PGM-19 Jupiter
Specifications (Juno II launch vehicle)
The Juno II was a four-stage rocket derived from the Jupiter IRBM. It was used for 10 satellite launches, six of which failed.

PGM-19 Jupiter

Section Title: Specifications (Juno II launch vehicle)
Table Section Text: The Juno II was a four-stage rocket derived from the Jupiter IRBM. It was used for 10 satellite launches, six of which failed.

Parameter	First stage	Second stage	Third stage	Fourth stage

Gross mass	54,431 kg	462 kg	126 kg	42 kg

Empty mass	5,443 kg	231 kg	63 kg	21 kg

Thrust	667 kN	73 kN	20 kN	7 kN

Isp	248 s (2.43 kN·s/kg)	214 s (2.10 kN·s/kg)	214 s (2.10 kN·s/kg)	214 s (2.10 kN·s/kg)

Burn time	182 s	6 s	6 s	6 s

Length	18.28 m	1.0 m	1.0 m	1.0 m

Diameter	2.67 m	1.0 m	0.50 m	0.30 m

Engine:	Rocketdyne S-3D	Eleven Sergeants	Three Sergeants	One Sergeant

Propellant	LOX/RP-1	Solid Fuel	Solid Fuel	Solid fuel

Sentence(s)

PGM-19 Jupiter was a propellant using RP-1 fuel and LOX, with a Rocketdyne (model S-3D) engine producing 667 kN of thrust.

final_sentence: PGM-19 Jupiter was a propellant using RP-1 fuel and LOX, with a Rocketdyne (model S-3D) engine producing 667 kN of thrust.