Abstract: Disclosed herein is a positive pressure relief valve having a valve assembly, a trigger mechanism, an inlet manual override knob, and an outlet manual override knob. The valve assembly may comprises a valve throat and a main piston positioned at least partially within the valve throat, the main piston configured to selectively open and close the valve throat as a function of a pressure at the inlet to the valve assembly. The valve assembly may comprise a set of throat inserts within the valve throat. The trigger mechanism serves to quickly pressurize the main piston's diaphragm. The trigger mechanism may be positioned in a trigger mechanism housing at the outlet end of the valve assembly. The inlet and outlet manual override knob may be coupled to the main piston and configured to pull or push the main piston, thereby displacing the main piston to open the valve assembly.

Abstract: Disclosed herein is a positive pressure relief valve having a valve assembly, a trigger mechanism, an inlet manual override knob, and an outlet manual override knob. The valve assembly may comprises a valve throat and a main piston positioned at least partially within the valve throat, the main piston configured to selectively open and close the valve throat as a function of a pressure at the inlet to the valve assembly. The valve assembly may comprise a set of throat inserts within the valve throat. The trigger mechanism serves to quickly pressurize the main piston's diaphragm. The trigger mechanism may be positioned in a trigger mechanism housing at the outlet end of the valve assembly. The inlet and outlet manual override knob may be coupled to the main piston and configured to pull or push the main piston, thereby displacing the main piston to open the valve assembly.

Abstract: A multi-functional composite system, the multi-functional composite system comprising a core, a plurality of structural composite fiber layers, a matrix material, a composite conductor assembly, the composite conductor assembly having one or more conductors disposed between two or more insulating layers, and an electric power source electronically coupled with said composite conductor assembly, the electric power source is configured to pass electric current through at least one of said one or more conductors.

Abstract: A multi-functional composite system generally comprises a core, a plurality of structural composite fiber layers, a matrix material, a connector configured to interface with one or more electrical devices and a composite conductor assembly, the composite conductor assembly having one or more conductors disposed between two or more insulating layers.

Abstract: A multi-functional composite system generally comprises a core, a plurality of structural composite fiber layers, a matrix material, a connector configured to interface with one or more electrical devices and a composite conductor assembly, the composite conductor assembly having one or more conductors disposed between two or more insulating layers.

Abstract: A multi-functional composite system, the multi-functional composite system comprising a core, a plurality of structural composite fiber layers, a matrix material, a composite conductor assembly, the composite conductor assembly having one or more conductors disposed between two or more insulating layers, and an electric power source electronically coupled with said composite conductor assembly, the electric power source is configured to pass electric current through at least one of said one or more conductors.

Abstract: A system and method for automatically varying the flight envelope of an aircraft based upon the material health of the aircraft and the flight environment is provided. The system includes a plurality of structural health monitoring and load sensors that determine the approximate size and the approximate location of the damage. The system performs residual strength calculations for individual aircraft components to determine the overall aircraft residual strength. The system uses these calculations to determine a maximum flight envelope based on the overall aircraft residual strength, and transmits this information to the flight controller and optionally to the pilot.

Abstract: A system and method for automatically varying the flight envelope of an aircraft based upon the material health of the aircraft and the flight environment is provided. The system includes a plurality of structural health monitoring and load sensors that determine the approximate size and the approximate location of the damage. The system performs residual strength calculations for individual aircraft components to determine the overall aircraft residual strength. The system uses these calculations to determine a maximum flight envelope based on the overall aircraft residual strength, and transmits this information to the flight controller and optionally to the pilot.