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Anson Biggs 2021-12-06 19:22:12 -07:00
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index.html
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@ -130,43 +130,6 @@
</div> </div>
</section> </section>
<hr /> <hr />
<section>
<div class="container">
<div class="row align-items-center">
<div class="col-xl-8">
<div class="p-1">
<embed
type="text/html"
src="helpers/opdem.html"
width="100%"
style="min-height: 60vh"
/>
</div>
</div>
<div class="col-xl-4">
<div>
<h2 class="display-4">Operational Demonstration Results</h2>
<p>
The experimental thrust curve shows that the four load cells
managed to match the thrust curve for the
<a href="https://www.thrustcurve.org/motors/Estes/F15/"
>Estes F15</a
>
within 6.2 Newton Seconds or 13.2% of expected. Due to
multiple changes in project and scope LANDER initially chose
very cheap load cells since the test stand demonstration was
originally mean't to be a verification for much larger goals.
Acquiring usable data from the load cells ended up taking much
more time and resources than the team initially expected, but
thanks to proper risk mitigation the team was able to overcome
the challenge and find a real solution.
</p>
</div>
</div>
</div>
</div>
</section>
<hr />
<section> <section>
<div class="container"> <div class="container">
<div class="row align-items-center"> <div class="row align-items-center">
@ -186,8 +149,10 @@
The fully assembled system and the CAD of the system can be The fully assembled system and the CAD of the system can be
seen on the figure to the right. LANDER consists of 5 seen on the figure to the right. LANDER consists of 5
subsystems, Control Software, Avionics, Control Mechanisms, subsystems, Control Software, Avionics, Control Mechanisms,
Structure, and Test Stand. The test stand involves a complex Structure, and Test Stand. These subsysems all come together
hardware in the loop computer simulation running on a to produce a test stand capable of simulating a vehicle
landing on the lunar surface. The test stand involves a
complex hardware in the loop computer simulation running on a
microcontroller. microcontroller.
</p> </p>
</div> </div>
@ -228,6 +193,43 @@
</div> </div>
</section> </section>
<hr /> <hr />
<section>
<div class="container">
<div class="row align-items-center">
<div class="col-xl-8">
<div class="p-1">
<embed
type="text/html"
src="helpers/opdem.html"
width="100%"
style="min-height: 60vh"
/>
</div>
</div>
<div class="col-xl-4">
<div>
<h2 class="display-4">Operational Demonstration Results</h2>
<p>
The experimental thrust curve shows that the four load cells
managed to match the thrust curve for the
<a href="https://www.thrustcurve.org/motors/Estes/F15/"
>Estes F15</a
>
within 6.2 Newton Seconds or 13.2% of expected. Due to
multiple changes in project and scope LANDER initially chose
very cheap load cells since the test stand demonstration was
originally mean't to be a verification for much larger goals.
Acquiring usable data from the load cells ended up taking much
more time and resources than the team initially expected, but
thanks to proper risk mitigation the team was able to overcome
the challenge and find a real solution.
</p>
</div>
</div>
</div>
</div>
</section>
<hr />
<section> <section>
<div class="container"> <div class="container">
<h2 class="display-4">Videos of the Operational Demonstration</h2> <h2 class="display-4">Videos of the Operational Demonstration</h2>