| Variable | Starship Min | Slider | Slider Value | Starship Max |
| ISP (s) | 350 | 380 | ||
| Fuel (mT) | 35 (header) | 1300 | ||
| Dry Mass (mT) | 100 | 150 | ||
| Mission DV (m/s) | 1 | 10000 |
-------------> Max Payload (mT) =
Cargo Starships to fill 1,200 MT LEO Orbital Fuel Depot = (assumes a DV of 6000 m/s)
Cost to fill 1,200 MT LEO Orbital Fuel Depot = (assumes a Starship upper stage DV of 6000 m/s)
| Mission | DV needed (m/s) |
| Starship Upper Stage -> LEO | 6000 |
| LEO -> Lunar Orbit | 4800 |
| LEO -> Lunar Surface | 6000 |
| Lunar Orbit -> Lunar Surface -> Lunar Orbit (HLS) | 3200 |
| LEO -> Lunar Orbit -> Earth Surface | 6400 |
| LEO -> Lunar Surface -> Earth Surface | 7800 |
| LEO -> Mars Surface (min fuel, 7 months, every 2 year window) | 4100 |
| LEO -> Mars Surface(fast 4 month, every 2 year window) | 5600 |
| LEO -> Low Mars Orbit (min fuel, 7 months) | 6100 |
| Mars Surface -> Earth Surface (min fuel, 7 months) | 6400 |
| Earth Orbit Inclination Change | Calc Below |
DV needed for an inclination change:
| Min | Slider | Slider Value | Max | |
| Inclination Change (deg) | 0 | 90 | ||
| Altitude (km) | 0 | 5000 |
Inclination Change DV (m/s) =
Total Mission Total Cost ($M) =
| Variable | Min | Slider | Value | Max |
| Starship Shell Cost ($M) | 40 | 150 | ||
| Starship Number Uses | 1 | 1000 | ||
| Cost of Starship Use ($M) | 1 | 50 | ||
| Super Heavy Cost ($M) | 100 | 500 | ||
| Super Heavy Uses | 1 | 100 | ||
| Super Heavy Use Cost ($M) | 1 | 100 | ||
| Number Launches | 1 | 100 |
Power
Major
advances in solar array performance are envisioned: a) near-term: 150–200 W/kg, b) mid- to farterm: 200–250 W/kg. A summary of the status of development of these advanced solar arrays is
given below.
Flexible Roll-out Arrays: Roll-out solar arrays (ROSA) have been recently unfurled and
successfully tested at the International Space Station (ISS). Mega-ROSA is a flexible roll-out solar
array under development at Deployable Space Systems, Inc. (DSS). It represents an extension of the
ROSA to higher power. The Mega-ROSA comprises a set of multiple ROSAs deployed from a
central structural spine. The Mega-ROSA is intended to reach power capability exceeding 100 kW
at 1 AU, BOL.
In Earth Orbit:
if .300KW/SQm
-> 10 m**2 -> 3 KW, 100 m**2 -> 30 KW, 300 m**2 -> 300 KW, 3000 m**2 -> 3000 KW
and if 150 KW/MT (low estimate)
-> 300 m**2 = 300 KW = 2 MT
-> 3000 m**2 (30 x 100) = 3,000 KW = 4 MT