Abstract
SARISTU morphing wing is mainly based on three devices: enhanced adaptive droop nose (EADN), adaptive trailing edge device (ATED) and winglet active trailing edge (WATE). All these devices are used together to improve the overall wing efficiency and to reduce the aerodynamic noise. The safety activities described in this paper were performed to verify whether this concept can comply with the standard civil flight safety regulations and airworthiness requirements. The safety analysis was performed in two steps: a functional hazard assessment (FHA) and a system safety assessment (SSA). Both analyses were performed at wing integration level (IS12) and at single morphing wing devices level. A complete mapping between these two levels of analysis was structured from the beginning of the process, starting from the aircraft functional definition, to integrate and harmonize both FHA and fault trees results. FHA was used to assess the severity of the identified Failure Conditions and then allocate safety requirements. Fault tree modelling technique was used to verify the compliance of the system architectures to the quantitative safety requirements resulting from the FHAs. The paper sets out the hypotheses and common data used by the fault trees. A complete but simple example illustrates the safety approach all through the different steps of the safety methodology. Other safety activities commonly performed in the aeronautical field such as the particular risk analysis (PRA), common mode analysis (CMA) and zonal safety analysis (ZSA) were identified in the frame of SARISTU project. This paper concludes with a summary highlighting the main results of these safety activities with some lessons learned from the safety approach adapted to SARISTU context.
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Notes
- 1.
Conditional event is a wording used with fault tree + tool.
Abbreviations
- A/C:
-
Aircraft
- AOA:
-
Angle of attack
- ATE(D):
-
Adaptive trailing edge (device)
- AS0x:
-
Application Scenario x
- CAT:
-
CATASTROPHIC
- CCA:
-
Common cause analyses
- CMA:
-
Common mode analyses
- DAL:
-
Design assurance level
- EADN:
-
Enhanced adaptive droop nose
- EASA:
-
European aviation safety agency
- EMC:
-
Electro magnetic compatibility
- EMI:
-
Electro magnetic interference
- FC:
-
Failure Condition
- FCS:
-
Flight control system
- FDAL:
-
Functional development assurance level
- FH:
-
Flight hour(s)
- FHA:
-
Functional hazard analysis/assessment
- FOD:
-
Foreign object damage
- FT:
-
Fault tree
- FTA:
-
Fault tree analysis
- HAZ:
-
HAZARDOUS
- HIRF:
-
High-intensity radiated fields
- HW:
-
Hardware
- IS12:
-
Integration Scenario 12
- LND:
-
Landing
- MAJ:
-
MAJOR
- MCS:
-
Minimal cut set
- MIN:
-
MINOR
- MoC:
-
Means of compliance
- MT:
-
Maintenance time
- NSE:
-
No safety effects
- PFHA:
-
Preliminary FHA
- PRA:
-
Particular risk analysis
- PSSA:
-
Preliminary system safety assessment
- REQ:
-
Requirement
- SSA:
-
System safety assessment
- SW:
-
Software
- T/O:
-
Take-off
- WATE:
-
Winglet active trailing edge
- ZSA:
-
Zonal safety analysis
References
Standard regulations and practices
EASA CS-25 (2014) Book 1, European Aviation Safety Agency—Certification specifications for large aeroplanes CS-25 amendment 15, 21 July 2014
EASA CS-25 (2014) Book 2, European Aviation Safety Agency—Acceptable means of compliance for large aeroplanes CS-25 amendment 15, 21 July 2014
SAE ARP 4754a (2010) US SAE international, guidelines for development of civil aircraft and systems, Revised Dec 2010
SAE ARP 4761 (1996) US SAE international, guidelines and methods for conducting the safety assessment process on civil airborne systems and equipment, Dec 1996
RTCA DO-160, Environmental conditions and test procedures for airborne electronic/electrical equipment and instruments from EUROCAE
SARISTU project documents
Baldassin E, Di Gifico M, Gemma R, Carossa GM, Russo S, Ricci S, De Gaspari A, Peter F. Deliverable A_DEU_121_1_R2, Reference baseline wing and morphing wing aeromechanical requirements
Wildschek A, Storm S. SARISTU AS03 Final Paper, Design, manufacturing, and testing of the wingtip active trailing edge
Apicella A, Russo S, Ricciardelli C. Deliverable A_DEU_ D123_1_R1, Wing demonstrator design principles
Other documents/papers
Working group document, Framework for the application of system engineering in the commercial aircraft domain
Acknowledgments
The research leading to these results has received funding from the European Union’s Seventh Framework Programme for research, technological development and demonstration under Grant Agreement No 284562.
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© 2016 Springer International Publishing Switzerland
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Verrastro, M., Metge, S. (2016). Morphing Wing Integrated Safety Approach and Results. In: Wölcken, P., Papadopoulos, M. (eds) Smart Intelligent Aircraft Structures (SARISTU). Springer, Cham. https://doi.org/10.1007/978-3-319-22413-8_2
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DOI: https://doi.org/10.1007/978-3-319-22413-8_2
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