Dragon (rocket)

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Dragon
Country of originFrance[1]
Applicationhigh altitude research
sounding rocket[2]

The Dragon is a two-stage French solid propellant[3] sounding rocket used for high altitude research.[4][5]

The dragon's first stage was a (diameter 56 cm) which burned 675 kg of fuel in 16 seconds and so produced a maximum thrust of 88 kN. A Bélier engine was used as the upper stage. It belonged thereby to a family of solid-propellant rockets derived from the Bélier, including the Centaure, the Dauphin and the Éridan. A payload of 30 to 120 kg could be carried on parabolic with apogees between 440 km (270 mi) (Dragon 2B)[6] and 560 km (340 mi)(Dragon III)[7] The Dragon was built in several versions including the Dragon-2B,[6] and Dragon-3,[7] Dragons have been launched from Andøya, Norway; Biscarrosse, France; Dumont d'Urville, Antarctica; Chamical, Argentina;[failed verification] CIEES in Hammaguir, Algeria; Kerguelen Islands; Kourou, French Guiana; Mar Chiquita, Argentina; Salto di Quirra, Sardinia; Sonmiani, Pakistan; Thumba, India; and Vík í Mýrdal, Iceland.[8]

References[]

  1. ^ United States. National Aeronautics and Space Administration (1965). Semiannual Report to the Congress. The Administration.
  2. ^ STAR. NASA, Office of Scientific and Technical Information. 1967.
  3. ^ United States. Department of the Army (1975). Your Army: 200 Years. U.S. Government Printing Office.
  4. ^ "Dragon 1". Encyclopedia Astronautica. Archived from the original on December 3, 2013. Retrieved August 11, 2015.
  5. ^ "France Fires Rocket". The Gazette. Montreal, QC. Reuters. April 2, 1968. p. 2. Retrieved July 15, 2015.
  6. ^ a b "Dragon 2B". Encyclopedia Astronautica. Archived from the original on December 3, 2013. Retrieved August 11, 2015.
  7. ^ a b "Dragon 3". Encyclopedia Astronautica. Archived from the original on November 8, 2013. Retrieved August 5, 2015.
  8. ^ "Overview of rocket launch sites worldwide". Encyclopedia Astronautica. Archived from the original on July 8, 2002. Retrieved August 11, 2015.
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