PRELIMINARY DESIGN AND STATIC ANALYSIS OF PASSENGER DOOR SURROUND STRUCTURE FOR REGIONAL TURBOPROP AIRCRAFT WITH COMPOSITE FUSELAGE

• Main Author: Prakarsa Utomo (NIM : 13613068), Sigit
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/30949
• Institution: Institut Teknologi Bandung

The usage of composite material for designing main aircraft components such as fuselage is increasing to answer the challenge for lighter and safer aircraft. Aside of designing a lighter and safer fuselage structure, other challenge is to design the structure near door opening for passenger access. Openings in structure may reduce its stiffness and cause stress concentration problem which accelerates failure initiation. Because of that, door opening reinforcement is required to redistribute the load near fuselage opening and also to provide attachment for door hinge and door stopper. <br /> <br /> The objective of this final year thesis is to design safe and lightweight main fuselage structure component (skin panel, stringer, and frame) with composite material and passenger door reinforcement on I-52 Asha Patangga conceptual passenger aircraft. The designed fuselage structure must be able to withstand these 2 loading conditions: combination of limit pressurization load with 1g symmetric maneuver load and the combination of limit symmetric maneuver load with operating pressure difference load without experiencing static failure, buckling, and deformation above 3 mm on door reinforcement structure. The design is done by defining structural configuration and size in which the main fuselage structure with composite material will be designed first before designing the door reinforcement structure. Finite Element Analysis using ANSYS 17.1 is done to check the capability of the structure on withstanding the prescribed load. After one design iteration, the fuselage structure which is able to withstand the prescribed load is obtained with total weight 136.9 kg.