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METHODOLOGICAL ERRORS OF AN ELECTRONIC SENSOR OF AIRCRAFT AIRSPEED VECTOR PARAMETERS

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Methodological errors of an electronic sensor, built on the basis of the ultrasonic method for monitoring the parameters of the incoming air flow (IAF), are analyzed. The sensor satisfies the increasing requirements for design simplification, weight and cost reduction, for the slip angle measurement range while simultaneously measuring the angle of attack. It is shown that the methodological errors of the electronic sensor of the airspeed vector parameters are of an aerodynamic nature and are associated with disturbances of the IAF during the aircraft movement and the flow around the fuselage with a fixed receiver of the IAF parameters installed on the fuselage. The IAF disturbances introduced by the movement and flow around the aircraft increase the local true airspeed perceived on the fuselage at the installation site of a fixed receiver with pairs of combined emitters-receivers of ultrasonic vibrations of the considered electronic sensor located on it. An expression is obtained that determines the influence of IAF disturbances on the value of the true airspeed measured by an electronic sensor at the location of a fixed receiver. Analytical models are obtained and the calculation of the methodological error in determining the true airspeed in the operating speed and altitude ranges of small aircraft operation are carried out. It is shown that IAF disturbances at the location of the fixed receiver of the electronic sensor also cause methodological errors in determining the indicated speed and Mach number, the angle of attack and the sideslip angle with the considered electronic sensor. Methodological errors in determining the indicated airspeed and Mach number in the actual ranges of small-sized aircraft operation are calculated from the local true airspeed measured by an electronic sensor. It is shown that the methodological error in measuring the sideslip angle due to the symmetry of the aircraft in the plane of change in the angle of attack can be neglected. The aerodynamic errors of the considered electronic sensor are due to an increase in the local true airspeed at the location of the electronic sensor on the aircraft fuselage, therefore the main direction of their reduction is the introduction of aerodynamic corrections into the output signals of the electronic sensor using the calculated values of aerodynamic errors.

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