AERONAUTICAL / AEROSPACE Supervisor: Dr Doug Auld Rm N310, Bldg J11, ph: 9351 2336 ; [email protected]1. DSMC computations of gas flow (subsonic flow boundary conditions) ion for smoke visualisation tunnel. 3. Experimental or CFD development and design of wind turbines 4. Validation of stalled aerofoil data All areas are wide ranging and hence allow the possibility of several students working in complementary topics in one of these areas. 2. M o d e l c o n s t r u c t
As you are aware UAVs are of great interest at the moment. The Aeronautics group at Sydney University has a long history of design and build experience in this field. Recent survey work has revealed that there is much interest in UAVs with a great variety of extreme performance. Rather than select one part of this design space we would like to start to create computational design tools that can facilitate a wide range of activity and performance. This software would include flight performance, control, aerodynamics and structural modules. For some of these the data is incomplete but we would nevertheless like to make a start. The task would involve scripting in Matlab or VB with as much data and analysis as we can get included.
Software to aid understanding of Structural Analysis in the High School Design and Technology curriculum Professor Grant Steven [email protected][email protected] e-mail for more information
The Australian Academy of Technological Sciences and Engineering (ATSE) have developed a very popular experimental laboratory in the renewable energy area which tours about 500 high schools each year. The STELR (www.stelr.org.au) Program is a hands-on, inquiry-based, in-curriculum program designed for Year 9 or Year 10 students, on the theme of global warming. They wish to develop material in the structural analysis area that aids students in the appreciation and understanding of this important subject in the area of design.
The research would comprise of looking at the High School curriculum and developing software that drives the Strand7 FEA engine to engender appreciation and encourage enquiry about how to make designs perform better.
The work would involving writing VB or Matlab script that generates GUIs and builds structures and examines the results. The Application Programming Interface (API) drives the Strand7 engine.
To undertake this important task you must enjoy programming and be interesting in the training of future engineers.
Design optimization for wing type structures that targets the ratio of bending to torsional stiffness (Honors project) Professor Grant Steven [email protected][email protected] Dr Gareth Vio [email protected] e-mail for more information
There are many strong reasons that the structure of a wing box is such that the ratio of the bending to the torsional stiffness achieve certain values. Traditionally this has never been studied from an optimization perspective and normally the bending stiffness is optimized and the torsional stiffness follows form this. In the past work has been done in the department that uses a process called Group Evolutionary Structural Optimization to maximize only the specific stiffness of structures, see some examples below. In the present research the same techniques will be used but with the very different objective as described in the title. There will be a significant coding activity in this project in the Matlab or VB driving an API for the Strand7 FEA code.
Simulating the Action of Sporting Equipment for Maximum Performance (Several potential honors projects) Professor Grant Steven [email protected][email protected] e-mail for more information
Long before Finite Element Analysis was developed, people were participating in sports and as competition intensified is became clear that for many sports, the equipment used played as important a part in performance as did the athlete. With the use of modern materials and manufacturing processes there is always scope for maximizing the performance of sporting equipment. Traditionally improvements were incremental, as athletes fed-back suggestions to manufacturers and new prototypes were built and tested. Given the cost of tooling for many of the
current manufacturing methods, carbon fibre with resin infusion to mention one, it is clear that such build and test iterations are not as preferable given the potential of limited success and high cost. Modern simulation techniques are capable of examining a “day–in–the-life” of an object and from an examination of the envelope of response the most sensitive regions can be detected. Iteration on the design variables, provided they remain within any constraints, physical or otherwise, can be incorporated to investigate their effect on performance. Methods such as Design of Experiments (DOE) and Response Surface Analysis (RSA), genetic algorithms (GA) and Monte-Carlo Methods are being increasingly applied to achieve optimisation goals For many sports the outcome depends in the interaction between the sportsperson and the equipment; boot with ball; bat with ball; bow and arrow, and so on. Previous research by my students has looked at tennis, cricket, and soccer. Although interesting results were obtained and valuable learning took place there are still many unanswered questions.
Pictures of ball impact in centre of tennis racquet and off-centre strike of cricket ball on bat.
Selecting this area for a project will involve selection of a sport, identification of desired improvements, leaning non-linear transient Finite Element Analysis with contact and other simulation skills.
There is a move globally to have covers on coal wagons and possibly also on iron ore and grains railcars. These will be to stop small losses of the product, prevent dust and also eliminate the need to spray water on the coal to reduce dust. What is not known is the pressure distribution on such covers which is needed for the purposes of the structural design. The project will involve wind tunnel testing and possibly CFD.
Interested students should first come to see me, and following the discussion if you are certain that
you are keen to do the project, then send an email outlining your interest in the project. For
students interested in learning the ‘nuts and bolts’ of CFD, there are also several possible projects
exploring the performance of state of the art numerical methods for fluid dynamics.
(1) Turbulent Mixing in Inertial Confinement Fusion
Inertial confinement Fusion involves compressing a small capsule of nuclear material (approx.
2mm diameter) using very powerful lasers until it reaches the necessary temperature and
pressures to produce a nuclear fusion reaction. This is one possible route towards fusion energy
production, however it has many challenges, being addressed in part by a $5bn US project called
the National Ignition Facility. Within the group we have Australian Research Council project to
address one challenge, which is the effects of mixing of the capsule shell material with the
nuclear material thus causing a decrease in yield or lack of ignition. This thesis project will use
state of the art computational fluid dynamics working within our research group to examine the
role of turbulent mixing in Inertial Confinement Fusion.
(2) Design and/or Analysis of a Test Facility for Apogee and Attitude Rockets
We have an ongoing collaboration with a UK/US propulsion systems company who are
working on their next generation of thrusters. There are several aspects to this thesis which
are available for students, namely the analysis of the design of a new contour for a thruster,
an analysis of the impact of mixture fraction (fuel/oxidiser ratio) on the performance of a
specific nozzle design, and design of a new test facility to be located in the UK.
(3) Ability of RANS models to capture junction flows
Flow separations at the junction of wings and bodies are of great interest to aircraft and
submarine designers. Such flows are challenging to capture and are the focus of a current
NASA program. This project has industrial involvement, and will explore the capabilities of
existing RANS modelling at capturing such complex phenomena. The ideal student will have
a background/affinity for CFD and will develop strong analytical skills.
(4) Investigation of Cavity Aeroacoustics
This project has been suggested by collaborators at DSTG who are interested in
understanding the aeroacoustic behaviour of cavities at transonic velocities. Cavity noise has
a major impact in several fields as a prime source of noise in aircraft wheel bays, weapons
bays, gaps between train carriages and open sunroofs/windows on cars. At high speeds the
noise levels are substantial (greater than 150dB) and can be severely damaging. This thesis
will explore the variation of acoustic noise in a generic cavity to give detailed insight into
experiments conducted at DSTO. We will investigate this using our in-house high order
accurate Computational Fluid Dynamics, running on multiple cores on our local cluster.
(5) Automotive Acoustic Noise Prediction
This project will explore the simulation of aeroacoustic (noise) levels for generic automotive
vehicles, focussing on experimental data produced by Hyundai. It will use state of the art
unsteady CFD to provide understanding of noise generation mechanisms and fidelity of
numerical simulation approaches. This is of key importance in an industry where there is
huge competition to provide a vehicle with class-leading performance. The student will work
closely with PhD researchers in our research group, which will strongly complement their
work
(6) Investigation of the Flow around a Hemisphere
This project has been suggested by collaborators at DSTO who are interested in
understanding the impact of proturberances on aerodynamic performance and/or structural
vibration. Such hemispheres are very common on modern aircraft, to house cameras or
other optical devices for example. There are several interesting challenges, namely
unsteady vortex shedding from the back of the hemisphere, and the behaviour of flow
dependent on the thickness of the incoming boundary layer. We will investigate this using
CFD. The ideal student will have a background/affinity for CFD and will develop strong
analytical skills.
(7) Rotorcraft Operations Close to Large Buildings and Ships
One of the most challenging manoeuvres which a helicopter pilot can undertake is to land
on a ship at sea, or a large building in poor weather conditions. Here we utilise CFD simulate
the wind flow over ships/buildings and analyse the impact of this flow on helicopter
operations. A particular focus is on helicopter operations close to the Australian Landing
Helicopter Dock (LHD). Here there would be several sub-thesis projects on (i) CFD study of
the LHD, (ii) Studies of the impact of wind velocities on rotorcraft operations, (iii) Novel
modelling of helicopter rotor blades within a CFD computation. This project is aligned with a
DST group project and the student would have the advantage of working alongside a PhD
student within our research group.
(8) Understanding of Fluid Flow in the Spinal Column
Recently, state of the art numerical methods for aerodynamics have been transferred across
to the medical field. A key area of interest is the understanding of the formation of small
cysts (syrinx) within the spinal cord. Such syrinxes lead to pain, loss of feeling and permanent
damage to the spinal cord and have a prevalence of from 0.84 to 8.5 cases per 10,000
people. They are believed to be formed due to disturbed pulsatile fluid flow within the spinal
cord, in particular abnormal transport of cerebrospinal fluid, and are often linked to the
Chiari malformation of the brain. This thesis will focus on the advancement of algorithms
for, or understanding of, the propagation of cerebrospinal fluid and pressure waves in the
spinal column using 1D models. The goal is to provide a fundamental understanding in
simplified physiology to contribute towards understanding and hence mitigation of this
disorder.
1
4th
YEAR THESIS TOPICS Prepared by L. Tong
1. Topology design optimization of a rib in aircraft wing box
An aircraft wing box typically consists of a number of ribs that are joined together by stringers and spars and
skin panels as shown in the Figure 1-1. While exterior configuration of an aircraft rib could be well determined
by the chosen airfoil, interior material distribution and structural topology could designed in a fashion to
achieve lightweight and performing structure. The thickness of an aircraft rib could be different at different
location and the cut-outs could take different shape. These selections could be determined by using topology
design optimization from initial design via finite element analysis to the final design as depicted in Fig 1-2.
Fig 1-1 Fig 1-2
This project aims to find optimum topological design for an aircraft rib panel that could be subjected to a range
of selected aerodynamic loads. For example, a particular airfoil section e.g. NACA-0012, could be selected
and several typical air dynamic load cases could be considered. The project involves the use of finite element
analysis software, interfacing with Matlab code developed and application to selected cases for topology design
of an aircraft rib structure. A prototype is expected to be manufactured and tested if sufficient progress is made
in the first semester.
2
2. Design and prototyping of pressure-actuated cellular structures for aircraft
morphing
Aircraft design is a multi-disciplinary, complex and challenging engineering task. Its general design cycle can
be broadly broken down into three technical phases, namely, the “Conceptual design”, “Preliminary structural
design”, and “Detailed structural design” as shown in Fig 2-1. There are a vast number of design requirements
for each phase.
The function of morphing may appear familiar as we all see the control surfaces on modern jets moves during
take-off, cruise and landing to achieve better flight performance. The challenging question is: Is it possible to
move other airframe components to drastically change aircraft configuration to perform specific requirements
during flight? How to define drastic configuration change, scope and extent? What are the limits? There are
numerous questions to be answered.
Fig 2-1
This project aims to extend the current hydraulic actuation technology to achieve drastic configuration change
and involves the use and design of pressurized cellular structures, which could be formed by an array of regular
hexagonal honeycomb cells or pouches or even skewed or irregular honeycomb cells (an example is shown in
Fig 2-2).
Fig 2-2
The project consists of design of cellular structural component in the form of leading or trailing edge in a
typical aircraft, or selected wing or fuselage sections. Finite element analysis of the designed cellular structure
will be conducted by considering different level of internal pressure applied. The deformation of the designed
structural will be analysed to understand the capability of morphing. A prototype of hardboard model with
pressure applied via balloons is expected to be used to demonstrate the proposed design.
3
3. Design and development of self-assembling mechanisms
Self-assembly is referred to as the spontaneous and reversible organization of units or
components into ordered structures via some sort of interactions. It can occur at different
length scales from nanometers to centimeters and is everywhere in nature. Some relevant
concepts drawn from natural contexts may have many applications in engineering. For
example, a modern civilian aircraft has movable parts e.g. control surfaces, a UAV may have
foldable wings. An aircraft can morph from one configuration to another via self-assembly.
One basic and useful form of self-assembly involves folding two dimensional materials into
three-dimensional (3D) structures and its reversal unfolding process. As in origami, folding
is capable of complex shapes and can be scaled to different sizes, and it can turn flat or
planar materials into 3D complex mechanisms. The figure below depicts: (a) an example of
compressing a 4 by 4 Miura-origami into a small part; and (b) a recent example of self-
folding a flat sheet of material into a complex 3D structures. Self folding requires
employment of one or more actuation methods to actuate the folding and unfolding
processes. It can be applied in remote, autonomous assembly as well as automation of
certain aspects of manufacturing.
Figure 3
This topic aims to explore basic inexpensive self-folding and self-unfolding techniques for
transforming planar material sheets to 3D structural mechanisms or machines. For example,
a self-folding hinge that could be actuated by an external stimulus, such as heat, electricity,
is considered as one of the key element in achieving the target of self-assembling
mechanisms. An ideal self-folding hinge should have the shape-memory characteristics.
4
4. Ambient motion based broadband PZT energy harvester
This project aims to design and prototype of ambient motion based broadband PZT energy
harvesters. As shown in Figure 4(a), a typical arrangement of a PZT based energy harvester
consists of a cantilever beam with a concentrated mass at its tip and a PZT film attached
close to the clamped end. Motion of the clamped end vibrate the beam and generates tensile
and compressive strain the PZT material, which in turn generates electrical charge that could
be collected if an appropriate electric circuit system is chosen. Such system work for a
chosen narrow frequency band, and the energy harvested due to mall amplitude of a random
ambient motion of the base support may be too small to be useful. Figure 4(b) depicts a
broadband energy harvester, which has two added magnets that creates a bi-stable system
and could generate an oscillation with large amplitude resulting in higher and consistent
harvested energy output.
Motion-driven energy harvesters are attractive and inexhaustible replacements for
electrochemical batteries in low-power wireless or portable electronic devices, which could
have significant applications in a wide industry sectors, e.g., health care, electronics, etc.
Figure 4 depicts several examples of such types of applications in self-powered body-
mounted or implanted medical devices or wearable devices, and self-powered and low power
wireless sensors and wireless sensor networks.
It is anticipated that this project will involve both modelling analysis and design and
prototyping. The modelling analysis will be on dynamic analysis of a system with single
mass, spring, damper and two magnets. Prototyping will involve design, fabrication and
testing of mechanical and electrical system.
(a) (b)
(c) (d) (e)
Figure 4 (a) A schematic of an energy harvester; (b) a broadband energy harvester with
magnets; (c) self-powered knee replacement components; (d) a PZT dimorph and PVDF
stave (approximately 18 μW of power could be generated under a stress corresponding to
that produced by a human weighing 68 kg during normal walking), and (e) an integrated
piezoelectric energy harvester and wireless temperature and humidity sensing node.
5
5. Multi-staged and reversible compact and high energy motion actuators
Actuators with large force and large stroke or high energy density are required for morphing
aircraft configuration or external shape. Hydraulic actuators currently used are heavy and
bulky, and hence light weight and compact actuators with high energy density are desirable.
This project aims to develop design basic concept for linear actuator based on snap-through
buckling of multiple structural components. The project involves numerical modeling and
design, and prototyping and testing. It is anticipated that: (a) finite element analysis software
will be used to conduct the necessary nonlinear buckling analysis; (b) selected designs will
be fabricated using 3D printer available in the school and experimentally tested; and (c) a
correlation between the analysis and test results be conducted.
As an illustrative example, Figure 5 depicts selected existing designs that could be
considered as the benchmarks and fabricated before the analysis, and how the designed
components buckle under compression. This project will explore ways of restoring the
collapsed structural components by using the elastic energy trapped in the buckled
components with limited input.
(a)
(b)
Figure 5
These types of actuators could be potentially used in aircraft wings to create smart ribs that
can change its chord-wise height during cruise.
6
6. Design of shape adaptable rotor blade airfoil section using smart material based
actuators
Morphing of rotor blade airfoil section is about actively changing the airfoil section
shape using compact actuators, such as PZT, SMA based actuators, to achieve active
airflow control for enhanced flight performance. This project aims to look into possible
solution to design and analysis of shape adaptable NACA-0012 airfoil section with a
rigid spar using smart material based actuators. Finite element based numerical
simulations are to be performed for achieving desired airfoil shapes.
7. Digital image correlation for full field measurement
This project will offer an opportunity for a student who is keen in
developing/implementing and verifying Matlab based software that is capable of
performing digital image correlation between two images to extract relevant structural
movement. It is expected that DIC software will be used to facilitate measurement of
selected adhesive properties in bonded joints.
8. Shape changing structure actuated with osmotic pressure
Shape changing mechanisms of Venus flytrap – is osmotic pressure the answer?
This project aims to extend an existing in-house UAV design tool with higher fidelity models.
The current tool uses lower level modelling of all disciplines. As part of this thesis you need to link the existing tool to higher fidelity
aerodynamic and structures tools like Tranair and NASTRAN.
Once integrated those tools will be used in an optimisation environ-ment to determine the optimum size and shape of a medium altitude long endurance UAV
UNMANNED AIRCRAFT DESIGN
Performance data for small propellers is virtually non-existent and a lot of the required geometry data needed for simulations is absent.
Various thesis projects are avai-lable in this domain to improve understanding of the dominant flow phenomena of small pro-pellers:
- 360 degree AoA airfoil data for low Reynolds numbers
- development of the USyd propeller database
- propeller-fuselage interactions and impact of fuselage block-age
Current UAVs are limited in alti-tude by their propulsion system. Small gas turbines could expand altitude capabilities provided they can be designed with an accep-table efficiency. The following projects aim to address some of the issues of micro gas turbines
Coleman engine The so-called Coleman engine, a semi-closed recuperated engine, is considered to be one of the major alternative cycles for high altitude
long endurance UAVs. This project consists of an analysis of a range of different gas turbine configu-rations at altitude with the aim to quantify the impact of low Reynolds number operation on the different cycles.
Altitude effect on turbo-machinery Low Reynolds numbers impact the performance of compressors and turbines significantly. In this thesis you will use CFD to quantify the
impact of operating altitude on a range of radial compressors and turbines
MICRO GAS TURBINES
HYPERSONIC AIRCRAFT AND SPACEPLANESGeneral Background The tec hn ical and commerc ial feasibility of both hypersonic aircraft and reusable space-planes is studied world-wide. The high temperatures associated with either hypersonic flight or atmospheric reentry result in severe thermal stress for the aircraft structure. Innovative structural designs are therefore required.
Specific projects A multitude of projects are available
in this domain. Possible projects include but are not limited to:
• impact of low speed handling qualities on waverider design and optimisation
• design of a hydrogen fuelled supersonic transport aircraft
• analysis of pre-cooled and variable cycle engines across a range of flight conditions
Fuel cells offer the potential to significantly increase endurance of small electric UAVs. However, their integration requires considerable research. The following topics are available in this general area
Fuel cell controller develop-ment and transient perfor-mance
Fuel cell performance during transients is significantly impacted
by the controller design. This thesis will consist of the design of a fuel
cell controller and an assessment of i t s impact on the t rans ient performance of the fuel cell.
Battery life prognostic model development
Battery life and endurance esti-mates are critical for the perfor-mance prediction of electric vehi-cles. In this thesis a NASA deve-loped battery health management model will be extended and applied to a range of mission profiles. The predicted perfor-mance will be compared with measured performance to assess the validity of the model
Electric motor dyno testing
Electric motor models are scarce and improved models are needed to correctly predict performance of electric UAVs. In this thesis an improved model will be derived for electric motors based on extensive dyne testing.
Electronic speed controllers are needed to drive brushless DC motors. However, efficiency data for these electronic devices is not widely available. In the current thesis electronic speed controller efficiency will be measured and a model will be developed that allows accurate prediction of speed controller efficiency.
Nature has used millions of years of evolution to perfect designs while humans have only recently started to explore options. Bio-inspired designs could lead to improvement s i n ef f i c iency, operational capabilities,…
This series of thesis project will seek inspiration in nature for
control and/or propulsion of unmanned aircraft and airships using various air swimming models
Multiple projects are available: - aerodynamics of flexible
• In support of Experiential Learning towards Global Engineering Design
2017 Honours/MPE Thesis (ver 1.0 – 04 October 2016) Please come and discuss possible topics with me as soon as possible. Subject areas supervised include Unmanned Aerial Vehicles (UAVs)/Remotely Piloted Aircraft Systems (RPAS)/”Drones”, Aircraft Design, Experimental Aerodynamics, Projects to enhance Experiential Learning, and Aeronautical Engineering Education. A particular focus will be on the development of Extreme UAVs, ie. Flight platforms with NEW, and potentially extreme, flight capabilities. Any topics within the following or related areas can be discussed and potentially agreed to. Topic Areas include: (1) Developing a Flight-Testing UAV based on a scaled Jabiru light aircraft:
a. Tooling and prototype; b. Instrumentation; c. Wind-Tunnel testing; d. Flight testing
(2) Developing the integration of the use of UAVs for Experiential Learning across the whole
Aeronautical Engineering curriculum, including the design and development of learning exercises including the following:
a. Aircraft Construction; b. Instrumentation;
For Internal Use Only – Not for external distribution
c. Flight performance; d. Aircraft Structures; e. Aerodynamics; f. Propulsion; g. Flight Mechanics; and h. Design improvements/Enhancements.
(3) (Multiple projects) mini Extreme-UAV Airframe Systems:
a. Tail Sitter VTOL concepts i. Distributed Thrust; ii. Thrust-vectoring; iii. Perching; iv. Micro-“Prop-hanging” fixed wing; v. High Manoeuvrability for flight in cluttered environment.
b. Aerodynamic Modelling, Stability and Control, Design Optimisation, Flight Simulation and Testing of Extreme UAV airframe concepts;
c. Development and testing of container/tube-launched UAV concepts;
d. Deployable and morphing structures for airframes;
e. Development of UAVs deployed from underwater platforms;
f. low Reynolds Number aerodynamics and bio-inspired concepts for indoor/outdoor operation;
g. Design and Development of High Speed mini-UAVs; h. Continuing development and testing of a modular Multi-
Disciplinary Experimental UAV Test Aircraft; i. Multi-Role Multi-Mode (Aerial-Maritime-Terrestrial) UAV
– need to see me to discuss details. j. Tethered Hovering UAV on floating platforms (multiple
projects – need to see me to discuss details).
(4) (Multiple projects) High Performance BWB (blended wing body) UAV:
a. Investigate the shifting in neutral point due to propwash; b. Investigate the use of Split ailerons on BWB aircraft; c. Composite airframe structural optimisation and Rapid Prototyping; d. Dynamic testing of model in the 7 X 5 wind tunnel e. Improvement of the instrumentation and flight testing
i. Alpha-beta-V sensor ii. Control position sensors iii. Interface with X-Plane Flight Simulation iv. Inertia measurement system
f. Graphical AVL/Panair editor with expansion to CATIA (part of a fast preliminary aircraft design optimisation tool)
g. Parameter estimation from flight testing i. BWB UAV ii. Cessna 182 (can be compared with full scale) iii. Jabiru J-400 (can be compared with full scale)
(5) Micro EDFs (Electric Ducted Fans) – effect of tailpipe design and thrust-
vectoring mechanisms. (6) (continuing project) Exploring Rapid Prototyping for new UAV designs, using 3D printing
(additive manufacturing) and other facilities. (7) Launch and Recovery for flight testing of small UAVs. (8) Lighter-than-Air UAV flight systems.
For Internal Use Only – Not for external distribution
(9) Quadcopter dynamic model in Matlab: There are many simple models available on the internet, so you must include some novel approaches in the model, such as adding the option to simulate an dynamic payload such as a moving arm and/or deployable payload, the actual dynamics of the motors/propellers we use (accurate throttle model) etc.
(10) Biomimetic Design in UAV: What is the most effective features that scare pest birds most
effectively? This is based on an industry-supported project. The thesis will involve testing your designs on a farm.
(11) Integrating and testing UAV flight guidance and planning systems in a lab equipped with Motion
Capture system. (12) …???...come and see me to discuss your ideas…
