Flight dynamic modelling and parameter identification of Single Engine (SE) Vertical Take-Off and Landing (VTOL) Air Mobility Aircraft

About the Project

Background

Uncrewed Aerial Systems and their larger cousins, Advanced Air Mobility vehicles represent the next stage of evolution of aviation. With current advances in technology, this class of vehicles represent ‘the last mile‘ of air transportation. Coupled with the current increased awareness of environmental preservation (i.e. zero-carbon footprint and noise reduction) as well as the increasing levels of achievable autonomy, development has accelerated in recent years.

However, this has also led to much hype developed through social and non-technical media. Consequently, the last challenge has been frequently overlooked, which is the capability to fly the distances required such that these vehicles become an actual game changer. Additionally, this has to be achieved at a cost comparable to current mobility-on-demand modes of transport. This necessitates research into viable air vehicle technology. One solution to this challenge is a hybrid VTOL fixed wing vehicle powered by a single power unit ( i.e. an internal combustion engine or gas turbine engine driving multiple propellers through an optimised drivetrain). The single power unit will reduce complexity, air vehicle certification, optional pilot requirements and maintenance costs associated with multi-engine aircraft.

Given that this configuration cannot be independently controlled using the same mechanism as the common multi-electric motor platform, a different control mechanism must be used. This would comprise both conventional fixed propellors for lift, and variable pitch and plane propellors for directional control and stabilisation, through the different stages of its flight envelope.

The integration of electric motors into airframes and the resulting aerodynamics have been well investigated. So have the impact of tilt rotors on the outer portion of the wing. However, the dynamics of variable pitch and variable plane thrusters embedded within aerodynamic lifting surface airframes has not been well studied. This is to the extent that the current flight dynamics models developed for electric VTOL air mobility vehicles cannot be used for this type of air vehicles. It is proposed that this programme of research does the following.

Objectives

Firstly, it is to see how different the flow interaction with the airframe is with respect to an electric fixed pitch propeller vs a variable pitch propeller. This has to occur at every stage of the flight envelope.

Secondly, the dynamics of the variation also has to be investigated. This is the variation of the force and moment parameters on a generic vehicle of this class with a corresponding variation of pitch and rotation plane of the thruster blades. It is anticipated that the dynamics of these type of vehicles will differ from electric multirotor VTOL or tilt-wing electric VTOL aircraft.

Aim

A flight dynamics model to be developed which can be used for certification and handling qualities for this class of aircraft.

Methodology

The investigation will utilise both wind tunnel experiments, ground rig tests and complex CFD and MATLAB simulations

Output

1. PhD thesis (placed in open access repository)
2. Technical open-source reports
3. Journal and conference paper publications
4. Possible build of a scaled demonstrator with an external partner from industry

Desired candidate profile

The desired candidate should preferable have a good undergraduate degree or masters degree in one of the following programmes:-Aeronautical engineering, aerospace engineering, aircraft engineering. In addition, the candidate should be able to demonstrate a good understanding of most of the following domains of knowledge:- flight static and dynamic stability, principles of air vehicle design, flight vehicle aerodynamics, aircraft performance and aircraft handling qualities.

Please use this Research Proposal, Personal statement, and CV GUIDEwhen preparing an application.