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A GTO is an intermediary orbit used to make this process more efficient. Satellite operators often use a high-thrust, low-efficiency launch vehicle to put their satellite into GTO, and then, after detaching the launch vehicle, use low-thrust, high-efficiency thrusters onboard the satellite itself to circularize its orbit (to GEO) over a longer ...
The International Space Station (ISS) is a large space station that was assembled and is maintained in low Earth orbit by a collaboration of five space agencies and their contractors: NASA (United States), Roscosmos (Russia), ESA (Europe), JAXA (Japan), and CSA (Canada).
A space station (or orbital station) is a spacecraft which remains in orbit and hosts humans for extended periods of time. It therefore is an artificial satellite featuring habitation facilities . The purpose of maintaining a space station varies depending on the program.
While both would use a cryogenic main stage powered by a Vulcain 2 engine and two P145 solid boosters, Ariane 6.1 would feature a cryogenic upper stage powered by the Vinci engine and boost up to 8,500 kg (18,700 lb) to GTO, while Ariane 6.2 would use a lower-cost hypergolic upper stage powered by the Aestus engine.
Vulcan Centaur is a heavy-lift launch vehicle [a] developed and operated by United Launch Alliance (ULA). It is a two-stage-to-orbit launch vehicle consisting of the Vulcan first stage and the Centaur second stage.
The European Ariane 5 first flew in 1996 and launched many commercial payloads to GTO. It benefited in this role by launching from Guiana Space Center, a spaceport near the equator in French territory. Ariane 5 often carried multiple payloads per launch and set records for mass to GTO delivered for commercial payloads.
A large spacecraft such as the International Space Station can be constructed by assembling modules in orbit, or in-space propellant transfer conducted to greatly increase the delta-V capabilities of a cislunar or deep space vehicle. Distributed launch enables space missions that are not possible with single launch architectures. [13]
Due to the thrust required for injecting the satellite in a geostationary transfer orbit (GTO) the third stage was to be powered by a LOX/LH 2 Cryogenic engine which at that time India did not possess or have the technological expertise to build.