Problem Definition: Linking trajectory optimisation with disciplinary-specific numerical tools can result in numerical system that cannot be defined by ordinary differential equations, and are differential-algebraic systems (DAE). This is the case with shape deformation, aeroelasticity, structural deformation or surface ablation mixed with flight dynamics and optimal control. Multi-fidelity management within a multi-objective constrained closed system design optimisation can allow a highly complex system and environment to be more accurately modelled and simulated, accounting the interactions between all sub-systems balanced with practical limitations of computational efficiency.
Research Objectives:
- Development of effective methods for integrating dynamic shape geometries into numerical solvers for PDAE (algebraic, ordinary and partial differential equations) systems
- Integration and advancement of multi-fidelity management within design optimisation and propagation tools for trans-atmospheric flight systems
- Application to multi-stage launch, ascent, orbital insertion and demise
Expected Results:
- Tools to generate optimal sets of launch vehicle designs and mission designs for sustainability, including robustness, emissions, and debris generation (risk)
- Assessment of the environmental impact at a system level of key parameters during early design phases
- Assessments of different launch systems to inform LCA
Secondments:
- Politecnico di Torino (POLITO, Torino, Italy, ca. 3 months): development/incorporation of propulsion and emissions modelling
- Deimos Engineering and Systems SLU (DEIMOS, Puertollano, Spain, ca. 3 months): high/low fidelity model cross-validation
Main Supervisor:
Co-Supervisors:
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