Path: Interplanetary/Insertion
% Simulate an optimal approach and orbit insertion at Mercury (fmincon)
Treat the problem as planar. Models a fixed mass. fmincon is used to find the
optimal trajectory. This optimization is on the slow side and may take several
hundred iterations.
Parameter space:
1. how long a time is allocated for the insertion burn (fTime)
2. the number of points along the trajectory
3. number of optimization iterations, or tolerances
Example solutions:
3500 kg / 40 or 20 N / fTime = 3 - coast time in trajectory
3000 kg / 15 N / 3
Note: lower thrust may require less mass, more points
The cost, f(x), is the total acceleration required for the maneuver. The
constraints, or Feasibility, are that the acceleration magnitude is less than
the maximum and that the final state is achieved at the endpoint.
Example output:
First-order Norm of
Iter F-count f(x) Feasibility optimality step
271 56026 8.140240e+01 5.301e-12 8.410e-01 3.252e-03
See also ApproachCost2DMag, ApproachConst2DIneq, Simulate2DApproach
%
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