Design Synthesis and Optimisation of VTOL Personal Air Vehicles
Author(s)
Katamish, Omar
Type
Thesis
Abstract
Personal Air Vehicles (PAVs) are envisaged to be the next logical step in mobility to alleviate
modern transport problems. PAVs could combine the freedom of point-to-point personal
mobility with the higher speeds of air travel. Hence the principal aim of this research programme
was to develop a preliminary design and optimisation methodology for an innovative
vertical take-off and landing (VTOL) PAV with a ducted fan propulsion system driven by a
single turboshaft engine. A feasibility study conducted at the start of the programme concluded
that a ducted fan powered VTOL PAV provides a
flexible, quiet and safe point-to-point
mobility platform free from runway constraints and any problems associated with jet efflux or
exposed rotating components. To satisfy VTOL and forward
flight requirements a design and
optimisation methodology for ducted fans and contra-rotating lift fans was developed from a
series CFD tests. With a single engine driving all the fans, a methodology was developed for
the design of a system of interconnecting gears, gearboxes and shafts. To accommodate the
propulsion system and all the other internal components of the aircraft, an innovative tri-surface
configuration was generated by adopting a systems packaging approach. Weight minimisation
through the use of composites and appropriate prediction methods was crucial to reducing the
power requirements and fuel consumption. The aerodynamic surface interaction was explored
and optimised using a vortex-lattice method. The same approach was also used to estimate the
stability derivatives of the aircraft. The overall performance was analysed utilising the data
produced from the above methodologies and that also included an analysis of the transition
from hover to forward
flight. All the above methodologies were integrated to form an automated
PAV design synthesis which in combination with a MATLAB global optimiser is capable
of producing variants of the baseline aircraft that are capable of meeting different mission and
passenger capacity requirements while maximising a specified merit function.
modern transport problems. PAVs could combine the freedom of point-to-point personal
mobility with the higher speeds of air travel. Hence the principal aim of this research programme
was to develop a preliminary design and optimisation methodology for an innovative
vertical take-off and landing (VTOL) PAV with a ducted fan propulsion system driven by a
single turboshaft engine. A feasibility study conducted at the start of the programme concluded
that a ducted fan powered VTOL PAV provides a
flexible, quiet and safe point-to-point
mobility platform free from runway constraints and any problems associated with jet efflux or
exposed rotating components. To satisfy VTOL and forward
flight requirements a design and
optimisation methodology for ducted fans and contra-rotating lift fans was developed from a
series CFD tests. With a single engine driving all the fans, a methodology was developed for
the design of a system of interconnecting gears, gearboxes and shafts. To accommodate the
propulsion system and all the other internal components of the aircraft, an innovative tri-surface
configuration was generated by adopting a systems packaging approach. Weight minimisation
through the use of composites and appropriate prediction methods was crucial to reducing the
power requirements and fuel consumption. The aerodynamic surface interaction was explored
and optimised using a vortex-lattice method. The same approach was also used to estimate the
stability derivatives of the aircraft. The overall performance was analysed utilising the data
produced from the above methodologies and that also included an analysis of the transition
from hover to forward
flight. All the above methodologies were integrated to form an automated
PAV design synthesis which in combination with a MATLAB global optimiser is capable
of producing variants of the baseline aircraft that are capable of meeting different mission and
passenger capacity requirements while maximising a specified merit function.
Date Issued
2012-03
Date Awarded
2012-07
Copyright Statement
Attribution NoDerivatives 4.0 International Licence (CC BY-ND)
Advisor
Serghides, Varnavas
Publisher Department
Aeronautics
Publisher Institution
Imperial College London
Qualification Level
Doctoral
Qualification Name
Doctor of Philosophy (PhD)