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During the flight of the aircraft, it is necessary to monitor the maximum principal strain of the aircraft's own cabin or tank. For the acquisition of the maximum principal strain, the fiber Bragg grating strain sensor is often pasted on the surface of the object to be measured in the mode of three-directional strain rosettes. The relevant measurement results are brought into the calculation formula to obtain the maximum principal strain. Aiming at the current situation that when a large number of fiber Bragg grating strain sensors are pasted on a large structure, it cannot be calibrated and can only be calibrated with empirical values. According to the large error source introduced by the sensor in the actual mounting process, a method for obtaining high-consistency strain of the fiber grating strain sensor is presented, which greatly improves the strain measurement accuracy of the fiber Bragg grating strain sensor on large structures.
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