design space pruning heuristics and global optimization method for ...
design space pruning heuristics and global optimization method for ...
design space pruning heuristics and global optimization method for ...
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Figure 18 Set of asteroids <strong>for</strong> sample problem.................................................................55<br />
Figure 19 Optimal solution <strong>for</strong> the small sample problem...............................................56<br />
Figure 20 Maximum final mass <strong>for</strong> each asteroid sequence as a function of inclination<br />
change. .............................................................................................................59<br />
Figure 21 Maximum final mass <strong>for</strong> each asteroid combination as a function of wedge<br />
angle, the angle between the two angular momentum vectors. .......................61<br />
Figure 23 Maximum final mass <strong>for</strong> each asteroid pair as a function of the minimum,<br />
phase-free, two-impulse ∆V. ...........................................................................62<br />
Figure 23 Comparison of two-impulse <strong>and</strong> low-thrust mass-optimal solutions <strong>for</strong> Earth –<br />
2006 QQ56 with a 600-day time of flight........................................................63<br />
Figure 24 Comparison of two-impulse <strong>and</strong> low-thrust mass-optimal solutions <strong>for</strong><br />
Chicago – Kostinsky with a 1200-day time of flight.......................................63<br />
Figure 25 Comparison of two-impulse <strong>and</strong> low-thrust mass-optimal solutions <strong>for</strong> Earth –<br />
Apophis with a time of flight up to 600 days...................................................64<br />
Figure 26 Final mass of all feasible trajectories as a function of arrival true anomaly at<br />
final asteroid.....................................................................................................65<br />
Figure 27 Maximum final mass <strong>for</strong> top twenty asteroid sequences as a function of arrival<br />
true anomaly at final asteroid...........................................................................66<br />
Figure 28 Final mass as a function of the summed <strong>pruning</strong> metric (Equation 17) <strong>for</strong> each<br />
asteroid sequence remaining in the small sample problem..............................67<br />
Figure 29 Final mass as a function of θwedge, summed over all legs <strong>for</strong> each asteroid<br />
sequence remaining in the small sample problem. ..........................................68<br />
Figure 30 Final mass as a function of optimal, phase-free, two-impulse ∆V summed over<br />
all legs <strong>for</strong> each asteroid sequence remaining in the small sample problem. ..69<br />
Figure 31 Comparison of mass-optimal low-thrust <strong>and</strong> two-impulse solutions <strong>for</strong> all<br />
Earth – Asteroid 1 sequences...........................................................................78<br />
Figure 32 Comparison of mass-optimal low-thrust <strong>and</strong> two impulse solutions <strong>for</strong> all<br />
Earth – Asteroid 1 – Asteroid 2 sequences. .....................................................78<br />
Figure 33 Comparison of mass-optimal low-thrust <strong>and</strong> two-impulse solutions <strong>for</strong> all<br />
Earth – Asteroid 1 – Asteroid 2 – Asteroid 3 sequences. ................................79<br />
Figure 34 Asteroid sequences identified by applying branch-<strong>and</strong>-bound algorithm to<br />
small sample problem. .....................................................................................82<br />
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