a PowerPoint presentation for a 100 level coding class for some reason

1. Satellite Constellation Access to Ground Station
Access analysis between a ground station and conical sensors.
The satellites’ conical sensors work interchangeably with the ground
station if the ground station is within conical sensors’ field of view.
Sensors’ elevation is no greater than the allowed minimum angle.
Sampling a scenario of a constellation of 40 satellites photographing a
geological site (42.3001 North and 71.3504 West) on 6-hour intervals.
Workflow:
1. Create a Satellite Scenario
2. Add Satellites to the Satellite Scenario
3. Add Cameras to the Satellites
4. Define the Geographical Site to be Photographed in the Satellite
Scenario
5. Add Access Analysis between the Cameras and the Geographical Site
6. Visualize the Scenario
7. Visualize the Camera’s Field of View
8. Customize the Visualization
9. Determine the Times when the Camera can photograph the Site
10. Calculate System-Wide Access Percentage
11. Improve Percentage by camera-tracking the site

2. Modified Code
1. Change the date of the
SatelliteScenario
2. Change the latitude
and longitude of the
geological site from
default to Area 51
3. Add cameras to
satellite #40, #17, and
#1
4. Change the color of
the contact line to
yellow
5. Change the field of
view contour so
they’re no longer

3. Analyze Access between a Satellite Constellation
and an Aircraft
This reference application gives example of how to model and visualize a mission scenario of the WalkerDelta method of
satelliteScenario Object interact with an aircraft
Workflow:
Define Mission Start Date and Duration
Load the Aircraft Trajectory
Add the Aircraft to a New Satellite Scenario
Add a Walker-Delta Constellation to the
Satellite Scenario
Add Sensors to the Constellation
Configure the Constellation to Point at the
Aircraft
Determine the Satellite-to-Aircraft Access
Intervals
Calculate System-Wide Access Percentage
Animate the Satellite Scenario

4. Create
Satellite
Scenario
Assume that the
path through the
large
constellation to
establish access
between two
ground stations
must be
determined as of
10 December
2021, 6:27:57
PM UTC
Multi-Hop Path Selection Through Large Satellite
Constellation
This reference application shows how to determine the path through a large constellation consisting of 1000 low-Earth orbit (LEO)
satellites to access between 2 ground stations, then how to calculate the intervals of 3-hour period on this path.
Add Large
Constellation of
Satellites
large satellite
constellation from
the Two-Line-
Element (TLE) file
consists of 1,000 LEO
satellites.
Work Flow
1. Define the
satellite
constellation.
2. Define the
source and
destination nodes.
3. Find the
shortest path
between the
source and
destination nodes.
4. Verify the path's
reliability.

5. Modified Code
Error in project4 (line 114)
nodes = [nodes, sat(id)];
Error in project4 (line 74)
nodes = [nodes, gsTarget];
startTime = datetime(2023, 5, 13, 10, 0, 0);
stopTime = startTime + hours(4);
sampleTime = 30;
sc = satelliteScenario(startTime, stopTime, sampleTime, "AutoSimulate", false);
sat = satellite(sc, "largeConstellation.tle");
numSatellites = numel(sat);
gsSource = groundStation(sac, 42.3601, -71.0589, ...
"Name", "Source Ground Station");
gsTarget = groundStation(sc, 37.7749, -122.4194, ...
"Name", "Target Ground Station");
advance(sc);
[~, elSourceToSat] = aer(gsSource, sat);
[~, elTargetToSat] = aer(gsTarget, sat);
elSourceToSatGreaterThanOrEqual30 = (elSourceToSat >= 30)';
elTargetToSatGreaterThanOrEqual30 = (elTargetToSat >= 30)';
trueID = find(elSourceToSatGreaterThanOrEqual30 == true);
[~, ~, r] = aer(sat(trueID), gsTarget);

6. Modified Code
[~, minRangeID] = min(r);
id = trueID(minRangeID);
nodes = {gsSource, sat(id)};
earthRadius = 6378137; altitude = 800000;
% meters
horizonElevationAngle = asind(earthRadius / (earthRadius + altitude)) - 90; minSatElevation = -10; pathFound
= false;
while ~pathFound
idCurrent = id;
if elTargetToSatGreaterThanOrEqual30(idCurrent)
nodes = [nodes, {gsTarget}];
pathFound = true;
continue
end
[~, els] = aer(sat(idCurrent), sat);
els(idCurrent) = -90;
s = els >= minSatElevation;
trueID = find(s == true);
[~, ~, r] = aer(sat(trueID), gsTarget);
[~, minRangeID] = min(r);
id = trueID(minRangeID);
nodes = [nodes(:)', {sat(id)}];
end

7. Modified Code
sc.AutoSimulate = true;
ac = access(nodes{:});
ac.LineColor = "red";
intvls = accessIntervals(ac);
v = satelliteScenarioViewer(sc, "ShowDetails", false);
sat.MarkerSize = 6; % Pixels
campos(v, 60, 5); % Latitude and longitude in degrees
play(sc);

8. Visualization
In this modified code, the start time is set to May 13, 2023, at 10:00:00 AM UTC, and the stop time is four hours later, at 2:00:00 PM
UTC. The sample time is set to 30 seconds.
The latitude and longitude values for the source and target ground stations are updated with approximate coordinates for Boston

9. Display Flight Trajectory Data Using Flight Instruments and Flight Animation
This toolbox is about displaying flight trajectory data using flight
instruments and flight animation. The code in the link uses the
Aerospace Toolbox to load flight trajectory data, create flight
instruments, and animate the flight trajectories. The flight
instruments can be used to display information about the flight,
such as the altitude, speed, and heading. The flight animation
can be used to visualize the flight trajectory.
Workflow:
1. Load the flight trajectory data.
2. Create the flight instruments.
3. Animate the flight trajectories.
4. Display the flight instruments
and the flight animation.

10. Modified Code
Error in LiveEditorEvaluationHelperE570995280 (line 41)
sl.ValueChangingFcn = @(sl, event) flightInstrumentsAnimationCallback(fig, simdata, h, event);
load('simdata.mat');
yaw = simdata(:, 7);
yaw(yaw < 0) = yaw(yaw < 0) + 2 * pi;
simdata(:, 7) = yaw;
h = Aero.Animation;
h.createBody('pa24-250_blue.ac', 'Ac3d');
h.Bodies{1}.TimeSeriesSource = simdata;
h.Camera.PositionFcn = @staticCameraPosition;
h.Figure.Position(1) = h.Figure.Position(1) + 572/2;
h.updateBodies(simdata(1, 1));
h.updateCamera(simdata(1, 1));
h.show();
fig = uifigure('Name', 'Flight Instruments', ...
'Position', [h.Figure.Position(1) - 572, h.Figure.Position(2) + h.Figure.Position(4) - 502, 572, 502],
...
'Color', [0.2667 0.2706 0.2784], 'Resize', 'off');
fig.Visible = "off";
imgPanel = imread('FlightInstrumentPanel.png');
ax = uiaxes('Parent', fig, 'Visible', 'off', 'Position', [10 30 530 460], ...
'BackgroundColor', [0.2667 0.2706 0.2784]);
image(ax, imgPanel);
disableDefaultInteractivity(ax);

11. Modified Code
Error in LiveEditorEvaluationHelperE570995280 (line 41)
sl.ValueChangingFcn = @(sl, event) flightInstrumentsAnimationCallback(fig, simdata, h, event);
alt = uiaeroaltimeter('Parent', fig, 'Position', [369 299 144 144]);
head = uiaeroheading('Parent', fig, 'Position', [212 104 144 144]);
air = uiaeroairspeed('Parent', fig, 'Position', [56 299 144 144]);
air.Limits = [25 250];
air.ScaleColorLimits = [0, 60; 50, 200; 200, 225; 225, 250];
hor = uiaerohorizon('Parent', fig, 'Position', [212 299 144 144]);
climb = uiaeroclimb('Parent', fig, 'Position', [369 104 144 144]);
climb.MaximumRate = 8000;
turn = uiaeroturn('Parent', fig, 'Position', [56 104 144 144]);
sl = uislider('Parent', fig, 'Limits', [simdata(1, 1) simdata(end, 1)], 'FontColor',
'white');
sl.Position = [50 60 450 3];
sl.ValueChangingFcn = @(sl, event) flightInstrumentsAnimationCallback(fig, simdata, h,
event);
lbl = uilabel('Parent', fig, 'Text', ['Time: ' num2str(sl.Value, 4) ' sec'], 'FontColor',
'white');
lbl.Position = [230 10 90 30];
fig.Visible = "on";

12. Visualization
The modified code generates a flight instrument panel with vertical indicators for altitude, heading, airspeed, horizon, climb rate, and
turn rate. The panel is integrated with the Aero.Animation object that loads and displays the 'pa24-250_orange.ac' model with
adjusted 'simdata' time series. The uislider allows you to control the animation time, and the uilabel displays the current time value.

13. Modeling Satellite Constellations Using Ephemeris Data
A tool for modeling satellite constellations using ephemeris
data. Ephemeris data is information about the position and
velocity of a satellite at a given time. The application uses this
data to create a model of the satellite constellation, which can
then be used to simulate the behavior of the constellation. The
application has a number of features that make it useful for
modeling satellite constellations. These features include:
1. The ability to import ephemeris data from a variety of
sources.
2. The ability to visualize the satellite constellation in 3D.
3. The ability to simulate the behavior of the satellite
constellation over time.
4. The ability to analyze the performance of the satellite
constellation.

14. Modified Code
Error in project5 (line 19)
geoscatter([gsUS.Latitude gsDE.Latitude gsIN.Latitude], ...
mission.StartDate = datetime(2023, 11, 30, 22, 23, 24);
mission.Duration = hours(24);
mission.ConstellationDefinition = table( ...
29599.8e3 * ones(24,1), ... % Semi-major axis (m)
0.0005 * ones(24,1), ... % Eccentricity
56 * ones(24,1), ... % Inclination (deg)
350 * ones(24,1), ... % Right ascension of the ascending node (deg)
sort(repmat([0 120 240], 1,8))', ... % Argument of periapsis (deg)
[0:45:315, 15:45:330, 30:45:345]', ... % True anomaly (deg)
'VariableNames', ["a (m)", "e", "i (deg)", ...
"Ω (deg)", "ω (deg)", "ν (deg)"]);
mission.ConstellationDefinition
mission.Ephemeris = load("SatelliteScenarioEphemerisData.mat", "TimeseriesPosITRF",
"TimeseriesVelITRF");
mission.Ephemeris.TimeseriesPosITRF
mission.Ephemeris.TimeseriesVelITRF
scenario = satelliteScenario(mission.StartDate, mission.StartDate + hours(24), 60);
sat = satellite(scenario, mission.Ephemeris.TimeseriesPosITRF, mission.Ephemeris.TimeseriesVelITRF,
...
CoordinateFrame="ecef", Name="GALILEO " + (1:24))
disp(scenario)

15. Modified Code
Error in project5 (line 19)
geoscatter([gsUS.Latitude gsDE.Latitude gsIN.Latitude], ...
timetable(...
datetime(getabstime(mission.Ephemeris.TimeseriesPosITRF), Locale="en_US"), ...
squeeze(mission.Ephemeris.TimeseriesPosITRF.Data(1,:,:))', ...
squeeze(mission.Ephemeris.TimeseriesPosITRF.Data(2,:,:))', ...
squeeze(mission.Ephemeris.TimeseriesPosITRF.Data(3,:,:))',...
VariableNames=["Satellite_1", "Satellite_2", "Satellite_3"])
set(sat(1:8), MarkerColor="#FF6929");
set(sat(9:16), MarkerColor="#139FFF");
set(sat(17:24), MarkerColor="#64D413");
orbit = [sat(:).Orbit];
set(orbit(1:8), LineColor="#FF6929");
set(orbit(9:16), LineColor="#139FFF");
set(orbit(17:24), LineColor="#64D413");
gsUS = groundStation(scenario, 37.2350, -115.7930, ...
MinElevationAngle=10, Name="Area 51");
gsUS.MarkerColor = "red";
gsDE = groundStation(scenario, 48.23206, 11.68445, ...
MinElevationAngle=10, Name="Munchen");
gsDE.MarkerColor = "red";
gsIN = groundStation(scenario, 35.6895, 139.6917, ...
MinElevationAngle=10, Name="Tokyo");
gsIN.MarkerColor = "red";

16. Modified Code
Error in project5 (line 19)
geoscatter([gsUS.Latitude gsDE.Latitude
gsIN.Latitude], ...
figure
geoscatter([gsUS.Latitude gsDE.Latitude gsIN.Latitude], ...
[gsUS.Longitude gsDE.Longitude gsIN.Longitude], "yellow", "filled")
geolimits([-75 75], [-180 180])
title("Ground Stations")
accessUS = access(gsUS, sat);
accessDE = access(gsDE, sat);
accessIN = access(gsIN, sat);
set(accessUS, LineWidth="1");
set(accessUS(1:8), LineColor="#FF6929");
set(accessUS(9:16), LineColor="#139FFF");
set(accessUS(17:24), LineColor="#64D413");
set(accessDE, LineWidth="1");
set(accessDE(1:8), LineColor="#FF6929");
set(accessDE(9:16), LineColor="#139FFF");
set(accessDE(17:24), LineColor="#64D413");
set(accessIN, LineWidth="1");
set(accessIN(1:8), LineColor="#FF6929");
set(accessIN(9:16), LineColor="#139FFF");
set(accessIN(17:24), LineColor="#64D413");
Error in project5 (line 43)
show(sat.Orbit)

17. Modified Code
Error in project5 (line 19)
geoscatter([gsUS.Latitude gsDE.Latitude
gsIN.Latitude], ...
intervalsUS = accessIntervals(accessUS);
intervalsUS = sortrows(intervalsUS, "StartTime", "ascend")
intervalsDE = accessIntervals(accessDE);
intervalsDE = sortrows(intervalsDE, "StartTime", "ascend")
intervalsIN = accessIntervals(accessIN);
intervalsIN = sortrows(intervalsIN, "StartTime", "ascend")
viewer3D = satelliteScenarioViewer(scenario, ShowDetails=false);
show(sat.Orbit);
gsUS.ShowLabel = true;
gsUS.LabelFontSize = 11;
gsDE.ShowLabel = true;
gsDE.LabelFontSize = 11;
gsIN.ShowLabel = true;
gsIN.LabelFontSize = 11;
[statusUS, timeSteps] = accessStatus(accessUS);
statusDE = accessStatus(accessDE);
statusIN = accessStatus(accessIN);
% Sum cumulative access at each timestep
statusUS = sum(statusUS, 1);
statusDE = sum(statusDE, 1);
statusIN = sum(statusIN, 1);

18. Modified Code
Error in project5 (line 19)
geoscatter([gsUS.Latitude gsDE.Latitude
gsIN.Latitude], ...
subplot(3,1,1);
stairs(timeSteps, statusUS);
title("51 to GALILEO")
ylabel("# of satellites")
subplot(3,1,2);
stairs(timeSteps, statusDE);
title("München to GALILEO")
ylabel("# of satellites")
subplot(3,1,3);
stairs(timeSteps, statusIN);
title("Tokyo to GALILEO")
ylabel("# of satellites")
statusTable = [table(height(intervalsUS), height(intervalsDE), height(intervalsIN)); ...
table(sum(intervalsUS.Duration)/3600, sum(intervalsDE.Duration)/3600,
sum(intervalsIN.Duration)/3600); ...
table(mean(intervalsUS.Duration/60), mean(intervalsDE.Duration/60),
mean(intervalsIN.Duration/60)); ...
table(mean(statusUS, 2), mean(statusDE, 2), mean(statusIN, 2)); ...
table(min(statusUS), min(statusDE), min(statusIN)); ...
table(max(statusUS), max(statusDE), max(statusIN))];
statusTable.Properties.VariableNames = ["Area 51", "München", "Tokyo"];
statusTable.Properties.RowNames = ["Total # of intervals", "Total interval time (hrs)",...
"Mean interval length (min)", "Mean # of satellites in view", ...
"Min # of satellites in view", "Max # of satellites in view"];
statusTable

19. Visualization
The modified code change the location of the ground station and the numbers of GALILEO satellites to 26

20. Project 6 - Create Scenario for 40 Satellites to track 5 Geological Sites
Using Satellite Constellation
Access to Ground Station
application. I’m trying to
visualize intelligence gathering
using satellites on various
countries that are considered
hostels to the United States
national defense strategies.
Workflow:
Create a Satellite Scenario
Add Satellites to the Satellite Scenario
Add Cameras to the Satellites
Define the Geographical Site to be
Photographed in the Satellite Scenario
Add Access Analysis between the Cameras
and the Geographical Site
Visualize the Scenario
Visualize the Camera’s Field of View
Customize the Visualization
Determine the Times when the Camera can
photograph the Site
Calculate System-Wide Access Percentage
Improve Percentage by camera-tracking
the site

21. Modified Code
startTime = datetime(1945,8,9,6,0,0);
stopTime = startTime + hours(6);
sampleTime = 30;
sc = satelliteScenario(startTime,stopTime,sampleTime)
tleFile = "leoSatelliteConstellation.tle";
sat = satellite(sc,tleFile)
names = sat.Name + " Camera";
cam = conicalSensor(sat,"Name",names,"MaxViewAngle",90)
name = "Geological Site 1";
minElevationAngle = 30; % degrees
geoSite = groundStation(sc, ...
"Name",name, ...
"MinElevationAngle",minElevationAngle, "Latitude",40.712742,"Longitude",-
74.013382)

22. Modified Code
name = "Geological Site 2";
minElevationAngle = 30; % degrees
geoSite = groundStation(sc, ...
"Name",name, ...
"MinElevationAngle",minElevationAngle, "Latitude",34.3853,"Longitude",132.4553)
name = "Geological Site 3";
minElevationAngle = 30; % degrees
geoSite = groundStation(sc, ...
"Name",name, ...
"MinElevationAngle",minElevationAngle, "Latitude",55.7558,"Longitude",37.6173)
name = "Geological Site 4";
minElevationAngle = 30; % degrees
geoSite = groundStation(sc, ...
"Name",name, ...
"MinElevationAngle",minElevationAngle, "Latitude",39.0738,"Longitude",125.8198)

23. Modified Code
name = "Geological Site 5";
minElevationAngle = 30; % degrees
geoSite = groundStation(sc, ...
"Name",name, ...
"MinElevationAngle",minElevationAngle,
"Latitude",39.9042,"Longitude",116.4074)
ac = access(cam,geoSite);
ac(1)
v = satelliteScenarioViewer(sc,"ShowDetails",false);
sat(4).ShowLabel = true;
sat(40).ShowLabel = true;
sat(1).ShowLabel = true;
sat(17).ShowLabel = true;
geoSite.ShowLabel = true;
show(sat(4))
show(sat(40))
show(sat(1))
show(sat(17))

24. Modified Code
fov = fieldOfView(cam([cam.Name] == "Satellite 3 Camera"))
fov = fieldOfView(cam([cam.Name] == "Satellite 2 Camera"))
fov = fieldOfView(cam([cam.Name] == "Satellite 15 Camera"))
fov = fieldOfView(cam([cam.Name] == "Satellite 23 Camera"))
fov = fieldOfView(cam([cam.Name] == "Satellite 17 Camera"))
fov = fieldOfView(cam([cam.Name] == "Satellite 12 Camera"))
fov = fieldOfView(cam([cam.Name] == "Satellite 10 Camera"))
fov = fieldOfView(cam([cam.Name] == "Satellite 7 Camera" ))
fov = fieldOfView(cam([cam.Name] == "Satellite 4 Camera"))
fov = fieldOfView(cam([cam.Name] == "Satellite 40 Camera"))
ac.LineColor = 'red';
accessIntervals(ac)
for idx = 2:numel(ac)
[s,time] = accessStatus(ac(idx));
if idx == 1
systemWideAccessStatus = s;
else
systemWideAccessStatus = or(systemWideAccessStatus,s);
end
end

25. Modified Code
plot(time,systemWideAccessStatus,"LineWidth",2);
grid on;
xlabel("Time");
ylabel("System-Wide Access Status");
n = nnz(systemWideAccessStatus)
systemWideAccessDuration = n*sc.SampleTime % seconds
scenarioDuration = seconds(sc.StopTime - sc.StartTime)
systemWideAccessPercentage = (systemWideAccessDuration/scenarioDuration)*100
pointAt(sat,geoSite)
for idx = 1:numel(ac)
[s,time] = accessStatus(ac(idx));
if idx == 1
systemWideAccessStatus = s;
else
systemWideAccessStatus = or(systemWideAccessStatus,s);
end
end
n = nnz(systemWideAccessStatus);
systemWideAccessDuration = n*sc.SampleTime;
systemWideAccessPercentageWithTracking = (systemWideAccessDuration/scenarioDuration)*10

26. Visualization
The modified code change the location of the default ground stations to
other five locations located in New York City, Moscow, Hiroshima, Beijing
and Pyongyang. These satellites have an elevation angles specified
where to point their cameras. Cameras 4, 40, 1 and 17 are shown to
allowed to track when they’re close to the “geological sites”