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Integrated Spacecraft/Payload Element Fact Sheet

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Integrated Spacecraft/Payload Element Fact Sheet National Aeronautics and Space Administration Space Launch System Integrated Spacecraft/ Payload Element NASA’s Space Launch System (SLS) will pro- vide the agency with super heavy-lift capability to return astronauts to the Moon and launch payloads to the Moon or deeper into the solar system. The integrated spacecraft/payload element for the initial SLS configuration, called Block 1, consists of the upper stage and payload section facts of the rocket, above the core stage, including adapters and separation systems. In the SLS Block 1 crew configuration, the inte- grated spacecraft/payload element connects the core stage to the Orion crew vehicle. In the Block 1 cargo variant, the integrated spacecraft/ payload element sits at the top of the vehicle, above the core stage, and includes a 5 meter- diameter payload fairing that encapsulates the payload. NASA is building the super heavy-lift SLS rocket to send astronauts in Orion to the Moon and NASA to launch cargo and scientific payloads to the Moon or deep into the solar system. Block 1 is the initial launcher, with progressively more powerful vehicles planned for the future to SLS Block 1 will be used for NASA’s first Artemis enable NASA to establish a sustainable pres- missions. The initial flight, Artemis I, is a test of ence at the Moon before sending humans to the new system – including Orion and ground sys- Mars. tems at Kennedy Space Center – and will include deployment of 13 CubeSats. The integrated spacecraft/payload element on the Block 1 crew vehicle is comprised of the In- The next flight, Artemis II, is a lunar flyby mission terim Cryogenic Propulsion Stage (ICPS), which that will make astronauts in Orion the record- provides in-space propulsion, the Launch Ve- holders for farthest distance humans have trav- hicle Stage Adapter (LVSA), and the Orion Stage eled from Earth. The third SLS Artemis mission is Adapter (OSA). The OSA provides space for planned to send the first woman and the next man small payloads, called CubeSats, to ride along to the surface of the Moon. on SLS deep space missions. Through NASA’s Artemis lunar exploration pro- On the Block 1 cargo vehicle, the integrated gram, the agency will use innovative new technol- spacecraft/payload element includes the ICPS, ogies and systems to explore more of the Moon LVSA, a payload attach fitting, and separation than ever before. NASA will use lessons learned system, as well as the 5 meter-diameter payload from those missions to send humans to Mars. fairing. Block 1 Crew - Initial SLS Configuration The integrated spacecraft/payload element for the SLS Block 1 crew configuration sits above the core stage and includes elements for in-space propulsion, adapters, a separation system, and a deployment system for CubeSat payloads. Interim Cryogenic Propulsion Stage Launch Vehicle Stage Adapter The ICPS is a 5-meter single-engine liquid hydrogen/ The cone-shaped LVSA partially encloses the ICPS liquid oxygen-based system that provides in-space and connects it to the SLS core stage below and the propulsion after the solid rocket boosters and core OSA above. A pneumatically actuated frangible joint stage are jettisoned. The ICPS, built by Boeing and assembly at the top of the adapter separates the core United Launch Alliance, is a modified Delta Cryogenic stage and LVSA from the ICPS, OSA, and Orion or Second Stage, a proven upper stage used on United payload fairing. In addition to providing structural sup- Launch Alliance’s Delta IV family of launch vehicles. port for launch and a separation system, the LVSA also Modifications for SLS include lengthening the liquid protects avionics and electrical devices in the ICPS hydrogen tank, adding hydrazine bottles for attitude from extreme vibration and acoustic conditions during control, and minor avionics changes. The ICPS is launch and ascent. Prime contractor Teledyne Brown powered by one Aerojet Rocketdyne RL10 engine and Engineering manufactures the LVSA using self-reacting generates 24,750 lbs. of maximum thrust. friction-stir welding tools at NASA’s Marshall Space Flight Center in Huntsville, Alabama. The ICPS, a modified United Launch Alliance Delta Cryogenic Second The LVSA connects the SLS core stage below to the OSA above and Stage, provides 24,750 lbs. of thrust for in-space propulsion for the includes a frangible joint assembly to separate the core from the Block 1 crew and cargo vehicles. upper stage. Space Launch System 2 NASA Facts Block 1 Cargo Configuration 5m Class Fairing Notional Payload Payload Attach Fitting Interim Cryogenic Propulsion Stage Solid Rocket Booster (2) RL10 Engine (1) Launch Vehicle Stage Adapter Core Stage RS-25 Engine (4) SLS Block 1 Cargo The integrated spacecraft/payload element for the SLS Block 1 cargo vehicle sits above the core stage and includes elements for in-space propulsion, adapters, a separation system, and a 5 meter-diameter fairing. Orion Stage Adapter The OSA, built by Marshall Space Flight Center, connects the ICPS to the Orion spacecraft. The adapter contains a diaphragm that provides a barrier to prevent gases generated during launch, such as hydrogen, from entering Orion. The OSA can also carry small payloads, called CubeSats, to deep space. The OSA can potentially accommodate up to 17 CubeSats in a combination of 6U and 12U sizes (one unit, or U, is 10 cm x 10 cm x 10 cm). The actual number of CubeSats manifested on a flight depends on several factors, including mission parameters and the combined weight of these small spacecraft. The SLS Program provides a comprehensive secondary payload deployment system for CubeSats, The OSA connects the ICPS to Orion and provides space for CubeSat including mounting brackets for commercial off- payloads to ride along on SLS missions to deep space. the-shelf (COTS) dispensers, cable harnesses, a vibration isolation system, and an avionics unit. CubeSats can play a key role in the Artemis missions by gathering data and demonstrating potential technologies that reduce risk, increase effectiveness, and improve the design of robotic and human space exploration missions. NASA Facts 3 Space Launch System Payload Fairing In addition to the ICPS and LVSA, the Block 1 cargo configuration has a 5-meter fairing, with an available volume of 229 cubic meters, for payloads. A payload attach fitting secures the payload in the fairing. Both the payload attach fitting and the payload are derived from the United Launch Alliance Delta IV launch vehicles, similar to the ICPS. Unique Capability for Deep Space Exploration SLS is designed to evolve to progressively more powerful variants, to give NASA the ability to send astronauts in Orion to the Moon or to launch strategic science payloads deep into the solar system. The initial version of SLS, Block 1, can launch more than 59,525 lbs. (27 metric tons [t]) to the Moon, powered by twin solid rocket boosters and four RS-25 engines in addition to the ICPS. The next planned evolution of SLS, Block 1B, will replace the ICPS with a more powerful Exploration Upper Stage to enable a lift capability of more than 92,500 lbs. (42 t) to the Moon, and to enable more ambitious missions. 92,500 lbs. (42 t)A later evolution, Block 2, will use more powerful solid rocket boosters to provide a 101,400 lbs. (46 t) lift capacity to the Moon. These future configurations of the vehicle will allow for larger and more varied payload capabilities. For more information about SLS, visit: http://www.nasa.gov/artemis http://www.nasa.gov/sls http://www.twitter.com/NASA_SLS http://www.facebook.com/NASASLS http://www.instagram.com/exploreNASA National Aeronautics and Space Administration George C. Marshall Space Flight Center Huntsville, AL 35812 www.nasa.gov/marshall www.nasa.gov FS-2020-07-35-MSFC.
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