Practises to identify and prevent adverse aircraft-and-rotorcraft-pilot couplings—A ground simulator perspective

Pavel, Marilena D.; Jump, Michael; Masarati, Pierangelo; Zaichik, Larisa; Dang-Vu, Binh; Smaili, Hafid; Quaranta, Giuseppe; Stroosma, Olaf; Yilmaz, Deniz; Johnes, Michael; Gennaretti, Massimo; Ioniţă, Achim

doi:10.1016/j.paerosci.2015.06.007

Cited by 10 publications

(5 citation statements)

References 33 publications

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“…Furthermore, a number of different low-speed and forward flight tasks were used to collect pilot subjective assessment and objective data. In this research, the conservative nature of the OLOP boundary was confirmed [4,15].…”

Section: Application To Rotorcraftsupporting

confidence: 51%

“…A number of studies, including those detailed in Refs. [4,8,[12][13][14][15][16], have used OLOP for analysis with varying success. Generally, OLOP has been used only when PIOs were encountered during research campaigns.…”

Section: Application To Rotorcraftmentioning

confidence: 99%

“…Furthermore, the model incorporates neuromuscular dynamics, control inceptor dynamics and vestibular feedback. All of these elements have been shown to influence the susceptibility of the vehicle to PIO [4,6,15]. With the use of the Hess model, detailed analysis of the influence of these elements can be conducted to assist in the design process.…”

Section: Extensions To Olopmentioning

confidence: 99%

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The use of the Open-Loop Onset Point (OLOP) to predict rotorcraft pilot-induced oscillations

Jones

2020

CEAS Aeronaut J

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The Open-Loop Onset Point (OLOP) criterion has, for many years, been successfully used as a method to predict quasi-nonlinear pilot-induced oscillations (PIOs) for fixed-wing aircraft. Only limited research has been conducted using the criterion for prediction of PIOs occurring in rotorcraft. This paper details a study to extend the application of OLOP to rotorcraft, using the combination of control inputs appropriate for the task and a suitable pilot model. Results are compared between pilot subjective opinion and OLOP predictions, from tests performed in a ground-based simulation facility. Using 'taskspecific' application of OLOP, results obtained in the investigation are encouraging, whereby the objective predictions reflect subjective pilot assessment. From results obtained, a modified boundary is presented.

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Section: Application To Rotorcraftsupporting

confidence: 51%

Section: Application To Rotorcraftmentioning

confidence: 99%

Section: Extensions To Olopmentioning

confidence: 99%

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The use of the Open-Loop Onset Point (OLOP) to predict rotorcraft pilot-induced oscillations

Jones

2020

CEAS Aeronaut J

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“…The main parameters that describe the rotorcraft at the conceptual design level of fidelity are used to generate a general-purpose, real-time capable multibody model for the FRAME-Sim [6,23,46] flight simulation facility currently under development at Politecnico di Milano. Although often seen as double-edged swords, offline and piloted flight simulations are important in RPC investigations [38]. The proposed toolchain, and specifically the physics-based multibody simulation capability, is a valuable tool for investigating phenomena of this type [40].…”

Section: Real-time Multibody Model For Piloted Flight Simulationmentioning

confidence: 99%

Handling Qualities in Rotorcraft Conceptual Design

Zanoni

Gerosa

Lallo

et al. 2022

Aerotec. Missili Spaz.

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This paper presents the development of a rotorcraft conceptual design tool able to incorporate handling qualities assessment at an early design stage. After a first conventional sizing, performed utilizing NASA’s NDARC software, a linearized model of the rotorcraft flight mechanics is built. The linear model is augmented by a simplified control system, designed according to structured $$H_{\infty }$$ H ∞ techniques, to determine augmentation requirements, rather than design the actual flight control system. ADS-33 Bandwidth and Phase-Delay standards are exploited to objectively assess the handling qualities of the current design and to drive an iterative redesign process aimed at enhancing the handling qualities ratings. The rotorcraft parameters resulting from the augmented sizing are subsequently used to automatically generate a real-time capable multibody model, which can be used for the subjective evaluation of its handling qualities via piloted flight simulation. The tool capabilities are demonstrated by designing a conventional lightweight helicopter of the class of the Airbus Helicopters BO105.

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“…Nonlinear methods such as fuzzy logic and neural network methods have also been applied to identification and control ( [20], [21]), hybrid fuzzy logic ( [22], [23]) real time optimization used on a morphing wing by [24]. Other parameter estimation and control methodologies were used and validated during flight tests ( [25]- [42]). …”

Section: Tracking Control With Lqr-pi Optimizationmentioning

confidence: 99%

New Methodology for Optimal Flight Control using Differential Evolution Algorithms applied on the Cessna Citation X Business Aircraft – Part 2. Validation on Aircraft Research Flight Level D Simulator

Boughari¹,

Ghazi²,

Mihaela³

et al. 2017

INCAS BULLETIN

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Practises to identify and prevent adverse aircraft-and-rotorcraft-pilot couplings—A ground simulator perspective

Cited by 10 publications

References 33 publications

The use of the Open-Loop Onset Point (OLOP) to predict rotorcraft pilot-induced oscillations

The use of the Open-Loop Onset Point (OLOP) to predict rotorcraft pilot-induced oscillations

Handling Qualities in Rotorcraft Conceptual Design

New Methodology for Optimal Flight Control using Differential Evolution Algorithms applied on the Cessna Citation X Business Aircraft – Part 2. Validation on Aircraft Research Flight Level D Simulator

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