Equipment planned to be part of space missions is put through a substantial series of tests inorder to ensure a very high degree of reliability. This also applies to the HPGP thrusters manufactured by ECAPS AB. While conducting live fire tests the temperature is monitored using two separate systems, one pyrometer and one Infrared camera. The two systems show a difference in temperature for the same spot on the thruster. This is believed to be due to changes in the emissivity. An experimental setup is designed in order to measure the behavior of the emissivity of this material to decrease measurement errors. The emissivity of the main construction, an aerospace alloy called TZM, is proven to change as function of temperature and surface state, thus giving rise to large inaccuracies in temperature when conducting measurements using an infrared camera.The acquired emissivity data are presented together with a suggested method to implement the results back into the system.
| Identifer | oai:union.ndltd.org:UPSALLA1/oai:DiVA.org:kth-104042 |
| Date | January 2012 |
| Creators | Fors, Erik |
| Publisher | KTH, Rymd- och plasmafysik |
| Source Sets | DiVA Archive at Upsalla University |
| Language | English |
| Detected Language | English |
| Type | Student thesis, info:eu-repo/semantics/bachelorThesis, text |
| Format | application/pdf |
| Rights | info:eu-repo/semantics/openAccess |
| Relation | EES Examensarbete / Master Thesis ; XR-EE-SPP 2012:009 |
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