Rapid Indirect Trajectory Optimization for Conceptual Design of Hypersonic Missions

摘要

During conceptual design, trajectory optimization is often performed using direct methods. This investigation illustrates that trajectory optimization and vehicle performance characterization can be rapidly performed by coupling indirect optimization, continuation, and symbolic manipulation. Examples illustrate that the historical challenges associated with indirect optimization methods can be overcome, enabling the rapid construction of high-quality solutions. In this design methodology, highly constrained optimal trajectories are rapidly constructed by traversing optimal manifolds of varying design problems throughout the continuation process.