Pilot-Involved-Oscillation Suppression Using Low-Order Antiwindup: Flight-Test Evaluation

Brieger, Oliver; Kerr, Murray; Postlethwaite, Ian; Turner, Matthew C.; Sofrony, Jorge

doi:10.2514/1.54441

Cited by 14 publications

(5 citation statements)

References 22 publications

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“…The example is realistic as the essence of the problem is similar to that of the applied work described in [9], but it is also illustrative due to the simple interpretation which can be given to the anti-windup compensator.…”

Section: Motivating Examplementioning

confidence: 92%

“…To illustrate the problem described above, we consider an example which has been inspired by the authors' work on anti-windup design for PIO avoidance [9]. The example is realistic as the essence of the problem is similar to that of the applied work described in [9], but it is also illustrative due to the simple interpretation which can be given to the anti-windup compensator.…”

Section: Motivating Examplementioning

confidence: 99%

“…It transpires that the use of this nonlinear gain, together with a simple filter of order equal to the number of anti-windup outputs, can enable stability to be maintained whilst also improving small signal performance. These ideas were motivated by a flight control application considered by the authors ( [8,9] and in unpublished work) which suffered a similar issue to that described above. Although the solution to these problems was a little different in the motivating work, some key ideas remain the same in this paper.…”

Section: Introductionmentioning

confidence: 99%

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A nonlinear modification for improving dynamic anti-windup compensation

Turner

Kerr

2018

European Journal of Control

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This paper presents a simple modification which can be made to a pre-designed dynamic anti-windup scheme in order to improve its performance. Roughly speaking, the modification enables the dynamic anti-windup compensator to act more like a static anti-windup compensator in certain circumstances. In particular, the modification enables the output of the compensator to decay more quickly than if it were absent, thereby effecting a swifter recovery of linear behaviour. The modification is therefore suitable for -and indeed motivated by -applications where the original anti-windup compensator contains slow poles, resulting in a potentially lengthy recovery of linear behaviour. The paper describes in detail the modification and presents conditions under which it is able to preserve stability.

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Section: Motivating Examplementioning

confidence: 92%

Section: Motivating Examplementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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A nonlinear modification for improving dynamic anti-windup compensation

Turner

Kerr

2018

European Journal of Control

Self Cite

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“…Influence of non-linearities like the "saturation" can also cause the so-called Pilot Involved Oscillations (PIOs), which violate the aircraft piloting, cf. [66][67][68][69][72][73][74][75][76][77][78]. This phenomenon is characterized by rapidly developing fluctuations with increasing amplitude of angular velocities, accelerations, and angular movements of manned aircraft.…”

Section: Aircraft-pilot Loopmentioning

confidence: 99%

Hidden attractors in aircraft control systems with saturated inputs

Andrievsky,

Kudryashova,

Kuznetsov

et al. 2017

Preprint

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“…These approaches include differentiate-limit-integrate (DLI) approach [9~12], phase compensation [13], linear or nonlinear reference filtering [14], Antiwindup type [15] and control allocation technique approach [16~18]. Among these approaches, control allocation technique to recover from pilot induced oscillations (CAPIO) is one of the first known techniques to address the problems that arise from stringent actuator rate limits for multiinput, multi-output (MIMO) applications without the use of ganging [18].…”

Section: Introductionmentioning

confidence: 99%

A phase compensator to prevent pilot induced oscillations by actuator rate limiting

Tan

2014

The 2014 2nd International Conference on Systems and Informatics (ICSAI 2014)

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In modern fly-by-wire control system, pilot induced oscillations (PIOs) have long been an aviation safety problem. The violation of actuator rate saturation is known to be a leading cause of PIO and has long been linked with performance and stability degradation of an aircraft. This paper proposes a phase compensator designed to reduce the adverse effects of rate saturation of the control surfaces. Without changing the structure of original control scheme in the design process, this proposed phase compensator reduces the effective time delay by minimizing the error of derivatives between the commanded input signal and the actual input signal, as well as minimizing the error of altitudes between these two signals. Simulations on the pilot-aircraft closed-loop system model with rate limiter are used to check the properties of the designed compensator. The pitch angle and roll angle rate commands, which are easy to induce PIO to a pilot, are chosen as references. Results from the simulation evaluation demonstrate that this compensator has good capability of decreasing the occurrence possibility of PIO, including the severity and duration of PIO, introduced by control surface rate limiting.

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Pilot-Involved-Oscillation Suppression Using Low-Order Antiwindup: Flight-Test Evaluation

Cited by 14 publications

References 22 publications

A nonlinear modification for improving dynamic anti-windup compensation

A nonlinear modification for improving dynamic anti-windup compensation

Hidden attractors in aircraft control systems with saturated inputs

A phase compensator to prevent pilot induced oscillations by actuator rate limiting

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