• R.D.V.PRASAD
• N.Manikanta
• S.Mohana Sangeetha
• P.Pavani
• P. Bhargavi, P.Anirudh

Rockets have multiple stages because the effectiveness of a rocket is inversely proportional to its mass and number of stages allows us to reduce the mass of the rockets as it operates. The single stage has a lot of empty fuel tank mass that we need to carry with us. The multi-stage has dropped its empty fuel tank and become a smaller; more effective rocket. The lower power stage will be flying up with empty tanks at the expense of fuel of a new tank. Each and every kilogram out will be beneficial. The masses of the empty tanks would not be nice to keep the engines and let go the tanks. We are doing a mathematical optimization of gross lift off mass for a required burnout velocity and payload ,optimal weight distribution for arbitrary number of stages like 2,3,4 and 5 having different structural ratios and specific impulses in each stage, staging optimization gives a quick insight about vehicle performance capability prior to trajectory design. Finally with this optimization technique we compared to gross lift off mass variation for two launch vehicles (i.e Ariane-1 and Proton m) for various burnout velocities and payloads at different number of stages.

Payload, Stages , structural ratio, burnout velocity ,trajectory losses, LaGranger optimization

"GROSS LIFT - OFF MASS OPTIMIZATION FOR SPACE LAUNCH VEHICLES", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.6, Issue 4, page no.550-555, April-2019, Available :http://www.jetir.org/papers/JETIR1904481.pdf

"GROSS LIFT - OFF MASS OPTIMIZATION FOR SPACE LAUNCH VEHICLES", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.6, Issue 4, page no. pp550-555, April-2019, Available at : http://www.jetir.org/papers/JETIR1904481.pdf