Masters projects

The progress in the area of electronic hardware has allowed a significant reduction in the size of satellites, and there has been an incredible growth in the nanosatellite market, e.g. cubesats. However, power requirements have not diminished at the same rate and so, small/nano satellites often need to deploy solar arrays in order to collect sufficient solar energy. In addition, the size of other equipment, such as mirrors, lenses, or antennas, is related to physical parameters, and cannot be reduced significantly without a decrease in performance. All this has generated increasing interest in satellite deployable structurers (and deployable surfaces in particular), as a means to stow a large item into a compact volume for launch and then deploy/unfold it to the required size and configuration for its in-orbit operations.

The purpose of this project is to carry out a review of the current technologies utilized for surface deployment on board satellites and identify a particular application to be developed. Various concepts will be assessed, and a preliminary design of a novel system will be produced and analysed. It is expected that besides research, design and computational work, the students will also have to produce physical model(s) (e.g. 3D printed) as proof of concept of the mechanism.

Space technologies are fundamental to humanity’s sustainable future. For example, of the 50 essential variables to assess Earth’s climate, 26 are only measurable by satellite technology. However, the trade-off between the environmental cost and the social, environmental or economic gain from developing space technology is poorly understood. The recent development of the European Space Agency (ESA) Life Cycle Assessment (LCA) and Eco Design framework will enable our understanding of these trade-offs.

This Masters project will research the sustainable design of space missions by assessing an Te Pūnaha Ātea – Auckland Space Institute mission in real-time during development. The project will involve LCA modeling using OpenLCA software, data collection, and qualitative analysis to identify data availability, barriers to sustainable design and assessment, and supply chain mapping.

No coding skills are required.

Reaction Wheels are a type of actuator typically used to control the attitude and pointing of satellites. In these mechanisms a rotor is connected to an electric motor which can accelerate or decelerate thus exchanging angular momentum with the satellite platform to produce rotations of the latter.

Unavoidable manufacturing tolerances (e.g. rotor unbalance, bearing surface roughness), during the functioning of the device produce microvibrations that can degrade the performance of accurately targeted instruments onboard the satellite.

This project will be carried out in cooperation with an industrial sponsor (Rocket Lab) and will focus on the issue of the balancing of the wheels and the micro vibrations that are produced by the device. Cutting edge technologies will be investigated to produce disrupting innovation in the design. In addition, during the project the student will carry out tests on physical hardware to correlate and verify predictions, and qualify equipment. 

Telescopes observe celestial objects (or sources) in the sky. The telescopes are usually movable and can point at different positions in the sky. Very large scientific telescopes in astronomical observatories are highly specialised, very expensive and scarce. Hence, they must be used as efficiently as possible.

In this project you will investigate and develop scheduling and ordering algorithms to optimise the use of telescopes. This includes the development of a tool that can process lists of sources to be observed, which then creates optimised observation sequences that can be used for the operation of real telescopes.

Fault tolerance is an important property of any space mission. In large, expensive satellites, redundant hardware systems are used to improve reliability of computing in space to ensure their success. For smaller, cheaper satellites, like CubeSats redundant hardware is often not an option.

Nevertheless, it is of vital interest to make all satellite missions as reliable as possible.

In this project we will investigate if and how we can make computing in CubeSats more fault tolerant. The focus will be on scheduling techniques for the various on board tasks of typical systems and payloads found in CubeSats.

After identifying common operating systems and software stacks of CubeSats in an extensive literature review, we will identify which scheduling and computing strategies can improve fault tolerance. Existing scheduling techniques will be adopted to this scenario and we will fill gaps with novel approaches and algorithms.

Supervisor: Oliver Sinnen

One of the challenging science problems in radio astronomy is the search and timing of pulsars and fast radio bursts (FSB). Pulsars are rotating neutron stars that cannot be seen but send out electromagnetic pulses with a very stable frequency. This makes them very precise clocks, but also helps to study the physical properties of other objects, including black holes, gravitational waves and general relativity.

Proposed methods to search for unknown pulsars are based on brute force approaches, where the telescope data is processed assuming wide ranges of possible parameters. This project will investigate and implement novel high performance algorithms and methods for the search and characterisation of Pulsars and FSBs.

New Zealand operates a year-round scientific station on Antarctica (Scott Base). Currently, satellite communications to Scott Base is achieved via Intelsat. However, there are significant limitations on bandwidth, which limits the amount of data that can be transferred to/from NZ over the existing link. Given these limitations, this project aims to develop the preliminary mission specifications for a dedicated communications SmallSat placed in a Molniya orbit. In particular, the project will consider operational parameters for the communications-subsystem of the satellite, including mode of operation, frequency, bandwidth, and power budget.

There is a renewed interest in missions in cislunar space, the American Artemis program and the Chinese Chang’e project are just two examples. As a result, the space around the Moon will be populated with spacecraft, some of which will be manned. To guarantee the safety of these missions, it will be necessary to extend space domain awareness to cislunar space. This new need will bring many challenges. The difficulty to track these distant objects and the non-Keplerian, possibly chaotic, dynamics are two relevant ones. This research project aims to develop new initial orbit determination algorithms tailored for non-Keplerian dynamics and the use of both ground- and space-based optical observations, an essential capability for space safety in cislunar space.

One of the main trends in space exploration is the use of small and low-cost probes. However, space operations are expensive as they involve the use of Earth-based facilities. Achieving autonomous navigation is a major objective to further reduce mission cost and enable new scenarios (e.g. when the communication latency is a major obstacle). Recently, concepts based on the use of both natural and artificial bodies as objects to track for navigation purposes (ONAV) have been proposed, as well as other more sophisticated approaches based on the relativistic perturbation of starlight (StarNav). In this project, we will investigate the development of spacecraft navigation algorithms that fuse different types of observations, and we will assess their suitability for use onboard low-cost missions.

Corrective manoeuvres are needed for space trajectories due to many reasons including mismodeled or neglected dynamics, navigation errors, missed thrust. The simplest way to guide a spacecraft is to track a reference trajectory: this method is computationally light and can be performed autonomously, however sacrificing optimality. This drawback can be avoided by calculating a new reference trajectory by solving an optimal control problem. However, this task is computationally intensive and thus must be performed on the ground and uploaded on the spacecraft. In this project, we will investigate the use of convex optimization to update trajectories autonomously onboard. We will apply this approach to rendezvous problems around the Earth (e.g. for active debris removal) and to the guidance of interplanetary missions.

The exact characterization of antenna properties is crucial for successful space missions. To enable efficient measurements a scanner is to be developed to move the measurement probe automatically with high precision in the near field of the antenna. The area to be covered is 2m by 2m. The control software for the scanner should be integrated into the existing software for data acquisition and signal analysis, which was coded in Matlab.

Outcome:

• Concept and design of the scanner including actuator and sensor.
• Development of the control software as part of an existing Matlab software.
• Realization at least as a prototype and proof of concept.

Reaction Wheels are a type of actuator typically used to control the attitude and pointing of satellites.  As for all satellite equipment the minimization of mass and volume is of paramount importance. The aim of this project is develop a very thin reaction wheel assembly, to enable the integration of these actuators in nanosatellite or CubeSat satellite wall panels. Electric motors with longitudinal dimension of only a few millimetres are routinely utilized in devices such as Laptop Hard Disks.

As a starting point the capability of these devices to operate in the space environment has to be investigated, and depending on the outcome, a suitable solution need s to be developed to enable their use. The project will then continue with the design and system optimization of the whole Reaction Wheel Assembly. Some hardware will be designed, and assembled with Commercial Off the Shelf components to establish proofs of concepts to de-risk critical areas of the design.

In a previous project a concept was developed for a shock test facility. The concept, design and drawings need to be thoroughly reviewed. Afterwards the manufacturing, assembly and commissioning can start. Software should be developed, which includes both data acquisition and analyses of shock response spectra (SRS). In order to reduce the number of trials to reach the correct shock response spectra, software would be helpful to simulate the resulting SRS dependent on the boundary and initial conditions.

Outcome:

• Reviewed drawings
• Software for measurement and analyses
• Method to predict shock response spectra
• Realization at least as a prototype and proof of concept

Te Pūnaha Atea  – Auckland Space Institute is conducting research into free space optical communications, in particular providing optical communication links between ground and in-orbit satellites. Successful candidates for this research project would tackle one or more of the following as preparatory work for optical communications:

* Designing instrumentation to record reflected light from in orbit satellites,

* Adapting existing telescope systems to track in-orbit satellites,

* Deriving satellite attitude characteristics from recorded reflected time series data.

Successful candidates will have experience in at least some of:

* optical astronomy and astronomical imaging,

* optics and/or optoelectronics,

* electronics,

* time series analysis, image analysis.

At the heart of a satellite is the On-Board Computer (OBC). This project will focus on the performance of a particular new high performance GPU designed for the aerospace industry. The project will involve testing the GPU-based OBC in a simulated space environment. This work will aim to perform qualification testing of the OBC in this environment, running existing example GPU codes to simulate on-orbit demands.

Successful candidates will require:

* GPU programming experience

* Electronics

Desirable experience includes:

* Working with vacuum systems,

* Vibration testing of mechanical systems.

Te Pūnaha Ātea – Auckland Space Institute is conducting a validation exercise with our German research collaborators on a particular design of a Pulsed Plasma Thruster. This research will be to create a thrust balance for our PPT, and operate the PPT in a vacuum chamber, measuring the thrust generated.

Successful candidates will require experience in:

* Applied physics or mechanics,

* CAD.

Desirable experience includes:

* Working with vacuum systems,

* Electronics, particularly power supplies

* Microcontroller programming

Appropriate thermal design is an often-overlooked aspect of CubeSat missions. Available tools for modelling have either a steep learning curve, poor supporting documentation, a considerable price tag, or a combination of all three. Despite this fact, the simplicity of the basic CubeSat lends itself to the development of a user-friendly software tool to provide a first order model of expected thermal performance of a CubeSat on orbit. In addition to supporting both novice and experienced spacecraft developers, the ability to easily change mechanical configurations and switch between standard materials and surface finishes, as well as the effect of different orbital parameters would also make for a valuable teaching aid. The successful candidate will have an understanding of thermal design and experience in software development. The student will perform a survey of existing software packages and a literature review of thermal modelling processes. A set of requirements should be established through consultation with internal and external spacecraft developers, followed by implementation and validation of the software with appropriate datasets.

Outcome:

• Thermal modelling literature review and software survey
• Capture of requirements for a CubeSat thermal modelling tool
• Implementation of an appropriate tool to meet requirements
• Validation of model performance

Project Outline

Te Pūnaha Ātea is developing a plasma propulsion physics research laboratory. This requires the construction of specialist electromechanical and optoelectronic sensors. The work will involve constructing these sensors and their controlling and interface circuits, and testing and validating this equipment. This work will involve becoming familiar with the research to date, and one or more of finalising an existing prototype thrust balance, and assembling a working thrust experiment.

The successful candidate will preferably have experience or training in:

• Applied physics,
• CAD,
• Power and control electronics.

Project Outline

Te Pūnaha Ātea is developing plans to create a New Zealand node of the Australian Optical Communication Ground Station Network. This requires site testing at several potential sites across New Zealand. Site testing comprises (i) astronomical seeing observations to estimate the stability of the atmosphere above the observing site and (ii) cloud and environment testing.

This project will involve conducting seeing observation tests with a Meade LX200GPS telescope configured as a Differential Image Motion Monitor and specialist commercial software.

The successful candidate will preferably have experience or training in:

• applied physics and/or astronomical imaging/astronomy,
• image analysis.

Project Outline

This project investigates ways to design low-delta v escape from the earth sphere of influence and injecting low-cost spacecraft into interplanetary transfers.

It will be assumed that the spacecraft is a secondary payload released on an GTO or Super GTO with constrained orbital parameters (from the launcher or main payload). Different strategies will need to be investigated and tradeoff between escape delta v and time for escape will be performed. The strategies will need to be assessed also by the capability of reaching desired sphere of influence exit conditions as much independently as possible from the initial release orbit. Ways to combine in multiple gravity assists of the Moon, the perturbation of the Sun as well as impulsive maneuvers will be analysed.

The project requires good knowledge of astrodynamics (ODE, gravity assist modelling), analytical and programming skills. Possible mission scenarios include low-cost transfer to small bodies using CubeSat.

Project Outline

Due to the growing population of space objects and increasing activity in space the number of maneuvers that operative spacecraft need to be performed is steadily increasing. In this project we will investigate methods to design such maneuvers that are computationally light to be potentially carried out autonomously onboard, while minimising the use of propellant. The researcher will have to investigate different aspects of the problem including

1. maneuver type (e.g. impulsive or low-thrust)
2. dynamical model (e.g. Keplerian or perturbed dynamic, absolute or relative dynamics)
3. formulation approach (e.g. based on perturbed Lambert solver or optimal control theory)
4. solution method (e..g. numerical vs analytical)

After a first phase of literature review, gaps in the current methods will be identified and a selected research question will be addressed in detail.

A set of test cases available in the literature will be analysed. The project requires good analytical (e.g. for the formulation and solution of optimal control problems) and numerical skills (for the solution of complex two-point boundary value problems).

Te Pūnaha Ātea – Space Institute is looking to launch and operate spacecraft operating in the S and X space operations bands (approximately 2GHz and 8GHz). At these frequencies a large dish antenna is required and the project is to investigate and produce a system to operate in these bands.  A large antenna is available for use with the project, but requires a mount, and servo system to allow it to track Low Earth Orbit (LEO) Spacecraft. Additionally an RF feed system and cable management should be considered within the mechanical design.

Students will consider the requirements relating to tracking satellites in LEO, as well as the environmental considerations of operating large antenna systems. The system specifications will be defined and a mechanical mount and electro-mechanical control system will be designed to meet the specification.

Outcome

• Understanding the requirements of communicating with spacecraft in Low Earth Orbit with large antenna systems
• System specification and environmental loading analyses
• System design of mechanical mount and servo control system

Specialisations

• Mechanical Engineering
• Mechatronic Engineering
• Electrical Engineering

The Tracking, Telemetry and Command (TT&C) subsystem is in charge of communications between satellites and ground stations. Its objectives are,

• To track the position of the spacecraft and follows its using angle, range and velocity information on a regular basis
• To gather information on the health of various subsystems of the satellite
• To receive, verify and execute remote control commands from the satellite ground stations to effect changes to the platform function, configuration, position and velocity.

In this project, students will design and build a part of TT&C for a CubeSat. Based on students’ own interests and experiences,  he/she will involve in one of areas of antenna design, RF front-end design selection and tests (e.g. Low noise amplifier, power amplifier, and RF switch), and transceiver selection and tests. If there is a group students working on this project, eventually, students will work on the overall subsystem integration and tests.

The objective of a high data-rate transmitter in satellites is to transmit application data back to the earth ground station at a high speed. With a higher data-rate transmitting ability, the overall data which can be downloaded from a satellite will be more. There are design challenges by considering CubeSat size and power constrains. Based on students’ own interests and experiences,  he/she will involve in one of areas of antenna design, RF front-end design, selection and tests (e.g. Low noise amplifier, power amplifier, RF filters and RF switch), Software-defined radio (SDR) selection and tests, and GNUradio algorithm developments. If there is a group students working on this project, eventually, students will work on the overall subsystem integration and tests.

Ground station is essential for satellite’s owner, customer and amateur radio operators to communicate with satellites. However most ground station requires antenna to be installed on top of building or tower thus the ground station coverage is fixed. Commercial equipment for field operation is expensive and too bulky for convenience operation. This project aims to design and build a portable ground station system for satellite communication. Based on students’ own interests and experiences,  he/she will involve in one of areas antenna developments with automatic rotator, RF front-end selection and tests, transceiver using software defined radio (SDR) and software based on GNUradio. The goal is to make a low-cost and compact ground station system with high mobility and adaptability. The ground station will be tested with real spacecrafts operating in space, such as International Space Station (ISS), and NOAA satellites.

Satellite data is obtained from satellite in space, which has been useful for us in various applications. For example, remote sensing on satellite images enables us to obtain more information than what is seen by the human eye. Applying Machine Learning on the data obtained from satellite makes it possible to gain better insights by performing analysis and understanding trends. Some applications of satellite data are fire detection, crop yield prediction, deforestation detection, environment monitoring and prediction etc. In this project, students are required to understand how machine learning has been used to analyze satellite data for different applications and to define a useful application as a project example.

The Electrical Power Subsystem (EPS) is a very critical subsystem in a satellite. Its objectives are,

• To supply electrical power to spacecraft loads during the mission
• To control and distribute electrical power
• To provide power conditioning and conversion
• To protect spacecraft against power failure
• To suppress transient bus voltage spikes
• To provide specialized power for specific functions

The EPS failure means loss of the whole satellite mission. In this project, based on students’ own interests and experiences,  he/she will involve in one of areas:

• Energy conversion to convert solar power to electrical power using Maximum Power Point Tracking (MPPT) method
• Energy storage to store the electrical power using commercial batteries
• Power control, distribution and protection to fit into CubeSat applications

If there is a group students working on this project, eventually, students will work on the overall EPS subsystem integration and tests.

Antennas have different forms and work in different operating frequencies with different purposes in satellite communication systems. The objective of this project is to design and test a deployable antenna for small satellites. It will involve literature review of different deployment mechanisms for different types of antennas, defining antenna specifications for certain useful applications, design of the antenna and its deployment mechanism, and verifications of overall design.

The Attitude Determination and Control Subsystem (ADCS) is a very critical subsystem in a satellite. Its objectives are,

• Determination of the orientation of the satellite at any point in time using various sensors
• Process of achieving and maintaining a desired attitude using various actuators

Based on students’ own interests and experiences,  he/she will involve in one of areas:

• Sensor calibrations. The common sensors used in a ADCS are coast and fine sun sensors, magnetometers and gyros.
• Magnetorquer design and control algorithm development.
• Reaction wheel control algorithm development

 If there is a group students working on this project, eventually, students will work on the overall ADCS subsystem integration and tests.

The aim of this project is to develop an integrated ADCS testbed for CubeSat. The testbed consists of the following components:

• Helmholtz cage for magnetometer and magnetorquer testing
• Spherical airbearing platform for Guidance, navigation and Control (GNC) operations
• Sun simulator for attitude determination using sun sensors

Based on students’ own interests and experiences, he/she will work on one of the components.

The structures and mechanisms subsystem mechanically supports all other spacecraft subsystems, attaches the spacecraft to the launch vehicle, and provides for ordnance-activated separation. The design must satisfy all strength and stiffness requirements of the spacecraft and of its interface to the booster. In this project, students will design and fabricate a structure based on a CubeSat standard. Students will also explore an innovative approach to design a structure which can be easily adjusted for different size of CubeSats.