Publication:
Numerical and Experimental Techniques for Quantifying Energy Deposition Effects on Representative Hypersonic Vehicle Structures
Numerical and Experimental Techniques for Quantifying Energy Deposition Effects on Representative Hypersonic Vehicle Structures
dc.contributor.advisor | Capra, Bianca | |
dc.contributor.advisor | Neely, Andrew | |
dc.contributor.author | Moran, Jeremy | |
dc.date.accessioned | 2022-02-10T00:42:21Z | |
dc.date.available | 2022-02-10T00:42:21Z | |
dc.date.issued | 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.identifier.uri | http://hdl.handle.net/1959.4/100078 | |
dc.language | English | |
dc.language.iso | en | |
dc.publisher | UNSW, Sydney | |
dc.rights | CC BY 4.0 | |
dc.rights.uri | https://creativecommons.org/licenses/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.accessRights.uri | https://purl.org/coar/access_right/c_abf2 | |
unsw.identifier.doi | https://doi.org/10.26190/unsworks/1988 | |
unsw.relation.faculty | UNSW Canberra | |
unsw.relation.school | School of Engineering and Information Technology | |
unsw.relation.school | School of Engineering and Information Technology | |
unsw.subject.fieldofresearchcode | 400106 Hypersonic propulsion and hypersonic aerothermodynamics | |
unsw.thesis.degreetype | Masters Thesis |
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