Unit 2.4 COE Flashcards
๐
Semi major axis Describes - size of the orbit Range - 0 to infinity Measured from: Perigee To: halfway to apogee
๐
Eccentricity Describes - Shape of the orbit Range - 0 to infinity ๐=0: Circular Orbit 01: Hyperbolic Orbit
๐
Inclination Describes - tilt of the orbit Range - 0 to 180 Measured from: K vector/equatorial plane To: H vector/orbital plane Equatorial: 0, 180 Polar Orbit: 90 Prograde Orbit: 0 - 90 Retrograde Orbit:90 - 180
ฮฉ
Right Ascension of the Ascending Node (RAAN) Describes: Twist of the orbit Range - 0 to 360 Measured from: Vernal Equinox To: Ascending node
๐
Argument of Perigee Describes: orbit rotation Range - 0 - 360 Measured from: Ascending Node To: Perigee
๐
True Anomaly Describes - satellite location Range - 0 - 360 Measured from: Perigee To: Satellite
When ๐=0
There is no perigee, thus ๐ and ๐ are undefined
Use argument of latitude, ๐ข, measured from ascending node to spacecraftโs position vector, ๐โ, in the direction of the spacecraftโs motion
When ๐=0
There is no ascending node, thus ฮฉ, and ๐ are undefined
Use Longitude of perigee, ฮ , measured from the principal direction, ๐ผฬ, to perigee, ๐โ, in the direction of the spacecraftโs motion
When ๐=0 and ๐=0
There is no perigee or ascending node, thus ฮฉ, ๐, and ๐ are undefined
Use True longitude, ๐, measured from the principal direction, ๐ผฬ, to the spacecraftโs position vector, ๐โ, in the direction of the spacecraftโs motion
TLE
Two-Line Element. Used to quantify satellite position, velocity, orbital perturbations showing all 6 orbital elements (mean anomaly instead of true anomaly) and values quantifying expected drag of a satellite
Orbital Propagation
Prediction of the orbital characteristics of a satellite at some future date given the current orbital characteristics