ECEF X ECEF Y ECEF Z ECEF Az ECEF El
Nodal Vector Sat Distance `epsilon` [a] `epsilon` [V,r] Semi-Major [`mu`,`epsilon`] Semi-Major [`r_a`,`r_p`] Eccentricty [`r_a`,a] Eccentricty [`r_p`,a] `vece` Eccentricty `||vece||` Eccentricty [E,L,m,`alpha`] Inclination, `i` Arg Perigee, `omega` RAAN, `Omega` `r_"perigee"` `r_"apogee"` Period [a, `R_E`] True Anomaly, `nu`[E] Period [a, `mu`] Period [a]
Force and Energy Characteristics
Force of Gravity Maintenance `Delta` V Specific Mech Energy (1) Specific Mech Energy (2)
Viewing Angles and Coverage
`V_"esc"` using `mu` `V_"sat"` using `mu` `V_"esc"` using `R_E` `V_"sat"` using `R_E` `V_"esc"` using r only `V_"sat"` using r only Orbit Period
Earth - mean spherical radius (km) Earth - mean spherical radius (NM) Earth - mean spherical radius (Miles) WGS-84| r - Earth equator (m) WGS-84| r - Earth polar WGS-84 Earth flattening Mass of Earth (units: kg)
Gravity / Energy Contants
G ( `m^3`/`kg * s^2`) `mu` ( `m^3`/`sec^2`) g (US) g (SI)
Tags
UUID
717ac38f-e309-11e3-b7aa-bc764e2038f2
This calculator contains equations for computing various constants and characteristics of a satellite's orbit. Most of these formula are based on a standard Keplarian elliptical orbit.
This calculator, Orbitology Calculator, references 47 pages Show
This calculator, Orbitology Calculator, is used in 1 page Show