The Application of Reliability Methods for Aircraft Design Project Management

Vieira, Darli Rodrigues; Rebaiaia, Mohamed-Larbi; Chain, Milena Chang

doi:10.4236/ajibm.2016.69094

Cited by 12 publications

(7 citation statements)

References 26 publications

(25 reference statements)

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“…Although ARP 4761 works as safety assessment guidance in the certification process, this assessment process is mainly performed using reliability prediction methods, such as failure modes and effects analysis, fault tree analysis (Saglimbene, 2009), common cause analysis, failure modes and effects summary (Vieira et al , 2016); therefore, there is a conjunction between safety assessment and reliability requirements.…”

Section: Certification Requirements and Reliability Of Aircraftmentioning

confidence: 99%

Initial airworthiness requirements for aircraft electric propulsion

Yildiz

2022

AEAT

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Purpose The purpose of this paper is to analyze the electric propulsion use in civil aviation and propose a framework for certification of electric propulsion subsystems. Although electric propulsion architectures are discussed as key technology for the future of aviation, the industry standards as well as regulations fail to cover the application in full extent, specifically for commercial large airplanes. This paper proposes an approach for the analyses of reliability and certification of the new-generation propulsion system by pointing out the “common structure” among the possible architectures. Design/methodology/approach The research process used in this paper consists of following steps: the challenges of the hybrid-electric propulsion is listed, the architectures of the hybrid-electric applications in the literature are identified, the differences of the hybrid architectures from the present applications by means of application and standardization are discovered, the architectures are analyzed and the two main subsystems are defined – the present combustion system and the common unit, which is a similar structure used in all-electric aircraft. For this purpose, the standards used for design basis and certification of the present propulsion system and their relationship with the subsystems of the architectures have been analyzed. The procedure for the reliability assessment of the system is given, a framework for the safety assessment and the certification of the propulsion systems is proposed to make it easier and without sacrificing the already accumulated experience. This study shows that by using the common unit, the present certification framework can be used, by focusing on the reliability of the common unit and its integration with the rest of the architecture. Findings A specific definition of common unit is proposed, to point out the difference in certification efforts of hybrid-electric propulsion architectures. Yet, there is no data available for propulsion-level airborne battery and electrical systems to assess the reliability. Thus, dividing the propulsion system into two main systems and providing a model for certification of the common unit sub-system would be beneficial for easy deployment of the hybrid architectures both for design and for certification. In this paper, it is proposed that by using this common unit, the present certification framework can be used as it is, by focusing on the reliability of the common unit and its integration with the rest of the architecture. Practical implications The aircraft certification regulations act in two ways: they provide a starting point for new design projects, and they are a basis for certification of the final system. This study aims to draw focus on certification issues on the new-generation hybrid-electric propulsion systems. With the introduction of hybrid-electric propulsion for large aircraft, the present standards (CS-25, CS-E, CS-P, CS-Battery and CS-APU) create an obstacle for further progress as their borders get into each other. Instead of developing a new set of standard(s), this paper proposes a new approach by dividing the propulsion system into two subsystems. Originality/value This research proposes a definition of “common unit” for simplification of the hybrid-electric propulsion architectures for large civil aircraft. The common unit consists of both battery and electrical components and their reliability shall be considered for hybrid-electric propulsion.

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Section: Certification Requirements and Reliability Of Aircraftmentioning

confidence: 99%

Initial airworthiness requirements for aircraft electric propulsion

Yildiz

2022

AEAT

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“…The reliability of an aircraft must be maintained during the operation stage of the aircraft as well. Increasing rate of using air travel creates safety concerns naturally, thus the term "airworthiness" certification, which will be explained later, is introduced and applied by aviation authorities to check if the aircraft producers follow the reliability requirements (Vieira et al, 2016).…”

Section: Reliability and Maintenance In Aviationmentioning

confidence: 99%

An Overview to Unmanned Aerial Vehicles from Perspectives of Quality and Safety Management in Aviation

Şenvar

ÜNVER

2022

IJERAD

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“…The use of block models (or block diagrams) is a standard way of graphically representing a system made up of components and sub-systems using simple blocks connected by lines representing their relationships [39,40]. The component and sub-system blocks each represent the component and sub-system symbols, as created using the AIAA symbolic representation, though their configuration is dictated in essentially two ways only: in series or in parallel.…”

Section: Block Modellingmentioning

confidence: 99%

Modelling Green VTOL Concept Designs for Reliability and Efficiency

Booker

Patel

Mellor

2021

Designs

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All-electric and hybrid-electric aircraft are a future transport goal and a possible ‘green’ solution to increasing climate-related pressures for aviation. Ensuring the safety of passengers is of high importance, informed through appropriate reliability predictions to satisfy emerging flight certification requirements. This paper introduces another important consideration related to redundancy offered by multiplex electric motors, a maturing technology which could help electric aircraft manufacturers meet the high reliability targets being set. A concept design methodology is overviewed involving a symbolic representation of aircraft and block modelling of two important figures of merit, reliability, and efficiency, supported by data. This leads to a comparative study of green aircraft configurations indicating which have the most potential now, and in the future. Two main case studies are then presented: an electric tail rotor retrofitted to an existing turbine powered helicopter (hybrid) and an eVTOL aircraft (all-electric), demonstrating the impact of multiplex level and number of propulsion channels on meeting target reliabilities. The paper closes with a summary of the important contribution to be made by multiplex electric machines, well as the advancements necessary for green VTOL aircraft sub-systems, e.g., power control unit and batteries, to improve reliability predictions and safety further.

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The Application of Reliability Methods for Aircraft Design Project Management

Cited by 12 publications

References 26 publications

Initial airworthiness requirements for aircraft electric propulsion

Initial airworthiness requirements for aircraft electric propulsion

An Overview to Unmanned Aerial Vehicles from Perspectives of Quality and Safety Management in Aviation

Modelling Green VTOL Concept Designs for Reliability and Efficiency

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