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Anson Biggs 2021-12-07 19:13:08 -07:00
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css/custom.css
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@ -20,7 +20,7 @@ header div img {
margin-top: 5vh; margin-top: 5vh;
} }
@media (max-width: 992px) { /* @media (max-width: 992px) {
.p-5 { .p-5 {
padding: 3rem; padding: 3rem;
padding-bottom: 1rem; padding-bottom: 1rem;
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div.col-lg-6 { div.col-lg-6 {
text-align: center; text-align: center;
} }
} } */
a { a {
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index.html
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@ -80,7 +80,7 @@
</nav> </nav>
<header class="text-center"> <header class="text-center">
<div class="container"> <div class="container">
<img src="img/logo.png" class="img-fluid" alt="LANDER Logo" /> <img src="img/logo.png" class="img-fluid" alt="LANDER Team Logo" />
</div> </div>
<a class="scroll" href="#scroll" <a class="scroll" href="#scroll"
><img src="img/chevrons-down.svg" style="width: 75px" ><img src="img/chevrons-down.svg" style="width: 75px"
@ -96,20 +96,21 @@
<p> <p>
As interest in colonizing the Moon increases, developing a As interest in colonizing the Moon increases, developing a
sustainable method of transporting equipment and resources to sustainable method of transporting equipment and resources to
and from the lunar surface will be necessary. LANDER's and from the lunar surface will be necessary. LANDER’s
approach to this problem is a system that uses one thruster approach to this problem is a system that uses one thruster
capable of vectoring thrust to control vehicle attitude and capable of vectoring thrust to control vehicle attitude and
perform propulsive landings with minimal fuel use. However, perform propulsive landings with minimal fuel use. The key to
key to the design challenge is creating a suitable test the design challenge is creating a suitable test environment
environment for such a system that can simulate variables, for a system that can simulate variables such as lunar gravity
such as lunar gravity and a lack of atmosphere. Project LANDER and a lack of atmosphere while on Earth. Project LANDER
endeavored to provide a potential solution by designing a endeavored to provide a potential solution by designing a
complex simulation utilizing live data. Due to an abbreviated complex simulation utilizing live data from a
timetable and low-quality components, LANDER did not meet all hardware-in-the-loop system. Unfortunately, due to an
of its requirements for the Thrust Vector Control Test and abbreviated timetable and low-quality components, LANDER did
Operational Demonstration. However, while LANDER was a not meet all its requirements for a successful Operational
proof–of-concept system, the team hopes to lay the foundation Demonstration. However, LANDER was a proof-of-concept system,
for future development in this area. and the team hopes to lay the foundation for future
development in this area.
</p> </p>
</div> </div>
</div> </div>
@ -137,13 +138,13 @@
<div> <div>
<h2 class="display-4">Test Stand Setup</h2> <h2 class="display-4">Test Stand Setup</h2>
<p> <p>
The fully assembled system and the CAD of the system can be The fully assembled system and the system's CAD can be seen in
seen on the figure to the right. LANDER consists of 5 the following figure. LANDER consists of 5 subsystems, Control
subsystems, Control Software, Avionics, Control Mechanisms, Software, Avionics, Control Mechanisms, Structure, and Test
Structure, and Test Stand. These subsysems all come together Stand. These subsystems all come together to produce a test
to produce a test stand capable of simulating a vehicle stand capable of simulating a vehicle landing on the lunar
landing on the lunar surface. The test stand involves a surface. The test stand involves a complex
complex hardware in the loop computer simulation running on a hardware-in-the-loop computer simulation running on a
microcontroller. microcontroller.
</p> </p>
</div> </div>
@ -153,7 +154,7 @@
<img <img
class="img-fluid" class="img-fluid"
src="img/assemblyCAD.png" src="img/assemblyCAD.png"
alt="Picture of people gathered at an SAE International Event" alt="Picture of the assembled test stand vehicle next to the CAD of the vehicle."
/> />
</div> </div>
</div> </div>
@ -175,12 +176,11 @@
title="proportional–integral–derivative controller is a control loop mechanism for driving an error in state (vehicle deflection) to zero." title="proportional–integral–derivative controller is a control loop mechanism for driving an error in state (vehicle deflection) to zero."
>PID</abbr >PID</abbr
> >
which gives commands to the simulated vehicle; the commands that gives the simulated vehicle commands; the commands are
are then translated back into hardware as TVC commands. The then rendered into hardware as TVC commands. The physical
physical vehicle encompasses the avionics, TVC, and load vehicle encompasses the avionics, TVC, and load cells. The
cells. The physical vehicle receives commands from the physical vehicle receives commands from the simulated vehicle
simulated vehicle and returns, calculated thrust data back to and returns calculated thrust data to the control software.
the control software.
</p> </p>
</div> </div>
</div> </div>
@ -189,7 +189,7 @@
<img <img
class="img-fluid" class="img-fluid"
src="img/conops.png" src="img/conops.png"
alt="Picture of people gathered at an SAE International Event" alt="Concept of Operations for the LANDER software and hardware control loop."
/> />
</div> </div>
</div> </div>
@ -205,18 +205,21 @@
<h2 class="display-4">Operational Demonstration Results</h2> <h2 class="display-4">Operational Demonstration Results</h2>
<p> <p>
The experimental thrust curve shows that the four load cells The experimental thrust curve shows that the four load cells
managed to match the thrust curve for the matched the thrust curve for the
<a href="https://www.thrustcurve.org/motors/Estes/F15/" <a href="https://www.thrustcurve.org/motors/Estes/F15/"
>Estes F15</a >Estes F15</a
> >
within 6.2 Newton Seconds or 13.2% of expected. Due to within 6.2 Newton Seconds or 13.2% of expected. Unfortunately,
multiple changes in project and scope LANDER initially chose due to multiple changes in project and scope, LANDER initially
very cheap load cells since the test stand demonstration was chose very cheap load cells since the test stand demonstration
originally mean't to be a verification for much larger goals. originally only served as verification for much more extensive
Acquiring usable data from the load cells ended up taking much goals, such as an actual propulsive landing. Therefore,
more time and resources than the team initially expected, but acquiring usable data from the load cells took much more time
thanks to proper risk mitigation the team was able to overcome and resources than the team initially expected. This time sink
the challenge and find a real solution. could have easily been mitigated if the team had spent more
money on load cells to handle the new mission profile.
However, the team overcame the challenge thanks to proper risk
mitigation.
</p> </p>
</div> </div>
</div> </div>
@ -291,9 +294,10 @@
<h1 class="display-4">Final Report</h1> <h1 class="display-4">Final Report</h1>
<p class="lead"> <p class="lead">
At the conclusion and verification of the Operational At the conclusion and verification of the Operational
Demonstration LANDER has compiled a Final Report for the project. Demonstration, LANDER has compiled a Final Report for the project.
The Final Report compiles two semesters of work into one succinct The Final Report compiles two semesters of work into one succinct
document that highlights all of the findings from the project. document that highlights all of the findings from the project.
Open FinalReport.pdf
</p> </p>
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