Tool Center

Hohmann Transfer

Inputs

Celestial Body

Celestial body the satellite is orbiting.

Celestial Body Mass

Mass of the celestial body the satellite is orbiting

Celestial Body Radius

Radius of the celestial body.

Initial Altitude

Distance from surface of the celestial body to the satellite.

Initial Inclination

deg

Initial orbit inclination.

Final Altitude

Distance from surface of the celestial body to the satellite.

Final Inclination

deg

Final orbit inclination.

Outputs

Delta V_{Burn 1}: 2454.63 m/s
Delta V_{Burn 2}: 1840.98 m/s
Delta V_Total: 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