Aircraft flow angles calibration via observed-based wind estimation. Issue 7 (8th July 2019)

• Record Type: Journal Article
• Authors: Schettini, Francesco; Di Rito, Gianpietro; Denti, Eugenio
• Is Part Of: Aircraft engineering and aerospace technology. Volume 91:Issue 7(2019)
• Page Start: 1033
• Page End: 1038
• Publication Date: 2019-07-08
• Subjects: Kalman filter -- Flight tests -- Angle-of-attack -- Angle-of-sideslip -- Nose-boom vanes; Aerospace engineering -- Periodicals; Aeronautics -- Systems engineering -- Periodicals; Astronautics -- Systems engineering -- Periodicals; Airplanes -- Equipment and supplies -- Periodicals; Space vehicles -- Equipment and supplies -- Periodicals; Aerospace industries -- Periodicals; 629.1
• DOI: 10.1108/AEAT-06-2017-0145
• Languages: English
• ISSNs: 1748-8842

Abstract

Abstract : Purpose: This paper aims to propose a novel approach, in which the reference data for the flow angles calibration are obtained by using measurements coming from an inertial navigation system and an air data sensor. Design/methodology/approach: This is obtained by using the Kalman filter theory for the evaluation of the reference angle-of-attack and angle-of-sideslip. Findings: The designed Kalman filter has been implemented in Matlab/Simulink and validated using flight data coming from two very different aircraft, the Piaggio Aerospace P1HH medium altitude long endurance unmanned aerial system and the Alenia-Aermacchi M346 Master™ transonic trainer. This paper illustrates some results where the filter satisfactory behaviour is verified by comparing the filter outputs with the data coming from high-accuracy nose-boom vanes. Practical implications: The methodology aims to lower the calibration costs of the air data systems of an advanced aircraft. Originality/value: The calibration of air-data systems for the evaluation of the flow angles is based on the availability of high-accuracy reference measurements of angle-of-attack and angle-of-sideslip. Typically, these are obtained by auxiliary sensors directly providing the reference angles (e.g. nose-boom vanes). The proposed methodology evaluates the reference angle-of-attack and angle-of-sideslip by analytically reconstructing them using calibrated airspeed measurements and inertial data.