Integrating Subsystem Sizing into the More Electric Aircraft Conceptual Design Phase

Ingram, Caroline; Dendinger, Thomas; Inclan, Eric; Charront, Yann; Handschuh, Katherine; Chakraborty, Imon; García, Elena; Mavris, Dimitri N.

doi:10.2514/6.2015-1682

Cited by 6 publications

(5 citation statements)

References 12 publications

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“…Chakraborty et al 3,5 developed an aircraft-specific conceptual design method, integrating sub-system architecture sizing with aircraft and propulsion sub-system sizing. It was further improved to cater for novel more electric architectures 4,15 . The method is aircraft specific while the computational workflows for sizing individual sub-systems as well as calculating system level performance are manually created.…”

Section: B State Of the Artmentioning

confidence: 99%

See 1 more Smart Citation

Towards Automating the Sizing Process in Conceptual (Airframe) Systems Architecting

Bile

Riaz

Guenov

et al. 2018

2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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Presented is a method for automated sizing of airframe systems, ultimately aiming to enable an efficient and interactive systems architecture evaluation process. The method takes as input the logical view of the system architecture. A source-sink approach combined with a Design Structure Matrix (DSM) sequencing algorithm is used to orchestrate the sequence of the subsystem sizing tasks. Bipartite graphs and a maximum matching algorithm are utilized to identify and construct the computational sizing workflows. A recursive algorithm, based on fundamental dimensions of additive physical quantities (e.g., weight, power, etc.) is employed to aggregate variables at the system level. The evaluation, based on representative test cases confirmed the correctness of the proposed method. The results also showed that the proposed approach overcomes certain limitations of existing methods and looks very promising as an initial systems architectural design enabler.

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Section: B State Of the Artmentioning

confidence: 99%

“…The default workflow satisfies the expression in Eq. (15). The independent inputs are as given in Table 6.…”

Section: Case-2: Under-determined System Of Modelsmentioning

confidence: 99%

Towards Automating the Sizing Process in Conceptual (Airframe) Systems Architecting

Bile

Riaz

Guenov

et al. 2018

2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

View full text Add to dashboard Cite

show abstract

“…The electro-thermal anti-icing system with CFRP composite has the advantages of simple and clean installation, convenient controllability, and efficient thermal response [ 5 ], which has attracted considerable research interest. This combination becomes highly applicable to the development of future aircraft that demands lightweight and eco-efficient systems and structures [ 6 ].…”

Section: Introductionmentioning

confidence: 99%

Impacts of Thermal and Mechanical Cycles on Electro-Thermal Anti-Icing System of CFRP Laminates Embedding Sprayable Metal Film

Zhang

2021

Materials

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The aircraft electro-thermal anti-icing system that can guarantee flight safety may be affected by periodic heating and cyclic aerodynamic force during long-term flight missions, which seems to be a potential threat to ice protection. This paper aims to investigate the impacts of thermal and mechanical cycles on heating elements of the electro-thermal anti-icing system. Specimens were manufactured with CFRP (carbon fiber reinforced polymer) laminated composite, glass fiber prepreg and copper screen, in which sprayable metal film (SMF) was embedded as the heating element. The study focuses on electric resistance variation of SMF and functional fatigue life under the cycling load. Thermal cycling tests were carried out in an insulated chamber where the specimens were heated up to 80 °C and then cooled down to −55 °C for 1000 cycles. Mechanical cycling tests were conducted on a fatigue testing machine where the specimens were imposed on tension-compression loading for 106 cycles. Results showed that the electric resistance of SMF increased with the number of loading cycles. The resistance was increased by 20% and the heating power was decreased by 16.67% after 1000 thermal cycles. During the mechanical cycling tests, it was found that the heating element was destructed before the structural failure, which indicated that the fatigue life of function was lower than that of the structure.

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“…To prevent the aircraft wings and stabilizers from ice accretion, all commercial aircrafts are equipped with ice protection systems [2]. Generally, the thermal anti-icing system is the most widely used for large commercial aircraft and it also accounts for about 20% energy consumption of the aircraft engines [3][4][5]. Therefore, it is critical to optimize the thermal anti-icing system to achieve energy conservation, which can lighten the take-off weight and extend the flying range [6,7].…”

Section: Introductionmentioning

confidence: 99%

Investigation on the Mechanism of Heat Load Reduction for the Thermal Anti-Icing System

Zhu

Zhang

2020

Energies

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The aircraft ice protection system that can guarantee flight safety consumes a part of the energy of the aircraft, which is necessary to be optimized. A study for the mechanism of the heat load reduction in the thermal anti-icing system under the evaporative mode was presented. Based on the relationship between the anti-icing heat load and the heating power distribution, an optimization method involved in the genetic algorithm was adopted to optimize the anti-icing heat load and obtain the optimal heating power distribution. An experiment carried out in an icing wind tunnel was conducted to validate the optimized results. The mechanism of the anti-icing heat load reduction was revealed by analyzing the influences of the key factors, such as the heating range, the surface temperature and the convective heat transfer coefficient. The results show that the reduction in the anti-icing heat load is actually the decrease in the convective heat load. In the evaporative mode, decreasing the heating range outside the water droplet impinging limit can reduce the convective heat load. Evaporating the runback water in the high-temperature region can lead to the less convective heat load. For the airfoil, the heating power distribution that has an opposite trend with the convective heat transfer coefficient can reduce the convective heat load. Thus, the optimal heating power distribution has such a trend that is low at the leading edge, high at the water droplet impinging limit and zero at the end of the protected area.

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Integrating Subsystem Sizing into the More Electric Aircraft Conceptual Design Phase

Cited by 6 publications

References 12 publications

Towards Automating the Sizing Process in Conceptual (Airframe) Systems Architecting

Towards Automating the Sizing Process in Conceptual (Airframe) Systems Architecting

Impacts of Thermal and Mechanical Cycles on Electro-Thermal Anti-Icing System of CFRP Laminates Embedding Sprayable Metal Film

Investigation on the Mechanism of Heat Load Reduction for the Thermal Anti-Icing System

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