Earth Departure Stage

The Earth Departure Stage (EDS) is the name given to the second stages of two Shuttle-Derived Launch Vehicles, the Ares V and the Block II Space Launch System. The EDS is intended to boost the rocket's payload into a parking orbit around the Earth and from there send the payload out of low Earth orbit to its destination in a manner similar to that of the S-IVB rocket stage used on the Saturn V rockets that propelled the Apollo spacecraft to the Moon between 1968 and 1972.

Ares V

Design

The EDS used on the Ares V would have been propelled by a single J-2X main engine fuelled with liquid oxygen (LOX) and liquid hydrogen (LH₂), and was to have been designed at NASA's Marshall Space Flight Center in Huntsville, Alabama as part of Project Constellation. Originally, the stage would have been based on the Space Shuttle's External Tank, and would have used two J-2X engines, while the Ares V core booster would have used five Space Shuttle Main Engines and two 5-segment Solid Rocket Boosters during the first eight minutes of flight. When the Ares V was then redesigned around the use of five (later six^[1]) RS-68B rocket engines currently used on the Delta IV EELV family, the EDS was then redesigned using only a single J-2X engine and a common bulkhead, thus in its final design, the EDS resembled an oversized S-IVB, but with the capability of on-site storage (using new propellant storage techniques along with a "loiter skirt" containing solar panels for electricity) for up to 4 days, something impossible with the old S-IVB.

Mission

Launched on the Ares V rocket, the EDS with its Altair payload would not have become active until the six RS-68 engines cutoff and the Ares V core was jettisoned to burn up in Earth's atmosphere. Upon separation using the on-board staging and ullage motors, the single J-2X engine would then have fired at full thrust to place itself and the Altair into a Low-Earth orbit until it was retrieved, via a separate launch on an Ares I, by the Orion MPCV and its four-person astronaut crew.

Once the Orion was docked with the Altair and its systems were checked out, the crew was to jettison the "loiter skirt" and then fire the J-2X engine for a second time, this time at 80% rated thrust, for Trans Lunar Injection (TLI). Unlike the S-IVB, which propelled the Apollo Spacecraft and its three-man crew in a forward-facing motion, the EDS would have fired its onboard rocket with the crew facing the EDS. This "eyeballs out" type of flying would be similar to the flight profile of the proposed, but never flown Manned Venus Flyby, from the cancelled Apollo Applications Program of the late 1960s.

When TLI was completed and the EDS was shut down for the last time, it would then have been jettisoned to fly into a heliocentric orbit, or in a manner similar to that employed by NASA from Apollo 13 to Apollo 17, it may have been deliberately crashed into the lunar surface to help scientists calibrate sensitive seismometers placed on the lunar surface by either astronauts on lunar sortie flights or by unmanned robotic probes.^[2]

Space Launch System

When the Ares program was cancelled in favor of the Space Launch System, the EDS was considered as a second stage for the Block 1B SLS.^[3] This version of the stage would have been about 80 feet (24 m) long and equipped with one or two J-2X engines.^[4] Technological development of the J-2X was expected to take considerably more time, so the EDS was dropped in favor of the Exploration Upper Stage, which will use the much lower-thrust but already-developed RL10. According to NASA, the J-2X will be overpowered for the lunar and asteroid missions of the Block I and IB SLS; its development has been put on hold (though not abandoned) until stages capable of transferring heavy payloads to Mars are required (currently expected in the 2030s, to be served by the Block II).^[5]

References

 This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.

Constellation program
Launch tests	Ares I-X Pad Abort 1
Later missions	List of Constellation missions Orion Asteroid Mission Orion Mars Mission
Components	Orion Crew Exploration Vehicle Ares I Ares V Earth Departure Stage Altair J-2X RS-68 Shuttle-Derived Launch Vehicle Shuttle-Derived Heavy Lift Launch Vehicle Jupiter (rocket family)
Launch sites	Kennedy Space Center Launch Complex 39
Abort	Orion abort modes Orion Abort Test Booster Launch Abort System (LAS) Max Launch Abort System (MLAS)
Related topics	Vision for Space Exploration Exploration Systems Architecture Study DIRECT Constellation Space Suit Advanced Technology Large-Aperture Space Telescope (AT-LAST) NASA Authorization Act of 2005 Augustine Commission
List of missions

J-2 rocket engine
Variants	J-2 J-2S J-2T J-2X
Technologies	Bipropellant Gas-generator cycle LOX LH2
Historic Vehicles	Saturn IB (S-IVB) Saturn V (S-II S-IVB)
Future Vehicles	Space Launch System (EDS)
Other LOX & LH2 Engines	RS-25 RS-68 RL-10 Vulcain