SM-65C Atlas
Atlas C awaiting launch (USAF) | |
| Function | Prototype ICBM |
|---|---|
| Manufacturer | Convair |
| Country of origin | United States |
| Launch history | |
| Status | Retired |
| Launch sites | LC-12, CCAFS |
| Total launches | 6 |
| Success(es) | 3 |
| Failure(s) | 3 |
| First flight | 24 December 1958 |
| Last flight | 24 August 1959 |
| Boosters | |
| No. boosters | 1 |
| Powered by | 2 XLR-89-5 |
| Total thrust | 341,130 lbf (1,517.4 kN) |
| Specific impulse | 282 s |
| Burn time | 135 s |
| Propellant | RP-1/LOX |
| First stage | |
| Powered by | 1 XLR-105-5 |
| Maximum thrust | 81,655 lbf (363.22 kN) |
| Specific impulse | 309 s |
| Burn time | 240 s |
| Propellant | RP-1/LOX |
The SM-65C Atlas, or Atlas C was a prototype of the Atlas missile. First flown on 24 December 1958, the Atlas C was the final development version of the Atlas rocket, prior to the operational Atlas D. It was originally planned to be used as the first stage of the Atlas-Able rocket, but following an explosion during a static test on 24 September 1959, this was abandoned in favor of the Atlas D. Atlas C was similar to Atlas B, but had a larger LOX tank and smaller RP-1 tank due to technical changes to the Rocketdyne engines. Improvements in materials and manufacturing processes also resulted in lighter-weight components than the Atlas A and B. Booster burn time was much longer than the A/B series, up to 151 seconds. All launches took place from LC-12 at CCAS.