NASA has (unwisely IMO - too expensive) been given clearance by Congress to build the Space Launch System launcher and the Orion MPCV (multi-purpose crew vehicle) capsule.
Space Launch System will be built in 2 scalable blocks;
Block 1:
Payload to low Earth orbit: 70 metric tons (150,000 lb)
Block 2:
Payload to low Earth orbit: 129,000 kg (280,000 lb)
First stage
Core diameter:8.4 meters (27.56 ft)
Liquid engines: 3 to 5 RS-25D/E (disposable Shuttle engines)
Sea level thrust (each): 1,817,400 newtons (408,600 lbf)
Vacuum thrust (each): 2,278,000 newtons (512,000 lbf)
Fuel/oxidizer: LH2/LOX
Solid rocket boosters (SRBs): 2 five-segment
Sea level thrust (each) 12,500,000 newtons (2,800,000 lbf)
Fuel/oxidizer (by weight): 16% aluminum, 12.04% PBAN (polymer), 1.96% epoxy, 0.4% iron oxide/69.6% ammonium perchlorate
(a competition will be held later to either keep the SRBs or replace them with liquid side boosters)
Second stage
Core diameter: 8.4 meters (27.56 ft)
Liquid engines: 1 or 2 Rocketdyne J-2X (upgraded Saturn V J2 2nd stage)
Vacuum thrust: 1,310,000 newtons (294,000 lbf)
Fuel/oxidizer: LH2/LOX
The Orion Multi-Purpose Crew Vehicle is a conical capsule build with the same mold line as Apollo, but larger.
Crew: 4
Diameter: 5 meters (16.5 ft)
Pressurized volume: 19.56 m3 (691 cu ft)
Habitable Volume: 8.95 m3 (316 cu ft)
Mass: 8,913 kg (19,650 lb)
Service Module Mass: 12,337 kg (27,198 lb)
Service Module Propellant Mass: 7,907 kg (17,433 lb)
Endurance: 21.1 days
Penciled-in flight manifest:
Here's is a huge weakness - the SLS & Orion are so expensive the funds for flying it will be very short -
Pics:
Space Launch System will be built in 2 scalable blocks;
Block 1:
Payload to low Earth orbit: 70 metric tons (150,000 lb)
Block 2:
Payload to low Earth orbit: 129,000 kg (280,000 lb)
First stage
Core diameter:8.4 meters (27.56 ft)
Liquid engines: 3 to 5 RS-25D/E (disposable Shuttle engines)
Sea level thrust (each): 1,817,400 newtons (408,600 lbf)
Vacuum thrust (each): 2,278,000 newtons (512,000 lbf)
Fuel/oxidizer: LH2/LOX
Solid rocket boosters (SRBs): 2 five-segment
Sea level thrust (each) 12,500,000 newtons (2,800,000 lbf)
Fuel/oxidizer (by weight): 16% aluminum, 12.04% PBAN (polymer), 1.96% epoxy, 0.4% iron oxide/69.6% ammonium perchlorate
(a competition will be held later to either keep the SRBs or replace them with liquid side boosters)
Second stage
Core diameter: 8.4 meters (27.56 ft)
Liquid engines: 1 or 2 Rocketdyne J-2X (upgraded Saturn V J2 2nd stage)
Vacuum thrust: 1,310,000 newtons (294,000 lbf)
Fuel/oxidizer: LH2/LOX
The Orion Multi-Purpose Crew Vehicle is a conical capsule build with the same mold line as Apollo, but larger.
Crew: 4
Diameter: 5 meters (16.5 ft)
Pressurized volume: 19.56 m3 (691 cu ft)
Habitable Volume: 8.95 m3 (316 cu ft)
Mass: 8,913 kg (19,650 lb)
Service Module Mass: 12,337 kg (27,198 lb)
Service Module Propellant Mass: 7,907 kg (17,433 lb)
Endurance: 21.1 days
Penciled-in flight manifest:
Here's is a huge weakness - the SLS & Orion are so expensive the funds for flying it will be very short -
Pics:
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