Icing detector
An icing detector includes an aircraft structure, an exposed member, an optical fiber sensor, and a measuring device. The exposed member is coupled to the aircraft structure and is exposed to an outside of the aircraft structure. The optical fiber sensor is coupled to the exposed member and is covered by one or both of the aircraft structure and the exposed member. The measuring device is configured to measure light received from the optical fiber sensor.
1. An icing detector comprising:
an aircraft structure;
an exposed member comprising a post including a first end coupled to an outer surface of the aircraft structure and exposed to an outside of the aircraft structure, and an optical fiber cable wound around the post with at least a portion of the optical fiber cable being spaced apart from the post;
an optical fiber sensor covered by the aircraft structure, the optical fiber sensor being coupled to a second end of the optical fiber cable; and
a measuring device coupled to the optical fiber sensor, the measuring device being configured to emit light into the optical fiber sensor and measure a change in a frequency of backscatter of the light traveling through the optical fiber sensor, the change being due to the optical fiber sensor being strained and/or deformed by transmission of vibration and/or load to the optical fiber sensor when ice is formed on the exposed member.
2. The icing detector according to claim 1 ,
wherein the exposed member further comprises a weight member coupled to a third end opposite to the first end of the post.
3. The icing detector according to claim 2 ,
wherein the weight member includes at least one gap provided between a plurality of portions of the weight member.
4. The icing detector according to claim 3 , wherein the weight member has a spiral shape, a conical shape, a shape of a spider's web, or a diamond shape.
5. The icing detector according to claim 2 , wherein the exposed member further comprises a flexible member, and
wherein one end of the flexible member is coupled to the optical fiber sensor, and the other end of the flexible member is coupled to the weight member.
6. The icing detector according to claim 5 , wherein the flexible member is wound around the post.
7. The icing detector according to claim 1 , wherein the optical fiber sensor is covered by the exposed member, extends through the aircraft structure, and is coupled to the measuring device that is provided inside the aircraft structure.
8. The icing detector according to claim 1 , wherein a resonance frequency of the exposed member permanently fixed to the optical fiber sensor is tunable by changing a weight of the weight member.
9. The icing detector according to claim 1 , wherein the optical fiber sensor is embedded in the post and extends through a center of the post.
10. The icing detector according to claim 1 , wherein the optical fiber sensor extends in a longitudinal direction of the post.
11. The icing detector according to claim 1 , wherein the optical fiber sensor covered by the exposed member is permanently fixed to the exposed member.