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<title>LANDER - Lunar Ascent and Descent of Excavation Resources</title>
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<h2 class="display-4">About LANDER</h2>
<p>
As interest in colonizing the Moon increases, developing a
sustainable method of transporting equipment and resources to
and from the lunar surface will be necessary. LANDER's
approach to this problem is a system that uses one thruster
capable of vectoring thrust to control vehicle attitude and
perform propulsive landings with minimal fuel use. However,
key to the design challenge is creating a suitable test
environment for such a system that can simulate variables,
such as lunar gravity and a lack of atmosphere. Project LANDER
endeavored to provide a potential solution by designing a
complex simulation utilizing live data. Due to an abbreviated
timetable and low-quality components, LANDER did not meet all
of its requirements for the Thrust Vector Control Test and
Operational Demonstration. However, while LANDER was a
proofâof-concept system, the team hopes to lay the foundation
for future development in this area.
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<h2 class="display-4">Test Stand Setup</h2>
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The fully assembled system and the CAD of the system can be
seen on the figure to the right. LANDER consists of 5
subsystems, Control Software, Avionics, Control Mechanisms,
Structure, and Test Stand. These subsysems all come together
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.
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<h2 class="display-4">Software Concept of Operations</h2>
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The simulated vehicle comprises a feedback loop where the
rocket motor causing forces on load cells translates to forces
in the simulation. The control system utilizes a
<abbr
title="proportionalâintegralâderivative controller is a control loop mechanism for driving an error in state (vehicle deflection) to zero."
>PID</abbr
>
which gives commands to the simulated vehicle; the commands
are then translated back into hardware as TVC commands. The
physical vehicle encompasses the avionics, TVC, and load
cells. The physical vehicle receives commands from the
simulated vehicle and returns, calculated thrust data back to
the control software.
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<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.
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<h2 class="display-4">Videos of the Operational Demonstration</h2>
<p style="font-style: italic">The Grand Finale</p>
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<h1 class="display-4">Final Report</h1>
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At the conclusion and verification of the Operational
Demonstration LANDER has compiled a Final Report for the project.
The Final Report compiles two semesters of work into one succinct
document that highlights all of the findings from the project.
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