コロキウム

We consider a problem to design optimally controlled transfers of spacecrafts with low energy from the Earth to the Moon. The planar circular restricted three-body problem is adopted as a mathematical model for the motion of the spacecraft. The cost functional of the optimal control includes the integral of the magnitude of the control inputs. The Pontryagin's minimal principle of optimal control theory is applied to reduce our problem to a nonlinear boundary value problem for a Hamiltonian system. In this talk I explain these materials and state my plan for the future work.