Reusable Surrogate Models for the Preliminary Design of Aircraft Application Systems

Giorgi, F. De; Budinger, Marc; Hazyuk, Ion; Reysset, Aurélien; Sanchez, Florian

doi:10.2514/1.j059486

Cited by 8 publications

(11 citation statements)

References 30 publications

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“…The drag coefficient C Dsc can be estimated by using different abacuses depending on the mass flow ratio ṁ ṁ0 , the Mach number Ma, and geometric parameters [10]. A generic model for this coefficient can be obtained by computing a surrogate model that is established by using the variable power law method (VPLM) [40,41] and a design of experiments from abacuses. Computations show that the C Dsc model can be simplified to a function based on only the two main variables, the Mach number Ma, and the mass flow ratio ṁ ṁ0 (obtained by using [10]), and that a polynomial model gives better results than variable power laws.…”

Section: Dragmentioning

confidence: 99%

Modeling and Design Optimization of an Electric Environmental Control System for Commercial Passenger Aircraft

et al. 2023

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The aircraft environmental control system (ECS) is the second-highest fuel consumer system, behind the propulsion system. To reduce fuel consumption, one research direction intends to replace conventional aircraft with more electric aircraft. Thus, new electric architectures have to be designed for each system, such as for the ECS. In this paper, an electric ECS is modeled and then sized and optimized for different sizing scenarios with the aim of minimizing fuel consumption at the aircraft level. For the system and for each component, such as air inlets and heat exchangers, parametric models are developed to allow the prediction of relevant characteristics. These models, developed in order to be adapted to aircraft design issues, are of different types, such as scaling laws and surrogate models. They are then assembled to build a preliminary sizing procedure for the ECS by using a multidisciplinary design analysis and optimization (MDAO) formulation. Results show that the ECS design is highly dependent on the sizing scenario considered. An approach to size the ECS globally with respect to all the sizing scenarios leads to an ECS that accounts for around 200 N of drag, 190 kW of electric power, and 1500 kg of mass for the CeRAS aircraft.

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Section: Dragmentioning

confidence: 99%

Modeling and Design Optimization of an Electric Environmental Control System for Commercial Passenger Aircraft

et al. 2023

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“…To tackle these issues, multidisciplinary design optimization (MDO) approaches that investigate aircraft architecture optimization with new technologies of components are relevant. As illustrated in Figure 6, such ideas have been promoted for complex system optimization involving multiple fields of disciplines and various design levels, from elementary components to the whole system [28][29][30][31][32][33][34][35][36][37][38][39][40].…”

Section: Literature Review On Electrically Propelled Aircraftmentioning

confidence: 99%

“…Energies 2023, 16, 6831 5 of 38 these issues, multidisciplinary design optimization (MDO) approaches that investigate aircraft architecture optimization with new technologies of components are relevant. As illustrated in Figure 6, such ideas have been promoted for complex system optimization involving multiple fields of disciplines and various design levels, from elementary components to the whole system [28][29][30][31][32][33][34][35][36][37][38][39][40]. However, MDOs are generally based on rough models often centred around specific power and energies (i.e., kW/kg, kWh/kg) to simultaneously integrate the aircraft architecture with the powertrain and the aerodynamic structure design inside the MDO process.…”

Section: Literature Review On Electrically Propelled Aircraftmentioning

confidence: 99%

A Review of Powertrain Electrification for Greener Aircraft

Roboam

2023

Energies

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This review proposes an overview of hybrid electric and full electric powertrains dedicated to greener aircraft in the “sky decarbonization” context. After having situated the state of the art and context of energy hybridization in the aviation sector, we propose the visit of several architectures for powertrain electrification, situating the potential benefits but also the main challenges to be faced to takeoff these new solutions. Then, as a first example, we consider the EU project “HASTECS” (Hybrid Aircraft: reSearch on Thermal and Electric Components and Systems) in the framework of Clean Sky 2. It relates to a series hybrid chain integrated into a regional aircraft. This energy system integrates especially power electronics and electric machines with a high degree of integration, which raises the “thermal challenge” and the need to integrate cooling devices. Through the snowball effects typical of the aviation sector, this example emphasizes how important it is to “hunt for kilos”, an alternative solution consisting of eliminating the power electronics within the powertrain. This is why we propose a second example, which concerns an AC power channel without power electronics that only integrates synchronous magnet machines (generator and motor) directly coupled on an AC bus. This last architecture nevertheless raises questions in terms of stability, with one solution being to insert an auxiliary hybridization branch via battery storage. Theoretical analyses and experiments at a reduced power scale show the viability of this concept. Finally, some recommendations for future research with potential technological breakthroughs complete that review.

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“…Taking the number of input parameters G i as q, the output parameter G 0 can be obtained through the parameter estimation model as follows [31]:…”

Section: Parameter Estimation Model Of the Frameless Motormentioning

confidence: 99%

Investigations on System Integration Method and Optimum Design Method of Electro-Mechanical Actuator System

Zheng

Han

et al. 2023

Actuators

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With technological advances and industrial upgrading, high-performance equipment has put higher demands on the performance of electro-mechanical actuators. With a view to making electro-mechanical actuators more reliable and integrated, firstly, an integrated electro-mechanical actuator module (IEMM) with multiple structural forms was proposed in this paper, and a comparative analysis was performed on the characteristics of different transmission schemes. Then, the feasibility of manufacturing the IEMM’s main bearing components using Carbon Fiber Reinforced Polymer (CFRP) with higher specific stiffness, specific modulus and specific strength was demonstrated by finite element simulation (FEA) software, in a bid to further reduce the weight of the IEMM. Next, a parameter estimation model, a heating power calculation model, and a thermal resistance calculation model were built, so that there is no need to rebuild the whole system model under different demand indexes. On this basis, a multi-objective optimization design model was built with light weight, low power loss, and high level of integration as optimization aims to achieve better comprehensive performance in the early design phase of the IEMM system. However, IEMM’s higher level of integration and its shell made of CFRP with a thermal conductivity of less than 5 W/m°C posed a challenge to the heat dissipation of the motor stator. Therefore, a thermal network model needs to be created in AMESim to evaluate the temperature of IEMM’s parts and components under different working conditions. Finally, the process of IEMM performance optimization design was described and improved, and performance optimization design was conducted by taking one of IEMM’s transmission schemes as an example.

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Reusable Surrogate Models for the Preliminary Design of Aircraft Application Systems

Cited by 8 publications

References 30 publications

Modeling and Design Optimization of an Electric Environmental Control System for Commercial Passenger Aircraft

Modeling and Design Optimization of an Electric Environmental Control System for Commercial Passenger Aircraft

A Review of Powertrain Electrification for Greener Aircraft

Investigations on System Integration Method and Optimum Design Method of Electro-Mechanical Actuator System

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