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Mars Reconnaissance Orbiter
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Launch Vehicle

Launch Vehicle

Launch Facts

Launch: August 12, 2005

Launch Location: Cape Canaveral Air Force Station, Florida

Arrival: March 10, 2006

Weight: 2,180 kilograms (4,806 pounds) at launch, including fuel

Electrical Power: Solar panels

Rocket: Atlas V

Mission Duration: 2006 - Ongoing

The launch vehicle supplied almost all of the energy that the spacecraft needed to get from Earth to Mars.

Read more about the launch vehicle here, or find out what happened during launch in the Mission Timeline.

Orbiter launched on an Atlas V-401

Mars Reconnaissance Orbiter used an Atlas V-401 launch vehicle, the smallest of the Atlas V family. It was 57 meters (188 feet) tall. This launch vehicle was selected because it provided the performance needed to fly a large spacecraft to Mars in the 2005 launch period.

Although the geometry of Earth and Mars permit missions to be launched every two years, the 2005 mission required more performance than was needed for the 2003 and 2007 launch dates, given the position of the planets in their orbits. In addition, this spacecraft was heavier than previous Mars missions.

Details about the Launch Vehicle

The Atlas V was developed by Lockheed Martin Commercial Launch Services as part of the U.S. Air Force Evolved Expendable Launch Vehicle (EELV) program. The term "expendable launch vehicle" means it was only used once.

The Mars Reconnaissance Orbiter version of the vehicle was a two-stage launch vehicle that did not use solid rocket boosters. The two-stage rocket was simpler than previous three-stage rockets and had better performance.

The total vehicle weight at liftoff was about 333,000 kilograms (733,000 pounds). Of that total, about 305,000 kg (672,000 pounds) was fuel for the launch vehicle; fuel for the orbiter weighed an additional 1,200 kilograms (about 2,600 pounds). To launch the orbiter and set it on its course to Mars, the Atlas V accelerated the spacecraft up to about 11,000 meters per second (25,000 miles per hour) at separation.

The main components of the launch vehicle were the:

drawing of Payload Adapter Payload Adapter: physical structure used to connect the orbiter to the launch vehicle.
drawing of Stage I Atlas Booster Stage I Atlas Booster: engine with propulsive energy for ascent.
Drawing of the payload fairing Payload Fairing: protective covering for the spacecraft during ascent (payload also shown).
drawing of the Stage II Centaur Upper Stage Booster Stage II Centaur Upper Stage Booster: engines used to augment Stage I thrust.