Features: 1.Use integrated design and integration technology; 2.Anti vibration, shock resistance, high precision, long storage maintenance; 3.Be widely used in aviation, aerospace, weapons, tactical missile ship and other fields.
The fiber-optic strapdown attitude system consists of a closed-loop fiber optic gyroscope (where the ER-AHRS-10M uses an ultra-small closed-loop fiber optic gyroscope) and a quartz flexible accelerometer as the core inertial component, which is aligned or initially self-aligned by external input heading. In the post-flight, the coordinated attitude system is realized by satellite signal combination correction. The product can work in pure inertial attitude state or satellite signal combined attitude state, and simultaneously output three-axis high-precision angular rate and line acceleration signals (where ER-AHRS-10 is not combined). Flight status parameters such as aircraft attitude, heading, position, speed, acceleration, and angular velocity can be provided for cockpit display, aircraft control, radar antenna platform, and other systems. The product has the characteristics of small size, light weight and high reliability.
Application areas: camera equipment, seekers, transport aircraft, drones, helicopters, small and medium-sized general aircraft.
|Power supply||24V±4VDC(18V-36V)Power consumption<30W||28VDC(18V-36V)Power consumption<35W||28VDC(18V-36V)Power consumption<30W|
|Inertial/GNSS/BDII combined attitude accuracy heading||Heading||0.05°（RMS）||0.05°（RMS）|
|Pure inertial attitude accuracy (60min)||Heading||0.2°（RMS）||0.3°（RMS）||0.5°（RMS）|
|Measuring range||Angular velocity||±400°/s|
|Conditions of Use||Operating temperature||-40℃-＋70℃|
|Shock||Half sine wave / 40g, 11ms|
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