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Inertial reference unit

About: Inertial reference unit is a research topic. Over the lifetime, 1306 publications have been published within this topic receiving 22068 citations. The topic is also known as: IRU.


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Patent
23 Jul 2014
TL;DR: A vehicle-based positioning system (VBPS) for a vehicle moving along a guideway, the VPS includes an inertial navigation system (INS) on-board the vehicle, wherein the detected inertial parameters including roll, pitch and yaw of the vehicle as mentioned in this paper.
Abstract: A vehicle-based positioning system (VBPS) for a vehicle moving along a guideway, the VPS includes an inertial navigation system (INS) on-board the vehicle, wherein the INS is configured to detect inertial parameters of the vehicle while the vehicle move along the guideway, the detected inertial parameters including roll, pitch and yaw of the vehicle. The VBPS includes a guideway database, wherein the guideway database is configured to store inertial parameters of the guideway at a plurality of locations along the guideway, the stored inertial parameters include roll, pitch and yaw of the guideway. The VBPS further includes a vital on-board controller (VOBC), the VOBC is configured to determine a position of the vehicle based on a comparison of the detected inertial parameters with the stored inertial parameters. The VOBC is configured to limit comparison of the inertial parameters with the stored inertial parameters based on a latest checkpoint passed by the vehicle.

4 citations

Journal ArticleDOI
TL;DR: In this paper, a new static unbalance measure system for the gimbals axes has been developed considering the coupling effects caused by a mass eccentricity, the static balance condition and measure sequence for each gimbal axis are obtained.
Abstract: To reduce the influence of the static unbalance on an infrared missile guidance system, a new static unbalance measure system for the gimbals axes has been developed. Considering the coupling effects caused by a mass eccentricity, the static balance condition and measure sequence for each gimbal axis are obtained. A novel static unbalance test approach is proposed after analyzing the dynamic model of the measured gimbal axis. This approach is to drive the measured gimbal axis to do sinusoidal reciprocating motion in a small angle and collect its drive currents in real time. Then the static unbalance of the measured gimbal axis can be obtained by the current multi-cycle integration. Also a measuring system using the proposed approach has been developed. A balanced simulator is used to verify the proposed approach by the load and repeatability tests. The results show the proposed approach enhances the efficiency of the static unbalance measurement, and the developed measuring system is able to achieve a high precision with a greater stability.

4 citations

Patent
20 Jun 1997
TL;DR: In this paper, the ground speed and ground speed drift vectors are expressed by their x, y and z components in a referential system related to the aircraft, and the matrix of rotation R is defined on the basis of the angles of positioning error in terms of yaw φ, attitude θ and roll ψ by the relationship.
Abstract: A method of calibration includes obtaining an estimation of the ground speed of an aircraft by an inertial unit V inertial and by a radar V radar in at least two different flight orientations and in using these estimations to determine the drift in speed B and a rotation matrix R corresponding to positioning errors of the radar with respect to inertial unit on the basis of the matrix relationship: V.sub.inertial =RV.sub.radar +B applied for each of the flight orientations. The ground speed and ground speed drift vectors are expressed by their x, y and z components in a referential system related to the aircraft, and the matrix of rotation R being defined on the basis of the angles of positioning error in terms of yaw φ, attitude θ and roll ψ by the relationship: ##EQU1##

4 citations

01 Jan 2009
TL;DR: In this article, the performance of inertial MEMS sensors is analyzed and compared with constant and varying temperature by modeling and compensation of the inertial sensors' temperature-correlated errors.
Abstract: The performance of inertial MEMS sensors – gyroscopes and accelerometers – depends heavily on the operating temperature. That is, their accuracy will degrade dramatically with rising temperature. In this paper the errors of inertial sensors as a result of varying temperature will be first modelled. The accuracies obtained with constant and varying temperatures will be compared and analysed. Then, the performance of the loosely-coupled GPS/MEMS-INS will be studied by simulations. The measurements are the differences of the GPS and INS positions. Two integration schemes are studied. In the first scheme, the error models of the inertial sensors are temperature-varying while they are temperature-invariant in the second scheme. That is, the temperature is not considered in the second scheme, even though the errors of the inertial sensors are temperature-varying. In this paper, three methods, including (1) control of the device’s working temperature, (2) modelling and compensation of the inertial sensors’ temperature-correlated errors, and (3) real-time compensation of these errors within the integration filter, are analysed and compared. The last method is the focus of this paper. Its effectiveness is investigated through simulations.

4 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202314
202221
20211
20202
20193
20189