This paper describes the design, flight testing and accompanying analysis of two anti-windup (AW) compensators for an experimental aircraft -the German Aerospace Center's (DLR) Advanced Technologies Testing Aircraft (ATTAS). The AW compensators were designed to reduce the deleterious effects of rate-saturation of the aircraft's actuators on handling qualities. The AW compensators were flight-tested and assessed using the resulting pilot comments, in the form of handling qualities ratings (HQR's) and pilot-involved-oscillation ratings (PIOR's), and flight test data. These media demonstrate that the AW compensators improved the predictability and handling of the aircraft. The results also provide an initial understanding of the relationship between the theory and design choices for AW controllers and the response of the piloted aircraft during periods of rate saturation.
This paper presents the results of recent flight tests of several anti-windup (AW) compensators on the German Aerospace Centre's (DLR) Advanced Technologies Testing Aircraft (ATTAS). The objectives of the tests were twofold: to demonstrate the potential for rigorously designed low order AW compensators to reduce the pilot-involved-oscillation (PIO) proneness of the aircraft and improve the handling qualities; and to compare a variety of low-order AW compensators to determine the importance of different design parameters. The AW compensators were assessed based on pilot handling qualities ratings (HQRs) and PIO ratings (PIORs). These ratings, and supporting pilot comments and flight data, demonstrate that the AW compensators improved the handling qualities and reduced the PIO proneness of the aircraft, albeit to different degrees. The results also provide a basic understanding of the relationship between design parameters and the response of the piloted aircraft during periods of rate saturation.
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