Share

PERFORMANCE OF LIQUID OXYGEN-LIQUID HYDROGEN CRYOGENIC PROPELLANT SYSTEM IN HIGH ENERGY ROCKET PROPULSION.

Author(s) : AIYAPPAN-PILLAI M., GHOSH S. C., NAMBOODRY E. V. S.

Type of article: Article

Summary

THE COMBINATION OF LIQUID OXYGEN WITH LIQUID HYDROGEN IS WIDELY USED TODAY IN SATELLITE LAUNCH VEHICLES. THE INDEX OF PERFORMANCE FOR THIS COMBINATION IS VERY MUCH HIGHER COMPARED TO THOSE OF SEMICRYOGENIC AND STORABLE PROPELLANTS. IN THE PAPER, THE PERFORMANCE PARAMETERS OF LIQUID OXYGEN-LIQUID HYDROGEN ENGINES ARE THEORETICALLY PREDICTED FOR VARIOUS OPERATING CONDITIONS. ALSO, THE PERFORMANCE CHARACTERISTICS OF VARIOUS LIQUID OXYGEN-LIQUID HYDROGEN ENGINES DEVELOPED BY OTHER COUNTRIES ARE BRIEFLY DEALT WITH.

Details

  • Original title: PERFORMANCE OF LIQUID OXYGEN-LIQUID HYDROGEN CRYOGENIC PROPELLANT SYSTEM IN HIGH ENERGY ROCKET PROPULSION.
  • Record ID : 1987-0048
  • Languages: English
  • Source: Indian J. Cryog. - vol. 10 - n. 4
  • Publication date: 1985
  • Document available for consultation in the library of the IIR headquarters only.

Links


See other articles in this issue (3)
See the source

Indexing