Abstract: There is provided a removable chromatic witness assembly, system, and method to monitor thermal events and impact events on a surface of a composite structure. The removable chromatic witness assembly has a plurality of chromatic witness geometric configurations separately coupled in an arrangement to one or more portions of a polymeric film layer. Each chromatic witness geometric configuration has a plurality of chromatic probes of a same type incorporated into an adhesive material. At least two of the geometric configurations have a different type of chromatic probes with a different sensing capability for thermal events and impact events on the composite structure. The polymeric film layer and the geometric configurations form the removable chromatic witness assembly in a form of a removable chromatic witness applique configured to be removably applied directly and continuously to the surface of the composite structure, and configured to monitor the thermal and impact events.

Abstract: There is provided a removable chromatic witness assembly, system, and method to monitor thermal events and impact events on a surface of a composite structure. The removable chromatic witness assembly has a plurality of chromatic witness geometric configurations separately coupled in an arrangement to one or more portions of a polymeric film layer. Each chromatic witness geometric configuration has a plurality of chromatic probes of a same type incorporated into an adhesive material. At least two of the geometric configurations have a different type of chromatic probes with a different sensing capability for thermal events and impact events on the composite structure. The polymeric film layer and the geometric configurations form the removable chromatic witness assembly in a form of a removable chromatic witness applique configured to be removably applied directly and continuously to the surface of the composite structure, and configured to monitor the thermal and impact events.

Abstract: A method of manufacturing a composite panel is described. The method includes pre-stabilizing a honeycomb core with at least one layer of a pre-stabilizing material, surrounding the honeycomb core with at least one composite laminate skin layer, and curing the at least one composite laminate skin layer.

Abstract: Structural components are disclosed that are fabricated from unidirectional carbon fiber composite materials into compound contour profiles along a longitudinal axis thereof without wrinkling of composite material plies oriented in various directions relative to the longitudinal axis. Methods of stacking, sequencing, and applying the material plies to fabricate the components are also disclosed.

Abstract: A method of manufacturing a composite panel is described. The method includes pre-stabilizing a honeycomb core with at least one layer of a pre-stabilizing material, surrounding the honeycomb core with at least one composite laminate skin layer, and curing the at least one composite laminate skin layer.

Abstract: Structural components are disclosed that are fabricated from unidirectional carbon fiber composite materials into compound contour profiles along a longitudinal axis thereof without wrinkling of composite material plies oriented in various directions relative to the longitudinal axis. Methods of stacking, sequencing, and applying the material plies to fabricate the components are also disclosed.

Abstract: Hybrid composite panel systems and methods are disclosed. In one embodiment, an assembly includes a primary section, a matrix member engaged with the primary section, and a secondary section engaged with the matrix member opposite the primary section. The primary section includes a plurality of first composite layers reinforced with a first reinforcing material, and the secondary section includes a plurality of second composite layers reinforced with a second reinforcing material. The primary and secondary sections are configured to bear an operating load at least partially transversely to the first and second composite layers, and are asymetrically configured such that the primary section bears a majority of the applied operating load.

Abstract: An aircraft panel assembly 10 is provided, including a panel core 28, a plurality of pre-preg layers 30 surrounding the panel core 28 forming an internal layer of plies 34, at least one metal foil layer 38 positioned on an outer layer 40 of the internal layer of plies 34. The at least one metal foil layer 38 providing an electrical conduit between the outer surface 24 of the aircraft panel assembly 10 and a sub-structure 26 for grounding.

Abstract: An aircraft panel assembly 10 is provided, including a panel core 28, a plurality of pre-preg layers 30 surrounding the panel core 28 forming an internal layer of plies 34, at least one metal foil layer 38 positioned on an outer layer 40 of the internal layer of plies 34. The at least one metal foil layer 38 providing an electrical conduit between the outer surface 24 of the aircraft panel assembly 10 and a sub-structure 26 for grounding.