We
outlined the methodology for converting a small turbojet engine
to operate on hydrogen and an aircraft design to incorporate the
modified engine and corresponding fuel system into a radio controlled
aircraft.
We addressed:
- engine modification
procedures
- a method for
lubricating the engine
- mass flow
rate conversions
- hydrogen
tank selection
- thrust stand
design
- engine testing
procedures
- aircraft
design principles
- aircraft
size determination methods
- aircraft
materials selection
- an aircraft
drawing package
- aircraft
parts list
- basic hydrogen
safety
Three main aspects
of the aircraft design included powertrain, aerodynamics and structures.
- The most
important aspect we considered when modifying the turbojet engine
was the mass flow rate of hydrogen required to provide the same
performance characteristics as an engine operating on conventional
kerosene fuel.
- The aerodynamic
aspects of the MATCH aircraft were tailored specifically to provide
the highest efficiency without complicating the construction
process. Model aircraft design research provided insight into
the size and placement for the control surfaces.
- The structural
aspect of this project was the most important in terms of design
considerations. In order to ensure our aircraft would be structurally
sound, multiple stress calculations were performed. The materials
for the various parts of the aircraft were selected based on
materials properties, weight and cost.
Our second project
objective, to design a radio controlled aircraft to be powered
by a
model turbojet engine, has been successfully completed. The completion of the
remainder of this project is feasible and we look forward to beginning modification and
construction in January 2006.
We will complete
our modification and construction processes according to the following
outline:
- Build thrust
stand
- Test engine
operating on kerosene
- Test engine
operating on hydrogen
- Construct
aircraft
- Integrate
engine into aircraft.
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The
major accomplishments and technical results of the project
to date are summarized below:
Powertrain
- A
turbojet engine has been selected.
- The
mass flow rate of hydrogen through the engine has
been determined.
- The
amount of hydrogen needed to operate the engine at
the desired conditions has been determined.
- A
hydrogen storage tank has been selected.
- An
outline for the conversion process has been written.
- A
thrust stand design has been finalized.
- A
thrust testing procedure has been finalized.
Aerodynamics
- The
final design of the main wing, horizontal stabilizer
and vertical stabilizer have been drawn in Pro-E.
- The
takeoff distance and takeoff velocity for the aircraft
have been determined.
- The
planform area, chord, wingspan, dihedral and aspect
ratio for the main wing have been determined based
on takeoff distance.
- The
planform area, chord, span, taper and aspect ratio
for the horizontal and vertical stabilizer have been
determined based on stability.
Structures
- The
materials for the main wing, including ribs, spars
and wing attachment box have been determined.
- The
materials for the fuselage have been determined.
- The
materials for the tail have been selected and an
attachment method has been determined.
- The
landing gear has been selected and an attachment
method has been determined.
- A
mounting procedure for the engine, fuel tank, pressure
regulator, mass flow controller and oil tank have
been determined.
- All
stress calculations have been performed on materials
selected to determine their suitability for the project.
Electrical
- All
servos have been selected.
- Placement
of all servos has been determined
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