Space and astronautical engineering

The course consists of four parts. Part one: Study the architecture of a software program for trajectory optimization for an interplanetary mission. Space flight mechanics, optimization techniques (direct and indirect), and nonlinear programming will be applied to the development of a software program for trajectory optimization for an interplanetary mission. This part also includes the study of solar sails and their thrust models. Part two: Given the circular three-body problem, we will study periodic and quasi-periodic trajectories around Lagrangian points: Lyapunov, Lissajous, and Halo orbits. Computational codes will be developed to obtain Lyapunov orbits around the Lagrangian points of the Earth-Moon system. Subsequently, we will find the ballistic trajectories that connect the Lyapunov orbits using stable and unstable manifolds and Poincaré maps. Part Three: This section explores the characteristics of the orbit around the target planet. The ground track, periodicity, illumination, and frozen orbits are studied to best meet mission requirements. Part Four: Four-body transfers are introduced. In particular, minimum-energy Earth-Moon transfers (Belbruno transfers) will be studied.

Knowledge of space flight mechanics, optimal control problems solved with direct and indirect techniques, and nonlinear programming. Programming experience (e.g., in Matlab) is required.

lecture notes and copies of book chapters

classroom lessons

evaluation of the numerical exercises proposed during the course and oral questions on the program

Oral exam in presence