Dragon lands in water, aided by parachute ...
http://www.spacex.com/dragon.phpDragon Highlights:
Fully autonomous rendezvous and docking with manual override capability in crewed configuration
6,000 kg (13,228 lbs) payload up-mass to LEO; 3,000 kg (6,614 lbs) payload down-mass
Payload Volume: 10 m3 (350 ft3) pressurized, 14 m3 (490 ft3) unpressurized
Supports up to 7 passengers in Crew configuration
Two-fault tolerant avionics system with extensive heritage
Reaction control system with 18 MMH/NTO thrusters designed and built in-house; these thrusters are used for both attitude control and orbital maneuvering
1290 kg of propellant supports a safe mission profile from sub-orbital insertion to ISS rendezvous to reentry
Integral common berthing mechanism, with LIDS or APAS support if required
Designed for water landing under parachute for ocean recovery Lifting re-entry for landing precision & low-g’s
Ablative, high-performance heat shield and sidewall thermal protection
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That is another aspect of the DC-X design that confounds - Where is the heat shield ? .... It still needs a heat shield for re-entry .... Imagine the difficulty of having workable engines BEHIND a hot heat shield .... I think the design of the Blue Origin spacecraft is a disaster ... It will never survive ...