If the orbit is a parabola, or close to a parabola (the eccentricity is 1.0 or nearly 1.0), then the algorithms for elliptical orbits will break down. This is called the low Earth orbit (LEO). Geocentric orbits ranging in altitude from 160 kilometers (100 statute miles) to 2,000 kilometres (1,200 mi) above mean sea level. Highly elliptical orbit (HEO) - Geocentric orbit with apogee above 35,786 km and low perigee (about 1,000 km) that result in long dwell times near apogee. Find (a) the eccentricity, (b) the altitude of perigee, (c) the semimajor axis, and (d) the period. A few large space stations have been launched in parts and assembled in orbit. Medium Earth orbit (MEO) A high Earth orbit is a geocentric orbit with an altitude entirely above that of a geosynchronous orbit (35,786 kilometres (22,236 mi)).

Geosynchronous orbit (GEO) - Geocentric circular orbit with an altitude of 35,786 kilometres (22,236 mi). Geosynchronous orbit (GEO) - Geocentric circular orbit with an altitude of 35,786 kilometres (22,236 mi). The orbital periods of such orbits are greater than 24 hours, therefore satellites in such orbits have an apparent retrograde motion – that is, even if they are in Approximately 63% of operational satellites are in low Earth orbit, 6% are in medium-Earth orbit (at 20,000 km), 29% are in geostationary orbit (at 36,000 km) and the remaining 2% are in elliptic orbit. For the Terra satellite for example, it’s always about 10:30 in the morning when the satellite crosses the equator in Brazil. A high Earth orbit is a geocentric orbit with an altitude entirely above that of a geosynchronous orbit (35,786 kilometres (22,236 mi)). The period of the orbit equals one sidereal day, coinciding with the rotation period of the Earth. The speed is approximately 3,000 metres per second (9,800 ft/s).

Geosynchronous transfer orbit - A geocentric-elliptic orbit where the perigee is at the altitude of a Low Earth Orbit (LEO) and the apogee at the altitude of a geosynchronous orbit. The most commonly used classification for geocentric orbits is the one based on altitude, which is the height of an object above the Earth's surface. The lowest altitude where a stable orbit can be created is 100 miles. The altitude of a satellite is the distance between the Earth's surface and the satellite, but the Earth itself is not spherical. At 160 km, one revolution takes approximately 90 minutes, and the circular orbital speed is 8,000 metres per second (26,000 ft/s). Synchronous orbit Semi-synchronous orbit Tidally locked Altitude Semi-major axis Altitude Semi-major axis Kerbol: 1 508 045.29 km 1 769 645.29 km 853 206.67 km 1 114 806.67 km – Moho: 18 173.17 km † 18 423.17 km † 11 355.87 km † 11 605.87 km † No Eve: … The speed is approximately 3,000 metres per second (9,800 ft/s). 3. So how is the altitude of a satellite actually defined? If the orbit is elliptical, compute the Mean Anomaly, M. Then compute r, the heliocentric distance, and v, the true anomaly. Geosynchronous orbit (GEO) - Geocentric circular orbit with an altitude of 35,786 kilometres ( Template:Convert/round mi). Low Earth Orbit (LEO) - Geocentric orbits ranging in altitude from 160 kilometeres (100 statue miles) to 2,000 kilometres (1,200 mi) above mean sea level.At 160 km, one revolution takes approximately 90 minutes, and the circular orbital speed is 8,000 metres per second (26,000 ft/s). The highest point of LEO is approximately 1,200 miles. This orbit is a Sun-synchronous orbit, which means that whenever and wherever the satellite crosses the equator, the local solar time on the ground is always the same.

At the equator the Earth's radius is 21 km more than at the poles, and in fact the shape of the Earth is not even a perfect oblate spheroid.. The speed is approximately 3,000 metres per second ( Template:Convert/round ft/s). The period of the orbit equals one sidereal day, coinciding with the rotation period of the Earth. At two points on a geocentric orbit, the altitude and true anomaly are z 1 = 1545 km, θ 1 = 126° and z 2 = 852 km, θ 2 = 58°, respectively. The period of the orbit equals one sidereal day, coinciding with the rotation period of the Earth. Solution

Low Earth Orbit (LEO) - Geocentric orbits ranging in altitude from 160 kilometeres (100 statue miles) to 2,000 kilometres (1,200 mi) above mean sea level. 4.