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A Titan IIIE-Centaur rocket (Centaur D-1T stage) launches Voyager 2. The Centaur D-1T (powered by RL10A-3-3 engines) was an improved version for use on the far more powerful Titan III booster in the 1970s, [47] with the first launch of the resulting Titan IIIE in 1974. The Titan IIIE more than tripled the payload capacity of Atlas-Centaur, and ...
The rocket's second stage, the Centaur V, is an upgraded version of the Centaur III used on the Atlas V offering enhanced performance. It is powered by two RL10 engines from Aerojet Rocketdyne , fueled by liquid hydrogen.
Centaure was a two-stage French sounding rocket consisting of a Venus first stage and a Belier second stage. [3] [4] [5] It belongs to a family of solid-propellant rockets consisting of the Belier, Centaure, Dragon, Dauphin, and Eridan. [4] [5] Sud-Aviation Belier rockets evolution. It was operated by Sud-Aviation between 1961 and 1986.
The Titan IIIE or Titan 3E, also known as the Titan III-Centaur, was an American expendable launch system. Launched seven times between 1974 and 1977, [ 4 ] it enabled several high-profile NASA missions, including the Voyager and Viking planetary probes and the joint West Germany-U.S. Helios spacecraft .
The facility was built in 1968 as part of the Centaur development. These upper-stage rockets (launched on Atlas V first stages) needed to be capable of firing at high altitude to launch their payloads out of Earth orbit. More than ten tests of Centaur rockets here enabled the later successful launches in the Pioneer, Voyager, and Viking programs.
The theme music from Star Wars was played, a crowd of 300, mostly General Dynamics employees, was in attendance, as were astronauts Fabian, Walker and Hauck, and speeches were given by dignitaries. [81] [82] [83] Centaur G-Prime arrives at the Shuttle Payload Integration Facility at the Kennedy Space Center
The RL10 is a liquid-fuel cryogenic rocket engine built in the United States by Aerojet Rocketdyne that burns cryogenic liquid hydrogen and liquid oxygen propellants. Modern versions produce up to 110 kN (24,729 lb f) of thrust per engine in vacuum.
A Centaur stage during assembly at General Dynamics in 1962 Diagram of a Centaur stage. Centaur was the first rocket stage to utilize liquid hydrogen (LH2) and liquid oxygen (LOX) as propellants. Despite boasting high performance, LH2 had to be chilled to extremely low temperatures (lower than LOX) and its low density meant that large fuel ...