READ ME File For 'High-Temperature Resistojets for All-Electric Spacecraft'
Dataset DOI: 		10.5258/SOTON/D0903
ReadMe Author: 		Federico Romei, University of Southampton

This dataset supports the thesis entitled:
AWARDED BY:		Federico Romei
DATE OF AWARD:		TBD

DESCRIPTION OF THE DATA
This dataset is composed of two folders, each one containing the data supporting the most important figures of Chapter 5 and Chapter 6. 
Each folder contains a dedicated README file with supporting information.

This dataset contains Data supporting the figures as follows:

Fig.3.10-i		Electrical resistivity of selected materials for the STAR resistojet heater. The materials in analysis are highlighted in orange.
				i = 1 (Inconel 718); i = 2 (AISI 316); i = 3 (Re); i = 4 (Ta); i = 5 (W)		
Fig.5.3-i			Specific impulse efficiency optimisation for the three cases in analysis, as function of the diverging angle of the nozzle.
				i = 1 (Inconel 718); i = 2 (Ta); i = 3 (Re);	
Fig.5.9-Ii*		Ignition of STAR-Inc from cold gas stationary solution. Maximum structural temperature (solid line) and Xe stagnation temperature at the inlet of the nozzle (dashed line) are shown at four current levels. The MOT of Inconel 718 is represented with a horizontal dashed line.
				i = 1 (I=17.6A); i = 2 (I=24.4A); i = 3 (I=29.7A); i = 4 (I=34.2A)		
Fig.5.10-top-Ii*	Ignition of STAR-Ta from cold gas stationary solution. Maximum structural temperature (solid line) and Xe stagnation temperature at the inlet of the nozzle (dashed line) are shown at four current levels. The MOT of the two materials are represented with a horizontal dashed line.
				i = 1 (I=17.6A); i = 2 (I=24.4A); i = 3 (I=29.7A); i = 4 (I=34.2A)
Fig.5.10-bottom-Ii*	Ignition of STAR-Re from cold gas stationary solution. Maximum structural temperature (solid line) and Xe stagnation temperature at the inlet of the nozzle (dashed line) are shown at four current levels. The MOT of the two materials are represented with a horizontal dashed line.
Fig.5.11-i*		Pulse-width heating cycle of STAR-Inc with two current levels corresponding to approximately 25 W and 50 W of electrical power.
				i = 1 (top subfigure); i = 2 (bottom subfigure)
Fig.6.24		Thrust transient of the M1 and M2 test series. 

In addition, the dataset containes the following files:
Dry 3D sector-symmetric simulations* results including the following parameters (used as filename):
				time: t#_s
				temperatures: T1#_terminal,T2#_inflow,T3#_casing,T4#_nozzle, T#_12, T#_23, T#_34, T#_max
			#(1 to 4) indicates the test current case
Dry_tests.txt		Raw data of the dry tests, including data supporting Fig.6.25 with solid lines. 
			Variables included:	time: t#
				current: I#
				thermocouples: TC1#_terminal,TC2#_inflow,TC3#_casing,TC4#_nozzle
				PSU voltage: Vpsu#
				Thruster voltage: Vts#
			#(1 to 4) indicates the test current case

*Data at actual time steps taken by the solver.

In addition, a collection of the technical drawings listed in Appendix D is attached in the pdf format.

Date of data collection: 4/06/2014 - 4/01/2018

Licence: Attribution 4.0 International

Related projects/Funders:
	EPSRC, grant no. EP/M50662X/1
	National Space Technology Programme (NSTP-2) fast track project 'High Performance Xenon Resistojet'

Federico Romei
Senior Research Assistant
FEPS, Astronautics Research Group
University of Southampton
federico.romei@soton.ac.uk
T: +44 23 8059 2682