New Propulsion

Mass_Budget_Earth.m

@@ -22,7 +22,7 @@
 VeleocityBurns = [deltaV1;deltaV2; deltaV_Incl];
 PropellantUsed = [initialMasses - finalMasses];
 
-massBudgetTable = table(Stages,initialMasses,finalMasses, VeleocityBurns, PropellantUsed);
+massBudgetTable = table(Stages,initialMasses,finalMasses, VeleocityBurns, PropellantUsed)
 
 wet_mass_earth = initial_Mass_1;
 prop_mass_earth = sum(PropellantUsed);

NewISP.m

@@ -0,0 +1,56 @@
+% These are the calculations for the task of checking the newly developed
+% rocket engine
+
+% Calculate exhaust velcoity
+k = 1.3564;
+R = 8.31434*10^3; % J/mol*K
+M = 17.996; % kg/kmol -> Clarify whether this is the correct unit. Wikipedia says yes
+p_e = 500; % pascal
+p_c = 12*10^5; %pascal
+T_c = 2529;% kelvin
+r_e = 80 *10^-3; % meters
+
+v_e = calculateExhaustVelocity(k,R,M,T_c,p_e,p_c);
+ROF = 0.85;
+mdot_fuel =  34*10^(-3); % kg/s
+mdot_ox = mdot_fuel * ROF;
+mdot_tot = mdot_ox + mdot_fuel;
+
+A_e = pi*(r_e)^2;
+p_a = 10^(-8); % ambient pressure in Pascal, from NASA source for ambient pressure at low earth orbit
+
+
+thrust = mdot_tot * v_e + (p_e-p_a)*A_e;
+
+c_e = thrust/mdot_tot;
+ISP_New = mdot_tot*c_e;
+
+% We get a lower ISP which means the engine is less efficient, from this we
+% could conclude that it wouldn't be smart to use this engine
+
+% Required propellant:
+
+
+Orbital_Mechanics; % Runs script orbital_Mechanics such that all variables are available
+dry_mass = 1.2*(442.8+153.6+150.8+268+132+171.2+192.8+491.6+62.8+206.56); % Dry Mass of Satellite, multiplied by margin
+
+%Burn V3 (Inclination):
+initial_Mass_3 = calc_WetMass(ISP_New, dry_mass, deltaV_Incl, g_0_earth);
+
+% Burn V2 (Hohmann 2):
+initial_Mass_2 = calc_WetMass(ISP_New, initial_Mass_3,deltaV2, g_0_earth);
+
+%Burn V1 (Hohmann 1):
+initial_Mass_1 = calc_WetMass(ISP_New, initial_Mass_2, deltaV1,g_0_earth);
+
+Stages =["Delta V1"; "Delta V2"; "Inclination Change"];
+initialMasses = [initial_Mass_1; initial_Mass_2; initial_Mass_3];
+finalMasses = [initial_Mass_2;initial_Mass_3;dry_mass];
+IspValues = [Isp_ini; Isp_ini; Isp_ini];
+VeleocityBurns = [deltaV1;deltaV2; deltaV_Incl];
+PropellantUsed = [initialMasses - finalMasses];
+
+massBudgetTable = table(Stages,initialMasses,finalMasses, VeleocityBurns, PropellantUsed)
+
+% We can conclude that more propellabt is needed, with the newly developed
+% engine

calculateExhaustVelocity.m

@@ -0,0 +1,5 @@
+function v_e = calculateExhaustVelocity(k,R,M,T_c,p_e,p_c)
+
+v_e = sqrt(2*(k/(k-1))*(R/M)*T_c*(1-(p_e/p_c)^((k-1)/k)));
+
+end