Jason Ong
2 years ago
18 changed files with 6362 additions and 1 deletions
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BIN2-DoF vs Astos 6-Dof.png
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25Code/DragInterpolations_ICANSAT.m
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76Code/DragInterpolations_MAD.m
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12Code/DragInterpolations_Spark.m
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6Code/ICANSAT/ICANSAT_DragData.txt
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64Code/ICANSAT/V0/ICANSAT.m
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202Code/ICANSAT/V0/ICANSAT_Thrust_v_Time.txt
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31Code/ICANSAT/V1/ICANSAT_V1.m
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82Code/ICANSAT/V1/ICANSAT_V1_Thrust_v_Time.txt
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43Code/MAD/MAD v 4.2B_Thrust_v_Time.txt
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11Code/MAD/MAD_DragData.txt
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2695Code/MAD/MAD_Nominal_Inputs.txt
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2603Code/MAD/MAD_Trajectory_Output.txt
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52Code/MAD/MAD_Validation.m
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441Code/SingleStageRocket.m
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8Code/Spark/Spark_DragData.txt
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12README.md
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BINzjd11_Thesis_Paper_Final.docx
| Before | After |
|---|---|
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| Width: 1457 | Height: 762 | Size: 61 KiB |
@ -0,0 +1,25 @@ |
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function [coeffdrag] = DragInterpolations_ICANSAT(velocity, altitude, time, tb) |
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|
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% global tb |
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|
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drag_data = dlmread("ICANSAT/ICANSAT_DragData.txt", "\t",1,0); |
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|
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% Mach No |
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mach_no = drag_data(:,1); |
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|
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% Full base drag |
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cd_full = drag_data(:,3); |
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|
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% No base drag |
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cd_zero = drag_data(:,2); |
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|
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[temp, sound_speed, P, rho] = atmosisa(altitude); |
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mach_speed = velocity/sound_speed; |
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|
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if (time > tb) |
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coeffdrag = interp1(mach_no, cd_full, mach_speed); |
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else |
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coeffdrag = interp1(mach_no, cd_zero, mach_speed); |
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end |
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|
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end |
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@ -0,0 +1,76 @@ |
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function [coeffdrag] = DragInterpolations_MAD(velocity, altitude, time, tb) |
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|
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drag_data = dlmread("MAD/MAD_DragData.txt", "\t",1,0); |
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|
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% Mach No |
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mach_no = drag_data(:,1); |
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% Altitude 0m, full base drag |
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cdfull_0 = drag_data(:,4); |
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|
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% Altitude 10000m, full base drag |
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cdfull_10000 = drag_data(:,5); |
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|
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% Altitude 30000m, full base drag |
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cdfull_30000 = drag_data(:,6); |
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|
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% Altitude 45000m, full base drag |
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cdfull_45000 = drag_data(:,7); |
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|
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% Altitude 60000m, full base drag |
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cdfull_60000 = drag_data(:,8); |
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|
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% Altitude 0m, no base drag |
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cdzero_0 = drag_data(:,2); |
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|
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% Altitude 10000m, no base drag |
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cdzero_10000 = drag_data(:,3); |
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|
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% Interpolate for Cd values at two stated altitudes, then interpolate for |
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% Cd value at a specific altitude |
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[temp, sound_speed, P, rho] = atmosisa(altitude); |
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mach_speed = velocity/sound_speed; |
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|
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% If propellant is still available |
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if (time > tb) |
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if (altitude <= 10000) |
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coeffdrag = interpolateCd(0, 10000, mach_no, cdfull_0, ... |
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cdfull_10000, mach_speed, altitude); |
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end |
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|
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if (altitude <= 30000 && altitude > 10000) |
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coeffdrag = interpolateCd(10000, 30000, mach_no, cdfull_10000, ... |
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cdfull_30000, mach_speed, altitude); |
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end |
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|
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if (altitude <= 45000 && altitude > 30000) |
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coeffdrag = interpolateCd(30000, 45000, mach_no, cdfull_30000, ... |
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cdfull_45000, mach_speed, altitude); |
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end |
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|
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if (altitude <= 60000 && altitude > 45000) |
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coeffdrag = interpolateCd(45000, 60000, mach_no, cdfull_45000, ... |
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cdfull_60000, mach_speed, altitude); |
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end |
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|
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if (altitude > 60000) |
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coeffdrag = interp1(mach_no, cdfull_60000, mach_speed); |
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end |
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else |
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if (altitude <= 10000) |
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coeffdrag = interpolateCd(0, 10000, mach_no, cdzero_0, ... |
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cdzero_10000, mach_speed, altitude); |
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end |
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if (altitude > 10000) |
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coeffdrag = interp1(mach_no, cdzero_10000, mach_speed); |
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end |
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end |
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|
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end |
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|
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function Cd_specific_alt = interpolateCd(low_alt, high_alt, mach_num, low_alt_Cd, ... |
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high_alt_Cd, mach_speed, specific_alt) |
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low_alt_interpolation = interp1(mach_num, low_alt_Cd, mach_speed); |
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high_alt_interpolation = interp1(mach_num, high_alt_Cd, mach_speed); |
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Cd_specific_alt = interp1([low_alt high_alt], [low_alt_interpolation high_alt_interpolation], specific_alt); |
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end |
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@ -0,0 +1,12 @@ |
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function [coeffdrag] = DragInterpolations_Spark(velocity, altitude) |
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spark_drag_data = dlmread("Spark/Spark_DragData.txt", "\t",1,0); |
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[temp, sound_speed, P, rho] = atmosisa(altitude); |
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mach_speed = velocity/sound_speed; |
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|
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mach = spark_drag_data(:,1); |
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drag = spark_drag_data(:,2); |
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coeffdrag = interp1(mach, drag, mach_speed); |
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end |
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@ -0,0 +1,6 @@ |
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Mach NBD FBD |
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0.00 0.259 0.35 |
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0.30 0.26 0.35 |
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0.60 0.229 0.324 |
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0.90 0.233 0.328 |
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0.99 0.261 0.4 |
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@ -0,0 +1,64 @@ |
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clc |
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addpath('../') |
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addpath('../..') |
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|
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% Df, Lr, Ls, ms, mp, tb |
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icansat = SingleStageRocket(0.1567, 2.391, 4, 14, 1.92, 8.0); |
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|
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% Timestep, no. of timesteps, launch angle |
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icansat.SetSimulationParams(0.01, 10000, 88); |
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icansat.SetRocketID("ICANSAT"); |
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icansat.InitializeVars(); |
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|
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% Uncomment to use non-constant mass flow rate |
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% icansat.SetVariableMassFlow(); |
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icansat.CalculateThrust('ICANSAT_Thrust_v_Time.txt'); |
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icansat.CalculateTrajectory(); |
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icansat.WriteDataFile(); |
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|
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subplot(2,3,1); |
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plot(icansat.t(1:icansat.NStepEnd), icansat.y(1:icansat.NStepEnd)/1000); |
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hold on |
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xlabel('Time (s)'); |
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ylabel('Altitude (km)'); |
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ylim([0 2]); |
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grid on |
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|
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subplot(2,3,2); |
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plot(icansat.t(1:icansat.NStepEnd), icansat.M(1:icansat.NStepEnd)); |
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hold on |
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xlabel('Time (s)'); |
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ylabel('Mach No.'); |
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grid on |
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|
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subplot(2,3,3); |
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plot(icansat.t(1:icansat.NStepEnd), icansat.thrust(1:icansat.NStepEnd)); |
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hold on |
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xlabel('Time (s)'); |
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ylabel('Thrust (N)'); |
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grid on |
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|
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subplot(2,3,4); |
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plot(icansat.x(1:icansat.NStepEnd)/1000, icansat.y(1:icansat.NStepEnd)/1000); |
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hold on |
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xlabel('Downrange(km)'); |
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ylabel('Altitude (km)'); |
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ylim([0 2]); |
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grid on |
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|
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subplot(2,3,5); |
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plot(icansat.t(1:icansat.NStepEnd), icansat.DvDt(1:icansat.NStepEnd)); |
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hold on |
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plot([0,50], [0, 0], 'k'); |
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xlabel('Time (s)'); |
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ylabel('Accleration (m/s^2)'); |
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grid on |
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|
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subplot(2,3,6); |
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plot(icansat.t(1:icansat.NStepEnd), icansat.m(1:icansat.NStepEnd)); |
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hold on |
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xlabel('Time (s)'); |
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ylabel('Mass (kg)'); |
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grid on |
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% --------- |
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@ -0,0 +1,202 @@ |
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0.00 0.000 |
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0.01 857.647 |
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0.04 954.785 |
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0.08 913.544 |
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0.12 927.823 |
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0.16 919.100 |
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0.20 919.595 |
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0.24 916.682 |
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0.28 915.395 |
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0.32 913.525 |
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0.36 912.058 |
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0.40 910.551 |
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0.44 909.180 |
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0.48 907.763 |
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0.52 906.496 |
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0.56 905.294 |
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0.60 904.034 |
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0.64 902.880 |
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0.68 901.733 |
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0.72 900.644 |
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0.76 899.489 |
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0.80 898.448 |
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0.84 897.394 |
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0.88 896.390 |
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0.92 895.312 |
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0.96 894.339 |
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1.00 893.343 |
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1.04 892.377 |
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1.08 891.435 |
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1.12 890.419 |
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1.16 889.500 |
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1.20 888.499 |
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1.24 887.654 |
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1.28 886.720 |
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1.32 885.754 |
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1.36 884.862 |
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1.40 883.893 |
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1.44 883.073 |
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1.48 882.110 |
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1.52 881.241 |
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1.56 880.337 |
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1.60 879.399 |
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1.64 878.531 |
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1.68 877.641 |
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1.72 876.782 |
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1.76 875.889 |
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1.80 874.959 |
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1.84 874.098 |
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1.88 873.210 |
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1.92 872.281 |
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1.96 871.422 |
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2.00 870.539 |
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2.04 869.685 |
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2.08 868.795 |
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2.12 867.867 |
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2.16 867.006 |
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2.20 866.117 |
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2.24 865.186 |
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2.28 864.323 |
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2.32 863.430 |
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2.36 862.496 |
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2.40 861.630 |
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2.44 860.789 |
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2.48 859.850 |
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2.52 858.979 |
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2.56 858.077 |
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2.60 857.133 |
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2.64 856.256 |
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2.68 855.348 |
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2.72 854.450 |
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2.76 853.492 |
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2.80 852.609 |
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2.84 851.690 |
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2.88 850.731 |
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2.92 849.837 |
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2.96 848.912 |
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3.00 847.996 |
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3.04 397.662 |
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3.08 270.454 |
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3.12 262.949 |
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3.16 254.969 |
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3.20 247.296 |
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3.24 239.841 |
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3.28 232.600 |
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3.32 225.594 |
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3.36 218.788 |
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3.40 212.177 |
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3.44 205.794 |
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3.48 199.581 |
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3.52 193.569 |
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3.56 187.741 |
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3.60 182.078 |
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3.64 176.589 |
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3.68 171.267 |
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3.72 166.117 |
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3.76 161.104 |
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3.80 156.244 |
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3.84 151.542 |
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3.88 146.973 |
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3.92 142.552 |
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3.96 138.249 |
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4.00 134.093 |
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4.04 130.048 |
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4.08 126.133 |
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4.12 122.330 |
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4.16 118.650 |
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4.20 115.075 |
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4.24 111.608 |
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4.28 108.254 |
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4.32 104.988 |
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4.36 101.828 |
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4.40 98.758 |
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4.44 95.787 |
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4.48 92.895 |
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4.52 90.102 |
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4.56 87.389 |
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4.60 84.752 |
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4.64 82.201 |
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4.68 79.722 |
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4.72 77.324 |
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4.76 74.998 |
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4.80 72.734 |
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4.84 70.543 |
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4.88 68.418 |
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4.92 66.359 |
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4.96 64.357 |
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5.00 62.417 |
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5.04 60.539 |
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5.08 58.714 |
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5.12 56.945 |
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5.16 55.226 |
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5.20 53.563 |
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5.24 51.947 |
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5.28 50.383 |
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5.32 48.864 |
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5.36 47.391 |
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5.40 45.962 |
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5.44 44.577 |
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5.48 43.231 |
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5.52 41.929 |
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5.56 40.664 |
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5.60 39.437 |
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5.64 38.247 |
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5.68 37.092 |
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5.72 35.973 |
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5.76 34.887 |
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5.80 33.836 |
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5.84 32.814 |
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5.88 31.826 |
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5.92 30.863 |
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5.96 29.930 |
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6.00 29.027 |
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6.04 28.150 |
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6.08 27.302 |
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6.12 26.477 |
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6.16 25.676 |
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6.20 24.900 |
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6.24 24.147 |
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6.28 23.418 |
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6.32 22.710 |
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6.36 22.022 |
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6.40 21.358 |
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6.44 20.712 |
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6.48 20.086 |
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6.52 19.477 |
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6.56 18.889 |
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6.60 18.316 |
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6.64 17.762 |
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6.68 17.224 |
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6.72 16.703 |
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6.76 16.197 |
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6.80 15.706 |
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6.84 15.230 |
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6.88 14.769 |
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6.92 14.320 |
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6.96 13.887 |
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7.00 13.466 |
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7.04 13.058 |
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7.08 12.661 |
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7.12 12.277 |
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7.16 11.904 |
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7.20 11.543 |
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7.24 11.193 |
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7.28 10.852 |
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7.32 10.523 |
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7.36 10.203 |
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7.40 9.890 |
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7.44 9.587 |
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7.48 9.301 |
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7.52 9.020 |
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7.56 8.748 |
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7.60 8.486 |
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7.64 8.213 |
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7.68 7.969 |
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7.72 7.736 |
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7.76 7.509 |
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7.80 7.289 |
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7.84 7.074 |
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7.88 6.864 |
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7.92 6.661 |
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7.96 6.464 |
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8.00 0.000 |
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@ -0,0 +1,31 @@ |
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clc |
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addpath('../') |
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addpath('../..') |
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|
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% Df, Lr, Ls, ms, mp, tb |
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icansat = SingleStageRocket(0.1567, 2.391, 4, 14, 1.160534, 4.0); |
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|
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% RunTrajectorySim(icansat, 88); |
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% RunTrajectorySim(icansat, 86); |
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% RunTrajectorySim(icansat, 84); |
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% RunTrajectorySim(icansat, 82); |
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% RunTrajectorySim(icansat, 80); |
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% RunTrajectorySim(icansat, 78); |
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% RunTrajectorySim(icansat, 76); |
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% RunTrajectorySim(icansat, 74); |
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% RunTrajectorySim(icansat, 72); |
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RunTrajectorySim(icansat, 70); |
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|
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function RunTrajectorySim(rocket, launch_angle) |
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% Timestep, no. of timesteps, launch angle |
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rocket.SetSimulationParams(0.01, 10000, launch_angle); |
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rocket.SetRocketID("ICANSAT"); |
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rocket.InitializeVars(); |
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|
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% Uncomment to use non-constant mass flow rate |
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rocket.SetVariableMassFlow(); |
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|
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rocket.CalculateThrust('ICANSAT_V1_Thrust_v_Time.txt'); |
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rocket.CalculateTrajectory(); |
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rocket.WriteDataFile(); |
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end |
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@ -0,0 +1,82 @@ |
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0.000000000 28.61809561 |
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0.049382716 865.7172252 |
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0.098765432 828.788367 |
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0.148148148 868.0198335 |
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0.197530864 855.1079959 |
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0.24691358 857.8965696 |
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0.296296296 854.5947699 |
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0.345679012 854.7495807 |
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0.395061728 853.0271145 |
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0.444444444 851.8792688 |
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0.49382716 850.5777483 |
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0.543209877 849.3378201 |
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0.592592593 848.0391454 |
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0.641975309 846.8108491 |
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0.691358025 845.5911444 |
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0.740740741 844.3810837 |
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0.790123457 843.1795528 |
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0.839506173 841.9861293 |
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0.888888889 790.6663048 |
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0.938271605 814.7418358 |
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0.987654321 803.4557486 |
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1.037037037 808.316949 |
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1.086419753 805.7695017 |
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1.135802469 806.6979621 |
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1.185185185 805.9333018 |
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1.234567901 806.0156238 |
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1.283950617 805.7302387 |
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1.333333333 805.6325586 |
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1.382716049 805.403352 |
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1.432098765 805.2754677 |
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1.481481481 805.1345303 |
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1.530864198 804.9574627 |
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1.580246914 804.8347208 |
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1.62962963 804.7205219 |
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1.679012346 804.5587272 |
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1.728395062 804.506189 |
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1.777777778 804.3839195 |
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1.827160494 804.2516444 |
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1.87654321 804.1588364 |
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1.925925926 804.0801232 |
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1.975308642 803.9493204 |
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2.024691358 803.8779173 |
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2.074074074 803.7574503 |
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2.12345679 803.6943463 |
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2.172839506 803.6351266 |
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2.222222222 803.5275729 |
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2.271604938 803.5265503 |
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2.320987654 803.4009857 |
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2.37037037 803.3696582 |
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2.419753086 803.3223497 |
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2.469135802 803.2353159 |
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2.518518519 803.1992204 |
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2.567901235 803.1158937 |
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2.617283951 803.0865164 |
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2.666666667 376.035258 |
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2.716049383 253.688266 |
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2.765432099 248.46047 |
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2.814814815 242.6136227 |
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2.864197531 236.9364371 |
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2.913580247 231.3951724 |
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2.962962963 225.9851368 |
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3.012345679 220.6900131 |
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3.061728395 215.53518 |
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3.111111111 210.4890237 |
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3.160493827 205.5629687 |
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3.209876543 200.7540814 |
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3.259259259 196.0723345 |
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3.308641975 191.4770118 |
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3.358024691 187.002752 |
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3.407407407 182.6232343 |
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3.456790123 178.3595068 |
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3.50617284 174.1854098 |
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3.555555556 170.1104297 |
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3.604938272 166.1321595 |
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3.654320988 162.2588809 |
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3.703703704 158.4668032 |
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3.75308642 154.7548871 |
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3.802469136 151.1405636 |
|||
3.851851852 147.6122193 |
|||
3.901234568 144.157891 |
|||
3.950617284 140.7854521 |
|||
4.000000000 0.0 |
|||
@ -0,0 +1,43 @@ |
|||
0.00 0.00 |
|||
0.10 9359.85 |
|||
0.50 9263.03 |
|||
1.00 9184.49 |
|||
1.50 9118.59 |
|||
2.00 9061.93 |
|||
2.50 9012.31 |
|||
3.00 8968.24 |
|||
3.50 8928.65 |
|||
4.00 8892.74 |
|||
4.50 8859.92 |
|||
5.00 8829.72 |
|||
5.50 8801.76 |
|||
6.00 8775.76 |
|||
6.50 8751.47 |
|||
7.00 8728.69 |
|||
7.50 8707.25 |
|||
8.00 8687.01 |
|||
8.50 8667.85 |
|||
9.00 8649.67 |
|||
9.50 8632.37 |
|||
10.00 8615.88 |
|||
10.50 8600.13 |
|||
11.00 8585.06 |
|||
11.50 8570.61 |
|||
12.00 8556.75 |
|||
12.50 8543.42 |
|||
13.00 8530.59 |
|||
13.50 8518.23 |
|||
14.00 8506.30 |
|||
14.50 8494.77 |
|||
15.00 8483.63 |
|||
15.50 8472.85 |
|||
16.00 8462.40 |
|||
16.50 8452.27 |
|||
17.00 8442.44 |
|||
17.50 8432.90 |
|||
18.00 8423.62 |
|||
18.50 8414.60 |
|||
19.00 8405.82 |
|||
19.50 8397.27 |
|||
20.00 8388.94 |
|||
20.10 0.00 |
|||
@ -0,0 +1,11 @@ |
|||
Mach NBD_0k NBD_10k FBD_0k FBD_10k FBD_30k FBD_45k FBD_60k |
|||
0.0 0.38 0.428 0.42 0.468 0.725 1.133 1.819 |
|||
0.5 0.38 0.428 0.42 0.468 0.725 1.133 1.819 |
|||
0.8 0.37 0.41 0.4 0.441 0.67 1.026 1.611 |
|||
1.1 0.51 0.547 0.58 0.617 0.813 1.115 1.607 |
|||
1.2 0.5 0.54 0.573 0.609 0.793 1.078 1.54 |
|||
1.5 0.46 0.5 0.53 0.563 0.734 1 1.424 |
|||
2.0 0.38 0.42 0.438 0.467 0.619 0.854 1.239 |
|||
3.0 0.28 0.31 0.315 0.34 0.463 0.661 1 |
|||
4.0 0.217 0.235 0.242 0.261 0.367 0.54 0.842 |
|||
5.0 0.217 0.235 0.242 0.261 0.367 0.54 0.842 |
|||
2695
Code/MAD/MAD_Nominal_Inputs.txt
File diff suppressed because it is too large
View File
File diff suppressed because it is too large
View File
2603
Code/MAD/MAD_Trajectory_Output.txt
File diff suppressed because it is too large
View File
File diff suppressed because it is too large
View File
@ -0,0 +1,52 @@ |
|||
clc |
|||
addpath('../') |
|||
|
|||
mad = SingleStageRocket(0.205, 4.96, 10, 68, 78, 20.1); |
|||
mad.SetSimulationParams(0.05, 10000, 85); |
|||
mad.SetRocketID("MAD"); |
|||
mad.InitializeVars(); |
|||
mad.SetThrustCorrection(); |
|||
mad.CalculateThrust('MAD v 4.2B_Thrust_v_Time.txt'); |
|||
mad.CalculateTrajectory(); |
|||
mad.WriteDataFile(); |
|||
|
|||
% MAD Data |
|||
% ----------------------------------------------------------------------------- |
|||
nominal_input = dlmread("MAD/MAD_Nominal_Inputs.txt", "\t",1,0); |
|||
nominal_time = nominal_input(:, 1); |
|||
astos_thrust = nominal_input(:, 2); |
|||
|
|||
trajectory_output = dlmread("MAD/MAD_Trajectory_Output.txt", "\t",1,0); |
|||
trajectory_time = trajectory_output(:, 1); |
|||
altitude = trajectory_output(:, 2); |
|||
mach = trajectory_output(:, 6); |
|||
|
|||
subplot(1,3,1); |
|||
plot(mad.t(1:mad.NStepEnd), mad.y(1:mad.NStepEnd)/1000); |
|||
hold on |
|||
plot(trajectory_time, altitude, '--o','MarkerIndices',1:100:length(trajectory_time)); |
|||
xlabel('Time (s)'); |
|||
ylabel('Altitude (km)'); |
|||
legend('2-DoF', 'ASTOS 6-DoF'); |
|||
ylim([0 60]); |
|||
grid on |
|||
|
|||
subplot(1,3,2); |
|||
plot(mad.t(1:mad.NStepEnd), mad.M(1:mad.NStepEnd)); |
|||
hold on |
|||
plot(trajectory_time, mach, '--o','MarkerIndices',1:100:length(trajectory_time)); |
|||
xlabel('Time (s)'); |
|||
ylabel('Mach No.'); |
|||
legend('2-DoF', 'ASTOS 6-DoF'); |
|||
grid on |
|||
|
|||
subplot(1,3,3); |
|||
plot(mad.t(1:mad.NStepEnd), mad.thrust(1:mad.NStepEnd)/1000); |
|||
hold on |
|||
plot(nominal_time, astos_thrust, '--o','MarkerIndices',1:100:length(nominal_time)); |
|||
xlabel('Time (s)'); |
|||
ylabel('Corrected Thrust (kN)'); |
|||
legend('2-DoF', 'ASTOS 6-DoF'); |
|||
xlim([0 25]); |
|||
grid on |
|||
% ----------------------------------------------------------------------------- |
|||
@ -0,0 +1,441 @@ |
|||
classdef SingleStageRocket < handle |
|||
properties |
|||
% Rocket parameters |
|||
Df % Diameter of fuselage (meters) |
|||
Ls % Length of structure (meters) |
|||
Lr % Length of launch rod (meters) |
|||
ms % Mass of structure (kg) |
|||
mp % Mass of propellant (kg) |
|||
tb % burn time (sec) |
|||
|
|||
% Boolean - constant mass flow or variable mass flow |
|||
mdot_constant |
|||
|
|||
% Boolean - thrust correction |
|||
thrust_correction |
|||
|
|||
% Derived parameters |
|||
mt % Total mass |
|||
mdot % Mass flow |
|||
|
|||
% Simulation parameters |
|||
Timestep |
|||
NSteps % No. of timesteps |
|||
n_tb % Burnout timestep |
|||
|
|||
% Thrust data file, thrust, isp |
|||
thrust_dat_file |
|||
thrust |
|||
isp |
|||
|
|||
% Simulation variables |
|||
t % Time |
|||
V, Vcr, M % Velocity magnitude, critical velocity, mach number; |
|||
v, u, ux % Velocity components in y and x, x-component velocity calc.4 |
|||
utheta % X-component of velocity for launch rod |
|||
m, Cd % Mass, drag coefficient |
|||
x, y, theta % X and Y positions, angle w.r.t. horizontal |
|||
DvDt, dvdt % Absolute and relative accelerations |
|||
kd, kt % Coefficients of drag and thrust |
|||
rho, g, c, T % Density, gravity, sound speed, temperature |
|||
area % Cross sectional area |
|||
q % Dynamic pressure |
|||
launch_angle |
|||
|
|||
% Rocket identifier (MAD, ICANSAT, Spark etc.) |
|||
% For purposes of drag identification |
|||
ID |
|||
|
|||
% End of simulation |
|||
NStepEnd |
|||
end |
|||
|
|||
methods |
|||
% Initialization |
|||
function self = SingleStageRocket(Df, Ls, Lr, ms, mp, tb) |
|||
% Set rocket parameters |
|||
self.Df = Df; |
|||
self.Ls = Ls; |
|||
self.Lr = Lr; |
|||
self.ms = ms; |
|||
self.mp = mp; |
|||
self.tb = tb; |
|||
|
|||
% Set booleans |
|||
self.mdot_constant = true; |
|||
self.thrust_correction = false; |
|||
|
|||
% Derived parameters |
|||
self.mt = self.ms + self.mp; |
|||
end |
|||
|
|||
% Set rocket ID |
|||
function SetRocketID(obj, id) |
|||
obj.ID = id; |
|||
end |
|||
|
|||
% Set booleans |
|||
function SetThrustCorrection(obj) |
|||
obj.thrust_correction = true; |
|||
end |
|||
|
|||
function SetVariableMassFlow(obj) |
|||
obj.mdot_constant = false; |
|||
end |
|||
|
|||
% Set simulation parameters |
|||
function SetSimulationParams(obj, dt, nsteps, launch_angle) |
|||
obj.Timestep = dt; |
|||
obj.NSteps = nsteps; |
|||
obj.launch_angle = launch_angle; |
|||
fprintf('Launch angle: %4.2f degrees.\n', launch_angle); |
|||
fprintf('Timestep: %5.3f s. Maximum no. of timesteps: %d.\n', dt, nsteps); |
|||
end |
|||
|
|||
% Initialize variables |
|||
function InitializeVars(obj) |
|||
obj.t = zeros(obj.NSteps, 1); |
|||
obj.V = zeros(obj.NSteps, 1); |
|||
obj.Vcr = zeros(obj.NSteps, 1); |
|||
obj.M = zeros(obj.NSteps, 1); |
|||
obj.v = zeros(obj.NSteps, 1); |
|||
obj.u = zeros(obj.NSteps, 1); |
|||
obj.ux = zeros(obj.NSteps, 1); |
|||
obj.utheta = zeros(obj.NSteps, 1); |
|||
|
|||
obj.m = zeros(obj.NSteps, 1); |
|||
obj.Cd = zeros(obj.NSteps, 1); |
|||
|
|||
obj.x = zeros(obj.NSteps, 1); |
|||
obj.y = zeros(obj.NSteps, 1); |
|||
obj.theta = zeros(obj.NSteps, 1); |
|||
|
|||
obj.DvDt = zeros(obj.NSteps, 1); |
|||
obj.dvdt = zeros(obj.NSteps, 1); |
|||
|
|||
obj.mdot = zeros(obj.NSteps, 1); |
|||
obj.thrust = zeros(obj.NSteps, 1); |
|||
obj.isp = zeros(obj.NSteps, 1); |
|||
|
|||
obj.kd = zeros(obj.NSteps, 1); |
|||
obj.kt = zeros(obj.NSteps, 1); |
|||
|
|||
obj.rho = zeros(obj.NSteps, 1); |
|||
obj.g = zeros(obj.NSteps, 1); |
|||
obj.c = zeros(obj.NSteps, 1); |
|||
obj.T = zeros(obj.NSteps, 1); |
|||
|
|||
obj.q = zeros(obj.NSteps, 1); |
|||
|
|||
obj.area = (pi/4)*(obj.Df.^2); |
|||
|
|||
% Set initial values |
|||
obj.V(1) = 0.447; % Velocity - m/s |
|||
obj.theta(1) = deg2rad(obj.launch_angle); |
|||
obj.u(1) = obj.V(1)*cos(obj.theta(1)); % x-component of velocity |
|||
obj.v(1) = obj.V(1)*sin(obj.theta(1)); % y-component of velocity |
|||
obj.y(1) = 0.0; % Altitude - m (XY) |
|||
obj.t(1) = 0; % Flight Time - s |
|||
obj.M(1) = 0; % Mach Number |
|||
obj.c(1) = 340.3961; % Speed of Sound - m/s^2 |
|||
obj.rho(1) = 1.23; % Sea Level Density - kg/m^3 |
|||
obj.T(1) = 288.16; % Temperature (K) |
|||
|
|||
obj.g(1) = 9.8066; |
|||
obj.m(1) = obj.mt; |
|||
end |
|||
|
|||
% Load thrust data (include thrust correction) |
|||
function CalculateThrust(obj, file) |
|||
data = dlmread(file); |
|||
force = data(:,2); |
|||
time = data(:,1); |
|||
dt = obj.Timestep; |
|||
|
|||
resampled_time = 0:dt:obj.tb; |
|||
resampled_force = interp1(time,force,resampled_time,'linear'); |
|||
|
|||
for i = 1:length(resampled_time) |
|||
obj.thrust(i) = resampled_force(i); |
|||
end |
|||
|
|||
obj.n_tb = length(resampled_time); |
|||
|
|||
% Find mass flow rate up till end of burnout |
|||
obj.CalculateMassFlow(length(resampled_time)); |
|||
end |
|||
|
|||
function [t,p,rho] = CalcAtmosQuantities(obj, h) |
|||
hg = h; % geometric alt in meters |
|||
R = 287; % Gas Constant |
|||
re = 6.356766e6; % radius of earth |
|||
g0 = 9.8066; % gravity |
|||
h = re/(re+hg)*hg; |
|||
|
|||
% Altitude in meters |
|||
h0 = 0.0; |
|||
h1 = 11000.0; |
|||
h2 = 25000.0; |
|||
h3 = 47000; |
|||
h4 = 53000; |
|||
h5 = 79000; |
|||
h6 = 90000; |
|||
h7 = 105000; |
|||
|
|||
% Temperature in Kelvin. |
|||
t0 = 288.16; |
|||
t1 = 216.66; |
|||
t2 = 216.66; |
|||
t3 = 282.66; |
|||
t4 = 282.66; |
|||
t5 = 165.66; |
|||
t6 = 165.66; |
|||
t7 = 225.66; |
|||
|
|||
%%equations |
|||
|
|||
a01 = (t1-t0)/(h1-h0); % slope of T/h in K/m for 0 to 11 km |
|||
a23 = (t3-t2)/(h3-h2); % slope of T/h in K/m for 25 to 47 km |
|||
a45 = (t5-t4)/(h5-h4); % slope of T/h in K/m for 53 to 79 km |
|||
a67 = (t7-t6)/(h7-h6); % slope of T/h in K/m for 90 to 105 km |
|||
|
|||
% Pressure in N/m^2 |
|||
p0 = 101325.0; |
|||
p1 = p0*(t1/t0)^(-g0/(a01*R)); |
|||
p2 = p1*exp(-(g0/(R*t1))*(h2-h1)); |
|||
p3 = p2*(t3/t2)^(-g0/(a23*R)); |
|||
p4 = p3*exp(-(g0/(R*t3))*(h4-h3)); |
|||
p5 = p4*(t5/t4)^(-g0/(a45*R)); |
|||
p6 = p5*exp(-(g0/(R*t5))*(h6-h5)); |
|||
p7 = p6*(t7/t6)^(-g0/(a67*R)); |
|||
|
|||
if h < h1 |
|||
t = t0+a01*h; |
|||
p = p0*(t/t0)^(-g0/(a01*R)); |
|||
elseif h < h2 |
|||
t = t1; |
|||
p= p1*exp(-(g0/(R*t))*(h-h1)); |
|||
elseif h < h3 |
|||
t = t2+a23*(h-h2); |
|||
p = p2*(t/t2)^(-g0/(a23*R)); |
|||
elseif h < h4 |
|||
t = t3; |
|||
p = p3*exp(-(g0/(R*t))*(h-h3)); |
|||
elseif h < h5 |
|||
t = t4+a45*(h-h4); |
|||
p = p4*(t/t4)^(-g0/(a45*R)); |
|||
elseif h < h6 |
|||
t = t5; |
|||
p = p5*exp(-(g0/(R*t))*(h-h5)); |
|||
elseif h < h7 |
|||
t = t6+a67*(h-h6); |
|||
p = p6*(t/t6)^(-g0/(a67*R)); |
|||
else |
|||
t= t7; |
|||
p = p7*exp(-(g0/(R*t))*(h-h7)); |
|||
end |
|||
rho=p/(R*t); % Density in kg/m^3 |
|||
end |
|||
|
|||
% Thrust correction based on ASTOS manual |
|||
function T = ThrustCorrection(obj, h, thrust) |
|||
[t,p,rho] = obj.CalcAtmosQuantities(h); |
|||
T = thrust*1.095 - 0.014 * p; |
|||
end |
|||
|
|||
% Calculate mass at each iteration |
|||
function CalculateMassFlow(obj,n_tb) |
|||
g0 = 9.8066; |
|||
if obj.mdot_constant == true |
|||
% Use constant mass flow rate |
|||
obj.mdot(2:n_tb) = obj.mp/obj.tb; |
|||
|
|||
% Calculate instantaneous Isp |
|||
for i = 2:n_tb |
|||
if obj.mdot(i) == 0 |
|||
obj.isp(i) = 0; |
|||
else |
|||
obj.isp(i) = obj.thrust(i)/(obj.mdot(i) * g0); |
|||
end |
|||
end |
|||
else |
|||
% Assuming constant Isp, use thrust values as ratios over |
|||
% the combined sum to obtain the mass flow rate |
|||
mdot_sum = obj.mp/obj.Timestep; |
|||
force_sum = sum(obj.thrust(1:n_tb)); |
|||
for i = 2:n_tb |
|||
obj.mdot(i) = obj.thrust(i)/force_sum * mdot_sum; |
|||
|
|||
if obj.mdot(i) == 0 |
|||
obj.isp(i) = 0; |
|||
else |
|||
obj.isp(i) = obj.thrust(i)/(obj.mdot(i) * g0); |
|||
end |
|||
end |
|||
end |
|||
end |
|||
|
|||
% Density calculation |
|||
function [T, rho] = CalculateRhoTemp(obj, h) |
|||
[T, p, rho] = obj.CalcAtmosQuantities(h); |
|||
return; |
|||
end |
|||
|
|||
% Gravity calculation |
|||
function g = CalculateGravity(obj, h) |
|||
g0 = 9.80665; % Sea Level Gravity - m/s^2 |
|||
RE = 6376000; % Radius of the Earth - m |
|||
|
|||
g = g0*(RE/(RE+h))^2; |
|||
return; |
|||
end |
|||
|
|||
% Drag interpolation |
|||
% Drag interpolation functions need to be specified separately in |
|||
% other files due to non-similarity in data. |
|||
function [Cd] = DragInterpolation(obj, V, y, t) |
|||
switch obj.ID |
|||
case "ICANSAT" |
|||
Cd = DragInterpolations_ICANSAT(V, y, t, obj.tb); |
|||
|
|||
case "MAD" |
|||
Cd = DragInterpolations_MAD(V, y, t, obj.tb); |
|||
|
|||
% Spark data not validated |
|||
case "Spark" |
|||
Cd = DragInterpolations_Spark(V, y); |
|||
end |
|||
return; |
|||
end |
|||
|
|||
% Trajectory calculation |
|||
function CalculateTrajectory(obj) |
|||
Rg = 286.9; |
|||
nSteps = obj.NSteps; |
|||
dt = obj.Timestep; |
|||
|
|||
% Calculate trajectory |
|||
for i = 2:nSteps |
|||
obj.t(i) = obj.t(i-1) + dt; |
|||
V_prev = obj.V(i-1); |
|||
y_prev = obj.y(i-1); |
|||
t_current = obj.t(i); |
|||
obj.Cd(i) = obj.DragInterpolation(V_prev, y_prev, t_current); |
|||
|
|||
% Get thrust from resampled thrust data |
|||
if obj.t(i) >= obj.tb |
|||
thrust_i = 0; |
|||
else |
|||
% Thrust correction if boolean true |
|||
if obj.thrust_correction == true |
|||
obj.thrust(i) = obj.ThrustCorrection(obj.y(i-1), obj.thrust(i)); |
|||
if obj.thrust(i) < 0 |
|||
obj.thrust(i) = 0; |
|||
end |
|||
end |
|||
thrust_i = obj.thrust(i); |
|||
end |
|||
|
|||
% Update mass |
|||
obj.m(i) = obj.m(i-1) - obj.mdot(i-1)*dt; |
|||
|
|||
% Find critical velocity for leaving launch structure |
|||
obj.Vcr(i) = sqrt((thrust_i/obj.m(i))*obj.Ls*2); |
|||
|
|||
% X Y Velocity Component Equations |
|||
obj.kd(i) = (obj.rho(i-1)*obj.Cd(i)*obj.area)/(2*obj.m(i)); |
|||
obj.kt(i) = thrust_i/obj.m(i); |
|||
obj.V(i) = sqrt(obj.u(i-1)^2 + obj.v(i-1)^2); |
|||
obj.DvDt(i) = obj.kt(i)*obj.v(i-1)/obj.V(i) - ... |
|||
obj.kd(i)*obj.v(i-1)*obj.V(i) - obj.g(i-1); |
|||
|
|||
% Use non-zero acceleration during burn phase |
|||
if obj.DvDt(i) < 0 && obj.t(i-1) <= obj.tb |
|||
obj.dvdt(i) = 0; |
|||
else |
|||
obj.dvdt(i) = obj.DvDt(i); |
|||
end |
|||
|
|||
obj.v(i) = obj.v(i-1) + obj.dvdt(i)*dt; |
|||
|
|||
obj.utheta(i) = obj.v(i) * obj.u(i-1)/obj.v(i-1); |
|||
obj.ux(i) = obj.u(i-1)+((obj.kt(i)*obj.u(i-1)/obj.V(i-1)) - ... |
|||
obj.kd(i)*obj.u(i-1)*obj.V(i-1))*dt; |
|||
|
|||
% Zero acceleration on the ground |
|||
if obj.DvDt(i) < 0 && obj.t(i-1) <= obj.tb |
|||
obj.u(i) = obj.u(i-1); |
|||
% Within the launch structure |
|||
elseif obj.x(i-1) <= obj.Lr*cos(obj.theta(1)) |
|||
obj.u(i) = obj.utheta(i); |
|||
% Under critical velocity for leaving launch structure |
|||
elseif obj.V(i) < obj.Vcr(i) |
|||
obj.u(i) = obj.utheta(i); |
|||
% In the air |
|||
else |
|||
obj.u(i) = obj.ux(i); |
|||
end |
|||
|
|||
obj.theta(i) = atan(obj.v(i)/obj.u(i)); |
|||
obj.x(i) = obj.x(i-1) + obj.u(i)*dt; |
|||
obj.y(i) = obj.y(i-1) + obj.v(i)*dt; |
|||
|
|||
% Calculate dynamic pressure |
|||
obj.q(i) = 0.5*obj.rho(i-1)*(obj.V(i-1)^2); |
|||
|
|||
% Update density |
|||
[obj.T(i), obj.rho(i)] = obj.CalculateRhoTemp(obj.y(i)); |
|||
|
|||
% Update sound speed |
|||
obj.c(i) = sqrt(1.4*Rg*obj.T(i)); |
|||
|
|||
% Update gravity |
|||
obj.g(i) = obj.CalculateGravity(obj.y(i)); |
|||
|
|||
% Update Mach no. |
|||
obj.M(i) = abs(obj.V(i))/obj.c(i); |
|||
|
|||
if obj.y(i) < 0 |
|||
obj.NStepEnd = i; |
|||
break |
|||
end |
|||
|
|||
end |
|||
|
|||
obj.theta = obj.theta*(180/pi); |
|||
obj.q = obj.q./1000; |
|||
%% PREDICTED PERFORMANCE |
|||
Vx = max(obj.V); |
|||
Mx = max(obj.M); |
|||
Yx = max(obj.y); |
|||
Xx = max(obj.x); |
|||
tx = max(obj.t); |
|||
Qx = max(obj.q); |
|||
|
|||
[valx,idxx] = max(obj.x); |
|||
[valy,idxy] = max(obj.y); |
|||
tX = obj.t(idxx); |
|||
tY = obj.t(idxy); |
|||
|
|||
disp(' '); |
|||
formatSpec = 'Apogee is %6.3f m occuring at %5.3f seconds.\n'; |
|||
fprintf(formatSpec,Yx,tY) |
|||
formatSpec = 'Landing Distance is %6.3f m occuring at %5.3f seconds.\n\n'; |
|||
fprintf(formatSpec,Xx,tX) |
|||
end |
|||
|
|||
% Write data file |
|||
function WriteDataFile(obj) |
|||
if obj.mdot_constant == true |
|||
result_dat_file = obj.ID + "_Result_" + obj.launch_angle + "deg.txt"; |
|||
else |
|||
text = "VariableMassFlow"; |
|||
result_dat_file = obj.ID + "_Result_" + obj.launch_angle + "_deg_" + text + ".txt"; |
|||
end |
|||
result_matrix = [obj.t obj.x/1000 obj.y/1000 obj.M obj.thrust obj.DvDt obj.m obj.mdot obj.isp]; |
|||
result_data = reshape(result_matrix, [], 9); |
|||
dlmwrite(result_dat_file, 'Time(s),x(km),y(km),Mach,Thrust(N),Acceleration(m/s2),Mass(kg),mdot(kg/s),Isp (s)','delimiter','') |
|||
dlmwrite(result_dat_file, result_data, '-append', 'delimiter', ','); |
|||
end |
|||
end |
|||
end |
|||
@ -0,0 +1,8 @@ |
|||
Mach CA |
|||
0 0.41 |
|||
0.1 0.41 |
|||
0.5 0.347 |
|||
0.8 0.328 |
|||
0.95 0.347 |
|||
1.1 0.441 |
|||
1.2 0.434 |
|||
@ -1,2 +1,12 @@ |
|||
# 2-DoF-TrajectorySim |
|||
## 2-DoF Rocket Trajectory Simulation Program |
|||
This 2-DoF rocket trajectory simulation is reproduced from the Master's thesis by Zachary Doucet. The original code has been rewritten in a OOP form so that it can be reused in a simple manner for future trajectories of single-stage rockets. Drag interpolations are included as standalone files for each rocket since data format is non-similar in nature. |
|||
|
|||
A validation test has been made and compared against the 6-DoF software ASTOS, from which the results of the MAD rocket have been obtained. Figures shown below are the comparisons of the altitude, Mach number and the corrected thrust curve for both 2-DoF and 6-DoF simulations. |
|||
|
|||
 |
|||
|
|||
Input settings used for the 2-DoF simulation for validation are found in the MAD_Validation.m file. A similar workflow has now been created for the ICANSAT data to demonstrate code-reuseability. |
|||
|
|||
Comments: |
|||
1. Numerical calculations are adapted based on the Angle_Tests_XY.m program used in the original code by Zachery Doucet. |
|||
2. Launch tower deflection is not included. |
|||
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