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- Mortazavi, Mahdi [remove] 8
- Astronautics -- Periodicals 3
- 629.405 2
- AAO all at once -- VTank, RTank volume, radius of tanks -- CO collaborative optimization -- Lcyl cylindrical length of tanks -- CSBO Combined Single-level and Bi-level Optimizations -- Rmax maximum permitted radius -- MDO multidisciplinary design optimization -- Zfill filling factor of tanks -- MDF multidisciplinary feasible -- Vfuel, VTank−fuel fuel volume, fuel tank volume -- BLISS bi-level integrated system synthesis -- Vox, VTank−ox oxidant volume, oxidant tank volume -- CSSO concurrent subspace optimization -- Vempty Empty volume of tanks -- O/F, oxidant mass by fuel mass ratio -- VTotal total volume of tanks -- SQP sequential quadratic optimization -- VPress.Tank, RPress.Tank volume, radius of pressurized gas tank -- GA genetic algorithm -- Rgas constant parameter of pressurizer gas -- A⁎, Rt throat area, radius of throat -- T∞ initial temperature -- Pe pressure at exit of the nozzle -- MPress.Gas required mass of pressurizer gas -- Me Mach number of exit nozzle -- Pmax maximum pressure of pressurized gas tank -- γ isentropic exponent -- Lfilm length of film cooling -- ṁ Mass flow of nozzle (thruster) -- ṁfilm mass flow of film cooling -- g0 gravitational acc -- Tvap vaporization temperature of coolant -- Thrustvac vacuum thrust -- ṁvap mass flow of vaporization -- Ae, Re exit area, radius of exit section -- q̇hγ convective heat flux -- Pcomb pressure of combustion chamber -- q̇rγ radiative heat flux -- P⁎ pressure of throat -- hγ convective heat coefficient -- Tcomb temperature of combustion chamber -- Ts wall temperature -- T⁎ Temperature at throat -- εγ radiative coefficient of hot gas -- Te temperature at exit section -- T˜ mean temperature -- R constant parameter of gas (combustion product ) -- Zc correction factor -- Vcomb volume of combustion chamber -- CP specific heat at constant pressure -- Lcomb Length of combustion chamber -- nS.F safety factor -- Vinj injection velocity of propellant -- q̇strr radiative heat flux from structure -- PTank tanks pressure -- δcomb required thickness of combustion chamber -- Dcomb, Rcomb diameter, radius of combustion chamber -- δpres.Gas required thickness of -- θ1 convergent angle -- δTanksph required thickness of spherical tank -- θ2 divergent angle -- δTankcyl required thickness of cylindrical tank -- Zexpantion expansion ratio of nozzle (area) -- δnozzle required thickness of nozzle -- Lcon convergent length of nozzle -- nσ mass correction factor -- Ldiv divergent length of nozzle -- λ2 temperature correction factor 2
- Aeronautics -- Periodicals 2
- Astronautics 2
- Multidisciplinary design -- Optimization -- Bipropellant thruster -- Upper-stage -- AAO -- CO 2
- Outer space -- Exploration -- Periodicals 2
- Periodicals 2
- 510.2462 1
- 617.7523 1