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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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Journal ArticleDOI
TL;DR: The simulation and flight test demonstrate that the presented method has a smaller calculation cost and satisfactory convergence, and the corresponding precision evaluation algorithm can describe the trend of true alignment error accurately, and is good enough to judge the moment for switching to the fine alignment.
Abstract: This paper presents an analytic coarse transfer alignment method based on inertial measurement vector matching for the inertial navigation system (INS) on vertically launched missiles from the ground. The alignment problem is transformed into the estimation of the relative attitude between the master INS (MINS) and slave INS (SINS) by decomposing the attitude matrix of SINS. As inspired by the ideology of the traditional analytic alignment method, the measurements from the accelerometers and gyroscopes of MINS and SINS are utilized to construct matching vectors to estimate the relative attitude between them without any initial information. Furthermore, the sensitivity of Euler angles with respect to the inertial sensor errors is analyzed according to the presented coarse transfer alignment principle. An algebraic expression for alignment error estimation is given, and thus the real-time precision evaluation for the presented coarse alignment method is achieved. It allows the system to switch to fine alignment in a timely and accurate manner. The simulation and flight test demonstrate that, compared with the quaternion-optimization-based alignment method proposed by Kang et al. , the presented method has a smaller calculation cost and satisfactory convergence. The corresponding precision evaluation algorithm can describe the trend of true alignment error accurately, and is good enough to judge the moment for switching to the fine alignment.

26 citations

Patent
17 May 2006
TL;DR: In this paper, a method for producing inertial measurement data from one or more inertial sensors is presented. But the method is not suitable for the measurement of high-dimensional data.
Abstract: A method for producing inertial measurement data is provided. The method comprises receiving raw inertial measurement data from one or more inertial sensors; receiving raw position data based on signals from a global navigation satellite system; processing the raw inertial measurement data and the raw position data with a filter to generate state variable estimates; and calculating enhanced inertial measurement data based on the raw inertial measurement data and the state variable estimates from the filter.

26 citations

Proceedings ArticleDOI
01 Jun 1993
TL;DR: In this paper, an initial assessment of the feasibility of strapdown stabilization for high-resolution imaging seekers was conducted, and a linear state space model and a detailed nonlinear planar simulation were developed of a tactical high resolution platform system including gimbal inertia, inertial sensors, position sensors, friction, mechanical alignment, compliances, and control loop compensation.
Abstract: : In space constrained applications such as tactical missiles, locating the inertial sensors off the platform simplifies packaging and may allow existing missile autopilot gyros to be used for platform stabilization. In strapdown stabilization, inertial sensors are fixed to the base of the inertial platform rather than directly on the platform itself. Gimbal position sensor information is combined with body-fixed inertial rate sensor information to estimate the inertial rate of the platform. This estimate of platform rate is a key factor that determines the stabilization performance of the system. An initial assessment of the feasibility of strapdown stabilization for high-resolution imaging seekers was conducted. A linear state space model and a detailed nonlinear planar simulation were developed of a tactical high-resolution platform system. The simulation includes gimbal inertia, inertial sensors, position sensors, friction, mechanical alignment, compliances, and control loop compensation. The simulation was used to predict the platform stabilization performance. In addition, effects of stabilization performance on target signal strength for an imaging seeker were estimated.

26 citations

Patent
25 Jun 2014
TL;DR: In this article, an inertial measurement unit comprising one or more gyroscopes configured to measure angular velocity about a respective one of three independent axes and one or multiple accelerometers configured to quantify specific force along a respective axis along each one of the three independent axis is used to measure strength of local magnetic field along each axis.
Abstract: A system comprises an inertial measurement unit comprising one or more gyroscopes configured to measure angular velocity about a respective one of three independent axes and one or more accelerometers configured to measure specific force along a respective one of the three independent axes; a magnetometer configured to measure strength of a local magnetic field along each of the three independent axes; and a processing device coupled to the inertial measurement unit and the magnetometer; the processing device configured to compute kinematic state data for the system based on measurements received from the magnetometer and the inertial measurement unit. The processing device is further configured to calculate magnetometer measurement calibration parameters using a first technique when position data is unavailable and to calculate magnetometer measurement calibration parameters using a second technique when position data is available.

26 citations

Patent
Charles R. Mcclary1
19 Jul 1995
TL;DR: In this paper, a fault tolerant inertial reference system employs two independent inertial units each having its own inertial sensor array with redundant output information, each inertial unit includes an independent source of position and velocity information through employment of a satellite positioning system.
Abstract: A fault tolerant inertial reference system employs two independent inertial reference units each having its own inertial sensor array with redundant output information. Each inertial reference unit includes an independent source of position and velocity information through employment of a satellite positioning system. In turn, a high-speed error estimator processes inertial sensor output data from a local inertial sensor array with inertial sensor output data from another external inertial sensor array for determining high-level errors, and a low-speed error estimator processes output data from the local inertial sensor array with the velocity and position information separately obtained from the satellite positioning system for determining low-level errors. In turn these high and low-level errors are processed to determine a fault-free inertial sensor configuration for subsequently determining reliable fault tolerant inertial reference data obtainable with a minimum set of inertial sensors.

26 citations


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