What is trajectories ?
Trajectories refer to the paths followed by objects as they move through space or other mediums. In physics and engineering, trajectories are often studied to understand and predict the motion of objects, such as projectiles, celestial bodies, spacecraft, particles, and more.
How to Calculate Mean Anomaly in Parabolic Orbit given Time since Periapsis?
Mean Anomaly in Parabolic Orbit given Time since Periapsis calculator uses Mean Anomaly in Parabolic Orbit = ([GM.Earth]^2*Time since Periapsis in Parabolic Orbit)/Angular Momentum of Parabolic Orbit^3 to calculate the Mean Anomaly in Parabolic Orbit, The Mean Anomaly in Parabolic Orbit given Time Since Periapsis formula is a parameter used to describe the position of an object in its orbit relative to a reference point. It's similar to the mean anomaly in elliptical orbits, but adapted for parabolic trajectories, given the time since periapsis , the mean anomaly in a parabolic orbit can be calculated using equations specific to parabolic orbits. Mean Anomaly in Parabolic Orbit is denoted by M_{p} symbol.
How to calculate Mean Anomaly in Parabolic Orbit given Time since Periapsis using this online calculator? To use this online calculator for Mean Anomaly in Parabolic Orbit given Time since Periapsis, enter Time since Periapsis in Parabolic Orbit (t_{p}) & Angular Momentum of Parabolic Orbit (h_{p}) and hit the calculate button. Here is how the Mean Anomaly in Parabolic Orbit given Time since Periapsis calculation can be explained with given input values -> 6568.417 = ([GM.Earth]^2*3578)/73508000000^3.