# Tag Info

79

Hobbes' answer focuses on why we might want to build SLS. There are also significant barriers to rebuilding Saturn/Apollo. In addition to the (vast) amount of existing technical documentation on those designs, there's a (probably vaster) pool of knowledge that the individuals who actually built the things collected during the process. Nearly all of those ...

70

Your picture is not of a Saturn V, it's of a Saturn IB. The purpose of the elevated platform (known as the "milkstool") is to lift the rocket up so that it can be launched from Pad 39B using the same connections to the launch tower that the much taller Saturn V used. The early Saturn IB launches used the shorter Pad 34 and Pad 37, but by 1973, those launch ...

62

Going directly to the Moon would require a very small launch window. The Earth orbit before enabled a launch window of about 3 to 4 hours, see this question. Abort from an Earth orbit was possible when the second ignition of the third stage of the Saturn V failed using the Service Module engine to initiate a reentry. Time in orbit was used to complete the ...

59

The photo is of the launch of Gemini 11 on September 12, 1966. The Saturn V in the background is SA-500F, a "Facilities Integration Vehicle". This was a nearly complete Saturn V that was used to test integration with the launch facilities at Kennedy Space Center: Tests included the mating of the Saturn's stages in the Vehicle Assembly Building (...

53

I don't know of any features on the Saturn V that are solely aesthetic in purpose. The flags and USA markings come closest, but they are ostensibly there to identify the origin of the vehicle. The overall white paint scheme is to minimize heating of the cryogenic propellant tanks from sunlight. The interrupted black stripes along the fuselage provide visual/...

44

There is very little to gain by going straight to the Moon, and as @Uwe has said, it makes the timing of the launch extremely demanding. Let me have my go at explaining why there is very little to gain. The most fuel efficient way for a rocket to get from Earth to the Moon is basically to accelerate as close to the Earth as possible until it is moving at ...

41

There are several reasons: We can do better these days. Saturn and Apollo were designed in the early 1960s, so the design tools used were mainly pen and paper, with some primitive computer tools thrown in here and there. These days CAD can be used to create a design that performs far better (because you can design parts closer to the strength they need, ...

41

Had a bit of a gander at what NASA Technical Report Server and Semantic Scholar had to offer and found a couple things that I reckon might be helpful. NASA created a 1/10 scale model of the Saturn V for a study vehicle dynamics and you can read the report here This gives us these two schematics. They also created a 1/25 scale model for aerodynamic testing. (...

38

What a fascinating question! Turns out it's less flammable. Ground Supply Fluid—Because the flash point of RP-1 fuel, which supplies the system in flight, is 110 to 139° F, it is classified as a Class Ill flammable liquid, not suitable for ground operations. A study was made to find substitute fluids with properties similar to RP-1 that could be ...

38

They used the Mobile Service Structure (MSS), which for some reason is rarely shown in Apollo pre-launch photos. The large work platforms at upper right completely surrounded the spacecraft and the upper section of the S-IVB stage, which held the Lunar Module. From these platforms, technicians could make last-minute changes to the flight hardware. ...

34

The one at the Space & Rocket Center in Huntsville has been stored outside so it wasn't in good shape. Displayed outdoors and on its side since 1969, the rocket was exhibiting widespread paint failure, moisture infiltration, an overall accumulation of atmospheric and biological soiling, and corrosion of its complex system of metal alloys, including ...

34

I think you may have a misunderstanding that isn't addressed by any of the other answers. It is true that most of a rocket's work in entering orbit is building up enough speed to reach orbital velocity. But you have to build up even more speed to make it to the moon. In fact, while they were on their way to the moon they were still in orbit around the earth,...

32

Three factors come to mind from my reading over the years: Heat Shield integrity, Escape Tower limitations, and avoiding fuel over the CM on the pad. Throughout this answer, keep in mind that the stacking order (from the top) is Escape Tower (ET), Command Module (CM), Service Module (SM), Lunar Module Shroud, Lunar Module (LM). See the full Saturn V diagram ...

31

No, the blueprints were not destroyed or lost. (This is) a claim John Lewis made in his 1996 book, Mining the Sky, that he went looking for the Saturn 5 blueprints a few years ago and concluded, incredibly, they had been "lost." Paul Shawcross, from NASA's Office of Inspector General, came to the agency's defense in comments published on CCNet -- ...

31

The J-2 engine used on the second and third stages of the Saturn V has a "PU valve" (propellant utilization) on the oxidizer turbopump. Adjusting the mixture ratio with this valve primarily provides a mechanism to ensure that the hydrogen and oxygen propellants are depleted at the same time. Secondarily, it allows a tradeoff between specific ...

31

The early prototypes of the A4/V2 were painted in the familiar black-and-white roll pattern scheme. This scheme was designed to aid in tracking the rocket after launch. This pattern made it easy to observe any variation or roll of the rocket. The exact pattern was changed many times, and as with the rest of the rocket, the pattern was examined and ...

30

Offered as a supplement, since no one has posted a direct size comparison: The height difference in the Saturn V and Saturn 1-B is clear in this image. Edit: SA-1 through -9 are Saturn 1s, SA-201 through -205 are 1-Bs, the last 2 are Vs. The mission payloads, from left to right: SA-1, development flight with dummy second stage and payload SA-4, more ...

30

Some switches were normally left in one position for the entire mission, and would only be changed in unusual situations. One particular semi-famous example is the switch controlling the power supply for a module called the Signal Conditioning Equipment (SCE), which was necessary for sending telemetry from the spacecraft to mission control. It had two ...

29

NOTE All dollar values are in present day values accounting for inflation. Another reason we're not reusing the Saturn V is the same reason it was cancelled in the first place: cost. The SLS is supposed to be half the cost per launch. Whether that works out remains to be seen. The Saturn V was expensive. The Saturn V program cost \\$47 billion over 10 ...

29

If the angular rates on the first stage are not close to zero there is a chance of the inter-stage contacting the engine bells. (Falcon 1 flight 2?) With a separate inter-stage the upper stage can hang onto it (protecting the engine bells) until under propulsion and rapidly accelerating away from it reducing the chance of contact.

27

In order to use the direct ascent method of landing on the moon, which is where the entire vehicle descends and leaves the moon, you would need a rocket an order of magnitude bigger than the Saturn V, not just a bit bigger. Here's an early comparison NASA made back before they decided to use Lunar Orbit Rendezvous: The C1 became the Saturn I, the C-5 ...

27

There's a more detailed profile drawing available for download at the bottom of this Heroic Relics page. Here's a representative slice: It used to be possible to get an inexpensive print of a cleaned-up, white-on blue version of this, 180cm long. (I have one, it's beautiful. The custom frame cost much more than the print.)

26

I carefully examined the Saturn V in Houston (in particular the instrumentation unit) few months ago. There's no way this Saturn V would fly for a couple reasons: It was stored outside and suffered lots of corrosion and damage. It was restored enough to be exhibited but the metal still has lots of corrosion covered by paint. The instrumentation unit is ...

24

The amount by which a spacecraft is able to change its velocity is called it's Δv (delta-velocity) budget. You can calculate the Δv-budget of each stage of a rocket using the Tsiolkovsky rocket equation which reads: $$\Delta v = I_{sp} * 9.81 * \ln \frac {Mass_{full}} {Mass_{dry}}$$ where Isp is the specific impulse ("fuel-efficiency") of the engine. The ...

24

The requirements of the first stage are that it deliver about 3340 m/s of delta v to a 690 ton payload (the upper stages and spacecraft), with an initial thrust-to-weight ratio of at least 1.16:1. The best candidate for a first-stage hydrogen engine in the Saturn era would be the never-completed M-1. At sea level, it would be much less powerful than the F-1,...

24

For the Saturn V, the first and second stages both cut off when a low-propellant-level sensor tripped in the tanks. Most launchers' booster stages do something similar -- burning to total depletion would be dangerous for a number of reasons noted here. For the S-IC first stage, it wasn't unusual to leave 30 tons of propellant unconsumed, as Apollo By The ...

22

This question seems to hinge on a fundamental misunderstanding about space, that is, to be fair, extremely common among the general public. It's the idea that space has no gravity, so things in space are weightless. "But wait!" you say. "I've seen videos of astronauts in space, and they sure seem weightless to me." And you'd be right, they do seem ...

21

During the early part of the Apollo program, the "direct ascent" mode was favored and Lunar-orbit rendezvous (LOR) was considered far too complex. In fact, the specifications of the Apollo service module were set by the direct ascent plan: the SPS engine is sized to lift off from the moon, and the fuel tankage is sufficient for lunar ascent and return to ...

21

From Stages to Saturn p. 212 The dual-plane separation was an alternative to a method called "fire in the hole," which involved ignition and separation of the S-II while still in contact with the interstage but not attached to it. Designers preferred to avoid this alternative because of possible perturbations and oscillations at the end of the ...

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