Abstract: The present disclosure relates to an additive manufacturing (AM) system for making a part. The system may have a build plate on which to form the part, and a print nozzle component configured to be supported above the build plate. The print nozzle may have a first and second axially extending passageways. The first axially extending passageway enables a first resin-infused feedstock material supplied from a first source of resin-infused feedstock material to be extruded onto the build plate. The second axially extending passageway enables a second resin-infused feedstock material supplied from a second source of resin-infused feedstock material to be extruded onto the build plate concurrently with, or alternately with, extrusion of the first resin-infused feedstock material, to form the part. The first and second resin-infused print feedstock materials differ in composition from one another.

Abstract: A product includes a three-dimensional scaffold structure having an open cell geometry with interconnected channels for allowing continuous communication throughout a volume of the scaffold structure. The scaffold structure is configured to enhance mechanical strength of an energetic material. A fuel material is present in the scaffold structure and/or a second material is coupled to the scaffold structure. The fuel material is configured to increase an output of energy release relative to an output of energy release from the scaffold structure having the fuel material not present.

Abstract: The invention relates to a device for determining total temperature for aircraft. This device is particularly useful in a probe, called a multifunction probe, for measuring several aerodynamic parameters such as, for example, the total pressure (Pt), the static pressure (Ps) and the total temperature (TT) of an airflow surrounding the aircraft. The device includes a deiced temperature probe. To obtain the total temperature (TTcorrected) of the airflow, the temperature (TTmeasured) recorded by the temperature probe is corrected as a function of the upstream infinity parameters (M?, Pt?, Ps?) of the aircraft and of the power (P) dissipated in the probe in order to deice it.