Name : P A Ramakrishna
Designation : Professor
Email-ID :
Office time : 8 AM to 5 PM
Phone : +91-44-2257 4018
Address : # 223, CTC Building,Department of Aerospace Engineering,IIT Madras, Chennai, 600036
2014 - Present
Department of Aerospace Engineering
2010-2014
Department of Aerospace Engineering
2005-2010
Department of Aerospace Engineering
2003-2005
Department of Aerospace Engineering
2001-2003
Combustion Gasification and Propulsion Laboratory
2003
Department of Aerospace Engineering
1996
Department of Aerospace Engineering
1993
Department of Mechanical Engineering
The setup is used to measure the burn rates of propellants. The current setup can measure burn rates up to pressure of 200 bar. The setup can successfully operate between the temperature range of -35C to +71C. All types of propellants (double base, composite - high burn rate, low burn rate, fuel rich, etc.) can be tested. The setup is capable of meauring burn rate of three samples in one go.
A Solid Fuel Ducted Ramjet (SFRJ) is powered with a Fuel-Rich Propellant (FRP). SFRJ consists of two combustion chambers. The Ramjet test facility has capability of measuring all parameters required for characterization of a SFRJ such as combustion efficiency, thrust, chamber pressure etc.
In the Hybrid Rocket Test Facility available at our lab, one can test the various types of fuel with the gaseous or liquid oxidizers. The hybrid Rocket motor is fixed on a movable thrust stand. The performance parameters such as thrust, combustion chamber pressure etc. can be measured.
This is a flyable platform which is under development. A “piston engine plus propeller” class of flying vehicle .The thrust production is done by 2 stroke 35cc Internal Combustion engine. A lab made control unit is integrated with the vehicle for fight control.
The propulsion system employs water as the oxidizer and generates different thrust under a varying flow rate of water. Therefore, the engine will be useful for underwater propulsion applications. Such a system increases safety as there are no specific requirements to handle water. Additionally, it has an advantage of the oxidizer being readily available.
Development of an active propulsion preferably with the use of ramjet in order to enhance the range.
The setup is used to obtain an extinguished propellant samples by rapid depressurization. The critical depressurization rate of any propellant can be measured. The depressurization rate up to 30000 bar/s can be obtained by varying throat diameter between primary and secondary chambers, which are separated by a mylar sheet diaphragms.
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Under Construction