Abstract: A system for an aircraft includes a pneumatic sensor, an optical sensor, and a computer system. The pneumatic sensor is configured to sense a value external to the aircraft. The optical sensor is configured to emit an optical signal external to the aircraft and receive an optical response. The computer system is configured to receive the value and the optical response. The pneumatic sensor and the optical sensor do not extend beyond a boundary layer of the aircraft.

Abstract: An aircraft air data system includes a first air data probe disposed on a first side of the aircraft, a second air data probe disposed on a second side of the aircraft, a first plurality of static pressure sensing ports disposed on the first side of the aircraft, and a second plurality of static pressure ports disposed on the second side of the aircraft. Each of the first air data probe and the second air data probe include a barrel portion configured to extend into an oncoming airflow, a total pressure sensing port, and an integrated total pressure sensor. Each of the first plurality of static pressure sensing ports is connected to one of a first plurality of integrated static pressure sensors. Each of the second plurality of static pressure sensing ports is connected to one of a second plurality of integrated static pressure sensors.

Abstract: A first air data system for providing first aircraft air data parameter outputs is formed by a first electronics channel of a first multi-function probe (MFP) that is electrically coupled with a first static pressure sensor. A second air data system for providing second aircraft air data parameter outputs is formed by a first electronics channel of a second MFP that is electrically coupled with a second static pressure sensor. A third air data system for providing third aircraft air data parameter outputs is formed by a second electronics channel of the first MFP that is electrically coupled with a second electronics channel of the first MFP.

Abstract: A first air data system for providing first aircraft air data parameter outputs is formed by a first electronics channel of a first multi-function probe (MFP) that is electrically coupled with a first electronics channel of a second MFP to receive static pressure data from the second MFP. A second air data system for providing second aircraft air data parameter outputs is formed by a second electronics channel of the second MFP that is electrically coupled with a second electronics channel of the first MFP to receive static pressure data from the first MFP. A third air data system for providing third aircraft air data parameter outputs is formed by a laser air data sensor that is configured to emit directional light into airflow about the aircraft exterior and to generate the third aircraft air data parameter outputs based on returns of the emitted directional light.

Abstract: A first air data system for providing first aircraft air data parameter outputs is formed by a first electronics channel of a first multi-function probe (MFP) that is electrically coupled with a first static pressure sensor. A second air data system for providing second aircraft air data parameter outputs is formed by a first electronics channel of a second MFP that is electrically coupled with a second static pressure sensor. A third air data system for providing third aircraft air data parameter outputs is formed by a second electronics channel of the first MFP that is electrically coupled with a second electronics channel of the first MFP.

Abstract: A vane for dynamic flow angle measurements may have improved performance for time lag responsiveness over a prior art delta-shaped vane. In various embodiments, a gust sensing vane may have a cropped-delta shape and configured to align to a fluid flow direction, where the gust sensing vane comprises a forward portion having a leading edge and an aft portion having a first trailing edge and a second trailing edge. A cross-sectional area of the forward portion may have a triangular shape. Furthermore, a cross-sectional area of the aft portion has two substantially parallel sides to form the cropped-delta shape of the gust sensing vane. The gust sensing vane may be coupled to, and extend away from, a rotary hub.

Abstract: A vane for dynamic flow angle measurements may have improved performance for time lag responsiveness over a prior art delta-shaped vane. In various embodiments, a gust sensing vane may have a cropped-delta shape and configured to align to a fluid flow direction, where the gust sensing vane comprises a forward portion having a leading edge and an aft portion having a first trailing edge and a second trailing edge. A cross-sectional area of the forward portion may have a triangular shape. Furthermore, a cross-sectional area of the aft portion has two substantially parallel sides to form the cropped-delta shape of the gust sensing vane. The gust sensing vane may be coupled to, and extend away from, a rotary hub.