| 摘要 |
A fibre optic gyroscope for use in detecting the movement and position of aeroplanes and space vehicles, uses a laser diode(LD) at its light source, projecting through a first polariser(P1) to a beam splitter(BS1). One light path leads from the beam splitter to the polarised light separating prism (Pd1) associated with a first light detector(DET1). The second light path is via a second polariser(P2) and control portion (PC1) to the optical fibre(F1) and the optical fibre directional coupler(DCO1) in which four single-mode fibres(F1,F2,F3,F4) are coupled by two ball lenses (L3,L4) and the half mirror(HF) between them.
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