Juno II

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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
[edit on Wikidata]

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.^{[1][2][3][4][5][6][7][8]}