AIRCRAFT WEIGHT AND CENTERING SYSTEM BASED ON ADDRESSED FIBER BRAGG STRUCTURES WITH TEMPERATURE COMPENSATION

Abstract

The report presents a system of sensors on addressable fiber Bragg structures for the implementation of the aircraft weight and balance control system. The use of addressable fiber Bragg structures allows creating an onboard radio-photonic interrogator that is resistant to critical loads and vibration during takeoff and landing. The design of the sensor part is concentrated on the wheel axes and the chassis strut according to the scheme, allowing to calculate the center of mass of the aircraft. The sensor scheme is single-axis and three-axis. To minimize the number of sensors, they are made according to the scheme on two fibers of different types, an example of which is given in the report for measuring temperature and simultaneous measurement of deformations. This allows to abandon separate temperature compensation sensors.