Parameterisation of A Hypersonic Guided Missile

DeGuzman, Leonard (2009). Parameterisation of A Hypersonic Guided Missile Honours Thesis, School of Engineering, The University of Queensland.

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Author DeGuzman, Leonard
Thesis Title Parameterisation of A Hypersonic Guided Missile
School, Centre or Institute School of Engineering
Institution The University of Queensland
Publication date 2009
Thesis type Honours Thesis
Supervisor Russel Boyce
Total pages 98
Language eng
Subjects 0913 Mechanical Engineering
Formatted abstract
According to Riley (2003), the next generation of hypersonic military weapons systems will be powered by supersonic combustion ramjet engines (scramjets). Research is currently being  conducted into applying scramjet technology to military strike weapons; high precision, long range  weapons used to attack high value targets.

This thesis aims to parameterise a hypersonic guided missile in order to explore some of the  scaling relationships that are required for a feasibility study or preliminary design study of a  high speed precision strike weapon.

This thesis considers two hypersonic missile configurations. Arrangement #1 consists of a scramjet  cruise engine accelerated from Mach 1 to 10 by a large solid rocket booster. Arrangement #2  consists of a small solid rocket booster that accelerates a dual-mode ramjet/scramjet engine from  Mach 1 to Mach 2.5. The dual-mode engine operating in ramjet mode accelerates the missile from Mach  2.5 to Mach 7.56, switches to scramjet operation and continues to accelerate to Mach 10, allowing  cruise in scramjet configuration.

Arrangement #2 configurations are smaller and facilitate internal carriage within the next  generation of strike fighter aircraft; however, the complex dual mode propulsion system switching  between ramjet and scramjet modes come at a considerable cost for a single-use strike weapon. This  thesis investigates the relationships associated with different engine combinations by scaling up  the booster in Arrangement #2, systematically replacing more and more of the dual-mode engine until  it reaches Arrangement #1 configuration.

The weapon system is parameterised in terms of size, weight, length and maximum range. The  implications of these relationships on potential future operational employment are considered.  Assessments of the performance characteristics, vulnerabilities, various trends and dependencies of  the system are expressed in terms of the above parameters. The conclusion comments on the system’s  suitability for operational use in a military environment, as well as recommending areas for  future study. The study is presented in a way that allows it to form part of a feasibility study or  preliminary design study of a high speed precision strike weapon.

Keyword Hypersonic Guided Missile

Document type: Thesis
Collection: UQ Theses (non-RHD) - UQ staff and students only
Citation counts: Google Scholar Search Google Scholar
Created: Fri, 18 Sep 2015, 15:40:27 EST by Asma Asrar Qureshi on behalf of Scholarly Communication and Digitisation Service