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Dr. Carlo E.D. Riboldi
Department of Aerospace Science and Technology, Politecnico di Milano, via La Masa 34, 20156 Milano, Italy

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Research Keywords & Expertise

0 Aircraft Design
0 Electric Aircraft
0 optimal design
0 Wind Turbine Control
0 Hybrid–electric aircraft

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Electric Aircraft
Hybrid–electric aircraft
optimal design
Aircraft Design
Wind Turbine Control

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Journal article
Published: 17 May 2021 in Aerospace
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Notwithstanding the interest in the three-surface concept shown by aircraft designers, this configuration was not thoroughly investigated in conjunction with the adoption of two-elevator surfaces, on both canard and tail. In fact, the inclusion of an additional elevator produces a redundant longitudinal control which can be specifically exploited to target trim optimization. The same redundancy can be also employed to improve the flying qualities of the three-surface aircraft. In this paper, after introducing a simple flight mechanics model, ideal for preliminary design and analyses, the advantages of this configuration are explored. Firstly, the problem of finding the elevator deflections of canard and tail for minimum drag in trim is formulated and solved. Secondarily, the updating of a two-surface back-tailed airplane into an equivalent three-surface one is demonstrated, showing the potential improvement in cruise performance. Finally, the controls are employed through a smart control law for achieving better flying qualities.

ACS Style

Stefano Cacciola; Carlo Riboldi; Matteo Arnoldi. Three-Surface Model with Redundant Longitudinal Control: Modeling, Trim Optimization and Control in a Preliminary Design Perspective. Aerospace 2021, 8, 139 .

AMA Style

Stefano Cacciola, Carlo Riboldi, Matteo Arnoldi. Three-Surface Model with Redundant Longitudinal Control: Modeling, Trim Optimization and Control in a Preliminary Design Perspective. Aerospace. 2021; 8 (5):139.

Chicago/Turabian Style

Stefano Cacciola; Carlo Riboldi; Matteo Arnoldi. 2021. "Three-Surface Model with Redundant Longitudinal Control: Modeling, Trim Optimization and Control in a Preliminary Design Perspective." Aerospace 8, no. 5: 139.

Journal article
Published: 03 February 2021 in Aerospace
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The adoption of hybrid-electric aircraft is expected to have a considerable impact on airport operations, with the need of new infrastructural requirements to support electric-powered fleets. In particular, battery-charging requirements shall play a decisive role. Preliminary investigations useful to perform scenario studies for the future implementation of electric-powered aviation can take advantage of the ARES methodology presented here, which provides the optimal solution to the sizing of airport battery recharging infrastructures. Based on the flight schedule and on the specifications of the aircraft fleet and the charging equipment, the solution assesses the number and type of charging points, the related electrical consumption in terms of energy and power, and further information needed to guarantee the required operational level while minimizing the procurement and operating costs. The method allows considering and comparing two charging strategies: plug-in recharge and battery swapping. Energy price variation in time is also taken into account and a full description of the optimal time scheduling of recharging operations is provided. Application studies to the reconfiguration of two existing aerodromes, a General Aviation airport and a large regional hub, are discussed, showing the potential of the proposed approach.

ACS Style

Lorenzo Trainelli; Francesco Salucci; Carlo Riboldi; Alberto Rolando; Federico Bigoni. Optimal Sizing and Operation of Airport Infrastructures in Support of Electric-Powered Aviation. Aerospace 2021, 8, 40 .

AMA Style

Lorenzo Trainelli, Francesco Salucci, Carlo Riboldi, Alberto Rolando, Federico Bigoni. Optimal Sizing and Operation of Airport Infrastructures in Support of Electric-Powered Aviation. Aerospace. 2021; 8 (2):40.

Chicago/Turabian Style

Lorenzo Trainelli; Francesco Salucci; Carlo Riboldi; Alberto Rolando; Federico Bigoni. 2021. "Optimal Sizing and Operation of Airport Infrastructures in Support of Electric-Powered Aviation." Aerospace 8, no. 2: 40.

Journal article
Published: 01 July 2020 in Journal of Aerospace Engineering
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A significant research effort in aviation is currently focused on the integration of electric or hybrid-electric power-trains onboard aircraft in an effort to improve efficiency and environmental friendliness. New designs incorporating these novel propulsion systems face the issue of penalizing battery characteristics, especially in terms of limited energy and power density performance, in turn imposing a toll on the inert weight of the machine. A possible solution to this issue is that of structural batteries. These are similar in structure to carbon fiber composites, where the matrix features dielectric characteristics, making the structure capable of storing electric energy while retaining the capability to withstand mechanical loads. The adoption of this technology, currently under advanced development, shall enable significant weight savings; yet it also raises relevant issues concerning aircraft sizing procedures that need to be conceived taking into account the specific characteristics of such multifunctional materials. This paper faces the new problem of aircraft initial design in presence of structural batteries. First, it presents a method for aircraft preliminary weight sizing, where the double effect of structural batteries on both structural mass and energy storage mass is considered. Subsequently, a procedure to size an airframe structure with the adoption of structural batteries in key components is shown, based on a weight-optimal approach. The complete sizing procedure is illustrated through an award-winning test case in the General Aviation category.

ACS Style

Carlo E.D. Riboldi; Lorenzo Trainelli; Fabio Biondani. Structural Batteries in Aviation: A Preliminary Sizing Methodology. Journal of Aerospace Engineering 2020, 33, 04020031 .

AMA Style

Carlo E.D. Riboldi, Lorenzo Trainelli, Fabio Biondani. Structural Batteries in Aviation: A Preliminary Sizing Methodology. Journal of Aerospace Engineering. 2020; 33 (4):04020031.

Chicago/Turabian Style

Carlo E.D. Riboldi; Lorenzo Trainelli; Fabio Biondani. 2020. "Structural Batteries in Aviation: A Preliminary Sizing Methodology." Journal of Aerospace Engineering 33, no. 4: 04020031.

Erratum
Published: 16 April 2020 in Aerospace Science and Technology
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ACS Style

Carlo E.D. Riboldi. Erratum to “Energy-optimal off-design power management for hybrid-electric aircraft” [Aerosp. Sci. Technol. 95 (2019) 105507]. Aerospace Science and Technology 2020, 101, 105833 .

AMA Style

Carlo E.D. Riboldi. Erratum to “Energy-optimal off-design power management for hybrid-electric aircraft” [Aerosp. Sci. Technol. 95 (2019) 105507]. Aerospace Science and Technology. 2020; 101 ():105833.

Chicago/Turabian Style

Carlo E.D. Riboldi. 2020. "Erratum to “Energy-optimal off-design power management for hybrid-electric aircraft” [Aerosp. Sci. Technol. 95 (2019) 105507]." Aerospace Science and Technology 101, no. : 105833.

Journal article
Published: 13 April 2020 in Noise Mapping
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In the quest for the reduction of noise pollution, novel hybrid-electric or fully-electric power-trains promise to provide a substantial contribution. Especially closer to airfields, where acceptability issues tend to limit air operations with conventional fuel-burning engines, such novel power-trains allow to fly terminal maneuvers with a dramatically reduced impact on pollution. Considering the General Aviation (GA) field, where such new types of propulsion are more likely to gain a significant market share thanks to their favorable characteristics for this weight category, the reduction of the noise impact on ground may increase the infrastructural value of smaller airfields, often located in densely populated areas. This in turn would help in making novel power-train technologies economically advantageous at a system level. Despite these evident advantages, a methodology to quantify noise emissions of a novel type of power-train has not been identified yet – a fundamental step towards the assessment of the potential contribution of hybrid-electric or fully-electric aircraft to the global scenario of future aviation. This work introduces and discusses a possible procedure to provide such estimation. While mainly focused on the field of propeller-driven GA aircraft, the procedure presented herein can be easily scaled to cope with the specific features of heavier categories.

ACS Style

Carlo E.D. Riboldi; Lorenzo Trainelli; Luca Mariani; Alberto Rolando; Francesco Salucci. Predicting the effect of electric and hybrid-electric aviation on acoustic pollution. Noise Mapping 2020, 7, 35 -56.

AMA Style

Carlo E.D. Riboldi, Lorenzo Trainelli, Luca Mariani, Alberto Rolando, Francesco Salucci. Predicting the effect of electric and hybrid-electric aviation on acoustic pollution. Noise Mapping. 2020; 7 (1):35-56.

Chicago/Turabian Style

Carlo E.D. Riboldi; Lorenzo Trainelli; Luca Mariani; Alberto Rolando; Francesco Salucci. 2020. "Predicting the effect of electric and hybrid-electric aviation on acoustic pollution." Noise Mapping 7, no. 1: 35-56.

Journal article
Published: 24 October 2019 in Aerospace Science and Technology
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Among the advantages associated with the adoption of hybrid-electric power-trains in aviation is the greater flexibility that this type of propulsion system offers. This results in the ability to fly an assigned mission profile making suitable use of both the electric and fuel-burning power components, based on a power management strategy targeting diverse alternative specific needs, like for instance reduced energy consumption or lower noise emission. However, the greater flexibility of a hybrid-electric power-train comes together with an increased complexity in its design and operation. Integrated design procedures for hybrid-electric aircraft have been the target of previous works, whereas the present paper focuses on the quantification of the off-design characteristics of an already defined hybrid-electric design. To this aim, the power management strategy is considered as configurable. The problem of how to balance electric and mechanical power, accounting for the limited energy availability on board while coping with generic mission requirements, is investigated. In order to smartly obtain the desired strategy, the paper introduces an optimal approach, capable of reducing energy expenditure by properly setting the throttle of the fuel-burning and electric components, in coordination with the amount of battery recharging power. The method is explained with a rigorous mathematical approach, and thoroughly tested on a realistic test-bed.

ACS Style

Carlo E.D. Riboldi. Energy-optimal off-design power management for hybrid-electric aircraft. Aerospace Science and Technology 2019, 95, 105507 .

AMA Style

Carlo E.D. Riboldi. Energy-optimal off-design power management for hybrid-electric aircraft. Aerospace Science and Technology. 2019; 95 ():105507.

Chicago/Turabian Style

Carlo E.D. Riboldi. 2019. "Energy-optimal off-design power management for hybrid-electric aircraft." Aerospace Science and Technology 95, no. : 105507.

Journal article
Published: 30 July 2018 in Aerospace Science and Technology
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Hybrid-electric propulsion is an interesting alternative for the light aviation market, carrying the advantages of electric propulsion in terms of lower noise and pollutive emissions in terminal maneuvers, while not renouncing to the flight performance – especially range – typical to conventional propulsion, based on hydrocarbon fuel. Some difficulty in the spreading of this new technology in light aviation may be ascribed to the lack of consolidated techniques to preliminary design hybrid-electric aircraft, complicating the negotiation of specifications and making design choices difficult. This is also the effect of a notable increase in the number of design variables needed to describe the hybrid-electric power-train, which include characteristics of both its thermal and electric parts, with respect to conventionally powered aircraft. The present paper presents a methodology to efficiently cope with this design problem. The procedure is based on an optimal approach where take-off weight is minimized, and constraints are included to assure meeting the mission performance requirements while not exceeding any technological limit. The paper recalls at first some simple mathematical models, allowing to translate flight performance requirements into constraints on the power-train. Then the proposed optimal design approach is thoroughly presented at a theoretical level. Finally, an example design of a hybrid-electric motor-glider is shown, where the optimal design tool is used both to find a baseline solution and to investigate the sensitivity of that design point with respect to constraints due to performance requirements and technological specifications.

ACS Style

Carlo E.D. Riboldi. An optimal approach to the preliminary design of small hybrid-electric aircraft. Aerospace Science and Technology 2018, 81, 14 -31.

AMA Style

Carlo E.D. Riboldi. An optimal approach to the preliminary design of small hybrid-electric aircraft. Aerospace Science and Technology. 2018; 81 ():14-31.

Chicago/Turabian Style

Carlo E.D. Riboldi. 2018. "An optimal approach to the preliminary design of small hybrid-electric aircraft." Aerospace Science and Technology 81, no. : 14-31.

Conference paper
Published: 18 June 2018 in Journal of Physics: Conference Series
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A typical concern in rotating systems is related to rotor imbalances, which result typically from pitch misalignment and unbalanced mass distribution. A novel control for simultaneously targeting mass and pitch imbalances on the rotor is presented. Additionally, a novel detection strategy is developed in order to detect the imbalance source out of the behavior of the control action. More in depth, since the control will generate an artificial aerodynamic imbalance which compensates the pre-existent aerodynamic and inertial ones, one can find and interpret the fingerprint of the imbalance source in the behavior of the balancing controller. A clear advantage of this approach is that the imbalance detection is performed while the control keeps the machine working within its operating limits reducing the down-time and unscheduled maintenance actions.

ACS Style

S. Cacciola; C.E.D. Riboldi; A. Croce. Monitoring rotor aerodynamic and mass imbalances through a self-balancing control. Journal of Physics: Conference Series 2018, 1037, 032041 .

AMA Style

S. Cacciola, C.E.D. Riboldi, A. Croce. Monitoring rotor aerodynamic and mass imbalances through a self-balancing control. Journal of Physics: Conference Series. 2018; 1037 (3):032041.

Chicago/Turabian Style

S. Cacciola; C.E.D. Riboldi; A. Croce. 2018. "Monitoring rotor aerodynamic and mass imbalances through a self-balancing control." Journal of Physics: Conference Series 1037, no. 3: 032041.

Conference paper
Published: 18 June 2018 in Journal of Physics: Conference Series
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ACS Style

A. Croce; S. Cacciola; Carlo Emanuele Dionigi Riboldi; L. Sartori. The Science of Making Torque from Wind (TORQUE 2018). Journal of Physics: Conference Series 2018, 1037, 011001 .

AMA Style

A. Croce, S. Cacciola, Carlo Emanuele Dionigi Riboldi, L. Sartori. The Science of Making Torque from Wind (TORQUE 2018). Journal of Physics: Conference Series. 2018; 1037 (1):011001.

Chicago/Turabian Style

A. Croce; S. Cacciola; Carlo Emanuele Dionigi Riboldi; L. Sartori. 2018. "The Science of Making Torque from Wind (TORQUE 2018)." Journal of Physics: Conference Series 1037, no. 1: 011001.

Journal article
Published: 01 January 2018 in Transportation Research Procedia
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The lack of consolidated preliminary design techniques coping with the characteristics of most recent electric and hybrid-electric power plants is often an obstacle for aircraft manufacturers and for owners and operators as well, making the design process less straightforward and hampering comparisons with respect to more traditional designs. In this paper, a technique for the preliminary weight sizing of electric aircraft in the General Aviation category is explained. This is based on existing procedures typical to conventionally-powered aircraft, integrated in a common framework to suitably tackle the issues raised by the peculiar features of electrically-powered aircraft. Then, an expansion of the design method to the case of a series hybrid propulsion system is investigated. Results in virtual environment on a realistic design are also presented.

ACS Style

Carlo E.D. Riboldi; Federico Gualdoni; Lorenzo Trainelli. Preliminary weight sizing of light pure-electric and hybrid-electric aircraft. Transportation Research Procedia 2018, 29, 376 -389.

AMA Style

Carlo E.D. Riboldi, Federico Gualdoni, Lorenzo Trainelli. Preliminary weight sizing of light pure-electric and hybrid-electric aircraft. Transportation Research Procedia. 2018; 29 ():376-389.

Chicago/Turabian Style

Carlo E.D. Riboldi; Federico Gualdoni; Lorenzo Trainelli. 2018. "Preliminary weight sizing of light pure-electric and hybrid-electric aircraft." Transportation Research Procedia 29, no. : 376-389.

Journal article
Published: 28 September 2017 in Journal of Solar Energy Engineering
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Control algorithms for rotor load mitigation are today generally adopted by industry. Most of them are based on the Coleman transformation, which is easy to implement and bears satisfactory results when the rotor is balanced. A multitude of causes, e.g., blade erosion, dirt, and especially pitch misalignment, may create significant imbalances. This gives birth to undesirable vibrations and reduced control performance in terms of load mitigation. In this paper, an alternative transformation is introduced, able to detect and quantify the rotor load harmonics due to aerodynamic imbalance. Next, a control algorithm, capable of targeting rotor imbalance itself and simultaneously lowering rotor loads, is presented. The effectiveness of the proposed solution is confirmed through simulations in virtual environment.

ACS Style

Stefano Cacciola; Carlo E.D. Riboldi. Equalizing Aerodynamic Blade Loads Through Individual Pitch Control Via Multiblade Multilag Transformation. Journal of Solar Energy Engineering 2017, 139, 061008 .

AMA Style

Stefano Cacciola, Carlo E.D. Riboldi. Equalizing Aerodynamic Blade Loads Through Individual Pitch Control Via Multiblade Multilag Transformation. Journal of Solar Energy Engineering. 2017; 139 (6):061008.

Chicago/Turabian Style

Stefano Cacciola; Carlo E.D. Riboldi. 2017. "Equalizing Aerodynamic Blade Loads Through Individual Pitch Control Via Multiblade Multilag Transformation." Journal of Solar Energy Engineering 139, no. 6: 061008.

Research article
Published: 15 September 2017 in Wind Energy
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Two‐bladed wind turbines have regained the attention of the community thanks to the advantages in manufacturing cost provided by the lower number of blades and the ease of implementation of effective passive systems for load reduction (ie, teetering pin). Considering both teetering and nonteetering architectures, the dynamics of 2‐bladed turbines is different from that of 3‐bladed machines especially in terms of how multiples of the rotor frequencies in blade signals are translated on the fixed system. Such characteristics have hampered the adoption of active control laws for load mitigation based on individual pitch control, extensively studied for 3‐bladed turbines. A basic element for control development allowing to capture the essence of the relationship between signals on the blades and the fixed system on 2‐bladed turbines–represented by the Coleman transformation for 3‐bladed turbines–has not been identified yet. The present paper tries to fill the gap, presenting an extended transformation–called multiblade multilag–applicable to turbines with an arbitrary number of blades, providing a systematic way to link rotor signals to fixed system signals, thus allowing the application of control algorithms for individual pitch control developed for 3‐bladed turbines to the 2‐bladed case. The paper addresses the problem first at a theoretical level, and subsequently providing applicative results from simulations on virtual models of teetering and nonteetering 2‐bladed turbines. The proposed transformation algorithm and control laws allow to effectively reduce some relevant loads and motions respectively in the nonteetering and teetering scenarios, through a cyclic pitch input.

ACS Style

C. E. D. Riboldi; S. Cacciola. Individual pitch control for 2-bladed wind turbines via multiblade multilag transformation. Wind Energy 2017, 20, 1955 -1969.

AMA Style

C. E. D. Riboldi, S. Cacciola. Individual pitch control for 2-bladed wind turbines via multiblade multilag transformation. Wind Energy. 2017; 20 (12):1955-1969.

Chicago/Turabian Style

C. E. D. Riboldi; S. Cacciola. 2017. "Individual pitch control for 2-bladed wind turbines via multiblade multilag transformation." Wind Energy 20, no. 12: 1955-1969.

Journal article
Published: 01 July 2017 in IFAC-PapersOnLine
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ACS Style

Stefano Cacciola; Carlo E.D. Riboldi; Alessandro Croce. A New Decentralized Pitch Control Scheme for Wind Turbines * *Paper prepared for IFAC open invited session: Wind turbine and wind farm control: Control challenges and solutions. IFAC-PapersOnLine 2017, 50, 9908 -9913.

AMA Style

Stefano Cacciola, Carlo E.D. Riboldi, Alessandro Croce. A New Decentralized Pitch Control Scheme for Wind Turbines * *Paper prepared for IFAC open invited session: Wind turbine and wind farm control: Control challenges and solutions. IFAC-PapersOnLine. 2017; 50 (1):9908-9913.

Chicago/Turabian Style

Stefano Cacciola; Carlo E.D. Riboldi; Alessandro Croce. 2017. "A New Decentralized Pitch Control Scheme for Wind Turbines * *Paper prepared for IFAC open invited session: Wind turbine and wind farm control: Control challenges and solutions." IFAC-PapersOnLine 50, no. 1: 9908-9913.

Journal article
Published: 01 December 2016 in Wind Energy Science
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This paper investigates the load alleviation capabilities of an articulated tip device, where the outermost portion of the blade can rotate with respect to the rest of the blade. Passive, semi-passive and active solutions are developed for the tip rotation. In the passive and semi-passive configurations tip pitching is mainly driven by aerodynamic loads, while for the active case the rotation is obtained with an actuator commanded by a feedback control law. Each configuration is analyzed and tested using a high-fidelity aeroservoelastic simulation environment, by considering standard operative conditions as well as fault situations. The potential benefits of the proposed blade tip concepts are discussed in terms of performance and robustness.

ACS Style

Carlo L. Bottasso; Alessandro Croce; Federico Gualdoni; Pierluigi Montinari; Carlo Emanuele Dionigi Riboldi. Articulated blade tip devices for load alleviation on wind turbines. Wind Energy Science 2016, 1, 297 -310.

AMA Style

Carlo L. Bottasso, Alessandro Croce, Federico Gualdoni, Pierluigi Montinari, Carlo Emanuele Dionigi Riboldi. Articulated blade tip devices for load alleviation on wind turbines. Wind Energy Science. 2016; 1 (2):297-310.

Chicago/Turabian Style

Carlo L. Bottasso; Alessandro Croce; Federico Gualdoni; Pierluigi Montinari; Carlo Emanuele Dionigi Riboldi. 2016. "Articulated blade tip devices for load alleviation on wind turbines." Wind Energy Science 1, no. 2: 297-310.

Journal article
Published: 01 November 2016 in Aerospace Science and Technology
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Electric propulsion has received attention in aviation as witnessed by studies in hybrid designs and by the production of aircraft with support electric motors to be used in limited parts of the mission with ancillary roles. Until the recent past, the main limit to a wider adoption of electric propulsion, which besides having a lower environmental impact with respect to internal combustion engines (ICE) in terms of noise and emissions, can also improve reliability and on-board comfort, was the need for mass and volume-inefficient battery packs as devices for energy storage. However, thanks to the level of technology now reached by batteries, it is becoming possible to design and build electrically propelled aircraft at least in the category of light or general aviation. Due to the relative novelty of this technology, only few examples of similar aircraft exist today, mainly modifications of more traditional concepts, and thinking of a completely new electric aircraft is made difficult by the lack of a consolidated design framework, differently from the case of traditional ICE-powered models. This paper tries to cope with some basic aspects typical to electrically propelled aircraft, to the aim of setting up a stable and reliable preliminary sizing procedure allowing designers and aircraft companies to quickly size up and compare all-electric designs. To this aim, a statistical analysis of the basic characteristics of existing aircraft is presented first, showing a good correlation level between some of them. Next a method for the preliminary sizing of weights is shown, obtained starting from a more usual step-by-step procedure typically adopted for ICE-propelled aircraft. Due to the peculiar characteristics of electrically powered aircraft, the new procedure involves an integrated use of the case-specific mission profile and sizing matrix. The validity of the proposed procedure is testified by example analyses on two realistic designs of lightweight aircraft.

ACS Style

C.E.D. Riboldi; F. Gualdoni. An integrated approach to the preliminary weight sizing of small electric aircraft. Aerospace Science and Technology 2016, 58, 134 -149.

AMA Style

C.E.D. Riboldi, F. Gualdoni. An integrated approach to the preliminary weight sizing of small electric aircraft. Aerospace Science and Technology. 2016; 58 ():134-149.

Chicago/Turabian Style

C.E.D. Riboldi; F. Gualdoni. 2016. "An integrated approach to the preliminary weight sizing of small electric aircraft." Aerospace Science and Technology 58, no. : 134-149.

Conference paper
Published: 30 September 2016 in Journal of Physics: Conference Series
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This paper describes tuning concepts for passive devices aimed at load alleviation in wind turbines. Two types of tuning are considered: inertial and aerodynamic. The first concept is illustrated with reference to a passive flap, while the second with reference to a passive tip. In both cases, the goal is to reduce loads with devices that are as simple as possible, and do not require sensors nor actuators. The main features and critical issues of each concept are highlighted and illustrated with reference to a large conceptual 10 MW wind turbine.

ACS Style

A Croce; F Gualdoni; P Montinari; Carlo Emanuele Dionigi Riboldi; C L Bottasso. Inertial and aerodynamic tuning of passive devices for load alleviation on wind turbines. Journal of Physics: Conference Series 2016, 753, 102005 .

AMA Style

A Croce, F Gualdoni, P Montinari, Carlo Emanuele Dionigi Riboldi, C L Bottasso. Inertial and aerodynamic tuning of passive devices for load alleviation on wind turbines. Journal of Physics: Conference Series. 2016; 753 (10):102005.

Chicago/Turabian Style

A Croce; F Gualdoni; P Montinari; Carlo Emanuele Dionigi Riboldi; C L Bottasso. 2016. "Inertial and aerodynamic tuning of passive devices for load alleviation on wind turbines." Journal of Physics: Conference Series 753, no. 10: 102005.

Journal article
Published: 08 June 2016 in Wind Engineering
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Individual pitch control has proved capable of reducing loads on the blades and shaft of a horizontal-axis wind turbine, at the price of a potentially substantial increase in actuator activity. With accurate tuning of the control parameters, the overall performance can be satisfactorily balanced, but a manual tuning procedure often proves unbearably costly and the solution found may be far from optimal. This study tries to explore the feasibility of an optimal approach to the problem of tuning of individual pitch control, by mapping reasonable cost functions with respect to some parameters of interest in control design. The analysis is carried out by considering a possible individual pitch control implementation, tested in a virtual environment on a realistic testbed. The merit functions are also analyzed visually, in order to easily understand the effects of the various design parameters on the positions and quality of the respective optima. In a later stage, results of complete optimization runs are presented, and the approach is critically discussed.

ACS Style

Carlo Ed Riboldi. On the optimal tuning of individual pitch control for horizontal-axis wind turbines. Wind Engineering 2016, 40, 398 -416.

AMA Style

Carlo Ed Riboldi. On the optimal tuning of individual pitch control for horizontal-axis wind turbines. Wind Engineering. 2016; 40 (4):398-416.

Chicago/Turabian Style

Carlo Ed Riboldi. 2016. "On the optimal tuning of individual pitch control for horizontal-axis wind turbines." Wind Engineering 40, no. 4: 398-416.

Journal article
Published: 25 January 2016 in Noise Mapping
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The present contribution aims at providing a comprehensive illustration of a new approach to rotorcraft noise abatement, especially during terminal procedures, when the vehicle approaches the ground and the acoustic impact is higher. This approach pursues the development of technologies and tools for real-time, in-flight monitoring of the emitted noise. The effect of the acoustic radiation is presented to the pilot in a condensed, practical form on a new cockpit instrumentation, the Pilot Acoustic Indicator (PAI), to be used for performing quieter maneuvers. The PAI is based on the synergetic composition of pre-calculated acoustic data, which are used in a noise estimation algorithm together with the data gathered by an innovative contactless measurement system, capable of acquiring the main rotor blade motion. The paper reports on the current studies in unsteady and quasi-steady aeroacoustic prediction and tip-path-plane angle of attack and thrust coefficient observation. Results on novel methodologies are discussed, together with the main features of the PAI design and development process.

ACS Style

Lorenzo Trainelli; Massimo Gennaretti; Giovanni Bernardini; Alberto Rolando; Carlo E. D. Riboldi; Matteo Redaelli; Luca Riviello; Alessandro Scandroglio. Innovative Helicopter In-Flight Noise Monitoring Systems Enabled by Rotor-State Measurements. Noise Mapping 2016, 3, 1 .

AMA Style

Lorenzo Trainelli, Massimo Gennaretti, Giovanni Bernardini, Alberto Rolando, Carlo E. D. Riboldi, Matteo Redaelli, Luca Riviello, Alessandro Scandroglio. Innovative Helicopter In-Flight Noise Monitoring Systems Enabled by Rotor-State Measurements. Noise Mapping. 2016; 3 (1):1.

Chicago/Turabian Style

Lorenzo Trainelli; Massimo Gennaretti; Giovanni Bernardini; Alberto Rolando; Carlo E. D. Riboldi; Matteo Redaelli; Luca Riviello; Alessandro Scandroglio. 2016. "Innovative Helicopter In-Flight Noise Monitoring Systems Enabled by Rotor-State Measurements." Noise Mapping 3, no. 1: 1.

Journal article
Published: 01 February 2015 in Renewable Energy
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ACS Style

Carlo Luigi Bottasso; C.E.D. Riboldi. Validation of a wind misalignment observer using field test data. Renewable Energy 2015, 74, 298 -306.

AMA Style

Carlo Luigi Bottasso, C.E.D. Riboldi. Validation of a wind misalignment observer using field test data. Renewable Energy. 2015; 74 ():298-306.

Chicago/Turabian Style

Carlo Luigi Bottasso; C.E.D. Riboldi. 2015. "Validation of a wind misalignment observer using field test data." Renewable Energy 74, no. : 298-306.

Journal article
Published: 19 June 2014 in Renewable Energy
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We consider LiDAR-enabled model-based collective pitch and torque controllers that can be implemented onboard a wind turbine in a hard real-time environment, in the sense that they can be computed efficiently on standard computer hardware and that require a fixed deterministic number of operations at each call. At first, we show that linear parameter varying wind-scheduled models provide for a reasonable approximation (for control purposes) of the wind turbine response over its entire operating regime. Based on these results, we formulate two model predictive controllers making use of such wind-scheduled linear models and a quadratic cost. The first controller is based on a classical constrained receding horizon approach that leads to the efficient on-line solution of a quadratic problem. The second can be interpreted as its steady-state unconstrained approximation; its implementation is straightforward and leads to the off-line computation of gain matrices that are then wind-scheduled at run time. Both controllers are tested in a high fidelity environment comprising of both a LiDAR and an aeroservoelastic simulator, in deterministic and unfrozen turbulent wind conditions. The numerical experiments show that the receding horizon controller outperforms a standard non-LiDAR-enabled one, as expected and as already reported by other authors. More interestingly, the second simpler controller is shown to provide for an almost similar performance of the more sophisticated one, although at a much lower and trivial computational cost. This behavior is interpreted as being due to the fact that, given the high disturbance level and the frequent solution update, even a rough approximation of the control problem is still capable of capturing the essence of the LiDAR preview information.

ACS Style

C.L. Bottasso; P. Pizzinelli; C.E.D. Riboldi; L. Tasca. LiDAR-enabled model predictive control of wind turbines with real-time capabilities. Renewable Energy 2014, 71, 442 -452.

AMA Style

C.L. Bottasso, P. Pizzinelli, C.E.D. Riboldi, L. Tasca. LiDAR-enabled model predictive control of wind turbines with real-time capabilities. Renewable Energy. 2014; 71 ():442-452.

Chicago/Turabian Style

C.L. Bottasso; P. Pizzinelli; C.E.D. Riboldi; L. Tasca. 2014. "LiDAR-enabled model predictive control of wind turbines with real-time capabilities." Renewable Energy 71, no. : 442-452.