Count Until a Staff Member Posts! (394)

[Momma Bird]

39


Be nice to Emtile, our enemy is Cheza

[Brisky]

40

No, don't mention her.

It is she, who's name should never be spoken! >_>


The KORD (Russian acronym for KOntrol Raketnykh Dvigateley—literally "Control (of) Rocket Engines"—Russian: Контроль ракетных двигателей)[16] was the automatic engine control system devised to throttle, shutdown and monitor the large cluster of 30 engines in Block A (the first stage). The KORD system controlled the differential thrusting of the outer ring of 24 engines for pitch and yaw attitude control by throttling them appropriately and it also shut down malfunctioning engines situated opposite each other. This was to negate the pitch or yaw moment diametrically opposing engines in the outer ring would generate, thus maintaining symmetrical thrust. Block A could perform nominally with two pairs of opposing engines shut down (26/30 engines), Block B with one pair of opposing engines shutdown (6/8 engines) and Block V with one engine shut down (3/4 engines). Unfortunately the KORD system was unable to react to rapidly occurring processes such as the exploding turbo-pump during the 5L launch.[17] Due to the deficiencies of the KORD system a new computer system was developed for the last launch, vehicle 7L, called the S-530. It was the first Soviet digital guidance and control system.[18] The telemetry system relayed data back at an estimated rate of 9.6 gigabytes per second on 320,000 channels on 14 frequencies. Commands could be sent to an ascending N1 at the same rate.[19]

[Bricket]

41
But seriously: who wants some Thierry?

[Aveq]

42


oke

[Brisky]

43

Can we get an example of this Thierry?

[Momma Bird]

44


Hello Aveq, welcome

[Brisky]

45

At 105 meters (344 ft), the N1-L3 was slightly shorter and more slender overall, than the American Apollo-Saturn V (111 meters, 363 ft), but wider at the base (17 m/56 ft vs. 10 m/33 ft). The N1 produced more thrust in each of its three stages than the Saturn V. It also produced more total impulse in its first four stages than the Saturn V did in its three (see table below).

The N1 was intended to place the ≈95 t (209,000 lb) L3 payload into low Earth orbit,[20] whereas the Saturn V placed the roughly 45 t (100,000 lb) Apollo spacecraft, plus 74.4 t (164,100 lb) of fuel for translunar injection, into Earth parking orbit. L3 translunar injection of a 23.5 t (52,000 lb) payload was to be provided by the fourth stage. The N1-L3 would have been able to convert only 9.3% of its three-stage total impulse into Earth orbit payload momentum (compared to 12.14% for the Saturn V), and only 3.1% of its four-stage total impulse into translunar payload momentum, compared to 6.2% for the Saturn V.

The N1-L3 used only kerosene-based rocket fuel in all three of its stages, while the Saturn V used liquid hydrogen to fuel its second and third stages, which yielded an overall performance advantage due to the higher specific impulse. The N1 also wasted available propellant volume by using spherical propellant tanks under its conical-shaped external skin, while the Saturn V used most of its available cylindrical skin volume to house capsule-shaped hydrogen and oxygen tanks, with common bulkheads between the tanks in the second and third stages.

The Saturn V also had a superior reliability record: it never lost a payload in two development and eleven operational launches, while four N1 development launch attempts all resulted in failure, with two payload losses.

[Aveq]

46


Thank you for the welcome

[Bricket]

47
Here is some Thierry


Also: Welcome Aveq

[Brisky]

48

    Apollo-Saturn V[21]    N1-L3
Diameter, maximum    10 m (33 ft)    17 m (56 ft)
Height w/ payload    111 m (363 ft)    105 m (344 ft)
Gross weight    2,938 t (6,478,000 lb)    2,750 t (6,060,000 lb)[12]
First stage    S-IC    Block A
Thrust, SL    33,000 kN (7,500,000 lbf)    45,400 kN (10,200,000 lbf)[12][13]
Burn time    168 seconds    125 seconds
Second stage    S-II    Block B
Thrust, vac    5,141 kN (1,155,800 lbf)    14,040 kN (3,160,000 lbf)
Burn time    384 seconds    120 seconds
Orbital insertion stage    S-IVB (burn 1)    Block V
Thrust, vac    901 kN (202,600 lbf)    1,610 kN (360,000 lbf)
Burn time    147 seconds    370 seconds
Total impulse[Note 1]    7,711,000 kilonewton·seconds (1,733,600,000 pound·seconds)    7,956,000 kilonewton·seconds (1,789,000,000 pound·seconds)
Orbital payload    120,200 kg (264,900 lb)[Note 2]    95,000 kg (209,000 lb)
Injection velocity    7,793 m/s (25,568 ft/s)    7,793 m/s (25,570 ft/s)[Note 3]
Payload momentum    936,300,000 kilogram·meters per second (210,500,000 slug·feet per second)    740,300,000 kilogram·meters per second (166,440,000 slug·feet per second)
Propulsive efficiency    12.14%    9.31%
Earth departure stage    S-IVB (burn 2)    Block G
Thrust, vac    895 kN (201,100 lbf)    446 kN (100,000 lbf)
Burn time    347 seconds    443 seconds
Total impulse[Note 1]    8,022,000 kilonewton·seconds (1,803,400,000 pound·seconds)    8,153,000 kilonewton·seconds (1,833,000,000 pound·seconds)
Translunar payload    45,690 kg (100,740 lb)    23,500 kg (51,800 lb)
Injection velocity    10,834 m/s (35,545 ft/s)    10,834 m/s (35,540 ft/s)[Note 3]
Payload momentum    495,000,000 kilogram·meters per second (111,290,000 slug·feet per second)    254,600,000 kilogram·meters per second (57,240,000 slug·feet per second)
Propulsive efficiency    6.17%    3.12%

[Aveq]

49


Nearly a half century

[Emtile]

50

I want some Thierry pie now.

[Bricket]

51
Thierry is the best

[Aveq]

52


No idea what you all mean

[Brisky]

53

Complex plumbing was needed to feed fuel and oxidizer into the clustered arrangement of rocket engines. This proved to be extremely fragile, and was a major factor in the design's launch failures. Furthermore, the N1's Baikonur launch complex could not be reached by heavy barge. To allow transport by rail, all the stages had to be broken down and re-assembled. The engines for Block A were only test-fired individually and the entire cluster of 30 engines was never static test fired as a unit. Sergei Khrushchev stated that only two out of every batch of six engines were tested, and not the units actually intended for use in the booster. The reason for this was that the NK-15 engines had a number of valves that were activated by pyrotechnics rather than hydraulic or mechanical means, this being a weight-saving measure. Once shut, the valves could not be re-opened.^[22] As a result, the complex and destructive vibrational modes (which ripped apart propellant lines and turbines) as well as exhaust plume and fluid dynamic problems (causing vehicle roll, vacuum cavitation, and other problems) in Block A were not discovered and worked out before flight.^[23] Blocks B and V were static test fired as complete units.
Because of its technical difficulties and lack of funding for full-up testing the N1 never completed a test flight. All four uncrewed launches out of 12 planned tests ended in failure, each before first-stage separation. The longest flight lasted 107 seconds, just before first-stage separation. Two test launches occurred in 1969, one in 1971, and the final one in 1972.