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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.


Papers
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Proceedings ArticleDOI
06 Jan 2012
TL;DR: In this article, a low-cost medium-precision tactical inertial measurement system can be developed, which uses the linear accelerometers at different positions in space to calculate the angular velocity and estimate the navigation parameters.
Abstract: An inertial navigation system with high anti-g capability, low power consumption, small volume and low cost is needed on certain specific tactical occasions. The gyroscope-free inertial measurement unit (GF-IMU) uses the linear accelerometers at different positions in space to calculate the angular velocity and estimate the navigation parameters. With the development of the MEMS sensors and Digital Signal Processors (DSP), a low-cost medium-precision tactical inertial measurement system can be developed. A SDRE-based filter algorithm is presented for dealing with the measurement error diverges of the linear accelerometers. A preliminary overall scheme is described, and the configuration profile of the sensors and the system equations are derived and analyzed.

2 citations

Patent
Colm Boran1, Edward J. Bedner1
21 Mar 2013
TL;DR: In this article, a system is provided for enhancing inertial sensing within a vehicle using an inertial measurement unit to determine measured rotational rates and translational accelerations of the vehicle using a remote sensing system.
Abstract: A system is provided for enhancing inertial sensing within a vehicle. The system determines measured rotational rates and translational accelerations of the vehicle using an inertial measurement unit. In addition, the system also determines estimated rotational rates and translational accelerations of the vehicle based on a remote sensing system. The system generates compensated rotational rates and translational accelerations to reduce gain errors or offset errors of the inertial measurement unit based on the estimated rotational rates and translational accelerations.

2 citations

Proceedings ArticleDOI
12 Jun 2013
TL;DR: In this article, the authors present an approach for filtering, integration and calibration of a strapped-down inertial navigation system for precise determining the spacecraft attitude, which contains an electrostatic micro-accelerometer, an inertial measurement unit based on the gyro sensors, an astronomical system based on star trackers, multi-head Sun sensor and magnetic sensor, the that are fixed to the spacecraft body.
Abstract: Contemporary information mini-satellites have general mass up to 500 kg and are placed onto the orbit altitudes from 500 up to 1500 km. For such spacecraft some principle problems on precise attitude determination and in-flight calibration are considered and elaborated methods are presented for their solving. Original multiple discrete algorithms for filtering, integration and calibration of a strapped-down inertial navigation system for precise determining the spacecraft attitude, are presented. This system contains electrostatic micro-accelerometer, an inertial measurement unit based on the gyro sensors, an astronomical system based on star trackers, multi-head Sun sensor and magnetic sensor, the that are fixed to the spacecraft body.

2 citations

Patent
Mark Takita1
25 Jun 2009
TL;DR: In this article, an image apparatus (10) includes an apparatus frame (224), a capturing system (228), a control feature, an inertial sensor assembly (218), and a control system (216).
Abstract: An image apparatus (10) includes an apparatus frame (224), a capturing system (228), a control feature, an inertial sensor assembly (218), and a control system (216). The control feature influences the image (258) captured by the capturing system (228). The inertial sensor assembly senses motion of the image apparatus. The control system adjusts the control feature based on the sensed motion from the sensor assembly. Thus, the control feature can be easily controlled by the controlled movement of the image apparatus. For example, the inertial sensor assembly can include one or more angular inertial sensors; one or more gyroscopes; and/or one or more accelerometers.

2 citations

Patent
23 Jun 2006
TL;DR: In this paper, the authors proposed a shock isolation system for an inertial sensor arrangement, which causes an advantageous moment of inertia by the special arrangement of the individual sensors, especially of the gyroscope used.
Abstract: The shock isolation system for an inertial sensor arrangement, on the one hand, causes an advantageous moment of inertia by the special arrangement of the individual sensors, especially of the gyroscope used. On the other hand, an advantageous long interval of the required shock-absorbing components (“shock mounts”) is provided by the use of several tubular shells. A measurement device with this inertial sensor arrangement thus achieves improved accuracy and reliability.

2 citations


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