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SLS Initial Lift Capability  
Initial Operational Capability (IOC): 2018
Maiden Flight: 2017
Total Production: ?
Origin: United States of America
Corporations: Boeing
Parent System: Space Launch System
Initial Operational Capability (IOC): 2018
Maiden Flight: 2017
Total Production: ?
Family Members: SLS Evolved Lift Capability
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Description: The NASA's Space Launch System (SLS) is a deep space exploration initiative aimed at developing a family of modular heavy-lift launch vehicles to transport spaceships and equipment. The SLS program has been designed to replace the failed Ares I and Ares V space rockets while delivering a more affordable and sustainable launch vehicles. The SLS rocket will incorporate technological investments from the Space Shuttle Program and the Constellation Program in order to take advantage of proven hardware and cutting-edge tooling and manufacturing technology that will significantly reduce development and operations costs. The core stage utilizes three to five RS-25D/E rocket engines that burns a mixture of liquid hydrogen and liquid oxygen. The J-2X rocket engine using liquid hydrogen and liquid oxygen has been selected for the upper stage. Besides, SLS will also use solid rocket boosters and follow-on boosters based on performance requirements.

The first development flight is targeted for the end of 2017. The new exploration-class vehicle since the Saturn V that took the United States of America to the Moon should be operational by 2018. SLS should expand NASA's reach in the solar system and allow to explore the space around the Moon, near-Earth asteroids, Mars and its moons and beyond. Its modular architecture is aimed to configure each launch vehicle for specific mission needs using a variation of common elements to achieve a variety of payload volumes and weights.

The SLS Initial Lift Capability will be designed to carry the Orion Multi-purpose crew vehicle, as well as important cargo, equipment and science experiments to Earth's orbit and support deep space exploration. Besides, the SLS will serve as backup system for transportation services to the International Space Station (ISS). It has a lift capacity for 70 metric tons or 77 tons. The SLS Initial Lift Capability features a core stage, interstage and the Orion multi-purpose crew vehicle along with the Launch Abort System (ALS). The core stage uses RS-25D/E rocket engines derived from the Space Shuttle Main Engines along with two solid rocket boosters (SRBs). At liftoff the rocket has 10 percent more thrust than the Saturn V heavy launch vehicle.

SLS Initial Lift Capability Specifications

Number of Stages: 1
Dimensions
Height: 320 foot (3,840 inch)
Volume
Payload Capacity: 70 metric ton
Weight
Max Lift-off Thrust: 8,400,000 pound (3,810 ton)
Max Lift-off Weight: 5,500,000 pound (2,495 ton)
Payload: 77 ton (169,753 pound)
CEP: Circular Error Probable
Meters (m)   Kilometers (km)   Nautic Miles (nm)   Inch (in)   Yard (yd)   Foot (ft)   Millimeter (mm)
Pound (lb)   Kilogram (kg)   kN (KiloNewton)   Ton (t)
Meters per Second (mps)   Kilometers per Hour (kph)   Knot (kt)   Miles per Hour (mph)
Liter (l)   Galon (gl)
Year (yr)   Minutes (min)   Second (sec)
Shaft-Horse-Power (shp)

SLS Initial Lift Capability News

There are 2 news between
14 Sep 2011 and 2 Jul 2014
Wednesday, July 2, 2014Boeing to Develop Core Stage of Space Launch System Contract
Wednesday, September 14, 2011NASA Announces Design for SLS Deep Space Exploration System

Operators & Related Equipment


OperatorsItems

Grand Total ?1
Propulsion Systems
RS-25D/Ex5
Solid Rocket Boosterx2
Space Systems
Orion
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