Unit 2.4 COE Flashcards

1
Q

๐‘Ž

A
Semi major axis
Describes - size of the orbit
Range - 0 to infinity
Measured from: Perigee
To: halfway to apogee
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2
Q

๐‘’

A
Eccentricity
Describes - Shape of the orbit
Range - 0 to infinity
๐‘’=0: Circular Orbit
01: Hyperbolic Orbit
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3
Q

๐‘–

A
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
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4
Q

ฮฉ

A
Right Ascension of the Ascending Node (RAAN)
Describes: Twist of the orbit
Range - 0 to 360
Measured from: Vernal Equinox
To: Ascending node
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5
Q

๐œ”

A
Argument of Perigee
Describes: orbit rotation
Range - 0 - 360
Measured from: Ascending Node
To: Perigee
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6
Q

๐œˆ

A
True Anomaly
Describes - satellite location
Range - 0 - 360
Measured from: Perigee
To: Satellite
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7
Q

When ๐‘’=0

A

There is no perigee, thus ๐œ” and ๐œˆ are undefined
Use argument of latitude, ๐‘ข, measured from ascending node to spacecraftโ€™s position vector, ๐‘Ÿโƒ—, in the direction of the spacecraftโ€™s motion

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8
Q

When ๐‘–=0

A

There is no ascending node, thus ฮฉ, and ๐œ” are undefined
Use Longitude of perigee, ฮ , measured from the principal direction, ๐ผฬ‚, to perigee, ๐‘’โƒ—, in the direction of the spacecraftโ€™s motion

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9
Q

When ๐‘’=0 and ๐‘–=0

A

There is no perigee or ascending node, thus ฮฉ, ๐œ”, and ๐œˆ are undefined
Use True longitude, ๐‘™, measured from the principal direction, ๐ผฬ‚, to the spacecraftโ€™s position vector, ๐‘Ÿโƒ—, in the direction of the spacecraftโ€™s motion

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10
Q

TLE

A

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

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11
Q

Orbital Propagation

A

Prediction of the orbital characteristics of a satellite at some future date given the current orbital characteristics

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