It has been known for four decades that high finesse millimeter-scale optical cavities can produce high-performance, compact optical gyroscopes. Yet, a practical implementation of such a device has been hindered by multiple technical challenges, including Rayleigh scattering and optical nonlinearity of the cavity material. In this Letter we report on the implementation of an integrated passive gyroscope using a monolithic cavity characterized by 7 mm diameter, finesse of 105, and Rayleigh backscattering less than 10 ppm. The device is characterized with quantum noise limited angle random walk of 0.02  deg/h1/2, and bias drift of 3  deg/h, corresponding to detection of rotation-originated optical path change of 1.3×10−16  cm.

Resonant microphotonic gyroscope

Air-core photonic bandgap fibers (PBFs) have great potential for the resonant fiber-optic gyroscope (RFOG), because they reduce both the Kerr-induced drift and the thermal polarization instability. We experimentally studied an open-loop RFOG in which a 20-m resonant loop of 7-cell air-core fiber is closed by connecting the air-core fiber to a conventional single-mode fiber directional coupler. We measured a random walk of 0.055 °/s1/2 and a long-term drift with a standard deviation of 0.5° /s and a peak-to-peak variation of 2.5 °/s over 1 hour. We discuss the sources of error in this RFOG and identify areas for future improvement. We project that with straightforward improvements, tactical-grade performance should be possible.

/pdf/resonant-fiber-optic-gyroscope-using-an-air-core-fiber-59aw6qtny5.pdf

Resonant Fiber Optic Gyroscope Using an Air-Core Fiber

The Kerr effect in an optical passive ring-resonator gyro (OPRG) is analyzed considering the optical source coherence. This effect causes the drift to be much greater than the theoretical limit of rotation sensing given by the detector shot noise for an OPRG with high sensitivity. The drift depends not only on the fluctuation of the power splitting ratio between two counter-propagating beams in the resonator, but also on the frequency modulation indices used to set the operating point. Square-wave intensity modulation of the incident beam is also discussed as a way to eliminate the drift. It is found that the ratio of the signal-beam round-trip time in the resonator to the modulation period must be an integer to optimize the drift elimination. From the practical viewpoint, the requirement for the modulation parameters is analyzed numerically.

Kerr effect in an optical passive ring-resonator gyro

A novel single-polarization single-mode double-ring hollow-core anti-resonant fiber with two single-polarization regions (1545–1553 nm and 1591–1596 nm) is proposed. Single-polarization guidance is achieved by coupling a polarized fundamental mode and silica mode by using different tube thicknesses. Specifically, when the wavelength is 1550 nm, only a single x-polarized fundamental mode with a low loss of 0.04 dB/m is propagated by a polarization extinction ratio of 17662 and minimum higher-order mode extinction ratio of 393 by optimizing the structural parameters. Furthermore, this fiber also exhibits high-performance bend resistance. The x-polarized FM loss is as low as 0.11 dB/m with single-polarization single-mode guidance when the proposed fiber was bent at a bend radius of 8 cm toward the x-direction.

Single-polarization single-mode double-ring hollow-core anti-resonant fiber.

The design, fabrication, and optical characterization of the sensing element of a photonic InP-based gyroscope intended for applications in the field of aerospace and defense are reported in this paper. The sensing element is a spiral resonator coupled to a straight bus waveguide through a multimode interference coupler and exhibits a $Q$ factor of approximately 600 000 with a footprint of approximately 10 mm 2. The design of each component of the sensor is based on some well-established numerical methods such as the Finite Element Method, the beam propagation method, and the film mode matching method. The spiral cavity was designed using the standard transfer matrix method. The selected fabrication process, which is an enhanced version of the standard COBRA process, allows the monolithic integration of the sensing element with the other active components of the gyroscope, e.g., lasers, photodiodes, and modulators. Each component of the fabricated sensing element was optically characterized using an appropriate setup, which was also used for the optical characterization of the whole sensor. Based on the results of the characterization, the gyro performance was evaluated, and a way to improve both the resolution and the bias drift, i.e., down to 10 °/h and 1 °/h, respectively, was also clearly identified. The achieved results demonstrate, for the first time, the actual feasibility of a photonic gyro-on-chip through a well-established InP-based generic integration process.

A High- $Q$ InP Resonant Angular Velocity Sensor for a Monolithically Integrated Optical Gyroscope

A passive fiber-optic resonator technique for rotation sensing has been investigated. Preliminary data show a noise-equivalent rotation-rate sensitivity of 0.5°/h (τ= 1 sec), which is an order of magnitude above the photonshot-noise limit. The major sources of error and ways of reducing such errors are discussed.

Passive fiber-optic ring resonator for rotation sensing.

The observation of a dependence of the measured resonance frequency of an optical cavity on the size and position of the detector is reported and attributed to the presence of higher-order transverse modes in the cavity. This effect, which is due to the nonorthogonality of these modes when averaged over a limited aperture or an inhomogeneous detector surface, has been carefully studied. The results of our calculations are in good agreement with experimental observations. Methods of minimizing such frequency-pulling effects are suggested.

Observation of spatial variations in the resonance frequency of an optical resonator

The resonators investigated include a mirror resonator and also an all -fiber resonator.Preliminary performance data and important sources of error are presented.The interest in passive ring resonator gyros' rather than active resonator2 ones(commonly referred to as ring laser gyros or RLG) is based on the fact that the passiveresonator approach offers very simple solutions to the major problems encountered in RLG's,such as lock -in and other gain medium related effects. In addition, the passive resonatorapproach lends itself to the development of an all solid state optical gyro.The operation of a passive ring resonator gyro is based on the measurement of thedifference in resonance frequency, Af, for counter -propagating fields induced by an inertialrotation rate,

Passive Resonator Gyro

High-finesse fiber ring resonator for rotation sensing

In this paper we summarize recent developments in passive resonator gyros in our labora­ tory. The resonators investigated include a mirror resonator and also an all-fiber resonator. Preliminary performance data and important sources of error are presented. The interest in passive ring resonator gyros1 rather than active resonator2 ones (commonly referred to as ring laser gyros or RLG) is based on the fact that the passive resonator approach offers very simple solutions to the major problems encountered in RLG's, such as lock-in and other gain medium related effects. In addition, the passive resonator approach lends itself to the development of an all solid state optical gyro. The operation of a passive ring resonator gyro is based on the measurement of the difference in resonance frequency, Af, for counter-propagating fields induced by an inertial rotation rate, ft, normal to the plane of the cavity. The dependence of Af on the area, A, and the optical perimeter, P, of the resonator is given by: 4 f A Af - ° o CQ P where fo is the average frequency of the fields propagating in the cavity and co is the speed of light in vacuum. It should be noted that this expression is identical to that for an RLG. Ring resonators may be classified according to the way the light is confined within the resonator, i.e. by using mirrors, optical fibers or thin film waveguides. In each case, the ratio of area to perimeter, A/P, is made as large as possible to maximize the scale factor, 4(fp/c0)(A/P), of the gyro. In order to measure the difference in resonance frequencies (Af) of the counter-propagating directions, light from an external laser (or lasers) is in­ jected into the cavity along both directions to determine the location of the corresponding resonances. The actual measurement of Af may be made by either open loop or closed loop techniques. Closed loop operation may use, for example, acousto-optic frequency shifters (Bragg cells) placed outside the cavity or a Faraday cell placed within the cavity1. In this paper we summarize recent data obtained in our laboratory for a mirror resona­ tor^ as well as a fiber resonator gyro . Figure 1 is a schematic representation of our mirror resonator gyro setup that uses external Bragg cells for closed loop operation. Light from a single frequency 0.5 mW HE-NE laser is split into two beams, each of which is shifted in frequency by a Bragg cell (A/0) before entering the resonator. The polarization of the light is aligned with one of the polarization axes of the resonator. The beam propagating in the clockwise (CW) direction is shifted by a fixed frequency f)_, and the counterclockwise (CCW) beam is shifted by f2. As described elsewhere4, the CW resonance of the cavity is automatically locked to fQ+f^ by means of a primary feedback loop driving a piezoelectrically controlled cavity mirror or mirrors (£Q is the laser frequency). The operation of the feed­ back loop is based on a 32 kHz cavity modulation rate, referred to as fmf with a peak to peak frequency excursion selected to achieve optimum discriminant sensitivity corresponding to the cavity line-width. The signal from photodetector (PD 1) monitoring the output of the CW beam is first passed through a notch filter at 2 fm before phase sensitive demodula­ tion at PSD 1. The resulting discriminant drives the piezo-electric transducer (PZT) through servo electronics.

the calculated photon shot noise given

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