Mission Description

• Launch from Earth on Julian date 2452751.5 (April 22, 2003) -- fixed
• Arrive at Mars on Julian date 2453151.5 (May 26, 2004) -- fixed
• Initial mass:  610.0 kg (fixed)
• Launch V∞ magnitude:  1.00 km/s (fixed)
• Launch V∞ direction is free
• Propulsion Model:  Electric Engine G (1 Engine)
• Power Model: apsa1 solar array, P0 = 7.0 kW, Psc = 0
• Objective function:  final mass
• Originally modeled using SEPTOP

Additional Mission Options

A. Same as Reference Case 2 except now the launch date is free. (Allow transfer duration to vary so that arrival date remains fixed).
B. Same as Reference Case 2 except now the flight time is free (optimize the arrival date with a fixed departure date, and therefore, a variable flight time).  This case does not converge in SEPTOP, but the output and input files are included for reference.
C. Same as Reference Case 2 except now the launch V¥ magnitude is free.  Launch vehicle:  Delta 7326-9.5.
D. Same as Reference Case 2 except now the reference power P0 = 4.0 kW.
E. Same as Reference Case 2 except now the launch date, arrival date, and launch V¥ magnitude are all free.  Launch vehicle:  Delta 7326-9.5.
F. Solar Sail Propulsion

• 100x100 m**2 solar sail with a mass of 260.75 kg.
• minimizing flight time
• launch date is free but around 200

Input/Output files

CHEBYTOPv6.zip (download)

Copernicus20060310.zip (download)

MALTO4_2_5.zip (download)

Mystic9_0_0.zip (download)

SAILv10_131.zip (download)

SEPTOP11_136.zip (download)

All Reference Case 2: Earth - Mars Rendezvous Input/Output Files (download zip)