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Problem "GTOC1" (MGA) This is a generic trajectory of the type Earth-Venus-Earth-Venus-Earth-Jupiter- Saturn-TW229 based on the objective function proposed in GTOC1. |
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Short description This 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. We transcribe this problem as a minimization problem by premultiplying the objective by -1. For the eight dimensional state vector we use the bounds given in the following table.
As constraints we limit the various fly-by pericenters to the values values: rp1 > 6351.8 km We also consider a launcher deltaV of 2.5 km/sec, a specific impulse of
Isp=2500s and a spacecraft initial mass of m0=1500 kg. |
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Solutions The first solution known to this problem (23 Jan, 2008), (credits: T., Vinko and D., Izzo using DiGMO): J(x) = - 1,580,599 kg km2/sec2, x=[6809.476683160, 169.598512787, 1079.375156244, 56.53776494142, 1044.014046276, 3824.160968179 1042.885114734 3393.057868710]. The best solution known this problem (date) (credits: M. Schlueter, M. Gerdts, University of Birmingham) found by MIDACO within the project "Non-linear mixed-integer-based Optimisation Technique for Space Applications" co-funded by ESA Networking Partnership Initiative, Astrium Limited (Stevenage, UK) and the School of Mathematics, University of Birmingham, UK. J(x) = - 1,581,950 kg km2/sec2, x=[6810.40521106, 168.37469758, 1079.47409963, 56.38731208, 1044.09288643, 3820.84181773, 1044.32726019, 3397.21349495]. Note that the arc joining Saturn with the asteroid is forced to be retrograde when solving the relative Lambert problem. | |
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