Atmospheric vehicle trajectory optimization with minimum dynamic pressure constraint

In this work, a trajectory optimization formulation for hypersonic boost–glide class vehicles to achieve maximum range under various in-flight and terminal constraints is proposed. While most of the published literature has considered maximum dynamic pressure as a constraint, the requirement of a certain minimum dynamic pressure has been addressed in this formulation to ensure aerodynamic controllability throughout the flight envelope for various ranges. The minimum dynamic pressure constraint is imposed as an in-flight inequality constraint and is achieved through a penalty function approach by casting it as a differential equation. Simulations are carried out, and the results are analyzed and presented to demonstrate the efficacy of the proposed formulation.