Abstract
Hypervelocity impacts occur frequently in space due to dust that occurs naturally from comets or other space debris often called meteoroids; other debris is man-made and can have disastrous effects on spacecraft. Even though the particle may have a very small mass its momentum can be extremely high and destroy space craft. It is therefore vitally important to simulate the effects of hypervelocity impacts on vulnerable areas of satellites and space stations. A two stage light gas gun was previously developed for this purpose. In this paper we briefly describe two fiber optic based impact measurement systems that were tested at the light gas gun facility at the University of Kent to establish that they could provide data that could not be obtained by any other technique.
Highlights
For surface mounting the Fiber Bragg Grating Sensors (FBG) was attached at ~1.5 cm from the centre of the plate along a line parallel to the plate edge at a distance of 1.75 cm from the plate centre
To enable orthogonal mounting a small hole was drilled through the plate ~2.5 cm from the plate centre along a line parallel to the plate edge
Results data shown in Fig 4(a)&(b) is for an OTFBG; no meaningful data was recovered with SUFBG
Summary
The jig allowed the FBG to be either surface or orthogonally mounted to the plate. For surface mounting the FBG was attached at ~1.5 cm from the centre of the plate along a line parallel to the plate edge at a distance of 1.75 cm from the plate centre. Interrogation The stress induced change in the mean reflecting wavelength of the FBG was converted to the time domain where the data is presented in a waterfall 3 format. This method has the ability to measure high strain at high frequencies.
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