Teile des Saturn V Launch Vehicle ab 1. Juli 1971 — die erste Stufe (S-IC) des Saturn V wird von der Boeing Company in der Michoud Assembly Facility der NASA, New Orleans, Louisiana, gebaut. Die fünf P-l-Motoren der Stufe entwickeln beim Start insgesamt rund 7,6 Millionen Pfund Schub. Hauptkomponenten der Bühne sind die Vorwärtsschürze, der Oxidationstank, die Zwischentank-Struktur, der Kraftstofftank und die Schubstruktur. Das Treibmittel zu den fünf Motoren fließt normalerweise mit einer Geschwindigkeit von 29.364,5 Pfund (3.400 Gallonen) pro Sekunde. Ein Motor ist starr auf der Mittellinie der Bühne montiert, die anderen vier Motoren sind montiert

• Bildanbieter: dpa picture alliance
• Bild-ID: 2JRM00Y
• Dateigröße: 81,5 MB (1,1 MB Komprimierter Download)
• Freigaben (Releases): Model - nein | Eigentum - nein
• Format: 5965 x 4774 px | 50,5 x 40,4 cm | 19,9 x 15,9 inches | 300dpi
• Aufnahmedatum: 1. Juli 1971
• Fotograf: dpa

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Parts of the Saturn V Launch Vehicle from July 1, 1971 — The first stage (S-IC) of the Saturn V is built by the Boeing Company at NASA's Michoud Assembly Facility, New Orleans, Louisiana. The stage's five P-l engines develop a total of about 7.6 million pounds of thrust at launch. Major components of the stage are the forward skirt, oxidizer tank, intertank structure, fuel tank, and thrust structure. Propellant to the five engines normally flows at a rate of 29, 364.5 pounds (3, 400 gallons) each second. One engine is rigidly mounted on the stage's centerline; the other four engines are mounted on a ring at 90-degree angles around the center engine. These four outer engines are gimbaled to control the vehicle's attitude during flight. The second stage (S-II) is built by the Space Division of the North American Rockwell Corporation at Seal Beach, California. Five J-2 engines develop a total of about 1.16 million pounds of thrust during flight. Major structural components are the forward skirt, liquid hydrogen and liquid oxygen tanks (separated by an insulated common bulkhead), a thrust structure, and an interstage section chat connects the first and second stages. The five engines are mounted and used in the same way as the first stage's P-1 engines: four outer engines can be gimbaled; the center one is rigid. The third stage (S-IVB) is built by the McDonnell Douglas Astronautics Company at Huntington Beach, California. Major components are the aft interstage and skirt, thrust structure, two propellant tanks with a common bulkhead, a forward skirt, and a single J-2 engine. The gimbaled engine has a maximum thrust of 230, 000 pounds and can be shut off and restarted. The Instrument Unit, Lunar Module, Service Module and Command Module are all stacked on top of the S-IVB stage. Credit: NASA via CNP

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