AAE 450 Spring 2008 - PowerPoint Presentation

AAE 450 Spring 2008 William Yeong Liang Ling2/14/2008PropulsionThe effect and trends of launch type on launch costs (Model Analysis)Credit to all code authors and all MAT teams Propulsion

AAE 450 Spring 2008 Model results and trendsPropulsion Credit to all code authors and all MAT teams Things of note: Rapid increase in price with delta-v Delta-v effect on price for balloons 1kg more expensive than 0.2kg at 18km/s All cases above 9km/s for aircraft had GLOW > White Knight payload Simplification of balloon cost model

AAE 450 Spring 2008 Future workPropulsion Refine ground support and personnel cost modifiers Consider aircraft that can carry higher payloads (e.g. cargo planes, very likely reduction in forward velocity) Code for automation from a list of cases

AAE 450 Spring 2008 Model data, ground launchPropulsion Payload (kg) Stages Δ V (m/s) GLOW (kg) Cost Prop 1 Prop 2 Prop 3 Material 1 Material 2 Material 3 0.2 2 9000 1,640 $22,020 Solid Solid Steel Titanium 0.2 3 12000 4,531 $71,942 Hybrid Solid Solid Steel Steel Steel 0.2 3 15000 12,583 $138,032 Cryo Solid Solid Al Al Al 0.2 3 18000 46,023 $248,934 Cryo Solid Solid Al Al Al 1.0 2 9000 1,711 $22.460 Solid Solid Steel Titanium 1.0 3 12000 4,728 $72,811 Hybrid Solid Solid Steel Steel Steel 1.0 3 15000 17,629 $138,408 Hybrid Solid Solid Al Al Al 1.0 3 18000 44,256 $243,126 Cryo Solid Solid Al Al Al 5.0 2 9000 2,070 $24,627 Solid Solid Steel Titanium 5.0 3 12000 5,262 $75,161 Hybrid Solid Solid Steel Steel Steel 5.0 3 15000 14,111 $141,170 Cryo Solid Solid Al Al Al 5.0 3 18000 49,533 $261,131 Cryo Solid Solid Al Al Al

AAE 450 Spring 2008 Model data, balloon launchPropulsion Payload (kg) Stages Δ V (m/s) GLOW (kg) Cost Prop 1 Prop 2 Prop 3 Material 1 Material 2 Material 3 0.2 2 9000 1,640 $31,703 Solid Solid Steel Titanium 0.2 3 12000 4,531 $98,593 Hybrid Solid Solid Steel Steel Steel 0.2 3 15000 12,583 $211,832 Cryo Solid Solid Al Al Al 0.2 3 18000 46,023 $518,168 Cryo Solid Solid Al Al Al 1.0 2 9000 1,711 $32,565 Solid Solid Steel Titanium 1.0 3 12000 4,158 $99,395 Hybrid Solid Solid Al Al Al 1.0 3 15000 13,118 $216,746 Cryo Solid Solid Al Al Al 1.0 3 18000 44,256 $502,037 Cryo Solid Solid Al Al Al 5.0 2 9000 2,070 $36,839 Solid Solid Steel Titanium 5.0 3 12000 4,325 $100,913 Hybrid Solid Solid Al Al Al 5.0 3 15000 14,111 $226,906 Cryo Solid Solid Al Al Al 5.0 3 18000 49,533 $550,868 Cryo Solid Solid Al Al Al

AAE 450 Spring 2008 Model data, aircraft launchPropulsion Payload (kg) Stages Δ V (m/s) GLOW (kg) Cost Prop 1 Prop 2 Prop 3 Material 1 Material 2 Material 3 0.2 2 9000 1,640 $47,140 Solid Solid Steel Titanium 1.0 2 9000 1,711 $47,580 Solid Solid Steel Titanium 5.0 2 9000 2,070 $49,747 Solid Solid Steel Titanium

AAE 450 Spring 2008 Automation codePropulsion % William Y.L. Ling % AAE 450 Spring 2008 % Propulsion Team % Model Analysis Automation v1.0 (2/9/08) function Output = Automation %% VARIABLES stages = 3; % Use either 2 or 3 to specify the number of stages % Propellant type - 1: Cryogenic, 2: Storable, 3: Hybrid, 4: Solid propellant_type_1 = [4]; % Change to [1], [2], [3] or [4] as necessary depending on your first stage propellant % Tank material - S: Steel, A: Aluminum, C: Composite, T: Titanium (Do not % confuse the code ( eg . CS-XS) with the propellant. The second character is % the tank material. tank_material_1 = ['A']; % Use ['S'], ['A'], ['C'] or ['T'] as necessary for your first stage tank material tank_material_2 = ['A']; % Use ['S'], ['A'], ['C'] or ['T'] as necessary for your second stage tank material tank_material_3 = ['A']; % Use ['X'] for two-stage, or ['S'], ['A'], ['C'] or ['T'] for your various 3rd stages %% Do not touch, with the exception of those doing code of course, or the world will explode delta_v = [9000,12000,15000,18000]; % Do not touch. Analysis of all delta- v's are required. payload_mass = [0.2,1,5]; % Do not touch. Analysis of all three payloads is required. launch_type = [1,2,3]; %Do not touch. All cases require analysis of all 3 launch types propellant_type_2 = [3,4,1,2]; % Do not touch. All cases have variable 2nd stages. This is arranged 3,4,1,2 on purpose. It allows the calculation of both 2 and 3 stages with the same code. propellant_type_3 = [3,4]; % Do not touch. All cases have variable 3rd stages. Restricted to hybrid/solid for the final stage. tank_material = ['A','A','A']; propellant_type = zeros(1,3);

AAE 450 Spring 2008 Propulsionif stages == 2 Status_total = length( delta_v ).*length( payload_mass ).*length( launch_type ).*2; elseif stages == 3 Status_total = length( delta_v ).*length( payload_mass ).*length( launch_type ).*length(propellant_type_2).*length(propellant_type_3); end Status = 0; % count_delta_v = 1; % count_payload_mass = 1; % count_stages = 1; % count_launch_type = 1; %count_tank_material_1 = 1; %count_tank_material_2 = 1; %count_tank_material_3 = 1; %count_propellant_type_1 = 1; %count_propellant_type_2 = 1; %count_propellant_type_3 = 1; for count_delta_v = 1:length( delta_v ) delta_v_current = delta_v ( count_delta_v ); for count_payload_mass = 1:length( payload_mass ) payload_mass_current = payload_mass ( count_payload_mass ); for count_stages = 1:length(stages) stages_current = stages( count_stages ); for count_launch_type = 1:length( launch_type ) launch_type_current = launch_type ( count_launch_type ); for count_tank_material_1 = 1:length(tank_material_1) tank_material (1) = tank_material_1(count_tank_material_1); for count_tank_material_2 = 1:length(tank_material_2) tank_material (2) = tank_material_2(count_tank_material_2); for count_tank_material_3 = 1:length(tank_material_3) tank_material (3) = tank_material_3(count_tank_material_3 );

AAE 450 Spring 2008 Propulsion if stages_current == 2 tank_material (3) = 'X'; % In case someone forgets to set to 'X' for count_propellant_type_1 = 1:length(propellant_type_1) propellant_type (1) = propellant_type_1(count_propellant_type_1); for count_propellant_type_2 = 1:2 propellant_type (2) = propellant_type_2(count_propellant_type_2); propellant_type (3) = 0; Status = Status + 1; fprintf ('\n Calculating % i /% i \n', Status, Status_total ) main_loop ( delta_v_current , payload_mass_current , stages_current , propellant_type , tank_material , launch_type_current ); %file_1 = fopen ('cases.txt', 'a+'); % fprintf (file_1, '% i ,', delta_v_current ); % fprintf (file_1, '% i ,', stages_current ); % fprintf (file_1, '%f,', payload_mass_current ); % fprintf (file_1, '% i ,', launch_type_current ); % fprintf (file_1, '% i ,', propellant_type (1)); % fprintf (file_1, '%s,', tank_material (1)); % fprintf (file_1, '% i ,', propellant_type (2)); % fprintf (file_1, '%s,', tank_material (2)); % fprintf (file_1, '% i ,', propellant_type (3)); % fprintf (file_1, '%s \n', tank_material (3)); % fclose (file_1); end end elseif stages_current == 3 for count_propellant_type_1 = 1:length(propellant_type_1) propellant_type (1) = propellant_type_1(count_propellant_type_1); for count_propellant_type_2 = 1:length(propellant_type_2) propellant_type (2) = propellant_type_2(count_propellant_type_2); for count_propellant_type_3 = 1:length(propellant_type_3) propellant_type (3) = propellant_type_3(count_propellant_type_3);

AAE 450 Spring 2008 Propulsion Status = Status + 1; fprintf ('\n Calculating % i /% i \n', Status, Status_total ) main_loop ( delta_v_current , payload_mass_current , stages_current , propellant_type , tank_material , launch_type_current ); %file_1 = fopen ('cases.txt', 'a+'); % fprintf (file_1, '% i ,', delta_v_current ); % fprintf (file_1, '% i ,', stages_current ); % fprintf (file_1, '%f,', payload_mass_current ); % fprintf (file_1, '% i ,', launch_type_current ); % fprintf (file_1, '% i ,', propellant_type (1)); % fprintf (file_1, '%s,', tank_material (1)); % fprintf (file_1, '% i ,', propellant_type (2)); % fprintf (file_1, '%s,', tank_material (2)); % fprintf (file_1, '% i ,', propellant_type (3)); % fprintf (file_1, '%s \n', tank_material (3)); % fclose (file_1); end end end end end end end end end end end Output = fprintf ('\n Analysis complete! Open ''output.txt'' and copy and paste everything into the Excel file. Make sure you move this file before running another case. \n\n');