General Saturn V Diagrams
I come across many Saturn V diagrams which, while interesting, are not so interesting that they necessarily merit their own separate page. I have created this page as a repository for such diagrams.
Here's a diagram which identifies each of the stages of the Saturn V launch vehicle:
A similar diagram, with the stages and major stage components called out. The height of the launch vehicle is quoted at 364.6 feet:
This one provides additional information about each stage:
|Power:||Five F-1 engines with combined thrust of 7.5 million pounds|
|Power:||Five J-2 engines with combined thrust of 1,000,000 pounds|
|Power:||One J-2 engine, 200,000 pounds thrust|
|Weight:||About 4,100 pounds|
I have two versions of this diagram, which shows each stage, their major components, and their respective manufacturers, one diagram with an inset showing the complete vehicle and one without the inset.
The stages, components, and manufacturers called out include
- LES - S&ID [heroicrelics: the Space and Information Systems Division of North American Rockwell]
- Apollo CM - S&ID
- Apollo SM - S&ID
- LEM Adapter - S&ID
- LEM - Grumman
- Instrument Unit - MSFC/IBM
- S-IVB - Douglas
- 1 J-2 Engine - Rocketdyne
- S-II - S&ID
- 5 J-2 Engines - Rocketdyne
- S-IC - Boeing
- 5 F-1 Engines - Rocketdyne
The inset notes that the Saturn V was 360 feet tall and had a total weight of 6,000,000 pounds.
No one seems to know the exact height of the Saturn V, as I've seen 360, 363, and 364.6 feet cited as its height. In reality, its height probably varied, as I imagine that weight of the propellants and the extreme cold of of its cryogenic propellants may have caused it to contract slightly. The difference between 360 and 364.6 feet is about 1.5%.
This diagram is from the Apollo 4 Press Kit (Apollo 4).
The stages and components called out include
- Launch Escape System
- Command Module
- Service Module
- Lunar Module
- Instrument Unit
- Fuel Tank
- LOX Tank
- J-2 Engine (1)
- Fuel Tank
- LOX Tank
- J-2 Engines (5)
- LOX Tank
- Fuel Tank
- F-1 Engines (5)
It's somewhat odd that a Lunar Module is depicted, as Apollo 4 flew without an actual Lunar Module; the LM did not fly until Apollo 5 (although Apollo 4 did carry a Lunar Module Test Article, LTA-10R).
This diagram identifies the height of the Saturn V as 363 feet, but I noticed that the “363'” is in a different font than the other call-outs. I later found an identical diagram from 1965 which cites an overall vehicle height of “~364.6'” (with this height appearing in the same font as the other captions).
Driving home my point about no one knowing the exact height of a Saturn V, we have this diagram, of SA-509 (Apollo 14), which shows a height of 363 feet. To add insult to injury, the gross weight is 6,423,754 pounds, well over the 6,000,000 pounds shown above. (Of course, as the program progressed, the Apollo spacecraft grew in weight, and the engines of the various stages were uprated slightly to compensate.)
This diagram merely notes the vehicle's height as 363 feet, the pre-launch launch vehicle gross weight as 6,423,754 pounds, and the following vehicle components
- S-IVB Stage
- S-II Stage
- S-IC Stage
This diagram is from the cover of the Saturn V Flight Manual, SA-510 (MSFC-MAN-510) (Apollo 15).
Visually, SA-510 through SA-512 are identical to each other but distinguished from earlier launch vehicles by the fact the four ullage motors were removed from S-II interstage. The resultant weight savings helped allow an increase in payload weight (recall that the weight of the Apollo spacecraft had grown substantially starting with Apollo 15, the first of “J missions”: it now carried both additional supplies to support three lunar EVAs as well as the first Lunar Roving Vehicle or LRV).
On SA-510, the S-IC stage also deleted four of the eight retromotors (which, installed beneath the engine fairings, are not visible in this diagram).
Analysis and previous flight experience had shown that adequate separation distance between the S-IC and S-II stages and adequate propellant seating in the S-II stage could be achieved with the deletion of these motors (although the coast period between S-IC engine cut-off and the S-II engine start command was extended by one second, to ensure adequate separate between the two stages).
As it turned out, separation distance on SA-510 was less than predicted and additional analysis showed that failure of one retromotor would fail to provide the desired separation distance or, in the extreme case, even allow recontact of the stages. SA-511 and subsequent returned to using eight retromotors on the S-IC.