Fiber optic sensing technologies potentially applicable for hypersonic wind tunnel harsh environments

Advances in Aerodynamics

Table 2 Research cases of distributed fiber optic sensors being applied to aircrafts [25, 89,90,91,92,93]

Country/Region	Applied model	Monitoring position	Achievement
USA	Predator B UAV	Wing skin structure	The real-time wing skin shapes are provided so as for aircraft to obtain the best aerodynamic performance.
	F-15 fighter	Aircraft structure	Real-time supervision of fatigue performance of aircraft fuselage
	Boeing 777	Aircraft structure
	X-33	Liquid - hydrogen tank structure	Real-time reflection of liquid-hydrogen tank structure and the insulating layer structure.
	F-35 fighter	Main structure of wing
EU	X-38	Aircraft structure	Able to measure the space temperature distribution and the strain of high-load structures, and estimate the residual life of main structures of aircraft.
	Some micro aircraft	Low Reynolds number in wind tunnel and physical parameters when aircraft is descending.	Able to simultaneously measure the aerodynamic load, instantaneous model position, wing deformation and distribution of flow field.
	A340 air liner	Aircraft structure	Able to record the cyclic stress load imposing onto the structure to monitor the fatigue strength of aircraft.
Japan	Some aircraft	Aircraft rubber grating	Able to integrate the damage supervision and the location based on the sensing network.
Japan	HOPE-X space shuttle model	Aircraft structure	Able to monitor the temperature distribution of aircraft model
Spain	A380 airline	Inflected plate of composite on fuselage	This sensor is used to detect if composite of aircraft is damaged and the sticking is failed.