Juno II
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.
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$25.4 million (2018) |
| 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 |
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