Encyclopedia Astronautica
HJ Nike Nike Recruit


American test vehicle. Four stage vehicle consisting of 1 x M-6 + 1 x Nike + 1 x Nike + 1 x Recruit

Status: Retired 1960.
Gross mass: 1,300 kg (2,800 lb).
Height: 10.00 m (32.00 ft).
Diameter: 0.58 m (1.90 ft).
Thrust: 365.00 kN (82,055 lbf).
Apogee: 30 km (18 mi).
First Launch: 1958.10.06.
Last Launch: 1960.08.03.
Number: 5 .

More... - Chronology...


Associated Countries
See also
  • Honest John Unguided single-stage solid-propellant US Army missile developed by Douglas Aircraft. It was later used as the booster stage for a range of sounding rockets, test vehicles, and targets. More...
  • Honest John Unguided single-stage solid-propellant US Army missile developed by Douglas Aircraft. It was later used as the booster stage for a range of sounding rockets, test vehicles, and targets. More...

Associated Manufacturers and Agencies
  • NASA Langley American agency overseeing development of rockets and spacecraft. Langley, USA. More...
  • NASA Langley American agency overseeing development of rockets and spacecraft. Langley, USA. More...

Associated Launch Sites
  • Wallops Island Small NASA launch site for sounding rocket launches and occasional Scout launches to orbit. Air launches are conducted from the Drop Zone Wallops Island, 37.00 N 72.0 W. With the last orbital launch in 1985 and the decline in sounding rocket launches, Wallops fell into near-disuse as a launch center. Its fortunes revised with the establishment of Mid-Atlantic Regional Spaceport in 2005 and orbital launches resumed in 2010. More...
  • Wallops Island Small NASA launch site for sounding rocket launches and occasional Scout launches to orbit. Air launches are conducted from the Drop Zone Wallops Island, 37.00 N 72.0 W. With the last orbital launch in 1985 and the decline in sounding rocket launches, Wallops fell into near-disuse as a launch center. Its fortunes revised with the establishment of Mid-Atlantic Regional Spaceport in 2005 and orbital launches resumed in 2010. More...

Associated Stages
  • HJ Nike-1 Solid propellant rocket stage. Loaded/empty mass 1,900/954 kg. Thrust 365.00 kN. Rocket motor originally developed for the Army Honest John tactical missile. In sounding rocket applications the interstage adapter was bolted to the front of the Taurus and consisted of a conical shaped adapter which slip-fit into the second stage nozzle, thus providing for drag separation at Taurus burnout. Each Taurus fin was 0.46 square meters in area. Normally, the fins were canted to provide a two revolutions per second spin rate at Taurus burnout. The weight of the booster system is 3005 pounds. More...
  • HJ Nike Nike-3 Solid propellant rocket stage. Loaded/empty mass 599/256 kg. Thrust 195.60 kN. Vacuum specific impulse 195 seconds. The average sea level thrust of the Nike rocket motor was 190.3 kN. The interstage adapter was bolted to the front of the Nike and consisted of a conical shaped adapter which slip-fit into the second stage nozzle, thus providing for drag separation at Nike burnout. Each Nike fin was 0.45 square meters in area. Normally, the fins were canted to provide a two revolutions per second spin rate at Nike burnout. More...
  • HJ Nike-1 Solid propellant rocket stage. Loaded/empty mass 1,900/954 kg. Thrust 365.00 kN. Rocket motor originally developed for the Army Honest John tactical missile. In sounding rocket applications the interstage adapter was bolted to the front of the Taurus and consisted of a conical shaped adapter which slip-fit into the second stage nozzle, thus providing for drag separation at Taurus burnout. Each Taurus fin was 0.46 square meters in area. Normally, the fins were canted to provide a two revolutions per second spin rate at Taurus burnout. The weight of the booster system is 3005 pounds. More...
  • HJ Nike Nike-3 Solid propellant rocket stage. Loaded/empty mass 599/256 kg. Thrust 195.60 kN. Vacuum specific impulse 195 seconds. The average sea level thrust of the Nike rocket motor was 190.3 kN. The interstage adapter was bolted to the front of the Nike and consisted of a conical shaped adapter which slip-fit into the second stage nozzle, thus providing for drag separation at Nike burnout. Each Nike fin was 0.45 square meters in area. Normally, the fins were canted to provide a two revolutions per second spin rate at Nike burnout. More...

HJ Nike Nike Recruit Chronology


1958 October 6 - . Launch Site: Wallops Island. LV Family: Honest John. Launch Vehicle: HJ Nike Nike Recruit.
  • Polaris Re-entry Vehicle test - . Nation: USA. Agency: USN. Apogee: 26 km (16 mi).

1958 December 1 - . Launch Site: Wallops Island. LV Family: Honest John. Launch Vehicle: HJ Nike Nike Recruit.
  • Polaris Re-entry Vehicle test - . Nation: USA. Agency: USN. Apogee: 26 km (16 mi).

1959 - . Launch Site: Wallops Island. LV Family: Honest John. Launch Vehicle: HJ Nike Nike Recruit.
  • Polaris Re-entry Vehicle test - . Nation: USA. Agency: USN. Apogee: 26 km (16 mi).

1959 September 9 - . Launch Site: Wallops Island. LV Family: Honest John. Launch Vehicle: HJ Nike Nike Recruit.
  • Mercury model test flight - . Nation: USA. Agency: NASA. Apogee: 10 km (6 mi).

1960 August 3 - . Launch Site: Wallops Island. LV Family: Honest John. Launch Vehicle: HJ Nike Nike Recruit.
  • Glide Rocket Re-entry Vehicle test - . Nation: USA. Agency: NASA Langley. Apogee: 27 km (16 mi).

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