1969 Apollo 11 Saturn V launch, 1969 TV broadcast

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1969 TV broadcast of the launch of the Apollo 11 Saturn V rocket which carried astronauts Neil Armstrong, Buzz Aldrin, and Michael Collins to the Moon. Armstrong and Aldrin landed the lunar module "Eagle" and became the first humans to set foot on another celestial body. Collins piloted the command module "Columbia" in its orbit around the Moon.

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Saturn V Info
~~~~~~~~~~~
Cost per launch: $1.23B (adjusted for 2019)
Height: 110.6 m (363.0 ft)
Diameter: 10.1 m (33.0 ft)
Mass: 2,970,000 kg (6,540,000 lb)
Payload to LEO: 140,000 kg (310,000 lb)
Payload to TLI: 48,600 kg (107,100 lb)
First/Last Flights: Nov 9, 1967 - May 14, 1973
13 launches, 12 successes, 1 partial failure (Apollo 6)

Saturn V First Stage (S-IC)
~~~~~~~~~~~~~~~~~
Height: 42.1 m (138 ft)
Diameter: 10.1 m (33 ft)
Dry mass: 130,000 kg (287,000 lb)
Launch mass: 2,290,000 kg (5,040,000 lb)
Engines: 5 Rocketdyne F-1
Thrust (sea level): 35,100 kN (7,891,000 lbf)
Specific impulse (sea level): 263 seconds (2.58 km/s)
Burn time: 168 seconds
Fuel: RP-1 / LOX
Manufacturer: Boeing

Saturn V Second Stage (S-II)
~~~~~~~~~~~~~~~~~~~~
Height: 24.8 m (81.5 ft)
Diameter: 10.1 m (33 ft)
Dry mass: 40,100 kg (88,400 lb)
Launch mass: 496,200 kg (1,093,900 lb)
Engines: 5 Rocketdyne J-2
Thrust (vacuum): 5,141 kN (1,155,800 lbf)
Specific impulse (vacuum): 421 seconds (4.13 km/s)
Burn time: 360 seconds
Fuel: LH₂ / LOX
Manufacturer: North American Aviation

Saturn V Third Stage (S-IVB)
~~~~~~~~~~~~~~~~~~~
Height: 18.8 m (61.6 ft)
Diameter: 6.6 m (21.7 ft)
Dry mass: 15,200 kg (33,600 lb)
Launch mass: 123,000 kg (271,000 lb)
Engines: 1 Rocketdyne J-2
Thrust (vacuum): 1,033.1 kN (232,250 lbf)
Specific impulse (vacuum): 421 seconds (4.13 km/s)
Burn time: 165 + 335 seconds (2 burns)
Fuel: LH₂ / LOX
Manufacturer: Douglas Aircraft Company

Apollo Command Module (CM)
~~~~~~~~~~~~~~~~~~~~~
Height: 3.5 m (11.4 ft)
Diameter: 3.9 m (12.8 ft)
Mass: 5,560 kg (12,250 lb)
Interior volume: 5.9 m³ (210 cu ft)
Crew capacity: 3
Reaction Control System thrusters: 12
RCS thrust, ea.: 410 N (93 lbf)
RCS fuel: MMH / N₂O₄
Manufacturer: North American Aviation / North American Rockwell

Apollo Service Module (SM)
~~~~~~~~~~~~~~~~~~~
Height: 7.6 m (24.8 ft)
Diameter: 3.9 m (12.8 ft)
Mass: 24,520 kg (54,060 lb)
Service Propulsion System engine: 1 Rocketdyne AJ10-137
SPS thrust: 91 kN (20,500 lb)
SPS fuel: Aerozine 50 (50:50 mix of hydrazine/UDMH) / N₂O₄
Reaction Control System thrusters: 4 x 4 (16) Marquardt R-4D
RCS thrust, ea.: 440 N (100 lbf)
RCS fuel: MMH / N₂O₄
Manufacturer: North American Aviation / North American Rockwell

Lunar Module (LM)
~~~~~~~~~~~~~
Height: 7.04 m (23 ft 1 in)
Diameter: 4.22 m (13 ft 10 in) without landing gear
Width: 9.4 m (31 ft) landing gear deployed
Dry mass: 4,280 kg (9,430 lb)
Launch mass: 15,200 kg (33,500 lb)
Crew cabin volume: 6.7 m³ (235 cu ft)
Habitable volume: 4.5 m³ (160 cu ft)
Crew capacity: 2
Descent Propulsion System engine: 1 TRW LMDE
DPS thrust: 45.04 kN (10,125 lbf), throttleable
DPS fuel: Aerozine 50 (50:50 mix of hydrazine/UDMH) / N₂O₄
Ascent Propulsion System engine: 1 Bell / Rocketdyne LMAE
APS thrust: 16 kN (3,500 pounds-force), fixed
APS thrust-to-weight ratio: 19.44
APS fuel: Aerozine 50 (50:50 mix of hydrazine/UDMH) / N₂O₄
Reaction Control System thrusters: 4 x 4 (16) Marquardt R-4D
RCS thrust, ea.: 440 N (100 lbf)
RCS fuel: MMH / N₂O₄
Manufacturer: Grumman Aircraft

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