Airspeed sensing system for an aircraft

An apparatus comprising:

• a plurality of pitot-static probes, wherein each of the plurality of pitot-static probes is a first sensor type, and wherein the plurality of pitot-static probes are configured to generate first data such that the first data comprises a first total pressure value and a first static pressure value for an environment surrounding an aircraft;
• a plurality of angle of attack sensor systems, wherein each of the plurality of angle of attack sensor systems is a second sensor type, and wherein the plurality of angle of attack sensor systems are configured to generate second data such that the second data comprises a second total pressure value and a second static pressure value for the environment surrounding the aircraft;
• a plurality of Venturi tubes, wherein each of the plurality of Venturi tubes is a third sensor type, and wherein the plurality of Venturi tubes are configured to generate third data such that the third data comprises a third total pressure value and a third static pressure value for the environment surrounding the aircraft;
• and
• a signal consolidation system configured to detect errors in the first data generated by the plurality of pitot-static probes, the second data generated by the plurality of angle of attack sensor systems, and the third data generated by the plurality of Venturi tubes.

A method for identifying an airspeed for an aircraft, the method comprising:

• generating, using a signal consolidation system receiving input from a plurality of pitot-static probes, a first total pressure value and a first static pressure value for an environment surrounding the aircraft;
• generating, using the signal consolidation system receiving input from a plurality of light detection and ranging sensors, a second total pressure value and a second static pressure value for the environment surrounding the aircraft;
• generating, using the signal consolidation system receiving input from a plurality of angle of attack sensor systems, a third total pressure value and a third static pressure value for the environment surrounding the aircraft;
• detecting, using the signal consolidation system receiving errors in the first total pressure value, the first static pressure value, the second total pressure value, the second static pressure value, the third total pressure value, and the third static pressure value to form a consolidated total pressure value and a consolidated static pressure value;
• and
• identifying, using a computer system implementing the signal consolidation system, the airspeed for the aircraft from the consolidated total pressure value and the consolidated static pressure value.