Fluid-thermal-structural interactions on high-speed aerospace vehicles. Sixteen years after the retirement of Concorde, high-speed commercial flight is once again on the rise with the development of new supersonic business jets and small airliners as well as hypersonic transport and reusable space launch systems. Robust and efficient designs for these light-weight vehicles must address the problem of aerodynamic heating and its effect on structural performance and lifing. This project will desig ....Fluid-thermal-structural interactions on high-speed aerospace vehicles. Sixteen years after the retirement of Concorde, high-speed commercial flight is once again on the rise with the development of new supersonic business jets and small airliners as well as hypersonic transport and reusable space launch systems. Robust and efficient designs for these light-weight vehicles must address the problem of aerodynamic heating and its effect on structural performance and lifing. This project will design and perform first-of-kind experiments that reproduce the complex fluid-thermal-structural interactions representative of those experienced by these aircraft and rockets. We will then use these measurements to assess, validate and improve the current state-of-the-art of simulation and modelling approaches for design.Read moreRead less
Dispersion of spacecraft components during re-entry. Destructive re-entry trajectories for used satellites are designed so debris remaining after re-entry falls harmlessly to the Earth. However, the dramatic increase in the mass of orbiting objects has outpaced improvements in predicting hazardous impact zones. This project aims to develop the experimental and theoretical methods needed to study separation of objects in hypersonic flow in order to better predict the dispersion of debris from re- ....Dispersion of spacecraft components during re-entry. Destructive re-entry trajectories for used satellites are designed so debris remaining after re-entry falls harmlessly to the Earth. However, the dramatic increase in the mass of orbiting objects has outpaced improvements in predicting hazardous impact zones. This project aims to develop the experimental and theoretical methods needed to study separation of objects in hypersonic flow in order to better predict the dispersion of debris from re-entering space objects. New hypersonic wind tunnel experiments, modelling, and computational simulations will be performed to enhance our understanding and improve predictions of how spacecraft components are dispersed during re-entry.Read moreRead less
Discovery Early Career Researcher Award - Grant ID: DE200101674
Funder
Australian Research Council
Funding Amount
$392,310.00
Summary
Novel Testing of a Supersonic Airbreathing Rotating Detonation Engine. Rotating detonation engines offer the potential for improved propulsive efficiency in high speed flight, but the challenges of integrating the advanced detonation combustion process with an airbreathing engine inlet are yet to be met. This project aims to develop a unique Australian testing capability for airbreathing rotating detonation engines and, utilising this capability, to generate unique experimental data to further t ....Novel Testing of a Supersonic Airbreathing Rotating Detonation Engine. Rotating detonation engines offer the potential for improved propulsive efficiency in high speed flight, but the challenges of integrating the advanced detonation combustion process with an airbreathing engine inlet are yet to be met. This project aims to develop a unique Australian testing capability for airbreathing rotating detonation engines and, utilising this capability, to generate unique experimental data to further the operational understanding of airbreathing rotation detonation engines. By contributing essential research to this new engine concept, Australia can forge intellectual capital and international partnerships, and help provide the benefits of cost and weight savings associated with higher performance engines.Read moreRead less
Electron Transpiration Cooling of Hypersonic Vehicles. Future aircraft for flight at hypersonic speeds require sharp leading edges for the best aerodynamic performance. Sharp leading edges incur high heat loads and cannot be adequately cooled with current technologies. The project aim is to investigate novel surface materials that emit electrons when heated. This emission of electrons from the surface can significantly contribute to the cooling of the sharp leading edges. This project is expecte ....Electron Transpiration Cooling of Hypersonic Vehicles. Future aircraft for flight at hypersonic speeds require sharp leading edges for the best aerodynamic performance. Sharp leading edges incur high heat loads and cannot be adequately cooled with current technologies. The project aim is to investigate novel surface materials that emit electrons when heated. This emission of electrons from the surface can significantly contribute to the cooling of the sharp leading edges. This project is expected to deliver new experimental data on novel surface materials exposed to a hypersonic flow environment and computer models that can simulate their cooling effect. This investigation will contribute towards enabling technologies for sustained hypersonic flight by overcoming critical head load limitations.Read moreRead less
Non-equilibrium reacting shock layers. This project aims is to study the non-equilibrium aerodynamic processes involved in hypervelocity flight. The design of vehicles for high speed flight is critically dependent on modelling the interactions between the flow field and the airframe, and the current lack of understanding is restricting the scope and benefit of viable activities in space. The expected outcomes include the ability to design optimised heat shields and air-frames with minimum mass a ....Non-equilibrium reacting shock layers. This project aims is to study the non-equilibrium aerodynamic processes involved in hypervelocity flight. The design of vehicles for high speed flight is critically dependent on modelling the interactions between the flow field and the airframe, and the current lack of understanding is restricting the scope and benefit of viable activities in space. The expected outcomes include the ability to design optimised heat shields and air-frames with minimum mass and maximum payload, precisely targeting specific flight conditions and vehicle shapes. The prospective benefits include increased productivity and reliability and reduced cost of missions to and from space, and a proliferation of new applications which this understanding will facilitate.Read moreRead less
Micro-perforation for passive drag reduction. This project aims to reduce skin friction drag by developing a novel passive flow control method using micro-perforated surfaces. Advanced analytical and experimental modelling will be used to develop specific design solutions to improve efficiency in many real life applications, such as to reduce drag in the aerospace, maritime, gas pipelines and wind turbine industries. Expected outcomes include widely applicable knowledge and skills, improved mode ....Micro-perforation for passive drag reduction. This project aims to reduce skin friction drag by developing a novel passive flow control method using micro-perforated surfaces. Advanced analytical and experimental modelling will be used to develop specific design solutions to improve efficiency in many real life applications, such as to reduce drag in the aerospace, maritime, gas pipelines and wind turbine industries. Expected outcomes include widely applicable knowledge and skills, improved modelling and experimental techniques and tools, and enhanced collaborations. Benefits to Australia are expected to include significant improvements to the efficiency of the aerospace and energy industries, a boost to the Australian economy, and a reduction in carbon emissions. Read moreRead less
Wind Tunnel Testing of a Hypersonic Plasma Engine. This project intends to evaluate an electric engine that is capable of speeds in excess of 10000 km/hr, for access to space and responsive surveillance in our region. The expertise of Lockheed Martin, Lockheed Martin Australia, the University of Qld and DST Group are to be combined to complete experimental and theoretical evaluations of an air-breathing plasma engine that is capable of out-performing rockets and scramjets. US Air Force Research ....Wind Tunnel Testing of a Hypersonic Plasma Engine. This project intends to evaluate an electric engine that is capable of speeds in excess of 10000 km/hr, for access to space and responsive surveillance in our region. The expertise of Lockheed Martin, Lockheed Martin Australia, the University of Qld and DST Group are to be combined to complete experimental and theoretical evaluations of an air-breathing plasma engine that is capable of out-performing rockets and scramjets. US Air Force Research Laboratory results will also be compared and shared. This project provides opportunities for young Australian researchers to be participate and lead an exciting new field of propulsion. It is anticipated that the program will be the foundations to future flight demonstrations from Woomera, Australia.Read moreRead less
Advancing the Science of Giant Planet Atmospheric Entry. This project aims to improve models used to design the heat shields which protect probes entering the atmospheres of the giant planets - four gaseous planets out beyond Mars. Further giant planet exploration is a key planetary science goal of the coming decade. However, the environment which an entry probe would experience features many unknowns and large uncertainties, making a mission a risky undertaking. Using unique experimental capabi ....Advancing the Science of Giant Planet Atmospheric Entry. This project aims to improve models used to design the heat shields which protect probes entering the atmospheres of the giant planets - four gaseous planets out beyond Mars. Further giant planet exploration is a key planetary science goal of the coming decade. However, the environment which an entry probe would experience features many unknowns and large uncertainties, making a mission a risky undertaking. Using unique experimental capabilities and state-of-the-art modelling, the expected project outcome is experimentally validated giant planet entry flow and surface chemistry models. This will allow more efficient heat shields to be designed while also increasing the chance of mission success, furthering our understanding of the universe.Read moreRead less
Discovery Early Career Researcher Award - Grant ID: DE210101072
Funder
Australian Research Council
Funding Amount
$431,722.00
Summary
Beyond Apollo: The interaction of radiation and ablation during Mars return. This project aims to investigate how flow radiation and heat shield ablation products interact under the fastest hypersonic Earth entry conditions ever considered – Mars return. To survive the harsh conditions experienced during planetary entry, spacecraft rely on ablative heat shields burning away through processes which are still not fully understood. Using UQ’s unique X2 hypersonic wind tunnel to generate realistic f ....Beyond Apollo: The interaction of radiation and ablation during Mars return. This project aims to investigate how flow radiation and heat shield ablation products interact under the fastest hypersonic Earth entry conditions ever considered – Mars return. To survive the harsh conditions experienced during planetary entry, spacecraft rely on ablative heat shields burning away through processes which are still not fully understood. Using UQ’s unique X2 hypersonic wind tunnel to generate realistic flight conditions, the expected outcome of this project is an enhanced understanding of the complex ablation radiation coupling physics experienced during Mars return. This will bring humankind closer to travelling to and from Mars and increase our knowledge of these entries and the specialist materials needed to survive them.Read moreRead less
Magnetohydrodynamic Aerobraking for Spacecraft Entry to Earth's Atmosphere. A spaceship returning from Mars will undergo unprecedented aerodynamic heating as it enters Earth's atmosphere. Magnetohydroynamic aerobraking involves applying a strong magnetic field to the plasma which forms around the spacecraft at these speeds, theoretically protecting it by reducing structural heat loads and enabling less severe flight trajectories. This project aims to experimentally study this technology for Eart ....Magnetohydrodynamic Aerobraking for Spacecraft Entry to Earth's Atmosphere. A spaceship returning from Mars will undergo unprecedented aerodynamic heating as it enters Earth's atmosphere. Magnetohydroynamic aerobraking involves applying a strong magnetic field to the plasma which forms around the spacecraft at these speeds, theoretically protecting it by reducing structural heat loads and enabling less severe flight trajectories. This project aims to experimentally study this technology for Earth return from deep space. It is significant because it will evaluate a new mechanism for managing the tremendous heat loads of planetary entry. The expected outcome and benefit will be development of a new technology to reduce spacecraft heating, leading to safer, more efficient, and potentially reusable spacecraft.Read moreRead less