Aircraft System Configured to Augment Lidar-Based Aircraft Air Data Measurements
AssigneeThe Boeing Company
InventorsRobert Justin Mayer, Christopher Heyrman, Robert Michael Dowgwillo
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Abstract
An aircraft system having a LIDAR system, one or more sensors, and a control unit. The control unit includes processing circuitry configured to calculate during flight a pressure altitude, calibrated airspeed, Mach number, equivalent airspeed, static temperature, static pressure, and dynamic pressure of an aircraft based on a combination of air data measurements from the LIDAR system and the one or more sensors.
Claims20
An aircraft system comprising:
- a LIDAR system;
- one or more sensors;
- and
- a control unit comprising processing circuitry configured to calculate during flight air data parameters comprising one or more of pressure altitude, calibrated airspeed, equivalent airspeed, Mach number, static temperature, static pressure, and dynamic pressure, the air data parameters based on a combination of air data measurements from the LIDAR system and the one or more sensors.
A non-transitory computer readable medium comprising instructions stored thereon that, when executed by processing circuitry of a control unit, configures the control unit to:
- receive a total pressure of an aircraft during a flight;
- receive a total temperature of an aircraft during the flight;
- receive air data measurements from a LIDAR system during the flight;
- and
- determine one or more of static temperature, static pressure, pressure altitude, calibrated airspeed, Mach number, dynamic pressure, and equivalent airspeed of the aircraft based on the total pressure, the total temperature, and the air data measurements.
A method of determining air data parameters during a flight of an aircraft, the method comprising:
- determining a true airspeed of the aircraft based on first inputs from a first input device;
- determining a total air temperature based on second inputs from a second input device;
- determining a total pressure based on third inputs from a third input device;
- and
- deriving static temperature, static pressure, pressure altitude, calibrated airspeed, Mach number, dynamic pressure, and equivalent airspeed based on the true airspeed, the total air temperature, and the total pressure.
Dependencies are inferred from the claim text.