Rocket equation F-m isp aFM M,=M.-mt ve ve ve t dmd △=a=p8-dt △V= g Isp nM。M g Ispenyo=g Ispin R propellant Where R- is the mass ratio Assumes zero losses due to drag and gravityRocket Equation Where is the mass ratio (Assumes zero losses due to drag and gravity) m t Mo veh g M veh M m Isp veh M a F    ' V adt Isp g ³ d m dt dt Mo d m d t t t o t f ³ ¸ ¸ ¹ · ¨ ¨ © § ¸ ¸ ¸ ¸ ¸ ¸ ¸ ¹ · ¨ ¨ ¨ ¨ ¨ ¨ ¨ © § ¸ ¸ ¸ ¸ ¸ ¸ ¸ ¹ · ¨ ¨ ¨ ¨ ¨ ¨ ¨ © §  ' g Isp n R f M g Isp n Mo propellant Mo M V g Isp " n Mo " " R Mo Mf