Merge branch 'main' of https://github.com/armaanmod/Intro2Spaceflight

armaanmod · Jul 13, 2023 · 0191a85 · 0191a85
2 parents 11420a8 + c042e50
commit 0191a85
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diff --git a/calc_DeltaVIdeal.m b/calc_DeltaVIdeal.m
@@ -0,0 +1,6 @@
+function deltaV_ideal = calc_DeltaVIdeal(g_0_earth, r_earth, h)
+
+    % Ascent into circular orbit
+    deltaV_ideal = sqrt ( g_0_earth * r_earth * (2 - (r_earth / (r_earth + h))));
+
+end
diff --git a/calc_DeltaV_propellant.m b/calc_DeltaV_propellant.m
@@ -0,0 +1,6 @@
+function deltaV = calc_DeltaV_propellant(Isp,g_0_earth, m_ini, m_f)
+
+    % Calculate delta-v using Tsiolkovsky rocket equation
+    deltaV = Isp*g_0_earth * log(m_ini / m_f);
+
+end
diff --git a/calc_launcher_capability.m b/calc_launcher_capability.m
@@ -0,0 +1,39 @@
+1;
+Orbital_Mechanics;
+%booster
+mass_booster = 23000 ;
+mass_propellant_booster = 284000 ;
+Isp_booster = 262 ;
+t_burn_booster = 130;
+%core stage
+mass_structure_core = 10500;
+mass_propellant_core = 140000;
+Isp_core = 429 ;
+%upper stage 
+mass_structure_upper = 8200;
+mass_propellant_upper = 31000;
+mass_adapterandfairing = 800;
+mass_launcher_payload = 9500; 
+deltav_losses = 1200;
+Isp_upper = 465;
+
+needed_velocity = calc_DeltaVIdeal(g_0_earth, r_earth, a_ini - r_earth);
+
+
+m_0_initial = mass_booster + mass_propellant_booster + mass_structure_core + mass_propellant_core + mass_structure_upper + mass_propellant_upper + mass_adapterandfairing + mass_launcher_payload;
+m_0_final = m_0_initial - mass_propellant_booster;
+deltav_booster = calc_DeltaV_propellant(Isp_booster, g_0_earth, m_0_initial, m_0_final);
+
+m_1_initial = mass_structure_core + mass_propellant_core + mass_structure_upper + mass_propellant_upper + mass_adapterandfairing + mass_launcher_payload;
+m_1_final = m_1_initial - mass_propellant_core;
+deltav_core = calc_DeltaV_propellant(Isp_core, g_0_earth, m_1_initial, m_1_final);
+
+m_2_initial = mass_structure_upper + mass_propellant_upper + mass_adapterandfairing + mass_launcher_payload;
+m_2_final = m_2_initial - mass_propellant_upper;
+deltav_upper = calc_DeltaV_propellant(Isp_upper, g_0_earth, m_2_initial, m_2_final);
+
+combined_delta_v = deltav_booster + deltav_core + deltav_upper;
+provided_ariane62_velocity = combined_delta_v - deltav_losses;
+if needed_velocity < provided_ariane62_velocity
+    disp("Successful"); 
+end