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| Original file line number | Diff line number | Diff line change |
|---|---|---|
| @@ -1,55 +1,35 @@ | ||
| """ | ||
| script to generate the values in the SP Aircraft different objective table | ||
| """ | ||
| from gpkit import units | ||
| from aircraft import Mission | ||
| from SPaircraft import optimize_aircraft | ||
| from subs.optimalD8 import get_optimalD8_subs | ||
|
|
||
| from SPaircraft import run_optimal_737 | ||
|
|
||
| #solve all the cases | ||
| base_sol = run_optimal_737('W_{f_{total}}', False, True, True) | ||
| emptyW_sol = run_optimal_737('W_{dry}', False, True, True) | ||
| span_sol = run_optimal_737('b', False, True, True) | ||
| AR_sol = run_optimal_737('AR', False, True, True) | ||
| engineW_sol = run_optimal_737('W_{engine}', False, True, True) | ||
| time_sol = run_optimal_737('Total_Time', False, True, True) | ||
| LD_sol = run_optimal_737('L/D', False, True, True) | ||
| LGw_sol = run_optimal_737('W_{lg}', False, True, True) | ||
|
|
||
| #compute times | ||
| base_time = sum(base_sol('thr')['thr_Mission/ClimbSegment/ClimbP/AircraftP'])+sum(base_sol('thr')['thr_Mission/CruiseSegment/CruiseP/AircraftP.1']) | ||
| emptyW_time = sum(emptyW_sol('thr')['thr_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2'])+sum(emptyW_sol('thr')['thr_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3']) | ||
| span_time = sum(span_sol('thr')['thr_Mission.2/ClimbSegment.2/ClimbP.2/AircraftP.4'])+sum(span_sol('thr')['thr_Mission.2/CruiseSegment.2/CruiseP.2/AircraftP.5']) | ||
| AR_time = sum(AR_sol('thr')['thr_Mission.3/ClimbSegment.3/ClimbP.3/AircraftP.6'])+sum(AR_sol('thr')['thr_Mission.3/CruiseSegment.3/CruiseP.3/AircraftP.7']) | ||
| engineW_time = sum(engineW_sol('thr')['thr_Mission.4/ClimbSegment.4/ClimbP.4/AircraftP.8'])+sum(engineW_sol('thr')['thr_Mission.4/CruiseSegment.4/CruiseP.4/AircraftP.9']) | ||
| LD_time = sum(LD_sol('thr')['thr_Mission.6/ClimbSegment.6/ClimbP.6/AircraftP.12'])+sum(LD_sol('thr')['thr_Mission.6/CruiseSegment.6/CruiseP.6/AircraftP.13']) | ||
| LGw_time = sum(LGw_sol('thr')['thr_Mission.7/ClimbSegment.7/ClimbP.7/AircraftP.14'])+sum(LGw_sol('thr')['thr_Mission.7/CruiseSegment.7/CruiseP.7/AircraftP.15']) | ||
|
|
||
| #output the columns of the table | ||
| print "column 2" | ||
| print "\n" | ||
| print [emptyW_sol('W_{f_{total}}')/base_sol('W_{f_{total}}'), emptyW_sol('W_{dry}')/base_sol('W_{dry}'), emptyW_sol('b')/base_sol('b'), emptyW_sol('AR')/base_sol('AR'), emptyW_sol('W_{engine}')/base_sol('W_{engine}'), emptyW_time/base_time, emptyW_sol('L/D')['L/D_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3'][0]/base_sol('L/D')['L/D_Mission/CruiseSegment/CruiseP/AircraftP.1'][0], emptyW_sol('W_{lg}')/base_sol('W_{lg}')] | ||
| print "\n" | ||
| print "\n" | ||
| print "column 3" | ||
| print "\n" | ||
| print [span_sol('W_{f_{total}}')/base_sol('W_{f_{total}}'), span_sol('W_{dry}')/base_sol('W_{dry}'), span_sol('b')/base_sol('b'), span_sol('AR')/base_sol('AR'), span_sol('W_{engine}')/base_sol('W_{engine}'), span_time/base_time, span_sol('L/D')['L/D_Mission.2/CruiseSegment.2/CruiseP.2/AircraftP.5'][0]/base_sol('L/D')['L/D_Mission/CruiseSegment/CruiseP/AircraftP.1'][0], span_sol('W_{lg}')/base_sol('W_{lg}')] | ||
| print "\n" | ||
| print "\n" | ||
| print "column 4" | ||
| print [AR_sol('W_{f_{total}}')/base_sol('W_{f_{total}}'), AR_sol('W_{dry}')/base_sol('W_{dry}'), AR_sol('b')/base_sol('b'), AR_sol('AR')/base_sol('AR'), AR_sol('W_{engine}')/base_sol('W_{engine}'), AR_time/base_time, AR_sol('L/D')['L/D_Mission.3/CruiseSegment.3/CruiseP.3/AircraftP.7'][0]/base_sol('L/D')['L/D_Mission/CruiseSegment/CruiseP/AircraftP.1'][0], AR_sol('W_{lg}')/base_sol('W_{lg}')] | ||
| print "\n" | ||
| print "\n" | ||
| print "column 5" | ||
| print [engineW_sol('W_{f_{total}}')/base_sol('W_{f_{total}}'), engineW_sol('W_{dry}')/base_sol('W_{dry}'), engineW_sol('b')/base_sol('b'), engineW_sol('AR')/base_sol('AR'), engineW_sol('W_{engine}')/base_sol('W_{engine}'), engineW_time/base_time, engineW_sol('L/D')['L/D_Mission.4/CruiseSegment.4/CruiseP.4/AircraftP.9'][0]/base_sol('L/D')['L/D_Mission/CruiseSegment/CruiseP/AircraftP.1'][0], engineW_sol('W_{lg}')/base_sol('W_{lg}')] | ||
| print "\n" | ||
| print "\n" | ||
| print "column 6" | ||
| print [time_sol('W_{f_{total}}')/base_sol('W_{f_{total}}'), time_sol('W_{dry}')/base_sol('W_{dry}'), time_sol('b')/base_sol('b'), time_sol('AR')/base_sol('AR'), time_sol('W_{engine}')/base_sol('W_{engine}'), time_sol('TotalTime')/base_time, time_sol('L/D')['L/D_Mission.5/CruiseSegment.5/CruiseP.5/AircraftP.11'][0]/base_sol('L/D')['L/D_Mission/CruiseSegment/CruiseP/AircraftP.1'][0], time_sol('W_{lg}')/base_sol('W_{lg}')] | ||
| print "\n" | ||
| print "\n" | ||
| print "column 7" | ||
| print [LD_sol('W_{f_{total}}')/base_sol('W_{f_{total}}'), LD_sol('W_{dry}')/base_sol('W_{dry}'), LD_sol('b')/base_sol('b'), LD_sol('AR')/base_sol('AR'), LD_sol('W_{engine}')/base_sol('W_{engine}'), LD_time/base_time, LD_sol('L/D')['L/D_Mission.6/CruiseSegment.6/CruiseP.6/AircraftP.13'][0]/base_sol('L/D')['L/D_Mission/CruiseSegment/CruiseP/AircraftP.1'][0], LD_sol('W_{lg}')/base_sol('W_{lg}')] | ||
| print "\n" | ||
| print "\n" | ||
| print "column 8" | ||
| print [LGw_sol('W_{f_{total}}')/base_sol('W_{f_{total}}'), LGw_sol('W_{dry}')/base_sol('W_{dry}'), LGw_sol('b')/base_sol('b'), LGw_sol('AR')/base_sol('AR'), LGw_sol('W_{engine}')/base_sol('W_{engine}'), LGw_time/base_time, LGw_sol('L/D')['L/D_Mission.7/CruiseSegment.7/CruiseP.7/AircraftP.15'][0]/base_sol('L/D')['L/D_Mission/CruiseSegment/CruiseP/AircraftP.1'][0], LGw_sol('W_{lg}')/base_sol('W_{lg}')] | ||
| # solve all the cases | ||
| Nclimb = 3 # number of climb segments | ||
| Ncruise = 2 # number of cruise segments | ||
| Nmission = 1 # number of missions | ||
| config = 'optimalD8' # String describing configuration: | ||
| m = Mission(Nclimb, Ncruise, config, Nmission) | ||
| substitutions = get_optimalD8_subs() | ||
| substitutions.update({'R_{req}': 3000.*units('nmi'), | ||
| 'n_{pass}': 180.}) | ||
| # Additional options | ||
| fixedBPR = False | ||
| pRatOpt = True | ||
| mutategparg = True | ||
| sol = {} | ||
| objectives = [m['W_{f_{total}}'],m['W_{dry}'],m['b'],m['AR'],m['W_{engine}'],m['TotalTime'],m['L/D'][Nclimb],m['W_{lg}']] | ||
| for i in range(0,8): | ||
| m.cost = objectives[i].sum() | ||
| sol[i] = optimize_aircraft(m, substitutions, fixedBPR, pRatOpt, mutategparg) | ||
| basesol = sol[0] | ||
|
|
||
| # output the columns of the table | ||
| for i in range(0,8): | ||
| print ("column %s" % i) | ||
| print "\n" | ||
| print [sol[i](objectives[j])/basesol(objectives[j]) for j in range(0,8)] | ||
| print "\n" | ||
| print "\n" |