Difference between revisions of "KEO"
m (*first link to this wiki and see also to Wikipedia;) |
m (added orbital period) |
||
| Line 3: | Line 3: | ||
The [[semi-major axis]] is {{OrbitAltitude|b=Kerbin|3=0}}. | The [[semi-major axis]] is {{OrbitAltitude|b=Kerbin|3=0}}. | ||
| − | The orbital altitude is {{OrbitAltitude|b=Kerbin}} at an orbital speed of {{OrbitVelocity|b=Kerbin}}, which is equivalent to a surface speed of zero (may read as 2.4 m/s). | + | The orbital altitude is {{OrbitAltitude|b=Kerbin}} at an orbital speed of {{OrbitVelocity|b=Kerbin}}, which is equivalent to a surface speed of zero (may read as 2.4 m/s) and an orbital period of 6h 0m 0s. |
== Maneuver Planning == | == Maneuver Planning == | ||
Revision as of 00:32, 4 November 2014
Kerbisynchronous Equatorial Orbit (or KEO for short) is the stationary orbit of the planet Kerbin, a very useful orbit for satellites. A spacecraft on this orbit will appear stationary when viewed from the surface. This can be useful when establishing a wireless connection between the craft and a structure on the surface, but it also makes obesrvation of a certain spot on the surface easy.
The semi-major axis is 3 463 334.06 m.
The orbital altitude is 2 863 334.06 m at an orbital speed of 1 009.81 m/s, which is equivalent to a surface speed of zero (may read as 2.4 m/s) and an orbital period of 6h 0m 0s.
Maneuver Planning
The basic maneuver plan for reaching this orbit is to first achieve a low energy orbit (LEO) and then perform two maneuvers to execute a Hohmann transfer. The first one called the periapsis maneuver is raising the apoapsis to the required altitude for a synchronous orbit. This places the spacecraft on a kerbisynchronous transfer orbit (KTO). The second one is at the apoapsis.
Depending on the required orbit the second burn also includes nearly all of the plane change to reduce the equatorial inclination to zero. For stationary orbits the periapsis maneuver should be executed when crossing the equatorial plane. Since the Kerbal Space Center is on the equator, the timing and trigonometry may be skipped.
The following are instantaneous impulse calculations for equatorial low energy orbits, and therefore the real maneuvers will always be somewhat more than these values.
| LKO Altitude | Periapsis | Apoapsis | Total |
|---|---|---|---|
| 70 km | 676.6 m/s | 434.9 m/s | 1111.5 m/s |
| 90 km | 659.6 m/s | 427.8 m/s | 1087.4 m/s |
| 100 km | 651.5 m/s | 424.3 m/s | 1075.8 m/s |
| 120 km | 635.5 m/s | 417.4 m/s | 1052.9 m/s |
| 150 km | 612.7 m/s | 407.3 m/s | 1020.0 m/s |
| 200 km | 577.4 m/s | 391.3 m/s | 968.7 m/s |
| 300 km | 515.3 m/s | 361.3 m/s | 876.6 m/s |
For direct launches, transfers from the lowest orbits will be more efficient because they require less delta-v to reach from the surface of Kerbin. Higher LEOs may be preferable if the spacecraft is visiting a tug or space station and requires altitude above the atmosphere to execute a rendezvous. These maneuver plans may also be useful for one who wishes to boost a large space station assembled to LKO to KEO (Keep in mind that you may not have the thrust to make burns very efficient).
Other celestial bodies
In theory those orbits also exists for other celestial bodies, but may be outside the sphere of influence.
See also
- Geostationary orbit on Wikipedia
- Geosynchronous orbit on Wikipedia
- Stationary orbit on Wikipedia
- Synchronous orbit on Wikipedia
