A5035437273- Rocket and propulsion systems research
- Energetic Materials and Combustion
- Combustion and Detonation Processes
- Thermal and Kinetic Analysis
- Spacecraft and Cryogenic Technologies
- Aerospace Engineering and Control Systems
- Advanced Combustion Engine Technologies
- Ranque-Hilsch vortex tube
- Electromagnetic Launch and Propulsion Technology
- Combustion and flame dynamics
- Bat Biology and Ecology Studies
- High-Velocity Impact and Material Behavior
- Advanced Thermoelectric Materials and Devices
- Catalytic Processes in Materials Science
- Advanced Battery Technologies Research
- Mechanical Engineering and Vibrations Research
- Advanced Thermodynamics and Statistical Mechanics
- Advancements in Solid Oxide Fuel Cells
- Polymer Nanocomposites and Properties
- Gas Dynamics and Kinetic Theory
- Flame retardant materials and properties
- Real-time simulation and control systems
- Fuel Cells and Related Materials
- Thermal Radiation and Cooling Technologies
- Powder Metallurgy Techniques and Materials
University of Pittsburgh
2025
Indian Institute of Technology Madras
2016-2025
Birla Institute of Technology, Mesra
2016
Acharya N. G. Ranga Agricultural University
2010
Indian Institute of Science Bangalore
2002-2009
Kyungpook National University
2005
Central College
1950-1977
Bangalore University
1967
University of Delhi
1967
National Centre for Biological Sciences
1949
Alzheimer's disease (AD) diagnosis relies on the presence of extracellular β-amyloid (Aβ) and intracellular hyperphosphorylated tau (p-tau). Emerging evidence suggests a potential link between AD pathologies infectious agents, with herpes simplex virus 1 (HSV-1) being leading candidate. Our investigation, using metagenomics, mass spectrometry, western blotting, decrowding expansion pathology, detects HSV-1-associated proteins in human brain samples. Expression herpesvirus protein ICP27...
Components of solid rocket motor that are susceptible to ageing propellant, insulator, inhibitor, interfaces, igniter system, and seals. Seals, ignition systems replaceable but the would be recast when deterioration in propellant liner beyond specified limits due ageing. There is a large body literature available on composite each focusing only particular type propellants rather than having synergistic view various different processes hence looks disconnected. Further, there few studies...
Abstract A fuel for the hybrid rocket system was developed. The attempts made to improve mechanical properties of wax by adding EVA (ethylene vinyl acetate) are illustrated. It observed that obtained were dependent on process curing specimen. proprietary method specimen established. percentage elongation with 20 % and 80 around 17 %, which much higher than values pure (4 %). from study content in was, better were. Regression rate studies combination carried out. regression decreased upon...
Abstract The current emphasis in aerospace component development is on creating safe, reliable and cost-effective technologies. However, the intricate design of stage separation systems renders reliability a critical factor determining mission success or failure. One technical challenges involves various mechanisms, such as payload separation, heavy propulsion system ejection auxiliary components detachment rigid components. These mechanisms commonly employ pyrotechnic devices, which, by...
In solid propellant rocket motors, the design of grain port geometry primarily dictates motor ballistic performance. The flexibility offered by spatial variation shape on performance is often discounted due to requirement complex mandrel shapes along with their associated manufacturing issues coupled processing constraints. Literature data indicate improvement in volumetric loading and stability planned distribution burn surface area length. This paper deals realization testing a subscale...
In this paper, an attempt is made to increase the regression rate of hybrid fuel (paraffin wax) using a hemispherical bluff body placed near head end motor. The oxidizer used for present study gaseous oxygen. results show that use increases by around two times at higher and three four lower . This in diminishes as motor increased from 9 27, whilst still being than case without body. was seen even port diameter, which initial diameter 15 mm. nearly constant with body, it 1.5 2 during...
This article explores the throttling aspect of hybrid rocket motor through experiments using a lab-scale motor. The utilizes wax-Al based fuel and compressed air as oxidizer. oxidizer flow rate was modulated PID controller to study closed-loop thrust control performance Numerical simulations cold tests were carried out identify suitable gains for algorithm. Pressure feedback used in algorithm obtain control. resultant system followed reference pressure accurately during step input response...
Burn rate is a vital parameter of propellant that highly influences the internal ballistics rocket motor. In case military applications solid motors, they are stored for long duration, during which their performance deteriorates considerably due to aging. Conventionally, accelerated isothermal technique used studying effects However, in actual storage conditions, temperature experienced by varies over time. present work, experimental investigations were carried out using cyclic and aging...
This paper proposes the use of micron-sized aluminum (pyral, average particle size ) with a higher specific surface area as good candidate to enhance burn rate composite propellant. Experiments were performed in pressure range 10 70 bar window bomb for measuring rate. Comparison these results those obtained using micron- and nanosized found that performance pyral was between aluminum. The reason high rates observed is due flake like appearance large area. It argued that, if large, then...
The measurement of the regression rate a hybrid rocket fuel is subject matter this paper. This an involved problem because both and oxidizer mass flux vary with port diameter, which itself varies during combustion. paper addresses issue how should be varied to obtain correctly. most commonly used weight loss method has been employed here. Three methods here are artificially changing flow oxidizer, interrupted burn test. From experiments conducted, it was evident that test best method. These...