Indian Missile News And Discussion

[Arun_S]

This pdf is a treasure trove for careful readers.

[url="http://www.drdo.gov.in/drdo/pub/dss/2010/dss2010.pdf"]DRDO SCIENCE SPECTRUM - 2010[/url]



In particular:

[url="http://www.drdo.gov.in/drdo/pub/dss/2010/dss2010.pdf"]Concepts and Modelling of Deterrence for Strategic Thinking - Page 263[/url]

N. K. Jain, Institute for Systems Studies and Analyses, Delhi–110 054



Also here is another one on teh same document:



[url="http://www.drdo.gov.in/drdo/pub/dss/2010/dss2010.pdf"]Successful Demonstration of Design, Development and Testing of Scramjet Combustor for HSTDV Mission of 20 s Duration

C. Chandrasekhar, Defence Research & Development Laboratory, Hyderabad-500 047[/url]

... .. .. . .

Static Testing and Performance Analysis of Scramjet Combustor for 20 s Duration

Successfully demonstrated sustained supersonic combustion of kerosene fuel in the Mach 2 vitiated air flow in the strut based scramjet combustor in the connect-pipe mode test facility using ejector system (i.e., to generate low pressure at the exit of the scramjet combustor) for 20 s test duration. Wall static pressure distribution along the length of the combustor for reacting flow with ejector operation is shown in Fig. 15. The computed thrust obtained is 484 kgf, which is meeting the HSTDV mission requirement.



The most important aspect of this test has been the survivability of the struts after 20 s duration of the test especially Stage-II fuel injection struts. Apart from achieving desired thrust the other important performance measure of success is to achieve steady mass flow rate of kerosene injection from the struts into the combustor for 20 s test duration.

... . .. . . .



1. Designed and developed the scramjet combustor for the Hypersonic Technology Demonstrator Vehicle (HSTDV).



2. Addressed the issues of fabrication to realize the fuel injection struts using Niobium C-103 alloy material and Tungsten alloy material.



3. Established the vitiated air–heater to produce high enthalpy air at 2000 K total temperature and 5 bar total pressure; the flow rate of vitiated air being 4.2 kg/s. This is the workhorse for all combustor tests at DRDL.



4. Successfully carried out 18 static tests of the strut based scramjet combustor, the results of which lead to gaining confidence in the indigenous development of scramjet combustor. The auto-ignition and sustained supersonic combustion have been proved in the connectpipe mode of static tests.



5. Successfully demonstrated sustained supersonic combustion of kerosene fuel in the Mach 2 vitiated air flow in the strut based scramjet combustor in the connect-pipe mode test facility using ejector system (i.e. to generate low pressure at the exit of the scramjet combustor) for 20 s test duration.

484 Kgf and flow rate of 4.2 Kg/s means engine ISP of around 800 to 1,000.