"The Saturn Propulsion System" Project Apollo Rocket Engines 1962 NASA Marshall Space Flight Center
more at
http://scitech.quickfound.net/astro/project_apollo
.html
Reupload of a previously uploaded film with improved sound and video.
"The theory of reaction engines and the application to the
Saturn propulsion system." Includes film of the first Saturn I launch in
1961 (
SA-1).
NASA f HQ-a77
I couldn't do much to improve the color on this one, but the sound cleaned up nicely.
Public domain film from NASA, slightly cropped to remove uneven edges, with the aspect ratio corrected, and 1-pass exposure & color correction applied (cannot be ideal in all scenes).
The soundtrack was also processed with volume normalization, noise reduction, clipping reduction, and/or equalization (the resulting sound, though not perfect, is far less noisy than the original).
Rocket engine development history:
V-2 engine led to
Navaho engine led to
Atlas engine led to Saturn
H-1 engine.
http://en.wikipedia.org/wiki/SM-64_Navajo
...Development of the first stage rocket engine for the Navaho began with two refurbished
V-2 engines in
1947. That same year, the phase II engine was designed, the XLR-41-NA-1, a simplified version of the V-2 engine made from
American parts. The phase
III engine, XLR-43-NA-1 (also called 75K), adopted a cylindrical combustion chamber with the experimental
German impinging-stream injector plate.
Engineers at
North American were able to solve the combustion stability problem, which had prevented it being used in the V-2, and the engine was successfully tested at full power in 1951. The
Phase IV engine, XLR-43-NA-3 (120K), replaced the poorly cooled heavy German engine wall with a brazed tubular ("spaghetti") construction, which was becoming the new standard method for regenerative cooling in American engines. A dual-engine version of this, XLR-71-NA-1 (240K), was used in the G-26 Navaho. With improved cooling, a more powerful kerosene-burning version was developed for the triple-engine XLR-83-NA-1 (405K), used in the
G-38 Navaho. With all the elements of a modern engine (except a bell-shaped nozzle), this led to designs for the Atlas,
Thor and
Titan engines...
http://en.wikipedia.org/wiki/H-1_(rocket_engine)
Rocketdyne's H-1 is a 205,
000 lbf (910 kN) thrust liquid-propellant rocket engine burning
LOX and
RP-1. The H-1 was developed for use in the
S-IB first stage of the Saturn I and Saturn IB rockets, where it was used in clusters of eight engines. After the
Apollo program, surplus H-1 engines were rebranded and reworked as the Rocketdyne
RS-27 engine with first usage on the
Delta 2000 series in
1974...
http://en.wikipedia.org/wiki/F-1_(rocket_engine)
The
F-1 is a rocket engine developed by Rocketdyne and used in the Saturn V. Five F-1 engines were used in the
S-IC first stage of each Saturn V, which served as the main launch vehicle in the Apollo program. The F-1 is still the most powerful single-chamber liquid-fueled rocket engine ever developed. The
RD-170 has slightly more thrust, using a cluster of four smaller combustion chambers and nozzles...
http://en.wikipedia.org/wiki/J-2_(rocket_engine)
The
J-2 was a liquid-fuel cryogenic rocket engine used on NASA's Saturn IB and Saturn V launch vehicles.
Built in the
United States of America by Rocketdyne, the J-2 burned cryogenic liquid hydrogen & liquid oxygen propellants, with each engine producing 1,
033.1 kN (232,250 lbf) of thrust in vacuum. Development of the engine began in the
1960s, with the first flight,
AS-201, occurring on
26 February 1966. The J-2 underwent several minor upgrades over its operational history to improve the engine's performance, with two major upgrade programs, the de
Laval nozzle-type
J-2S and aerospike-type
J-2T, being cancelled after the conclusion of the Apollo program.
Five J-2 engines were used on the Saturn V's
S-II second stage, and one J-2 was used on the
S-IVB upper stage used on both the Saturn IB and Saturn V. Proposals also existed to use various numbers of J-2 engines in the upper stages of an even larger rocket, the planned
Nova. The J-2 was
America's largest production liquid hydrogen fuelled rocket engine before the
RS-25 Space Shuttle Main Engine, and a modernised version of the engine,
the J-2X, is intended for use on the
Earth Departure Stage of NASA's
Space Shuttle replacement, the
Space Launch System.
Unlike most liquid-fuelled rocket engines in service at the time, the J-2 was designed to be re-started once after shutdown when flown on the Saturn V. The first burn, lasting about two minutes, placed the
Apollo spacecraft into a low
Earth parking orbit. After the crew verified that the spacecraft was operating nominally, the J-2 was re-ignited for translunar injection, a 6.5 minute burn which accelerated the vehicle to a course for the
Moon...
http://en.wikipedia.org/wiki/Saturn_I
http://en.wikipedia.org/wiki/Saturn_IB
http://en.wikipedia.org/wiki/Saturn_V