Fig. 1. Classification and application of optical fiber strain sensors in aerodynamic and hydrodynamic testing

Fig. 2. Schematic diagram of fiber Bragg grating strain sensing

Fig. 3. Schematic diagram of optic fiber Fabry-Perot interference strain sensing

Fig. 4. (a) Fiber optic balance designed by EWA ^[16]; (b) Two-slot fiber bar balance ^[50]

Fig. 5. Five-component optical fiber balance developed by Shenyang University of Aeronautics and Astronautics ^[51]

Fig. 6. (a) Fiber optic balance designed by the Indian Institute of Aeronautical Research^[53]; (b) AEDC Fiber optic balance^[54]

Fig. 7. (a) Fiber optic balance of high temperature resistant fiber FP strain sensor^[55]; (b) Fiber optic balance resistant to 800 ℃^[56]; (c) CAEDC fiber optic balance ^[57-58]

Fig. 8. (a) Single-component small-range cantilever beam fiber optic balance^[59]; (b) Rod strain fiber optic balance^[60]; (c) Three-component fiber optic balance^[61]

Fig. 9. (a) Six-component fiber optic balance ^[62]; (b) Temperature self-compensating fiber optic balance ^[63]

Fig. 10. (a) Structural self-compensating fiber optic balance ^[64]; (b) New three-component fiber optic balance ^[65]

Fig. 11. (a) FBG performs fuselage deformation health monitoring^[4,66]; (b) Installation of fiber-optic sensors on the lower surface of the right wing after modification^[73]

Fig. 12. (a) Aircraft flight demonstration monitoring system ^[74]; (b) Identification network of wing load distribution and angle of attack ^[75]

Fig. 13. (a) Overall design of strain field monitoring and reconstruction method^[76]; (b) New method of shape sensing ^[79]; (c) Deformation and strain monitoring over wingspan^[80]