Wikipedia:WikiProject Launch vehicles

{{Infobox Aircraft
 |name=Boeing LGM-25 Minuteman
 |image=Image:Minuteman3launch.jpg
 |caption=The launch of a Minuteman III.
 |type=[[Intercontinental ballistic missile]]
 |manufacturer=[[Boeing]]
 |designer=
 |first flight=
 |introduced=1960
 |retired=
 |status=
 |primary user=[[United States Air Force]]
 |more users=
 |produced=
 |number built=
 |unit cost=US$7 million
 |variants with their own articles=
}}

==Specifications (LGM-25A)==
{{rocket specifications
 |length main=59 ft
 |length alt=18 m
 |diameter main=5 ft 5.7 in
 |diameter alt=1.67 m
 |empty mass main=<!-- lb-->
 |empty mass alt=<!-- kg-->
 |launch mass main=71,000 lb
 |launch mass alt=32,000 kg

 |stage1=1× [[Thiokol]] solid-propellant rocket
  |thrust1 main= lbf
  |thrust1 alt= kN
 |stage2=1× [[Aerojet-General]] solid-propellant rocket
  |thrust2 main= lbf
  |thrust2 alt= kN
 |stage3=1× [[United Technologies]] Chemical Systems Division solid-propellant rocket
  |thrust3 main= lbf
  |thrust3 alt= kN

 |guidance=Inertial
 |launch platform=[[Missile silo]]

 |speed main=15,000 mph
 |speed alt=24,000 km/h
 |altitude main=696 mi
 |altitude alt=1,120 km
 |range main=6,200 mi
 |range alt=10,000 km

 |warhead=nuclear
 |fuzes=n/a
}}

Specifications (LGM-25A)

General characteristics

• Length: 59 ft (18 m)
• Diameter: 5 ft 5.7 in (1.67 m)
• Launch mass: 71,000 lb (32,000 kg)

Engine

• First stage: 1× Thiokol solid-propellant rocket
  • Thrust: lbf (kN)
• Second stage: 1× Aerojet-General solid-propellant rocket
  • Thrust: lbf (kN)
• Third stage: 1× United Technologies Chemical Systems Division solid-propellant rocket
  • Thrust: lbf (kN)

Technical information

• Guidance: Inertial
• Launch platform: Missile silo

Performance

• Cruise speed: 15,000 mph (24,000 km/h)
• Operating altitude: 696 mi (1,120 km)
• Range: 6,200 mi (10,000 km)

Warhead

• Warhead: nuclear
• Fuzes: n/a

==Specifications==
{{rocket specifications
 |crew=3
 |length main=364 ft
 |length alt=111 m
 |diameter main=33 ft
 |diameter alt=10 m
 |empty mass main=<!-- lb-->
 |empty mass alt=<!-- kg-->
 |launch mass main=6,699,000 lb
 |launch mass alt=3,039,000 kg
 |payload to LEO main=260,000 lb
 |payload to LEO alt=118,000 kg
 |payload to moon main=104,000 lb
 |payload to moon alt=47,000 kg

 |stage1 name=First stage (S-IC)
 |stage1=5× [[F-1 (rocket engine)|Rocketdyne F-1]]
  |thrust1 main=7,648,000 lbf
  |thrust1 alt=34.02 MN
  |burn time1=150 s
  |fuel1=[[RP-1]] and [[liquid oxygen]]
 |stage2 name=Second stage (S-II)
 |stage2=5× [[J-2 (rocket engine)|Rocketdyne J-2]]
  |thrust2 main=1,000,000 lbf
  |thrust2 alt=5 MN
  |burn time2=360 s
  |fuel2=[[Liquid hydrogen]] and liquid oxygen
 |stage3=1× Rocketdyne J-2
  |thrust3 main=230,000 lbf
  |thrust3 alt=1 MN
  |burn time3=<br/>
*** '''First burn:''' 165 s
*** '''Second burn:''' 335 s
  |fuel3=Liquid hydrogen and liquid oxygen

 |guidance=
 |launch platform=

 |speed main=<!-- mph-->
 |speed alt=<!-- km/h-->
 |altitude main=<!-- ft-->
 |altitude alt=<!-- m-->
 |range main=<!-- mi-->
 |range alt=<!-- km-->

}}

Specifications

General characteristics

• Crew: 3
• Length: 364 ft (111 m)
• Diameter: 33 ft (10 m)
• Launch mass: 6,699,000 lb (3,039,000 kg)
• Payload:
  • To low Earth orbit: 260,000 lb (118,000 kg)
  • To the Moon: 104,000 lb (47,000 kg)

Engine

• First stage (S-IC): 5× Rocketdyne F-1
  • Thrust: 7,648,000 lbf (34.02 MN)
  • Burn time: 150 s
  • Fuel: RP-1 and liquid oxygen
• Second stage (S-II): 5× Rocketdyne J-2
  • Thrust: 1,000,000 lbf (5 MN)
  • Burn time: 360 s
  • Fuel: Liquid hydrogen and liquid oxygen
• Third stage: 1× Rocketdyne J-2
  • Thrust: 230,000 lbf (1 MN)
  • Burn time:
    
    • First burn: 165 s
    • Second burn: 335 s
  • Fuel: Liquid hydrogen and liquid oxygen