ePrints@IIScePrints@IISc Home | About | Browse | Latest Additions | Advanced Search | Contact | Help

Spontaneously Igniting Hybrid Fuel-Oxidizer Systems

Jain, SR (1995) Spontaneously Igniting Hybrid Fuel-Oxidizer Systems. In: Defence Science Journal, 45 (1). pp. 5-16.

Full text not available from this repository. (Request a copy)
Official URL: http://publications.drdo.gov.in/ojs/index.php/dsj


After briefly outlining the recent developments in hybrid rockets, the work carried out by the author on self-igniting (hypergolic) solid fuel-liquid oxidiser systems has been reviewed. A major aspect relates to the solid derivatives of hydrazines, which have been conceived as fuels for hybrid rockets. Many of these N-N bonded compounds ignite readily, with very short ignition delays, on coming into contact with liquid oxidisers, like HNO3 and N2O4. The ignition characteristics have been examined as a function of the nature of the functional group in the fuel molecule, in an attempt to establish a basis for the hypergolic ignition in terms of chemical reactivity of the fuel-oxidiser combination. Important chemical reactions occurring in the pre-ignition stage have been identified by examining the quenched reaction products. Hybrid systems exhibiting synergistic hypergolicity in the presence of metal powders have been investigated. An estimation of the rocket performance parameters, experimental determination of the heats of combustion in HNO3, thermal decomposition characteristics, temperature profile by thin film thermometry and and product identification by the rapid scan FT-IR, are among the other relevant studies made on these systems. A significant recent development has been the synthesis of new N-N bonded viscous binders, capable of retaining the hypergolicity of the fuel powders embedded therein as well as providing the required mechanical strength to the grain. Several of these resins have been characterised. Metallised fuel composites of these resins having high loading of magnesium are found to have short ignition delays and high performance parameters.

Item Type: Journal Article
Publication: Defence Science Journal
Publisher: Defence Research & Development Organisation, India
Additional Information: Copyright of this article belongs to Defence Research & Development Organisation, India.
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 26 May 2011 05:57
Last Modified: 26 May 2011 05:57
URI: http://eprints.iisc.ac.in/id/eprint/37915

Actions (login required)

View Item View Item