US 12,486,041 B2
Computation of aircraft airspeed by inclusion of static air temperature
Arun Anant Nadkarni, Kirkland, WA (US); and Douglas L. Wilson, Mercer Island, WA (US)
Assigned to THE BOEING COMPANY, Arlington, VA (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on Nov. 29, 2021, as Appl. No. 17/536,893.
Claims priority of provisional application 63/183,883, filed on May 4, 2021.
Prior Publication US 2022/0355948 A1, Nov. 10, 2022
Int. Cl. B64D 43/02 (2006.01); G01K 13/02 (2021.01); G01P 5/10 (2006.01); G01P 5/175 (2006.01); G01P 13/02 (2006.01)
CPC B64D 43/02 (2013.01) [G01K 13/028 (2013.01); G01P 5/10 (2013.01); G01P 5/175 (2013.01); G01P 13/025 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A method comprising:
receiving, at flight control electronics of an aircraft, a static air temperature from a static air temperature probe, wherein the static air temperature probe is mounted on a fuselage of the aircraft at a location where a computational fluid dynamics analysis indicates that an air temperature proximate to the fuselage is substantially equal to an outside air temperature;
calculating, at the flight control electronics, a Mach number associated with the aircraft at a current flight altitude based on the static air temperature;
calculating, at the flight control electronics, a true air speed of the aircraft based on the Mach number; and
operating the aircraft via the flight control electronics using the true air speed.