Juno II
Juno II on pad | |
| Function | Expendable launch system |
|---|---|
| Manufacturer | Chrysler for ABMA |
| Country of origin | United States |
| Cost per launch | US$2.9 million (1958), US$31.5 million (2024) |
| Size | |
| Height | 24.0 m (78.7 ft) |
| Diameter | 2.67 m (8 ft 9 in) |
| Mass | 55,110 kg (121,500 lb) |
| Stages | 3-4 |
| Capacity | |
| Payload to Low Earth orbit | |
| Mass | 41 kg (90 lb) |
| Payload to Sub-orbital TLI | |
| Mass | 6 kg (13 lb) |
| Associated rockets | |
| Family | Jupiter |
| Launch history | |
| Status | Retired |
| Launch sites | LC-5 and LC-26B, CCAFS |
| Total launches | 10 |
| Success(es) | 4 |
| Failure(s) | 5 |
| Partial failure(s) | 1 |
| First flight | 6 December 1958 |
| Last flight | 24 May 1961 |
| First stage - Jupiter | |
| Engines | 1x Rocketdyne S-3D |
| Thrust | 667 kN (150,000 lbf) |
| Specific impulse | 248 seconds |
| Burn time | 182 seconds |
| Propellant | RP-1 / LOX |
| Second stage MGM-29 Sergeant | |
| Engines | 11 Solid |
| Thrust | 74.8 kN (16,800 lbf) |
| Specific impulse | 220 seconds |
| Burn time | 6 seconds |
| Propellant | Solid - Polysulfide-aluminum and ammonium perchlorate |
| Third stage - MGM-29 Sergeant | |
| Engines | 3 Solid |
| Thrust | 20.4 kN (4,600 lbf) |
| Specific impulse | 236 seconds |
| Burn time | 6 seconds |
| Propellant | Solid - Polysulfide-aluminum and ammonium perchlorate |
| Fourth stage - MGM-29 Sergeant | |
| Engines | 1 Solid |
| Thrust | 6.8 kN (1,500 lbf) |
| Specific impulse | 249 seconds |
| Burn time | 6 seconds |
| Propellant | Solid - Polysulfide-aluminum and ammonium perchlorate |
Juno II was an American space launch vehicle used during the late 1950s and early 1960s. It was derived from the Jupiter missile, which was used as the first stage.