DEVELOPMENT OF AIRCRAFT AILERON SYSTEM BASED ON ELECTROMECHANICS

• Main Author: Tri Susilo, Bangkit
• Format: Theses
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/79468
• Institution: Institut Teknologi Bandung

The development of the primary aircraft control design has significantly evolved over time. In recent periods, innovation has been focused on transitioning from full mechanical control systems in passenger aircraft towards full electrical control systems. Currently, aircraft using fully electrical systems are seen in Unmanned Aerial Vehicles (UAVs). Subsequently, the concept of More Electric Aircraft (MEA) emerged, adopting hybrid controls. The future aim is to develop Zero Emission Aircraft (ZEA). Up until now, neither MEA nor ZEA has obtained the type certification from airworthiness regulators. Considering this circumstance, research pertaining to the development of electromechanical-based aileron control is conducted due to its relevance and promising potential within the Indonesian aviation industry. The research process commences with the selection of aircraft complying with CASR 23 regulations. The existing aircraft's aileron control system architecture is then replaced with a new electromechanical-based control system. This process involves system failure analysis using Fault Tree Analysis (FTA) and dynamic system analysis through numerical simulations, followed by calculating the power requirements and system weight. The system failure analysis results indicate that the proposed architecture exhibits a failure rate of approximately 10 under loss of aileron control conditions and 10 under aileron hard over conditions, meeting regulatory requirements. Power analysis reveals a demand of only 1667.8 Watts, which aligns with the available power on the aircraft. However, weight analysis demonstrates that the new electromechanical system is approximately 35.7% heavier than the previously used full mechanical system.