Akademik Veri Yönetim Sistemi
8th INTERNATIONAL CONFERENCE ON HEALTH, ENGINEERING AND APPLIED SCIENCES, Sarajevo, Bosna-Hersek, 24 - 26 Ekim 2025, ss.127-142, (Tam Metin Bildiri)
This paper addresses a 1:1-scale dummy approach that preserves the geometry and interface of the flight hardware to reduce risks in dynamic verification, using a finite-element and random-vibration–based workflow. The dummy was iteratively optimized to match the real equipment’s mass properties with deviations of 0.2% in mass; 0.2% in center of gravity (X/Y) and 0.1% in Z; and 4.3% in Ixx, 1.8% in Iyy, and 0.8% in Izz. The numerical model employed a TET10 (quadratic tetrahedral) solid mesh for the body, an RBE2 (Rigid Body Element, form 2) interface representation, a CBUSH (connection bushing) flexible-joint idealization, and an assumed damping ratio of ζ ≈ 2.5%. Modal solutions were obtained and the first natural frequency was identified. On the PSD (Power Spectral Density) side, FRF- (Frequency Response Function) based analysis was performed using input spectra defined by breakpoints for horizontal (X/Y) and vertical (Z) axes. Band contributions were decomposed from RMS (Root Mean Square) acceleration distributions and cumulative RMS–frequency curves. The verification strategy is to conduct a resonance survey, followed by a random vibration test, and then a post-test resonance survey to enable test–analysis correlation. Correlation metrics will include frequency deviation, mode-shape similarity, and response PSD overlap. The results indicate that the numerical model built with a dummy matching the interface and mass properties provides a traceable and repeatable basis for subsequent experimental validation.