| abstract |
A structural fuse 1 (i.e a shear pin, fuse pin or breakaway pin) is configured to shear upon an application of a predetermined load. The fuse 1 comprises a plurality of longitudinal reinforcing elements 4 in a metal matrix 5. The reinforcing elements 4 may include ceramic fibres such as aluminium oxide or silicon carbide fibres, or may include carbon fibres. At least a portion of the metal matrix 5 may include a plurality of hollow metal ceramic spheres. The structural fuse 1 may be used in an aircraft. |