Ring laser gyroscope

About: Ring laser gyroscope is a research topic. Over the lifetime, 2070 publications have been published within this topic receiving 18609 citations. The topic is also known as: Sagnac interferometer.

Coupled Dynamic Analysis and Decoupling Optimization Method of the Laser Gyro Inertial Measurement Unit.

Abstract: The mechanical dithered ring laser gyro (RLG) effectively overcomes the lock-in effect and ensures the sensitive accuracy of the low angular rate for the gyro. However, in the inertial measurement unit (IMU) system, the dither excitation of three RLGs causes the coupled vibration of the IMU structure, which could seriously limit the measuring accuracy of RLGs. In this paper, the vibration frequency response characteristic of laser gyro IMU is taken as the focus point, and the method of multi-rigid body dynamics is used to establish the dynamic model of IMU suitable for vibration frequency response analysis. On the basis of the model, the multi-degree-of-freedom coupling vibration of IMU with the gyro dither excitation is clearly described. A new IMU dynamic decoupling optimization method is proposed to minimize the coupled vibration frequency response, and compared with the previous optimal design method. The prototype experimental test results show that the coupled vibration of IMU is restrained more effectively by the proposed new method than by the previous optimal design method. Finally, on the basis of this new method, the measuring accuracy of the RLGs in the IMU system is improved, which is quite useful for practical engineering application.

Design of a New TEC-based Accurate Incubator

Abstract: In this paper, a new constant temperature control system is set up based on the semiconductor cooler. The close-loop self-controlling system is designed with the help of a integrated temperature controller for Peltier modulus, the controller is MAX1978. At room temperature, the temperature control scope is about 10℃-45℃, the precision of temperature is 0.1℃. This system is fast in control speed and accurate in control precision, it also has no active component. It provides an applied method in improving the stability of laser gyroscope and in reaching the steady state quickly. It also offers a beneficial reference to similar temperature control systems.

Ring laser gyros

Abstract: Along with advanced digital computing a revolutionary new inertial sensor has changed the design of inertial navigation systems. This new sensor, the ring laser gyroscope, is discussed

Power supply circuit for prism digital laser gyroscope

Abstract: The utility model provides a power supply circuit for a prism digital laser gyroscope. The power supply circuit comprises a conditioning circuit connected with the prism digital laser gyroscope. The conditioning circuit is connected with an A/D (analog/digital) conversion circuit, the A/D conversion circuit is connected with a FPGA (field programmable gate array) master control circuit, the FPGA master control circuit is connected with a D/A (digital/analog) conversion circuit, the D/A conversion circuit is respectively connected with a range length control amplifying circuit and a light intensity control amplifying circuit, a shake amplifying circuit, the range length control amplifying circuit is connected with a range length control servo mechanism, the light intensity control amplifying circuit is connected with a light intensity servo mechanism, the shake amplifying circuit is connected with a shake mechanism, the FPGA main control circuit is connected with an output circuit, and the output circuit is connected with the prism digital laser gyroscope. The power supply scheme includes that power supply of the prism digital laser gyroscope is improved. Therefore, power consumption of the prism digital laser gyroscope is lowered, and reliably thereof is improved.

Design of Vibration Isolation System for Laser Strapdown IMU

Abstract: The circular probable error is a little larger in the ground dynamic navigation test of the laser gyroscope Strap down inertial navigation system, so a better vibration damping system needs to be designed for SINS with laser gyro. Through analysis for the model of the vibration and the old vibration damping system, a new system of the double free degree be bring forwarded to reduce the response of random vibration on inertial navigation system. During the design, considering the installing plate is part of the vibration damping system and reckoning the inner space of the tactical missile carefully , using the finite element dynamic optimization method, a satisfactory installing plate and a damper with better dynamic characteristics is designed, then through ground vibration experiment and the designed of repetition parameter optimization, now the new vibration damping system can work effectively and the effect of vibration absorbing has achieved the requirement, it can be applied to the aircraft.