Keplerian Elements — The 6 Numbers That Describe an Orbit, short TUTORIAL скачать в хорошем качестве

Keplerian Elements — The 6 Numbers That Describe an Orbit, short TUTORIAL

In this video, we break down the six classical Keplerian elements that fully describe an orbit’s size, shape, orientation, and a satellite’s current position at a specific time (the epoch). You’ll learn what each element means, how it affects the orbit, and how “elements + epoch” define the full orbital state. What you’ll learn Semi-major axis (a): sets orbital size & energy Eccentricity (e): how stretched the ellipse is (e = 0 → circle) Inclination (i): tilt relative to Earth’s equator Argument of perigee (ω): orientation of the ellipse in its plane Right ascension of the ascending node (Ω): where the orbit crosses the equator heading north, measured from the vernal equinox Mean anomaly (M): where the satellite is along the orbit, increasing uniformly with time from perigee Epoch (time reference): needed because satellites move—elements are valid at a given time Chapters: 00:00 Intro 00:28 Why we need an epoch 01:15 Semi-major axis (a) 02:05 Eccentricity (e) 02:42 Inclination (i) 03:25 Argument of perigee (ω) 04:05 RAAN (Ω) 04:45 Mean anomaly (M) 05:25 Putting it all together: elements + epoch Resources & links Video on Two Line Element (TLE):    • Two Line Element Set, TLE, list of orbital...   Videos made in VTS and Scilab Simu-CIC, see tutorial:    • Satellite Mission Simulation Tutorial | SS...   If this helped, please like 👍 and subscribe for more space/astro tutorials. Drop your questions below—happy to help! #DiscoLapy; #VTS; #spaceengineering