Topic
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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20 Apr 1998
TL;DR: The system architecture is reviewed, a brief description of the key subassemblies and the test results from a prototype unit are described, demonstrating the capabilities of the overall system, including integrated GPS/INS navigation and enhanced performance of the GPS receiver as a result of carrier loop aiding.
Abstract: Honeywell and its teammates, Allied Signal and Trimble, have developed a design for a compact (100 in/sup 3/) integrated Global Positioning System/Inertial Navigation System (GPS/INS) under the GPS Guidance Package (GGP) Program funded by DARPA. This effort included developing new inertial sensor technology and implementing inertial aiding of the GPS receiver's tracking loops. The inertial sensors consist of fiber-optic gyroscopes and solid-state silicon accelerometers suitable for a 1-nmi/hr-class navigation system. Inertial aiding of the GPS receiver's carrier tracking loop was used to enhance tracking under severe dynamics without compromising anti-jam performance. This paper reviews the system architecture, provides a brief description of the key subassemblies and describes the test results from a prototype unit. These prototype units demonstrated the capabilities of the overall system, including integrated GPS/INS navigation and enhanced performance of the GPS receiver as a result of carrier loop aiding.
9 citations
06 Nov 2016
TL;DR: In this paper, the accuracy of an inertial measurement unit during 100m sprints against a criterion measure from a tripod-mounted Laveg laser was evaluated using the LAVA laser.
Abstract: Wearable micro sensor measurement devices are a promising development in sports technology. This paper presents preliminary data evaluating the accuracy of an inertial measurement unit during 100m sprints against a criterion measure from a tripod-mounted Laveg laser. The inertial measurement units were found to be a valid tool for the analysis of peak velocity (r = 0.92) and average split velocities for splits after the first 10m (r = 0.85 - 0.95). Validation data suggests some caution should be taken in interpretation of the first lorn split (r = 0.32). Whilst data from the two devices for this split were correlated, the inertial measurement unit showed an overestimation for this parameter in comparison to the athlete velocity as measured by the laser. Further in-depth analysis should investigate this period.
9 citations
07 Aug 2002
TL;DR: A new Coriolis Vibratory Gyro (CVG) Specification Format Guide and Test Procedure is being developed by the IEEE/AESS Gyro and Accelerometer Panel for consideration by IEEE Standards Association as IEEE Std. 1431 as mentioned in this paper.
Abstract: A new Coriolis Vibratory Gyro (CVG) Specification Format Guide and Test Procedure is being developed by the IEEE/AESS Gyro and Accelerometer Panel for consideration by the IEEE Standards Association as IEEE Std. 1431. It provides guides for specifying CVG performance and gives test procedures for verifying compliance with requirements. It also describes the various types of CVG, ranging from vibrating shell macro-sized devices to low-cost silicon and quartz chip micro-sized devices. Model equations are given for the various CVG operating and readout modes: whole-angle, open-loop, force-rebalance, and ratiometric. Also discussed in this paper are the IEEE standards that have been published for single- and two-degree-of-freedom spinning wheel gyros, laser gyros, interferometric fiber optic gyros, angular accelerometers, linear accelerometers, accelerometer centrifuge testing, and inertial sensor terminology, and an inertial sensor test equipment and analysis document and an inertial systems terminology document that are under development.
9 citations
TL;DR: The method of GPS-aided attitude estimation described herein is distinguished from other methods in that it does not employ search algorithms to resolve the carrier phase cycle ambiguity, and is modeled as a random process and is included as an error state of a statistical filter.
Abstract: This paper describes the design and simulation of an integrated GPS/INS that accomplishes space vehicle navigation and attitude estimation. The simulation contains models of an inertial measurement unit (IMU), a GPS receiver processing signals from an array of antennas placed on the spacecraft structure, and an integrated navigation filter.
Interferometric equations are employed to process GPS carrier accumulated-phase measurements from precise antenna locations in the user vehicle. Vehicle orientation in inertial space is then obtained by relating baseline-difference phase measurements to orientations of antenna baselines relative to satellite line-of-sight vectors.
The method of GPS-aided attitude estimation described herein is distinguished from other methods in that it does not employ search algorithms to resolve the carrier phase cycle ambiguity. Instead, the ambiguity is modeled as a random process and is included as an error state of a statistical filter. As a result, the attitude estimation time history evolves directly for any dynamic environment.
9 citations
9 citations