From Wikipedia, the free encyclopedia

Saturn A-1
FunctionUncrewed launch vehicle
ManufacturerVon Braun
Country of originUnited States
Size
Height49.62 m (162.29 ft)
Diameter6.52 m (21.39 ft)
Mass524,484 kg
Stages3 (all used on various vehicles, now retired)
Capacity
Payload to low Earth orbit
Mass13,600 kg (30,000 lb)
for LEO
Launch history
StatusNever flown
Launch sitesN/A
First stage - S-I
Engines8 H-1
Thrust7,582 kN
Burn time150 seconds
Propellant RP-1/ LOX
Second stage Titan I
Engines2 LR-87-3
Thrust1,467 kN
Burn time138 seconds
PropellantRP-1/LOX
Third stage - Centaur C
Engines2 RL-10A-1
Thrust133 kN
Burn time430 seconds
Propellant LH2 / LOX

Saturn A-1, studied in 1959, was projected to be the first version of Saturn I and was to be used if necessary before the S-IV liquid hydrogen second stage became available. [1]

It was designed as a three stage vehicle. The S-I first stage (initially proposed for the Juno V rocket and eventually used on Saturn I) would propel the Saturn A-1 into space, continuing the flight with a Titan I [2]: 3–6  missile based second stage. Finally a Centaur [2]: 3–6  C high-energy double-engine third stage could send a payload into its final Earth orbit or to other planets.

The Saturn A-1 never flew, but all proposed stages were used on different launch vehicles. Today, they are all retired.

See also

References

  1. ^ "Saturn A-1". November 14, 2016. Archived from the original on November 14, 2016. Retrieved May 27, 2024.
  2. ^ a b Lunar Exploration with Saturn-Boosted Systems (PDF) (Technical report). Army Ballistic Missile Agency. October 1, 1959. Archived (PDF) from the original on May 31, 2023. Retrieved May 31, 2023.
From Wikipedia, the free encyclopedia

Saturn A-1
FunctionUncrewed launch vehicle
ManufacturerVon Braun
Country of originUnited States
Size
Height49.62 m (162.29 ft)
Diameter6.52 m (21.39 ft)
Mass524,484 kg
Stages3 (all used on various vehicles, now retired)
Capacity
Payload to low Earth orbit
Mass13,600 kg (30,000 lb)
for LEO
Launch history
StatusNever flown
Launch sitesN/A
First stage - S-I
Engines8 H-1
Thrust7,582 kN
Burn time150 seconds
Propellant RP-1/ LOX
Second stage Titan I
Engines2 LR-87-3
Thrust1,467 kN
Burn time138 seconds
PropellantRP-1/LOX
Third stage - Centaur C
Engines2 RL-10A-1
Thrust133 kN
Burn time430 seconds
Propellant LH2 / LOX

Saturn A-1, studied in 1959, was projected to be the first version of Saturn I and was to be used if necessary before the S-IV liquid hydrogen second stage became available. [1]

It was designed as a three stage vehicle. The S-I first stage (initially proposed for the Juno V rocket and eventually used on Saturn I) would propel the Saturn A-1 into space, continuing the flight with a Titan I [2]: 3–6  missile based second stage. Finally a Centaur [2]: 3–6  C high-energy double-engine third stage could send a payload into its final Earth orbit or to other planets.

The Saturn A-1 never flew, but all proposed stages were used on different launch vehicles. Today, they are all retired.

See also

References

  1. ^ "Saturn A-1". November 14, 2016. Archived from the original on November 14, 2016. Retrieved May 27, 2024.
  2. ^ a b Lunar Exploration with Saturn-Boosted Systems (PDF) (Technical report). Army Ballistic Missile Agency. October 1, 1959. Archived (PDF) from the original on May 31, 2023. Retrieved May 31, 2023.

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