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