DYNAMIC RESPONSE ANALYSIS OF JET FIGHTER AIRCRAFT WING EXERTED BY AEROELASTIC CONDITION AND ARMAMENT RELEASE

• Main Author: Untarsa, Yohanes
• Format: Theses
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/75405
• Institution: Institut Teknologi Bandung

Fighter aircraft are designed to operate in extreme conditions, i.e. high speed regimes. Fighter aircraft are designed to do several types of missions, one of them is combat in which armaments are released. The armament configuration of a fighter aircraft is adjusted based on the type of mission of the fighter aircraft; hence, the aircraft is designed to operate with several armament configurations. The armament release during a mission can affect the dynamic response of the aircraft wing. In this thesis, a dynamic response analysis is conducted by evaluating the effect of armament release on the aircraft wing. The wing and the armament are modeled by means of finite element method (FEM). The unsteady aerodynamic loads are evaluated via Doublet Lattice Method (DLM) and Piston Theory for subsonic and supersonic regimes, respectively. The evaluation the aeroelastic instability of wing structure configurations with and without armament is conducted. The structural dynamic analysis shows that wing with armament has a lower natural frequency compared to the clean wing and the vibration modes of wing with armament differ with the clean wing. The aeroelastic analysis depicts that the aeroelastic instability, i.e., critical flutter speed, of the wing with armament happened at the supersonic regime and a higher speed compared to the clean wing. Thus, the dynamic response of the armament release, at the subsonic regime, generates a constant oscillation movement with a relatively small amplitude and does not create any instability.