Invited Paper ABSTRACT. Keywords: Fiber gyro, fiber optic gyro, FOG, IFOG, RFOG, fiber resonator, resonator fiber optic gyro, laser gyro.

Transcription

1 Invited Paper Fiber optic gyro development at Honeywell Glen A. Sanders *a, Steven J. Sanders a, Lee K. Strandjord b, Tiequn Qiu a, Jianfeng Wu a, Marc Smiciklas a, Derek Mead a, Sorin Mosor a, Alejo Arrizon a, Waymon Ho a, Mary Salit b a Honeywell International, N. 19 th Ave, Phoenix, AZ USA b Honeywell International, State Highway 55, Plymouth, MN, USA ABSTRACT Two major architectures of fiber optic gyroscopes have been under development at Honeywell in recent years. The interferometric fiber optic gyro (IFOG) has been in production and deployment for various high performance space and marine applications. Different designs, offering very low noise, ranging from better than navigation grade to ultra-precise performance have been tested and produced. The resonator fiber optic gyro (RFOG) is also under development, primarily for its attractive potential for civil navigation usage, but also because of its scalability to other performance. New techniques to address optical backscatter and laser frequency noise have been developed and demonstrated. Development of novel, enhanced RFOG architectures using hollow core fiber, silicon optical bench technology, and highly stable multifrequency laser sources are discussed. Keywords: Fiber gyro, fiber optic gyro, FOG, IFOG, RFOG, fiber resonator, resonator fiber optic gyro, laser gyro. 1. INTRODUCTION Guidance and Navigation (G&N) represents one of the core business elements within Honeywell Aerospace. Figure 1(a) shows the breadth of platforms on which Honeywell G&N systems are deployed for a multitude of land, sea, air, and space applications. And inertial sensors are necessarily at the heart of these G&N systems. For this reason, Honeywell has been developing, designing, manufacturing, and selling gyroscopes for nearly 5 decades. Microelectromechanical Systems (MEMS), Ring Laser Gyros (RLG), and Fiber-Optic Gyros (FOG) all form key pieces of Honeywell s inertial sensor portfolio. Figure 1(b) shows the rough mapping of these various gyro technologies to applications according to their performance classes: MEMS gyros primarily target the tactical market needs. RLGs satisfy a wide range of high-volume applications spanning the spectrum from high-end tactical performance through navigation-grade. As can be seen in the figure, Honeywell FOGs service the niche of the most demanding long-life applications in space, submarine, and strategic applications. Although this high-performance market segment is much lower in volume than mainstream navigation applications, the rigorous performance and life requirements (nav-plus through strategic grade) maintain an active demand for IFOG products. Defense Nansi ORS Teal 0., O mm Adjacent Commercial MU Customer value r Tactical Missiles UAV5 Guided Projectiles Smarr Weapons Sensor Mil /First Stabilization Responder Genera/ Aviation Personal Nav Commercial, Space 8 Military Aircraft 8 Land Vehicles Space Submarine Strategic \1 Sensor Precision )Navigation Tactical 1000 Consumer Tactical Navigation Precision Figure 1 Honeywell s navigation and inertial sensing portfolio *glen.a.sanders@honeywell.com; phone ; Fiber Optic Sensors and Applications XIII, edited by Eric Udd, Gary Pickrell, Henry H. Du, Proc. of SPIE Vol. 9852, SPIE CCC code: X/16/$18 doi: / Proc. of SPIE Vol

2 To address the navigation-grade-plus through strategic market and beyond, over the last 25 years Honeywell has developed a number of interferometric FOG (IFOG) products utilizing both polarization-maintaining and depolarized closed loop architectures as the high-performance complements to its navigation-grade RLG product lines. These IFOG designs provide precision guidance and pointing in the deg/hr range to the deg/hr range of bias instability and represent mature and deployable products. The IFOG measures the interference of two counter-propagating light-waves in the fiber-optic loop of a Sagnac interferometer to measure inertial rotation rate. Rotation sensitivity is tunable by scaling the length-diameter (LD) product of the Sagnac coil, and excellent signal-to-noise ratios can be obtained: minimum detectable signals can be below a single rotation per century. Excellent bias stability is obtained with a broadband light source and the well-known minimum reciprocal architecture 1, while scale factor (SF) instability and SF nonlinearity in the range of single-digit parts per million (PPM) can be achieved using closed feedback-loop electronics to null and linearize the rotation signal 2. In Section 2 we give a survey of active Honeywell IFOG products and developments. The resonator fiber optic gyro (RFOG) measures rotation rate by using the frequency shift between clockwise (cw) and counterclockwise (ccw) resonances in a multi-turn fiber ring resonator 3,4. Despite its less proven performance, the development of the RFOG has been motivated by its potential to achieve the same rotation-sensing performance in a more attractive form factor than the RLG and IFOG 5. This improvement is due to the fact that RFOG combines the signal to noise sensitivity enhancements of the RLG and IFOG, given that the light is recirculated around the loop many times (signified by the resonator finesse, F) and multi-turn coils can be deployed to increase path length well beyond that of an RLG. The same shot noise-limited signal to noise sensitivity can be obtained in an RFOG of F/2 less fiber length than that of an IFOG of comparable diameter and optical power. Thus, for a finesse of 100, the shot-noise-limited angle random walk (ARW) sensitivity of the RFOG should be obtainable with fifty times less fiber than the IFOG counterpart. Hence, RFOG development is motivated by the promise of an inexpensive, small optical gyro for commercial navigation applications. However, the technical barriers to performance become significantly more challenging due to the requirements of a resonant design, and in particular, the need for a highly stable, truly coherent narrow-linewidth light source and at least one high-quality frequency shifter. While the use of a broadband light source solved many issues in the IFOG case, RFOG requires different solutions for mitigation of problems such as optical backscatter, Kerr Effect, and Stimulated Brillouin Scattering. These solutions, and progress towards mitigation of optical backscatter effects using a novel RFOG architecture, are discussed in the Section IFOG STATUS 2.1. Navigation-plus Grade IFOGs Honeywell IFOG efforts began in the mid-1980s, with first products being tactical-grade gyros for attitude, heading, and reference systems (AHRS) on commercial aircraft. Flight production started in the mid-1990s and over 5000 open loop gyros were built and sold for both commercial and business commuter jet use. More recent IFOG products at Honeywell are more focused on higher-performance, radiation-hardened, and long-life niches inaccessible to other gyro technologies such as MEMs and RLG. One such niche is in the nav-plus performance range deg/hr bias instability 0.01 deg/hr and deg/sqrt(hr) ARW deg/sqrt(hr). Two product offerings in this class are mature and in active production today. The first is the SPIRIT IMU, designed for long-life space applications to low-noise platform stabilization. Figure 2(a) shows a photo of the IMU, which boasts 4 IFOGs, 2 optional banks of 4 accelerometers, redundant low-voltage power supplies (28-50V & V inputs optional), and Mil-Std-1553 and RS-422 interfaces. This fault-tolerant unit completed space qualification in 2014 and is in production for commercial and military applications today. Six units have been delivered, with three more scheduled for delivery in 2016 and additional units on order for the foreseeable future. These gyros utilize a depolarized sensing loop 6 shown conceptually in Figure 2(a), rather than a simpler polarization-maintaining coil (c.f., part[c] of the Figure) to leverage the inherent radiation tolerance and cost benefits of non-polarization-maintaining, single-mode optical fiber. Proc. of SPIE Vol

3 (b) Single -Mode Architecture Depolarizers To /from loop coupler Integrated Optics Chip To /from loop coupler (c) Polarization Maintaining Architecture < z Integrated Optics Chip Figure 2 (a) Photo of Spirit IMU. (b) Basic depolarized and (c) polarization-maintaining IFOG architectures. With the depolarized architecture, SPIRIT is radiation-hardened and qualified for MEO environments as well as manmade hazards. Figure 3(a) plots typical de-trended angle from these gyros, giving noise-equivalent angle (NEA) of a few asec, adequate short-term pointing performance for many commercial and other space applications. A root-allan variance of typical bias performance, under spacecraft thermal conditions (typically ±10 C over 10-20hrs), is given in Figure 3(b): all gyros have bias instability in the range of deg/hr (1 ). Finally Figure 3(c) presents characteristic SPIRIT scale factor instability under the same thermal conditions; approximately 100ppm pk-pk error is typical. SF Shift (ppm) Detrended Angle (asec) ee e e e e Root Allan Variance (deg/hr) ql: 8a Á Á j 4 44 Figure 3 (a) Typical short-term angle drift performance. (b) Root Allan Variance of typical short-term bias performance under characteristic spacecraft thermal profile. (c) Typical short-term scale factor instability under the same thermal profile. IFOGs in the SPIRIT performance class are also available as single-axis sensors, as shown in Figure 4. Individually shielded, sense heads are provide very low magnetic sensitivity and offer guaranteed bias instability and ARW commensurate with the IMU performance discussed above. These gyros are in active production in quantities of roughly per month. Proc. of SPIE Vol

4 Figure 4 Family of depolarized, single-axis gyro sense heads in the performance class of the SPIRIT IMU gyros Strategic Grade IFOGs The next performance range of interest for Honeywell IFOGs is strategic-grade, i.e., deg/hr bias instability deg/hr and deg/sqrt(hr) ARW deg/sqrt(hr). This range of applications is addressed by two IFOG products which began development in the late 1990s and entered low-volume production in the early 2000s. One of these gyros is the High-Performance Space FOG (HPSFOG), serving the most demanding space pointing needs. An HPSFOG typically delivers short-term pointing instability 10 nrad, bias instability in the range of deg/hr over a typical diurnal thermal profile, and total scale factor error in the single-digit PPM range. Serving a low-volume but nevertheless highly demanding market segment, Honeywell strategic IFOGs are produced in volumes of roughly 5-10 per year Reference Grade IFOGs Honeywell has developed a prototype IFOG in a class we call reference grade, namely bias instability deg/hr and ARW deg/sqrt(hr). With the sensing loop shown conceptually in Figure 5, this gyro is intended for a possible new range of applications in earth and scientific sensing, rather than as a compact unit for vehicle guidance and navigation. Figure 6 illustrates the reference-grade bias and ARW of this sensor: in a month-long segment of data, uncompensated bias instability is better than deg/hr and the ARW is about deg/sqrt(hr) (16 deg/sqrt(hr)). Figure 7 gives typical angle noise data for this gyro: NEA is about 300 nrad over 30 minutes and angle white noise is less than asec/sqrt(hz). Some non-white angle noise is visible in the Hz range, clearly an artifact of test equipment contamination which can be improved in the usual straightforward ways. The aggregate performance of this gyro compares well to the best published performance (to our knowledge) of any practical laboratory instrument. For example, the ARW here is comparable to that of state-of-the-art atomic gyros 7, but the IFOG is far more mobile and reproducible as a piece of engineering equipment. Similarly, the IFOG bias instability and angle white noise compare favorably to the best-ever published data for a hemispherical resonator gyro 8. Hence, we believe the noise and bias performance of this reference-grade IFOG may be useful in a range of metrology, seismic, and structural sensing applications, as well as calibration of inertial test equipment. Proc. of SPIE Vol

5 Figure 5 Sensing Loop Assembly of Reference-Grade Gyro RAV: ARW udeg/rthr. AWNß.105e-05 asec/rt-hz > bias instability < ~ 30µdeg /hr over 1 month C7 ARW = 16 µdeg/hr1/ , I I Ó Time(hr) Figure 6 Root Allan Variance of month-long run of Reference-Grade Gyro E Dew.] wo.hr-«` wear, 0,1.1 n, civlo IP,LIi(' IOWA' I7J i111i1dilt!.,iii:i :!sii I, IIUIt 'I.'IÜ1; I Al `!fllltll: I: i`,i lu, I 1L:'IillfllAAlllllllllllf N EA = 0.065asec -310 nrad lifilleheembiesliffiga 1 O i MM (N(! f r. ; < AWN < asec /rthz (b) r,.,q1. ytrv> Figure 7 Typical reference-grade gyro data: (a) Detrended angle over 30 minutes showing NEA, (b) Angle root power spectral density (PSD) showing Angle White Noise. Proc. of SPIE Vol

6 3. RFOG DEVELOPMENT The basic principle of the RFOG, being based on the passive cavity technique 3, is shown in Figure 8 below. Light from a highly coherent laser at frequency f 0 is split into two waves, one of which is frequency shifted by frequency f before each wave is introduced into a fiber ring resonator. To track the resonance frequencies of the resonator, optical frequencies f 0 and f 0 + f are tuned to be centered on the counterclockwise (ccw) and clockwise (cw) resonances of the resonator using a standard phase sensitive detection technique for sensing line center. Resonance is sensed in transmission through the optical ring resonator by two photodetectors (PD). In the presence of rotation, the necessary frequency shift to track resonance between the two waves will be given by f= DΩ/nλ, where D is the diameter of the coil, n is the index of refraction of the fiber, λ is the optical wavelength, and Ω symbolizes the rotation rate. Laser f0 CCW input PD f f Frequency Shifter CCW resonances f0 + f CW input PD f 0 CW resonances f 0 + f Figure 8. Basic principle of RFOG operation New RFOG Architecture The basic architecture of Figure 8 has several challenging issues related to its implementation and performance. The use of a single laser plus a frequency shifter was originally chosen so that relative frequency noise between cw and ccw inputs was minimized. In this way, any low frequency laser jitter in the rotation band between cw and ccw waves was common to both inputs; thus, not appearing as rotation-induced resonant frequency changes. Laboratory designs have centered on the use of acousto-optic frequency shifters which require high drive power, and are expensive and large. Integrated optic, or serrodyne-type frequency shifters using lithium niobate, suffer from either poor sideband suppression, or from size and cost issues. This has been one factor leading Honeywell to the use of the multi-laser architecture 9, shown below. This RFOG configuration does not use frequency shifters to derive the different-frequency light waves needed to independently track cw and ccw resonance peaks, but rather separate semiconductor lasers. The architecture also facilitates the use of an improved method to reduce errors from optical backscatter by locking to the lasers a free spectral range apart. In the architecture of Figure 9, it is imperative to highly suppress relative frequency jitter in the sub-hz to 100 Hz frequency region of the rotation sensing spectrum. Magnitudes in the milli-hertz region are needed near DC so as to not add excess ARW that exceeds the requirement for navigation-grade sensing. This is now becoming realizable using ultra-high gainbandwidth phase lock loops to lock the lasers together. As shown in Figure 9, there are three laser diodes in a multifrequency laser source used in the RFOG approach. A master laser is used to perform a tight lock between the laser array Proc. of SPIE Vol

7 and the resonator. This design uses feedback from the high speed port of the resonator, namely the reflection port in combination with phase modulation applied by PM 3 to adjust the Master Laser frequency to a resonance of the resonator. This loop uses the well-known Pound-Drever-Hall technique to provide very a high gain-bandwidth loop. The slave lasers are then locked to the Master Laser by interfering them with the Master to obtain a beat-note, and then maintaining the beat note to an offset frequency via an Optical Phase Lock Loop (OPLL). The end result is that Slave Lasers 1 and 2 are now stabilized with respect to each other via electronic means instead of using optical frequency shifting means. Slave lasers 1 and 2 are introduced into the resonator in the cw and ccw directions, respectively. Each of them is sensed in transmission through the resonator and locked to the top of the resonance via a resonance tracking loop. The resonance tracking loops rely on phase modulation imparted by PM1 and PM2 to produce a frequency modulation over the resonance lineshape that is used to ascertain resonance line center. A different phase modulation frequency is applied to PM1 and PM2, so as to separate the intensity of back-reflected waves from the main signal wave, as suggested by Iwatsuki, et al 10. The intensity of each slave laser is stabilized via an intensity modulator (IM) in a feedback loop (not shown) to reduce the effects of the optical Kerr Effect. PDH loop CW Resonance Tracking CCW Transmission port Slave Laser 1 Circulator Fibercoupler CW reflection.rt Master Laser Resonator fiber coil Circulator Slave Laser 2 IMI PM 2 IMI Fiber coupler CW Resonance Tracking CW Transmission port Figure 9 Improved RFOG Configuration using phase-locked lasers Another significant challenge to realizing a navigation grade RFOG that is addressed by the configuration of Figure 9 is that of interference due to optical backscatter 11,10,12. Backscatter from one wave into another causes beats at their frequency difference which at low rotation rate, is an oscillatory error in the rotation rate band of interest. This has been shown to produce dead-zone behavior in closed loop operation 13 or the lock-in effect, without sufficient countermeasures. The RFOG arrangement using separate lasers allow this issue to be addressed: The slave lasers are offset by a large frequency difference to prevent the deleterious effects of backscatter from one direction into another. By locking to adjacent longitudinal resonances, as shown in Figure 10, backscatter from one wave into the other produces a beat note that is at a high frequency because the free spectral range is included in their frequency separation (e.g., 2 MHz for a resonator of 100 m length that is not rotating). The phase locked loops are instructed by the resonance tracking control loops to tune the laser frequencies to resonance peaks that are separated by a free spectral range plus a variable frequency f (for rotation rate). Proc. of SPIE Vol

8 Resonance Mode Structure CW Laser Locked CCW Laser Locked o 0.5 Frequency (MHz).5 Figure 10 Ring resonator modes for clockwise (blue) and counter-clockwise (green) propagating directions. The cw laser frequency is locked onto the lower longitudinal resonance, whereas the ccw laser frequency is locked to the higher-frequency longitudinal resonance. The two resonances in each direction are separated by 1 free spectral range (FSR), and the cw and ccw resonances are shifted by f, due to rotation rate RFOG Experimental Results An RFOG of the arrangement shown in Figure 9 was built and tested for scale factor performance to verify its benefit to reducing the effects of backscattered light. The resonator total length was nominally 100 meters, and consisted of two polarization maintaining fiber couplers, a polarization maintaining fiber coil, and two short strands of polarizing fiber. The latter is used for eliminating light in the undesired polarization state of the fiber within the ring 14. The free spectral range was roughly 2 MHz. The lasers were narrow-linewidth semiconductor lasers operating at nominally 1.55 μm wavelength. Performance data was taken for the scale factor linearity, scale factor stability, and linearity about a region near zero rotation rate (dead-band test) all of these performance characteristics are known to be degraded with backscattered light. It was also an objective to demonstrate the functionality and the range of the multi-frequency source. The gyro was mounted on a turn-table as shown in Figure 11(a). With the gyro s sensitive axis pointing along the applied rate, the gyro output vs rate was recorded across a rotation range of ± 500 /s. As shown in Figure 11(b), there is a very linear relationship between resonance frequency shift and rotation rate. To further quantify the scale factor linearity residuals, the gyro was pre-calibrated by an initial runs forming a lookup table, and subsequent runs were measured relative to the lookup table. The residuals in parts per million (ppm) versus rotation rate are shown in Figure 11(c). The 1 sigma deviation of the residuals was computed to be less than 25 ppm. Proc. of SPIE Vol

9 SS0 500 ISO (a) b Seals Factor Linearity Input Rita (doesec) (b) 20 o i I ZOO Rotation R.R. (d.pl..e) 200 RotRotation (C) OCIO COO Figure 11 RFOG scale factor linearity tests: (a) RFOG mounted on a rate table with electronic equipment and power supplies, (b) the gyro output frequency shift due to rotation as a function of rotation rate, and (c) the residual non-linearity of the gyro scale factor (25 ppm). An even more discriminating test for the effects of optical backscatter in the RFOG is that of linearity near zero rate, or a dead-band test. To do this the gyro s sensitive axis was placed perpendicular to the rate table axis. As the table was rotated at about 1 /s, the gyro s sensitive axis was swept through eastern, southern, western, and northern pointing directions measuring a component of earth rate that ranged from 0 /hr. to 12 /hr. Data was taken over a 10 hour period to assess repeatability. The data is shown in Figure 12 below. Note that in this test, the gyro axis was not perfectly perpendicular to the table axis, causing a 5 /hr offset when the gyro axis was oriented east or west. The measured earth rate of ±0.11 /hr was consistent with the true earth rate at our latitude. No dead-band was observed at zero rate. Scale factor stability was also measured by mounting the gyro s axis parallel to that of the rate table and cycling the input rate from 100 /s to -100 /s with a 15 sec dwell at each rate. This was repeated for 5 hours. The scale factor was computed by comparing the gyro output for positive and negative rates. The Allan deviation of the scale factor drift is shown in Figure 13 giving a scale factor stability of about 12 ppm over the course of the measurement, which is approaching navigation-grade performance. Proc. of SPIE Vol

10 Horizontally Mounted Gyro - Rate Table Test (Actual Earth Component = deg/hr) Measured Earth Component = ± deg/hr; Deviation = 1.4u o Rate Table Position (deg) Figure 12 RFOG dead-band test. The gyro s sensitive axis is rotated around to pick off a varying component of Earth s rate. Within the error bars, no dead-zone is visible. Allan Deviation io' io Averaging Time (hrs) io' Figure 13 Allan deviation of scale factor variation RFOG component development and future implementation Several emerging technologies that are envisioned to play a role in enhancing future RFOG products are being developed. These include low loss hollow core fiber (HCF), integrated photonics technology for the multi-frequency light source (MFLS) and silicon optical bench (SiOB) technology. The RFOG platform is capable of utilizing a sensing coils of either polarization maintaining solid core fiber, polarizing solid core fiber, or bandgap HCF with a length and diameter tailored toward the exact application. HCF is a very attractive choice 15 in that it vastly reduces the size of the Kerr effect due to optical power imbalances in the coil, and dramatically increases the power threshold for Stimulated Brillouin Scattering (SBS). In short, it allows for the use of higher optical power to increase signal to noise sensitivity. The cross-section of a typical hollow core fiber is shown in Figure 14. The fiber of Figure 14 has been developed to provide a high glass-free region and low loss for the propagation of the light near 1550 nm wavelength. It has special provisions to maintain polarization and attenuate higher order spatial modes both characteristics needed to achieve the demanding bias stability requirements of commercial navigation applications. This fiber shows encouraging performance characteristics at 1550 nm of 5.1 db/km loss, and h= 3.2x10-5 m -1. While more Proc. of SPIE Vol

11 development is needed, formulation and demonstration of a fiber design of this type represents an importance step toward readiness in an improved RFOG design. Figure 14 Cross-section of hollow core fiber. A key element to the use of hollow core fiber for the resonator coil is the silicon optical bench (SiOB). The SiOB is a chip scale platform that allows precise placement of optical component on a silicon substrate. When the light wave is traveling between components it can propagate in free space allowing ease of coupling into and out of hollow core fiber with virtually no index mismatch. Not only is this a compact, low cost platform for component integration, it is an efficient means for coupling light into a hollow core fiber, since no HCF fiber couplers have proven to be feasible. The SiOB is produced using many of the same process technologies used of MEMS technology. Specific attention is paid to the SiOB design to eliminate the need for active alignment. The SiOB is quite attractive in that it is capable of hosting fibers, lenses, mirrors, beam splitters, detectors and circulators all on a single chip. A portion of a SiOB used for a resonator is shown in the photo 16 of Figure 15, which is shown schematically in Figure 16. In Figure 16, the fiber ends are placed in two ends of a vee-groove and ball lenses couple the light from one fiber to the other, completing the resonator loop. To couple light into and out of the resonator 2% reflective mirrors are used, which represent the resonator s input output couplers. A scan of one free spectral range shows a finesse of 15 for this demonstration unit 17.. Figure 15 Silicon optical bench used for efficiently coupling two ends of a resonator fiber coil. Proc. of SPIE Vol

12 I To Resonator Fiber Loop Fiber Fiber To Resonator Fiber Loop J Ball Lens R-2% R-2% Ball Lens OBall Lens Photodiode Input Laser Signal Figure 16 Schematic of SiOB-based resonator and scan of the resonances. In order to reduce the size and cost of the RFOG, it is important to miniaturize optical components associated with the multi-frequency light source (MFLS). As an early step, a significant and important part of the MFLS shown Figure 9 was realized in a miniaturized subsystem using silicon photonics (SiP). The module is shown in Figure 17, which houses a SiP chip and an electronics board that are used for phase locking the slave lasers to the master laser. The slave lasers are tightly controlled to minimize relative phase noise, so as to achieve gyro ARW. Figure 17 Silicon photonics subsystem and electronics used for phase locking of the lasers within the MFLS. Initial test results 18 of the relative frequency noise of the two slave lasers stabilized by the SiP module are shown Figure 18. The results are shown over a -39C to +89C temperature range. The top two plots show free running frequency noise between the DFB and ECL lasers. The very bottom plots (all coinciding) show the stabilized laser relative frequency noise for various temperatures. The frequency noise at low frequency is suppressed into the millihz/sqrt(hz) regime, and is invariant with temperature. This shows exciting progress toward an MFLS assembly for our RFOG navigation applications. Proc. of SPIE Vol

13 1. E+04 1.E+03 1-E+02 1.E+01 _ a 1.E E-Ol N N 1.E-02 1.E-03 1.E E-05 1.E+03 I IIII Yi:,» RFN stable vs T Heat sink: -39 C to +89 C) 1.E E +05 Frequency (Hz) Figure 18 Relative frequency noise of MFLS, and its stability over temperature. DFB free -running DFB discrete components *DFB Sip chip ECL free -running 39 degc 27 degc -17 degc -+2 degc +20 degc +42 degc +61 degc +74 degc +89 degc 1.E+06 1.E SUMMARY Honeywell commitment to the fiber-optic gyro remains strong, with active production of numerous IFOG products for navigation- and strategic grade-applications, as well as new developments in the reference grade performance range. In parallel, RFOG development is underway for next-generation applications with both rigorous performance requirements and reduced size allowance. An improved RFOG approach has been presented here using two phase locked lasers to probe adjacent resonant frequencies in a ring resonator. This approach enables countermeasures for effects of optical backscatter and is expected to eliminate the need for expensive and power-consuming frequency shifters The scale factor stability of 12 ppm over 5 hours, the 25 ppm linearity up to +/- 500 /sec rotation rate, and the dead-band-free operation represent the state of the art in RFOG scale factor performance, to our knowledge. Taken together, these results demonstrate the functionality of the new approach and its attractiveness toward backscatter-error mitigation. Future designs involving hollow core fiber, the silicon optical bench technology, and a miniaturized phase locked laser system are under development as an attractive product approach of the future. These developments represent a significant step towards navigation grade RFOGS for civil and military land, sea, and aircraft applications. REFERENCES [1] Lefevre, H. C., [The Fiber-Optic Gyroscope], Artech House, Boston and London, 30-32, (1993). [2] Lefevre, H. C., Graindorge, P., Arditty, H., Vatoux, S., Papuchon, M., Double closed-loop hybrid fiber gyroscope using digital phase ramp. Proc. SPIE MS 8, (1985). [3] Ezekiel, S. and Balsamo, S., Passive ring resonator laser gyroscope, Appl. Phys. Lett. 30(9), (1977). [4] Shupe, D., Fiber resonator gyroscope: sensitivity and thermal nonreciprocity, Appl. Opt. 20(2), (1981). [5] Ezekiel, S. and Arditty, H., Fiber-optic rotation sensors in [Fiber-Optic Rotation Sensors and Related Technologies], Springer-Verlag, Berlin & Heidelberg, 2-26, (1982). [6] Szafraniec, B., Feth, J., Bergh, R., Blake, J., Proc SPIE 2510, (1995). [7] Durfee, D., Shaham, Y., and Kasevich, A., Long-term stability of an area-reversible atom-interferometer Sagnac gyroscope, Phys. Rev. Lett. 97, (2006). [8] Rozelle, D., Proc. ION Joint Navigation Conference, (2015) Proc. of SPIE Vol

14 [9] Wu, J., Smiciklas, M., Strandjord, L., Qiu, T., Ho, W., and Sanders, G., Resonator fiber optic gyro with high backscatter-error suppression using two independent phase locked lasers, Proc. of OFS-24, [10] Iwatsuki, K., Hotate, K.., and Higashiguchi, M., Effect of Rayleigh backscattering in an optical passive resonator gyro, Appl. Opt., 23(21), (1984). [11] Sanders, G., Prentiss, M., and Ezekiel, S., Passive ring resonator method for sensitive inertial rotation measurements in geophysics and relativity, Opt. Lett. 6(11), (1982). [12] Kaiser, T., Cardarelli, D., and Walsh, J., Experimental developments in the RFOG, Proc. SPIE 1367, Fiber Optic and Laser Sensors VIII, , (1990). [13] Zarinetchi, F., and Ezekiel, S., Observation of lock-in behavior in passive resonator gyroscope, Opt. Lett. 11, (1986). [14] Iwatsuki, K., Hotate, K., and Higashiguchi, M., Eigenstate of polarization in a fiber ring resonator and its effect in an optical passive ring-resonator gyro, Appl. Opt. 25(15), (1986). [15] Sanders, G., Strandjord, L., and Qiu, T. Hollow core fiber optic ring resonator for rotation sensing, Proc of OFS- 18, [16] Benser, E., Sanders, G., Smiciklas, M., Wu, J., and Strandjord, L., Development and evaluation of a navigation grade resonator fiber optic gyroscope, Proc. of ISS, [17] Strandjord, L., Qiu, T., Wu, J., Ohnstein, T., and Sanders, G., Resonator fiber-optic gyro orogress including observation of navigation-grade angle random walk, Proc. OFS 22, (2012). [18] Ayotte, S., Faucher, D., Babin, A., Costin, F., Latrasse, C., Poulin, M., G-Deshenes, E., Pelletier, M., and Laliberte, M., Silicon photonics-based laser system for high performance fiber sensing, Proc of OFS-24, Proc. of SPIE Vol

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