Propulsion and Aerodynamic Control of a Spin-stabilised Circular Planform UAS

About the Project

Please note, there is no funding attached to this project. All tuition fees and any other associated costs (including bench fees) must be financed by the student. Please consider this before submitting your application.

PhD Research Topic

The most recent work in spin stabilised disc wing aerodynamics (Kamaruddin, Potts & Crowther, 2018) suggests a controllable uninhabited aerial system (UAS), comprising a pulsed jet propulsion system, combined with a geometric skin morphing aerodynamic control system would offer novel in flight manoeuvrability relative to more conventional fixed wing and rotor aircraft. The proposed research would seek to demonstrate the propulsion and aerodynamic control capabilities, initially using lab-based fluid flow simulation and experimental tools, then to develop a UAS platform capable of short in-flight systems demonstrations to establish the flight envelop.

Aim

The overall aim is to establish the capabilities of an in-flight demonstrator, including propulsion and aerodynamic control in six degrees of freedom.

Objectives

1. Determine a suitable aerodynamic geometry as the focus UAS platform using CFD simulations, then validation via wind tunnel test.
2. Aerodynamic characterisation of propulsion and control methodologies, again using CFD simulations, then validation both on the bench and via wind tunnel test.
3. Develop a UAS system using open-source Arduino technologies (or similar) capable of controlling the aircraft platform and recording in-flight data.
4. Conduct in-flight demonstrations to establish the flight envelop.

Methodology

The programme will be split into four work packages, WP1 – WP4.

WP1 Aerodynamic Planform Geometry Definition

An aerodynamic planform geometry must be chosen carefully to enable the effective integration of propulsion and aerodynamic control methodologies. The chosen geometry will be a design trade off between highly sensitive parameters such as lift to drag ratio, rolling moment coefficient and thrust to weight ratio. Parametric sets of planform geometries will be analysed using commercial CFD simulation software, then promising geometries will be validated in the wind tunnel.

WP2 Propulsion and Aerodynamic Control Methodologies Definition

The propulsion methodology will be a pulsed air jet system, gaining added efficiency through entrainment. Roll control will be achieved through skin morphing to modify the wetted surface geometry of the airframe. Pitch control will be gained cyclically using fluidic effectors, strategically positioned on the airframe surface. Parametric sets of propulsion and aerodynamic control specifications will be analysed using commercial CFD simulation software, promising methodologies will be validated in the wind tunnel.

WP3 Uninhabited Aerial Systems Development

The mechanical and fluidic systems will be deployed on the down selected planform geometry. An open-source Arduino (or similar) UAS will be developed to integrate propulsion and control sub-systems with in-flight data capture, to record the aircraft motion and position in 6DOF. The systems will be fully integrated and tested on the bench, then tethered testing conducted in the wind tunnel.

WP4 Flight Test Campaign Demonstrations

A flight test campaign will demonstrate the performance of the propulsion and aerodynamic control methodologies, as independently as possible initially, then together in an increasingly integrated approach to extend the flight envelop. Post-processing of the in-flight data set will provide evidence to support the definition of proposed mission profiles.

Eligibility

Applicants should hold a 1st or 2:1 Honours degree in Aerospaceor a related discipline. A Master’s degree in a related area is desirable. We welcome applications from all candidates irrespective of age, pregnancy and maternity, disability, gender, gender identity, sexual orientation, race, religion or belief, or marital or civil partnership status.

International candidates are required to provide an IELTS certificate with a score of at least 6.5 overall , and a minimum of 6.0 in all components. For further information on English Language requirements, please click here.

How to apply

To apply, please use ouronline application form.

As part of your application, please upload:

• A research proposal (max. 1500 words) in your own words, briefly outlining the proposed research, the current knowledge and context referencing key background literature; a proposed methodology or approach to answer the key questions, and any potential significance or impact of the research
• Copy of your highest degree certificate
• Non-UK applicants must submit IELTS results (or equivalent) taken in the last two years and a copy of their passport.

Applicants must provide 2 references, with at least one to be academic. References must be received directly from the referees.

We strongly recommend you contact the lead academic, Dr Jonny Pottsj.r.potts@shu.ac.uk, to discuss your application.

Information about our research degrees can be found here.

Funding Notes

There is no funding attached to this project. The applicant will need to fund their own tuition fees, as well as any associated bench fee and living expenses. The home tuition fee for 25/26 is £5,006 and the international tuition fee for 25/26 is £17,725 (not including any applicable bench fee). For further information on fees, visit View Website.

References

KAMARUDDIN, Noorfazreena M., POTTS, Jonathan R. and CROWTHER, William J. (2018). Aerodynamic performance of flying discs. Aircraft Engineering and Aerospace Technology, 90 (2), 390-397.