Rate Measurement Unit for Attitude Determination and Control Subsystem

Over the past 50 years, many different gyro technologies have been developed and used in space, with Fiber Optical Gyros (FOG), Ring Laser Gyros (RLG) and Hemispherical Resonator Gyros (HRG) being predominantly used from the late ‘90s up to today.

Each technology offers a wide range of advantages and disadvantages while most of the time offering a similar performance. More recently, new applications have emerged in the commercial industry for which accuracy and precision are no longer the driving factors. Instead, reliability, mass, power budgets, and meeting performance at reduced cost and size have become paramount.

In that context, InnaLabs has developed a Coriolis Vibratory Gyroscope (CVG) sharing common features with HRG, and, with the support of the European Space Agency, a 3-axis Rad-Hard Rate Measurement Unit (RMU) named ARIETIS is now being developed by Innalabs to address Earth Observation ap-plications in Low-Earth Orbit (LEO), Navigation in Medium-Earth Orbit (MEO), and AOCS in Geostationary Orbit (GEO) with lifetime of more than 15 years. After a brief description of the InnaLabs CVG basic principles and an overview of the CVG technical strengths in comparison to competing for available technologies, this paper describes the key features and budgets of ARIETIS, it’s design, construction and operating principles, with a special emphasis on the targeted end-of-life performance.

Download the application note to read the whole article.

Highlighted application notes