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.

Research on the technology of rotational motion for FOG strapdown inertial navigation system

Abstract: In order to improve the accuracy of strapdown inertial navigation system, the constant drift of gyro and the bias of accelerometer in inertial measurement unit (IMU) will be translated into periodic signal by the rotation of IMU, and the undesirable effects of constant drifts of inertial components can be eliminated by integral operations. The uniaxial unidirectional and reciprocating rotary compensation methods are listed in this paper, and the uniaxial rotary compensation principle is also derived. According to the scale error and the installation error of inertial components, the error characteristics of two rotation modes are analysed and simulated. Simulation results show that, the unidirectional rotation mode of IMU will lead to navigational errors due to the existence of scale factor, whereas such errors can be avoided in IMU reciprocating rotation mode.

Inertial sensor orientation detection and measurement correction for navigation device

Abstract: Implementations relating to methods, apparatuses and systems are disclosed for obtaining corrected inertial measurements based on an observed orientation of an inertial sensor system relative to a reference body.

Testing of the attitude and heading reference system

Abstract: Rzeszow University of Technology has undertaken the task of designing and providing of equipment to a flying laboratory. This paper presents basic design principles of the Inertial Reference Unit (IRU) which employs measuring signals from the Fiber Optic Gyros (FOG), accelerometers and electronic compass module. A microcomputer follows the algorithm of complementary filtration for of calculating the Euler angles for the aircraft attitude (pitch, roll and heading), angular rates, and linear accelerations. The correction systems that minimize error of the steady‐state measuring have been employed. The results of computer simulations, lab tests and selected flight tests have also been presented. The Inertial Reference Unit μIRU‐1 was tested in flight on board of the general aviation aircraft PZL‐110 “Koliber”. It has been confirmed that metrological properties of the system are appropriate for the purposes of teaching process. Currently, a modified version of the unit is being prepared. The new IRU is planned as a main reference unit for integrated flight control system of general aviation aircraft.

Improved precision of strapdown inertial navigation system brought by dual-axis continuous rotation of inertial measurement unit

Abstract: When systemic rotation autocompensation technique is implemented in inertial navigation system (INS), inertial measurement unit (IMU) undergoes intentionally devised mechanical motions. This technique is one of the strategies of improving the system precision performance at the system level. A dual-axis continuous rotation scheme is introduced, and system error equation is derived. The behaviors of different errors are analyzed. It is concluded that the whole error of INS is attenuated effectively. The error model of the dual-axis continuous rotation INS is designed on digital computer, and the theoretical conclusion is validated.