AIRBUS VIEW ON STRUCTURAL MODIFICATIONS TO COMPOSITE COMPONNENT

Transcription

1 AIRBUS Barry SCHROEDER AIRBUS VIEW ON STRUCTURAL MODIFICATIONS TO COMPOSITE COMPONNENT FAA Workshop Wichita Kansas JULY 19-20, 2016

2 Design Requirements (1/2) Pre-requisite for structural modification to composite components - Main requirements and performance objectives versus Type Certification Standards of the initial design have to be maintained - Check any potential influence of the proposed structural modification on the initial design (interfaces, maintenance, system integration), is needed Main requirements to be addressed in section 25 (FAR and EASA) A/ Loads cases: Dedicated loads levels have to be developed, pending of the item (antenna, cabin monument, nose radome,.. ) in superposition of overall initial loading conditions -Flight and ground loads cases (Ultimate and residual strength loads conditions) -Any specifics loads conditions : decompression loads (antenna), emergency landing conditions (cabin monuments), discrete source conditions (bird strike ).. -Maintenance program validation B/System integration - Any specific system requirements, mainly on nose radome, meteorological radar function

3 Design Requirements (2/2) Basics certification requirements: Main paragraphs to be addressed Section Vibration and Buffeting Section (b) - Flight Loads Validation Section Factor of safety Section , Section (e)(3) - Pressurized Compartment Loads Section Proof of structure Section (c) Emergency landing conditions, general Section Damage-Tolerance and Fatigue Evaluation of Structure Section (e)(1) (CS ) - Bird Strike Section Lightning Section General design and construction Section Materials Section Fabrication Methods Section Protection of Structure Section Material Strength Properties and Design Values Section Aeroelastic Stability Requirements (flutter, etc.) Section Cabin Pressurization Section (c) and (c) - Sustained Engine Imbalance (windmilling) Section Icing Section Instructions for continuous Airworthiness Any applicable Airworthiness directives

4 Interface Loads Evaluations Example on large antenna integration All Flight & Ground Load Cases are considered. Designing load case is a vertical gust GFEM: TC standard C76 Pr1 Shall strains distribution µm/m An optional live TV antenna has been considered on GFEM level for justification of Fuselage upper shell with a set of 2 additional antenna load cases in superposition with the envelope of all flight & ground load cases View on Upper Shell with TV antenna Additional unitary load case with antenna force in GFEM Pr1 C76 Additional strains due to antenna unitary load case compression about -20µm/m

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