REPLAY: Artemis 1 mission status briefing, upcoming fly-by (18 Nov 2022)

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This is a replay of the live stream.
NASA’s Space Launch System super heavy-lift rocket will launch from LC-39B at Kennedy Space Center, on its first test flight with an uncrewed Orion spacecraft. The mission, known as Artemis 1, will place the Orion spacecraft into orbit around the moon for 3-4 weeks. Orion will then return to Earth for splashdown in the Pacific Ocean. Ten small CubeSat rideshare payloads will also tag along. This test flight paves the way for the first crewed mission to return humans to the Moon - Artemis 2 - currently planned for May 2024.

-=[ SLS Block 1 Crew rocket ]=-
Height: 322 ft (98 m)
Stages: 2
Payload to LEO: 209,000 lb (95 t)
Payload to Trans-Lunar Injection: 59,500+ lb (27 t)
Fuel: Cryogenic liquid hydrogen (LH2)
Oxidizer: Cryogenic liquid oxygen (LOX)
Total thrust at liftoff: 8,800,000 lbf (39 MN)

-=[ Core Stage ]=-
Height: 213 ft (65 m)
Diameter: 27.6 ft (8.4 m)
Engines: 4 Aerojet Rocketdyne RS-25D's (all previously flown on Space Shuttle missions)
Thrust (each): 513,000 lbf (2,281 kN)
Total Core Stage thrust: 2,052,000 lbf (9,124 kN)

-=[ Solid Rocket Boosters ]=-
2 Five-segment Northrop Grumman SRB's, derived from the Space Shuttle
Height: 177 ft (54 m)
Diameter: 12 ft (3.7 m)
Weight (each): 1.6 million lb (800 t)
Fuel: Polybutadiene acrylonitrile (PBAN)
Thrust (each): 3.6 million lbf (16 MN)
Total SRB thrust: 7.2 million lbf (32 MN)
Burn time: 126 sec

-=[ Interim Cryogenic Propulsion Stage (ICPS) ]=-
Modified Delta IV Delta Cryogenic Second Stage
Engine: 1 Aerojet Rocketdyne RL-10B-2
Propellant: LH2 / LOX
Thrust: 24,800 lbf (110.1 kN)
Specific impulse (vacuum): 465.5 seconds (4.565 km/s)
Burn time: 1,125 s

-=[ Orion Multi-Purpose Crew Vehicle ]=-
Crew capacity: 2-6 (Artemis 1 will be uncrewed)
Height: 10 ft 10 in (3.30 m)
Diameter: 17 ft 6 in (5.03 m)
Total launch mass (with Launch Abort System): 73,735 lb (33,446 kg)
Injected lunar mass: 58,467 lb (26,520 kg)
Volume (pressurized): 690.6 cu ft (20 m³)
Volume (habitable): 316 cu ft (9 m³)
Return payload capacity: 220 lb (100 kg)

-=[ Orion Crew Module (CM) ]=-
Manufactured by Lockheed Martin
Dry mass: 20,500 lb (9,300 kg) landing weight
Launch mass: 22,900 lb (10,400 kg)

-=[ Orion European Service Module (ESM) ]=-
Manufactured by Airbus Defence and Space
Dry mass: 13,635 lb (6,185 kg)
Launch mass: 34,085 lb (15,461 kg)

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Intro video courtesy efeuEntertainment using Space Engine
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