Multi-Objective Optimization of Reentry Vehicle Design: Aerodynamics, Heat Transfer, and Structural Durability
Abstract
Re-entry vehicles are humanity's gateway to safe space exploration; without them, manned space flights would be obsolete. Re-entry vehicles face extreme aerothermal and structural forces and loads in such critical environments while ensuring the safety of the astronauts within the capsule. Since the Cold War, Russian-made Soyuz spacecraft were the first and proven choice for all manned space missions, but their design and features were primitively outdated as they were operated entirely manually and the systems were crammed in such a small space. Until recently, SpaceX introduced Dragon, which proved to be a more viable option as it offered more space for a larger crew and all systems were controlled automatically or from the ground control station, offering better landing accuracy and control. With its reusability, it has turned the spacecraft market upside down and has become a new favourite choice for countries with manned space programs, amidst sanctions against Russia; all arrows seem to point to SpaceX's Dragon as the new spacecraft champion. This study aims to establish a balance between aerothermodynamics and structural integrity, aerodynamic shape optimization, thermal protection system improvement, flight path optimization, and modular spacecraft interior design for manned missions, cargo missions, and luxury commercial flights. This is to be achieved computationally using CAD modelling, CFD, FEA simulations