New methodology for flight control system sizing and hinge moment estimation

Hoz, Carlos Cabaleiro De La; Fioriti, Marco

doi:10.1177/09544100211063110

Cited by 3 publications

(11 citation statements)

References 17 publications

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“…Flight control system sizing: This can be carried out with ASTRID; however, this tool does not reach the component level required for this analysis, and, consequently, a dedicated tool is developed for this subsystem. This specific tool is based on the study shown in [5], which can provide component-level estimations based on high-level information. It is further explained in Section 2.1.3.…”

Section: Performancementioning

confidence: 99%

“…The flight control system is sized following the methodology presented in [5]. This allows a component-level estimation to be reached starting from only some TLARs (i.e., maximum take-off weight, wing surface, fin surface and cruise Mach).…”

Section: Flight Control System Sizingmentioning

confidence: 99%

“…State-of-the-art high-lift devices predominantly consist of a mechanical transmission shaft connected to ballscrew actuators that deploy the surfaces [3,4]. Power is provided by a central power drive unit (PDU) that is connected to the main shaft through some gearboxes [5]. The shaft is mechanically connected to each of the actuators that deploy the flaps and slats synchronously and symmetrically.…”

Section: Introduction and State Of The Artmentioning

confidence: 99%

“…Each flap surface is deployed by two actuators that are connected to the main shaft through the correspondent gearboxes. Two extra gearboxes per wing are typically located between the power drive unit and the first actuator in order to redirect the main shaft through the fuselage and wing [5]. Two torque limiters are located at the wing tips.…”

Section: Introduction and State Of The Artmentioning

confidence: 99%

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Performance and Reliability Evaluation of Innovative High-Lift Devices for Aircraft Using Electromechanical Actuators

Cabaleiro de la Hoz,

Fioriti,

Boggero

2024

Aerospace

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In the last decades, electromechanical actuators started to be introduced in transport aircraft for primary and secondary flight control surfaces. Some innovative architectures have been proposed in the literature to use these actuators for high-lift devices (flaps and slats). The state-of-the-art architecture is built with a central mechanical shaft powered by a power distribution unit connected to ballscrew actuators that actuate the flap and slat surfaces. New innovative concepts have the potential to improve the state-of-the-art architectures. However, there is a lack of quantitative results for such innovative architectures. A new methodology is proposed to preliminarily estimate performance and reliability aspects of conventional and innovative architectures. This allows quantitative comparisons to finally be obtained. The methodology is applied to a new architecture that uses electromechanical actuators for flaps and slats, providing results in terms of performance and reliability and comparing them to the current state-of-the-art high-lift devices. Results show that the new architecture is lighter than the reference one and can be more reliable. This is achieved thanks to the removal of the mechanical links among components, which allows each control surface to be deployed independently from the others. This highly increases the operational reliability of the system. Two cases are analyzed, with and without actuator jamming. This provides more realistic results since this failure mode is currently the main reason why electromechanical actuators are not being used for more applications. The innovative architecture outperforms the conventional one in the case where the electromechanical actuators are not affected by the jamming failure mode.

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Section: Performancementioning

confidence: 99%

Section: Flight Control System Sizingmentioning

confidence: 99%

Section: Introduction and State Of The Artmentioning

confidence: 99%

Section: Introduction and State Of The Artmentioning

confidence: 99%

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Performance and Reliability Evaluation of Innovative High-Lift Devices for Aircraft Using Electromechanical Actuators

Cabaleiro de la Hoz,

Fioriti,

Boggero

2024

Aerospace

Self Cite

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“…These forces are then transmitted to the fuselage and the respective variable-pitch mechanisms through components connected to the swashplate [19]. Aerodynamic hinge moments can often be obtained through methods such as wind tunnel tests and theoretical calculations [20][21][22][23]. However, due to the significant variability of aerodynamic hinge moments in rotorcraft, this increases the difficulty of measurement and research.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Hinge Moment Characteristics of Pitch Regulated Mechanism for Mars Rotorcraft: Investigation and Experiments

Meng,

Hu,

Wei

et al. 2024

Preprint

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The precise regulation of hinge moment and pitch angle driven by the pitch regulated mechanism is crucial for modulating thrust requirements and ensuring stable attitude control in Martian coaxial rotorcraft. Nonetheless, the aerodynamic hinge moment in rotorcraft presents time-dependent dynamic properties, posing significant challenges for accurate measurement and assessment for such characteristics. In this study, we delve into the detailed aerodynamic hinge moment characteristics associated with the pitch regulated mechanism of Mars rotorcraft under a spectrum of control strategies. A robust computational fluid dynamics model has been developed to simulate rotor’s aerodynamic loads, accompanied by a quantitative hinge moment characterization that takes into account the effects of varying rotor speeds and pitch angles. Our investigation has yielded a thorough understanding of the interplay between aerodynamic load behavior and rotor surface pressure distributions, leading to the creation of an empirical mapping model for hinge moments. To validate our findings, we engineered a specialized test apparatus capable of measuring the hinge moments of the pitch regulated mechanism, facilitating empirical assessments under replicated atmospheric conditions of both Earth and Mars. The result indicates aerodynamic hinge moments depend non-linearly on rotational speed, peaking at a 0° pitch angle and showing minimal sensitivity to pitch under 0°. Above 0°, hinge moments decrease, reaching a minimum at 15° before rising again. Simulation and experimental comparisons demonstrate that under Earth conditions, the aerodynamic performance and hinge moment errors are within 8.54% and 24.90%, respectively. For Mars conditions, errors remain below 11.62%, proving the CFD model’s reliability. This supports its application in the design and optimization of Mars rotorcraft systems, enhancing their flight control through accurate prediction of aerodynamic hinge moments across various pitch angles and speeds.

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Aerodynamic Hinge Moment Characteristics of Pitch-Regulated Mechanism for Mars Rotorcraft: Investigation and Experiments

Meng,

Hu,

Wei

et al. 2024

Drones

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The precise regulation of the hinge moment and pitch angle driven by the pitch-regulated mechanism is crucial for modulating thrust requirements and ensuring stable attitude control in Martian coaxial rotorcraft. Nonetheless, the aerodynamic hinge moment in rotorcraft presents time-dependent dynamic properties, posing significant challenges for accurate measurement and assessment for such characteristics. In this study, we delve into the detailed aerodynamic hinge moment characteristics associated with the pitch-regulated mechanism of Mars rotorcraft under a spectrum of control strategies. A robust computational fluid dynamics model was developed to simulate the rotor’s aerodynamic loads, accompanied by a quantitative hinge moment characterization that takes into account the effects of varying rotor speeds and pitch angles. Our investigation yielded a thorough understanding of the interplay between aerodynamic load behavior and rotor surface pressure distributions, leading to the creation of an empirical mapping model for hinge moments. To validate our findings, we engineered a specialized test apparatus capable of measuring the hinge moments of the pitch-regulated mechanism, facilitating empirical assessments under replicated atmospheric conditions of both Earth and Mars. The result indicates aerodynamic hinge moments depend nonlinearly on rotational speed, peaking at a 0° pitch angle and showing minimal sensitivity to pitch under 0°. Above 0°, hinge moments decrease, reaching a minimum at 15° before rising again. Simulation and experimental comparisons demonstrate that under Earth conditions, the aerodynamic performance and hinge moment errors are within 8.54% and 24.90%, respectively. For Mars conditions, errors remain below 11.62%, proving the CFD model’s reliability. This supports its application in the design and optimization of Mars rotorcraft systems, enhancing their flight control through the accurate prediction of aerodynamic hinge moments across various pitch angles and speeds.

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New methodology for flight control system sizing and hinge moment estimation

Cited by 3 publications

References 17 publications

Performance and Reliability Evaluation of Innovative High-Lift Devices for Aircraft Using Electromechanical Actuators

Performance and Reliability Evaluation of Innovative High-Lift Devices for Aircraft Using Electromechanical Actuators

Aerodynamic Hinge Moment Characteristics of Pitch Regulated Mechanism for Mars Rotorcraft: Investigation and Experiments

Aerodynamic Hinge Moment Characteristics of Pitch-Regulated Mechanism for Mars Rotorcraft: Investigation and Experiments

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