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| === Well Known Earth Orbits === | === Earth Orbit Parameterms === |
Earth Orbits
Orbits are complicated, because they involve both position and velocity in three spatial dimensions and time. Simple two-body "Kepler" orbits relate the position and velocity at one time to the position and velocity at other times. In reality, orbits are also complicated by drag, light pressure, and gravitational perturbations by other bodies, and in the extreme by relativistic effects. For this discussion, we will not consider the complications, so that we get closed-form algebraic solutions. Of course, in real life, we will need to include all the complications in our calculations of orbital properties. Server-sats are deployed in closely packed orbital families. One central orbit, perfectly circular and in the orbital plane, with a sidereal period of 14393 seconds and a radius of 12789 kilometers, surrounded by slightly inclined and slightly elliptical orbits that fill a toroidal region around that central orbit. By carefully assigning orbital parameters, this region can be filled with densely packed orbits and objects in them.
Describing Earth Orbits
Orbits are ellipses in a plane which also contains the center of the mass that defines the orbit.
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Earth Orbit Parameterms
system |
status |
number |
planes |
#/plane |
perigee |
apogee |
inclination |
period |
uplink GHz |
downlink GHz |
Space Station |
in use |
1 |
1 |
1 |
6727 |
6736 |
51.6 |
5480 |
x |
x |
Iridium |
in use |
66 |
6 |
11 |
7158 |
7158 |
86.4 |
6027 |
Ka band |
Ka band |
Teledesic |
bankrupt |
288 |
12 |
24 |
7778 |
7778 |
98.2 |
6827 |
28.6-29.2 |
18.9-19.3 |
Globalstar |
in use |
48 |
x |
x |
7792 |
7792 |
52 |
6845 |
x |
x |
m288 core |
empty |
0 |
1 |
0 |
12789 |
12789 |
0 |
14393 |
x |
x |
m288 outer |
empty |
0 |
many |
0 |
12739 |
12839 |
2.24 |
14393 |
x |
x |
Molniya |
in use |
3? |
3? |
1 |
7885 |
45683 |
63.4 |
43082 |
x |
x |
GPS |
in use |
31 |
6? |
- |
26600 |
26600 |
55 |
43082 |
x |
x |
GEO |
in use |
361 |
1 |
- |
42164 |
42164 |
0 to 14.3 |
86164 |
- |
- |
Moon |
natural |
1 |
1 |
1 |
364397 |
406731 |
5.14 |
2360592 |
x |
x |
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Volunteer Opportunity: Space Debris Orbits The Norad Two Line Elements (TLEs) for all tracked satellites and space debris are available for individuals signing up at www.space-track.org (see references). It would be very useful to build a program that can go through all the two line elements, and look for orbits that cross the equatorial plane in the vicinity of m288 . How many are there?
References
Wikipedia : Two Line element description (with SGP4 fortran)
SaVi satellite constellation visualization
Description of NORAD 2 line elements
NORAD Space Tracking Information requires account.
NASA 3D Realtime Satellite Tracker (Java)
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