• Journal of Sensor Science and Technology
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• v.8 no.2
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• pp.139-147
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• 1999

In this paper, we present the new angular velocity pick-off method for DTG (dynamically tuned gyroscope) which is widely used in various inertial navigation systems and motion control systems. In case of the external angular velocity input, the proposed scheme can make a smaller tilt-angle rather than that of conventional PI method in the transient and steady state because it has an additional inner rebalance loop with a mathematical model of the real gyroscope. So, without any mechanical redesign of the DTG, its dynamic range can be enlarged by the proposed method. The theoretical analysis and simulation model of DTG with the proposed scheme are given. Finally, the proposed scheme is verified.

• Proceedings of the KIEE Conference
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• 1987.11a
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• pp.53-56
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• 1987

Gyroscope is a key sensor for inertial navigation system (INS) which is a navigational instrument necessary to guide and control a free vehicle, and an important instrument for defense, aeronautical, and space industries that is and will be actively involved. In this study, design parameters, scale factor and linearity, of torquer which is one of the components of two degree of freedom dynamically tuned gyroscope (DTG) are presented. The magnetic circuit of torquer is so complicated that it is difficult to analyze it with analytic method. Thus these parameters are calculated by using finite element method with analysis of magnetic vector potential for axisymmetric 3-dimension magnetic field.

• 제어로봇시스템학회:학술대회논문집
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• 1989.10a
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• pp.28-32
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• 1989

In this paper, a DTG(Dynamically Tuned Gyroscope) and a DTG-based accelerometer designed and fabricated in the Seoul National University are described. For the purpose of the design, the functions and properties of DTG and accelerometer are investigated. The performance of the DTG is tested with the help of a single - degree - of - freedom rate table and a computer. The test result shows that the standard deviation of the DTG's random drift is 9.2 deg/(20min). The error model of the accelerometer is shown also.

• 제어로봇시스템학회:학술대회논문집
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• 1988.10a
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• pp.643-648
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• 1988

A strapdown inertial navigation system fabrication utilizing dynamically tuned gyroscope was finished as a first stage development. So it's design, fabrication and tests are reported. Although this system lacks in accuracy compared with the cimballed system, factors such as low cost, small size and lightness make it useable in wide range of applications. The initial cost for investment is relatively cheap, and so it is best suitable for local development in various kind of inertial navigation system. Since all of the locally used systems are imported and even with it's close relation to the military, foreign technical transfer is practically non-existent. The independent local development of such system at a time of domestic initation in aerospace and defense industry, can be seen as a significant milestone in the advancement of the inertial navigaion system field.

• The Transactions of the Korean Institute of Electrical Engineers A
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• v.48 no.4
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• pp.428-433
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• 1999

The errors of IMU(Inertial Measurement Unit) can be divided into deterministic and random errors. Since the required accuracy of the IMU is very high, the errors must be compensated by using an accurate error mode. In this paper, we present a method to get a more accurate error model in a laboratory test. This was done by considering the setting misalignment in the laboratory test in the IMU error model. We considered here the IMU which consits of DTG(dynamically tuned gyroscope) and pendulum type accelerometer. First, it was shown that the estimation result from the model which does not contain the setting misalignment gives considerable estimation error at the validation test. Second, a new model considering the setting misalignment was derived. Finally, by validation test using the estimation results from new model the validity of it was proved.

• Journal of the Korean Magnetics Society
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• v.6 no.1
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• pp.48-53
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• 1996

The role of the torquer in dynamically tuned gyroscope (DTG) is to erect the slanted rotor straight. This IBper presents the design method of the torquer. The torquer must satisfy the desired maximum angular velocity condition. The performance of magnet-residual flux density, maximum energy product, and so on-is limited by the material characteristics. So we should design the torquer with the limited condition that magnet performance is given. If the mechanical size of DTG is deter-mined, the dimension of the torquer is calculated and the space of the torquer becomes constant. Therefore, if we determine the diameter of the torquer coil, the number of coil turns is calculated automatically. Using these dimensions, we can calculate the torque and the scale factor. The maximum angular velocity is computed if we know the maximum current density. The analysis of the torquer was carried out by the 3-dimensional finite element method. The proposed algorithm of the torquer design was valid in comparison with the experimental data obtained from fabricated DTG.