DOI: 10.5281/zenodo.7702919
title: Fokker F-28 Fellowship typical fuselage surface model for crashworthiness

description: 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 at https://www.airliners.net/photo/Piedmont-Airlines/Fokker-F-28-1000-Fellowship/0451713/L. <br> 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-<br> tical speed of 9.14 m s−1. 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. 1568–1573. 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<br> clips are represented using a combination of shell and beam elements. The skin stiffeners are also represented by beam elements.<br> The present data set includes CAD files (STP files) and Abaqus input files (INP) that were used to obtain validated acceleration measurements, when compared to NASA experiments. Description; INP file; STP file 4 frames F28 section, no friction, no damage; Abaqus_20220906_F28_4FR_JOB1; CAD_F28_4FR;<br> 5 frames F28 section, no friction, no damage; Abaqus_20220906_F28_5FR_JOB1; CAD_F28_5FR;<br> 6 frames F28 section, no friction, no damage; Abaqus_20220906_F28_6FR_JOB1; CAD_F28_6FR;<br> 4 frames F28 section, yes friction & damage; Abaqus_20221017_F28_4FR_JC_F; CAD_F28_4FR;<br> 5 frames F28 section, yes friction & damage; Abaqus_20221011_F28_JCD_Baseline; CAD_F28_5FR;<br> 5 frames F28 oval section, e = 0.20, yes friction and damage; Abaqus_20221018_F28_Oval_F_0.20; CAD_F28_5FR_e020;<br> 5 frames F28 oval section, e = 0.40, yes friction and damage; Abaqus_20221018_F28_Oval_F_0.40; CAD_F28_5FR_e040;<br> 5 frames F28 oval section, e = 0.60, yes friction and damage; Abaqus_20221018_F28_Oval_F_0.60; CAD_F28_5FR_e060;<br> 5 frames F28 oval section, e = 0.70, yes friction and damage; Abaqus_20221018_F28_Oval_F_0.70; CAD_F28_5FR_e070;<br> 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;<br> 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;<br> 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;<br> 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;