This study was initiated in response to an incident that occurred at Muan Airport, with the goal of finding a more effective and faster method for aircraft deceleration in emergency situations. While conventional spoilers are primarily designed to assist deceleration during landing, their simple structure limits the amount of drag they can generate in unexpected situations. To address this limitation, we designed a curved, deployable spoiler system that can normally adjust drag but additionally deploy in four extra stages during emergencies to significantly increase aerodynamic resistance. The curved geometry was modeled using CATIA and converted into an STL file for 3D printing to create a prototype. The initial mechanical reliability of the actuating components was verified through physical testing. The curved structure is advantageous for generating high drag coefficients by intentionally disturbing airflow, causing flow separation and increasing resistance. Future work includes wind tunnel testing and CFD analysis to quantitatively evaluate the increase in drag coefficient and determine how effectively the aircraft can be decelerated and stabilized across different speeds and flight attitudes. If successfully implemented, this system could contribute significantly to enhancing flight safety by ensuring rapid deceleration and attitude stability during emergency landings or other critical scenarios.
목차
Abstract 1. 서론 2. 항목기재 2.1 CATIA를 이용한 curved spoiler 설계 2.2 3D 프린팅을 이용한 curved spoiler 제작 후기 References