Dataset: Fokker F-28 Fellowship typical fuselage surface model for crashworthiness

DOI10.5281/zenodo.7724227Zenodo7724227MaRDI QIDQ6726017

Dataset published at Zenodo repository.

Author name not available (Why is that?)

Publication date: 6 March 2023

Copyright license: No records found.

The Fokker F-28 Fellowship aircraft is a twin-engined jetliner developed by the Dutch aircraft manufacturer Fokker in the 1960s, and introduced in 1969. It has a wingspan ranging between 23.6 m and 25.1 m, and a MTOW between 29 480 kg and 33 110 kg, depending on the variant. The fuselage outer diameter is about 3.3 m, with passengers sitting in a 2-3, single aisle configuration. A picture of the F-28 can be found athttps://www.airliners.net/photo/Piedmont-Airlines/Fokker-F-28-1000-Fellowship/0451713/L. In the late 1990s, NASA purchased a complete, retired F-28 aircraft, plus three additional fuselage sections; to test them as part of the Systems Approach for Crashworthiness program: K. E. Jackson et al. Finite Element Simulations of Two Vertical Drop Tests of F-28 Fuselage Sections. Tech. rep. Hampton, Virginia, USA: NASA Langley Research Center, Feb. 2018. URL: http://www.sti.nasa.gov. Subsequently, in 2001, a vertical drop test of one of the three sections, the typical section, was performed. The drop test that took place at the NASA LandIR research facility was carried out in a clean configuration, meaning that no luggage was present in the test section, but only 20x34 kg (75 lb) dummy masses representing the passengers. The section impacted the ground, a concrete surface, at a ver- tical speed of 9.14 m s1. The physical drop test was compared to an MSC.Dytran simulation that has been simultaneously developed, for validation purposes. The finite element model was developed by modifying an existing one of a similar aircraft, the Fokker 70: K. H. Lyle et al. Application of Probability Methods to Assess Airframe Crash Modeling Uncertainty. In: Journal of Aircraft 44.5 (Sept. 2007), pp. 15681573. ISSN: 15333868. DOI: 10.2514/1.27722. URL: https://arc.aiaa.org/doi/10.2514/1.27722. The model includes a four-frames section of the fuselage portion forward of the wings. Structural features, such as frames and shear clips are represented using a combination of shell and beam elements. The skin stiffeners are also represented by beam elements. The present data set includes CAD files (STP files) and Abaqus input files (INP) that were used to obtain validated acceleration measurements, whencompared to NASA experiments. Description; INP file; STP file 4 frames F28 section, no friction, no damage; Abaqus_20220906_F28_4FR_JOB1; CAD_F28_4FR; 5 frames F28 section, no friction, no damage; Abaqus_20220906_F28_5FR_JOB1; CAD_F28_5FR; 6 frames F28 section, no friction, no damage; Abaqus_20220906_F28_6FR_JOB1; CAD_F28_6FR; 4 frames F28 section, yes friction damage; Abaqus_20221017_F28_4FR_JC_F; CAD_F28_4FR; 5 frames F28 section, yes friction damage; Abaqus_20221011_F28_JCD_Baseline; CAD_F28_5FR; 5 frames F28 oval section, e = 0.20, yes friction and damage; Abaqus_20221018_F28_Oval_F_0.20; CAD_F28_5FR_e020; 5 frames F28 oval section, e = 0.40, yes friction and damage; Abaqus_20221018_F28_Oval_F_0.40; CAD_F28_5FR_e040; 5 frames F28 oval section, e = 0.60, yes friction and damage; Abaqus_20221018_F28_Oval_F_0.60; CAD_F28_5FR_e060; 5 frames F28 oval section, e = 0.70, yes friction and damage; Abaqus_20221018_F28_Oval_F_0.70; CAD_F28_5FR_e070; 5 frames F28 oval section, e = 0.75, yes friction and damage, baseline floor beam height (500mm from keel); Abaqus_20221018_F28_Oval_F_0.75; CAD_F28_5FR_e075_FBh500; 5 frames F28 oval section, e = 0.75, yes friction and damage, FB height = 550mm; Abaqus_20221025_F28_Floor_550; CAD_F28_5FR_e075_FBh550; 5 frames F28 oval section, e = 0.75, yes friction and damage, FB height = 600mm; Abaqus_20221025_F28_Floor_600; CAD_F28_5FR_e075_FBh600; 5 frames F28 oval section, e = 0.75, yes friction and damage, FB height = 650mm; Abaqus_20221025_F28_Floor_650; CAD_F28_5FR_e075_FBh650;

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