System and method for angle of attack indication with no dedicated sensors and aircraft information
A system for and method of indicating an angle of attack of an aircraft is provided. The system utilizes measurements from existing aircraft sensors so that a dedicated angle of attack sensor is not required. The system enables and benefits from a unique method that includes performing standard flight operations during a calibration flight. The system does not need any aerodynamic model of the aircraft because it utilizes information from the calibration flight to develop an estimated aerodynamic model of the specific airplane. The system utilizes the aerodynamic model and other information to estimate an angle of attack of the aircraft during flight. Finally, the system utilizes additional information to indicate the estimated angle of attack of the aircraft relative to an optimum angle of attack for the aircraft and/or a critical angle of attack of the aircraft. The system further enables recalibration, so as to accommodate aircraft aerodynamic modifications.
1. A method of installing a system on an aircraft comprising:
uploading a software package into a database of the system;
establishing data communication between the database of the system and a system processor such that the software package is capable of controlling the system processor;
establishing a data connection between the system processor and one or more existing aircraft components;
running a calibration algorithm during a calibration flight, thereby identifying aerodynamic characteristics of the aircraft, including a lift profile of the aircraft, and
performing a calibration process to estimate an angle of attack of the aircraft during normal flight operations, the calibration process resulting in an estimated aerodynamic model for the aircraft,
wherein the system does not utilize angle of attack information from a dedicated angle of attack sensor.
2. The method of claim 1 , further comprising applying the estimated aerodynamic model, by way of an estimation algorithm, to compute the estimation of the angle of attack of the aircraft during normal flight operations.
3. The method of claim 2 , wherein the estimation algorithm utilizes an Extended Kalman Filter that is based on a kinematic process model, which is not dependent on the estimated aerodynamic model or an aircraft weight, to merge sensor data with the estimated aerodynamic model.
4. The method of claim 3 , further comprising computing an angle of attack indication, via an indication algorithm, by comparing the estimation of the angle of attack to a plurality of parameters of the aircraft.
5. The method of claim 4 , wherein the plurality of parameters of the aircraft include calibration parameters and installation parameters.
6. The method of claim 5 , wherein the system is installed on an aircraft that does not have the dedicated angle of attack sensor.
7. The method of claim 5 , wherein the system is installed on an aircraft that has a dedicated angle of attack sensor but the system does not have a data connection to the dedicated angle of attack sensor.