We describe, in the framework of global optimisation, four trajectory optimisation problems, representative of three different important typologies often encountered in space mission design. After giving a brief description of the astrodynamical details necessary to implement the problems we solve them by applying Differential Evolution and Multiple Particle Swarm Optimisation keeping the number of objective function evaluations to a minimal amount to ensure low computational times. We show how these techniques may be usefully exploited to perform fast optimisations getting first estimates of relevant mission design parameters thus helping to take early decisions on the overall spacecraft design.
展开▼
