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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11 Mar 2016
TL;DR: In this article, the relationship between the sensor quality and the INS (Inertial Navigation System) performance is firstly derived in details based on a 6 DOF (Degree of Freedom) model.
Abstract: In GNSS/INS navigation integrated systems, the selection of inertial sensors is a factor which can impact their system performances implicitly. Unfortunately, the research of the relationship between the inertial sensor errors and the navigation performances is not sufficient yet. In this case, the mathematical relationship between the sensor quality and the INS (Inertial Navigation System) performance is firstly derived in details based on a 6 DOF (Degree of Freedom) model. Since the INS is a part of the GNSS/INS system, the influence of the sensor errors on the total performance is further analyzed. By simulating an integrated system using three different grade IMUs (Inertial Measurement Units), the influence mechanism is proved.
6 citations
TL;DR: In this paper, a one-time systematic IMU calibration method using two-axis low precision turntable is presented, where the detail error model of inertial sensors using defined body frame is established.
Abstract: As an inertial sensors assembly, the FOG inertial measurement unit (FIMU) must be calibrated before being used. The paper presents a one-time systematic IMU calibration method only using two-axis low precision turntable. First, the detail error model of inertial sensors using defined body frame is established. Then, only velocity taken as observation, system 33 state equation is established including the lever arm effects and nonlinear terms of scale factor error. The turntable experiments verify that the method can identify all the error coefficients of FIMU on low-precision two-axis turntable, after calibration the accuracy of navigation is improved.
6 citations
Patent•
19 Oct 2012
TL;DR: An on-board communication and navigation system for an aircraft is provided for allowing an aircraft to transmit and receive information via satellite link as mentioned in this paper, which includes a radome assembly and a fuselage coupler.
Abstract: An on-board communication and navigation system for an aircraft is provided for allowing an aircraft to transmit and receive information via satellite link. Specifically, the system includes a radome assembly and a fuselage coupler. The radome assembly, for example, may include an antenna, an antenna control unit and an inertial reference unit. During installation, the fuselage coupler is securely and permanently mounted on the aircraft, typically on the fuselage at the top of the aircraft. Once the fuselage coupler is securely mounted, the radome assembly can be removably attached to the fuselage coupler, allowing the radome assembly to be quickly and easily removed and reattached to the aircraft, as needed.
6 citations
10 Jun 2013
TL;DR: In this paper, an inertial sensor with rate gyros, accelerometers, and magnetic sensors can best define attitude and sensor velocity, and this solution is explored along with sophisticated processing of simpler measurements.
Abstract: Measuring current from a sensor beneath a surface buoy, either attached to the buoy or hung on its mooring cable, subjects the measurement to error from sensor motion due to waves. While vector averaging over many wave periods would remove this error, simple averaging over one wave period is not sufficient because of attitude change in the sensor during passage of the wave. Determining attitude and sensor velocity might be done by sophisticated processing of linear accelerometer and vector magnetic sensor measurements but an inertial sensor with rate gyros, accelerometers, and magnetic sensors can best define attitude and sensor velocity. This solution is being explored along with sophisticated processing of simpler measurements.
6 citations
01 Jul 1975
TL;DR: The history of a unique development program that produced an operational fixed guidance system of inertial quality is presented in this paper, where each phase of development, beginning with requirement definition and concluding with qualification and testing, is addressed, and developmental problems are emphasized.
Abstract: The history of a unique development program that produced an operational fixed guidance system of inertial quality is presented. Each phase of development, beginning with requirement definition and concluding with qualification and testing, is addressed, and developmental problems are emphasized. Software generation and mission operations are described, and specifications for the inertial reference unit are included, as are flight performance results. Significant program observations are noted.
6 citations