Encyclopedia Astronautica
Iris-0


Solid rocket stage. 84.00 kN (18,884 lbf) thrust. Mass 100 kg (220 lb).

No Engines: 7.

Status: Retired 1968.
Gross mass: 100 kg (220 lb).
Unfuelled mass: 59 kg (130 lb).
Height: 0.80 m (2.62 ft).
Diameter: 0.30 m (0.98 ft).
Thrust: 84.00 kN (18,883 lbf).
Burn time: 0.80 s.

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Associated Countries
Associated Engines
Associated Launch Vehicles
  • Iris American sounding rocket. Sounding rocket developed by Navy, then handed over to NASA. Flown only four times, but then used in unique Hydra-Iris test series. More...

Associated Manufacturers and Agencies
  • USN American agency overseeing development of rockets, spacecraft, and rocket engines. USN Joint Task Force 7, USA. More...

Associated Propellants
  • Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...

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