# Tool Center

## Inputs

Celestial body the satellite is orbiting.

kg

Mass of the celestial body the satellite is orbiting

km

Radius of the celestial body.

km

Distance from surface of the celestial body to the satellite.

deg

Initial orbit inclination.

km

Distance from surface of the celestial body to the satellite.

deg

Final orbit inclination.

Delta VBurn 1
2454.63 m/s
Delta VBurn 2
1840.98 m/s
Delta VTotal
4295.61 m/s
Time of Flight
315.53 min

## Calculation Log

``` satcatalog: python hohmann_transfer.py radius_initial = 6378.1366 km + 200.0 km velocity_initial = sqrt(398613.89 / 6578.1366) radius_final = 6378.14 km + 35786.0 km velocity_final = sqrt(398613.89 / 42164.1366) semi_major_axis_transfer = (6578.1366 km + 42164.1366 km) / 2 semi_major_axis_transfer = 24371.14 km velocity_perigee_transfer = sqrt((2 x 398613.89 / 6578.1366) - (398613.89 / 24371.1366)) velocity_perigee_transfer = 10.24 km/s tof = 3.1416 x sqrt((24371.1366^3) / 398613.89) tof = 18931.60 sec delta_v_1 = 10.24 km/s - 7.78 km/s delta_v_2 = sqrt((1.60 x sin(0.50 rad))^2 + (3.0747 - 1.5974 x cos(0.50 rad))^2) delta_v_total = 2.45 km/s + 1.84 km/s delta_v_total = 4.30 km/s delta_v_total = 4295.61 m/s ```