This instance of a Multiple Gravity Assist problem draws inspiration from the first edition of the Global Trajectory Optimisation Competition (GTOC1). It is an MGA problem with a rather long fly-by sequence including mainly Earth and Venus. The final target is the asteroid TW229. The objective of the mission is to maximise the change in sami-major axis of the asteroid orbit following an anaelastic impact of the spacecraft with the asteroid J(x) = m_f U v.
- MATLAB: use the function gtoc1.m and pass to it the MGAproblem variable contained in gtoc1.mat
- C++: call the function “double gtoc1(const std::vector & x, std::vector& rp)” provided in the GTOPtoolbox.
- C++ (PaGMO): use the class pagmo::problem::gtoc_1
- Python 2.7 (PyGMO): use PyGMO.problem.gtoc_1().obj_fun(x)
The box bounds on each of the decision vector variable are given below.
Constraints on the various fly-by pericenters are also considered to the values:
- rp1 > 6351.8 km
- rp2 > 6778.1 km
- rp3 > 6351.8 km
- rp4 > 6778.1 km
- rp5 > 600000 km
- rp6 > 70000 km
Solutions are rounded to the fourth digit and only improvements on that level is considered. No constraint violation is allowed.
The record holders of this problem are listed below in chronological order: