Scramjet Engine Fluidic Thrust Balancing to Achieve Side Loading

Davy, Brendan (2017) Scramjet Engine Fluidic Thrust Balancing to Achieve Side Loading. [USQ Project]


The purpose and aim of this project is to study the effects of thrust vectoring through fluidic within an axisymmetric nozzle to achieve a percentage of side loading. The aims of this project are then to study these effects mathematically, and to gain the relevant data for testing and experimentation of thrust vectoring. By mathematically modelling thrust vectoring, an indication to the inputs that are required in order to gain a specific thrust loading can be determined for physical experimentation. In addition to this, the data obtained from calibration tests and the conducted experiments can then be used for further research into thrust vectoring. Whereas, by determining the effects of side loading, as well as the causes behind the side loading effects. This project can then be successful in determining new methods of manoeuvrability, as well as increasing the control over the scramjet engine in hypersonic flight.

The methods used to conduct the experiment will then consist of 3D model designing, mathematical modelling, manufacturing through 3D printing and machining, and physical experimentation at the TUSQ. In addition to this, physical experimentation will use the Mach 6 nozzle to engage hypersonic flow, and a load cell to measure the forces that are occurring from the experiment. However, before the experiment can be conducted, the loading cell will have to be calibrated to ensure that the forces can be measured at the high speed. Whereas, the use of a schlieren system will be able to provide visual evidence that the hypersonic flow has been achieved, and the model can maintain this flow. The results obtained from this project found that the modelled design was able to withstand the hypersonic flow, while also being able to develop thrust. In addition to this, the schlieren images illustrated that hypersonic flow was achieved, and that the nozzle was able to maintain this flow.

However, the results from this experiments also illustrated that there was a 50z interference with the loading cell, and the silicon joined section was also effecting the measure force data. Due to this interference further calibration was required, which prevented further thrust vector tests. Therefore, from the results of this experiment, it was then found that another method for the joining section between the outer shroud and the nozzle was required in order to isolating the nozzle and gain the physical loading.

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Item Type: USQ Project
Item Status: Live Archive
Additional Information: Bachelor of Engineering (Mechanical Engineering)
Faculty/School / Institute/Centre: Historic - Faculty of Health, Engineering and Sciences - School of Mechanical and Electrical Engineering (1 Jul 2013 - 31 Dec 2021)
Supervisors: Buttsworth, David
Date Deposited: 06 Sep 2022 22:54
Last Modified: 06 Sep 2022 22:54
Uncontrolled Keywords: thrust vectoring; side loading; scramjet engine; hypersonic flight

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