Closed-loop fiber optic gyros
Closed-loop fiber optic gyros
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DOI：
10.1117/12.258198
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发表时间：
1996-11
期刊：
影响因子：
--
通讯作者：
G. Pavlath
中科院分区：
文献类型：
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作者：
G. Pavlath
光纤陀螺仪的研发始于1970年代中期，重点是提高陀螺仪的旋转灵敏度和降低噪声。接下来，解决了偏差性能问题。到 20 世纪 80 年代初，光纤陀螺仪在实验室环境中实现了 0.01 O/ 的偏置误差。 McDonnell Douglasi 最初在 1970 年代末通过使用采用声光移频器的闭环光纤陀螺仪来解决比例因子性能问题。取得了良好的性能，但这种方法并未投入生产。 20 世纪 80 年代中期，Thomson CSF 开发了一种光纤陀螺仪，该陀螺仪采用双闭环技术，采用数字相位斜坡和电光相位调制器2。这种方法的衍生产品已被世界上大多数陀螺仪生产商采用。该技术使光纤陀螺仪具有高比例因子线性度，并显着提高了比例因子稳定性和重复性。如今，使用该技术衍生产品的闭环光纤陀螺仪已用于许多战术应用3。这些包括战术导弹、智能炸弹以及姿态和航向参考系统 (AHRS)，需要 1 至 1 0 O/ 的陀螺仪偏置性能和 1 00 至 1 000 ppm 的陀螺仪比例因子性能。目前正在开发使用该技术衍生物的闭环光纤陀螺仪，用于未来的惯性导航系统4 (INS)，该系统需要 0.00 1 至 0.01 0/小时的偏置性能和 5 至 50 ppm 范围内的比例因子性能。本文将研究这种双闭环数字相位斜坡技术如何发挥作用。将检查这种类型的闭环陀螺仪特有的误差源，即死区误差，以及消除它的技术。
Research and development of fiber optic gyros began in the mid 1 970s and focused on improving the gyro's sensitivity to rotation and reducing noise. Next, bias performance was addressed. By the early 1980s, fiber gyros were achieving bias errors of 0.01 O/ in a laboratory environment. Scale factor performance was initially addressed at McDonnell Douglasi in the late 1 970s by the use of a closed-loop fiber gyro which employed acousto-optic frequency shifters. Good performance was achieved but this approach was not productionized. In the mid 1980s, Thomson CSF developed a fiber gyro which used a double closed-loop technique employing a digital phase ramp and an electro-optic phase modulator2. Derivatives of this approach have been adopted by most gyro producers in the world. This technique has enabled fiber gyros to have high scale factor linearity and has significantly improved scale factor stability and repeatability. Today closed-loop fiber optic gyros using derivatives of this technique are in production for many tactical applications3 . These include tactical missiles, smart bombs, and attitude and heading reference systems (AHRS) and require gyro bias performance of 1 to 1 0 O/ and gyro scale factor performance of 1 00 to 1 000 ppm. Closed-loop fiber gyros using derivatives of this technique are presently in development for future inertial navigation systems4 (INS) which require bias performance in the 0.00 1 to 0.01 0/hr and scale factor performance in the 5 to 50 ppm range. This paper will examine how this double closed-loop, digital phase ramp technique functions. An error source unique to this type of closed-loop gyro, the deadband error, will be examined along with a technique for eliminating it.