Abstract: A system for calculating forces exerted into an aircraft component includes a test hinge assembly and a monitoring system. In at least one embodiment, the test hinge assembly is a triangular shaped assembly, and includes at least one beam, at least one connecting joint having a channel configured to receive and retain a fastening member, and at least one strain gage secured to an outer surface of the beam(s). The strain gage(s) is configured to detect one or more strains exerted into the beam(s). The monitoring system is in communication with the strain gage(s). The monitoring system is configured to calculate forces exerted into the fastening member(s) by analyzing the strain(s) exerted into the beam(s).

Abstract: A system for calculating forces exerted into an aircraft component may include a test hinge assembly and a monitoring system. The test hinge assembly may be a triangular shaped assembly, and may include at least one beam, at least one connecting joint having a channel configured to receive and retain a fastening member, and at least one strain gage secured to an outer surface of the beam(s). The strain gage(s) is configured to detect one or more strains exerted into the beam(s). The monitoring system is in communication with the strain gage(s). The monitoring system may be configured to calculate forces exerted into the fastening member(s) by analyzing the strain(s) exerted into the beam(s).

Abstract: An active wing and lift surface control system for an aircraft is described. The wing and lift surface control system includes an aeroelasticity measurement system configured to provide at least one of real time wing twist measurements and real time measurements of aircraft body bending, at least one actuator mechanically coupled to a control surface of the aircraft, and a control system communicatively coupled to the aeroelasticity measurement system and to the at least one actuator. The control system is operable to receive the measurements from the aeroelasticity measurement system and generate control signals, based on the real time measurements, to operate the at least one actuator to adjust a drag associated with one or more of the wing and the aircraft body.

Abstract: An active wing and lift surface control system for an aircraft is described. The wing and lift surface control system includes an aeroelasticity measurement system configured to provide at least one of real time wing twist measurements and real time measurements of aircraft body bending, at least one actuator mechanically coupled to a control surface of the aircraft, and a control system communicatively coupled to the aeroelasticity measurement system and to the at least one actuator. The control system is operable to receive the measurements from the aeroelasticity measurement system and generate control signals, based on the real time measurements, to operate the at least one actuator to adjust a drag associated with one or more of the wing and the aircraft body.

Abstract: A fairing system developed to reduce the flow disturbance around sensor elements allowing accurate measurement of the pressure distribution on an object surface. The fairing also protects the sensors and electronics of the pressure belt from direct exposure to airflow.

Abstract: A fairing system developed to reduce the flow disturbance around sensor elements allowing accurate measurement of the pressure distribution on an airplane exterior surface. The fairing also protects the sensors and electronics of the pressure belt from direct exposure to airflow.