A hypersonic vehicle is an aircraft with a flight speed exceeding 5 times the speed of sound, combining the characteristics of both spacecraft and aircraft, with significant military and economic potential. The thesis focuses on a re-entry hypersonic vehicle, which is a spacecraft that travels through space and re-enters the atmosphere of a planet (e.g., Earth). When landing, a safe re-entry is needed. The entry guidance system is crucial for ensuring a successful atmospheric re-entry, particularly for these class of vehicles which face multiple constraints during this critical flight phase. Traditional entry guidance approaches, such as reference trajectory-based guidance (RTG) and numerical predictor–corrector guidance (NPCG), have been widely employed in past missions.