connor/thesis
1
0
Fork 0
Code Issues Pull Requests Actions Packages Projects Releases Wiki Activity

Maybe nearing the final commit

Browse Source
This commit is contained in:
Connor
2022-04-18 10:59:25 -06:00
parent 0fb875c777
commit 5b6656a9a6
3598 changed files with 79349 additions and 572 deletions
Download Patch File Download Diff File Expand all files Collapse all files

54
LaTeX/results.tex
View File

@@ -101,6 +101,47 @@
\item EVVJS
\end{itemize}
For each of these trajectories, the optimization algorithm was run. During the MBH phase
of the optimization algorithm, anytime a new ``basin best'' mission was discovered, it
was recorded. The resultant cost function values of each of those discovered missions
can be found in the table below:
\begin{table}[H]
\centering
\begin{adjustbox}{height=0.3\textheight}
\begin{tabular}{ | c c c c | }
\hline
\bfseries Flyby Selection &
\bfseries Cost Function Value &
\bfseries Flyby Selection &
\bfseries Cost Function Value \\
\hline
EMS & 0.64797 & EMJS & 0.66014 \\
EMS & 0.68828 & EMS & 0.69704 \\
EMJS & 0.74576 & EMJS & 0.79745 \\
EMJS & 0.80372 & EMJS & 0.82510 \\
EMMJS & 0.91149 & EMJS & 0.94148 \\
EMJS & 0.96141 & EMS & 1.02972 \\
EJS & 1.12848 & ES & 1.23167 \\
EVMS & 1.32600 & EMS & 1.32879 \\
EMS & 1.33779 & EMJS & 1.39527 \\
EVMS & 1.41517 & EVMS & 1.45960 \\
EVMS & 1.46649 & EVMS & 1.52207 \\
EVMS & 1.59234 & EVMJS & 1.66943 \\
EMS & 1.70295 & EMJS & 1.70438 \\
EMS & 1.78107 & EVVJS & 2.0106 \\
EMJS & 2.15952 & EJS & 2.16216 \\
EMJS & 2.22167 & EMMJS & 2.38431 \\
EMJS & 2.42457 & EMMJS & 2.46453 \\
EVVJS & 2.49257 & EMJS & 2.49485 \\
EVMS & 2.71118 & EMJS & 2.76812 \\
\hline
\end{tabular}
\end{adjustbox}
\caption{Table of resultant cost function values for every discovered mission}
\label{cost_fn_table}
\end{table}
\section{Faster, Less Efficient Trajectory}
In order to showcase the flexibility of the optimization algorithm (and the chosen cost
@@ -120,11 +161,14 @@
The mission begins in late June of 2024 and proceeds first to an initial gravity assist with
Mars after three and one half years to rendezvous in mid-December 2027. Unfortunately, the
launch energy required to effectively use the gravity assist with Mars at this time is
quite high. The $C_3$ value was found to be $60.4102 \frac{\text{km}^2}{\text{s}^2}$. However,
for this phase, the thrust magnitudes are quite low, raising slowly only as the spacecraft
approaches Mars, allowing for a nearly-natural trajectory to Mars rendezvous. Note also that
the in-plane thrust angle was neither zero nor $\pi$, implying that these thrusts were
steering thrusts rather than momentum-increasing thrusts.
quite high. The $C_3$ value was found to be $60.4102 \frac{\text{km}^2}{\text{s}^2}$. While
not as low as some of the other missions found to be very optimal, it should be noted that
missions with this $C_3$ and launch mass are still quite feasible.
However, for this phase, the thrust magnitudes are quite low, raising slowly only as the
spacecraft approaches Mars, allowing for a nearly-natural trajectory to Mars rendezvous.
Note also that the in-plane thrust angle was neither zero nor $\pi$, implying that these
thrusts were steering thrusts rather than momentum-increasing thrusts.
\begin{figure}[H]
\centering