Difference between revisions of "Atlas V"
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[[Image:MRO_Liftoff.jpg|thumb|200px|right|The '''Atlas V''' Rocket launches the [[Mars Reconnaissance Orbiter]] into space.]] | [[Image:MRO_Liftoff.jpg|thumb|200px|right|The '''Atlas V''' Rocket launches the [[Mars Reconnaissance Orbiter]] into space.]] | ||
| − | The '''Atlas V''' rocket is an expendable launch vehicle | + | The '''Atlas V''' rocket is an expendable launch vehicle built by the [[Lockheed Martin]]-[[Boeing]] joint venture [[United Launch Alliance]]. The rocket consists of a first stage powered by kerosene and liquid oxygen, which uses a Russian made RD-180 engine, and a liquid hydrogen–liquid oxygen powered [[Centaur]] upper stage crafted by the American rocket manufacturer [[w:Aerojet_Rocketdyne|Aerojet Rocketdyne]]. |
| − | The Atlas V rocket was used to launch the [[Mars Reconnaissance Orbiter]] on August 12, 2005. | + | The Atlas V rocket was used to launch the [[Mars Reconnaissance Orbiter]] on August 12, 2005, as well as the Mars Science Laboratory, the MAVEN Mars Orbiter, the InSight Mars and the Mars 2020-Perseverance mission. |
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| + | Atlas V has a capacity to LEO of 8000 to 18500 kg. | ||
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| + | Launch systems list. | ||
| − | [[category: | + | {{stub}} |
| + | [[category:Exploration Transport Systems]] | ||
| + | [[category:Astronautics]] | ||
Latest revision as of 05:16, 6 October 2021
The Atlas V Rocket launches the Mars Reconnaissance Orbiter into space.
The Atlas V rocket is an expendable launch vehicle built by the Lockheed Martin-Boeing joint venture United Launch Alliance. The rocket consists of a first stage powered by kerosene and liquid oxygen, which uses a Russian made RD-180 engine, and a liquid hydrogen–liquid oxygen powered Centaur upper stage crafted by the American rocket manufacturer Aerojet Rocketdyne.
The Atlas V rocket was used to launch the Mars Reconnaissance Orbiter on August 12, 2005, as well as the Mars Science Laboratory, the MAVEN Mars Orbiter, the InSight Mars and the Mars 2020-Perseverance mission.
Atlas V has a capacity to LEO of 8000 to 18500 kg.
Launch systems list.
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