Numerical and Experimental Techniques for Quantifying Energy Deposition Effects on Representative Hypersonic Vehicle Structures

dc.contributor.advisor Capra, Bianca
dc.contributor.advisor Neely, Andrew Moran, Jeremy 2022-02-10T00:42:21Z 2022-02-10T00:42:21Z 2022
dc.description.abstract There has been a global increase in the research and development of military hypersonic technology. Thermal directed-energy systems have been identified as a capability to defend against hypersonic threats. A numerical and experimental methodology for studying the effects of thermal energy deposition on representative hypersonic panels is presented. This thesis contains four sections, (i) theory and implementation of a first-order, fast, transient thermal-structural code: "Rapid Engineering Determination of Heating over a Trajectory'' (REDHOT), (ii) thermal-structural results from two case studies using REDHOT with energy deposition, (iii) development of an experimental technique to create and measure adverse thermal-structural failure caused by energy deposition, (iv) experimental validation of the technique. The first-order thermal structural code uses the reference-enthalpy method and two-dimensional conduction to calculate the thermal state of a representative hypersonic panel. Thermal stresses are calculated analytically with linear plate theory and non-linear finite element analysis simulation. Numerical results using the HyperX and HEXAFLY-INT trajectory as case studies are presented. REDHOT calculated nominal temperatures without energy deposition are within 1-10% of reported results in literature, acceptable for the first-order analysis in this thesis. Energy deposition is observed to have a greater effect on the skin panel when it is already thermally and aerodynamically loaded. The panel is more structurally compromised for energy pulses of long duration, of higher magnitude and/or applied at times of strong aerodynamic loading. The experimental technique builds on existing electro-resistive heating techniques used for wind tunnel testing. Parametric studies were conducted to understand the design space and determine optimal panel thicknesses and direct-current application to maximise thermal-structural effects. A method to measure the induced thermal strain using digital image correlation was developed. To validate the experimental technique, a model with a 120mm by 80mm graphite panel with varying thicknesses was designed and tested on the bench. For the thinnest available plate, and a direct-current power supply of 350A material failure was not observed. Finite element modelling of the experimental conditions was conducted. Recorded temperatures were approximately within 9% of simulated results. Measured thermal strain was within 0.05% of simulated material.
dc.language English
dc.language.iso en
dc.publisher UNSW, Sydney
dc.rights CC BY 4.0
dc.subject.other energy deposition
dc.subject.other aerothermal heating
dc.subject.other thermal-structural
dc.subject.other hypersonics
dc.subject.other hypersonics vehicle
dc.subject.other hot wall experiment
dc.subject.other joule heating
dc.subject.other FTSI
dc.title Numerical and Experimental Techniques for Quantifying Energy Deposition Effects on Representative Hypersonic Vehicle Structures
dc.type Thesis
dcterms.accessRights open access
dcterms.rightsHolder Moran, Jeremy
dspace.entity.type Publication
unsw.relation.faculty UNSW Canberra School of Engineering and Information Technology School of Engineering and Information Technology
unsw.subject.fieldofresearchcode 400106 Hypersonic propulsion and hypersonic aerothermodynamics
unsw.thesis.degreetype Masters Thesis
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