It looks like you're using an Ad Blocker.
Please white-list or disable AboveTopSecret.com in your ad-blocking tool.
Thank you.
Some features of ATS will be disabled while you continue to use an ad-blocker.
originally posted by: InfiniteTrinity
a reply to: oldcarpy
I already answered that question.
Can you now answer this one?
Can you explain why it has to move around Earth then?
Can you explain why it has to move around Earth then?
It has been explained to you many times over but as you appear unable to comprehend very basic physics
And it does move around the circumference of the earth.
originally posted by: InfiniteTrinity
a reply to: captainpudding
I will also say yes a satellite in earth orbit, orbits the earth.
Now say something relevant. The topic was geostationary satellites. Not satellites in general.
And once more, from NASA
An orbit is a regular, repeating path that one object in space takes around another one.
Now does a geostationary sat move around the object Earth? No it doesnt. Its geo stationary.
Rofl.
originally posted by: InfiniteTrinity
a reply to: oldcarpy
Again, give me a simple yes or a no answer to my question and i will answer yours.
Lol, Carpy the moment has passed already you did a very good job. Sheesh.
originally posted by: neutronflux
a reply to: InfiniteTrinity
Did you ever stop to think
originally posted by: InfiniteTrinity
a reply to: neutronflux
And it does move around the circumference of the earth.
Give it up man. Just admit that it doesnt orbit around the Earth then. If it would orbit around the Earth you would just say "Earth".
Btw your peer thinks that you explained to me that it has to move around the Earth. Doesnt that annoy you?
A geostationary satellite clearly orbits the space around earth
originally posted by: InfiniteTrinity
a reply to: neutronflux
A geostationary satellite clearly orbits the space around earth
Come on now sport, this is getting very childish.
So again you admit that it does not move around the Earth.
Now man up and tell your friends they are wrong.
Orbital elements
en.m.wikipedia.org...
Orbital elements are the parameters required to uniquely identify a specific orbit. In celestial mechanics these elements are generally considered in classical two-body systems, where a Kepler orbit is used. There are many different ways to mathematically describe the same orbit, but certain schemes, each consisting of a set of six parameters, are commonly used in astronomy and orbital mechanics.
A real orbit (and its elements) changes over time due to gravitational perturbations by other objects and the effects of relativity. A Keplerian orbit is merely an idealized, mathematical approximation at a particular time.
The traditional orbital elements are the six Keplerian elements, after Johannes Kepler and his laws of planetary motion.
When viewed from an inertial frame, two orbiting bodies trace out distinct trajectories. Each of these trajectories has its focus at the common center of mass. When viewed from a non-inertial frame centred on one of the bodies, only the trajectory of the opposite body is apparent; Keplerian elements describe these non-inertial trajectories. An orbit has two sets of Keplerian elements depending on which body is used as the point of reference. The reference body is called the primary, the other body is called the secondary. The primary does not necessarily possess more mass than the secondary, and even when the bodies are of equal mass, the orbital elements depend on the choice of the primary.
Two elements define the shape and size of the ellipse:
Eccentricity (e)—shape of the ellipse, describing how much it is elongated compared to a circle (not marked in diagram).
Semimajor axis (a)—the sum of the periapsis and apoapsis distances divided by two. For circular orbits, the semimajor axis is the distance between the centers of the bodies, not the distance of the bodies from the center of mass.
Two elements define the orientation of the orbital plane in which the ellipse is embedded:
Inclination (i)—vertical tilt of the ellipse with respect to the reference plane, measured at the ascending node (where the orbit passes upward through the reference plane, the green angle i in the diagram). Tilt angle is measured perpendicular to line of intersection between orbital plane and reference plane. Any three points on an ellipse will define the ellipse orbital plane. The plane and the ellipse are both two-dimensional objects defined in three-dimensional space.
Longitude of the ascending node (Ω)—horizontally orients the ascending node of the ellipse (where the orbit passes upward through the reference plane, symbolized by ☊) with respect to the reference frame's vernal point (symbolized by ♈︎). This is measured in the reference plane, and is shown as the green angle Ω in the diagram.
The remaining two elements are as follows:
Argument of periapsis (ω) defines the orientation of the ellipse in the orbital plane, as an angle measured from the ascending node to the periapsis (the closest point the satellite object comes to the primary object around which it orbits, the blue angle ω in the diagram).
True anomaly (ν, θ, or f) at epoch (M0) defines the position of the orbiting body along the ellipse at a specific time (the "epoch").
The mean anomaly is a mathematically convenient "angle" which varies linearly with time, but which does not correspond to a real geometric angle. It can be converted into the true anomaly ν, which does represent the real geometric angle in the plane of the ellipse, between periapsis (closest approach to the central body) and the position of the orbiting object at any given time. Thus, the true anomaly is shown as the red angle ν in the diagram, and the mean anomaly is not shown.
The angles of inclination, longitude of the ascending node, and argument of periapsis can also be described as the Euler angles defining the orientation of the orbit relative to the reference coordinate system.
Note that non-elliptic trajectories also exist, but are not closed, and are thus not orbits. If the eccentricity is greater than one, the trajectory is a hyperbola. If the eccentricity is equal to one and the angular momentum is zero, the trajectory is radial. If the eccentricity is one and there is angular momentum, the trajectory is a parabola.