Count Until a Staff Member Posts! (394)

[Bricket]

4
Let's start again!

[Brisky]

5

The S-IVB was built by the Douglas Aircraft Company at Huntington Beach, California. It had one J-2 engine and used the same fuel as the S-II. The S-IVB used a common bulkhead to separate the two tanks. It was 58 feet 7 inches (17.86 m) tall with a diameter of 21 feet 8 inches (6.604 m) and was also designed with high mass efficiency, though not quite as aggressively as the S-II. The S-IVB had a dry weight of about 23,000 pounds (10,000 kg) and, fully fueled, weighed about 262,000 pounds (119,000 kg).[24]

The S-IVB-500 model used on the Saturn V differed from the S-IVB-200 used as the second stage of the Saturn IB, in that the engine was restartable once per mission. This was necessary as the stage would be used twice during a lunar mission: first in a 2.5 min burn for the orbit insertion after second stage cutoff, and later for the trans-lunar injection (TLI) burn, lasting about 6 min. Two liquid-fueled Auxiliary Propulsion System (APS) units mounted at the aft end of the stage were used for attitude control during the parking orbit and the trans-lunar phases of the mission. The two APSs were also used as ullage engines to settle the propellants in the aft tank engine feed lines prior to the trans-lunar injection burn.

The S-IVB was the only rocket stage of the Saturn V small enough to be transported by plane, in this case the Pregnant Guppy.

[Bricket]

6
How am I supposed to post with this interesting information?

[Momma Bird]

7

Well, good luck, sorry I really have to go soon.


As for the one word challenge, you should try to incorporate the word; conviviality (I do not know the Dutch equivalent)

[Brisky]

8

Instrument Unit
Main article: Saturn V Instrument Unit
The Instrument Unit for the Apollo 4 Saturn V

The Instrument Unit was built by IBM and rode atop the third stage. It was constructed at the Space Systems Center in Huntsville, Alabama. This computer controlled the operations of the rocket from just before liftoff until the S-IVB was discarded. It included guidance and telemetry systems for the rocket. By measuring the acceleration and vehicle attitude, it could calculate the position and velocity of the rocket and correct for any deviations.
Range safety

In the event of an abort requiring the destruction of the rocket, the range safety officer would remotely shut down the engines and after several seconds send another command for the shaped explosive charges attached to the outer surfaces of the rocket to detonate. These would make cuts in fuel and oxidizer tanks to disperse the fuel quickly and to minimize mixing. The pause between these actions would give time for the crew to escape using the Launch Escape Tower or (in the later stages of the flight) the propulsion system of the Service module. A third command, "safe", was used after the S-IVB stage reached orbit to irreversibly deactivate the self-destruct system. The system was also inactive as long as the rocket was still on the launch pad.[25]

Bye bye, Momma!

[Momma Bird]

9 Bye Brisky

[Bricket]

10
Bya Momma, and the word? i'll easily use it

[Brisky]

11

Titan II

The Saturn V had a much lower thrust-to-weight ratio than Project Gemini's Titan II GLV. Richard F. Gordon, Jr. described Saturn as "an old man's ride", with "a lot more shake-rattle-and-roll" but milder thrust. Buzz Aldrin and other Apollo 11 astronauts agreed that they could not tell when Saturn liftoff occurred except from instruments, unlike on Titan.[26]
Soviet N1-L3
A comparison of the U.S. Saturn V rocket with the Soviet N1-L3

The Soviet space program's counterpart to the Saturn V was Sergei Korolev's N1-L3. The Saturn V was taller, heavier, and had greater payload capacity, both to low Earth orbit and to translunar injection.[27] The N-1 was a three-stage launch vehicle with more liftoff thrust and a larger first stage diameter than the Saturn V.[28] It was to carry the 209,000 lb (95,000 kg) L3 vehicle into orbit. The L3 contained an Earth departure stage, which would send to the Moon a 51,800 lb (23,500 kg) package which contained another stage for lunar orbit insertion and powered descent initiation, a single-cosmonaut lander, and a two-cosmonaut lunar orbiter for the return to Earth. The N1/L3 would have produced more total impulse (product of thrust and time) in its first four stages than the three-stage Saturn V, but it was not able to convert as much of this into payload momentum (product of mass and velocity).

The N1 never became operational; four test launches each resulted in catastrophic vehicle failure early in flight, and the program was canceled. Korolev elected to cluster 30 relatively small engines for the first stage, rather than develop a large engine like the Rocketdyne F-1.

The three-stage Saturn V grew over its lifetime to a peak thrust of at least 7,650,000 lbf (34,020 kN) (AS-510 and subsequent)[29] and a lift capacity of 310,000 lb (140,000 kg) to LEO. The AS-510 mission (Apollo 15) had a liftoff thrust of 7,823,000 lbf (34,800 kN). The AS-513 mission (Skylab 1) had slightly greater liftoff thrust of 7,891,000 lbf (35,100 kN). By comparison, the N-1 had a sea-level liftoff thrust of about 10,200,000 lbf (45,400 kN).[30] No other operational launch vehicle has ever surpassed the Saturn V in height, weight, total impulse, or payload capability. The closest contenders were the US Space Shuttle and the Soviet Energia.
   Saturn V (Apollo 11)[31]    N1-L3
Diameter, maximum    33 ft (10 m)    56 ft (17 m)
Height w/ payload    363 ft (111 m)    344 ft (105 m)
Gross weight    6,478,000 lb (2,938 t)    6,030,000 lb (2,735 t)
First stage    S-IC    Block A
Thrust, SL    7,500,000 lbf (33,000 kN)    10,200,000 lbf (45,400 kN)
Burn time, s    168    125
Second stage    S-II    Block B
Thrust, vac    1,155,800 lbf (5,141 kN)    3,160,000 lbf (14,040 kN)
Burn time, s    384    120
Orbital insertion stage    S-IVB (burn 1)    Block V
Thrust, vac    202,600 lbf (901 kN)    360,000 lbf (1,610 kN)
Burn time, s    147    370
Total impulse[32]    1.7336×109 lbf (7.711×106 kN)·s    1.789×109 lbf (7.956×106 kN)·s
Orbital payload    264,900 lb (120.2 t)[33]    209,000 lb (95 t)
Injection velocity    25,568 ft/s (7,793 m/s)    25,570 ft/s (7,793 m/s)[34]
Payload momentum    2.105×108 slug-ft/s (9.363×108 kg·m/s)    1.6644×108 slug-ft/s (7.403×108 kg·m/s)
Propulsive efficiency    12.14%    9.31%
Earth departure stage    S-IVB (burn 2)    Block G
Thrust, vac    201,100 lbf (895 kN)    100,000 lbf (446 kN)
Burn time, s    347    443
Total impulse[32]    1.8034×109 lbf (8.022×106 kN)·s    1.833×109 lbf (8.153×106 kN)·s
Translunar payload    100,740 lb (45.69 t)    52,000 lb (23.5 t)
Injection velocity    35,545 ft/s (10,834 m/s)    35,540 ft/s (10,834 m/s)[34]
Payload momentum    1.1129×108 slug-ft/s (4.95×108 kg·m/s)    5.724×107 slug-ft/s (2.546×108 kg·m/s)
Propulsive efficiency    6.17%    3.12%

[Bricket]

12
Alright, 60 more to go

[Brisky]

13

*Triggered*

[Emtile]

14

Woo! I'm so bored!

[Brisky]

15

Me too!

End my suffering, now!

[Aveq]

16


Hello again

[Bricket]

17
Hey there aveq, welcome back

[Brisky]

18

Hai!

U.S. Space Shuttle

The Space Shuttle generated a peak thrust of 6,800,000 lbf (30,100 kN),[35] and payload capacity to LEO (excluding the Orbiter itself) was 63,500 pounds (28,800 kg), which was about 25 percent of the Saturn V's payload. Total mass in orbit, including the Orbiter, was about 247,000 lb (112,000 kg), compared to the Apollo 15 total orbital mass of the S-IVB third stage and Apollo spacecraft, of 309,771 lb (140,510 kg),[36] some 62,800 lb (28,500 kg) heavier than the Shuttle was rated to carry to LEO.
Soviet Energia/Buran

Energia had a liftoff thrust of 7,826,000 lbf (34,810 kN),[37] and flew twice in 1987 and 1988, the second time as the launcher for the Buran shuttle. However, both the Energia and Buran programs were cancelled in 1993. Hypothetical future versions of Energia might have been significantly more powerful than the Saturn V, delivering 10,000,000 lbf (46,000 kN) of thrust and able to deliver up to 386,000 lb (175 t) to LEO in the "Vulkan" configuration. Planned uprated versions of the Saturn V using F-1A engines would have had about 18 percent more thrust and 302,580 pounds (137,250 kg) payload.[38] NASA contemplated building larger members of the Saturn family, such as the Saturn C-8, and also unrelated rockets, such as Nova, but these were never produced.

Some other recent US launch vehicles have significantly lower launch capacity to LEO than Saturn V: the US Delta 4 Heavy capacity is 63,470 lb (28,790 kg), the Atlas V 551 has a capacity of 41,478 lb (18,814 kg), and the planned SpaceX Falcon Heavy has a 141,000 lb (64,000 kg) projected capacity. The European Ariane 5 ES delivers up to 46,000 lb (21,000 kg) and the Russian Proton-M can launch 49,000 lb (22,000 kg).
Space Launch System

NASA's Space Launch System, planned for its first flight in 2018, in its final configuration is planned to be 400 feet (120 m) tall with payload, and lift up to 290,000 pounds (130,000 kg) into low Earth orbit.[39]