• Sangilipandi M
• S.R.Arun
• Sowbesh. R
• Subash.S
• Thangeshwaran K

A computational tool ready to perform a quick analysis of hybrid rocket engines is presented, describing briefly the mathematical and physical models used. Validation of the code is additionally shown: 16 different static firing tests available within the open literature are accustomed compare measured operational parameters like chamber pressure, thrust, and specific impulse with the code’s output. the aim of the program is to perform rapid evaluation and assessment on a possible first design of hybrid rockets, without wishing on computationally expensive simulations or onerous experimental tests. The validated program considers as benchmark and study case the look of a liquid-oxygen/paraffin hybrid rocket to be used because the upper stage of a small launcher derived from VEGA building blocks. A full-factorial parametric analysis is performed for both pressure-fed and pump-fed systems to search out a configuration that delivers the equivalent total impulse of a VEGA-like launcher third and fourth stage as a primary evaluation. This parametric analysis is additionally useful to focus on how the oxidizer injection system, the fuel grain design, and also the nozzle features affect the performance of the rocket.

Hybrid Rocket, paraffin, oxidizer injection system, pressure fed, pump-fed systems etc.

"DESIGN AND ANALYSIS OF HYBRID ROCKET ENGINE TEST FIRE BY USING HONEY COMB PARAFFIN WAX", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.9, Issue 5, page no.b775-b783, May-2022, Available :http://www.jetir.org/papers/JETIR2205205.pdf

"DESIGN AND ANALYSIS OF HYBRID ROCKET ENGINE TEST FIRE BY USING HONEY COMB PARAFFIN WAX", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.9, Issue 5, page no. ppb775-b783, May-2022, Available at : http://www.jetir.org/papers/JETIR2205205.pdf