Wing is one of the key components of aircraft. On-line monitoring of wing deformation during flight is helpful to improve the safety and mission performance of the aircraft. Therefore, a dynamic wing deformation monitoring system based on the fiber Bragg grating sensor technology is proposed in this article. The relationship between wavelength variation of FBG and wing surface curvature is analyzed theoretically. The strain compensation is realized by the temperature sensor, and the serialization of discrete curvature is realized by cubic spline interpolation. Then, the deformation reconstruction algorithm based on continuous curvature is used to measure the wing deformation. 36 FBG strain sensors and 4 FBG temperature sensors are set on the wing surfaces of the CA42 aircraft. The ground static test results indicate that the measuring error of wing-tip deflection is 2. 5% . Finally, a flight test is carried out for the wing dynamic deformation measurement system. The strain, temperature and deformation data of the wing surface are recorded completely during the test process. The flight test results show that the wing tip deflection caused by the wing deformation is directly proportional to the vertical acceleration of the wing, and the coefficients are 86. 33 mm/ g (left wing) and 80. 04 mm/ g (right wing), respectively. The maximum deflection of the wing tip is 250 mm, which occurs when the normal overload is 2. 25 g. In addition, the smaller the radius of the aircraft maneuvering, the more the wing deforms. The dynamic wing deformation monitoring system shows good engineering adaptability.