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GTO is a highly elliptical Earth orbit with an apogee (the point in the orbit of the moon or a satellite at which it is furthest from the earth) of 42,164 km (26,199 mi), [3] or a height of 35,786 km (22,236 mi) above sea level, which corresponds to the geostationary altitude.
A geostationary orbit, also referred to as a geosynchronous equatorial orbit [a] (GEO), is a circular geosynchronous orbit 35,786 km (22,236 mi) in altitude above Earth's equator, 42,164 km (26,199 mi) in radius from Earth's center, and following the direction of Earth's rotation.
For example, although more fuel is needed to transfer a heavier communication satellite from low Earth orbit to geosynchronous orbit than for a lighter one, the delta-v required is the same. Delta- v is also additive, as contrasted to rocket burn time, the latter having greater effect later in the mission when more fuel has been used up.
Geostationary or geosynchronous transfer orbit (GTO): An elliptic orbit where the perigee is at the altitude of a low Earth orbit (LEO) and the apogee at the altitude of a geostationary orbit. Hohmann transfer orbit: An orbital maneuver that moves a spacecraft from one circular orbit to another using two engine impulses.
Delta-v (also known as "change in velocity"), symbolized as and pronounced /dɛltə viː/, as used in spacecraft flight dynamics, is a measure of the impulse per unit of spacecraft mass that is needed to perform a maneuver such as launching from or landing on a planet or moon, or an in-space orbital maneuver.
This variant uses an Indian cryogenic engine, the CE-7.5, and is capable of launching 2500 kg into geostationary transfer orbit. Previous GSLV vehicles (GSLV Mark I) have used Russian cryogenic engines. [30] For launches from 2018, a 6% increased thrust version of the Vikas engine was developed.
The launch was successful, placing the WGS-9 into a geostationary transfer orbit (GTO), from which the spacecraft raised itself into geostationary orbit using its onboard propulsion system. The satellite was designated USA-275 under the U.S. military's designation system , and received the International Designator 2017-016A and Satellite ...
Function: Expendable launch system: Country of origin: United States: Size; Height: 35 m (114 ft) Diameter: 2.44 m (8 ft) Mass: 130,392 kg (287,465 lb) Payload to GTO (Geostationary transfer orbit)