Apogee in the context of "Epoch (astronomy)"

A low Earth orbit (LEO) is an orbit around Earth with a period of 128 minutes or less (making at least 11.25 orbits per day) and an eccentricity less than 0.25. Most of the artificial objects in outer space are in LEO, peaking in number at an altitude around 800 km (500 mi), while the farthest in LEO, before medium Earth orbit (MEO), have an altitude of 2,000 kilometers, about one-third of the radius of Earth and near the beginning of the inner Van Allen radiation belt.

The term LEO region is used for the area of space below an altitude of 2,000 km (1,200 mi) (about one-third of Earth's radius). Objects in orbits that pass through this zone, even if they have an apogee further out or are sub-orbital, are carefully tracked since they present a collision risk to the many LEO satellites.

The Safir (Persian: سفیر, meaning "ambassador") was the first Iranian expendable launch vehicle able to place a satellite in orbit. The first successful orbital launch using the Safir launch system took place on 2 February 2009 when a Safir carrier rocket placed the Omid satellite into an orbit with a 245.2 km (152.4 mi) apogee. This made Iran the ninth nation capable of producing and launching a satellite.

The Simorgh is a larger orbital launcher based on Safir technology which has since replaced the Safir, and is sometimes called the Safir-2.

MW 18014 was a German A-4 test rocket launched on 20 June 1944, at the Peenemünde Army Research Center in Peenemünde. It was the first man-made object to reach outer space, attaining an apogee of 176 kilometres (109 mi), well above the Kármán line that was established later as the lowest altitude of space. It was a vertical test launch, and was not intended to reach orbital velocity, so it returned and impacted Earth, making it the first sub-orbital spaceflight.

A sounding rocket or rocketsonde, sometimes called a research rocket or a suborbital rocket, is an instrument-carrying rocket designed to take measurements and perform scientific experiments during its sub-orbital flight. The rockets are often used to launch instruments from 50 to 150 km (30 to 90 mi) above the surface of the Earth, the altitude generally between weather balloons and satellites; the maximum altitude for balloons is about 40 km (25 mi), and the minimum for satellites is approximately 120 km (75 mi).

Due to their suborbital flight profile, sounding rockets are often much simpler than their counterparts built for orbital flight. Certain sounding rockets have an apogee between 1,000 and 1,500 km (600 and 900 mi), such as the Black Brant X and XII. Sounding rockets may be flown to altitudes as high as 3,000 km (2,000 mi) to allow observing times of around 40 minutes to provide geophysical observations of the magnetosphere, ionosphere, thermosphere, and mesosphere.

In space mission design, a geostationary transfer orbit (GTO) or geosynchronous transfer orbit is a highly elliptical type of geocentric orbit, usually with a perigee as low as low Earth orbit (LEO) and an apogee as high as geostationary orbit (GEO). Satellites that are destined for geosynchronous orbit (GSO) or GEO are often put into a GTO as an intermediate step for reaching their final orbit. Manufacturers of launch vehicles often advertise the amount of payload the vehicle can put into GTO.