Design and Analysis of Aerospike Nozzle to Improve Thrust in Hybrid Rocket Engine
|International Journal of Engineering Trends and Technology (IJETT)||
|© 2016 by IJETT Journal|
|Year of Publication : 2016|
|Authors : T.Karthikeyan, S.K.Aravindhkumar, J.Arun Kumar
|DOI : 10.14445/22315381/IJETT-V36P265|
T.Karthikeyan, S.K.Aravindhkumar, J.Arun Kumar"Design and Analysis of Aerospike Nozzle to Improve Thrust in Hybrid Rocket Engine", International Journal of Engineering Trends and Technology (IJETT), V36(7),347-351 June 2016. ISSN:2231-5381. www.ijettjournal.org. published by seventh sense research group
The Present Computational Analysis deal with improvement of momentum distribution of the high- temperature exhaust in Rocket Engine through change in profile of aero spike nozzle. Due to change of profile we can improve thrust and mass flow rate of exhaust gas. This analysis is done by using Fluent (ANSYS) on modified profile of Aero spike nozzle. The Comparison has been done with respect to mass flow rate, velocity streamline and vector between unmodified and modified profile. This Profile modification has done on basic aero spike nozzle and this CAD Model designed by CATIA V5.It has been analyzed that due to change profile in exist nozzle area. The new has improved mass flow rate of exhaust gas and also reduced non –uniform exhaust flow.
 Aerospike nozzle contour design and its performance validation Chang-Hui Wang?, Yu Liu, Li-Zi Qin403 Teaching and Research Section, Beijing University of Aeronautics and Astronautics, 100083 Beijing, People’s Republic of China
 MULTIDISCIPLINARY APPROACH TO LINEAR AEROSPIKE NOZZLE OPTIMIZATION J. J. Korte*, A.O. Salast, H.J. Dunn?, and N.M. Alexandrov P NASA Langley Research Center, Hampton, Virginia 23681
 Development of a Reusable Aerospike Nozzle for Hybrid Rocket Motors Patrick Lemieux1 California Polytechnic State University, San Luis Obispo, CA, 93407
 Flight Research of an Aerospike Nozzle Using High Power Solid Rockets Trong T. Bui* and James E. Murray NASA Dryden Flight Research Center, Edwards, CA, 93523 Charles E. Rogers Air Force Flight Test Center, Edwards Air Force Base, CA, 93523 Scott Bartel§ blacksky Corporation, Carlsbad, CA, 92008 and Anthony Cesaroni** and Mike Dennett Cesaroni Technology/Cesaroni Aerospace, Sarasota, FL, 34243
 NUMERICAL ANALYSIS OF AERO-SPIKE NOZZLE FOR SPIKE LENGTH OPTIMIZATION SANOOB S N1, PRINCE MG2 & SUNDAR B3 1Research Scholar, MES College of Engineering, Kuttipuram, Malappuram, Kerala, India 2Assistant Professor, MES College of Engineering, Kuttipuram, Malappuram, Kerala, India 3Deputy Head, VSSC, ISRO, Kerala, India
 Aerospike Engines for Nanosat and Small Launch Vehicles (NLV/SLV) Eric Besnard* California State University, Long Beach, CA, 90840 and John Garvey† Garvey Spacecraft Corporation, Huntington Beach, CA 92649
 THRUST FORCE ANALYSIS OF SPIKE BELL NOZZLE V.GOPALA DEVA KOWSIK1, CHRIS JOSEPH2, M.P.ARUN JUSTIN3, R.SAINATH4, D.THANIKAIVEL MURUGAN5, S.ILAKKIYA6 1to4: UG Students, 5&6: Assistant Professor Department of Aeronautical Engineering, Jeppiaar Engineering College, Chennai – 600119.
 Hybrid propulsion: an overview of the Onera activities JérômeAnthoine and Michel Prévost ONERA – The French Aerospace Lab 31410 Mauzac, France
RECENT ADVANCES IN HYBRID PROPULSION1Brian Cantwell,?ArifKarabeyoglu, & David Altman StanfordUniversity, Stanford,California 94305,USAand Space Propulsion Group, Incorporated ,Sunnyvale, California 94085,USA
 Numerical Modeling of Pressure drop due to Single - phase Flow of Water and Two - phase Flow of Air - water Mixtures through Thick Orifices- Manmatha K. Roul , Sukanta K. Dash. "Numerical Modeling of Pressure drop due to Single - phase Flow of Water and Two - phase Flow of Air - water Mixtures through Thick Orifices". International Journal of Engineering Trends and Technology (IJETT).
 Design Optimization and Analysis of Rocket Structure for Aerospace Applications- Anoop Thankachen, Santosh kumar"Design Optimization and Analysis of Rocket Structure for Aerospace Applications", International Journal of Engineering Trends and Technology (IJETT), V24(6),286-291 June 2015. ISSN:2231-5381.
Aero spike, Mass flow rate, Velocity streamline, Velocity vector, Flow analysis.