School of Aerospace, Mechanical and Mechatronic Engineering

Thesis/Capstone project topics.

2018 AEROSPACE TOPICS

Supervisor: Xiaofeng Wu

xiaofeng.wu@sydney.edu.au

Topic: Implementing ECSS Systems Engineering Process to the Design and Construction of a Sounding Rocket

Supervisor: Xiaofeng Wu, assisted by Mr. Warwick Holmes

Summary: The European Cooperation for Space Standardization (ECSS) is an organisation that enforces standardisations for the European space sector, in particular the European Space Agency (ESA). The aim of this thesis topic is to design, construct and launch a sounding rocket under the ECSS systems engineering process. The project would encompass many different responsibilities from systems integration to project management. The only requirement for the student undertaking this thesis topic is that the student must be elected in as the Chief Design Officer (CDO) of the USYD Rocketry Team to lead the project team working on the rocket. A major component of undertaking this thesis topic under USYD Rocketry Team is to contribute to the construction of a rocket for the Intercollegiate Rocket Engineering Competition (IREC) which is held in America every year. The student will work together with thesis students researching into other components of the same project. For more information regarding the topic, please contact Liyong. For information regarding USYD Rocketry Team or IREC, please contact Joshua CM or Zoren Liu.

Topic: Design of Sounding Rocket Avionics System

Supervisor: Xiaofeng Wu, assisted by Mr. Warwick Holmes

Summary: The avionics system is an important component of a sounding rocket. It is

responsible anywhere from ensuring the proper recovery system deployment to determining the rocket’s attitude. Students working on this topic may also develop a control system for the rocket in simulation. A major component of undertaking this thesis topic under USYD Rocketry Team is to contribute to the construction of a rocket for the Intercollegiate Rocket Engineering Competition (IREC) which is held in America every year. The student will work together with thesis students researching into other components of the same project. For more information regarding the topic, please contact Liyong. For information regarding USYD Rocketry Team or IREC, please contact Joshua CM or Zoren Liu.

Supervisor: L. Tong (liyong.tong@sydney.edu.au)

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. 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. 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.

Conceptual design

Input

Preliminary design Detailed design

Output

Input

Output

Output

Design requirements, e.g.•VTOL•stealth•flight ceiling•range… etc

A/C configuration, e.g.•body configuration•wing configuration•number of engines•tail configuration… etc

Structural design•optimized structure•“down to the last rivet”•manufacturing ready

Structural layout, e.g.•airframe flange spacing•spar arrangement•rib spacing

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. 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. 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. Structural Optimisation of a Sounding Rocket Fuselage

A key area of optimisation for a sounding rocket is to reduce the weight of the structure to allow for more payload mass. During launch, flight and recovery, the fuselage will experience various load cases, from compressive force produced by the motor to aerodynamic drag. Students will need to investigate the effect of dynamic loading, static loading, temperature effects, and also analyse deflection, buckling and material performance.

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 full field displacements and strains, including strain concentration areas, in a selected configuration of adhesively bonded joints. The thesis will involve finite element analyses using commercial software, learning and using DIC measurement technology, preparing and testing selected bonded joint under tension in an Instron test machine, and correlating numerical results with DIC measuremeants.

8. Design and prototyping of soft actuators

A soft actuator is referred to as a slender composite structure that can extend, contract, bend and twist with simple pressurized fluid input control. The soft actuator may consist of soft materials, such as elastomeric matrices, with embedded flexible materials, e.g. fiber and cloth. This project will involves design of a soft actuator including simple pressurized control input and detailed analyses by using finite element method, development of an affordable, multi-step, rapid fabrication process, possibly moulding, and comparison between predicted and measured actuation motion trajectories and force profiles.

9. 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.

Dr Gareth A. Vio Rm N306, Bldg J11,

ph: 9351 2394 gareth.vio@sydney.edu.au

2018 THESIS

TOPICS

Fluid-Structure Interaction

This project aims to look at the interaction that an elastic body immersed in a cavity has on the acoustic/pressure spectrum. General fluid-structure interaction problems can also be addressed.

Energy Harvesting

This topic aims to research this behaviour of piezo-crystal with hysteresis and shear modes. Change in materials phase transition can produce increased power level. This has been noticed if shear modes are excited. This project aims to look at these effects.

Model Updating

Finite element model are just a representation of the real world. These model need to be tuned to the real experimental results. This topic aim to explore how to modify FE models to acquire the characteristics of an experiment.

The Elastic Wing

This project will look at the sensorcraft structure. Different direction can be explored to include active aeroelastic testing, dynamic testing and static as well as designing and testing a very flexible wing. The model will be scale replica of the full scale and aeroelastic scaling laws will have to be applied.

Topology Optimisation

Topology or shape optimisation allows you to distribute material for optimum performance. A range of project can be developed leading to the design of UAV, morphing structure, composite, transient problems. Fatigue and frangibility problems are of interest. 2D wing structure under supersonic flow and heat conditions

MIMO Testing

Multi-Input Multi–Output testing is required to obtain information on a structure during a test. The project will look at techniques like the Resonant Decay method for nonlinear systems for locating, identify non-linearities and generating the equation of motion of the system under investigation.

Flat Plate Interaction in Wind Tunnel Testing

Recent tests have shown that flat plates interact with each other in an incompressible flow field. The nature of this interaction requires further investigation ad modelling This project will require you to gain knowledge of CFD, wind tunnel testing and basic vibration analysis techniques.

On-Line Flutter Prediction Methods

Flutter is a dynamic instability that can occur in aircraft. A number of techniques have been developed over the last 100 years, form the Flutter margin method to the ERA-DC/Extended ERA and wavelets. You will build a test wing and use these techniques to predict flutter from wind tunnel data. Further introduction of non-linearities and evaluation of these linear techniques will be performed. This project will require you to gain knowledge of wind tunnel testing and basic vibration and non-linear dynamics analysis techniques.

Active/Morphing Aeroelastic

Morphing / active structures are being investigated as potentially improving flight performance. NASA has recently experimented with a new material to remove control surfaces and have seamless control surface. It is of interest to further explore the capability of these models and what secondary performance enhancements can be achieved.

Mr. Warwick HOLMES Aeronautical Building J11, Rm N326, ph: 02-93512183 warwick.holmes@sydney.edu.au 2018 UG THESIS TOPICS

Small Satellite downlink data transmission optimisation

Proposed USYD “HISA” satellite

DLR “BIROS” satellite

Low Earth EO satellite orbits

This thesis topic is to perform analysis of the maximum possible payload data transmission rate to ground that can be achieved with current technology for a LEO-SSO orbiting small satellite. The small satellite requirements being: 600km altitude, 97⁰ inclination, 0.5m3-1.0m3 volume, dimensions 80x80x80cm up to 100x100x100cm, 100kg-200kg mass small satellite with downlink BER = 10-6. The analysis shall focus on the maximum data transmission downlink rate to maximize throughput for a LEO-SSO small satellite with one ground station. The “type” of data being transmitted to ground by the satellite is irrelevant for this exercise. However, the data must be reproduced on the ground as generated on-board with a BER of no more than 10-6. All calculations and assumptions shall be reported in detail. The thesis shall present what is possible to achieve based on current technologies for a maximum data transmission rate from space to ground. Analysis should look at advanced QAM modulation schemes, legal satellite frequencies (e.g. S,X,Ka,Ku), error correction techniques, etc to achieve the maximum possible data transmission rate to ground. Assume ground station receiving dish diameters of 5, 3, 2 and 1m diameter. Analysis must take into account the high Doppler shift associated with LEO satellite RF transmission and modulation schemes. The downlink must be reliably “locked” and demodulated for high Doppler shift transmissions. A detailed literature review is essential to see what small satellite systems are currently reporting actual in-orbit maximum possible (not proposed) transmission rates. Finally an assessment of an optical data transmission link of data by laser from the satellite to ground (one way only) shall also be assessed to make comparison to the best RF data link to ground. If “real” optical laser data communication information is sparse then the next best (most mature) or reliable TRL level technology can be presented. This analysis shall also include analysis of the laser optical transmission technology used by DLR on the BIROS satellite

Small Satellite ground segment optimisation

Proposed USYD “HISA” satellite

Ground Station optimisation

DLR “BIROS” satellite

Satellite Laser downlink to ground

This thesis topic shall perform the analysis for ground segment system optimisation for the number and location of ground stations in Australia. The purpose is to maximize the amount of payload data that can be received on ground to optimise the acquisition and throughput for downlink data from a LEO SSO small satellite over Australia. Analysis shall include the requirement to then transfer a maximum of 100TByte of received downlink image data from the GS to the central CSIRO image processing site in Canberra. The small satellite requirements being: 600km altitude, 97⁰ inclination, 0.5m3-1.0m3 volume, dimensions 80x80x80cm up to 100x100x100cm, 100kg-200kg mass small satellite with downlink BER = 10-6. Based on the orbital ground-track precession of the trajectory of a LEO-SSO satellite over the Earth, the analysis is to determine the optimum number and placement of ground stations on Australian territories that shall maximise the acquisition and throughput of an Australian remote sensing satellite. A detailed literature review is essential to see what ground station (GS) assets currently exist in Australia for LEO-SSO downlink reception. What possible cost-reduction by station leasing or reuse is possible, What GS siting parameters optimisations was responsible for these ground station locations being chosen in Australia. Analysis should look at ground stations operating with legal satellite frequencies (e.g. S, X, Ka, Ku), to ground and assume GS dish diameters of 5, 3, 2 and 1m including rain fade weather effects on reducing downlink capacity etc. Analysis should also include possibility of receiving LEO satellite data in remote locations with data being transfer to central processing site (e.g Canberra) by retransmission via GEO telecommunication satellites (OPTUS or NBN) accounting for data transmission rates, methods, cost etc. Finally GS analysis shall also include a section to analyse the optimal placement of a data transmission downlink by laser from satellite to ground (one way only) to compare to the best RF data downlink GS configurations. This analysis needs to focus on the best “cloudless” GS location with access to high speed optic fibre Internet access. If “real” optical laser data communication information is sparse then the next best (most mature) or reliable TRL level technology can be presented. This analysis shall also include analysis of the laser optical transmission technology used by DLR on the BIROS satellite

Small Satellite OB autonomy and data compression optimisations

Proposed USYD “HISA” satellite

ESA Satellite control centre

Lossless compression algorithm

Spacecraft Solid State RAM on-board data recorder

This thesis topic shall perform the analysis of methods to optimise the acquisition and pre transmission data transmission of high speed optical data from a high capacity 12 channel multi-spectral or hyper-spectral camera The small satellite requirements being: 600km altitude, 97⁰ inclination, 0.5m3-1.0m3 volume, dimensions 80x80x80cm up to 100x100x100cm, 100kg-200kg mass small satellite with downlink BER = 10-6. The thesis requires the detailed assessment of on-board data compression algorithms specifically optimised for lossless image compression of Multi-spectral and hyperspectral data sets. The intention is to compress raw image data on-board to maximise data throughput to the ground without wasting precious bandwidth and acquisition time on uncompressed images but without compromising any spatial or spectral resolution data. LEO image acquisition satellites require a significant amount of on-board RAM storage (up to 10 TByte … or more?) until the next GS pass occurs to downlink the image data. Examine and present design methods to performing high speed image acquisition, lossless compression, error correction and then on-board storage into volatile RAM storage. What data bus and transfer protocol, serial/parallel, space qualified technologies can manage these high speed data transfers. Define important requirements for high speed data bus and on-board volatile RAM storage unit specifications. Ground segment mission planning for pointing and acquisition of remote sensing image data is a time consuming, complex and expensive (human operators on ground) activity. Examine methods of cost saving for the mission planning and ground segment operations using on-board autonomy algorithms for scheduling image pointing and camera acquisition. This may also include “Level-0” on-board image calibration. Perform a detailed literature review to find what is the current optimal “state-of-the-art” ground operations optimisations strategies and operating practices currently being made to simplify operations and reduce operating costs, specifically for LEO image acquisition satellite missions. Taking into account specific aspects of LEO Earth Observation high throughput image acquisition missions, what system design and on-board algorithms or hardware design strategies can be implemented to reduce operating and processing costs on the ground for these kind of missions.

Small Satellite water quality & fire monitoring instrument definition

Proposed USYD “HISA” satellite

Water quality monitoring by satellite

Australian bushfires by IR sensors

Hyperspectral Data Cube

This thesis topic shall require the very detailed assessment and review of the CSIRO document below, to make a selection of optical wavelengths and the number of optical (spectral) bands for an optimised water quality monitoring image acquisition camera. This camera shall become the primary payload for a small Australian fresh water monitoring satellite making Earth observation and remote sensing imagery for river, lakes and dam fresh water quality assessments. The reference CSIRO document is: “Evaluating the Feasibility of Systematic Inland Water Quality Monitoring with Satellite Remote Sensing By: Arnold Dekker & Erin Hestir CSIRO 117441 May 2012 https://publications.csiro.au/rpr/download?pid=csiro:EP117441&dsid=DS10 A detailed assessment of existing space-based remote sensing multi-spectral and hyperspectral image cameras needs to be made. Once this is complete the synthesis of data presented in the CSIRO article then needs to be merged into the existing sensor or camera designs as a proposal for an optimised Australian water quality imaging payload camera. Other data references are also required The emphasis shall be on adapting or modifying multi-spectral or hyperspectral cameras/sensors from existing small satellites (RapidEye, DMC, PROBA-V, BIROS, TET, etc) using the best information & conclusions from the CSIRO document. The thesis needs to define a requirements definition to specify the most useful and optimised primary payload for Australian fresh water quality monitoring. The volume envelope of this camera shall not exceed dimensions 50cm x 50cm x 70cm (TBC) The second optical imaging payload shall focus on InfraRed imaging of Australia for thermal bush-fire detection, similar to the data presented in the “Sentinel HotSpots” website. The bush fire data for this website is acquired from the MODIS instrument on the AQUA and TERRA satellites. https://sentinel.ga.gov.au/#/ However this IR camera occupies a large volume far greater than can be accommodated on a small satellite. Assessment of a smaller IR sensor and camera technology needs to be made Eg. The IR sensors on DLR-BIROS, TET and other small satellites. The volume envelope of the IR camera shall not exceed the dimensions 30cm x 30cm x 50cm (TBC)

Dr KC Wong School of Aerospace, Mechanical and Mechatronic Engineering Email: kc.wong@sydney.edu.au

The University of Sydney

UAV/Aircraft Design & Development

A/Prof KC Wong kc.wong@sydney.edu.au

Rapid Prototyping, Instrumentation, Testing and Characterisation of UAV systems:•as Multi-Disciplinary Experimental Flight Platforms;

•Exploring Advanced aircraft concepts, eg. BWB, VTOL, Tube-Launched systems, and Bio-inspired morphing airframes;

• In support of Experiential Learning towards Global Engineering Design

2018 BE Honours/MPE Thesis (ver 1.0 – 17 October 2017) Part 1: 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; 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) Exploring Rapid Prototyping for new micro-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. (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) Autonomous laser tag target drones. Not sure if you have played laser tag before, basically you

have a laser gun and if your laser beam hits the sensor on your opponent’s body, your opponent’s game is over. Now we put the laser sensor on the drones, and make them dodge the human targeting them autonomously, it will be a very fun project. Since we have Optitrack Motion Capture lab, it is not difficult to make them move randomly, the innovation will be the trajectory generation, and how to make them smart enough to know when the human player is targeting them.

(11) Drone sports. ETH has done this (https://www.youtube.com/watch?v=3CR5y8qZf0Y) If we use two multirotors on either side of a high net, and they have to push the ball back and forth over the net without falling to the ground, we has just invented drone volleyball. There are so many possibilities. Optitrack can take care of the ball position, challenge is in the controller design.

(12) UAV performance optimisation. Selecting components for a specific mission is still more or less depending on experience. There are many websites that provide tools for performance estimation, but they are only good if you know the combination will work, otherwise they will fail. We need a tool that takes endurance and maximum payload as input, and outputs suggestions for the configuration, frame size, motor KV and ESC. We can start with just a performance estimator, then move on to an algorithm that can optimise a design.

(13) Fetching UAV. A UAV that fetches whatever you throw at it, ETH has done this with the omnicopter and a net (https://www.youtube.com/watch?v=0gR1ekapOAE), it will be interesting if you can put a claw on it, and it throws the ball back to you.

(14) UAV tuning bench. Tuning the PID of a drone is painful, there is a need for a tuning bench which we can isolate the motion of the UAV into only one axis. A systematic way of determining these PID parameters are also needed. Such bench can also be used for UAV testing, so that when things go wrong the UAV doesn’t hit the roof or crash really hard.

(15) A fixed wing/VTOL UAV for bird scaring. This can go parallel with current PhD research project, with all the bird scaring payload currently mounted on a hexacopter because it is straightforward. We also want to explore using fixed wing/VTOL aircraft. This is Biomimetic Design project in UAVs. 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.

(16) Integrating and testing UAV flight guidance and planning systems in a lab equipped with Motion

Capture system.

(17) I am happy to discuss your ideas for any UAV/Drone Design-Build-Test-Fly projects.

Part 2: Projects relating to Aircraft Restoration

These thesis projects will be co-supervised with Nicholas Cale and his partner engineers in the project.

1. De Havilland Vampire Fatigue Life Extension

Background: The original wing lower spar cap design of the de Havilland Vampire jet aircraft had a

limited fatigue life of 1800 hours when operating over a standard air force life-cycle. As a result of

extensive fatigue testing at the Aeronautical Research Laboratories a modification of the spar cap

area was designed for life extension. In the present era, aircraft designers and military service

support organisations seek to minimise project costs by minimising physical structural tests,

replacing them with increased use of FEA and other computer-based methods. Comparison of the

modelling with small scale testing or historical test results is essential for validation of the cheaper

methods.

Thesis: Create a 3D model of the wing structure and use FEA and fatigue analysis methods to assess

the original and modified wing design. Compare the model results with the original results. Assess

wing life for operation under civilian operations in the Limited category. Identify specific areas where

cracks may develop and propose a schedule for inspection.

2. Design Tools for Aircraft Support

Background: The design of repairs or modifications to aircraft in service is often complicated by the

lack of original drawings or CAD data from the manufacturer of the aircraft or of fitted equipment.

The design of large or complex repairs or modifications becomes a slow or iterative process that

includes a series of measurements of aircraft structure and other components, and development of

replacement parts with a maintenance engineer. Powerful workstations, advanced algorithms and

standardisation of file formats mean that photogrammetry can be used to create 3D data for use as a

Digital Mock-up (DMU) of the area of interest in a CAD package. Systems in use today that allow

detail design of repairs or modifications are often very expensive and time-consuming to use, and do

not represent an effective replacement for traditional manual methods for many enterprises. Smart

software can be used with inexpensive equipment to create a cost-effective system that produces

results quickly.

Thesis: Develop tools that make use of the output of a standard camera and photogrammetry

software in CAD software. The tools will generate accurate 3D geometry of user-nominated features

of an aircraft structure or systems. From the photogrammetry point cloud, the tools will generate

geometry such structural datums, sheet-metal and tubular elements, and hole patterns that can then

be used directly for detail design of repairs or modifications.

3. Non-destructive Testing (NDT) Methods for Vampire-like Wood

Structures

Background: In recent years, validating the integrity of ‘historic’ glued wooden aircraft structures

that include complex build-ups of different elements has usually included destructive testing.

Destructive testing relies on the availability of equivalent structure or removing coupons from the

structure being validated (which is subsequently repaired). ‘Tap-testing’ is an accepted method that

helps to validate some modern composite secondary structures. It is a manual method with

subjective aspects. Ultrasonic methods are not suitable for testing these structures because they may

not detect failed glue-lines that have ‘intimate contact’ of the structural elements.

Thesis: Develop a practical and objective NDT method for validating the integrity of ‘historic’ complex

glued wooden aircraft structures. Application of the method will consider criticality and geometry of

the structure, and conclusions should take in to account other standard methods, such as visual

inspection.

4. Re-engine Vampire Aircraft with a Modern Turbine

Background: Replacement of aging aircraft fleets that have become uneconomical or of outdated

capability, whether in the military or civil arena, is an expensive process. Often, the airframe itself

remains viable and a program to update some systems, interiors and equipment is more cost

effective than replacing the fleet. Replacing the aircraft’s engine(s) with a modern type can provide a

major improvement in economics, with a modern engine of similar thrust having lower weight and

superior fuel consumption. Serviceability and maintenance support aspects also improve

dramatically. Upgrading an aircraft with an engine that is very different to that originally fitted,

however, does have many challenges, and changes to the rest of the aircraft must be minimised to

ensure the upgrade remains cost-effective.

Thesis: Determine the feasibility of replacing the De Havilland Goblin engine in the Vampire aircraft

with a Williams International FJ44-3AP turbine engine. Consider all aspects of the installation of the

replacement engine to present a viable upgrade with minimal impacts on the aircraft’s structure and

other systems. Calculate aircraft performance, such as range and time-to-climb, and compare with

the original configuration.

5. Product Data Management (PDM)

Background: Whether during design, manufacture or service, the volume of engineering data behind

the support of complex or modern aircraft types is vast. Traditional methods for handling this data

rely upon paper copies of all drawings, reports, manuals, records and schedules with indexing that

requires manual navigation through the data to ensure the manufacture or in-service support to

achieve a complying aeronautical product. Current handling of the set of aeronautical data for an

aircraft type or particular aircraft in the digital world is often by processes that simply replicate those

used in the old hardcopy world, relying upon humans tracing through various documents for

servicing schedules, spare parts, and the like. Some aircraft put in to production and entering

operational service in the last ten years are supported by varying levels of sophisticated PDM. Older

designs, even those that continue to be manufactured at significant rates and are in service in large

numbers around the world, rely upon technical support using traditional data management. Fully

integrated PDM systems, making use of modern ‘app’ concepts and computing power, would

improve turn-around times and save costs for design, manufacture and in-service support.

Thesis: Having established the relationship between all the sorts of engineering data for design,

manufacture and in-service support of an aircraft, design and test a data management software

system that integrates the data to allow the full range of maintenance and repair actions to be

documented in an efficient manner. The system will include configuration management to account

for changes to documentation and airworthiness authority rules, and modifications to the aircraft.

Searching for requirements and parts is simplified and uses graphical interfaces. A database of

standard repeat tasks is established for easy generation of new task documentation. Scheduling of

maintenance events is automated, providing calendar or flight-based alarms to the appropriate

maintenance personnel.

Thesis/Projects – Ben Thornber (ben.thornber@sydney.edu.au)

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) 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.

There is also space in this project to work on new advanced Fluid Structure Interaction

algorithms in collaboration with Dr. Gareth Vio’s group.

(4) 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

(5) 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.

(6) 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.

(7) 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.