From 61ec132aeed71d7bfe0fdde3513189097b84f086 Mon Sep 17 00:00:00 2001
From: Joshua Drake <joshua.ellis.drake@gmail.com>
Date: Tue, 5 Nov 2024 03:19:56 -0600
Subject: Finished Electric Motor Section.

---
 introduction.tex | 10 ++++++++--
 1 file changed, 8 insertions(+), 2 deletions(-)

(limited to 'introduction.tex')

diff --git a/introduction.tex b/introduction.tex
index 58879b3..dcac94b 100644
--- a/introduction.tex
+++ b/introduction.tex
@@ -9,6 +9,7 @@ Motivation
 Objectives
 Questions Answered
 
+Hybrid electric aircraft present an attractive combination of energy density provided by the combustion of hydrocarbon fuels with the power density of batteries. The advantages conffered by energy density to the effectiveness of an aircraft are improved flight duration and efficiency, whereas power density allows for improved performance at takeoff and instantaneous power production. These benefits have motivated an increase in research into the field of hybrid electric aircraft.
 However, there is a distinct lack of practical knowledge
 associated with the physical construction of such systems. More
 public research in constructing distributed hybrid turbo-electric
@@ -17,8 +18,13 @@ detailing the real-world implementation of electrical systems,
 safety systems, experimental results, and mechanical–electrical
 powertrain interactions. These objectives are accomplished specifically through
 a relatively low voltage electrical system comprised of a pulley coupled generator, battery, distributed propulsors, and requsite mechanisms to enable safe operation. A second electrical configuration was implemented into the Cessna test rig \cite{melvincessna}to observe the transient performance of the mechainical elements of a turboelectic powertrain.
-\par
-The multifaceted nature of this work presents a unique opportunity to compare the disperate effects of two electrical configurations on the mechanical systems common to both, in addition to what has been gathered from their individual operation. Configuration one is more representative of real hybrid turboelectric aircraft by nature of its use of a battery and accompanying safety mechanisms, distributed propulsion, and full integration into an airframe. Thus, the results obtained from configuration one provides insight into the benefits afforded to hybrid turboelectric systems by the inclusion of batteries, the considerations necessarry to safely use these batteries, and the increased takeoff performance of electrically augmented aircraft. Configuration two presents a worst case scenario
+ \begin{figure}
+  \centering
+  \includegraphics[width=.7\textwidth]{img/cessna1.png}
+  \caption{\label{fig:cessna1}Cessna Test Rig with Wing Mounted Propulsors}
+ \end{figure}
+ \par
+The multifaceted nature of this work presents a unique opportunity to compare the disperate effects of two electrical configurations on the mechanical systems common to both, in addition to what has been gathered from their individual operation. Configuration one is more representative of real hybrid turboelectric aircraft by nature of its use of a battery and accompanying safety mechanisms, distributed propulsion, and full integration into an airframe. Thus, the results obtained from configuration one provides insight into the benefits afforded to hybrid turboelectric systems by the inclusion of batteries, the considerations necessarry to safely use these batteries, and the increased takeoff performance of electrically augmented aircraft. Configuration two presents a worst case scenario for the mechanical stresses induced through electric loading due to the system's lack of capacitance. This characteristic makes the effects of electrical loading on the turbine incredibly apparent, as all of the torque induced by the electrical system must be accounted for by the turbine engine.
 \par
 All sections pertaining to configuration one are recapitulated from research originally funded by the FAA and eventually published in ASME's Journal of Engineering for Gas Turbines and Power \cite{CessnaASME}. Similarly, sections over configuration two cover research funded by NASA. The author is pursuing publication of this work for presentation at ASME's 2025 Turboexpo Conference.
 % \begin{figure}
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