A Methodology for Systems Integration in Aircraft Conceptual Design - Estimation of Required Space

Liscouët-Hanke, Susan; Huynh, Kenny

doi:10.4271/2013-01-2235

Cited by 7 publications

(5 citation statements)

References 1 publication

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“…In addition to weight estimation, the three-dimensional layout and estimating the space occupied by the aircraft system plays a crucial role in conceptual design [24]. The estimation of available space for systems installation within the aircraft is particularly important for hybrid-electric aircraft configurations in which significant space might be required to install batteries.…”

Section: Literature Reviewmentioning

confidence: 99%

Systems Integration Framework for Hybrid-Electric Commuter and Regional Aircraft

2023

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System integration is one of the key challenges to bringing future hybrid-electric and all-electric aircraft into the market. In addition, retrofitting and redesigning existing aircraft are potential paths toward achieving hybrid and all-electric flight, which are even more challenging goals from a system integration perspective. Therefore, integration tools that bridge the gap between the aircraft and the subsystem level need to be developed for use in the conceptual design stage to address current system integration challenges, such as the use of space, the share between propulsive and secondary power, required level of electrification, safety, and thermal management. This paper presents a multidisciplinary design analysis (MDA) framework that integrates aircraft and subsystem sizing tools. In addition, this paper includes improved physics-based subsystem sizing methods that are also applicable to smaller, commuter, or regional aircraft. The capabilities of the developed framework and tools are presented for a case study covering the redesign of the DO-228 with a hybrid-electric propulsion system in combination with the electrification of its systems architecture and different subsystem technologies.

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Section: Literature Reviewmentioning

confidence: 99%

Systems Integration Framework for Hybrid-Electric Commuter and Regional Aircraft

2023

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“…As discussed in the Conventional Approach section, the kinematics is essentially constrained by the installation envelope. For this redesign, a reaction/kick-link mount 10,22 is implemented to increase the lever arm and preserve the composite primary structure (rear spar) from excessive loading. The piston head dimensions are adjusted following the industry standards.…”

Section: Sizingmentioning

confidence: 99%

“…The kinematics depends on the actuator dimensions and mounting, for example, flange, pin-to-pin, or reaction/kick-link mount. 10,22 The mounting depends on the installation environment characteristics, for example, space envelope, structural attachment points, and accessibility for maintenance. It is a highly iterative step because the kinematics and actuator dimensions are interdependent.…”

Section: Design Challenge: Actuator Oversizingmentioning

confidence: 99%

A model-based design methodology for flight control systems: Global 7500 pitch control case study

Liscouët

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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This article introduces an original model-based design methodology addressing a high-performance aircraft design challenge: conflicting performance requirements. The case study of the Global 7500 elevator actuation system also provides in-depth insight into the complex design process of today’s fly-by-wire flight control systems. The methodology presented here redefines the aircraft manufacturer’s involvement in the design process of the systems, implementing analysis and iteration capabilities early in system development. To this end, it introduces a novel modeling approach for analyzing loaded rate requirements by simulating closed-loop performance with a generic nonlinear second-order state filter, including the main performance limitations without requiring a preliminary design definition. In this way, it provides means to mature the system requirements and addresses requirement conflicts upfront. Then, a simulation-based preliminary sizing and performance assessment validates the candidate design concept. It also secures the preliminary design phase by implementing advanced design uncertainties and involving interfacing systems and disciplines early in the process. The redefined methodology identified directly that the problem’s root cause was a conflict between stability and control and flutter protection requirements. It also indicated that the first sizing driver is the response time required under a specific failure case. These findings lead to an optimal elevator actuator design compliant with matured performance requirements. Thus, the methodology resolved a design challenge blocking the Global 7500 aircraft development and prevented redesign occurrences later during the detailed design phase. In this way, it directly contributed to the successful development of the Global 7500 and its optimal operational performance. This methodology applies to future aircraft design challenges, and the technical insight provides valuable lessons learned for high-performance T-tail business jets.

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“…The causal diagram is a graphical representation in which each entity is modelled by a block and the interactions are identified by oriented arrows. This formalism was used to organize the sizing process of a flight control actuator [17]. On a causal diagram, it may be difficult to rapidly visualize the couplings between the different entities.…”

Section: Evaluation Function : Multi-physical Sizing Processmentioning

confidence: 99%

Optimal design of the Integrated Modular Power Electronics Cabinet

Giraud

Budinger

Roboam

et al. 2016

Aerospace Science and Technology

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This paper deals with a new concept of electrical power distribution system called IMPEC for Integrated Modular Power Electronics Cabinet. The paper defines methods aiming at carrying out an optimal design of IMPEC, the main variables being on one hand the number and size of power electronics module. On the other hand, reconfigurations between these modules and electrical loads are also optimized.The formalization of the problem highlights that designers must deal simultaneously with a combinatorial explosion and a multi-physical system sizing. The main objective of the study is to propose a methodological framework for solving this original optimal design problem. A heuristic-based algorithm is developed to solve this combinatorial optimization problem. A particular attention is paid to develop a weight estimation procedure using generic sizing models. Finally a mapping is performed to identify the best solutions and to highlight the technological components having the most significant sensitivity on the complete system weight.

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A Methodology for Systems Integration in Aircraft Conceptual Design - Estimation of Required Space

Cited by 7 publications

References 1 publication

Systems Integration Framework for Hybrid-Electric Commuter and Regional Aircraft

Systems Integration Framework for Hybrid-Electric Commuter and Regional Aircraft

A model-based design methodology for flight control systems: Global 7500 pitch control case study

Optimal design of the Integrated Modular Power Electronics Cabinet

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