not been investigated in detail for transport passenger aircraft, probably due to airport infrastructure constraints (e.g., runway width and terminal access).…”

Section: Introductionmentioning

confidence: 99%

Conceptual design and comparative study of strut-braced wing and twin-fuselage aircraft configurations with ultra-high aspect ratio wings

Karpuk

Elham

2021

Aiaa Aviation 2021 Forum

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Ultra-high aspect ratio wing Strut-braced wing Twin-fuselage Advanced airframe technology Conceptual designSustainable and fuel-efficient next-generation air transportation demands a step change in aircraft performance. The ultra-high aspect ratio wings (UHARW) configuration is one key enabling strategy for improving aircraft aerodynamic efficiency and reducing fuel consumption and emissions. Unconventional aircraft configurations and advanced airframe technologies are required to address the large bending moment and shear stresses in the UHARW structure. This paper considers two promising unconventional configurations for adopting UHARW design, including strut-braced-wing (SBW) and twin-fuselage (TF), with advanced airframe technologies, i.e., active flow control, active load alleviation, and advanced airframe structures and materials. Three typical missions, including short-range (SR), medium-range (MR), and long-range (LR), are considered for aircraft design. A conceptual design and performance analysis framework for SBW and TF configurations is developed in this paper. According to the mission profile and top-level requirements proposed for each mission, an SBW and a TF configuration are designed, respectively. A comparative study is carried out to determine the best-in-class configuration of the corresponding mission to evaluate the potential of SBW and TF configurations for next-generation sustainable aviation applications. The results showed that the TF configuration has a better wing weight reduction effect than the SBW configuration, and the MR-TF and LR-TF aircraft have lower takeoff weight and fuel weight than those of the SBW aircraft for the same mission. However, due to the adjustment of the cabin dimensions for the SR-TF aircraft, the SBW configuration outperforms the TF configuration in this mission.

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Sizing Method and Sensitivity Analysis for Distributed Electric Propulsion Aircraft

Cited by 47 publications

References 23 publications

Experimental Investigation of Over-the-Wing Propeller–Boundary-Layer Interaction

Experimental Investigation of Over-the-Wing Propeller–Boundary-Layer Interaction

Initial weight estimation of twin-fuselage configuration in aircraft conceptual design

Conceptual design and comparative study of strut-braced wing and twin-fuselage aircraft configurations with ultra-high aspect ratio wings

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