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Title: Conceptual design methodologies appropriate to hypersonic space and global transportation systems
Author: Sziroczak, David
ISNI:       0000 0004 5915 6528
Awarding Body: Cranfield University
Current Institution: Cranfield University
Date of Award: 2015
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The scope of this research is to investigate the design process, and develop methodologies appropriate to the conceptual level designs of hypersonic vehicles; the Space Launcher and the Hypersonic Transport. Currently most large airframe manufacturers are focusing on developing more efficient, cheaper, greener aircraft designs. On the contrary to this trend, since the late 1930s, there is variable intensity, but continuous interest in hypersonic vehicles. Both classes of hypersonic vehicles can deliver capabilities beyond the current state of the art. The ability in itself, to drastically reduce travelling time, could justify the existence of a Hypersonic Transport for applications such as emergency response, time critical business trips, not to mention military applications. Since the recent retirement of the Space Shuttle, all space launches are dependent on expendable launch vehicles, which are inherently high cost and low reliability vehicles. Compared to this contemporary space access technology, Space Launchers offer a significant advantage: they can reach, operate in and return from orbit without expending the vehicle. These days there is definite renewed interest in hypersonic vehicle technology. This thesis explores the design process as a whole, and focuses on the special area of aircraft design. Past, current and future methodologies and trends are discussed, along with the role of computer aided design in modern aircraft conceptual design. The hypersonic vehicle design process is examined in detail. Each of the essential design areas appropriate at conceptual level are investigated; common and state of the art methodologies are discussed. With the explored methodologies, example results are generated, strengths and shortcomings are highlighted. Where appropriate the results are compared to available data, to validate the methodology on a moduleby- module basis. In addition to the piecewise verification, the design process as a whole is demonstrated. An instance of SSTO Space Launcher conceptual design was generated using the GENUS aircraft design environment. Using GENUS it can be concluded that the methodology is adequate to generate a conceptual level hypersonic vehicle design. The limitations of a SSTO design were identified and the relevance and limits of using airbreather engines explored. Potential for future research and focus areas were identified for the key areas of propulsion and structures. The approach for effective use of the design methodology and the GENUS design environment is explained in detail. This critical appraisal and demonstration of methodology is the basis of the quasi-validation of the methodology as a whole.
Supervisor: Smith, Howard Sponsor: Not available
Qualification Name: Thesis (Ph.D.) Qualification Level: Doctoral
EThOS ID:  DOI: Not available