Multidisciplinary Integrated Preliminary Design Applied to Unconventional Aircraft Configurations

Werner-Westphal, Christian; Heinze, Wolfgang; Horst, Peter

doi:10.2514/1.32138

Cited by 48 publications

(21 citation statements)

References 3 publications

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“…It highlights the most relevant methods developed for the current hybrid electric propulsion applications instead of giving a general detailed description of the tool. Figure 3 describes the general approach of the modeling structure, which follows a typical aircraft conceptual/preliminary design logic [52][53][54][55]. Some important points are discussed in the following to better illustrate the features and modeling strategies.…”

Section: Simulation Structurementioning

confidence: 99%

Conceptual Design of Operation Strategies for Hybrid Electric Aircraft

et al. 2018

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Ambitious targets to reduce emissions caused by aviation in the light of an expected ongoing rise of the air transport demand in the future drive the research of propulsion systems with lower CO 2 emissions. Regional hybrid electric aircraft (HEA) powered by conventional gas turbines and battery powered electric motors are investigated to test hybrid propulsion operation strategies. Especially the role of the battery within environmentally friendly concepts with significantly reduced carbon footprint is analyzed. Thus, a new simulation approach for HEA is introduced. The main findings underline the importance of choosing the right power-to-energy-ratio of a battery according to the flight mission. The gravimetric energy and power density of the electric storages determine the technologically feasibility of hybrid concepts. Cost competitive HEA configurations are found, but do not promise the targeted CO 2 emission savings, when the well-to-wheel system is regarded with its actual costs. Sensitivity studies are used to determine external levers that favor the profitability of HEA.

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Section: Simulation Structurementioning

confidence: 99%

Conceptual Design of Operation Strategies for Hybrid Electric Aircraft

et al. 2018

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“…In addition, the design tool is built to be able to incorporate multidisciplinary results for building surrogates, which can give reasonably accurate predictions at the overall aircraft level. Following a typical aircraft conceptual/preliminary design logic [30,[40][41][42]-especially the very comprehensive aircraft design platforms developed at the TU Braunschweig (PRADO tool [43]) and at the RWTH Aachen University (MICADO tool [42]) in Germany, some features and modelling strategies are illustrated as follows. It has to be noted that the tool developed within the EWL project has a very good compromise between complexity and fidelity levels, which is more suitable for aircraft technology assessment for such a joint research project as compared to other tools already being developed.…”

Section: General Approachmentioning

confidence: 99%

“…Besides, parameterization is also a necessity when we consider the further air transport level estimation of emissions, noise, direct operating costs, or life cycle costs, which are dependent on aircraft parameters and operation parameters. Currently, there are several prevailing ways used in industries and academia for aircraft parameterization [41,42], and most have the capability to work with the DLR CPACS data format [44,45]. In the present modelling, the parameterization method is also based on DLR CPACS format.…”

Section: Parameterization Of Aircraft Geometriesmentioning

confidence: 99%

Exploring Vehicle Level Benefits of Revolutionary Technology Progress via Aircraft Design and Optimization

et al. 2018

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Abstract:It is always a strong motivation for aeronautic researchers and engineers to reduce the aircraft emissions or even to achieve emission-free air transport. In this paper, the impacts of different game-changing technologies together on the reduction of aircraft fuel consumption and emissions are studied. In particular, a general tool has been developed for the technology assessment, integration and also for the overall aircraft multidisciplinary design optimization. The validity and robustness of the tool has been verified through comparative and sensitivity studies. The overall aircraft level technology assessment and optimization showed that promising fuel efficiency improvements are possible. Though, additional strategies are required to reach the aviation emission reduction goals for short and medium range configurations.

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“…For overall design analysis and optimization of the reference configuration, the preliminary aircraft design and optimization tool PrADO [19] of Technische Universität Braunschweig has been used as integrated design methodology. PrADO has a modular structure and simulates in its core the iterative overall design process for any desired aircraft concept.…”

Section: Design Of the Reference Short Takeoff And Landing Aircraftmentioning

confidence: 99%

Aerodynamic Installation Effects of an Over-the-Wing Propeller on a High-Lift Configuration

Müller¹,

Heinze²,

Kožulović³

et al. 2014

Journal of Aircraft

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Preliminary design studies indicate that a cruise-efficient short takeoff and landing aircraft has enhanced takeoff performance at competitive direct operating costs when using high-speed propellers in combination with internally blown flaps. The original tractor configuration is compared to an over-the-wing propeller, which allows for noise shielding. An additional geometry with partially embedded rotor similar to a channel wing is considered to increase the beneficial interaction. This paper shows the aerodynamic integration effects with a focus on climb performance and provides an assessment of the three aforementioned configurations for a simplified wing segment at takeoff conditions. Steady Reynolds-averaged Navier-Stokes simulations have been conducted using an actuator disk model and were evaluated based on the overall design. Interacting with the blown flap, the conventional tractor propeller induces large lift and drag increments due to the vectored sliptream. Although this effect is much smaller for an overthe-wing configuration, by halving the lift augmentation, the lift-to-drag ratio and the propulsive efficiency are considerably improved. Besides a moderate lift gain, the main advantage of a channel wing design is the location of the thrust vector close to the center of gravity resulting in a smaller nosedown pitching moment due to thrust. A disadvantage of over-the-wing propellers is the inhomogeneous inflow at higher velocity, which leads to oscillating blade loads and reduced efficiency.lift coefficient of aircraft C M;y = M y ∕q ∞ · S ref · MAC, pitching moment coefficient of aircraft C P;s = shaft power coefficient C T = 2 · T∕q ∞ · S ref , thrust coefficient of aircraft c = chord length of rectangular wing segment c d = section drag coefficient c l = section lift coefficient c m = section pitching moment coefficient c p = p − p ∞ ∕q ∞ , pressure coefficient D P = propeller diameter p = static pressure q ∞ = dynamic pressure of freestream S ref = wing area of reference aircraft s = semispan of rectangular wing segment T = thrust of one engine T inst = T − ΔD, installed thrust t∕t max = relative blade element thrust V ∞ = freestream velocity α = angle of attack α e = effective angle of attack at blade element β 75= propeller blade pitch angle (at 75% radius) η P = propeller efficiency η Pro = propulsive efficiency ρ ∞ = density of freestream Subscripts x,y,z = Cartesian coordinates

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Multidisciplinary Integrated Preliminary Design Applied to Unconventional Aircraft Configurations

Cited by 48 publications

References 3 publications

Conceptual Design of Operation Strategies for Hybrid Electric Aircraft

Conceptual Design of Operation Strategies for Hybrid Electric Aircraft

Exploring Vehicle Level Benefits of Revolutionary Technology Progress via Aircraft Design and Optimization

Aerodynamic Installation Effects of an Over-the-Wing Propeller on a High-Lift Configuration

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